B
AEROPLANE OPERATING MANUAL
TRANSMITTAL LETTER
REVISION 18
This package contains Revision 18 to the Dash 8 Series 400 Aeroplane Operating Manual (AOM),
PSM 1-84-1, DOT METRIC dated November 21, 2016.
To bring your manual up to date, refer to each Chapter's List of Effective Pages. Remove the old chapters,
pages or Temporary Revisions (TRs) as indicated below.
Please retain this letter for record purposes and insert it in the front of the manual.
No TRs have been issued or incorporated in Revision 18.
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Chapter 00
Section
Page(s)
Chapter 00
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Page(s)
00 LEP
1
00 LEP
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Chapter 01
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Chapter 01
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Page(s)
01 LEP
1
01 LEP
1
Chapter 02
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Chapter 02
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02 LEP
1-2
02 LEP
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2.4
1-2
2.4
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2.15
3-16
2.15
3-14
2.17
3-4
2.17
3-4
2.17
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2.17
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2.17
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2.17
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2.17
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2.17
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2.17
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2.17
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PSM 1-84-1 - DOT - METRIC
Effectivity: **ALL
Transmittal Letter
Page 1
Nov 21/2016
B
AEROPLANE OPERATING MANUAL
REMOVE
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Chapter 03
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Chapter 03
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03 LEP
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ToC 3
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ToC 3
3-4
3.1
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3.1
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3.1
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3.1
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3.1
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3.1
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6.6
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6.6
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ToC 6.7
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ToC 6.7
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6.7
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6.7
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6.7
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6.7
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PSM 1-84-1 - DOT - METRIC
Effectivity: **ALL
Transmittal Letter
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Nov 21/2016
BOMBARDIER
Series 400
AEROPLANE OPERATING MANUAL
PSM 1-84-1
BOMBARDIER INC.
BOMBARDIER AEROSPACE COMMERCIAL AIRCRAFT
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AEROPLANE OPERATING MANUAL
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INTRO - 1
INTRODUCTION
[Rev. 16] 7 MAR 2016
ORGANIZATION OF THE MANUAL
GENERAL
This Aeroplane Operating Manual (AOM) has been prepared by Bombardier Aerospace Regional Aircraft.
It is provided for the guidance of pilots when operating the DHC 8-Q400 Series airplanes.
It is in the responsibility of pilots who are qualified to operate this airplane to be entirely familiar with the information contained in this publication to ensure that the airplane is operated at all times within the approved flight
envelope.
NOTE:
It is the operator’s responsibility to keep the manual in a current status.
For clarity and simplicity, this manual is written in the imperative, in order that the information and operating
instructions may be presented in a positive sense and require no interpretation by the user.
Specific items requiring emphasis are expanded upon and ranked in increasing order of importance in the form
of a NOTE, CAUTION or WARNING.
NOTE:
Expands on information which has already been provided.
CAUTION: Provides information to prevent misuse of systems which could directly affect their
function or serviceability.
WARNING: Emphasizes information of immediate flight safety importance.
Bombardier Aerospace, Regional Aircraft publications use both metric and imperial systems of measurement.
The system used in the original reference document is given first, followed by the conversion in parentheses.
If the data or procedures written in this manual are different from those given by the regulatory authority (which
controls operation of the airplane), obey the data and procedures of the regulatory authority.
NOTE:
The information in this manual applies only to the Dash 8-Q400 airplanes.
The AOM consists of 4 Volumes (6 Chapters) as follows:
Volume 1 – Chapters 0 to 3
Volume 2 – Chapters 4 and 5
Volume 3 – Chapters 6.1 to 6.12
Volume 4 – Chapters 6.13 to 6.29
Each Volume is identified by the title page only.
Each Chapter is identified by the list of effective pages (LEP) and a table of content (ToC).
In the event of a disagreement the AFM is relevant.
CONTENTS
The AOM provides flight crews with necessary information concerning the airplane systems, limitations, procedures and performance data. The system described may differ from the actual customized airplane.
Chapters are divided into Sub-Chapters and Subjects.
Tab dividers showing chapter titles and numbers are provided for prompt identification.
Procedures and checklists reflect Bombardier Aerospace Flight Operations Department philosophy.
PAGE IDENTIFICATION
Each manual page presents airplane series, manual designation and chapter title and number.
Page identification consists of the Chapter, Sub-Chapter, Page number, Revision status and Date of effectivity.
Arrangement of Page identification (sample):
0.0-1
= [Chapter] . [Sub-Chapter] - [Page Number]
[Rev. X] 31 MAY 2011= Revision Number and Date of last issue
A normal Blank Page within a page block is identified with the phrase:
AOM DASH 8-Q400
THIS PAGE
INTENTIONALLY
LEFT
BLANK
INTRO - 2
INTRODUCTION
[Rev. 16] 7 MAR 2016
TABLES and DRAWINGS
Tables and drawings are identified by their titles and numbers.
Table numbers and titles are displayed at the top.
Figure numbers and titles at the bottom of the respective illustration.
MANUAL UP-DATING
LIST OF EFFECTIVE PAGES (LEP)
The LEP enables the user to determine that the manual is up-to-date, with all revisions incorporated and all
deleted pages removed.
The contents of this AOM must at all times comply with the contents as given by the LEP.
REVISION
Revisions will be distributed whenever necessary.
The revision date is shown on the revised page, even if there is only one page affected by the revision.
Revised text (added or deleted material) and / or illustrations are indicated by a vertical black line along the
outside margin of the column or page.
Changes in capitalization, spelling, punctuation or the physical location of material on a page will not be identified by a symbol.
RECORD OF REVISIONS (RoR)
The record of revisions contains revision date, date inserted and incorporator’s initials.
Revisions are issued on the assumption that previous revisions have been incorporated.
TEMPORARY REVISIONS (TR)
Sometimes it may be necessary to supply the operator with information which has not yet been processed fully.
A Temporary Revision will then be issued on a subscription basis.
It will be printed on yellow paper to distinguish these from normal revisions.
The Temporary Revisions are not incorporated in the LEP.
Every Temporary Revision has a follow-up; either a normal revision or a notice stating that the Temporary Revision has been cancelled.
RECORD OF TEMPORARY REVISIONS (RoTR)
The Record of Temporary Revisions enables recording of the successive temporary revision numbers, page
numbers and issue dates, with additional columns for date inserted, date removed and incorporator’s /
remover’s initials.
The replacement page will be issued only after the available entry space has been used.
OBTAINING REVISIONS
The user has to check the pages in the manual for approval date to be the same as shown in the LEP for that
page.
If any page is missing or shows an incorrect approval date, the user has to apply for replacements to:
BOMBARDIER INC.
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT
CUSTOMER SUPPORT
123 GARRATT BLVD., DOWNSVIEW, ONTARIO
CANADA M3K 1Y5
AOM DASH 8-Q400
ACRONYMS - 1
ACRONYMS
[Rev. 16] 7 MAR 2016
-AAC ......................................................................................................................................... Alternating Current
AC ............................................................................................................................................. Air Conditioning
AC ................................................................................................................................. Advisory Circular (FAA)
AC, A/C ................................................................................................................................................... Aircraft
ACARS ................................................................... Aircraft Communication Addressing and Reporting System
ACAS ....................................................................................................... Airborne Collision Avoidance System
ACCB ............................................................................................................ Alternating Current Contactor Box
ACM ....................................................................................................................................... Air Cycle Machine
ACN ..................................................................................................................... Aircraft Classification Number
ACOC ................................................................................................................................ Air Cooled Oil Cooler
ACP ..................................................................................................................................... Audio Control Panel
ACS .......................................................................................................................... Aircraft Cabin System (PA)
ACT ....................................................................................................................................................... Actuator
ACU ................................................................................................................................... Advisory Control Unit
A/COL ............................................................................................................................................ Anti-Collision
ADC ........................................................................................................................................ Air Data Compute
ADF .......................................................................................................................... Automatic Direction Finder
ADI .............................................................................................................................. Attitude Director Indicator
ADPT ...................................................................................................................................................... Adapter
ADS ........................................................................................................................................... Air Data System
ADU ................................................................................................................................................ Air Data Unit
ADVSY .................................................................................................................................................. Advisory
AEC ............................................................................................................... Abnormal & Emergency Checklist
AEO .................................................................................................................................. All Engines Operative
AES ......................................................................................................................... Audible Evacuation System
A/F .................................................................................................................................................... Autofeather
AF ....................................................................................................................................................... Auto Flight
AFCS ............................................................................................................... Automatic Flight Control System
AFM ................................................................................................................................... Aircraft Flight Manual
AGB .................................................................................................................................... Accessory Gear Box
AGL .................................................................................................................................... Above Ground Level
AH ......................................................................................................................................... Attendant Handset
AHCP ........................................................................................ Attitude and Heading Reference Control Panel
AHRS .................................................................................................. Attitude and Heading Reference System
AHRU ....................................................................................................... Attitude and Heading Reference Unit
AIC ......................................................................................................................... Anti-lce Controller (WSHLD)
AIL .............................................................................................................................................................Aileron
AIM .................................................................................................................. Aeronautical Information Manual
AIP ............................................................................................................ Aeronautical Information Publication
AIS .................................................................................................................. Aeronautical Information System
AIS .............................................................................................................................. Audio Integration System
ALP ................................................................................................................................. Attendant Light Panels
ALT ......................................................................................................................................... Altitude / Altimeter
ALT ....................................................................................................................................................... Alternate
AMLCD ........................................................................................................ Active Matrix Liquid Crystal Display
ANVCS ......................................................................................................... Active Noise and Vibration Control
AOA ............................................................................................................................................ Angle Of Attack
AP, A/P .................................................................................................................................................. Autopilot
AP AU ............................................................................................................................. Autopilot Actuator Unit
AOM DASH 8-Q400
ACRONYMS - 2
ACRONYMS
[Rev. 16] 7 MAR 2016
APD ........................................................................................................ Advanced Pneumatic Detectors (Fire)
APPOS .............................................................................. Automatic Presentation Passenger Oxygen System
APPR ................................................................................................................................................... Approach
APU .................................................................................................................................... Auxiliary Power Unit
ARCDU .................................................................................................... Audio and Radio Control Display Unit
ARMS .................................................................................................... Audio and Radio Management System
ART ................................................................................................................... Antenna, Receiver, Transmitter
ARTE .......................................................................................................... Above Runway Threshold Elevation
AS........................................................................................................................................ Aerospace Standard
ASCU ................................................................................................................................ Anti Skid Control Unit
ASDA ........................................................................................................... Accelerate Stop Distance Available
ASDR ........................................................................................................... Accelerate Stop Distance Required
ASI ........................................................................................................................................ Air Speed Indicator
ASL .......................................................................................................................................... Above Sea Level
ATA ............................................................................................................................. Air Transport Association
ATC .......................................................................................................................................... Air Traffic Control
ATCRBS ............................................................................................. Air Traffic Control Radio Beacon System
ATPCS .............................................................................................. Automatic Take-off Power Control System
ATT .......................................................................................................................................................... Attitude
ATTCS .............................................................................................. Automatic Take-off Thrust Control System
ATVA ............................................................................................................ Active Tuned Vibration Attenuators
AUPC ................................................................................................. Automatic Underspeed Protection Circuit
AUTO .................................................................................................................................................. Automatic
AUX ....................................................................................................................................................... Auxiliary
AWS ............................................................................................................................ Audible Warning System
-BBA ................................................................................................................................... Bombardier Aerospace
BAG ...................................................................................................................................................... Baggage
BAR .................................................................................................................................................... Barometric
BAS ......................................................................................................................................... Bleed Air System
BAT, BATT ............................................................................................................................................... Battery
BAZ ................................................................................................................................... Back Course Azimuth
BFO ........................................................................................................................... Beat Frequency Oscillator
BFT .......................................................................................................................... Beta Feedback Transducer
BITE ............................................................................................................................... Built-In Test Equipment
BlT .................................................................................................................................................... Built-In Test
BTL ............................................................................................................................................................. Bottle
-C°C ............................................................................................................................................... Degrees Celsius
CAB ............................................................................................................................................................ Cabin
CAS ..................................................................................................................................... Calibrated Airspeed
CAT ........................................................................................................................................................Category
CAT ......................................................................................................................................Clear Air Turbulence
CAUT ....................................................................................................................................................... Caution
CB .................................................................................................................................................Circuit Breaker
CDL ......................................................................................................................... Configuration Deviation List
CDS .......................................................................................................................... Central Diagnostic System
CDU ..................................................................................................................................... Control Display Unit
CFIT ....................................................................................................................... Controlled Flight Into Terrain
AOM DASH 8-Q400
ACRONYMS - 3
ACRONYMS
[Rev. 16] 7 MAR 2016
CG ............................................................................................................................................ Centre of Gravity
CL ..................................................................................................................................................... Centre Line
CL ............................................................................................................................................... Condition Lever
CLA ................................................................................................................................. Condition Lever Angle
clsd ........................................................................................................................................................... Closed
cm ................................................................................................................................................. Centimetre(s)
CM ..................................................................................................................................... Configuration Module
CNTRL, CONT, CTRL ............................................................................................................................. Control
COM, COMM ............................................................................................................................. Communication
COMP ........................................................................................................................................... Compartment
CONF ............................................................................................................................................ Configuration
CPC ................................................................................................................... Cabin Pressurization Controller
CPCS ....................................................................................................... Cabin Pressurization Control System
CR ......................................................................................................................................... Customer Request
CSI .......................................................................................................... Commonwealth of Independent States
CSMU ................................................................................................................. Crash Survivable Memory Unit
CVMSS ................................................................................. Cabin Video Monitoring and Surveillance System
CVR ............................................................................................................................... Cockpit Voice Recorder
-Dd ............................................................................................................................................................... Day(s)
DADC ......................................................................................................................... Digital Air Data Computer
DADS ............................................................................................................................... Dual Air Data System
dB ........................................................................................................................................................ Decibel(s)
DC ................................................................................................................................................ Direct Current
DCCB .................................................................................................................... Direct Current Contactor Box
DCMP ....................................................................................................................... Direct Current Motor Pump
DDO .................................................................................................................................... Drop Down Oxygen
DECR .................................................................................................................................................. Decrease
DET ...................................................................................................................................................... Detection
DG ............................................................................................................................................. Directional Gyro
DH .............................................................................................................................................. Decision Height
DIFF ................................................................................................................................................... Differential
DISC ........................................................................................................................................................ Discing
DISC .................................................................................................................................................. Disconnect
DISENG ............................................................................................................................................. Disengage
DME ............................................................................................................. Distance Measurement Equipment
DN .............................................................................................................................................................. Down
DOT ............................................................................................................. Department Of Transport (Canada)
DTG ............................................................................................................................................ Distance To Go
DU .................................................................................................................................................... Display Unit
-EEADI ......................................................................................................... Electronic Attitude Direction Indicator
EAS ..................................................................................................................................... Equivalent Airspeed
EASA ............................................................................................................. European Aviation Safety Agency
ECIU .................................................................................................................... Engine Controls Interface Unit
ECS .................................................................................................................... Environmental Control System
ECTM .......................................................................................................... Engine Condition Trend Monitoring
ECU ................................................................................................................................. Electronic Control Unit
ED ............................................................................................................................................... Engine Display
AOM DASH 8-Q400
ACRONYMS - 4
ACRONYMS
[Rev. 16] 7 MAR 2016
EDP ................................................................................................................................... Engine Driven Pump
EED ............................................................................................................................. Electro Explosive Device
EFCP ........................................................................... Electronic Flight Instrumentation System Control Panel
EFIS .................................................................................................... Electronic Flight Instrumentation System
EGPWS ...................................................................................... Enhanced Ground Proximity Warning System
EGT ........................................................................................................................... Exhaust Gas Temperature
EHSI ..................................................................................................... Electronic Horizontal Situation Indicator
EHSV ............................................................................................ Electro-Hydraulic Servo Valve (NWS, Flaps)
EHV ................................................................................................................ Electro-Hydraulic Valve (Rudder)
EIS ........................................................................................................................ Electronic Instrument System
EL ......................................................................................................................................................... Elevation
ELEV ..................................................................................................................................................... Elevator
ELT ................................................................................................................... Emergency Locator Transmitter
EMER, EMERG ................................................................................................................................. Emergency
EMI ...................................................................................................................... Electro-Magnetic Interference
EMS ...................................................................................................................... Engine Management System
EMU ................................................................................................................................ Engine Monitoring Unit
ENG ......................................................................................................................................................... Engine
EPCU ..................................................................................................................... Electrical Power Control Unit
EPGDS ............................................................................ Electrical Power Generation and Distribution System
EPNdB .............................................................................................................. Effective Perceived Noise Level
EPS .............................................................................................................. External Protection System (NAV)
ESCP ............................................................................. Engine and System Integrated Displays Control Panel
ESID .................................................................................................... Engine and System Integrated Displays
ETOPS ................................................................................................................... Extended Operations (FAA)
ETOPS ................................................................................... Extended Range Twin-Engine Operations (JAA)
EXT ........................................................................................................................................................ External
EXTG ............................................................................................................................................... Extinguisher
-FFA, F/A ....................................................................................................................................... Flight Attendant
FAA .................................................................................................................... Federal Aviation Administration
FADEC ..................................................................................... Full Authority Digital Engine / Electronic Control
FAK ................................................................................................................................................... First Aid Kit
FC, FLT COMP .................................................................................................................... Flight Compartment
FCECU ..................................................................................................... Flight Control Electronic Control Unit
FCS .................................................................................................................................. Flight Control System
FCSOV ................................................................................................................ Flow Control & Shut-Off Valve
FCU ......................................................................................................................................... Flap Control Unit
FD ................................................................................................................................................. Flight Director
FDIR ........................................................................................... Fault Detection, Isolation and Reconfiguration
FDP .................................................................................................................................. Flight Data Processor
FDPS ................................................................................................................. Flight Data Processing System
FDR ................................................................................................................................... Flight Data Recorder
FF, F/F ................................................................................................................................................. Fuel Flow
FGC .......................................................................................................................... Flight Guidance Computer
FGCP .................................................................................................................. Flight Guidance Control Panel
FGM .............................................................................................................................. Flight Guidance Module
Fl .......................................................................................................................................................... Flight Idle
FL ..................................................................................................................................................... Flight Level
AOM DASH 8-Q400
ACRONYMS - 5
ACRONYMS
[Rev. 16] 7 MAR 2016
FLT ............................................................................................................................................................. Flight
FLTR ........................................................................................................................................................... Filter
FMA .............................................................................................................................. Flight Mode Annunciator
FMC .................................................................................................................... Flight Management Computer
FMCW ........................................................................................................ Frequency Modulated Carrier Wave
FMS ......................................................................................................................... Flight Management System
FMU ...................................................................................................................................... Fuel Metering Unit
FOHE ........................................................................................................................... Fuel Oil Heat Exchanger
FP ....................................................................................................................................................... Flight Plan
FPIU ....................................................................................................................... Flap Position Indication Unit
FPU ........................................................................................................................................... Flap Power Unit
FQC ................................................................................................................................Fuel Quantity Computer
FS ............................................................................................................................................. Fuselage Station
ft ......................................................................................................................................................... Foot / Feet
ft3 ............................................................................................................................................. Cubic Foot / Feet
ft/min .......................................................................................................................................... Feet per Minute
FTHR ...................................................................................................................................................... Feather
FWD ....................................................................................................................................................... Forward
FWSOV ......................................................................................................................... Fire Wall Shut-Off Valve
-Gg, G ................................................................................................... Gravitational Acceleration / Gravity Force
g ............................................................................................................................................................. Gram(s)
gal ........................................................................................................................................................ Gallon(s)
gal/min ................................................................................................................................ Gallon(s) per Minute
GA ..................................................................................................................................................... Go Around
GBS ................................................................................................................................. Ground Based System
GCU ................................................................................................................................ Generator Control Unit
GEN .................................................................................................................................................... Generator
GMT ................................................................................................................................ Greenwich Mean Time
GND ........................................................................................................................................................ Ground
GPS ........................................................................................................................... Global Positioning System
GPU ..................................................................................................................................... Ground Power Unit
GPWC ...................................................................................................... Ground Proximity Warning Computer
GPWS .......................................................................................................... Ground Proximity Warning System
GPWSC ....................................................................................... Ground Proximity Warning System Converter
G/S ..................................................................................................................................................... Glideslope
GS ................................................................................................................................................ Ground Speed
GSE............................................................................................................................ Ground Speed Equipment
-Hh .............................................................................................................................................................. Hour(s)
HBOV .......................................................................................................................... Handling Bleed-Off Valve
HDG ...................................................................................................................................................... Heading
HF COMM ...................................................................................................... High Frequency Communications
HIRF ...................................................................................................................... High Intensity Radiated Field
Hg ........................................................................................................................................................... Mercury
HML .................................................................................................................. Hinge Moment Limiter (Rudder)
HOT .............................................................................................................................................. Holdover Time
HP ................................................................................................................................................ High Pressure
hPa ............................................................................................................................................. Hectopascal(s)
AOM DASH 8-Q400
ACRONYMS - 6
ACRONYMS
[Rev. 16] 7 MAR 2016
HPSOV ................................................................................................................. High Pressure Shut-Off Valve
HRD ................................................................................................................................... High Rate Discharge
HS ..................................................................................................................................................... High Speed
HSC ...................................................................................................................................... High Speed Cruise
HSI ........................................................................................................................ Horizontal Situation Indicator
HSM ........................................................................................................................................ High Speed Mode
HT ................................................................................................................................................................ Heat
HTCS .................................................................................................. Hydraulic Torque Compensation System
HTR .......................................................................................................................................................... Heater
HYD ..................................................................................................................................................... Hydraulic
Hz ............................................................................................................................................................... Hertz
-IIAS ....................................................................................................................................... Indicated Air Speed
IBIT ..................................................................................................................................... Initiated Built-ln Test
IBV .................................................................................................................................. Interstage Bleed Valve
ICAO ..................................................................................................... International Civil Aviation Organization
ICP ....................................................................................................................................... Index Control Panel
ID .................................................................................................................................................... Identification
IDP ........................................................................................................................................ Ice Detector Probe
IDS .................................................................................................................................... Ice Detection System
I/F ......................................................................................................................................................... Interface
IFC ............................................................................................................................... Integrated Flight Cabinet
IFE .................................................................................................................................. In-Flight Entertainment
IFR ................................................................................................................................. Instrument Flight Rules
ILS ........................................................................................................................... Instrument Landing System
in ............................................................................................................................................................ Inch(es)
INBD ....................................................................................................................................................... Inboard
INCR ...................................................................................................................................................... Increase
IND ........................................................................................................................................................ Indicator
INOP .................................................................................................................................................. Inoperative
INVLD ....................................................................................................................................................... Invalid
I/O .................................................................................................................................................. Input / Output
IOM ................................................................................................................................... Input / Output Module
IOP ............................................................................................................................... Input / Output Processor
IRPS ................................................................................................................. Ice and Rain Protection System
ISA ............................................................................................................... International Standard Atmosphere
ISC ............................................................................................................................ Intermediate Speed Cruise
ISI ....................................................................................................................... Integrated Standby Instrument
ISO ........................................................................................................................................................... Isolate
ISOL ...................................................................................................................................................... Isolation
ITT ...................................................................................................................... Indicated Turbine Temperature
ITV .......................................................................................................................... Interturbine Vane Assembly
IVSI .................................................................................................................... Inertial Vertical Speed Indicator
-JJAA ..................................................................................................................... Joint Airworthiness Authorities
JAR ................................................................................................................... Joint Airworthiness Regulations
AOM DASH 8-Q400
ACRONYMS - 7
ACRONYMS
[Rev. 16] 7 MAR 2016
-K°K ............................................................................................................................................... Degrees Kelvin
KCAS .................................................................................................................... Calibrated Airspeed in Knots
kg ..................................................................................................................................................... Kilogram(s)
kg/h ................................................................................................................................... Kilogram(s) per Hour
kHz ........................................................................................................................................................ Kilohertz
KIAS ........................................................................................................................ Indicated Airspeed in Knots
km ................................................................................................................................................... Kilometre(s)
kt ............................................................................................................................................................. Knot(s)
KTAS .............................................................................................................................. True Airspeed in Knots
kVA ....................................................................................................................................... Kilo Volt Ampere(s)
-LL .................................................................................................................................................................... Left
L ............................................................................................................................................................... Litre(s)
LAV ........................................................................................................................................................ Lavatory
lb .......................................................................................................................................................... Pound(s)
lb/h ........................................................................................................................................ Pound(s) per Hour
LCD .................................................................................................................................. Liquid Crystal Display
LCN ......................................................................................................................... Load Classification Number
LDA .......................................................................................................................... Landing Distance Available
LDG ........................................................................................................................................................ Landing
LDG INOP ................................................................................................................... Landing Gear Inoperable
LDR ......................................................................................................................... Landing Distance Required
LED ..................................................................................................................................... Light Emitting Diode
LEZ ............................................................................................................................. Leading Edge Zone (Fire)
LFSS .................................................................................................................... Landing Flap Selector Switch
LG, L/G .......................................................................................................................................... Landing Gear
LHS ............................................................................................................................................. Left Hand Side
LMWW .............................................................................................................................. Left Main Wheel Well
LNAV ...................................................................................................................................... Lateral Navigation
LOC ...................................................................................................................................................... Localizer
LOUT........................................................................................................ Lowest Operational Use Temperature
LP .................................................................................................................................................. Low Pressure
LRC ...................................................................................................................................... Long Range Cruise
LRD .................................................................................................................................... Low Rate Discharge
LRU .................................................................................................................................. Line Replaceable Unit
LS ......................................................................................................................................................... Left Seat
LSM ......................................................................................................................................... Low Speed Mode
L/V ........................................................................................................................................ Language / Volume
LVDT ................................................................................................ Linear Variable Displacement Transformer
LWD .......................................................................................................................................... Left Wing Down
-Mm ........................................................................................................................................................... Metre(s)
M ................................................................................................................................................................ Mass
MAC .......................................................................................................................... Mean Aerodynamic Chord
MAN ........................................................................................................................................................ Manual
MAP ............................................................................................................................... Missed Approach Point
MAT .......................................................................................................................... Mass Altitude Temperature
MAX .................................................................................................................................................... Maximum
AOM DASH 8-Q400
ACRONYMS - 8
ACRONYMS
[Rev. 16] 7 MAR 2016
MB .............................................................................................................................................. Marker Beacon
MCL ............................................................................................................................... Maximum Climb Power
MCP ...................................................................................................................... Maximum Continuous Power
MCR ............................................................................................................................ Manual Change Request
MCR ............................................................................................................................. Maximum Cruise Rating
MDP .................................................................................................................................. Master Display Panel
MDU ............................................................................................................................... Magnetic Detector Unit
ME .................................................................................................................................... Maximum Endurance
MEA ......................................................................................................................... Minimum En-Route Altitude
MFD ................................................................................................................................. Multi-Function Display
MIC ................................................................................................................................................... Microphone
min ....................................................................................................................................................... Minute(s)
MIN ....................................................................................................................................................... Minimum
MLG ...................................................................................................................................... Main Landing Gear
MLS ........................................................................................................................ Microwave Landing System
MLW .......................................................................................................................... Maximum Landing Weight
mm ................................................................................................................................................... Millimetre(s)
MMEL .............................................................................................................. Master Minimum Equipment List
MON ....................................................................................................................................................... Monitor
MORA ..................................................................................................................... Minimum Off-Route Altitude
MOT .................................................................................................................................. Main Oil Temperature
MPU ................................................................................................................................. Magnetic Pick-Up Unit
MS ................................................................................................................................... Modification Summary
MTOM .......................................................................................................................... Maximum Take-Off Mass
MTOP ........................................................................................................................ Maximum Take-Off Power
MTOW ...................................................................................................................... Maximum Take-Off Weight
MUH .................................................................................................................................. Minimum Use Height
MWW ....................................................................................................................................... Main Wheel Well
-N# .............................................................................................................................................................. Number
N ......................................................................................................................................................... Newton(s)
NACA ........................................................................................... National Advisory Committee for Aeronautics
NAV ................................................................................................................................................... Navigation
NCD ................................................................................................................................... Non-Computed Data
ND ......................................................................................................................................... Navigation Display
ND .................................................................................................................................................... Nose Down
NFCSOV ............................................................................................. Nacelle Flow Control and Shut-Off Valve
NH ................................................................................................................ High Pressure Rotor Speed (RPM)
NL ................................................................................................................. Low Pressure Rotor Speed (RPM)
NLG ..................................................................................................................................... Nose Landing Gear
NM .............................................................................................................................................. Nautical Mile(s)
NM/kg ................................................................................................................... Nautical Mile(s) per Kilogram
NM/lb ........................................................................................................................ Nautical Mile(s) per Pound
NP .................................................................................................................................. Propeller Speed (RPM)
NPT ........................................................................................................................ Power Turbine Speed (RPM)
NORM ...................................................................................................................................................... Normal
NOTAM ........................................................................................................................ Notice To Airmen (ICAO)
NSOV ............................................................................................................................. Nacelle Shut-Off Valve
NTOP ............................................................................................................................. Normal Take-Off Power
AOM DASH 8-Q400
ACRONYMS - 9
ACRONYMS
[Rev. 16] 7 MAR 2016
NU ......................................................................................................................................................... Nose Up
NVM .................................................................................................................................. Non-Volatile Memory
-OOAT .............................................................................................................................. Outside Air Temperature
OEI ................................................................................................................................ One Engine Inoperative
OFP ................................................................................................................................ Operational Flight Plan
OH ....................................................................................................................................................... Overhead
OPN ........................................................................................................................................................... Open
O/RID ..................................................................................................................................................... Override
O/S .................................................................................................................................................... Overspeed
OSG .................................................................................................................................. Overspeed Governor
OTP ...................................................................................................................... Online Technical Publications
OUTBD ................................................................................................................................................. Outboard
-PPa ........................................................................................................................................................ Pascal(s)
PA .................................................................................................................................................. Public Adress
PA ............................................................................................................................................ Pressure Altitude
PAA ...................................................................................................................... Passenger Address Amplifier
PACIS .................................................................................. Passenger Address and Cabin Interphone System
PAX .................................................................................................................................................... Passenger
PBE .................................................................................................................. Protective Breathing Equipment
PCN ................................................................................................................. Pavement Classification Number
PCU ......................................................................................................................................... Pitch Control Unit
PCU .......................................................................................................... Power Control Units (HYD Actuators)
PEC ..................................................................................................................... Propeller Electronic Controller
PES ............................................................................................................... Passenger Entertainment System
PEZ ................................................................................................................................... Primary Engine Zone
PF ....................................................................................................................................................... Pilot Flying
PFCS ..................................................................................................................Powered Flight Control Surface
PFCSI .................................................................................................. Powered Flight Control Surface Indicator
PFD .................................................................................................................................. Primary Flight Display
PG ............................................................................................................................................ Propylene Glycol
PIC .......................................................................................................................................... Pilot In Command
PK BRK .............................................................................................................................................. Park Brake
PL .....................................................................................................................................................Power Lever
PLA ....................................................................................................................................... Power Lever Angle
PLT ................................................................................................................................................................Pilot
PM ............................................................................................................................................... Pilot Monitoring
PMA ................................................................................................................... Permanent Magnet Alternators
PN .................................................................................................................................................. Part Number
PNF ............................................................................................................................................ Pilot Non-Flying
POSN ..................................................................................................................................................... Position
POST ................................................................................................................................... Power On Self Test
PPSM ........................................................................................................ Primary Power Supply Module (IFC)
PPU ................................................................................................................................... Power Protection Unit
PRESS .................................................................................................................................................. Pressure
PRI .......................................................................................................................................................... Primary
PROP .................................................................................................................................................... Propeller
PSA .................................................................................................................. Permanent System Area (MFD)
AOM DASH 8-Q400
ACRONYMS - 10
ACRONYMS
[Rev. 16] 7 MAR 2016
PSC .............................................................................................................................. Proximity Sensor Circuit
PSEU ............................................................................................................... Proximity Sensor Electronic Unit
psi ..................................................................................................................................Pounds per Square Inch
psia .................................................................................................................Pounds per Square Inch Absolute
psid ............................................................................................................. Pounds per Square Inch Differential
psig ................................................................................................................... Pounds per Square Inch Gauge
PSM .............................................................................................................................. Product Support Manual
PSU ............................................................................................................................... Passenger Service Unit
PT ................................................................................................................................................ Power Turbine
PTT ................................................................................................................................................. Push To Talk
PTU ..................................................................................................................................... Power Transfer Unit
PWC ............................................................................................................................. Pratt & Whitney Canada
PWR ......................................................................................................................................................... Power
-Qqt ............................................................................................................................................................ Quart(s)
QRH ........................................................................................................................ Quick Reference Handbook
QTY ....................................................................................................................................................... Quantity
-RR ................................................................................................................................................................. Right
RA ............................................................................................................................................... Radio Altimeter
RA ........................................................................................................................... Resolution Advisory (TCAS)
RCAU ....................................................................................................................... Remote Control Audio Unit
RCOMM ............................................................................................................................ Radio Communication
RDI ............................................................................................................................... Refuel / Defuel Indicator
RDP .................................................................................................................................. Refuel / Defuel Panel
REC ..........................................................................................................................................................Record
RECIRC ...........................................................................................................................................Recirculation
RF ............................................................................................................................................. Radio Frequency
RGB ..................................................................................................................................... Reduction Gearbox
RHS .......................................................................................................................................... Right Hand Side
RMI ............................................................................................................................ Radio Magnetic Integrator
RMS .................................................................................................................................... Root Mean Squared
RMWW ........................................................................................................................... Right Main Wheel Well
RNAV ....................................................................................................................................... Radio Navigation
ROC .............................................................................................................................................. Rate Of Climb
ROD ............................................................................................................................................ Rate Of Decent
RPM ............................................................................................................................... Revolutions Per Minute
RS ....................................................................................................................................................... Right Seat
RTD ....................................................................................................... Resistance Temperature Device (Fuel)
RUD ......................................................................................................................................................... Rudder
RV ............................................................................................................................. Relief / Dump Valve (HYD)
RVDT ......................................................................... Rotary Variable Differential Transformers (nose steering)
RWD ........................................................................................................................................ Right Wing Down
RWY ....................................................................................................................................................... Runway
-Ss .......................................................................................................................................................... Second(s)
SAE ................................................................................................................ Society of Automotive Engineers
SAT .................................................................................................................................. Static Air Temperature
AOM DASH 8-Q400
ACRONYMS - 11
ACRONYMS
[Rev. 16] 7 MAR 2016
SC/A ............................................................................................................................... Senior Cabin Attendant
SCU .................................................................................................................................... Steering Control Unit
SD .............................................................................................................................................. System Display
SEC .................................................................................................................................................... Secondary
SEL ........................................................................................................................................................... Select
SHP ....................................................................................................................................... Shaft Horse Power
SID .................................................................................................................... Standard Instrument Departure
SL, S/L ................................................................................................................................................ Sea Level
SLS .................................................................................................................................. Screen Line Selection
SM ................................................................................................................................................ Statute Mile(s)
SNOWTAM ...................................................................................... Snow Conditions Notice To Airmen (ICAO)
SOV .............................................................................................................................................. Shut-Off Valve
SPEC .............................................................................................................................................. Specification
SPI ............................................................................................................................. Special Purpose Identifier
SPLR ........................................................................................................................................................ Spoiler
SPM .............................................................................................................................. Stall Protection Module
SPS ................................................................................................................................ Stall Protection System
SPU ..................................................................................................................................... Standby Power Unit
SSCVR ........................................................................................................ Solid State Cockpit Voice Recorder
SSEC ........................................................................................................... Static Source Error Compensation
SSFDR ............................................................................................................. Solid State Flight Data Recorder
STAR ........................................................................................................................... Standard Terminal Arrival
STBY, SBY ............................................................................................................................................. Standby
SU ............................................................................................................................................... Service Unit(s)
SYST ....................................................................................................................................................... System
-Tt .................................................................................................................................................. Metric Tonne(s)
T ..................................................................................................................................... Temperature (°C or °K)
TA .................................................................................................................................. Temporary Amendment
TA .................................................................................................................................. Traffic Advisory (TCAS)
TAD .......................................................................................................................... Terrain Awareness Display
TAS .............................................................................................................................................. True Airspeed
TAT .................................................................................................................................... True Air Temperature
TC .......................................................................................................................................... Transport Canada
TCAS ............................................................................................ Traffic Alert and Collision Avoidance System
TCF ............................................................................................................................... Terrain Clearance Floor
TCS ................................................................................................................................ Tactile Control Steering
TDR ................................................................................................... Time Delay Relay (# 3 STBY HYD Pump)
TEMP .............................................................................................................................................. Temperature
THR ..................................................................................................................................................... Threshold
TMCU .......................................................................................... Timer and Monitor Control Unit (Prop De-ice)
TMR ........................................................................................................................................................... Timer
TO, T/O ................................................................................................................................................. Take-Off
TODA ...................................................................................................................... Take-Off Distance Available
TODR ...................................................................................................................... Take-Off Distance Required
TOP ............................................................................................................................................ Take-Off Power
TORA ....................................................................................................................... Take-Off Runway Available
TORR ....................................................................................................................... Take-Off Runway Required
TPEDS ............................................................................................... Transmitting Portable Electronic Devices
AOM DASH 8-Q400
ACRONYMS - 12
ACRONYMS
[Rev. 16] 7 MAR 2016
TRANS .............................................................................................................................................. Transmitter
TRQ, TQ .................................................................................................................................................. Torque
TRSOV .................................................................................................. Temperature Reduction Shut-Off Valve
TRU .......................................................................................................................... Transformer Rectifier Units
TWY ........................................................................................................................................................ Taxiway
-UUL ........................................................................................................................................................... UniLink
ULB ....................................................................................................................... Underwater Locating Beacon
USA ............................................................................................................................. United States of America
UTC ........................................................................................................................ Universal Time Coordinated
-VV ................................................................................................................................................................ Volt(s)
V AC ............................................................................................................................... Volt(s) Alternate Curent
V DC .................................................................................................................................... Volt(s) Direct Curent
V1 ................................................................................................................................................ Decision Speed
V2 ..................................................................................................................................... Take-Off Safety Speed
VA ....................................................................................................................................... Maneuvering Speed
VAPP .......................................................................................................................................... Approach Speed
VEF ........................................................................................................................ Critical Engine Failure Speed
VERT ....................................................................................................................................................... Vertical
VFAC ..................................................................................................... Variable Frequency Alternating Current
VFE ................................................................................................................................... Flap Extended Speed
VFR .................................................................................................................................. Flap Retraction Speed
VFRI ................................................................................................................... Flap Retraction Initiation Speed
VFR ....................................................................................................................................... Visual Flight Rules
VFTO .................................................................................................................................. Final Take-Off Speed
VG .................................................................................................................................................. Vertical Gyro
VGA ......................................................................................................................................... Go Around Speed
VGO ............................................................................................. Lowest Decision Speed (Contaminated RWY)
VHF ................................................................................................................................... Very High Frequency
VLE ..................................................................................................................... Landing Gear Extended Speed
VLO .................................................................................................................... Landing Gear Operating Speed
VLOF .............................................................................................................................................. Lift-Off Speed
VLV ............................................................................................................................................................. Valve
VMCA ....................................................................................................................... Minimum Control Speed, Air
VMCG .............................................................................................................. Minimum Control Speed, Ground
VMCL ............................................................................................ Minimum Control Speed, Landing / Approach
VMO .......................................................................................................................... Maximum Operating Speed
VNAV ..................................................................................................................................... Vertical Navigation
Vol ........................................................................................................................................................... Volume
VOR ................................................................................. Very High Frequency Omni-Directional Radio Range
VOR/LOC ....................................................... Very High Frequency Omni-Directional Radio Range / Localizer
VR ............................................................................................................................................... Rotation Speed
VREF ........................................................................................................................................... Landing Speed
VS ................................................................................................................................................ Vertical Speed
VSI ................................................................................................................................. Vertical Speed Indicator
VSI ................................................................................................................................. Visual Service Indicator
VSR .................................................................................................................................. Reference Stall Speed
AOM DASH 8-Q400
ACRONYMS - 13
ACRONYMS
[Rev. 16] 7 MAR 2016
VSTOP ......................................................................................... Highest Decision Speed (Contaminated RWY)
-WW ............................................................................................................................................................. Watt(s)
W .............................................................................................................................................................. Weight
WARN .................................................................................................................................................... Warning
WAT ....................................................................................................................... Weight Altitude Temperature
WCP ........................................................................................................................ Warning and Caution Panel
WDO ...................................................................................................................................................... Window
WED .............................................................................................................................. Water Equivalent Depth
WL ...................................................................................................................................................... Water Line
WOW ..................................................................................................................................... Weight On Wheels
WR, WXR ................................................................................................................................... Weather Radar
WS .................................................................................................................................................. Wing Station
WSHLD ............................................................................................................................................. Windshield
WT ............................................................................................................................................................ Weight
WTG ............................................................................................................................. Warning Tone Generator
WTGS ........................................................................................................... Warning Tone Generation System
WX ........................................................................................................................................................ Weather
WXCP .................................................................................................................. Weather Radar Control Panel
-XXTK .................................................................................................................................................. Cross Track
XWIND ............................................................................................................................................... Crosswind
-YYD .................................................................................................................................................. Yaw Damper
YD AU ...................................................................................................................... Yaw Damper Actuator Unit
-ZZ ....................................................................................................................................................... Zulu (GMT)
ZFW ........................................................................................................................................ Zero Fuel Weight
ZB ......................................................................................................................................... Barometric Altitude
AOM DASH 8-Q400
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DEFINITIONS - 1
DEFINITIONS
[Rev. 16] 7 MAR 2016
IAS
Indicated Airspeed – airspeed reading corrected for instrument error.
Values in this manual assume zero instrument error.
CAS
Calibrated Airspeed – Indicated Airspeed corrected for position error.
EAS
Equivalent Airspeed – Calibrated Airspeed corrected for compressibility error.
TAS
True Airspeed = (EAS) / √σ
VMCA
Minimum Control Speed, Air – Minimum flight speed at which the airplane is controllable
with a maximum of 5° bank, when the critical engine suddenly becomes inoperative,
with the remaining engine at maximum take-off power.
VMCG
Minimum Control Speed, Ground – Minimum speed on the ground at which control can
be maintained and take-off continued using aerodynamic controls alone, when the critical engine suddenly becomes inoperative, with the remaining engine at maximum takeoff power.
V1
Take-off Decision Speed – Speed at which, due to engine failure or other causes, the
pilot may elect to stop or to continue take-off.
VR
Rotation Speed – Speed at which rotation is initiated during take-off to attain V2 at or
before a height of 35 ft above the runway.
V2
Take-off Safety Speed – Target climb speed to be attained at or before a height of 35 ft
above the runway during a continued take-off, following an engine failure.
VMCL
Minimum Control Speed, Landing / Approach – Minimum flight speed at which the airplane is controllable with a maximum of 5° bank, when the critical engine suddenly
becomes inoperative and with the remaining engine at maximum take-off power.
VREF
Landing / Approach Speed at a height 50 ft above the runway in the landing configuration
OAT
Outside Air Temperature (in flight SAT = OAT).
SAT
Static Air Temperature (in flight SAT = OAT).
σ
Density Ratio.
Take-off Distance
The Take-off Distance is the longer of:
a. 115% of the distance from the start of the take-off roll to the point at which the airplane attains a height of 35 ft above the take-off surface, with all engines operating.
b. For dry runway, the distance from the start of the take-off roll to the point where the
airplane attains a height of 35 ft above the take-off surface, with a critical engine failure such that the failure would be recognized at the decision speed V1.
c. For wet runway, the distance from the start of the take-off roll to the point where the
airplane attains a height of at least 15 ft above the take-off surface, with a critical
engine failure such that the failure would be recognized at the decision speed V1.
Take-off Run
The Take-off Run is the longer of:
a. 115% of the distance from the start of the take-off roll to the mid-point between lift-off
and the point at which the airplane attains a height of 35 ft above the take-off surface, with all engines operating.
b. For dry runway, the distance from the start of the take-off roll to the mid-point
between lift-off and the point at which the airplane attains a height of 35 ft above the
take-off surface, with a critical engine failure such that the failure would be recognized at the decision speed V1.
c. For wet runway, the distance from the start of the take-off roll to the point where the
airplane attains a height of at least 15 ft above the take-off surface, with a critical
engine failure such that the failure would be recognized at the decision speed V1.
Stopway
An area beyond the take-off runway at least as wide as the runway and centered upon
the extended centerline of the runway, able to support the airplane during an aborted
take-off, without causing structural damage to the airplane and designated by the airport authorities for use in decelerating the airplane during an aborted take-off.
AOM DASH 8-Q400
DEFINITIONS - 2
DEFINITIONS
[Rev. 16] 7 MAR 2016
Accelerate-Stop
Distance
The Accelerate-Stop Distance is the longer of a) and b) which are defined below:
a) Accelerate-Stop Distance with an engine failure at VEF as defined below:
1. The distance necessary to accelerate the airplane from a standing start to VEF
with all engines operating plus:
2. The distance required to accelerate the airplane from VEF to V1 and continue the
acceleration for a further 1 s, assuming the critical engine fails at VEF plus:
3. The distance required to come to a full stop from the point reached at the end of
the acceleration period prescribed in paragraph a)2. above, assuming that the
pilot does not apply any means of retarding the airplane until that point is reached
and that the critical engine is still inoperative plus:
4. A distance margin equal to 2 s at V1.
b) Accelerate-Stop Distance with all engines operating as defined below:
1. The distance necessary to accelerate the airplane from a standing start to V1 and
continue the acceleration for a further 1.0 s with all engines operating plus:
2. The distance required to come to a full stop from the point reached at the end of
the acceleration period prescribed in paragraph b)1. above, assuming that the
pilot does not apply any means of retarding the airplane until that point is reached
and that all engines are still operating plus:
3. A distance margin equal to 2 s at V1.
Clearway
An area beyond the runway, not less than 500 ft (152 m) wide, centrally located about
the extended centerline of the runway and under the control of the airport authorities.
The clearway is expressed in terms of a clearway plane, extending from the end of the
runway with an upward slope not exceeding 1.25%, above which no object nor any terrain protrudes.
However, threshold lights may protrude above the plane if their height above the end of
the runway is 26 in (66 cm) or less and if they are located to each side of the runway.
(the clearway in no instance may be more than one half the runway length as required
by the relevant operating regulation)
Wet Runway
A runway is considered as wet when there is sufficient moisture on the runway surface
to cause it to appear reflective, but without significant areas of standing water.
Take-off Field
Lengths on Wet
Runway
The Take-off Run required is equal to the Take-off Distance required.
Take-off Path
The Take-off Path begins from a standing start and ends at 1500 ft above the take-off
surface or at the point where transition from take-off to enroute configuration is completed, whichever is higher.
Take-off Flight Path
The Take-off Flight Path begins at the end of the take-off distance and at a height of 35
ft above the take-off surface and ends at 1500 ft above the take-off surface, or at the
point where transition from take-off to enroute configuration is completed, whichever is
higher.
Net Take-off Flight
Path
The Net Take-off Flight Path is the actual take-off flight path diminished by a gradient of
climb (or equivalent reduction in acceleration along that part of the take-off flight path at
which the airport is accelerated in level flight) of 0.8%.
Land Immediately
at the Nearest
Suitable Airport
Land at the Nearest Suitable Airport that offers sufficient runway Landing Distance
Available and if required, emergency services to support the emergency or abnormality.
Land at the
Nearest Suitable
Airport
The airplane may continue to the destination airport or the nearest airport where maintenance services are available.
Maintenance
Action Required
Prior to Next Flight
“Next Flight” is referring to the immediate or imminent Take-Off after discovery
AOM DASH 8-Q400
CHAPTER 0
LIST OF EFFECTIVE PAGES
00 - Effective Pages
1
21 Nov 2016
00 - Contents
ToC 0-1
30 Jan 2015
00 LEP - Page 1
(Rev 18) 21 NOV 2016
Chapter 0
0.0-1
31 May 2011
0.1-1
31 May 2011
0.1-2
31 May 2011
0.1-3
31 May 2011
0.2-1
31 May 2011
0.3-1
31 May 2011
0.4-1
31 May 2011
0.5-1
31 May 2011
0.5-2
31 May 2011
0.6-1
31 May 2011
0.6-2
31 May 2011
0.7-1
07 Mar 2016
AOM DASH 8-Q400
DOT
T H IS PA G E
INTE NTIONA LLY
L EF T
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
ToC 0-1
[Rev. 13] 30 JAN 2015
- TABLE OF CONTENTS -
0.0
GENERAL INFORMATION and UNITS OF MEASUREMENT .............................................. 0.0-1
0.0.1
General Information of Measurement used in the AOM ......................................................... 0.0-1
0.1
UNITS OF MEASUREMENT – CONVERSION TABLES ...................................................... 0.1-1
0.1.1
General Conversion Tables .................................................................................................... 0.1-1
0.1.2
Temperature - Conversion Tables ........................................................................................... 0.1-2
0.1.3
Calculation of ISA Temperature .............................................................................................. 0.1-3
0.1.4
Conversion of Climb / Descent Gradient ................................................................................ 0.1-3
0.2
DIMENSIONS OF DHC 8-Q400 SERIES ............................................................................... 0.2-1
0.3
PLAN VIEW DHC 8-Q400 SERIES ........................................................................................ 0.3-1
0.4
AIRCRAFT DOORS AND DIMENSIONS ............................................................................... 0.4-1
0.5
FUSELAGE CROSS SECTION ............................................................................................. 0.5-1
0.6
CONVERSION OF REPORTED WIND TO HEAD / TAILWIND AND CROSSWIND ............. 0.6-1
0.7
CERTIFICATED NOISE LEVELS .......................................................................................... 0.7-1
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0.0
GENERAL INFORMATION AND UNITS OF MEASUREMENT
0.0.1
General Information of Measurement used in the AOM
0.0-1
[Rev. X] 31 MAY 2011
If not otherwise indicated in this manual the following dimensional units are used:
Masses (metric)
kilogram or metric tons
Weights (imperial)
lb
Distance
- short
centimeters or meters (inches or feet - imperial)
- airway
NM
Altitude
feet
Flight Levels
feet/100
Torque
%
Fuel flow
kg per hour (lb per hour - imperial)
Fuel loads
kilogram (lb - imperial)
Brake energy
106 ft lbs
Pressure
psi
Speeds
knots
Vertical speeds
ft/min (fpm)
Temperature
degrees Celsius (o C)
Time
hours
minutes
seconds
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.1
UNITS OF MEASUREMENT – CONVERSION TABLES
0.1.1
General Conversion Table
LB into KG
KG into LB
INCHES into CENTIMETERS
FEET into METERS
METERS into FEET
NM into KM
lb
x 0.4536
kg
x 2.2045855 = lb
inches x 2.54
feet
x 0.3048
= kg
0.1-1
[Rev. X] 31 MAY 2011
M
A
S
S
E
S
= centimeters
= meters
metersx 3.2808
= feet
NM
x 1.852
= km
liters
x 0.796
= kg
liters
x 1.7547
= lb
D
I
S
T
A
N
C
E
S
LITERS into KG
(Jet A-1/15°C)
LITERS into LB
(Jet A-1/15°C)
US Gallons into LITERS
US Gallons x 3.7853= liters
KG into LITERS
kg
x 1.2565
= liters
lb
x 0.57
= liters
ft3
x 0.0283168 = m3
ft2
x 0.09290304 = m2
(Jet A-1/15°C)
V
O
L
U
M
E
S
LB into LITERS
(Jet A-1/15°C)
CU feet (ft3)
square feet (ft2)
AOM DASH 8-Q400
A
R
E
A
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.1-2
[Rev. X] 31 MAY 2011
0.1.2
°C
-60
-59
-58
-57
-56
-55
-54
-53
-52
-51
-50
-49
-48
-47
-46
-45
-44
-43
-42
-41
-40
-39
-38
-37
-36
-35
-34
-33
-32
-31
-30
-29
-28
-27
-26
-25
-24
-23
-22
-21
-20
Temperature – Conversion Tables
°F
-76
-74
-72
-70
-69
-67
-65
-63
-62
-60
-58
-56
-54
-52
-51
-49
-47
-45
-44
-42
-40.0
-38.2
-36.4
-34.6
-32.8
-31.0
-29.2
-27.4
-25.6
-23.8
-22.0
-20.2
-18.4
-16.6
-14.8
-13.0
-11.2
-9.4
-7.6
-5.8
-4.0
°C
-19
-18
-17
-16
-15
-14
-13
-12
-11
-10
-9
-8
-7
-6
-5
-4
-3
-2
-1
0
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
°F
-2.2
-0.4
1.4
3.2
5.0
6.8
8.6
10.4
12.2
14.0
15.8
17.6
19.4
21.2
23.0
24.8
26.6
28.4
30.2
32.0
33.8
35.6
37.4
39.2
41.0
42.8
44.6
46.4
48.2
50.0
51.8
53.6
55.4
57.2
59.0
60.8
62.6
64.4
66.2
68.0
69.8
°C → °F
°C
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
TEMPERATURE
°F
°F
71.6
140
73.4
138
75.2
136
77.0
134
78.8
132
80.6
130
82.4
128
84.2
126
86.0
124
87.8
122
89.6
120
91.4
118
93.2
116
95.0
114
96.8
112
98.6
110
100.4
108
102.2
106
104.0
104
105.8
102
107.6
100
109.4
98
111.2
96
113.0
94
114.8
92
116.6
90
1187.4
88
120.2
86
122.0
84
123.8
82
125.6
80
127.4
78
129.2
76
131.0
74
132.8
72
134.6
70
136.4
68
138.8
66
140.0
64
62
60
°C
60
58.8
57.7
56.7
55.6
54.4
53.3
52.2
51.1
50.0
48.8
47.8
46.7
45.6
44.4
43.3
42.2
41.1
40.0
38.9
37.8
36.7
35.6
34.4
33.3
32.2
31.1
30.0
28.9
27.8
26.7
25.6
24.4
23.3
22.2
21.1
20.0
18.9
17.8
16.7
15.6
°F
59
58
56
54
52
50
48
46
44
42
40
38
36
34
32
30
28
26
24
22
20
18
16
14
12
10
8
6
4
2
0
-2
-4
-6
-8
-10
-12
-14
-16
-18
-20
°C
15.0
14.4
13.3
12.2
11.1
10.0
8.9
7.8
6.7
5.6
4.4
3.3
2.2
1.1
0.0
-1.1
-2.2
-3.3
-4.4
-5.6
-6.7
-7.8
-8.9
-10.0
-11.1
-12.2
-13.3
-14.4
-15.6
-16.7
-17.8
-18.9
-20.0
-21.1
-22.2
-23.3
-24.44
-25.6
-26.7
-27.8
-28.9
°F
-22
-24
-26
-28
-30
-32
-34
-36
-38
-40
-42
-44
-46
-48
-50
-52
-54
-56
-58
-60
-62
-64
-66
-68
-70
-72
-74
-76
°C
-30
-31.1
-32.2
-33.3
-34.4
-35.6
-36.7
-37.8
-38.9
-40.0
-41.1
-42.2
-43.3
-44.4
-45.6
-46.7
-47.8
-48.9
-50.0
-51.1
-52.2
-53.3
-54.4
-55.6
-56.7
-57.8
-58.9
-60.0
°F → °C
AOM DASH 8-Q400
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.1.3
Calculation of ISA Temperature
Calculation of ISA temperature (rule of thumb):
15 - (feet/1000) x 2 + ISA temp in oC
or:
15 - (flight/10) x 2 + ISA temp in oC
0.1.4
Conversion of Climb/Descent Gradient
AOM DASH 8-Q400
0.1-3
[Rev. X] 31 MAY 2011
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.2
0.2-1
[Rev. X] 31 MAY 2011
DIMENSIONS OF DHC 8-Q400 SERIES
Wing Span
=
28.42 m (93 ft 3 in)
Fuselage Length
=
31.04 m (101 ft 10 in)
Total Length
=
32.83 m (107 ft 9 in)
Approx Total Height
=
8.34 m (27 ft 4 in)
Distance main wheels to nose wheel
=
13.94 m (45 ft 9 in)
Distance outer main wheel to outer main wheel
=
9.52 m (31 ft 9 in)
Propeller clearance from ground
= ~ 0.98 m (38.67 in)
Distance propeller tips to fuselage
=
1.10 m (43.31 in)
Propeller diameter
=
4.11 m (13 ft 6 in)
Height of wing tips above ground
= ~ 3.92 m (12 ft 10 in)
Fuselage width
=
2.69 m (106 in)
Height of cabin floor above ground
=
1.16 m (45.76 in)
• ground
=
2.03 m (80.0 in)
• max
=
2.51 m (99.0 in)
Cabin height
=
1.95 m (77.0 in)
Aisle width (standard)
=
0.51 m (20.0 in)
Interior fuselage width
AOM DASH 8-Q400
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.3
0.3-1
[Rev. X] 31 MAY 2011
PLAN VIEW DHC 8-Q400 SERIES
93ft 3in.
(28.42m)
30ft 5in.
(9.27m)
13ft 6in.
(4.11m)
25ft 8in.*
(7.81m)
12ft 10in.*
(3.92m)
38.67in.*
(98.22cm)
DIHEDRAL 2.5
o
43.31in.
(1.10m)
28ft 10in.
(8.80m)
NOTE
8ft 2in.
(2.48m)
*
Dimensions with respect to ground
reference line are approximate and
will vary with aeroplane configuration
and loading conditions.
12ft 4in.
(3.76m)
36ft 10in.
(11.22m)
10ft 9in.*
(3.28m)
27ft 4in.*
(8.34m)
45.94in.*
(1.17m)
48.98in.*
(1.24m)
GROUND
REFERENCE LINE
101ft 10in.
(31.04m)
107ft 9in.
(32.83m)
AOM DASH 8-Q400
60.85in.*
(1.55m)
60.83in.*
(1.55m)
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.4
AIRCRAFT DOORS AND DIMENSIONS
AOM DASH 8-Q400
0.4-1
[Rev. X] 31 MAY 2011
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CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.5
FUSELAGE CROSS SECTION
AOM DASH 8-Q400
0.5-1
[Rev. X] 31 MAY 2011
0.5-2
[Rev. X] 31 MAY 2011
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
FUSELAGE CROSS SECTION (NEXT GEN INTERIOR)
AOM DASH 8-Q400
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.6
0.6-1
[Rev. X] 31 MAY 2011
CONVERSION OF REPORTED WIND TO HEAD/TAILWIND AND CROSSWIND
AOM DASH 8-Q400
0.6-2
[Rev. X] 31 MAY 2011
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
CONVERSION OF REPORTED WIND TO HEAD/TAILWIND AND CROSSWIND (cont’d)
AOM DASH 8-Q400
CHAPTER 0
GENERAL INFORMATION AND
UNITS OF MEASUREMENT
0.7
0.7-1
[Rev. 16] 7 MAR 2016
CERTIFICATED NOISE LEVELS
Certificated noise levels at the following measurement points for the applicable Gross Mass / Weight version:
CERTIFICATED EFFECTIVE PERCEIVED NOISE LEVELS
GROSS MASS / WEIGHT
[EPNdB]
VERSION
FLYOVER
LATERAL
APPROACH
77.1
84.1
94.9
(Flap 5°)
(Flap 5°)
(Flap 15°)
78.0
84.0
94.8
(Flap 5°)
(Flap 5°)
(Flap 15°)
BASIC:
MTOW: 27987 kg (61700 lb)
MLW: 27442 kg (60500 lb)
INTERMEDIATE:
MTOW: 28998 kg (63930 lb)
MLW: 28009 kg (61750 lb)
HIGH:
MTOW: 29257 kg (64500 lb)
MLW: 28009 kg (61750 lb)
78.3
84.0
94.8
(Flap 5°)
(Flap 5°)
(Flap 15°)
78.6
84.0
94.8
(Flap 5°)
(Flap 5°)
(Flap 15°)
ENHANCED HIGH:
MTOW: 29574 kg (65200 lb)
MLW: 28123 kg (62000 lb)
For more detailed certificated noise levels information, see Sub-Section 5.1 of the AFM.
[with MS 4-459409 Incorporated] the certified noise levels at the following measurement points for the Basic
Gross Mass / Weight are as follows:
Aircraft
Configuration
BASIC
MTOW / MLW
Noise Limits
Measured Levels
Phase of Flight
[kg]
[lb]
[EPNdB]
[EPNdB]
FLYOVER
25991
57300
89.0
75.6
LATERAL
25991
57300
94.0
84.0
APPROACH
25991
57300
98.0
95.2
AOM DASH 8-Q400
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CHAPTER 1
LIST OF EFFECTIVE PAGES
01 LEP - Page 1
(Rev 18) 21 NOV 2016
01 - Effective Pages
1
21 Nov 2016
01 - Contents
ToC 1-1
30 Jun 2016
ToC 1-2
30 Sep 2014
Chapter 1
1.1-1
31 May 2011
1.2-1
31 May 2011
1.3-1
31 May 2011
1.4-1
31 May 2011
1.5-1
07 Mar 2016
1.5-2
07 Mar 2016
1.6-1
31 May 2011
1.7-1
31 May 2011
1.8-1
30 Jun 2016
1.8-2
30 Jun 2016
1.8-3
30 Jun 2016
1.9-1
30 Jun 2016
1.9-2
30 Jun 2016
1.10-1
31 May 2011
1.10-2
31 May 2011
1.10-3
31 May 2011
1.10-4
31 May 2011
1.10-5
31 May 2011
1.10-6
31 May 2011
1.10-7
31 May 2011
1.10-8
31 May 2011
1.11-1
31 May 2011
1.11-2
30 Jan 2015
1.11-3
30 Jan 2015
1.11-4
31 May 2011
1.11-5
05 Dec 2011
1.11-6
13 Sep 2013
1.11-7
13 Sep 2013
1.11-8
30 Jan 2015
1.11-9
30 Sep 2014
1.11-10
30 Jan 2015
1.11-11
30 Sep 2014
1.11-12
07 Mar 2016
1.11-13
30 Sep 2014
AOM DASH 8-Q400
DOT
T H IS PA G E
INTE NTIONA LLY
L EF T
BLANK
CHAPTER 1
LIMITATIONS
ToC 1-1
[Rev. 17] 30 JUN 2016
- TABLE OF CONTENTS 1.1
INTRODUCTION .................................................................................................................... 1.1-1
1.2
CERTIFICATION STATUS ..................................................................................................... 1.2-1
1.3
PASSENGER SEATING CONFIGURATION ......................................................................... 1.3-1
1.3.1
Maximum number of passenger seats .................................................................................... 1.3-1
1.3.2
Maximum number of passengers on board ............................................................................ 1.3-1
1.3.3
Maximum number of infants ................................................................................................... 1.3-1
1.4
CREW COMPOSITION .......................................................................................................... 1.4-1
1.4.1
Minimum Flight Crew .............................................................................................................. 1.4-1
1.4.2
Crew Seats ............................................................................................................................. 1.4-1
1.5
MASS / WEIGHT and CENTER OF GRAVITY LIMITS ......................................................... 1.5-1
1.5.1
General ................................................................................................................................... 1.5-1
1.5.2
Maximum Allowable Gross Masses / Weights ........................................................................ 1.5-1
1.5.3
Mean Aerodynamic Chord (MAC) and Balance Limits ........................................................... 1.5-2
1.6
SPEED LIMITATIONS ............................................................................................................ 1.6-1
1.7
MANEUVERING LIMIT LOAD FACTORS ............................................................................. 1.7-1
1.8
OPERATIONAL LIMITATIONS and INFORMATION ............................................................. 1.8-1
1.8.1
Wind Limitations ..................................................................................................................... 1.8-1
1.8.2
Temperature Limitations ......................................................................................................... 1.8-2
1.8.3
Take-off Power Setting Limitation ........................................................................................... 1.8-2
1.8.4
Maximum Operating Altitude .................................................................................................. 1.8-2
1.8.5
Maximum Slope for Take-off and Landing .............................................................................. 1.8-2
1.8.6
Maximum Glide Slope Angle for Cat II Approaches ............................................................... 1.8-2
1.8.7
Eye to Wheel Path and ILS to Wheel Path Distances ............................................................ 1.8-2
1.8.8
Adverse Weather Operation ................................................................................................... 1.8-3
1.8.9
Airframe Contamination .......................................................................................................... 1.8-3
1.8.10
Baggage / Cargo Compartment Limitations ............................................................................ 1.8-3
1.9
GROUND OPERATIONAL LIMITATIONS and INFORMATION ............................................ 1.9-1
1.9.1
Minimum Turning Radius ........................................................................................................ 1.9-1
1.9.2
Line-up Losses ....................................................................................................................... 1.9-1
1.9.3
Eye to Ground and ILS to Ground Distances ......................................................................... 1.9-1
1.9.4
Minimum Runway Width ......................................................................................................... 1.9-2
1.9.5
Aircraft Classification Number / Load Classification Number (ACN / LCN Values) ................ 1.9-2
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 1
ToC 1-2
[Rev. 12] 30 SEP 2014
LIMITATIONS
- TABLE OF CONTENTS - (cont’d)
1.10
PERFORMANCE LIMITATIONS .......................................................................................... 1.10-1
1.10.1
General ................................................................................................................................. 1.10-1
1.10.2
Flap Settings ......................................................................................................................... 1.10-1
1.10.3
Operation with Landing Gear Extended ................................................................................ 1.10-1
1.10.4
Reduced Power Take-off ....................................................................................................... 1.10-1
1.10.5
Take-off and Landing with Bleed “ON” .................................................................................. 1.10-2
1.10.6
Operation with Inoperative Nosewheel Steering ................................................................... 1.10-2
1.10.7
Take-off with Maximum Take-off Power and Uptrim Disabled ............................................... 1.10-2
1.10.8
Operation with 32 in Tires ...................................................................................................... 1.10-2
1.10.9
Operation with Inoperative Flight Spoilers in Ground Mode .................................................. 1.10-3
1.10.10
Operation with 10 min Maximum Take-off Power .................................................................. 1.10-3
1.10.11
Noise Abatement Procedures - Landing with 850 RPM ........................................................ 1.10-3
1.10.12
Operation in Tailwinds Between 10 and 20 kt ....................................................................... 1.10-4
1.10.13
Operation on Contaminated Runways with Measured Friction Values ................................. 1.10-4
1.10.14
Operation with Inoperative Anti-Skid Brake Control System.................................................. 1.10-5
1.10.15
Steep Approach and Landing ................................................................................................ 1.10-6
1.10.16
Take-off with Bleed ON ......................................................................................................... 1.10-7
1.10.17
Operation from Unpaved / Gravel Runways ......................................................................... 1.10-7
1.10.18
Restricted Operation from Unpaved / Gravel Runways ........................................................ 1.10-8
1.10.19
Take-off into Icing Conditions to 1000 ft AGL with
REF SPEEDS Switch OFF ................................................................................................... 1.10-8
1.11
SYSTEM LIMITATIONS ........................................................................................................ 1.11-1
1.11.1
Airspeed Indicators ............................................................................................................... 1.11-1
1.11.2
Altimeters .............................................................................................................................. 1.11-1
1.11.3
Outside Air Temperature (OAT) / Static Air Temperature (SAT) Relationship ....................... 1.11-1
1.11.4
Power Plant Limitations ......................................................................................................... 1.11-2
1.11.5
APU Limitations ..................................................................................................................... 1.11-8
1.11.6
Fuel Limitations ..................................................................................................................... 1.11-9
1.11.7
Air Conditioning and Pressurization .................................................................................... 1.11-11
1.11.8
Electrical Systems ............................................................................................................... 1.11-11
1.11.9
Landing Gear and Flap Systems ......................................................................................... 1.11-11
1.11.10
Wheel Brake Cooling Systems ............................................................................................ 1.11-11
1.11.11
Airframe Ice Protection ........................................................................................................ 1.11-11
1.11.12
Automatic Flight Control System (AFCS) ............................................................................ 1.11-12
1.11.13
Avionics ............................................................................................................................... 1.11-12
1.11.14
Flight Management System (FMS) ..................................................................................... 1.11-12
1.11.15
Data Link System ................................................................................................................ 1.11-13
1.11.16
Enhanced Ground Proximity Warning System (EGPWS) ................................................... 1.11-13
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.1
1.1-1
[Rev. X] 31 MAY 2011
INTRODUCTION
Chapter 1 contains all relevant type certificate and operational limitations for the operation of the Dash 8-Q400
Series. If any deviation between the information given in this chapter and Section 2 of the AFM should be
observed, the latter manual shall take precedence.
As far as instrument markings are concerned, the following interpretation shall apply:
GREEN = Normal operating range
AMBER = Caution range
RED
= Limit of operation
AOM DASH 8-Q400
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CHAPTER 1
LIMITATIONS
1.2
1.2-1
[Rev. X] 31 MAY 2011
CERTIFICATION STATUS
The Dash 8-Q400 Series is certified under the airworthiness regulations of JAR 25 (including change 14), JARAWO (change 1 plus orange paper AWO 91/1) and FAR 25 for the following types of operation:
IFR / VFR day and night
Flights in icing conditions
CAT II operation (optional)
Furthermore, the nav-equipment meets the requirements for RNP 5 (B-RNAV).
The airplane also meets the noise limitations of JAR 36/FAR 36 and the exhaust emission requirements of JAR
34/FAR 34.
The airplane is also certified for ditching provided the required safety equipment as specified under the applicable JARs/FARs is installed.
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CHAPTER 1
1.3-1
LIMITATIONS
1.3
PASSENGER SEATING CONFIGURATION
1.3.1
Maximum number of passenger seats
[Rev. X] 31 MAY 2011
The maximum approved passenger seating capacity is 80 (with the respective approved interior).
The airplane cabin configuration shown is fitted with 78 seats (see Figure 1.1).
BAGGAGE DOOR
24.00 in. W x 54.00 in. H
FORWARD
BAGGAGE
COMPARTMENT
G6 GALLEY
SERVICE DOOR/TYPE I EXIT
24.00 in. W x 54.00 in. H
TYPE II/III EXIT
20.20 in. W x 56.00 in. H
LAVATORY
NO.2
ATTENDANT
SEAT
102 (ROW 2R)
G3 GALLEY
D
C
ROW
1
2
3
4
5
6
7
8
9
10
11
12
14
15
16
17
18
19
20
21
70
103
133
163
193
223
253
283
313
343
373
403
433
463
493
523
553
583
613
643
B
A
WARDROBE
OPTIONAL
ENTRY
STAIRS
PASSENGER C.G. (in.)
NO.1
ATTENDANT
SEAT
AIRSTAIR/TYPE I EXIT
30.00 in. W x 65.00 in. H
PAX DOOR/TYPE I EXIT
24.00 in. W x 65.00 in. H
Figure 1.1. Cabin Configuration - 78 Pax at 30 inch Pitch
NOTE:
1.3.2
The above cabin configuration is a “typical” layout. Please refer to the Weight and Balance
Manual, PSM 1-84-8 or PSM 1-84-8M, for your airplane’s specific cabin configuration.
Maximum number of passengers on board
The actual number of passengers – excluding infants – shall not exceed the number of serviceable seats provided with seat belts and the number of life vests – when required under JAR-OPS 1.825/FAR 121.
1.3.3
Maximum number of infants
An infant may be seated on the knee of an adult. The number of infants carried is however limited to the number of available infant’s life vests – should life vests be required as per JAR-OPS 1.825/FAR 121.
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CHAPTER 1
LIMITATIONS
1.4
CREW COMPOSITION
1.4.1
Minimum Flight Crew
1.4-1
[Rev. X] 31 MAY 2011
For commercial operations the minimum flight deck crew shall consist of a pilot qualified as a captain/commander and a second pilot qualified as a first officer.
For passenger carrying operations a minimum of two qualified cabin attendants are required.
1.4.2
Crew Seats
Two pilot seats and one observer seat are provided in the flight compartment.
One forward cabin attendant seat is provided in the forward cabin section and one aft cabin seat is provided in
the rear cabin section. An optional third cabin attendant seat, in the aft cabin section, may be available with the
applicable interior.
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CHAPTER 1
1.5-1
LIMITATIONS
1.5
MASS / WEIGHT and CENTER OF GRAVITY LIMITS
1.5.1
General
[Rev. 16] 7 MAR 2016
The mass / weight limits for take-off and for landing as shown under Sub-Chapter 1.5.2 are structural limits and
may be further restricted by performance requirements (see individual airport / runway performance charts).
1.5.2
Maximum Allowable Gross Masses / Weights
Mass / Weight
Basic
Intermediate
Gross
Gross
High Gross
Enhanced
High Gross
[MS 4-201539]
[MS 4-459409]
[MS 4-308807]
[MS 4-308907]
[MS 4-309238]
Maximum
28077 kg
26082 kg
29089 kg
29347 kg
29665 kg
Ramp
(61900 lb)
(57500 lb)
(64130 lb)
(64700 lb)
(65400 lb)
Maximum
27987 kg
25991 kg
28998 kg
29257 kg
29574 kg
Take-off
(61700 lb)
(57300 lb)
(63930 lb)
(64500 lb)
(65200 lb)
Maximum
27442 kg
25991 kg
28009 kg
28009 kg
28123 kg
Landing
(60500 lb)
(57300 lb)
(61750 lb)
(61750 lb)
(62000 lb)
Maximum
25174 kg
25174 kg
25855 kg
25855 kg
26308 kg
Zero Fuel
(55500 lb)
(55500 lb)
(57000 lb)
(57000 lb)
(58000 lb)
Minimum
Structural
Design
AOM DASH 8-Q400
14403 kg
(31753 lb)
CHAPTER 1
1.5-2
LIMITATIONS
[Rev. 16] 7 MAR 2016
1.5.3
Mean Aerodynamic Chord (MAC) and Balance Limits
The certified limits for the MAC are:
Mass / Weight
Up to 24040 kg
(53000 lb)
27987 kg
(61700 lb)
28998 kg
(63930 lb)
29257 kg
(64500 lb)
29574 kg
(65200 lb)
Forward
Aft
Limit
Limit
13.8%
36%
16.6%
36%
17.3%
36%
17.4%
36%
17.7%
36%
[with MS 4-459409 Incorporated] the certified limits for the MAC are:
Mass / Weight
Up to 24040 kg
(53000 lb)
25991 kg
(57300 lb)
NOTES:
Forward
Aft
Limit
Limit
13.8%
36%
15.2%
36%
1. If these Center of Gravity limits are met with the landing gear down, then safe limits in flight
are automatically achieved.
2. The maximum aft limit is 20% MAC for operations with one inoperative stall warning and / or
stick pusher system.
To compensate for index-system associated errors (e.g. using one arm for more seat rows or moment changes
caused by cabin attendants or passengers) an operational envelope is restricting the certified limits.
This operational envelope is printed on the load & trim sheet.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.6
1.6-1
[Rev. X] 31 MAY 2011
SPEED LIMITATIONS
NOTE:
The airspeed limitations apply to all masses (weights) up to 29,574 kg (65,200 lb) gross
weight, unless otherwise stated.
Type of Speed Limitations
Limiting Speed
VMCG - flaps 15° - flaps 10° - flaps 5° - flaps 0° -
89 KCAS
89 KCAS
89 KCAS
101 KCAS
VMCA - flaps 15° - flaps 10° - flaps 5° - flaps 0° -
91 KCAS
95 KCAS
98 KCAS
113 KCAS
VMCL - flaps 35° - flaps 15° - flaps 10° - flaps 5° -
92 KCAS
96 KCAS
99 KCAS
100 KCAS
NOTE:
VMO varies linearly between the given altitudes.
VMO - 0 - 8000 ft. - at 10000 ft. - at 18000 ft. - at 20000 ft. - at 25000 ft. -
245 KIAS
282 KIAS
286 KIAS
275 KIAS
248 KIAS
VFE
200 KIAS
181 KIAS
172 KIAS
158 KIAS
- flaps 5° - flaps 10° - flaps 15° - flaps 35° -
VLO
VLE
Alternate Gear Extension Speed
200 KIAS
215 KIAS
185 KIAS
VRA
VMAX TIRE
210 KIAS
182 knots ground speed
VA
204 KIAS
CAUTION
Rapid and large alternating control inputs, especially in combination with
large changes in pitch, roll or yaw (e.g. large sideslip angles), may result
in structural failure at any airspeed, including below VA.
Aquaplaning Speeds (assumption: main gear tire pressure 141 psi for 34 inch tire)
VAQUAPLANING for T/O
= 107 kts GS
VAQUAPLANING for Landing = 92 kts GS
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CHAPTER 1
LIMITATIONS
1.7
1.7-1
[Rev. X] 31 MAY 2011
MANOEUVERING LIMIT LOAD FACTORS
The following maneuvering limit load factors limit the permissible angle of bank in turns and limit the severity of
pull-up and push-over maneuvers.
Flaps retracted: + 2.5 g
- 1.0 g
Flaps extended: + 2.0 g
0.0 g
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CHAPTER 1
1.8-1
LIMITATIONS
[Rev. 17] 30 JUN 2016
1.8
OPERATIONAL LIMITATIONS and INFORMATION
1.8.1
Wind Limitations
1.8.1.1
Maximum Crosswind
Runway Conditions
Contaminated
Conditions
Dry / Wet
WED 3 mm
(0.125 in) or less
WED greater than
3 mm (0.125 in)
Compacted Snow
Wet Ice
Braking Action Poor
Take-off
32 kt
14 kt
14 kt
20 kt
0
Landing
32 kt
14 kt
14 kt
20 kt
0
CAT II Landing
- coupled
- manual
18 kt
10 kt
14 kt
10 kt
14 kt
10 kt
18 kt
10 kt
0
0
1.8.1.2
Maximum Tailwind
Runway Conditions
Conditions
Dry / Wet
Contaminated
Ice and Wet Ice
Braking Action Poor
Take-off Flap 5°
10 kt
10 kt
0
Take-off Flap 10° / 15°
10 kt *
10 kt
0
Landing Flap 10° / 15°
10 kt
10 kt
0
Landing Flap 35°
10 kt *
10 kt
0
CAT II Landing
(Flap 10° / 15° only)
10 kt
10 kt
0
5 kt
5 kt
0
Steep APPR Landing
(Flap 35° only)
* Limits may be increased, when AFM Supplement 3 (Operation In Tailwinds Between 10 and 20 kt)
is applicable
1.8.1.3
Maximum Headwind (CAT II Landing)
Maximum Headwind
CAT II Landing
- coupled
- manual
NOTE:
24 kt
10 kt
Additional operating regulations and / or stricter limits, or as set forth by the operator, may
result in limits lower than those given in Sub-Chapters 1.8.1.1 and 1.8.1.2
AOM DASH 8-Q400
CHAPTER 1
1.8-2
LIMITATIONS
[Rev. 17] 30 JUN 2016
1.8.2
Temperature Limitations
MAX ambient temperature = + 50°C or ISA + 35°C, whichever is lower.
MIN ambient temperature = - 54°C
CAUTION: The cold weather operations procedures provided in the Ramp Servicing Manual
PSM 1-84-2S, must be observed prior to starting engines on the ground after the aircraft
is parked in excess of 3 h in temperatures of - 15°C or lower.
1.8.3
Take-off Power Setting Limitation
Setting take-off power prior to brake release, with nose of the airplane more than 45° out of wind, is prohibited
for wind speeds greater than 8 kt (measured at a height of 10 m).
1.8.4
Maximum Operating Altitude
Maximum operating altitude = 25000 ft.
Maximum operating altitude for take-off and landing = 10000 ft.
1.8.5
Maximum Slope for Take-off and Landing
Maximum runway slopes approved for take-off and landing are:
+ 2% (uphill slope)
- 2% (downhill slope)
1.8.6
Maximum Glide Slope Angle for CAT II Approaches
When certified for CAT II operations, the maximum glide slope angle shall not exceed 3.5° during CAT II
approaches.
1.8.7
Eye to Wheel Path and ILS to Wheel Path Distances
Approach
Flap
Eye to Wheel Path
ILS to Wheel Path
[°]
[°]
[ m (ft) ]
[ m (ft) ]
10
4.662 (15.30)
4.446 (14.59)
15
4.339 (14.24)
3.927 (12.88)
35
3.928 (12.89)
3.273 (10.74)
35
3.934 (12.91)
3.278 (10.76)
3
4.5
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.8.8
Adverse Weather Operation
1.8.8.1
Operation from Contaminated Runways
1.8-3
[Rev. 17] 30 JUN 2016
1. Take-off with reduced power is prohibited
2. Operation from runways contaminated with standing water, slush or loose snow
a. Maximum operating altitude for take-off and landing is 6000 ft ASL.
b. The maximum permitted WED of contaminant is 15 mm (0.59 in).
c. The maximum permitted depth of contaminant 6 cm (2.4 in).
d. For WED greater than 3 mm (0.125 in); selection of power levers aft of DISC is prohibited.
e. The maximum crosswind component for take-off and landing is 14 kt.
3. Operation from runways contaminated with compacted snow
a. The maximum crosswind component for take-off and landing is 20 kt.
1.8.8.2
Operation in Icing Conditions
Observe performance penalties as given in Chapter 4 (Performance).
1.8.9
Airframe Contamination
Observe the relevant procedures for de-icing and anti-icing and the relevant hold-over times as specified in the
Flight Operation Manual (Operations Manual Part A).
Also observe the instruction for the different de-icing / anti-icing fluids and the performance penalties as given
in Chapter 4 - Performance.
1.8.10
Baggage / Cargo Compartment Limitations
For your airplanes particular baggage compartment loading limits, refer to the Cargo Loading Manual
PSM 1-84-8A.
1.8.10.1
Baggage Compartment Classification
Both the forward and aft baggage compartments are classified as “Class C” compartments (see also SubChapter 6.6.3). Class C compartments do require:
1)
a separate approved smoke detector or fire detector system to give warning at the pilot station;
2)
an approved built-in fire extinguishing system controllable from the pilot stations;
3)
any means to exclude hazardous quantities of smoke, flames or extinguishing agent, from any compartment occupied by the crew or passengers; and
4)
any means to control ventilation and draughts within the compartment so that the extinguishing agent
used can control fire that may start within the compartment.
1.8.10.2
Baggage Compartment Fire Extinguishing
Unless the forward and aft baggage compartments are empty, the airplane must not be operated further than
1 h flying time from a suitable airport for landing.
1.8.10.3
Cargo Compartment Fire Extinguishing
[with Option - CR 825 CH 03262 Incorporated]
Unless the cargo compartment is empty, the airplane must not be operated further than 1 h flying time from a
suitable airport for landing.
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CHAPTER 1
1.9-1
LIMITATIONS
[Rev. 17] 30 JUN 2016
1.9
GROUND OPERATIONAL LIMITATIONS and INFORMATION
1.9.1
Minimum Turning Radius
Minimum pavement width for a 180° turn = 26 m (85 ft).
This minimum radius assumes a full nose wheel steering angle of 70°.
1.9.2
Line-up Losses
(as per JAR-OPS 1.490(c)(6) IEM and IATA SCAP Specification Annex XIII)
Steering Angle
90° ENTRY
30°
35°
40°
45°
50°
55°
60°
65°
70°
TODA / TORA loss [m]
32
28
25
22
20
18
16
15
13
ASDA loss [m]
46
42
38
36
34
32
30
28
27
TODA / TORA loss [m]
31
28
25
23
22
21
20
19
18
ASDA loss [m]
45
42
39
37
36
34
33
33
32
180° ENTRY (turnaround)
1.9.3
Eye to Ground and ILS to Ground Distances
Eye to Ground
ILS to Ground
[ m (ft) ]
[ m (ft) ]
3.029 (9.94)
1.864 (6.12)
AOM DASH 8-Q400
CHAPTER 1
1.9-2
LIMITATIONS
[Rev. 17] 30 JUN 2016
1.9.4
Minimum Runway Width
Unless otherwise approved in a Supplement to the AFM (“narrow runway” supplement), the minimum width of
a runway should not be less than 30 m (98 ft).
1.9.5
Aircraft Classisfication Number / Load Classification Number
(ACN / LCN – 34” Tires – Values)
ACN – Values, 34” tires
(for maximum take-off mass (weight))
Rigid Pavement Subgrades
A High
B Medium
C Low
D Ultra Low
17.6
18
19.1
19.9
Flexible Pavement Subgrades
A High
B Medium
C Low
D Ultra Low
15.2
16.0
18.3
20.2
RECOMMENDATION: as most airports have a rigid pavement with a Class B subgrade, use “20” for
planning purposes.
LCN – Values 34” tires
Rigid Pavement Subgrades: - use LCN 39
Flexible Pavement Subgrades: - use LCN 43
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.10
PERFORMANCE LIMITATIONS
1.10.1
General
1.10-1
[Rev. X] 31 MAY 2011
In addition to the data presented in chapter 4 - AOM showing the applicable performance data - this sub-chapter presents some performance - related limitations which may also become applicable when using special
AFM - supplements.
1.10.2
Flap Settings
The approved flap-settings are as follows:
Take-off +
Initial Climb
-
5°
10°
15°
-
0°
-
-
-
-
Approach
-
5°
10°
15°
-
Landing
-
-
10°
15°
35°
Cruise
1.10.3
Operation with Landing Gear Extended
1.10.3.1
General
Operation with the landing gear extended (doors closed) are subject to the approval of the local airworthiness
authorities.
1.10.3.2
Operating Limitations
The operating limitations in Chapter 1 of the Aeroplane Operating Manual are applicable with the addition of
the following:
1.
Take-off on a contaminated runway is prohibited.
2.
Dispatch into known or forecast icing conditions is prohibited.
3.
Bleed air must be off for take-off and landing.
4.
Landing gear doors must be closed, and landing gear fairings installed.
5.
Maximum airspeed with landing gear extended and the landing gear doors closed (VLE) is 215 KIAS.
6.
Maximum altitude with the landing gear extended and landing gear doors closed is 20,000 ft.
7.
Ditching emergency procedure is not applicable.
8.
The operating procedures under Chapter 2 and 3 (Normal and Abnormal Procedures) and the performance penalties as per Chapter 4, page 4.8-1 shall be observed.
1.10.4
Reduced Power Take-off
This procedure corresponds to supplement 13 of the AFM.
1.10.4.1
Limitations
The maximum assumed OAT is ISA +35°C.
Once every 24 hours (flying day) a take-off, using Normal Take-off power setting (see chapter 4.10, table 1),
must be accomplished to verify engine performance. The minimum torque for the assumed outside air temperature is 90% of the Normal Take-off power setting (see table on page 4.10-2).
When supplement 61 (Take-off with BLEED “ON”) is incorporated, use data for torque as shown on table 1a
page 4.10-3.
•
May not be used with the following AFM supplements: 3, 7, 21, 25, 26, 37, 46, 77 and 94.
•
See chapter 4.12 for the applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
1.10-2
[Rev. X] 31 MAY 2011
1.10.5
LIMITATIONS
Take-off and Landing with Bleed “ON”
This procedure corresponds to supplement 21 of the AFM.
This supplement must not be used with the following AFM supplements:
•
Operation in tailwinds in excess of 10 kt (Supplement 3)
•
Using reduced power for Take-off (Supplement 13)
•
Operation from unpaved/gravel runways (Supplement 25 and 26)
•
Take-off with maximum take-off power and uptrim disabled (Supplement 46)
•
Take-off with Bleed “ON”
(Supplement 61)
•
Operation with Landing Gear Extended (Supplement 94)
1.10.5.1
Limits
− The applicable take-off power torque settings (as for the conditions of pressure altitude and temperature)
will be found in the AOM, chapter 4, pages 4.10-2a, 4.10-3a and 4.10-4a.
− The OAT increased by 11°C must not exceed 50°C (ISA +35°C).
→ See chapter 4.13 for the applicable performance data.
1.10.6
Operation with Inoperative Nosewheel Steering
This procedure corresponds to supplement 8 of the AFM.
1.10.6.1
Limits
An operation with inoperative nosewheel steering is not permitted when operating on contaminated runways or
when operating with an inoperative anti-skid brake system.
Furthermore, operations from unpaved runways are also not permitted. The maximum permitted tailwind shall
not exceed 10 kt.
May not be used with the following AFM supplements: 3, 7, 25, 26, 37 and 77.
→ See chapter 4.14 for applicable performance data.
1.10.7
Take-off with Maximum Take-off Power and Uptrim Disabled
This procedure corresponds to supplement 46 of the AFM.
1.10.7.1
Limits
With the Bypass Doors Open, the maximum ambient temperature is ISA +25°C.
May not be used with the following AFM supplements: 13, 21, 61 and 94.
→ See chapter 4.15 for applicable performance data.
1.10.8
Operation with 32 Inch Tires
This procedure corresponds to supplement 65 of the AFM.
1.10.8.1
Limitations
Operation from unpaved/gravel runways is prohibited.
When operating with 32 inch tires (MS 4-200006 or MS 4-436865) performance data must be corrected.
→ See chapter 4.16 for applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.10.9
1.10-3
[Rev. X] 31 MAY 2011
Operation with Inoperative Flight Spoilers in Ground Mode
This procedure corresponds to supplement 17 of the AFM.
1.10.9.1
Limitations
An operation with inoperative flight spoilers in ground mode is not permitted when operating from contaminated
runways.
Furthermore, the maximum tailwind component shall not exceed 10 kt, steep approaches (supp. 12), noise
abatement procedures (supp. 39) and ILS row data steep approaches (supp. 45) are not permitted when operating with inoperative flight spoilers in ground mode.
May not be used with the following AFM supplements: 3, 12, 25, 26, 37, 39, 45 and 77.
→ See chapter 4.17 for applicable performance data.
1.10.10
Operation with 10-Minute Maximum Take-off Power - Following an Engine Failure
This procedure corresponds to supplement 27 of the AFM.
1.10.10.1
Limitations
Standard certification is based upon a 5 minute time limit for maximum take-off power. With the incorporation of
AFM Supplement 27, a maximum of 10 minutes with maximum take-off power is permitted .
May not be used with AFM supplements 3 and 94.
The maximum tailwind shall not exceed 10 kt.
→ See chapter 4.18 for applicable performance data.
1.10.11
Noise Abatement Procedures - Landing with 850 Prop RPM
This procedure corresponds to supplement 39 of the AFM.
1.10.11.1
Limitations
An approach and landing with 850 NP must not be performed with:
•
Anti-skid brake control system is inoperative (AFM Supp. 7)
•
CAT II operations (AFM Supp. 16)
•
Inoperative flight spoilers in ground mode (AFM Supp. 17)
•
Operation on contaminated runways (AFM Supp. 37 and Supp. 77)
•
Operation in tailwinds in excess of 10 kt (AFM Supp. 3)
•
Operation from runways with slopes greater than +2%
•
Steep approaches (AFM Supp. 12 and Supp. 45)
•
Operation from unpaved/gravel runways (AFM Supps. 25 and 26)
•
Operation with landing gear extended (AFM Supp. 94)
→ See chapter 4.19 for applicable performance data.
With MS 4-901204 or MS 4-901304 or MS 4-126306 or MS 4-126293 or MS 4-901326 or MS 4-126337 not
incorporated, or with MS IS4Q7600001 incorporated and MS 4-901204 not fully incorporated, or without a serviceable radio altimeter:
With REF SPEEDS switch selected to INCR, flap 35°, landing with reduced RPM is prohibited.
NOTE:
The referenced modification summaries (MS) refer to the incorporation of the radio altitude
information into PSEU/WOW logic for the Propeller Electronic Controller (PEC).
AOM DASH 8-Q400
CHAPTER 1
1.10-4
[Rev. X] 31 MAY 2011
1.10.12
LIMITATIONS
Operation in Tailwinds between 10 and 20 Knots
This procedure corresponds to supplement 3 of the AFM.
1.10.12.1
General
When supplement 3 to the AFM is approved by the appropriate airworthiness authority and incorporated in the
respective AFM, the normal tailwind limit of 10 kt may be increased to 20 kt for take-off and landing.
1.10.12.2
Operating Limitations
Unless additional limitations are set forth by the operator (see page 1.8-1), take-off and landing with tailwind
operations in excess of 10 kt are not permitted under the following conditions:
•
when the Anti-Skid Brake Control System is inoperative. (AFM Supplement 7),
•
when the Nosewheel Steering System is inoperative. (AFM Supplement 8),
•
when taking off with reduced power (AFM Supplement 13),
•
for CAT II operations (AFM Supplement 16),
•
when the Flight Spoilers are inop. in Ground Mode (AFM Supplement 17),
•
when taking off and landing with Bleed “ON” (AFM Supplement 21 and 61),
•
when using more than 5 minutes maximum take-off power following an engine failure during take-off (AFM
Supplement 27),
•
when operating on contaminated runways (AFM Supplement 37)
•
when landing with 850 Propeller RPM (AFM Supplement 39).
•
when operating from unpaved/gravel runways (AFM Supplement 25 and 26)
•
when performing steep approaches and landings (AFM Supplement 12 or AFM Supplement 45)
•
when taking-off into icing conditions to 1000 ft AGL (AFM Supplement 76)
→ See chapter 4.20 for applicable performance data.
1.10.13
Operation from Narrow Runways
− Reserved for the possible incorporation of supplement 54 1.10.14
Operation with Inoperative Anti-skid Brake Control System
This procedure corresponds to supplement 7 of the AFM.
1.10.14.1
General
The operation with inoperative anti-skid brake control system is permitted under the conditions as specified in
the approved MEL and the operating limitations.
1.10.14.2
Operating Limitations
Unless additional limitations as specified in the MEL do apply, the operation with inoperative Anti-Skid Brake
Control System is not permitted:
•
when operating from wet and/or contaminated runways (AFM Supplement 37 or 77),
•
when the nose wheel steering system is inoperative (AFM Supplement 8),
•
when using reduced take-off power (AFM Supplement 13).
•
when performing steep approaches and landings (supp. 12, 45)
•
when operating from unpaved runways (supp. 25 or 26)
•
when performing noise abatement procedures (supp. 39)
•
when operating in tailwind conditions in excess of 10 kt.
→ See chapter 4.22 for applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.10.15
Steep Approach and Landing
1.10.15.1
General
1.10-5
[Rev. X] 31 MAY 2011
Subject to the operational approval and the incorporation of MS 4-456970 approach angles higher than 4,5°
may be flown when supplement 12 is applicable.
1.10.15.2
Operating Limitations
A steep approach and the subsequent landing shall not be carried out under the following conditions:
•
approach angles higher than 5.5°
•
at tailwind conditions greater than 5 kt
•
on CAT II operations (AFM Supplement 16)
•
with inoperative flight spoilers in ground mode (AFM Supplement 17)
•
when the anti skid brake system is inoperative (AFM Supplement 7)
•
when the runway is contaminated (AFM Supplement 37 or 77)
•
when operating from unpaved runways
•
when landing with 850 Prop. RPM (AFM Supplement 39)
•
on CAT I autopilot (coupled) and Flight Director (Manual) Approaches
•
when using a flap setting other than 35° (landing gear down, flap 35° and condition levers to MAX must be
selected prior to commencing a steep approach)
•
when no suitable glide path system is available for day/night operations
•
when the runway slope exceeds plus/minus 0.5%
•
when the landing mass exceeds 26,308 kg (58,000 lbs)
•
when the maximum operating altitude for landing is exceeding 5,000 feet ASL
•
with one engine out.
May not be used with the following AFM supplements: 2, 3, 7, 16, 17, 25, 26, 37, 39, 75 and 77.
The minimum height for transition to a steep approach is 1,000 ft. The minimum height for go-around following
an engine failure after the steep approach has been started is 300 feet AGL.
NOTE:
1.10.15.3
The height loss during a go-around following an engine failure is 150 ft (46 m)
ILS-Raw Data Only Steep Approach (AFM Supplement 45)
When operationally approved in conjunction with the approval for steep approaches, the following additional
limitations will apply:
•
landing gear down, flap 35° and condition levers MAX must be selected prior to glide slope intercept and
used during guided approach
•
approach must not be commenced or must be discontinued prior to DH in the event of an engine failure
•
minimum DH is 300 ft ARTE (above rwy THR)
May not be used with the following AFM supplements: 2, 3, 7, 16, 17, 25, 26, 37, 39, 75 and 77.
→ See chapter 4.23 for applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
1.10-6
[Rev. X] 31 MAY 2011
1.10.16
LIMITATIONS
Take-Off with Bleed ON
This procedure corresponds to Supplement 61 of the AFM.
1.10.16.1
Limitations
A take-off with BLEED ON is not permitted under the following conditions:
•
at tailwinds in excess of 10 kt
•
when operating on runways with slopes greater than +2%
•
when taking-off with maximum take-off power and uptrim disabled
•
operations with landing gear extended
•
operations with one bleed system inoperative
→ See chapter 4.24 for applicable performance data.
1.10.17
Operation from Unpaved/Gravel Runway
This procedure corresponds to supplements 26 of the AFM.
1.10.17.1
Operating Limitations
1.10.17.1.1 General Limitations:
An operation on unpaved/gravel runways is not permitted:
•
in tailwind condition in excess of 10 kt (AFM Supplement 3),
•
with inoperative Anti-Skid Brake System (AFM Supplement 7),
•
with inoperative Nosewheel Steering System (AFM Supplement 8),
•
when performing steep approaches (AFM Supplement 12),
•
when taking off with reduced power (AFM Supplement 13),
•
with inoperative flight spoilers in ground mode (AFM Supplement 17),
•
when taking off with Bleed “ON” (AFM Supplement 21),
•
when the runway is contaminated (AFM Supplement 37 or 77),
•
when using Noise Abatement Procedures (landing with 850 Prop RPM) (AFM Supplement 39)
•
when performing an ILS Raw Data only Steep Approach (AFM Supplement 45),
•
when the aeroplane is equipped with 32 inch tires (AFM Supplement 65)
1.10.17.1.2 Additional Limitations:
1) The runway:
a. Shall have a uniform covering of surface material that is graded smooth and kept free from ruts to avoid
the formation of pools of water during periods of precipitation.
b. Surface bearing material must not be less than 12 inches in depth and well compacted. The surface
bearing material must demonstrate a minimum average California Bearing Ratio (CBR) of 30 with the
lowest measured CBR points of not less than 20, as determined by a Boeing High Load Penetrometer.
c. Areas of loose gravel and surface stones greater than 1 inch (2.54 cm) in diameter shall not be permitted.
d. Vegetation shall not be permitted.
e. Shall be inspected at a frequency dictated by local conditions to assure satisfactory surface condition.
2) Use of reverse thrust is prohibited.
3) Take-off from unpaved/gravel runways is approved with flap 15° only.
4) Landing on unpaved/gravel runways is approved with flap 35° only.
5) Engine inlet nacelle bypass doors must be open for take-off and landing.
6) Maximum temperature for take-off and landing is ISA +25°C.
→ See Chapter 4.25 for the applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.10.18
1.10-7
[Rev. X] 31 MAY 2011
Restricted Operation from Unpaved/Gravel Runway
This procedure corresponds to supplements 25 of the AFM.
1.10.18.1
Operating Limitations
1.10.18.1.1 General Limitations:
An operation on unpaved/gravel runways is not permitted:
•
in tailwind condition in excess of 10 kt (AFM Supplement 3),
•
with inoperative Anti-Skid Brake System (AFM Supplement 7),
•
with inoperative Nosewheel Steering System (AFM Supplement 8),
•
when performing steep approaches (AFM Supplement 12),
•
when taking off with reduced power (AFM Supplement 13),
•
with inoperative flight spoilers in ground mode (AFM Supplement 17),
•
when taking off with Bleed “ON” (AFM Supplement 21),
•
when the runway is contaminated (AFM Supplement 37 or 77),
•
when using Noise Abatement Procedures (landing with 850 Prop RPM) (AFM Supplement 39)
•
when performing an ILS Raw Data only Steep Approach (AFM Supplement 45),
•
when the aeroplane is equipped with 32 inch tires (AFM Supplement 65)
1.10.18.1.2 Additional Limitations:
1) The runway:
a. Shall have a uniform covering of surface material that is graded smooth and kept free from ruts to avoid
the formation of pools of water during periods of precipitation.
b. Surface bearing material must not be less than 12 inches in depth and well compacted. The surface
bearing material must demonstrate a minimum average California Bearing Ratio (CBR) of 30 with the
lowest measured CBR points of not less than 20, as determined by a Boeing High Load Penetrometer.
c. Areas of loose gravel and surface stones greater than 1 inch (2.54 cm) in diameter shall not be permitted.
d. Vegetation shall not be permitted.
e. Shall be inspected at a frequency dictated by local conditions to assure satisfactory surface condition.
2) Use of reverse thrust is prohibited.
3) Take-off from unpaved/gravel runways is approved with flap 15° only.
4) Landing on unpaved/gravel runways is approved with flap 35° only.
5) Maximum operating altitude for take-off and landing is 5000 ft. MSL.
6) Engine inlet nacelle bypass doors must be open for take-off and landing.
7) Maximum temperature for take-off and landing is ISA +25°C.
8) Maximum runway slope is plus/minus 0.5%.
9) Take-off and landing in tailwind conditions is prohibited.
→ See Chapter 4.26 for the applicable performance data.
AOM DASH 8-Q400
CHAPTER 1
1.10-8
[Rev. X] 31 MAY 2011
1.10.19
LIMITATIONS
Take-off Into Icing Conditions to 1000 ft AGL with REF SPEEDS Switch OFF
This procedure corresponds to supplement 76 of the AFM.
1.10.19.1
Limitations
This procedure must not be used:
•
when operating in tailwinds in excess of 10 kt (AFM Supplement 3)
•
in operations with landing gear extended
AOM DASH 8-Q400
CHAPTER 1
1.11-1
LIMITATIONS
1.11
SYSTEM LIMITATIONS
1.11.1
Airspeed Indicators
[Rev. X] 31 MAY 2011
•
During ground operation the position error is negligible.
•
Readings in climb, cruise and descent are for practical purposes equal to true values.
Maximum difference between left and right indicators (all weights):
At approach speed ................................................................................................................................. 2 kt
At cruise speed ....................................................................................................................................... 2 kt
Maximum difference between any indicator and standby airspeed indicator (all weights):
At approach speed ............................................................................................................................... 10 kt
At cruise speed ..................................................................................................................................... 10 kt
NOTE:
1.11.2
Any mechanical errors are not considered.
Altimeters
•
During ground operation the position error is negligible.
•
Readings in climb, cruise and descent are for practical purposes equal to true values.
When altitude mismatch appears on PFD, with Integrated Standby Instrument
(MS 4-432835 or MS 4-456883 Not Incorporated), the following standby altitude correction will apply:
Flaps 0°
VAPP
150
PA
IAS
or
VMO
below
SL
15000
20000
and
above
Subtract
(ft)
Subtract
(ft)
Subtract
(ft)
Flaps 5°, 10° and 15°
or
VFE
VREF
0
0
0
100
0
300
0
100
0
400
-
-
(Compare altimeter reading of # 1 PFD and # 2 PFD.)
1.11.3
Outside Air Temperature (OAT) / Static Air Temperature (SAT) Relationship
In flight indicated SAT is equal to OAT.
On ground indicated SAT may be higher than OAT.
AOM DASH 8-Q400
CHAPTER 1
1.11-2
LIMITATIONS
[Rev. 13] 30 JAN 2015
1.11.4
Power Plant Limitations
1.11.4.1
General
•
•
•
•
•
Manufacturer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pratt & Whitney Canada
Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PW 150A
Ambient Temperature Limitations (Lower) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - 54°C
Ambient Temperature Limitations (Upper) . . . . . . . . . . . . . . . . + 50°C or ISA + 35°C (whichever is lower)
With the Engine Intake Bypass Doors Open,
take-off, landing, setting MTOP and MCP are limited to
a maximum Ambient Temperature Limitation of . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISA + 25°C
• Maximum Altitude for Airstart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20000 ft
• Automatic Take-off Power Uptrim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10% torque (nominal)
1.11.4.2
Operating Limits (Engines / Propellers)
Table 1
Power Setting
MAX Torque MAX ITT MAX NL MAX NH MAX NP Oil PRESS Oil TEMP
(%)
(°C)
(% RPM) (% RPM) (RPM)
(psid)
(°C) (4)
MAX Take-Off Power
(MTOP) (1)
106
880
100
100
1020
(6b)
61 to 72
0 to 107
115 (4.f.)
Normal Take-Off Power
(NTOP)
90.3
(6a)
(7)
(8)
(9)
1020
(6b)
61 to 72
0 to 107
115 (4.f.)
MAX Continuous Power
(MCP)
100
880
100
100
1020
(6b)
61 to 72
0 to 107
115 (4.f.)
100 MAX
165 (5)
- 40 MIN
920
(2)
Starting
Transient
(2)
135
920
102.3
101.2
1173
44 to 61
72 to 100
125 MAX
(3)
MAX Reverse
35
880
100
100
1020
61 to 72
0 to 107
NOTE:
The above table Must Not be used for setting engine power.
Chart References:
1) The take-off rating is limited to 5 min (unless 10 min are approved in the AFM Supplement 27).
2) 20 s maximum.
3) 5 s maximum for torque values above flight idle and less than 55%.
4) a. Maximum oil temperature is 125°C between discing and flight idle.
b. Minimum oil temperature required for power settings above flight idle is 0°C.
c. Minimum oil temperature required to ensure engine air inlet ice protection, prior to take-off in icing conditions, is 55°C.
d. Minimum oil temperature required to ensure engine air inlet ice protection in icing conditions, in flight
and within 3 min of setting take-off power is 65°C.
NOTE:
To maintain the minimum engine oil temperature of 65°C during descent, holding and
approach, in icing conditions, it may be necessary to increase engine power.
The increase in engine power will be limited by the allowable maximum airspeed appropriate
to VMO, VLO, VFE, aircraft system malfunctions, turbulence and ATC instructions.
e. Minimum oil temperature to unfeather propeller is - 18°C.
f. Maximum oil temperature permissible for completion of flight with a 20% reduction in power is 115°C.
Maintenance action required prior to next flight
AOM DASH 8-Q400
CHAPTER 1
1.11-3
LIMITATIONS
[Rev. 13] 30 JAN 2015
Operating Limits (Engine / Propellers) (cont’d)
5) Maximum oil pressure at discing with OAT below 0°C.
6) a. NTOP torque indication will be 90% or 91%.
b. Maximum allowable continuous NP overspeed is 1071 RPM.
7) The Normal Take-off ITT limit for a given ambient air temperature is given in the following table:
Table 2 - Variation of ITT with Ambient Air Temperature for NTOP
OAT
(°C)
ITT NTOP
(°C)
- 40
823
- 16
824
- 10
828
0
832
+ 10
838
+ 20
840
+ 30
844
+ 33
845
and above
8) The Normal Take-off NL limit for a given ambient air temperature is given in the following table:
Table 3 - Variation of NH and NL with Ambient Air Temperature for NTOP
OAT
(°C)
NL
% NTOP
NH
% NTOP
- 50
95.40
97.60
- 40
95.60
97.63
- 30
95.80
97.66
- 20
95.95
97.70
- 10
96.45
97.80
0
97.05
98.00
+ 10
97.50
98.18
+ 20
97.80
98.32
+ 30
98.20
98.50
+ 40
98.25
98.70
+ 50
98.28
98.85
9) The Normal Take-off NH limit for a given air temperature is given in the following table:
Table 4 - Starter Cranking Limits
AOM DASH 8-Q400
Start
MAX Time ON
... Followed by Time OFF
1
70 s
2 min
2
70 s
2 min
3
70 s
30 min
CHAPTER 1
1.11-4
LIMITATIONS
[Rev. X] 31 MAY 2011
1.11.4.3
Engine and Propeller Ground Operating Limitations
1) Maximum torque is 100%.
2) Minimum NH is 64.2%.
3) Maximum wind speed for ground operation, with the nose of the airplane more than 30° out of wind is 50 kt
4) For wind speeds greater than 8 kt, with the nose of the airplane more than 30° out of wind, the maximum
power for ground maneuvering is as follows:
Maximum Power for Ground Maneuvering
Wind Speed
(kt)
9 to 20
21 to 35
36 to 50
(gusts to 55)
NOTE:
Maximum Power Setting
(Ground Maneuvering)
FLIGHT IDLE
(POWER levers may be momentarily increased above
FLIGHT IDLE for acceleration)
FLIGHT IDLE
FLIGHT IDLE
(POWER levers must be at DISC with airplane static)
Ground operations in winds greater than 50 kt must be recorded and the maximum wind
speed provided to maintenance within 24 h (flying day).
5) For wind speeds greater than 8 kt, with the nose of the airplane more than 30° out of wind, the maximum
power for ground static operation is as follows:
Maximum Power for Ground Static Running
Wind Speed
(kt)
9 to 20
21 to 35
36 to 50
(gusts to 55)
1.11.4.4
Maximum Power Setting
(Ground Static Running)
POWER levers angle at 60°
(Approximately midway between
FLIGHT IDLE and Take-off Power detent)
FLIGHT IDLE
DISC
Engine Airborne Operating Limitations
During flight operation movement of the POWER levers aft of the FLT IDLE gate is prohibited.
Minimum SAT for engine relight is - 40°C.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.11.4.5
1.11-5
[Rev. 2] 2 DEC 2011
Oil Limitations
PRESSURE
Oil Pressure minimum .......................................................................................................................... 44 psi
Normal operating range ............................................................................................................... 61 to 72 psi
Transient minimum ...................................................................................................................... 44 to 61 psi
TEMPERATURE
Oil Temperature for start up ..................................................................................................................- 40°C
GND IDLE
Minimum ...............................................................................................................................................- 40°C
Maximum ......................................................................... 107°C (125°C PLA between FLT IDLE and DISC)
Above GND IDLE
Minimum ........................................................................................ 0°C (55°C for take-off in icing conditions)
Maximum ..............................................................................................................................................107°C
Maximum Continuous ...........................................................................................................................107°C
APPROVED OILS
→ refer to the Aircraft Maintenance Manual (AMM)
1.11.4.6
Engine Rating Limitations
The pilot should set the torque to the target bug to obtain the required rating.
•
This target-bug rating should not be exceeded deliberately except in an emergency situation.
•
Setting can be found in the normal checklist and in the AOM, Chapter 4.
Maximum Take-Off (MTOP) (5071 SHP) 106% TRQ
•
This is the maximum power on the operating engine certified and is time limited to 5 min (or 10 min when
approved in an AFM Supplement).
Normal Take-Off (NTOP) (4580 SHP) 90.3% TRQ
•
This is the take-off power developed under normal take-off conditions.
Maximum Continuous (MCP) ................................................................................................................100%
•
The maximum continuous power rating is the maximum power certified for continuous use.
This rating should only be used when required to ensure safe flight (i.e. engine failure).
1.11.4.7
Engine Ice Protection
Engine intake by-pass doors must be open for engine operation in icing conditions.
NOTES:
1. Icing conditions exist when the SAT on the ground and for take-off is 10°C or below, or SAT in flight
is 5°C or below and visible moisture in any form is present (such as clouds, fog with visibility of one
mile or less, rain, snow, sleet or ice crystals).
Ice accretion on aerodynamic surfaces is not considered to exist at temperatures of - 40°C or
below.
2. Icing conditions also exist when the SAT on the ground and for take-off is 10°C or below when operating on ramps, taxiways or runways where surface snow, ice, standing water or slush may be
ingested by the engines or freeze on engines, nacelles or engine sensor probes.
AOM DASH 8-Q400
CHAPTER 1
1.11-6
LIMITATIONS
[Rev. 8] 13 SEP 2013
1.11.4.8
Instrument Limitation Markings
Colour-coded markings representing operating limits and ranges are presented on the Engine Display (ED) to
facilitate observance.
Torque Indicators (%)
Over-Limit
(red pointer / digits)
above 106
Maximum
(red radial)
106
Caution
(yellow arc)
100 to 106
Normal Operating
(green arc)
0 to 100
Turbine Temperature Indicators (ITT) (°C)
Over-Limit
(red pointer / digits)
above MAX (red radial),
above 920 transient (start only)
Maximum – starting
(red radial)
920
Maximum
(red radial)
Limit shown in Table 2 (Sub-Chapter 1.11.4.2) for NTOP rating,
880 for MTOP and MCP rating
Normal Operating
(green arc)
250 to Limit shown in Table 2 (Sub-Chapter 1.11.4.2) for NTOP rating,
250 to 880 for MTOP and MCP rating
Propeller RPM Indicators (NP)
Over-Limit
(red pointer / digits)
above 1071
Maximum
(red radial)
Caution
(yellow arc)
Normal Operating
(green arc)
1071
1020 to 1071
660 to 1020
Gas Generator (High Pressure) Rotor Speed Indicator (NH)
Over-Limit
(red pointer / digits)
above MAX (red radial)
Maximum
(red radial)
Limit shown in Table 3 (Sub-Chapter 1.11.4.2) for NTOP rating,
100% for MTOP and MCP rating
Normal Operating
(green arc)
64.2% to NH maximum limits shown above
Gas Generator (Low Pressure) Rotor Speed Indicator (NL)
Over-Limit
(red digits)
Limit shown in Table 3 (Sub-Chapter 1.11.4.2) for NTOP rating,
above 100% for MTOP and MCP rating
Normal Operating
(white digits)
0% to NL maximum limits shown above
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.11-7
[Rev. 8] 13 SEP 2013
Instrument Limitation Markings (cont’d)
Oil Temperature Indicator (°C)
Over-Limit
(red pointer / digits)
Maximum
(red radial)
above MAX (red radial),
below - 40
107, - 40
except as specified below
125, - 40
with POWER levers between DISC and FLIGHT IDLE
107 to 125
for conditions where red radial is at 125
Caution
(yellow range)
- 40 to 0
with PROP selector OFF
- 40 to 55
(changing to 65, 3 min after take-off)
with PROP selector TEST or ON
Normal Operating
(green arc)
0 to 107
with PROP selector OFF
55 (changing to 65, 3 min after take-off) to 107
with PROP selector TEST or ON
Oil Pressure Indicator (psi)
Under-Limit
(red pointer / digits)
below 44
Minimum
(red radial)
44
Caution
(yellow arc)
44 to
Low Pressure
(warning light)
44 to 50
Normal Operating
(green arc)
61 and 72 to 100
61 to 72
Fuel Temperature Indicator (°C)
Over-Limit
(red digits)
Caution
(yellow digits)
Normal Operating
(white digits)
AOM DASH 8-Q400
above 71
below 0
0 to 71
CHAPTER 1
1.11-8
LIMITATIONS
[Rev. 13] 30 JAN 2015
1.11.5
APU Limitations
NOTE:
This Sub-Chapter corresponds to Supplement 6 of the AFM
1) APU is approved for GROUND OPERATIONS ONLY.
2) APU must be shutdown prior to take-off.
3) APU must not be operated unattended with passengers onboard.
4) APU must not be operated during gravity refuelling.
5) APU ambient temperature limitation (Lower) - 54oC
NOTE:
When the APU has been shut-down in outside air temperatures below - 35oC for greater than
1 h, it must be preheated prior to start in accordance with applicable maintenance procedures.
6) APU ambient temperature limitation (Upper):
a) + 30°C or ISA + 25°C, whichever is lower,
b) + 50°C or ISA + 35°C, whichever is lower (with MS 4-900136 or MS 4-900137 Incorporated)
7) With APU Inlet Louvres (MS 4-428900) installed, APU operation is limited to + 21°C maximum ambient
temperature.
8) Fuel: Approved Fuel Specifications are listed in Sub-Chapter 1.11.6.1.
9) Oil:
MIL-L-7808, MIL-L-23699C, Castrol 98UK or Mobile Jet II.
Do Not mix oils.
10) APU Starter Cranking Limits:
START
1
2
NOTE:
MAX Time ON
60 s
60 s
... Followed by Time OFF
5 min
Maintenance Action Required
Including the time taken for the maintenance action following the second start attempt, a
minimum of 30 min off must elapse prior to the next start attempt.
AOM DASH 8-Q400
CHAPTER 1
1.11-9
LIMITATIONS
1.11.6
Fuel Limitations
1.11.6.1
Fuel Grades
[Rev. 12] 30 SEP 2014
Fuels conforming to any of the following specifications are approved for use. Mixing of fuels is permitted.
SPECIFICATION
TYPE
CANADIAN
USA
CIS
CHINESE
GOST 10227
GOST 10227
JET FUEL # 3 (RP-3)
-
KEROSENE
JET A, JET A1
JP-5
JP-8
JP-8 + 100
RT
TS-1
CGSB 3.23
CGSB 3-GP-24
-
ASTM D 1655
MIL-DTL-5624
MIL-DTL-83133
MIL-DTL-83133
-
WIDE CUT (PWC SB 35189 Incorporated)
JET B
JP-4
CGSB 3.22
CGSB 3.22
ASTM-D1655
MIL-DTL-5624
-
-
WARNING: With PWC SB 35189 Not Incorporated, the use of Wide Cut Type fuels is prohibited.
Dispatch with Wide Cut type fuels is prohibited with an Outside Air Temperature (OAT) or Static Air Temperature (SAT) warmer than - 20°C.
NOTE: When using JET B or JP-4, if fuel tank temperature on the FUEL page of the MFD exceeds
35°C, the maximum operating altitude is 20000 ft.
NOTE: When using JP-8 + 100 fuel, the refuel distribution system must meet the requirements as
published in the industry standards.
REFERENCE: (a) API / IP-1581: Specifications and Qualification Procedures for
Aviation Jet Fuel Filter / Separators, 5th Edition. Category ‘M100’.
(b) CSA-B836: Storage, Handling and Dispensing of Aviation Fuels at Aerodromes.
NOTE: Maintenance must be notified when using TS-1 fuel.
1.11.6.2
Minimum Fuel Tank Temperature
The minimum operating fuel tank temperature must not be less than 5°C above the freezing temperature of the
fuel being used.
FREEZING TEMPERATURE
(°C)
FUEL TYPE
ALLOWED BULK
FUEL TEMPERATURE
(°C)
KEROSENE
JET A
- 40
- 35
JET A1, JP-8, JP-8 + 100, JET FUEL # 3 (RP-3)
- 47
- 42
JP-5
- 46
- 41
RT
- 55
- 50
TS-1
- 60
- 55
WIDE CUT (PWC SB 35189 Incorporated)
JET B
- 50
- 45
JP-4
- 58
- 53
AOM DASH 8-Q400
CHAPTER 1
1.11-10
LIMITATIONS
[Rev. 13] 30 JAN 2015
NOTE:
If the fuel tank contains different fuel grades, the highest fuel freezing temperature of the fuel
grades in the tank must be used.
To ensure that the freezing point of the fuel is maintained, the refueled tank should contain a
minimum of 90% of the fuel grade with the lowest fuel freezing temperature.
1.11.6.3
Fuel Additives
The following fuel system ice inhibitors are approved for use with approved fuels:
FUEL SYSTEM ICE INHIBITOR
CANADIAN and USA
MIL-DTL-85470
Maximum concentration of 0.15% by volume.
1.11.6.4
CIS
Fluid I
Fluid I - M
Fluid TGF
Fluid TGF - M
(GOST 8313)
(TU 6-10-1458)
(GOST 17477)
(TU 6-10-1457)
Maximum concentration of 0.3% by volume.
Usable Fuel
Fuel remaining in fuel tanks when quantity indicators show zero fuel is not usable in flight.
Usable fuel tank capacities are 2659 kg (5862 lb) per tank.
1.11.6.5
Auxiliary Fuel Pumps
Tank 1 and Tank 2 auxiliary fuel pumps must be on for take-off and landing.
1.11.6.6
Fuel Heater
Take-of and continuous in-flight operation with fuel heater outlet temperature indication below 0°C or above
71°C is PROHIBITED.
1.11.6.7
Maximum Fuel Imbalance
Maximum fuel imbalance between contents of main fuel tanks is 272 kg (600 lb).
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.11.7
1.11-11
[Rev. 12] 30 SEP 2014
Air Conditioning and Pressurization
Normal cabin pressure differential limit
5.46 ± 0.1 psid
Maximum cabin pressure differential limit
5.95 psid
Maximum cabin pressure differential limit during taxiing, take-off and landing 0.5 psid
Maximum cabin altitude (pressurized flight)
8000 ft
Bleed air must be off for take-off and landing.
1.11.8
Electrical Systems
STANDBY BATTERY, AUX BATTERY and MAIN BATTERY
Maximum loadmeter reading for take-off .............................................................................................. = 0.1
Minimum battery temperature for take-off ........................................................................................... - 20°C
MAIN & ESSENTIAL BUSES
Integrated Flight Cabinet
Power-up requires a minimum 23 V DC respective main and essential busses.
1.11.9
Landing Gear and Flap Systems
Maximum altitude with the landing gear and / or flap extended is 15000 ft.
1.11.10
Wheel Brake Cooling Limits
Brake cooling times must be observed between a landing or a low-energy rejected take-off and a subsequent
take-off, to ensure that sufficient brake energy is available to bring the airplane to a complete stop if the subsequent take-off is rejected.
REFERENCE: AFM Sub-Section 5.12 and AOM Chapter 4.
1.11.11
Airframe Ice Protection
When ice is detected, the AIRFRAME MODE SELECT selector must be positioned at FAST or SLOW.
AOM DASH 8-Q400
CHAPTER 1
1.11-12
[Rev. 16] 7 MAR 2016
1.11.12
LIMITATIONS
Automatic Flight Control System (AFCS)
1) AFCS is approved for autopilot (AP) approaches to CAT I limits only.
2) In APPR mode, AP engaged approaches are approved for:
a. Flap 0° (minimum altitude: 1000 ft AGL),
b. Flap 5°, 10° and 15° [MS 4-126091 Incorporated]
c. Flap 15° [MS 4-126091 Not Incorporated]
3) The use of Flap 35° in APPR mode with AP engaged is prohibited.
4) With [MS 4-126091 Not Incorporated], Flight Director (FD) only approaches are prohibited.
5) AP must be disengaged in severe icing.
6) During AP operation, the pilot must be seated at the controls with harness secured.
7) Use of VOR without associated DME is prohibited in APPR mode.
8) After take-off or go-around, the minimum height for AP engagement is 1000 ft AGL.
9) For non-precision approaches the AP must be disengaged at or above 200 ft AGL.
10) Flight in conditions of severe atmospheric turbulence with AP engaged is prohibited.
11) An AP approach must not be commenced or continued with an inoperative engine.
NOTE:
The AP must be disengaged at or above 1000 ft AGL
12) AP and FD only approaches are approved for glideslope (G/S) angles of 2.5° to a maximum of 4°.
13) AP approaches have been demonstrated in crosswind components up to 18 kt
15 kt [with MS 4-126091 Not Incorporated].
This is not considered limiting.
14) On precision approaches, the AP must be disengaged at or above a minimum altitude of 200 ft AGL.
1.11.13
Avionics
1) HOT MIC select switches on the pilot and the co-pilot ARCDU must be OFF and the INT / RAD switch on
the observers Audio Control Panel must be centred, when using the flight compartment speakers.
2) With HF Comm installed, use of the HF transmitter is prohibited when the ADF is used as the prime means
of navigation or for position confirmation.
3) With Integrated Standby Instrument [MS 4-432835 or MS 4-456883] installed, the airplane must not be
operated further than 1 h flying time from a suitable airport for landing.
4) To ensure uninterrupted operation of the pilot’s and co-pilot’s PFD, MFD and the ED, electrical power must
be cycled on all displays once every 24 h (flying day).
5) With [MS 4-459347 Incorporated] or subsequent Bombardier IFE modsums, the In-Flight Entertainment
(IFE) system has been approved for use with Transmitting Portable Electronic Devices (TPEDS) operating
in ‘Airplane Mode’ with only ‘Wi-Fi Mode’ active in all phases of flight.
The IFE power is controlled by the Flight Attendant through a switch located on the IFE crew terminal
1.11.14
Flight Management System (FMS)
For specific FMS limitations, please refer to the respective AFM Supplement and the FMS Operator’s Manual.
AOM DASH 8-Q400
CHAPTER 1
LIMITATIONS
1.11.15
1.11-13
[Rev. 12] 30 SEP 2014
Data Link System
NOTE:
This procedure corresponds to:
- AFM Supplement 81: UniLink UL-701 Data Link System
- AFM Supplement 109: UniLink UL-801 Data Link System
The limitations in Section 2 (AFM) and the Supplement Compatibility Table in Sub-Section 1.5 (AFM) are applicable with the addition of the following:
1.
The Data Link System is approved for the transmission and receipt of messages that will not create an
unsafe condition, if the message is improperly received.
An unsafe condition may exist if:
a. The message or part of a message is delayed or not received;
b. The message is delivered to the wrong recipient;
c. The message content is corrupted.
2.
Pilot action, based on messages such as pre-departure clearance, digital automatic terminal information
service, weight and balance, take-off data (speeds, trim settings, runway distances), is prohibited unless
approved operational procedures are used to verify that the message is received by the intended recipient,
the message is valid and the content is not corrupted.
1.11.16
Enhanced Ground Proximity Warning System (EGPWS) - HONEYWELL MK V
(Option - CR 831 CH 00064 or CR 831 SO 90180)
NOTE:
This Sub-Chapter corresponds to Supplement 64 of the AFM
The limitations in Section 2 (AFM) and the Supplement Compatibility Table in Sub-Section 1.5 (AFM) are applicable with the addition of the following:
1.
Pilots are authorized to deviate from their current air traffic control clearance (ATC) to the extent necessary
to comply with an EGPWS warning.
2.
Navigation must not be predicated upon the use of Terrain / Obstacle Awareness Display on the MFD.
NOTE:
3.
The Terrain / Obstacle Awareness Display is intended to serve as a situational awareness tool
only and may not provide the accuracy and / or fidelity on which to solely base terrain
avoidance maneuvering.
To avoid giving unwanted alerts, the Terrain Awareness Alerting and Display function must be inhibited by
selecting the TERRAIN Inhibit switch on the glareshield panel, when within 15 NM of take-off, approach or
landing of an airport not contained in the EGPWS Airport Database.
Refer to Honeywell Worldwide Airport Database PN: 060-4267-000 for airports contained in the installed
EGPWS terrain database.
4.
The following ModSums must be incorporated concurrently:
- Display Unit
- MS 4-126103
- Flight Guidance Module
- MS 4-126128
- Flight Data Processing System - MS 4-126127
and are required pre-requisites for this installation.
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AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
ToC 2-1
[Rev. 13] 30 JAN 2015
- TABLE OF CONTENTS 2.0
NORMAL PROCEDURES ...................................................................................................... 2.0-1
2.0.1
Introduction ............................................................................................................................. 2.0-1
2.0.2
General ................................................................................................................................... 2.0-1
2.0.3
Normal Checklists ................................................................................................................... 2.0-3
2.0.4
Automatic Flight Control System (AFCS) ............................................................................... 2.0-4
2.0.5
Navigation Systems ................................................................................................................ 2.0-4
2.0.6
Standard Callouts ................................................................................................................... 2.0-5
2.1
PRE-FLIGHT .......................................................................................................................... 2.1-1
2.1.1
Exterior and Interior Inspection ............................................................................................... 2.1-1
2.1.2
Exterior Inspection - Walkaround Sequence (TBD) ................................................................ 2.1-2
2.2
PRE-DEPARTURE ................................................................................................................. 2.2-1
2.2.1
Take-off Briefing ...................................................................................................................... 2.2-1
2.2.2
Rejected Take-off Briefing ....................................................................................................... 2.2-1
2.2.3
Flight Director Setup (TBD) .................................................................................................... 2.2-1
2.2.4
Engine Start ............................................................................................................................ 2.2-2
2.3
ALTIMETER SETTING and CHECKING ............................................................................... 2.3-1
2.3.1
Altitude Tolerances ................................................................................................................. 2.3-1
2.4
TAXI and TAKE-OFF .............................................................................................................. 2.4-1
2.4.1
Push Back - Towbar ................................................................................................................ 2.4-1
2.4.2
Push Back - Towbarless ......................................................................................................... 2.4-1
2.4.3
Power Back - Taxi in Reverse ................................................................................................. 2.4-1
2.4.4
Taxiing .................................................................................................................................... 2.4-1
2.4.5
Normal Take-off ...................................................................................................................... 2.4-2
2.4.6
Take-off with Reduced Power ................................................................................................. 2.4-4
2.4-7
Take-off with Maximum Take-off Power and Uptrim Disabled ................................................ 2.4-4
2.4.8
Take-off with Bleeds “ON” ...................................................................................................... 2.4-5
2.4.9
Crosswind Take-off ................................................................................................................. 2.4-5
2.4-10
Operation in Tailwinds between 10 and 20 kt ......................................................................... 2.4-5
2.4.11
Noise Abatement Procedures ................................................................................................. 2.4-5
2.5
CLIMB, CRUISE and DESCENT ............................................................................................ 2.5-1
2.5.1
Normal Climb .......................................................................................................................... 2.5-1
2.5.2
Cruise ..................................................................................................................................... 2.5-1
2.5.3
Descent .................................................................................................................................. 2.5-1
2.5.4
Holding ................................................................................................................................... 2.5-1
2.5.5
Fuel Management ................................................................................................................... 2.5-2
AOM DASH 8-Q400
CHAPTER 2
ToC 2-2
[Rev. 13] 30 JAN 2015
NORMAL PROCEDURES
- TABLE OF CONTENTS - (cont’d)
2.6
APPROACH, LANDING PREPARATION and BRIEFING ..................................................... 2.6-1
2.6.1
Approach Briefing .................................................................................................................... 2.6-1
2.6.2
Use of Flaps ............................................................................................................................ 2.6-1
2.6.3
Flight Director Setup (TBD) ..................................................................................................... 2.6-1
2.6.4
Approach with Bleeds “ON” ..................................................................................................... 2.6-1
2.6.5
VFR Approach ......................................................................................................................... 2.6-1
2.6.6
Steep Approach and ILS Raw Data Only Steep Approach ..................................................... 2.6-2
2.6.7
Go-Around from Final Approach ............................................................................................. 2.6-2
2.6.8
Engine Torque Split Between Engines .................................................................................... 2.6-2
2.7
NORMAL LANDING ............................................................................................................... 2.7-1
2.7.1
General ................................................................................................................................... 2.7-1
2.7.2
Landing ................................................................................................................................... 2.7-1
2.7.3
Crosswind Landing Technique ................................................................................................ 2.7-3
2.7.4
Normal Landing in Tailwinds Between 10 and 20 kt ................................................................ 2.7-3
2.7.5
Noise Abatement Procedures (Landing with 850 RPM Propeller) .......................................... 2.7-3
2.7.6
Operation from Unpaved / Gravel Runways ........................................................................... 2.7-3
2.8
POST LANDING ..................................................................................................................... 2.8-1
2.8.1
After Landing ........................................................................................................................... 2.8-1
2.8.2
Shutdown ................................................................................................................................ 2.8-1
2.9
OPERATION ON CONTAMINATED RUNWAYS ................................................................... 2.9-1
2.9.1
General ................................................................................................................................... 2.9-1
2.9.2
Limitations ............................................................................................................................... 2.9-2
2.9.3
Normal Procedures ................................................................................................................. 2.9.2
2.9.4
Performance Data ................................................................................................................... 2.9-3
2.10
FLIGHT PROFILES .............................................................................................................. 2.10-1
Figure 2.10-1 Normal Take-off .............................................................................................. 2.10-1
Figure 2.10-2 Visual Approach and Landing ......................................................................... 2.10-2
Figure 2.10-3 Circling Approach ........................................................................................... 2.10-3
Figure 2.10-4 Precision Approach ......................................................................................... 2.10-4
Table 2.10-1 Precision Approach and Landing Procedures .................................................. 2.10-5
Figure 2.10-5 CAT II Precision Approach .............................................................................. 2.10-6
Table 2.10-2 CAT II Precision Approach and Landing Procedures ....................................... 2.10-7
Figure 2.10-6 Non Precision Approach ................................................................................. 2.10-8
Table 2.10-3 Non Precision Approach and Landing Procedure ............................................ 2.10-9
Figure 2.10-7 Missed Approach .......................................................................................... 2.10-10
Table 2.10-4 Missed Approach Procedure .......................................................................... 2.10-11
Figure 2.10-8 Balked Landing ............................................................................................. 2.10-12
Table 2.10-5 Balked Landing Procedure ............................................................................. 2.10-13
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
ToC 2-3
[Rev. 13] 30 JAN 2015
- TABLE OF CONTENTS - (cont’d)
2.11
AIRWORK and BASIC FLIGHT TECHNIQUES .................................................................... 2.11-1
2.11.1
Steep Turns ........................................................................................................................... 2.11-1
2.12
LOW VISIBILITY OPERATION ............................................................................................ 2.12-1
2.12.1
Category II Operation ........................................................................................................... 2.12-1
2.12.2
Low Visibility Take-off ........................................................................................................... 2.12-2
2.13
GPWS OPERATION ............................................................................................................ 2.13-1
2.13.1
EGPWS (Enhanced Ground Proximity Warning System Honeywell MK V) ......................... 2.13-1
2.13.1.1
Flight Compartment Check - Power ON ............................................................................... 2.13-1
2.13.1.2
In-Flight Response to Warnings ........................................................................................... 2.13-1
2.13.1.3
Normal Approach .................................................................................................................. 2.13-3
2.14
TCAS OPERATION ............................................................................................................. 2.14-1
2.14.1
ACAS II / TCAS II ................................................................................................................. 2.14-1
2.14.1.1
ACAS II / TCAS II Operating Characteristics ........................................................................ 2.14-1
2.14.1.2
Traffic Advisory (TA) Announcements .................................................................................. 2.14-1
2.14.1.3
Resolution Advisory (RA) Announcements ........................................................................... 2.14-2
2.14.1.4
In-Flight Use of TCAS ........................................................................................................... 2.14-3
2.14.2
Mode S Transponder System for Elementary and Enhanced Surveillance .......................... 2.14-4
2.14.2.1
Normal Procedures ............................................................................................................... 2.14-4
2.14.2.1.1 Pre-Taxi Checks ................................................................................................................... 2.14-4
2.15
COLD WEATHER OPERATIONS ........................................................................................ 2.15-1
2.15.1
Airplane Contamination on the Ground - Frost, Ice or Snow ................................................ 2.15-1
2.15.2
Ground De-Icing / Anti-Icing ................................................................................................. 2.15-1
2.15.3
De-Icing Procedures ............................................................................................................. 2.15-3
2.15.4
De-Icing and Anti-Icing Fluids ............................................................................................... 2.15-4
2.16
OPERATING IN ICING CONDITIONS ................................................................................. 2.16-1
2.16.1
Taxi ....................................................................................................................................... 2.16-2
2.16.2
Take-Off ................................................................................................................................ 2.16-2
2.16.3
Enroute, Climb, Cruise and Descent .................................................................................... 2.16-3
2.16.4
Holding and Approach .......................................................................................................... 2.16-3
2.16.5
Landing ................................................................................................................................. 2.16-4
2.16.6
Parking ................................................................................................................................. 2.16-4
AOM DASH 8-Q400
CHAPTER 2
ToC 2-4
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
- TABLE OF CONTENTS - (cont’d)
2.17
NORMAL EXPANDED PROCEDURES and CHECKLISTS ............................................. 2.17-1
2.17.1
FLIGHT COMPARTMENT PREPARATION ...................................................................... 2.17-1
2.17.1.1
PREFLIGHT ....................................................................................................................... 2.17-1
2.17.2
FLIGHT COMPARTMENT PREPARATION - POWER OFF ............................................. 2.17-1
2.17.2.1
For DC External Power ...................................................................................................... 2.17-2
2.17.2.2
For APU Power .................................................................................................................. 2.17-3
2.17.2.3
For Battery Power Only ..................................................................................................... 2.17-4
2.17.2.4
Start Approved (Battery Power Only) ................................................................................. 2.17-5
2.17.3
FLIGHT COMPARTMENT PREPARATION - POWER ON .............................................. 2.17-7
2.17.3.1
Captain ............................................................................................................................... 2.17-7
2.17.3.2
First Officer ...................................................................................................................... 2.17-17
2.17.4
FLIGHT COMPARTMENT PREPARATION CHECKLIST .............................................. 2.17-18
2.17.5
NORMAL CHECKLIST .................................................................................................... 2.17-23
2.17.5.1
Originating Before Start .................................................................................................... 2.17-23
2.17.5.2
Before Start ...................................................................................................................... 2.17-24
2.17.5.3
Start Approved ................................................................................................................. 2.17-25
2.17.5.4
After Start ......................................................................................................................... 2.17-26
2.17.5.5
System Check Once Every 24 h (Flying Day) .................................................................. 2.17-29
2.17.5.6
Taxi Check ....................................................................................................................... 2.17-36
2.17.5.7
Line-up ............................................................................................................................. 2.17-38
2.17.5.8
After Take-off .................................................................................................................... 2.17-40
2.17.5.9
Cruise .............................................................................................................................. 2.17-42
2.17.5.10
Descent ............................................................................................................................ 2.17-43
2.17.5.11
Approach ......................................................................................................................... 2.17-44
2.17.5.12
Landing ............................................................................................................................ 2.17-46
2.17.5.13
After Landing .................................................................................................................... 2.17-47
2.17.5.14
Shut-down ........................................................................................................................ 2.17-48
2.17.5.15
Last Flight ........................................................................................................................ 2.17-49
2.17.5.16
Ice Protection Procedures ............................................................................................... 2.17-50
2.17.5.16.1
Take-off in or into Icing Conditions ................................................................................... 2.17-50
2.17.5.16.2
Flight in Icing Conditions .................................................................................................. 2.17-51
2.17.5.16.3
Flight in Severe Icing ....................................................................................................... 2.17-53
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.0
NORMAL PROCEDURES
2.0.1
Introduction
2.0-1
[Rev. X] 31 MAY 2011
The Procedures described herein are intended to facilitate the safe and expeditious operation of the Dash 8, in
both an operational and training environment. It is essential that both crew members have a thorough knowledge of the procedures, and adhere to them unless the safety of the flight dictates otherwise.
This document consists of five Sections:
General Information
Describes policies regarding crew co-ordination, checklist procedures, use of the Autoflight Control System
(AFCS) and standard calls.
Normal Operating Procedures
Normal Operations for normal flight and Operation on Wet and Contaminated Runways.
Flight Procedures
This Section supplements the Normal Operating Procedures by providing detailed information on how to operate the aeroplane. It also describes some flight maneuvers and procedures which will be required for simulator
and flight training.
Special Procedures
Described herein are Procedures concerning Low Visibility, GPWS and TCAS Operation.
Normal Procedures and Checklists
The expanded Normal Procedures and Checklists for daily Operation.
2.0.2
General
2.0.2.1
Application of Normal Procedures
Normal Procedures are performed by ‘challenge and response’, ‘read and do’, or silent according to
Table 2.0-2.
2.0.2.2
Crew Co-ordination
Crew co-ordination is an essential part of every successful flight. It is the responsibility of each crew member to
be familiar with his/her responsibilities and execute them in a professional and timely manner. Each member of
the crew must also be familiar with responsibilities of other crew members.
2.0.2.3
Chain of Command
In order of priority:
1.
Pilot-in-command
2.
Second-in-command or copilot/First Officer
(2IC or F/O)
3.
Senior Cabin Crew Member
Cabin Crew Member
(CA 1)
(CA2 + CA3)
2.0.2.4
(PIC)
Pilot Duties
The inflight duties of the pilots are interchangeable. Therefore the terminology Pilot Flying (PF) and Pilot Not
Flying (PNF) will be used to distinguish pilot duties. When the First Officer (2IC) is the PF, the Commander
(PIC) assumes the PF duties until the aeroplane is lined up for Take-off and, once again, takes over PF duties
when the aeroplane has decelerated to 50 Knots, after landing.
2.0.2.5
Change of Pilot Control
The PF/PNF duties may be exchanged during flight. The pilot relinquishing PF duties will announce; "YOU
HAVE CONTROL". The pilot assuming control will announce; "I HAVE CONTROL".
AOM DASH 8-Q400
CHAPTER 2
2.0-2
[Rev. X] 31 MAY 2011
2.0.2.6
NORMAL PROCEDURES
Communications
ATC Communications:
The PNF will normally handle all communications with ATC unless otherwise directed by the PF.
Flight Deck / Cabin Crew Communications:
The PF will normally handle all communications with the cabin crew.
For normal communication use the CALL button to contact the cabin crew. The Senior Cabin Crew Member will
come to the flight deck or respond on the interphone.
During emergency situations, standardized communication between the Pilots and the Cabin Crew Member(s)
is essential. The following is a list of the standard communications to be used during emergency operations.
Table 2.0-1 Flight Deck / Cabin Crew Communications
Action Required
Signal
Notify cabin crew of an emergency
PA: "SENIOR CABIN CREW MEMBER TO THE
FLIGHT DECK"
Alternate: Emergency Lights ON
Evacuate aeroplane
PA: “EVACUATE, EVACUATE, EVACUATE - LEFT (or
RIGHT) SIDE"
Alternate: More than 3 Chimes.
Passengers to brace prior to an emergency landing PA: "BRACE, BRACE, BRACE"
(This call should be made approximately one (1)
minute prior to landing.)
Alternate: More than 3 chimes.
Cabin Crew to resume duties after an emergency
descent
PA: "CABIN CREW RESUME YOUR DUTIES"
Prevent evacuation
PA: "REMAIN SEATED"
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.0.3
Normal Checklists
2.0.3.1
Use of Checklists
2.0-3
[Rev. X] 31 MAY 2011
The normal checklists are organized by phase of flight and assume completion of the previous checklist.
An un-shaded box separating procedural steps (i.e. START APPROVED), defines a logical break that allows
partial completion of the checklist until further action is appropriate.
When the required checklist has been completed, the PNF will announce the appropriate checklist complete,
e.g.: "AFTER TAKE-OFF CHECKLIST COMPLETE".
When the response to a particular checklist item is "as req’d" the actual response will be positive and the action
required will be stated, such as: "ON", "OFF", "CLOSED", etc.
Table 2.0-2 Checklist Conduct
Item
Action
FLIGHT DECK PREPARATION
Read and Do (Flow)
ORIGINATING BEFORE START
Challenge and Response
BEFORE START
Challenge and Response
AFTER START
Challenge and Response
TAXI
Read and Do
Challenge and Response (configuration items: flaps,
trims, and condition levers)
LINE UP
Read and Do
AFTER TAKE-OFF
Read and Do
CRUISE
Read and Do
DESCENT
Read and Do
APPROACH
Read and Do
LANDING
Challenge and Response (Landing Gear, Flaps, and
Condition Levers)
Read and Do (remaining items)
AFTER LANDING
Read and Do
SHUTDOWN
Challenge and Response
LAST FLIGHT
Challenge and Response
AOM DASH 8-Q400
CHAPTER 2
2.0-4
[Rev. X] 31 MAY 2011
NORMAL PROCEDURES
2.0.4
Auto Flight Control System (AFCS)
2.0.4.1
Flight Director
To reduce crew work load and improve safety, use of the Flight Director / Autopilot is recommended from initial
climb out to final approach. During normal operations the PF should select the Flight Guidance Controller
(FGC) to his or her side. Selected AFCS modes must be confirmed on the PFD’s.
When the PF controls the aeroplane manually, the PNF normally selects the AFCS modes as directed by the
PF.
2.0.4.2
Use of Flight Director
The Flight Director should be used for most phases of flight. When the Flight Director is being used, care must
be taken to ensure it is providing correct commands.
2.0.4.3
Autopilot
When the PF engages or disengages the Autopilot (AP) he or she should announce: "AP ENGAGED" or "AP
DISENGAGED".
When the Autopilot is engaged the PF should control all AFCS modes.
Minimum height for Autopilot engagement after take-off or go-around is 1000 ft AGL.
Select flight guidance modes as required.
AP pushbutton...........................................................................................................................................Press
Check AP advisory pointers illuminate and AP is displayed on PFD’s.
NOTES:
1. In the event of an engine failure disengage the autopilot.
Except for approach, the autopilot may be re-engaged following re-trimming.
2. If HSI transfer is selected, all flight guidance modes will disengage and the autopilot will
revert to basic lateral and pitch modes.
Re-select flight guidance modes as required following HSI transfer.
3. With the autopilot engaged, POWER and SPEED changes may require the pilot to manually re-trim the rudder. Trimming should be accomplished with TCS button pressed or autopilot disengaged.
4. If FD XXX (NAV or ADC) DATA INVLD message appears on PFD, select an alternative
flight guidance mode or press STBY on FGCP to clear the message.
5. With MS 4-126360 incorporated: To de-select altitude select mode, press and hold the ALT
SEL pushbutton for greater than 1 second.
2.0.4.4
Autopilot Operation in Turbulence
Disengage Autopilot in severe turbulence. The Autopilot is approved for normal operations in light or moderate
turbulence only.
2.0.4.5
Autopilot Approach
Flap should be extended to approach setting 5°, 10° or 15° before glide slope capture on a precision approach
or before commencing final descent to minimum descent altitude (MDA).
2.0.4.6
Altitude Select
Changes of selected altitude should be followed by selection of Altitude Select (ALT SEL) on the FGC (unless
the ALT SEL has already been selected). ALT SEL shall be visually confirmed by both pilots on the PFD’s.
2.0.5
NOTE:
2.0.5.1
Navigation Systems
VOR symbol may not always be visible on the navigation page of the MFD. With FMS off or
not installed, two pushes on the EFCP DATA button are required to return the VOR Navaid
symbol to the NAV page.
Flight Management System
For specific FMS operational information, please refer to the respective AFM Supplement and the FMS Operator’s Manual.
AOM DASH 8-Q400
CHAPTER 2
2.0-5
NORMAL PROCEDURES
2.0.6
[Rev. 1] 21 NOV 2011
Standard Callouts
Safety demands that crew members remain aware of airplane position, altitude, and instrument indications
during flight.
One method of achieving this is to adopt a system of standard calls to reduce ambiguity and to minimize conversation during critical phases of flight, i.e. take-off, approach and landing.
It is recommended that crews refrain from all non-essential and distracting conversation below 10000 ft ASL.
Tables 2.0-4 to 2.0-7, outline a series of standard calls, which shall be used to enhance safety during VFR and
IFR operations.
The PNF shall make the appropriate call, based on instrument indications or observations for the condition outlined in the table and the PF shall verify and acknowledge the call.
If the PNF does not make the required callout, then the PF shall make it.
Table 2.0-4 Standard Call Procedures All Phases Of Flight
Observations
Call (PNF)
Response (PF)
Any time bank angle exceeds 30°
"BANK"
"CORRECTING"
Heading ± 10°
"HEADING"
"CORRECTING"
Speed Deviations + 10 / - 0 KNOTS
"SPEED"
"CORRECTING"
ALT Deviations ± 100 ft
"ALTITUDE"
"CORRECTING"
Table 2.0-5 Standard Call Procedures Climb And Descent
Observations
Call (PNF)
Response (PF)
Approaching transition altitude
"TRANSITION, ALTIMETER
SET 29.92 / 1013"
"29.92 / 1013 SET AND
CROSS CHECKED"
Climb or Descent (1000 ft to go)
"8000 FOR 9000"
"1000 to go"
"ALTITUDE SELECTED"
Altitude Change
"LEAVING FL 190 FOR 3000"
"ALTITUDE SELECTED"
Table 2.0-6 Standard Call Procedures Final Approach Fix Inbound
Observations
Call (PNF)
Response (PF)
Speed deviation VAPP + 10 / - 0 KNOTS
"SPEED"
"CORRECTING"
Rate of descent exceeds 1000 ft/min.
"SINK RATE"
"CORRECTING"
First positive movement of localizer bar
"LOCALIZER ALIVE"
"CHECK"
1 dot localizer deviation
"LOCALIZER"
"CORRECTING"
First positive movement of glide slope
"GLIDESLOPE ALIVE" "CHECK"
1 dot glideslope deviation
"GLIDESLOPE"
"CORRECTING"
VOR approach - one half (1/2) DOT left or right "TRACK"
"CORRECTING LEFT / RIGHT"
NDB approach - 5° left or right of track
"CORRECTING LEFT / RIGHT"
"TRACK"
Table 2.0-7 Standard Call Procedures Landing
Observations
Landing flare and touchdown
AOM DASH 8-Q400
Call (PNF)
Response (PF)
"5 DEGREES"
"CHECK"
"6 DEGREES"
"CORRECTING"
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CHAPTER 2
NORMAL PROCEDURES
2.1
PRE-FLIGHT
2.1.1
Exterior and Interior Inspection
2.1-1
[Rev. X] 31 MAY 2011
Before each flight, an external inspection of the aeroplane is to be performed by the flight deck crew or maintenance personnel to verify it is acceptable for flight.
The exterior inspection has to include the following:
1. Remove main gear safety lock pins.
2. Disengage nosegear lock.
3. Check oxygen discharge indicating disc.
If door locking provisions are installed:
4. Remove airstair and baggage door external locking devices.
Upon entering the aeroplane:
5. Remove all internal locking devices from the forward, right hand, left hand mid-cabin emergency doors and
the right hand aft service door.
For originating flights, complete the flight deck preparation and "ORIGINATING BEFORE START" checklist.
On through flights, only the "BEFORE START" checklist items need to be accomplished. These items include
those systems which require switch repositioning, and items vital to safety of flight. The first crew member
entering the aeroplane will power up the aeroplane using the checklist appropriate to the power supply available.
See page 2.1-2 Exterior Inspection - Walkaround Sequence.
AOM DASH 8-Q400
CHAPTER 2
2.1-2
[Rev. X] 31 MAY 2011
2.1.2
NORMAL PROCEDURES
Exterior Inspection - Walkaround Sequence
- TBD -
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.2
PRE-DEPARTURE
2.2.1
Take-off Briefing
2.2-1
[Rev. X] 31 MAY 2011
After reception of ATC clearance, PF performs the take-off briefing as follows:
-
departure route including first altitude to be maintained as well as respective minimum altitudes.
-
Engine Failure Procedure including acceleration altitude and minimum safe altitude.
-
special aspects (i.e. type of T/O, weather, obstacle situation, noise abatement procedures, etc.).
2.2.2
Rejected Take-off Briefing
The minimum contents of the RTO Briefing consists of:
-
margin to runway limited weight and stop margin available,
-
special aspects (i.e. runway contamination, MEL dispatch items concerning RTO, etc.).
2.2.3
Flight Director Setup
- TBD -
AOM DASH 8-Q400
CHAPTER 2
2.2-2
[Rev. X] 31 MAY 2011
2.2.4
NORMAL PROCEDURES
Engine Start
Before Start:
When ready for start, the Commander (PIC) will call for the "BEFORE START CHECKLIST" (Challenge and
Response).
Engine Start
The engines are started by the Commander (PIC) who will communicate with the ground engineer.
The normal start sequence is right engine (#2) then left engine (#1).
Table 2.2-1 Start Procedure
COMMANDER (PIC)
FIRST OFFICER (2IC)
Engine START select switch - Pull out then set to 2.
Observes SELECT light illuminates.
Calls "CLEAR #2".
Makes sure the area is clear. Calls "#2 CLEAR".
Engine START switch - Press. Make sure START light illuminates.
Starts stopwatch running to time the start.
NOTE:
When conducting an engine start using external
power or the APU, No. 2 engine oil pressure may
momentarily indicate full scale deflection upon
selection of the START switch for No. 1 or No. 2
engine. No. 2 engine oil pressure should immediately return to normal values.
At first indication of NH:
Sets condition lever to START FEATHER.
NOTE:
Fuel flow indication on ED is not accurate until the engine is stable at idle NH.
Check that engine accelerates to above 64.2% NH and ITT does not exceed 920×C.
Check engine START and ENGINE START SELECT switches OFF – observe SELECT and START lights off.
For the appropriate engine, make sure oil pressure is greater than 44 psi, ENG OIL PRESS warning light,
ENG FUEL PRESS and ENG HYD PUMP caution lights off.
NOTES:
1. Engine START light will remain illuminated for approximately 15 seconds after engine
START and SELECT switches off.
2. At low fuel levels, the TANK FUEL LOW caution lights may take up to four minutes to go
out following engine start.
Repeat start procedure for other engine.
NOTE:
Silent flight deck procedures require only that non-normal situations be announced during the
Start Procedure.
AFTER START:
Once the engines have started the Commander (PIC) will call for the "AFTER START CHECKLIST" (Challenge and Response).
NOTE:
The "Systems Checks" must be accomplished once every 24 hours by the flight crew.
AOM DASH 8-Q400
CHAPTER 2
2.3-1
NORMAL PROCEDURES
2.3
[Rev. X] 31 MAY 2011
ALTIMETER SETTING AND CHECKING
The Altimeter Setting for Flights at or below ‘Transition Altitude’ will be the Regional QNH.
Flights conducted above the Transition Altitude shall use the ‘Standard’ Altimeter Setting of 1013 hPa/29.92 in.
After each setting of the altimeters, the readings on the flight deck shall be compared including standby and
metric (if installed) altimeters when these are used.
2.3.1
Altitude Tolerances
The altitude indications on pilot’s and co-pilot’s PFD have to be compared in several phases of flight.
The primary altimeter readouts have to be within 60 ft, below 5000 ft, varying linearly to 170 ft at 25000 ft.
Cross-check with standby altimeter in case of mismatch. With Integrated Standby Instrument (MS 4-432835 or
MS 4-456883) NOT incorporated, the standby altimeter readings have to be within the following tolerances:
IAS (kt)
ALT (ft)
150 or lower
VMO
1000
940 - 1060
1050 - 1170
5000
4940 - 5060
5100 - 5220
10000
9900 - 10100
10090 - 10290
15000
14850 - 15150
15240 - 15540
20000
19800 - 20200
20260 - 20660
25000
24750 - 25250
25185 - 25685
AOM DASH 8-Q400
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CHAPTER 2
NORMAL PROCEDURES
2.4
TAXI and TAKE-OFF
2.4.1
Push Back – Towbar
2.4-1
[Rev. 18] 21 NOV 2016
The Push Back Manoeuvre is to be performed with Nosewheel Steering switched to off and all 3 green gear
locked down advisory lights illuminated.
2.4.2
Push Back – Towbarless
The Push Back Manoeuvre is to be performed with Nosewheel Steering switched to off.
Operators may continue using the Lektro models 8750 and 8850 towbarless vehicles pending final approval of
the landing gear and airplane structure for the use of towbarless Lektro vehicles.
The use of these towbarless towing vehicles shall be in strict accordance with the manufacturer’s operating
procedures (refer to Ramp Servicing Manual RSM 1-84-2S).
Maximum towing loads / limits must not be exceeded.
2.4.3
Power Back – Taxi in Reverse
For taxiing in reverse use the following procedure:
STEERING Switch .......................................................................................................................... STEERING
Check NOSE STEERING caution light out.
Nosewheel ......................................................................................................................................... Centered
Steering Tiller and Rudder Pedals ................................................................................................... Centered
Do Not use steering tiller or rudder pedals during reverse taxiing.
CAUTION: Exercise extreme care when taxiing in reverse due to the length of the fuselage.
NOTE:
2.4.4
Taxiing in reverse should only be conducted on paved surfaces and in crosswinds less than 10
kt
Taxiing
Once the airplane is clear of congested areas, the PIC will call for the “TAXI CHECKLIST” (Read and Do) .
Taxi checks should be completed early enough so as to allow both pilots to monitor their surroundings while
taxiing to the active runway.
The configuration items on the Taxi Checklist will be Challenge and Response, i.e. Flaps, Trims and Condition
Levers.
If carrying passengers, the senior cabin crew member will come to the flight compartment and report “CABIN
SECURE” for departure.
Take-off clearance will not be accepted until a “CABIN SECURE” has been received.
During the line-up check, notify the cabin crew that take-off is imminent.
2.4.4.1
Operation from Unpaved / Gravel Runways
At the option of the operator, the aircraft may be operated on unpaved / gravel airfields in accordance with the
limitations and procedures contained in this volume and AFM Supplements 25 and 26.
Ground running and taxiing:
POWER Levers ................................................................... Not forward of mid way between FLIGHT IDLE
and DISC when the aircraft is stationary
AOM DASH 8-Q400
CHAPTER 2
2.4-2
[Rev. 9] 28 FEB 2014
2.4.5
Normal Take-off
2.4.5.1
General
2.4.5.2
Line-Up Check
NORMAL PROCEDURES
Once the airplane has been cleared onto the active runway, the PIC calls for the “LINE-UP CHECK” (Read and
Do).
Line-up checks should be done as early as possible, after being cleared to line up on the active runway, to
allow flight attendants to be seated and both pilots to monitor runway surroundings before and while entering
the active runway.
When aligned, the PF will move his or her hand to the control wheel.
2.4.5.3
Take-off Procedure
The PF's hand must be on the power levers during take-off until V1 so that he / she can execute the rejected
take-off if necessary.
POWER Levers ................................................................................................. Advance smoothly to Rating
detent with brakes off
• Check normal take-off power setting (NTOP) is displayed on ED.
• Observe torque matches the torque bugs.
• Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights out and PFCS indication on # 1 MFD
shows LI, RI and LO, RO SPOILERS retracted.
• Check autofeather ARM advisory on ED.
CAUTION: If autofeather ARM advisory does not appear on ED, take-off must be rejected.
Use rudder pedals to maintain centerline of runway.
At VR rotate to 8° nose-up to achieve lift-off.
NOTE:
To achieve the take-off performance given in Chapter 4, at airport altitudes greater than 5000
ft, the required take-off rotation rate is less rapid.
CAUTION: Nose-up pitch attitudes greater than 8° prior to lift-off may cause the tail to touch the
runway.
After lift-off, continue rotation to a minimum pitch attitude of 10° to achieve V2 + 10 kt at 35 ft.
2.4.5.4
After Take-off
Upon observing a positive rate of climb on altimeter and IVSI:
Landing Gear Lever ..................................................................................................................................... UP
Check all gear, door and LANDING GEAR lever advisory lights out.
Minimum Airspeed ........................................................................................................................... V2 + 10 kt
At acceleration altitude (minimum 400 ft AGL or appropriate obstacle clearance height) increase airspeed:
Minimum airspeed .............................................................................................. Final Take-off Climb Speed
Flaps Lever ........................................................................................... 0o at flap retraction Initiation Speed
Check flap indication on the # 2 MFD.
Bleed Air 1 and 2 ....................................................................................................................... ON / As Req’d
Check white BLEED annunciations on ED and set Bleed selector to NORM or MAX as required.
AUTOFEATHER Switch ............................................................................................................................... Off
Check A/F SELECT and ARM out on ED and SELECT advisory light out.
Condition Levers ............................................................................................................................... As Req’d
Set climb power by moving the Condition Levers to the 900 RPM detent (to climb at 850 RPM, select the Condition Levers to the 850 RPM detent then press the MCL button on the Engine Control panel).
Check maximum climb power settings (MCL) displayed on ED.
Climb to at least 1000 ft AGL and accelerate to enroute climb speed.
Set Flight Director guidance as required.
AOM DASH 8-Q400
CHAPTER 2
2.4-3
NORMAL PROCEDURES
Table 2.4-1 - Take-off Procedure
PF
[Rev. 9] 28 FEB 2014
PNF
“LINE-UP CHECK COMPLETE”
Advances POWER Levers to detent.
“CHECK POWER”
Check NTOP power setting and observes torque
matches the torque bugs.
Observes spoiler advisory lights go out, PFCS indication
on # 1 MFD shows spoilers retracted and auto-feather
ARM annunciation on ED
“POWER SET”
At 80 kt:
“80 KNOTS”
“80 KNOTS”
At V1: “V1”
At VR: “ROTATE”
Cross checks airspeed, places both hands on the
control column then rotates at VR
Observes positive rate on altimeter and VSI
“POSITIVE RATE”
“GEAR UP”
Selects Landing Gear Lever Up
Confirms speed greater than VFRI
“FLAPS ZERO, BLEEDS ON”
At acceleration altitude (minimum 400 ft or appropriate
obstacle clearance height)
“____ FEET”
Confirms speed VFRI or above
Selects Flaps 0°
Selects Bleeds - ON / NORM
“CLIMB POWER 900” (or “850 MCL”)
Selects auto-feather off then sets Condition Levers to
900 RPM detent (or 850 RPM detent then presses the
MCL button)
Checks MCL power setting on ED.
“CLIMB POWER SET”
Climbs to at least 1,000 ft AGL and accelerates to
enroute climb speed.
“SET IAS ____”
NOTE:
Sets Flight Director
“IAS SET ____”
The PF will call for the “AFTER TAKE-OFF CHECKLIST” (Read and Do) at his / her
discretion once the airplane is established in the climb and clear of busy terminal airspace
(minimum 1000 ft AGL).
AOM DASH 8-Q400
CHAPTER 2
2.4-4
[Rev. 9] 28 FEB 2014
2.4.6
NORMAL PROCEDURES
Take-off with Reduced Power
2.4.6.1
General
At the option of the operator, take-off with reduced power may be performed in accordance with the limitations
and performance data contained in this volume and AFM Supplement 13.
Engine power settings and performance data are determined by the use of an assumed outside air temperature higher than actual by a specific increment.
2.4.6.2
Normal Procedures
The normal procedures in Sub-Chapter 2.15 are applicable with the addition of the following:
2.4.6.2.1
Taxi Check
RDC TOP TRQ DEC switch ........................................Press to achieve the desired reduced torque setting
Check RDC TOP engine rating appears on ED and correct torque values have been set.
NOTES:
1. If the RDC TOP TRQ DEC switch is held for more than 10 s, the reduced power function
will become inoperative.
2. To reset NTOP press the RDC TOP RESET TRQ switch.
2.4.6.2.2
Take-off Procedures
POWER Levers .......................................................... Advance smoothly to RATING detent with brakes off
• Check reduced take-off power setting (RDC TOP) is displayed on ED,
• Observe torque matches torque bugs,
• Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights out,
• Check PFCS indication on # 1 MFD shows LI, RI and LO, RO SPOILERS retracted,
• Check autofeather ARM advisory on ED.
2.4.7
Take-off with Maximum Take-off Power and Uptrim Disabled
2.4.7.1
General
At the option of the operator, take-off can be accomplished with maximum take-off power, and uptrim disabled
using the limitations and performance data contained in this volume and AFM Supplement 46.
2.4.7.2
Normal Procedures
The normal procedures in Sub-Chapter 2.15 are applicable with the addition of the following:
2.4.7.2.1
Taxi Checks
MTOP switch ............................................................................................................................................. Press
Check MTOP engine rating appears on ED.
2.4.7.3
Take-off Procedure
POWER Levers .......................................................... Advance smoothly to RATING detent with brakes off
• Check maximum take-off power setting (MTOP) is displayed on ED,
• Observe torque matches torque bugs,
• Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights out,
• Check PFCS indication on # 1 MFD shows LI, RI and LO, RO SPOILERS retracted.
• Check autofeather ARM advisory on ED.
2.4.7.4
In-flight Procedures - After Take-off
Autofeather switch ........................................................................................................................................ Off
Check A/F SELECT and ARM out on ED and SELECT advisory light out.
MTOP switch ............................................................................................................................................. Press
Check NTOP engine rating appears on ED.
Reduce power to climb setting.
NOTE:
Following de-selection of the MTOP rating switch, engine power will decrease to the
appropriate NTOP value.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.4.8
2.4-5
[Rev. 9] 28 FEB 2014
Take-off with Bleeds “ON”
At the option of the operator, take-off and landing with bleed “ON” may be performed in accordance with the
limitations, procedures and performance data contained in this volume and AFM Supplements 21 or 61.
The normal procedures in this Chapter are applicable with the addition of the following:
2.4.8.1
Taxi Checks
BLEED Selector............................................................................................................................................ MIN
BLEED 1 and BLEED 2 Switches................................................................................BLEED 1 and BLEED 2
2.4.9
Crosswind Take-off
2.4.9.1
Line-Up Check
When lining up for a crosswind take-off, keep the controls locked until the airplane is aligned with the runway.
2.4.9.2
Take-off Procedure
During the take-off run, directional control can be maintained with rudder pedal steering.
At VR, the airplane should be lifted off cleanly but smoothly to prevent scuffing the tires as they leave the
ground.
Observe the applicable rotation pitch attitude limitations.
When safely airborne, keep the wings level and maintain runway heading or follow the applicable SID for the
remainder of the climb.
Crew callouts and coordination are the same as for a normal take-off.
2.4.10
Operation in Tailwinds between 10 and 20 kt
At the option of the operator, take-off in tailwinds between 10 and 20 knots may be performed in accordance
with the limitations and performance contained in this volume and AFM Supplement 3.
2.4.10.1
Line-Up Check
Unlock and check flight controls with airplane headed into wind.
CAUTION: With airplane headed downwind and flight controls unlocked, firmly hold the control
wheel in the centered position to restrain uncommanded movement of the ailerons.
2.4.10.2
NOTE:
Take-off Procedure
The take-off rotation rate is less rapid than required for a normal, into wind take-off.
2.4.11
Noise Abatement Procedures
2.4.11.1
Initial Climb-out for Noise Abatement
Unless national or local regulations prescribe other noise abatement procedures the following shall apply:
• Climb to 1,500 ft above airfield elevation at normal take-off power (take-off flaps/V2 + 10 kt),
• at 1,500 ft reduce to max. climb power and increase to V2 + 20 kt,
• at 3000 ft initiate flap retraction and accelerate to en-route climb speed.
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CHAPTER 2
NORMAL PROCEDURES
2.5
CLIMB, CRUISE AND DESCENT
2.5.1
Normal Climb
2.5-1
[Rev. 9] 28 FEB 2014
During the climb, both pilots will monitor the power.
The normal climb speed profile is Type II - 185 kt to FL 200 then reduced by approximately 5 kt for every 1,000
ft thereafter.
•
Refer to Sub-Chapter 5.4, Climb (Time, Distance, Fuel), for appropriate climb profile.
2.5.2
.
Cruise
Table 2.5-1 Climb And Cruise Procedures
PF
At Transition Altitude
"TRANSITION, Altimeter Set 1013/29.92"
PNF
“1013/29.92 SET AND CROSS CHECKED”
After reaching cruise altitude and speed
"CRUISE CHECKLIST"
Sets cruise power and completes the “CRUISE
CHECKLIST” (Read and Do)
“CRUISE CHECKLIST COMPLETE”
2.5.3
Descent
Prior to commencing the descent it is recommended that landing information be obtained through ATC (ATIS if
available), and the Approach Briefing completed.
The Descent Checklist is normally called for when initiating the descent for landing.
Normal Descent Profile is flown at VMO.
Select the SEAT BELT sign ON through 10,000 feet. This will advise the cabin crew the aeroplane is descending for landing. Once the cabin is secure, the senior cabin crew member will come to the flight deck and advise
“CABIN SECURE”. Once the aeroplane is on final approach, two chimes (fasten belts switch) will be sounded
to advise the cabin crew that landing is imminent.
Table 2.5-2 Descent Procedures
PF
"DESCENT CHECKLIST"
PNF
Completes “DESCENT CHECKLIST” (Read and
Do)
“DESCENT CHECKLIST COMPLETE”
At transition level
“TRANSITION, <Current Altimeter Setting>”
“<Current Altimeter Setting> SET AND CROSS
CHECKED”
2.5.4
Holding
Refer to Sub-Chapter 5.10, Holding.
AOM DASH 8-Q400
CHAPTER 2
2.5-2
[Rev. 9] 28 FEB 2014
2.5.5
Fuel Management
2.5.5.1
Normal Fuel Operation
NORMAL PROCEDURES
1. Fuel TRANSFER switch.......................................................................................................................... OFF
Check both VALVE CLOSED appear on the FUEL page of MFD.
2. TANK 1 AUX PUMP and TANK 2 AUX PUMP switches ......................OFF (except for take-off and landing)
Check TANK 1 AUX PUMP ON and TANK 2 AUX PUMP ON advisory lights out and TANK 1 AUX PUMP
and TANK 2 AUX PUMP indication OFF, on FUEL page of MFD.
2.5.5.2
Fuel Transfer
TRANSFER FROM TANK 1 TO TANK 2:
1. Fuel TRANSFER switch............................................................................................................... TO TANK 2
Check both VALVE OPEN, TO TANK 2 TRANSFER SW arrow and TANK 1 AUX PUMP indication appears
on the FUEL page of MFD, and TANK 1 AUX PUMP ON advisory light illuminates.
At completion of transfer:
2. Fuel TRANSFER switch.......................................................................................................................... OFF
Check both VALVE CLOSED indicators appear, TO TANK 2 TRANSFER SW arrow and TANK 1 AUX
PUMP indication OFF on the FUEL page of MFD, and TANK 1 AUX PUMP ON advisory light out.
TRANSFER FROM TANK 2 TO TANK 1:
1. Fuel TRANSFER switch............................................................................................................... TO TANK 1
Check both VALVE OPEN, TO TANK 1 TRANSFER SW arrow and TANK 2 AUX PUMP indication appears
on the FUEL page of MFD, and TANK 2 AUX PUMP ON advisory light illuminates.
At completion of transfer:
2. Fuel TRANSFER switch.......................................................................................................................... OFF
Check both VALVE CLOSED indicators appear, TO TANK 1 TRANSFER SW arrow and TANK 2 AUX
PUMP indication OFF on the FUEL page of MFD, and TANK 2 AUX PUMP ON advisory light out.
NOTES:
1. For monitoring of the fuel state, the FUEL page of MFD is to remain displayed until the fuel
TRANSFER switch is selected off.
2. Maximum fuel imbalance is indicated by the FUEL quantity readout on ED and fuel gauge
pointers on FUEL page of MFD changing from white to amber and [BALANCE] appears,
flashing on ED.
3. If TANK 1 QTY or TANK 2 QTY is inoperative, the [BALANCE] advisory is also inoperative.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.6
APPROACH, LANDING PREPARATION AND BRIEFING
2.6.1
Approach Briefing
2.6-1
[Rev. X] 31 MAY 2011
The Approach Briefing is a plan of action for the approach, landing and possible missed approach. Proper
planning will normally permit the Approach Briefing to be accomplished prior to entering busy terminal airspace.
NOTE:
Approaching destination, the crew shall re-evaluate the weather situation and recalculate the
required landing distance.
The Approach Briefing will be given by the PF and should consist of at least the following:
1. Terrain situation (MEA, MGA)
2. Type of approach/RWY in use
3. Radio/Nav set up
4. Minimum Sector Altitude
5. Initial Approach Altitude/Descent point
6. Runway condition/landing distance
7. Special aspects (e.g. taxi procedure, system malfunctions,...).
Following items shall be briefed “by heart”:
1. Final Altitude
2. MDA/Descent Altitude/Decision Height
3. Missed Approach Procedure including Missed Approach Point.
The approach speed is based on the minimum speed which can be flown with approach flap configuration
(VAPP = 1.23 VSR with approach flap). Landing speeds are based on the minimum speed which can be flown
with the landing flap configuration (VREF = 1.23 VSR with landing flap).
NOTE:
The solid bug is set to VREF and the outline bug is set to VGA.
The Approach Check should be initiated not less than 25 nautical miles prior to commencing the approach, or
through 10000 ft.
2.6.2
Use of Flaps
The flap setting for landing may either be 10°, 15° or 35°. The flap setting is confirmed by checking the flap
indication on the #2 MFD.
2.6.3
Flight Director Setup (TBD)
2.6.4
Approach with Bleeds “ON”
This procedure corresponds to Supplement 21 of the AFM.
BLEED selector ............................................................................................................................................ MIN
BLEED 1 and BLEED 2 switches ................................................................................ BLEED 1 and BLEED 2
2.6.5
VFR Approach
For a normal visual approach under VFR conditions refer to figure 2-2 on page 2.10-2.
Table 2.6-1 Approach Procedure
PF
PNF
“APPROACH CHECKLIST”
Completes “APPROACH CHECKLIST” (Read and
Do)
“APPROACH CHECKLIST COMPLETE”
NOTE:
For the different approach procedures refer to chapter 2.10.
AOM DASH 8-Q400
CHAPTER 2
2.6-2
[Rev. X] 31 MAY 2011
2.6.6
NORMAL PROCEDURES
Steep Approach and ILS Raw Data Only Steep Approach
(MS 4-456970 or MS 4-309206)
These procedures correspond to Supplement 12 and 45 of the AFM
2.6.6.1
General
Enhanced Ground Proximity Warning System (Supplement 64) must be incorporated.
NOTE:
This procedure does not constitute approval to conduct steep approach and landing.
IN RANGE
GPWS LDG FLAP switch .................................................................................................................. Select 35°
Check 35° advisory light illuminates.
APPROACH
Prior to glide path intercept:
LANDING GEAR Lever .................................................................................................................................. DN
Check 3 green gear locked down advisory lights illuminate, all amber doors open, red gear unlocked and
LANDING GEAR lever advisory lights out.
FLAPS lever ................................................................................................................................................... 35°
FLAP 35° APPROACH switch .................................................................................................................STEEP
Check STEEP advisory light illuminates.
Condition levers ................................................................................................................................ MAX/1020
2.6.7
Go-Around from Final Approach
Condition Levers ............................................................................................................................. MAX / 1020
POWER Levers ......................................................................................................Advance to RATING detent
Check normal take-off setting. Observe torque matches the torque bug.
Pitch attitude........................................................................................................ Rotate to approximately 10°
FLAPS Lever ................................................................................................................................. 5°, 10° or 15°
Check FLAP indication on #2MFD.
Minimum airspeed ................................................................................. Go-around speed Flap 5°, 10° or 15°
Positive rate of Climb:
LANDING GEAR Lever .................................................................................................................................. UP
Check all gear, door and LANDING GEAR Lever advisory lights out.
When clear of obstacle:
Minimum airspeed .................................................................................................. Final take-off climb speed
FLAPS Lever .......................................................................................................0° at flap retraction initiation
Speed flap ..................................................................................................................................... 5°, 10° or 15°
Check FLAP indication on #2MFD.
2.6.8
Engine Torque Split Between Engines
At low engine power settings, normally associated with descent and approach, an indicated torque difference
between the two engines is not considered abnormal.
The degree of torque difference will depend on the engine gas generator matching, accuracy of POWER lever
matching and the ambient operating conditions.
The torque difference will be more pronounced if one engine is operating with its Handling Bleed-off Valve
(HBOV) open while the other engine is operating with its HBOV closed.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.7
NORMAL LANDING
2.7.1
General
2.7-1
[Rev. 9] 28 FEB 2014
At or prior to reaching the point where the aircraft will be maneuvered for final approach and landing, the aircraft will normally be configured at Flap 5.
On final approach, the PF is to, at their discretion, command the landing gear, flaps and condition levers to the
required position for the subsequent landing. Once the aircraft is configured for landing, the PF is to call for the
"LANDING CHECKLIST" (Challenge and Response).
2.7.2
Landing
When established on final approach:
Landing Gear ................................................................................................................................. DN / 3 Green
Check 3 green gear locked down advisory lights are illuminated, all amber doors open, red gear unlocked and
selector lever advisory lights out.
Flap Selector...................................................................................................................................___ Set / ind
Move the flap selector to the detent for the desired approach flap (Flap 15° or 10° or 5° depending on approach
climb WAT requirements). Check flap indication on #2 MFD.
Condition Levers.........................................................................................................................................MAX
Move Condition Levers to the MAX detent (if using Reduced NP for landing, first press the RDC NP button on
the Engine Control panel then move the Condition Levers to MAX within 15 sec).
Minimum Airspeed ................................................................................................................. Approach Speed
Reduce to approach speed.
Bleed Air 1 and 2 .........................................................................................................................MIN / As req’d
Set Bleed selector to MIN and Bleed 1 and 2 switches Off (Bleed 1 and 2 switches remain On if conducting a
"Bleed On" landing).
Flap Selector...................................................................................................................................___ Set / ind
Move the flap selector to the detent for the desired landing flap (Flap 35° or 15° or 10° depending on landing
WAT requirements). Check flap indication on #2 MFD.
Minimum Airspeed ......................................................................................................................................VREF
Reduce airspeed to VREF then fly a stable approach with small corrections regarding control inputs and power
to maintain runway centerline and glidepath.
NOTE:
The landing performance given in Sub-Chapter 4.4, assumes that the appropriate VREF is
achieved by 50 ft AGL.
Commence flare and adjust power to achieve positive ground contact with minimum descent rate at the
desired point on the runway.
POWER Levers ............................................................................................FLIGHT IDLE prior to touchdown
then DISC after touchdown
•
Check PROPELLER GROUND RANGE advisory lights illuminate.
•
Check ROLL OUTBD and ROLL INBD SPOILER advisory lights on at mainwheel contact.
CAUTION: Pitch attitudes greater than 6° in the landing flare may cause the fuselage to contact the
runway.
NOTES:
1. To decrease the landing descent rate and not exceed a pitch attitude of 6° when the landing
descent rate is higher than desired, power will be required in the landing flare through to
touchdown.
2. To decrease the landing descent rate at airport altitudes greater than 5000 ft, it may be
necessary to maintain power in the landing flare through to touchdown.
The nosewheel should be promptly brought into contact with the ground following mainwheel contact.
Anti-Skid Brakes .................................................................................................................................. As req’d
Apply Anti-Skid braking as required to decelerate the aircraft within the available runway.
AOM DASH 8-Q400
CHAPTER 2
2.7-2
NORMAL PROCEDURES
[Rev. 9] 28 FEB 2014
Table 2.7-1 Approach and Landing Procedure
PF
PNF
“FLAP 5”
Confirms at or below VFE
Selects Flap 5°
Established on Final Approach
“GEAR DOWN”
Confirms at or below VLO
Selects Landing Gear DOWN
Observes gear down lights illuminate
“FLAP 15” (or 5° or 10° if WAT limited)
“CONDITION LEVERS MAX” or
“REDUCED NP, CONDITION LEVERS MAX”
“LANDING CHECKLIST”
Confirms at or below VFE
Selects Flap 15° (5° or 10°)
Sets Condition Levers to MAX detent
"SET" or
Selects RDC NP switch
Sets Condition Levers to MAX detent
Observes RDC NP LANDING on ED
Calls "REDUCED NP, CONDITION LEVERS SET"
Completes Landing Checklist.
(Challenge and Response)
“LANDING CHECKLIST COMPLETE” (see note below)
If Landing Flap is Not Selected:
“FLAP 35” (or 15° or 10° if WAT limited)
NOTE:
Selects flap 35° (or 15° or 10°)
Observes flap travel to required setting
“FLAP 10, 15 or 35 INDICATING”
When a different flap setting is used for landing from that used for approach, the PF will call for
the “LANDING CHECKLIST” prior to landing flap selection.
At completion of the checklist the PNF will call:
“LANDING CHECKLIST COMPLETE – FLAP 10, 15 or 35 TO GO”.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.7.3
2.7-3
[Rev. 9] 28 FEB 2014
Crosswind Landing Technique
Crosswind landing is based on the steady state wing down / zero crab technique, i.e. approach and touch
down with upwind wing lowered, using rudder to align airplane with runway.
Following touch down hold nosewheel on runway with elevators and use lateral control to inhibit any upwind
wing lifting.
2.7.4
Normal Landing in Tailwinds between 10 and 20 kt
2.7.4.1
General
At the option of the operator, landings in tailwinds between 10 and 20 kts may be conducted in accordance with
the limitations, procedures and performance data contained in the respective chapters of this AOM and AFM
Supplement 3.
NOTE:
Maintain the appropriate VREF airspeed throughout the approach and the landing.
The landing flare angle will be less than that required for a normal, into wind landing.
2.7.5
Noise Abatement Procedures
(Landing with 850 RPM Propeller)
2.7.5.1
General
At the option of the operator, approach and landing with 850 NP may be conducted in accordance with the limitations, procedures and performance data contained in the respective Chapters of this AOM and AFM Supplement 39.
2.7.5.2
Reduced NP Landing
Condition Levers................................................................................................................................. MIN / 850
RDC NP LDG Switch ................................................................................................................................. Press
Check REDUCED NP LANDING message appears on ED.
Condition Levers.........................................................................................................................................MAX
Check PROP RPM on ED remain at 850 RPM.
NOTE:
Reduced NP Landing mode will be cancelled if condition levers are not set to MAX / 1020
within 15 s of selecting RDC NP LDG switch.
Required power lever movements will be larger with condition levers set to 850 RPM than experienced at
MAX/1020 during the final approach and landing phase, to achieve the same result.
2.7.6
Operation from Unpaved / Gravel Runways
2.7.6.1
General
At the option of the operator, landings on unpaved/gravel runways may be conducted in accordance with the
limitations, procedures and performance data contained in the respective chapters of this AOM and AFM Supplement 26.
2.7.6.2
Landing
Below 30 KIAS and on detection of mainwheel skidding:
Reduce maximum braking effort to an intermittent brake application with the duration of each application
approximately 1 s and intervals of reduced braking as brief as possible.
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CHAPTER 2
2.8-1
NORMAL PROCEDURES
2.8
POST LANDING
2.8.1
After Landing
[Rev. 14] 27 MAY 2015
On roll-out, the Left Seat (LS) pilot will call for control at approximately 60 kt.
Once clear of the runway, the Right Seat (RS) pilot completes the after landing checklist.
Table 2.8-1
After Landing Procedure
Captain (PIC - LS)
First Officer (F/O - RS)
At approximately 60 kt
“I HAVE CONTROL”
“YOU HAVE CONTROL”
Once clear of runway
“AFTER LANDING CHECKLIST”
Completes “AFTER LANDING CHECKLIST”
(Read and Do)
Responds
“AFTER LANDING CHECKLIST COMPLETE”
2.8.2
Shutdown
As the airplane approaches the gate / parking spot, the PIC will select the TAXI light OFF.
Once the airplane is stopped, the PIC will:
EMERG BRAKE ....................................................................................................................................... PARK
Call for “SHUTDOWN CHECKLIST” (Challenge and Response).
NOTE:
If using ground power or APU, ensure that it is on line prior to shutting down both engines.
For all shutdowns allow the engines to run for 30 s at START / FEATHER before selecting
FUEL OFF.
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CHAPTER 2
NORMAL PROCEDURES
2.9
2.9-1
[Rev. X] 31 MAY 2011
OPERATION ON CONTAMINATED RUNWAYS
This section corresponds to Supplement 37 of the AFM.
2.9.1
General
The general information in Chapter 0 is applicable with the addition of the following:
a. This information has been prepared by the manufacturer and approved as guidance material to assist
operators in developing suitable guidance, recommendations or instructions for use by their flight crews
when operating on wet or contaminated runway surface conditions.
b. The data have been prepared using reasonable estimates of the effects of wet and contaminated runway conditions on the accelerating ground roll and the braking ground roll. The effects of actual conditions may differ from those used to establish the data.
c.
The performance information assumes any standing water, slush or loose snow to be of uniform depth
and density.
d. The level of safety is decreased when operating on contaminated runways and therefore every effort
should be made to ensure that the runway surface is cleared of any significant contaminant.
e. The provision of performance information for contaminated runways should not be taken as implying
that ground handling characteristics on these surfaces will be as good as can be achieved on dry or wet
runways, in particular, in crosswinds and when using reverse thrust.
2.9.1.1
Definitions
Runway Contaminated
by Standing Water,
Slush or Loose Snow
NOTE:
A runway is considered to be contaminated when more than 25% of the runway surface area (whether in isolated areas or not) within the required length and width
being used, is covered by standing water, slush or loose snow.
Runways with water depths, slush or loose snow less than 3 mm (0.125 in), may be
considered not contaminated provided braking is considered good.
Runway Contaminated
by Compacted Snow
A runway is considered to be contaminated when completely covered by snow
which has been compressed into a solid mass which resists further compression.
Runway Contaminated
by Wet Ice
A runway is considered to be contaminated when, due to the presence of wet ice,
the braking effectiveness is expected to be very low.
VGO*
The lowest decision speed from which a continued take-off is possible within the
take-off run and take-off distance required.
VSTOP*
The highest decision speed from which the aircraft can stop within the acceleratestop distance required.
NOTE:
Take-off Distance
* Under the JAR-OPS1 regulations only one single V1 value for the
rejected and continued take-off is permitted. This is why the data in
Sub-Chapter 4.1 only show Vgo/VR = 1 for take-off and VSTOP/VR =
1 for accelerate-stop.
The take-off distance on a contaminated runway is the longer of:
a. 115% of the distance from the start of the take-off roll to the point at which
the airplane attains a height of 35 feet above the take-off surface, with all
engines operating.
b. The distance from the start of the take.off roll to the point at which the airplane attains a height of at least 15 feet above the take-off surface, with critical engine failure such that the failure would be recognized at the Decision
Speed VGO.
Take-off Run
(cont’d on next page)
AOM DASH 8-Q400
The take-off run on a contaminated runway is equal to the take-off distance on contaminated runway.
CHAPTER 2
2.9-2
NORMAL PROCEDURES
[Rev. X] 31 MAY 2011
Definitions (cont’d)
Accelerate-Stop
The accelerate-stop distance on a contaminated runway is the longer of:
a. Accelerate-stop distance with an engine failure at VEF as defined below:
i)
The distance necessary to accelerate the airplane from a standing start
to VEF with all engines operating plus:
ii)
The distance required to accelerate the airplane from VEF to VSTOP
assuming the critical engine fails at VEF plus;
iii) The distance required to come to a full stop from the point reached at
the end of the acceleration period described in paragraph a. ii) above
assuming that the pilot does not apply any means of retarding the airplane until that point is reached and that the critical engine is still inoperative, plus:
iv) A distance margin equal to 2.0 seconds at VSTOP
b. Accelerate-stop distance with all engines operating as defined below:
i)
The distance necessary to accelerate the airplane from a standing start
to VSTOP with all engines operating plus:
ii)
The distance required to come to a full stop from the point reached at
the end of the acceleration period described in paragraph b. i) above,
assuming that the pilot does not apply any means of retarding the airplane until that point is reached and that all engines are still operating,
plus:
iii) A distance margin equal t~ 2.0 seconds at VSTOP
WED
The water equivalent depth of contaminant = the depth of water producing an equivalent performance effect as that of contaminant of lower specific gravity. WED for
take-off is not based on contaminant depth x specific gravity and must be determined in accordance with Section 4.1.4.
For further definitions and performance data regarding take-off on wet and contaminated runways, refer to
chapter 4, Performance.
2.9.2
Limitations
The limitations in Chapter 1 are applicable with the addition of the following:
2.9.2.1
1.
Operations
Take-off with reduced power is prohibited on contaminated runways.
2.9.2.2
Operation From Runways Contaminated with Standing Water, Slush or Loose Snow
1.
Maximum operating altitude for take-off and landing is 6,000 ft ASL.
2.
The maximum permitted WED of contaminant is 15 mm (0.59 in).
3.
The maximum permitted depth of contaminant is 6 cm (2.4 in).
4.
For WED greater than 3 mm (0.125 in): selection of power levers aft of DISC is prohibited.
5.
The maximum crosswind component for take-off and landing is 14 kt.
2.9.2.3
1.
Operation From Runways Contaminated with Compacted Snow:
The maximum crosswind component for take-off and landing is 20 kt.
2.9.3
Normal Procedures
The normal procedures in Chapter 2 are applicable with the addition of the following:
CAUTION: Operation in crosswinds on runways contaminated with wet ice is not recommended.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.9.4
2.9-3
[Rev. X] 31 MAY 2011
Performance Data
The performance data in Chapter 4 and compatible supplements are applicable with the addition of the following:
NOTE:
Compatible supplement performance penalties are cumulative.
NOTE:
Where applicable, the performance factor of the compatible supplement must be applied to the
calculated performance data in chapter 4 prior to applying corrections of this supplement.
2.9.4.1
NOTE:
Take-off Performance on a Contaminated Runway:
Tests in water of 19 mm (0.75 in) average depth have shown that there is no spray
impingement on engine intakes or tail surfaces at any speed up to lift-off, from either main or
nose wheels. Some spray from the nosewheel and propellers impinges on the lower surface of
the fuselage, nosewheel well, nacelles, and inboard wing and flap.
AOM DASH 8-Q400
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CHAPTER 2
NORMAL PROCEDURES
2.10
FLIGHT PROFILES
Figure 2.10-1
Normal Take-off
AOM DASH 8-Q400
2.10-1
[Rev. 9] 28 FEB 2014
CHAPTER 2
2.10-2
[Rev. 14] 27 MAY 2015
NORMAL PROCEDURES
“
“
Figure 2.10-2
Visual Approach and Landing
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
Figure 2.10-3
Circling Approach
AOM DASH 8-Q400
2.10-3
[Rev. 9] 28 FEB 2014
CHAPTER 2
2.10-4
[Rev. 9] 28 FEB 2014
Figure 2.10-4
NORMAL PROCEDURES
Precision Approach
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.10-5
[Rev. 9] 28 FEB 2014
Table 2.10-1 Precision Approach and Landing Procedure
PF
PNF
Approaching the initial approach fix or on radar vectors to intercept the final approach course:
“FLAP 5”
Confirms VFE
Selects Flap 5°
Observes flap travels to 5°
At approximately one and a half (1.5) dots below
glideslope
“GEAR DOWN”
Confirms VLO
Selects gear down
Observes gear down lights
At approximately one (1) dot below glideslope
“FLAP 15” (or 10° or 5° if WAT limited)
“CONDITION LEVERS MAX” or
“REDUCED NP CONDITION LEVERS MAX”
Confirms VFE
Selects requested flap angle
Observes flap travels to required setting
Sets Condition Levers to MAX detent
or
Selects RDC NP switch
Sets Condition Levers to MAX detent
Observes RDC NP LANDING on ED
“LANDING CHECKLIST”
Conducts landing checklist (Challenge
Response)
“LANDING CHECKLIST COMPLETE”
(see note below)
and
Outer Marker (or FAF) inbound
“<FAF NAME>” (i.e. “JULIET”)
“<GLIDESLOPE CHECK ALTITUDE>” (i.e. “1830”)
“CROSSCHECK”
“FLAP 35” (or 10° or 15° if WAT limited)
Confirms VFE
Selects requested flap angle
Observes flap travels to required setting
“FLAP ___ INDICATING”
“100 ABOVE” (minimums)
“CONTINUING”
At decision height
“MINIMUMS VISUAL”
“LANDING”
or
“MINIMUMS NO CONTACT”
“GO AROUND, CHECK POWER”
(see “Missed Approach Procedure” on page 2.10-10)
NOTE:
When a different flap setting is used for landing from that used for approach, the PF will call for
the “LANDING CHECKLIST” prior to landing flap selection.
At completion of the checklist the PNF will call “LANDING CHECKLIST COMPLETE – FLAP
15 or 35 TO GO”.
AOM DASH 8-Q400
CHAPTER 2
2.10-6
[Rev. 9] 28 FEB 2014
Figure 2.10-5
NORMAL PROCEDURES
CAT II Precision Approach
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.10-7
[Rev. 9] 28 FEB 2014
Table 2.10-2 CAT II Precision Approach and Landing Procedure
PF
PNF
Approaching the initial approach fix or on radar vectors to intercept the final approach course:
“FLAP 5”
Confirms VFE
Selects Flap 5°
Observes flap travels to 5°
At approximately one and a half (1.5) dots below
glideslope
“GEAR DOWN”
Confirms at or below VLO
Selects gear down
Observes gear down lights
At approximately one (1) dot below glideslope
“FLAP 15” (or 10° if WAT limited)
Confirms VFE
Selects requested flap angle
Observes flap travels to required setting
“CONDITION LEVERS MAX”
Sets Condition Levers to MAX detent
“LANDING CHECKLIST”
Conducts landing checklist (Challenge
Response)
“LANDING CHECKLIST COMPLETE”
(see note below)
and
Outer marker (or FAF) inbound:
“<FAF NAME>” (i.e. “JULIET”)
“<GLIDESLOPE CHECK ALTITUDE>” (i.e. “1830”)
“CROSSCHECK”
At 1200 ft RA
“DUAL”
“CHECK”
“100 ABOVE” (minimums)
“CONTINUING”
At decision height “MINIMUMS VISUAL”
or
“MINIMUMS NO CONTACT”
“LANDING”
“GO-AROUND, CHECK POWER”
(see “Missed Approach Procedure” on page 2.10-10)
NOTE:
CAT II Approach and Landing are approved using flap 10° or 15° only.
Autopilot must be disengaged at or above 100 ft.
Airplane must be in landing configuration prior to final approach fix.
AOM DASH 8-Q400
CHAPTER 2
2.10-8
[Rev. 9] 28 FEB 2014
Figure 2.10-6
NORMAL PROCEDURES
Non-Precision Approach
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.10-9
[Rev. 9] 28 FEB 2014
Table 2.10-3 Non-Precision Approach And Landing Procedure
PF
PNF
Approaching the initial approach fix or on radar vectors to intercept the final approach course:
“FLAP 5”
Confirms VFE
Selects Flap 5°
Observes flap travels to 5°
Prior to Final Approach Fix inbound:
“GEAR DOWN”
Confirms at or below VLO
Selects Landing Gear DOWN
Observes gear down lights
“FLAP 15” (or 10° or 5° if WAT limited)
Confirms VFE
Selects requested flap angle
Observes flap travels to required setting
“CONDITION LEVERS MAX” or
“REDUCED NP CONDITION LEVERS MAX”
Sets Condition Levers to MAX detent
or
Selects RDC NP switch
Sets Condition Levers to MAX detent
Observes RDC NP LANDING on ED
“LANDING CHECKLIST”
Conducts landing checklist (Challenge and
Response)
“LANDING CHECKLIST COMPLETE” (see note
below)
Final Approach Fix (Inbound):
Starts timing (if required)
“<FAF NAME>” (i.e. “JULIET”)
“CROSSCHECK”
“100 ABOVE” (minimums)
“CONTINUING”
At MDA
“MINIMUMS __ SECONDS TO GO”
If runway environment is in sight
“VISUAL __ O’CLOCK”
“LANDING”
“FLAP 35” (or 15° or 10° if WAT limited)
Confirms VFE
Selects requested flap angle
Observes flap travels to required setting
“FLAP ___ INDICATING”
At the missed approach point
“MISSED APPROACH POINT”
“GO-AROUND, CHECK POWER”
Approach Procedure” on page 2.10-10)
NOTE:
(see
“Missed
When a different flap setting is used for landing from that used for approach, the PF will call for
the “LANDING CHECKLIST” prior to landing flap selection.
At completion of the checklist the PNF will call “LANDING CHECKLIST COMPLETE - FLAP
15 or 35 TO GO”
AOM DASH 8-Q400
CHAPTER 2
2.10-10
[Rev. 9] 28 FEB 2014
Figure 2.10-7
NORMAL PROCEDURES
Missed Approach
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.10-11
[Rev. 9] 28 FEB 2014
Table 2.10-4 Missed Approach Procedure
PF
PNF
Simultaneously:
Advances power levers to detent, presses GA button
(as required) and rotates the nose of the aircraft to
approximately 10°
“GO-AROUND, CHECK POWER”
Sets Condition Levers to MAX
Sets POWER Levers, checks NTOP power setting on ED
and observes torque matches the torque bugs
“POWER SET”
If landing flap selected:
“FLAP 15” (or 10° or 5° depending upon landing flap
setting)
Selects flap as requested
Maintains a minimum airspeed of not less than VGA Observes positive rate
“POSITIVE RATE”
Selects Landing Gear Lever UP
“GEAR UP”
“HDG/ALT SELECT” (see Note 1)
Selects HDG, ALT SEL and confirms correct altitude
selected
“HDG AND ALT SEL SELECTED”
At a minimum of 400 feet AGL (or obstacle clearance
height)
“___ FEET” (or obstacle clearance height)
“FLAP 0, BLEEDS ON”
Confirms speed VFRI or above
Selects Flap to 0°
Selects Bleeds - ON / NORM
“CLIMB POWER, 900 (or 850 MCL)”
Sets Condition Levers to 900 RPM detent (or 850
RPM detent then the MCL button).
Checks MCL power setting on ED
“CLIMB POWER SET”
Climbs to at least 1000 feet AGL and accelerates to
climb speed
“SET IAS ___” (as required)
Sets Flight Director (as requested)
“IAS SET ___”
NOTES:
1. Heading and Altitude Select should only be used after GA-MODE has been selected.
2. The PNF will advise ATC of the missed approach once the airplane is established in the
climb.
3. If carrying passengers the PIC will make a P.A. or request that the Senior Cabin Crew
Member do it on his or her behalf.
4. The PF will call for the “AFTER TAKE-OFF CHECKLIST” (Read and Do) at his / her
discretion once the airplane is established in the climb and clear of busy terminal airspace
(minimum 1,000 ft AGL.
AOM DASH 8-Q400
CHAPTER 2
2.10-12
[Rev. 9] 28 FEB 2014
Figure 2.10-8
NORMAL PROCEDURES
Balked Landing
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.10-13
[Rev. 9] 28 FEB 2014
Table 2.10-5 Balked Landing Procedure
PF
PNF
Simultaneously:
Advances power levers to detent, presses GA button (as
required) and rotates the nose of the aircraft to
approximately 10°
“GO-AROUND, CHECK POWER”
Sets Condition Levers to MAX
Sets POWER Levers, checks NTOP power setting
on ED and observes torque matches the torque
bugs
“POWER SET”
If landing flap selected:
“FLAP 15” (or 10° or 5° depending upon landing flap setting)
Selects flap as requested
Maintains a minimum airspeed of not less than VGA
Observes positive rate
“POSITIVE RATE”
Selects Landing Gear Lever UP
“GEAR UP”
“HDG/ALT SELECT” (see Note 1)
Selects HDG, ALT SEL and confirms correct
altitude selected
“HDG AND ALT SEL SELECTED”
At a minimum of 400 feet AGL (or obstacle
clearance height)
“___ FEET” (or obstacle clearance height)
“FLAP 0, BLEEDS ON”
Confirms speed VFRI or above
Selects Flap to 0°
Selects Bleeds - ON / NORM
“CLIMB POWER, 900 (or 850 MCL)”
Sets Condition Levers to 900 RPM detent (or
850 RPM detent then the MCL button).
Checks MCL power setting on ED
“CLIMB POWER SET”
Climbs to at least 1,000 feet AGL and accelerates to climb
speed
“SET IAS ___” (as required)
Sets Flight Director (as requested)
“IAS SET ___”
NOTES:
1. Heading and Altitude Select should only be used after GA-MODE has been selected.
2. The PNF will advise ATC of the Balked approach once the aeroplane is established in the
climb.
3. If carrying passengers the PIC will make a PA or request that the Senior Cabin Crew
Member do it on his or her behalf.
4. The PF will call for the “AFTER TAKE-OFF CHECKLIST” (Read and Do) at his / her discretion once the airplane is established in the climb and clear of busy terminal airspace
(minimum 1,000 ft AGL.
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CHAPTER 2
NORMAL PROCEDURES
2.11
AIRWORK and BASIC FLIGHT TECHNIQUES
2.11.1
Steep Turns
2.11.1.1
Objective
2.11-1
[Rev. 9] 28 FEB 2014
This maneuver familiarizes the pilot with airplane handling characteristics and helps to improve the instrument
cross check.
2.11.1.2
Description
Steep Turns (45° of bank) will be practiced in both directions at 180 kt.
Apply back pressure, as required, to maintain altitude and increase torque, as required, to maintain airspeed.
Power settings during Steep Turns are the responsibility of the PF.
The PF has the option to use the PNF to set power.
However, it is essential that very precise calls be made, e.g. “increase power 10%”.
2.11.1.3
Entry
Stabilize the airplane in trim at the desired speed, heading and altitude.
Enter the Steep Turn with the same roll rate as a normal turn.
As bank angle is increased apply back pressure as required to maintain altitude and increase power as
required to maintain airspeed.
2.11.1.4
During Turn
Maintain a rapid scan so that deviations will be detected early enough to require only small corrections.
2.11.1.5
Rollout
Rollout should be initiated 10° to 15° prior to target heading.
Roll out of the turn at the same rate as a normal turn.
As bank angle is decreased reduce back pressure as required to maintain altitude and decrease power as
required to maintain airspeed.
2.11.1.6
Completion Standard
For the purposes of determining proficiency, two 360° Steep Turns (one in each direction) will be conducted to
the following standard:
Airspeed (180 kt)
 10 kt
Bank Angle (45°)
 5°
Altitude
 100 ft
Heading
 10°
AOM DASH 8-Q400
CHAPTER 2
2.11-2
[Rev. 9] 28 FEB 2014
Figure 2.11-1
NORMAL PROCEDURES
Steep Turns
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.11.2
Steep Turns
2.11.2.1
Objective
2.11-3
[Rev. X] 31 MAY 2011
This maneuver familiarizes the pilot with aeroplane handling characteristics and helps to improve the instrument cross check.
2.11.2.2
Description
Steep turns (45° of bank) will be practiced in both directions at various airspeeds with Condition Levers set at
1020 RPM. Apply back pressure, as required, to maintain altitude and increase torque, as required, to maintain
airspeed.
Power settings during steep turns are the responsibility of the PF. The PF has the option to use the PNF to set
power. However, it is essential that very precise calls be made, e.g.: “increase power 10%”.
2.11.2.3
Entry
Stabilize the aeroplane in trim at the desired speed, heading and altitude. Enter the steep turn with the same
roll rate as a normal turn. As bank angle is increased apply back pressure as required to maintain altitude and
increase power as required to maintain airspeed.
2.11.2.4
During Turn
Maintain a rapid scan so that deviations will be detected early enough to require only small corrections.
2.11.2.5
Rollout
Rollout should be initiated 10° to 15° prior to target heading. Roll out of the turn at the same rate as a normal
turn. As bank angle is decreased reduce back pressure as required to maintain altitude, and decrease power
as required to maintain airspeed.
2.11.2.6
Completion Standard
For the purposes of determining proficiency, two 360° steep turns (one in each direction) will be conducted to
the following standard:
Airspeed (170 knots)
±10 knots
Angle of bank (45°)
±5°
Altitude
±100 ft
Heading
±10°
AOM DASH 8-Q400
CHAPTER 2
2.11-4
NORMAL PROCEDURES
[Rev. X] 31 MAY 2011
DURING TURN
ENTRY
1. THROUGH 30 DEGREES,
INCREASE BACK PRESSURE
TO MAINTAIN ALTITUDE
2. INCREASE POWER AS
REQUIRED TO MAINTAIN
AIRSPEED
PRIOR TO ENTRY
1. SET CONDITION LEVERS
TO 1,020/MAX
2. STABILIZE AIRPLANE IN
TRIM AT DESIRED
AIRSPEED, HEADING AND
ALTITUDE
Figure 2.11-2
1. MAINTAIN RAPID SCAN FOR EARLY
DETECTION OF DEVIATION
2. APPLY CORRECTIONS AS REQUIRED
3. MAINTAIN 45 DEGREES OF BANK
ROLL OUT
1. ANTICIPATE ROLL OUT BY 15 DEGREES
OF HEADING
2. ROLL OUT RATE SHOULD BE AT A
NORMAL ROLL RATE
3. THROUGH 30 DEGREES OF BANK,
DECREASE BACK PRESSURE TO MAINTAIN
ALTITUDE AND DECREASE POWER TO
MAINTAIN AIRSPEED
Steep Turns
AOM DASH 8-Q400
CHAPTER 2
2.12-1
NORMAL PROCEDURES
2.12
LOW VISIBILITY OPERATION
2.12.1
Category II Operation
NOTE:
2.12.1.1
[Rev. 17] 30 JUN 2016
This procedure corresponds to Supplement 16 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
The Q400 has been shown to meet the performance criteria of JAR-AWO Subpart 2 for Category II Flight Director and Autopilot approaches with the following equipment or later standards:
Description
Part Number
Model Number
VHF NAV Receiver
066-01101-0060 or
400-048500-0105
VN-411B
CVN-251
2
Flight Guidance Module
(FGM)
C12429AA05 or
C12429AA06 or
C12429AA07 or
C12429AA08
IMS-100
2
Radio Altimeter
(RA)
066-01153-0101 or
822-0615-102 or
822-0615-312 or
822-0615-316
KRA-405B
ALT-4000
1
Air Data Unit
(ADU)
C17053AB02 or
C17053AC03 or
C17053AD04
ADU-3008
2
APIRS-207
APIRS-F207
2
Electronic Indication System
(EIS)
C19190AB03 or
C19190AB04 or
C19190AB05 or
C19190AB06 or
C19190AB07 or
C19190AB08 or
C19190AC07 or
C19190AC08 or
C19190BB08 or
C19190BC08 or
C19190BD08 or
C19190BE08 or
C19190BE09
SMD68
5
Input / Output Processor
C12432AA03 or
C12432AA04 or
C12432AA05 or
C12432AA06 or
C12432AB07 or
C12432AB09
IMS-100
2
420-00332-501 or
Attitude and Heading Reference Unit
261500123-0501 or
(AHRU)
261500123-2501
Windshield Wipers
NOTE:
Quantity
2
This Sub-Shapter does not constitute operational approval to conduct Category II Approaches
AOM DASH 8-Q400
CHAPTER 2
2.12-2
[Rev. 17] 30 JUN 2016
2.12.1.2
NORMAL PROCEDURES
Limitations
The limitations in Chapter 1 are applicable with the addition of the following:
1.
An ILS approach to Category II minimums must not be commenced or an approach continued unless the
above airborne equipment, associated control panels and ground installations are operating satisfactorily.
2.
An ILS approach to Category II minimums must not be continued if the DUAL FD message does not
appear on both PFDs by 1100 ft radio altitude.
3.
Category II approaches are limited to using flap 10° and 15° only for landing.
4.
Airplane must be in the landing configuration prior to the final approach fix.
5.
Autopilot Category II approaches in a crosswind component exceeding 18 kt or tailwind component
exceeding 10 kt or headwind component exceeding 24 kt are prohibited.
6.
Flight Director only Category II approaches in a crosswind component exceeding 10 kt or tailwind component exceeding 10 kt or headwind component exceeding 10 kt are prohibited.
7.
Category II approaches must be discontinued in the event of engine failure before or during landing
approach.
8.
Category II approaches are limited to glideslope angles of 2.5° to a maximum of 3.5°.
9.
The autopilot must be disengaged at or above a minimum altitude of 100 ft AGL.
2.12.1.3
CAT II Approach and Landing
The normal procedures in this chapter are applicable with the addition of the following:
1.
Ensure Decision Height (DH) is set on both PFDs prior to commencement of final approach.
2.
Observe that the DUAL FD message appears on both PFDs by 1100 ft radio altitude.
3.
Disengage autopilot at or above 100 ft AGL.
2.12.1.4
Procedures after Failures / Warnings in CAT II Approach
CAT II FAIL ANNUNCIATION OR NO DUAL FD ANNUNCIATION
1.
Discontinue CATEGORY II approach.
2.12.2
Low Visibility Take-Off
PIC - T/O Scanning is primarily head up with brief instrument reference until VR, then head down
2IC - Scanning is primarily head down with brief outside looking until V1.
These procedures are additional to the normal duties of PIC and 2IC during take-off.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.13-1
[Rev. 7] 7 MAR 2013
2.13
GPWS OPERATION
2.13.1
EGPWS - Enhanced Ground Proximity Warning System Honeywell MK V
(Option - CR 831 CH 00064 or CR 831 SO 90180)
NOTE:
2.13.1.1
This procedure corresponds to Supplement 64 of the AFM.
Flight Compartment Check - Power ON
# 1 NAV Receiver.......................................................................... Operative and Tuned to a VOR Frequency
FMS 1...................................................................................................................................... On and Initialized
FLAP Selector Lever ....................................................................................................................................... 0°
EFCP................................................................................................................................Select NAV and TERR
GPWS FLAP OVERRIDE Switch .................................................................................... Normal and Guarded
GPWS Caution Light .....................................................................................................................................Out
PULL UP - GPWS TEST Switch.......................................................................................... Press Momentarily
Check that the GPWS caution light, BELOW G/S and PULL UP advisory lights illuminate and
the “GLIDESLOPE”, “PULL UP” and “TERRAIN PULL UP” voice warnings are audible and
a “TERRAIN TEST” and the terrain test pattern is displayed on the MFDs.
NOTE:
2.13.1.2
Pressing PULL UP - GPWS TEST switch for longer than 3 s result in a long self test which
annunciates all configured and activated alert voices, including warning voices, caution voices
and altitude voices.
In-Flight Response to Warnings
1. Whenever the:
- “SINK RATE”
- “TERRAIN TERRAIN"
- “DON’T SINK”
- “TOO LOW - FLAPS”
- “TOO LOW - GEAR”
- “CAUTION TERRAIN”
- “CAUTION OBSTACLE”
- “BANK ANGLE”
- “GLIDESLOPE”
aural warnings are heard, take appropriate action to correct the unsafe condition.
2. Whenever the:
- “TOO LOW - TERRAIN”
- “TERRAIN PULL UP”
- “OBSTACLE PULL UP”
- urgent “PULL UP”
aural warnings are heard, immediately establish the power setting and attitude which will produce the maximum climb gradient consistent with the airplane configuration.
AOM DASH 8-Q400
CHAPTER 2
2.13-2
NORMAL PROCEDURES
[Rev. 9] 28 FEB 2014
Table 2.13-1 - Windshear Recovery / Terrain Avoidance Procedure
PF
PNF
Commands
“WIDSHEAR (TERRAIN) MAX POWER”
Sets Condition Levers to MAX
Follows up on Power Levers to set NTOP
Calls “POWER SET”
Monitors radar altimetre and IVSI
Calls “<radar altitude> FEET CLIMBING” or
“<radar altitude> FEET DESCENDING”
Simultaneously selects GA, advances Power
Levers towards NTOP, rolls wings level then
smoothly rotates aircraft to GA altitude
Aircraft Still Descending or GPWS Warning Continues
Advances POWER Levers to maximum available
Power (firewall)
Increases Pitch attitude suficient to stop descent
Do Not allow airspeed to decrease below V2 / VGA
If Stick Shaker Occurs (and / or Airspeed tape Turns red)
Immediately reduces Pitch attitude to silence
Shaker (achieves an airspeed above low speedcue) then adjust Pitch to return to V2 / VGA
Aircraft Climbing
Continues climb as required to Safe Altitude
Determines Safe Altitude
Calls “<obstacle clearance alt ASL> FEET”
Once Clear of Terrain
Reduces Power and Pitch attitude appropriate to
the phase of flight
Reconfigures aircraft as necessary
Advises ATC of any Deviation to clearance
AOM DASH 8-Q400
CHAPTER 2
2.13-3
NORMAL PROCEDURES
2.13.1.3
[Rev. 9] 28 FEB 2014
Normal Approach
GPWS LDG FLAP Selector Switch ...........................................................................10°, 15° or 35°, As Req’d
NOTE:
The GPWS LDG FLAP selector switch must be selected to the intended landing flap to ensure
correct GPWS flap advisory logic.
The following aural altitude callouts are heard as airplane descends through the respective radio altitudes:
Table 2.13-2
Aural Altitude Callouts
(3)
BASIC
Menu 28
-
Menu 85
(2)
Menu 34
(2)
“TWENTY FIVE HUNDRED” “TWENTY FIVE HUNDRED”
Menu 42
Radio
Altitude
(ft)
-
2500
-
1000
-
500
“ONE THOUSAND”
-
-
-
“FIVE HUNDRED”
-
“PLUS HUNDRED”
-
“MINIMUMS,
MINIMUMS”
“MINIMUMS”
“MINIMUMS”
“MINIMUMS”
DH
(1)
-
-
“ONE HUNDRED”
-
100
-
“FIFTY”
“FIFTY”
“FIFTY”
50
-
“FORTY”
“FORTY”
“FORTY”
40
“PLUS HUNDRED” 100 above DH
-
“THIRTY”
“THIRTY”
“THIRTY”
30
-
“TWENTY”
“TWENTY”
“TWENTY”
20
-
“TEN”
“TEN”
“TEN”
10
NOTES:
1. “MINIMUMS” is triggered from the PFD having the higher Decision Height (DH) setting.
2. When descending through 2500 ft (Radio Altitude) a “TWENTY FIVE HUNDRED” aural altitude callout may not be heard with MS 4-901021 not incorporated.
3. Depending on aircraft configuration, Configured Altitude Callouts may be verified by performing a “long self test”.
AOM DASH 8-Q400
THIS PAGE
I NT E N T ION A L L Y
LEFT
BLANK
CHAPTER 2
NORMAL PROCEDURES
2.14
TCAS OPERATION
2.14.1
Airborne Collision Avoidance System (ACAS II) and
2.14-1
[Rev. 9] 28 FEB 2014
Traffic Alert and Collision Avoidance System (TCAS II)
NOTE:
This procedure corresponds to:
- AFM Supplement 33 (ACAS II / TCAS II - HONEYWELL)
- AFM Supplement 106 (ACAS II / TCAS II - ACSS)
2.14.1.1
1.
ACAS II / TCAS II Operating Characteristics
ACAS II / TCAS II self test is inhibited in flight.
(Option: ACAS II / TCAS II - HONEYWELL)
2.
“INCREASE DESCENT” RA announcements are inhibited below 1450 ft AGL.
(Option: ACAS II / TCAS II - ACSS)
2. “INCREASE DESCENT” RA announcements are inhibited below 1650 ft AGL when climbing and below
1450 ft AGL when descending..
3. “DESCEND” RA announcements are inhibited below 1200 ft AGL when climbing and below 1000 ft AGL
when descending.
4.
All RAs are inhibited below 1100 ft AGL when climbing, below 900 ft AGL when descending.
5.
All ACAS II / TCAS II announcements are inhibited below 600 ft AGL when climbing and below 400 ft AGL
when descending.
6.
RA increase climb announcements and advisories are inhibited during the following conditions:
a. Landing gear down and flaps extended 15° or greater; or
b. Propeller Autofeather switch selected and the white ‘ARM’ annunciation on the ED.
7.
During an engine-out condition, climb announcements and advisories are inhibited.
8.
The ACAS II / TCAS II mode of operation automatically changes as follows:
a. TA ONLY mode to TA / RA mode at 1100 ft AGL when climbing.
b. TA / RA mode to TA ONLY mode at 900 ft AGL when descending.
2.14.1.2
1.
Traffic Advisory (TA) Announcements
“TRAFFIC TRAFFIC”
AOM DASH 8-Q400
Conduct visual search for the intruder.
CHAPTER 2
2.14-2
[Rev. 9] 28 FEB 2014
2.14.1.3
1.
2.
NORMAL PROCEDURES
Resolution Advisory (RA) Announcements
“CLIMB CLIMB”
“DESCEND DESCEND”
Climb at rate shown on the green arc of the IVSI / PFD.
Descend at rate shown on the green arc of the IVSI / PFD.
(Option: ACAS II / TCAS II - HONEYWELL)
Adjust rate of descent or climb to that shown on IVSI / PFD.
3. “ADJUST VERTICAL SPEED ADJUST”
(V7.0) or
“LEVEL OFF LEVEL OFF”
(V7.1)
(Option: ACAS II / TCAS II - ACSS)
3. “LEVEL OFF LEVEL OFF”
4.
“MONITOR VERTICAL SPEED”
5.
“CLEAR OF CONFLICT”
6.
“CLIMB CROSSING CLIMB
CLIMB CROSSING CLIMB”
7. “DESCEND CROSSING DESCEND
DESCEND CROSSING DESCEND”
8. “MAINTAIN VERTICAL SPEED
MAINTAIN”
9. “MAINTAIN VERTICAL SPEED
CROSSING MAINTAIN”
Promptly and smoothly reduce vertical speed to that shown on
IVSI / PFD
Monitor present vertical speed to prevent entering restricted red
arc speed.
Range is increasing and separation is adequate;
return to previous ATC assigned altitude.
Safe separation will be best achieved by climbing through the
intruder's flight path.
Safe separation will be best achieved by descending through the
intruder's flight path.
Maintain present vertical speed to prevent entering restricted red
arc speed.
Maintain present vertical speed to prevent entering restricted red
arc speed.
Indicates that own flight path will cross that of intruder.
The following voice messages are announced when the initial RA does not provide sufficient vertical separation from an intruder:
10. “INCREASE CLIMB
INCREASE CLIMB”
(received after CLIMB” advisory)
11. “INCREASE DESCENT
INCREASE DESCENT”
(received after “DESCEND” advisory)
“CLIMB - CLIMB NOW
CLIMB - CLIMB NOW”
(received after “DESCEND” advisory)
12. “DESCEND - DESCEND NOW
DESCEND - DESCEND NOW”
(received after “CLIMB” advisory)
NOTE:
Additional climb rate is required.
Additional descent rate is required.
A reversal from a descent to a climb condition is required to provide adequate vertical separation.
A reversal from a descent to a climb condition is required to provide adequate vertical separation.
ACAS II / TCAS II RA announcements are based on the pilot immediately adjusting the flight
profile as directed.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.14.1.4
NOTE:
2.14-3
[Rev. 9] 28 FEB 2014
In-Flight Use of TCAS
The following procedures correspond to:
- AFM Supplement 33 (ACAS II / TCAS II - HONEYWELL)
- AFM Supplement 106 (ACAS II / TCAS II - ACSS)
(Option: ACAS II / TCAS II - HONEYWELL)
NOTE:
GPWS alert takes priority over an ACAS RA.
(Option: ACAS II / TCAS II - ACSS)
NOTE:
GPWS alert takes priority over an TCAS TA / RA.
NOTE:
With MS 4-126388 Not Incorporated and with transponder P/N 066-01143-2101 installed, a
FAIL message may be displayed on the TCAS / ATC page of the ARCDU.
This FAIL message can be ignored unless accompanied by a TCAS FAIL message presented
on the PFD and MFD.
After Take-off, Climb, Cruise, Descent and Landing:
EFCP Range Knob .............................................................................................................................. As Req’d
Observe annunciation on ND / MFD.
TCAS / ATC page on ARCDU.............................................................................................................. As Req’d
Select ABOVE, BELOW or NORM as required, observe annunciation on ND / MFD.
Resolution Advisory
Autopilot .......................................................................................................................................... Disconnect
Immediately Adjust the Flight Profile............................................................................................As Directed
CAUTION: If stall warning (stickshaker) occurs during an RA maneuver, take immediate stall
recovery action.
CAUTION: If a threat aircraft track or altitude information is lost during an RA, the RA will
terminate without a “CLEAR OF CONFLICT” announcement.
AOM DASH 8-Q400
CHAPTER 2
2.14-4
[Rev. 9] 28 FEB 2014
2.14.2
NORMAL PROCEDURES
Mode S Transponder System for Elementary and Enhanced Surveillance
(Option - MS 4-309226 or MS 4-901280 or MS 4-457297 or MS 4-457530 or
MS 4-457576 or MS 4-457703 or MS 4-457719)
NOTE:
2.14.2.1
This procedure corresponds to AFM Supplement 82.
Normal Procedures
The normal procedures in this chapter are applicable with the addition of the following:
2.14.2.1.1 Pre-Taxi Checks
Aircraft Identification:
1.
FMS FPL MENU 2/2, LSK [3R]............................................................................................................Press
Check FLT NBR field is highlighted.
2.
Input the Aircraft Identification
3.
ENTER Key ..........................................................................................................................................Press
NOTES:
1. The FMS is capable of entering up to 10 alpha / numeric characters in the FLT NBR field
(e.g. ABC1234567) for Aircraft ID, however,
only the first 8 characters will be transmitted by the Mode S transponder (e.g. ABC12345).
2. In a dual FMS configuration, the Aircraft ID must be entered into FMS 1 for broadcast by
Transponder 1 or FMS 2 for broadcast by Transponder 2.
In a single FMS configuration, both transponders are connected to the FMS.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.15
Cold Weather Operations
2.15.1
Airplane Contamination on the Ground - Frost, Ice or Snow
2.15-1
[Rev. 13] 30 JAN 2015
Air regulation stipulate that take-off is prohibited when frost, ice or snow is adhering to any critical surface of
the airplane.
This principle is referred to as “the clean airplane concept” and is essential to the maintenance of flight
safety.
Regardless of the de-icing and anti-icing procedures used, the only method of ensuring flight safety in icing
conditions is by inspecting critical airplane surfaces and ensuring that they are clean before take-off.
The PIC has the ultimate responsibility to determine whether or not the airplane is safe to fly.
Frost less than 3 mm in depth is permitted on the underside of the fuel tank area of the wing.
This poses no concern.
The frost accumulation will dissipate as of post engine start, due to heat transfer from the fuel tanks.
A thin layer of hoar frost on the upper surface of the fuselage is not considered to be critical and can remain on the
fuselage for take-off.
Provided all vents and ports are clear of the frost and it is possible to distinguish fuselage surface features (markings
and lines).
References:
•
Holdover Time (HOT) Guidelines - Transport Canada
•
Guidelines for Aircraft Ground-Icing Operations (TP 14052E)
NOTE:
2.15.2
The above mentioned documents complement each other and should be used together.
It is the responsibility of the end user to periodically check the Transport Canada website for
updates on HOT Guidelines.
Ground De-Icing / Anti-Icing
DE-ICING is a procedure by which frost, ice or snow is removed from the airplane by applying hot water or a
hot mixture of water and de-icing / anti-icing fluid.
De-icing using infrared energy is an alternative procedure for removing frozen precipitation.
It is accomplished through heat that breaks the bond of adhering frozen contamination.
De-icing with forced air (alone or with injected fluid) is used to remove most of the contamination from aircraft
surfaces.
It will reduce de-icing times and fluid quantities, but it will not provide a clean wing for take-off.
ANTI-ICING consists of the application of a mixture of an anti-icing fluid or a mixture of anti-icing fluid and
water to the airplane to protect against the accumulation and adherence of frost, ice or snow to airplane surfaces before the condition exists.
TYPE I FLUIDS are used for de-icing and anti-icing, but provide very limited anti-icing protection.
TYPE II FLUIDS are “thickened” and are designed to be deposited in a thicker film and to remain on the airplane surfaces until the time of take-off.
TYPE II fluids are used for de-icing (when heated) and anti-icing and provide greater protection than do TYPE I
fluids against frost, ice or snow formation in conditions conducive to airplane on the ground.
Because of its flow-off characteristics it is not considered suitable for airplane with rotation speeds < 100 kt.
TYPE III FLUIDS are a “thickened” fluid that has properties that lie between TYPES I and II.
Because of its flow-off characteristics it is considered acceptable for airplane with rotation speeds below 100 kt
TYPE IV FLUIDS are similar to TYPE II fluids with a marked increase in holdover time capabilities.
ONE-STEP DE-ICING / ANTI-ICING consists of the application full strength or water diluted de-icing / antiicing fluid, heated as necessary considering the ambient temperature and weather condition, to both remove
and protect the surfaces from frost, ice or snow adherence and accumulation.
TWO-STEP DE-ICING / ANTI-ICING consists of de-icing with hot water only or a hot mixture of water diluted
de-icing / anti-icing fluid, followed immediately by anti-icing with an overspray of anti-icing fluid.
Care must be taken not to allow the airplane surfaces to re-freeze between the de-icing and anti-icing processes.
To prevent re-freezing, the first mixture (de-icing) fluid concentration may have to be increased appropriate to
local conditions.
AOM DASH 8-Q400
CHAPTER 2
2.15-2
[Rev. 13] 30 JAN 2015
NOTE:
NORMAL PROCEDURES
When anti-icing with SAE Type II, III and IV anti-icing fluids, it is strongly recommended that
the operator use the two-step de-icing / anti-icing procedure, the first step with heated water,
and / or heated SAE Type I de-icing fluid.
HOLDOVER TIME is the estimated time which anti-icing fluid will prevent ice, snow and / or frost from forming
or accumulating on the treated surfaces of an airplane.
The protection time is dependent upon the weather conditions and fluid mixture selected and cannot be precisely determined for each application.
Guidelines have been published for HOT under varying atmospheric conditions, however, it must be emphasized that the best method to ensure a clean airplane is to inspect after treatment and just prior to take-off.
If any frost, ice or snow is adhering to a critical surface, re-treatment must be requested.
While in most operations de-icing / anti-icing of the airplane is supervised by the maintenance organization, the
following precautions are presented to familiarize flight crews with potential problem areas:
a. De-icing / anti-icing fluid concentration must be adjusted for OAT before application to the airplane.
To determine the mixture percentage of de-icing / anti-icing fluid to water that should be used at a
given temperature, refer to the manufacturer’s specifications for the particular fluid;
b. It is strongly recommended Not to operate the Engines and APU during the de-icing / anti-icing procedure.
If it is necessary to have the engines running for operational reasons, select bleed air off to avoid sending fumes into the cabin.
c.
Do Not spray de-icing / anti-icing fluid directly into Engine or APU Inlets, Exhausts, Probe Inlets,
Scoops, Vents, Drains or other areas where the fluids may pool.
d. Do Not direct a solid stream of fluid perpendicular to airplane surfaces as a high pressure stream of
fluid can damage airplane surfaces.
Also, Do Not spray fluid directly on flight compartment windows and Do Not spray hot fluid directly on
cold windows;
e. Do Not force ice and snow into openings around flight control surfaces where it may re-freeze later;
f.
Both right and left sides of the wing and horizontal stabilizer must receive the same thorough de-icing /
anti-icing treatment.
g. When using infrared energy to de-ice, wet surfaces require an application of heated de-icing fluids to
preclude refreezing after removal of infrared energy source.
h. When using infrared energy other than to remove frost or leading edge ice and when OAT is at or
below 0°C (32°F), an additional treatment with hot de-icing fluid shall be preformed within the infrared
de-icing facility to prevent re-freezing of water, which may remain in hidden areas.
i.
If the aircraft requires re-de-icing and the de-icing / anti-icing fluids had been applied before flight, conventional de-icing / anti-icing with fluids shall be preformed before entering the infrared de-icing facility.
j.
The use of forced air alone to remove wet snow, especially during snowfall and cold outside air, is not
a feasible alternative for either a two-step de-icing or a one-step de-icing procedure.
k.
The forced air and fluid combination to remove wet snow will produce a clean wing but the time to refreeze is very short.
Following de-icing / anti-icing, it is the PIC who is ultimately responsible to see that the airplane is free of snow,
ice and frost; that pitot heads, static ports, fuel tank vents, air conditioning inlets / exits and landing gear doors
are clear of snow, ice and slush.
“Clear Ice”, which is difficult to detect, can be present below the layer of water and fluid remaining on the surface of the airplane and may require inspection by touch.
If any doubt remains as to the aerodynamic readiness of airplane, request re-treatment.
Residual fluid on the airplane following de-icing / anti-icing treatment may result in detrimental effects on handling and performance.
The magnitude of these effects, with the original de-icing fluid formulations (TYPE I fluids), was generally not
an operational problem.
With the advent of TYPE II, TYPE III and TYPE IV fluids, this is no longer true.
In general, the cruise, descent, approach and landing phases of flight are not affected by the use of de-icing or
anti-icing fluids.
When the airplane has been sprayed with de-icing and / or anti-icing fluids, the take-off procedures, distances
and reference speeds shall be adjusted as per Sub-Chapter 4.7.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.15.3
De-Icing Procedures
2.15.3.1
Pre-Fluid Application
2.15-3
[Rev. 18] 21 NOV 2016
Engines ........................................................................................................................ Shut Down (if possible)
If engines running:
BLEED Air ................................................................................................................................................... OFF
De-Icing Operator ................................................................................................................................ Advised
•
Engine must Not ingest de-icing fluid.
•
Avoid direct spray on the following:
- Intakes and exhausts, vents and drains
- Air data probes and sensors / ports and AOA vanes
- Windshields and all windows
- Antennas
•
Do Not spray hot fluid directly on cold windows.
•
Do Not spray high-pressure fluid perpendicular to airplane surfaces.
•
Avoid forcing snow / ice into parings around flight control surfaces.
2.15.3.2
Flap Configuration During Anti-Icing / De-Icing Procedures
Two possible options are: delaying flap deployment until just prior to take-off or deploying the flaps prior to deicing / anti-icing so that the surfaces under these flaps are treated.
With the second option, the holdover time and allowance time will be reduced due to the steeper angles of the
flap in the deployed configuration.
In this situation, it is acceptable to use the 90% adjusted holdover / allowance times.
Delaying the flap deployment may be the preferred option for optimum protection from ice buildup.
If it is necessary to remove contamination from the flaps, it may be best to deploy the flaps for de-icing and
anti-icing and then retract them prior to taxi.
2.15.3.3
Post-Fluid Application
Critical Areas ........................................................................................................................................ Inspect
•
Ensure the following:
- Airplane free of snow, ice and frost
- Control surfaces clean
- Protective covers removed
- Engine inlets, pitot static ports, fuel tank vents, air conditioning inlets / exits, landing gear doors clear of
snow / ice.
NOTE:
2.15.3.4
Following the application of de-icing or anti-icing fluids, it is strongly recommended that the
pilot conduct a slow control throw of the elevator and aileron / spoiler control circuits.
Move the control column and control wheel in both directions to the control stops.
Should a restriction of the controls or an unusual control force be noted, a take-off must not be
conducted until the affected control is inspected for ice contamination and if required, another
application of de-icing or anti-icing fluid is applied.
Taxi Precautions
Bypass Door ............................................................................................................................................. Open
•
Increase distance between airplane while taxiing.
•
Avoid the following:
- Reverse thrust;
- Excessive power to prevent displacement of applied fluids;
- Hot gases from preceding airplane.
AOM DASH 8-Q400
CHAPTER 2
2.15-4
[Rev. 15] 30 OCT 2015
2.15.4
NORMAL PROCEDURES
De-Icing and Anti-Icing Fluids
A. Fluids which meet the SAE Low Speed Aerodynamic Acceptance Test for the following specification:
- SAE Low Speed Type III
may be used full strength (or diluted per the fluid manufacturer’s instructions) over the fluid manufacturer’s
recommended temperature range, under the following conditions:
(1) All approved take-off flap settings
(2) Rotation should be smooth and at a normal rate, “Avoid Rapid Rotation”.
(3) No correction to the take-off distances and speeds is needed.
NOTE:
For SAE High Speed Type III apply the performance corrections of Paragraph B below.
B. Fluids which meet the SAE High Speed Aerodynamic Acceptance Test for the following specifications:
- SAE Type I
- SAE Type II
- SAE Type IV
may be used full strength (or diluted per the fluid manufacturer’s instructions) over the fluid manufacturer’s
recommended temperature range, under the following conditions:
(1) All approved take-off flap settings.
(2) Rotation should be smooth and at a normal rate. “Avoid Rapid Rotation”.
(3) Take-off distances available and corresponding speeds must be corrected by the margins as shown in
Table 1 in Sub-Chapter 4.7.3.
(4) Where close-in obstacle(s) impact the second climb segment, the increased V2 is to be maintained to a
gross height of 400 ft AGL.
Thereafter the uncorrected V2 must be flown to the end of the second climb segment.
For all other cases, the increased V2 may be continued to the end of the second climb segment.
C. SAE Type I fluids containing ethylene glycol at full strength or diluted and di-ethylene glycol or propylene
glycol when diluted 50 / 50 or more with water may be used with any flap setting over the fluid manufacturer’s recommended temperature ranges for these mixtures.
No correction to the take-off distances and speeds is needed.
In all cases de-icing / anti-icing fluids do not affect the following phases of flight:
• Cruise
• Descent
• Approach
• Landing
2.15.4.1
Holdover Times (HOT)
Holdover Time is the estimated time which anti-icing fluid will prevent ice, snow and / or frost from forming or
collecting on the treated surfaces of the airplane.
Factors that reduce HOT:
• Where conditions are worse than those given in the tables times may be reduced to the point of suspension of operations,
• High wind velocity
• Jet blast
• Aircraft skin temperature significantly lower than OAT
• Moisture content of snow, i.e. large snowflakes may produce higher than expected precipitation rates
AOM DASH 8-Q400
CHAPTER 2
2.15-5
NORMAL PROCEDURES
[Rev. 18] 21 NOV 2016
The definition of Lowest Operational Use Temperature (LOUT) for a given fluid is the higher (warmer) of:
- the lowest temperature at which the fluid meets the aerodynamic acceptance test (according to AS 5900)
for a given type of aircraft (high or low speed), or
- the actual freezing point of the fluid plus its freezing point buffer of:
→ 10°C (18°F) - for a Type I fluid, or
→ 7°C (13°F) - for a Type II, III or IV fluid.
For applicable values refer to the fluid manufacturer’s documentation.
NOTE:
Fluid manufacturers state that a fluid must not be used when the Outside Air Temperature
(OAT) or skin temperature is below the LOUT of the fluid
See the following Tables for specific HOT.
2.15.4.2
Active Frost HOLDOVER Guidelines for Winter 2016 - 2017
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
Outside Air Temperature
(OAT) 1, 2, 3
[°C]
[°F]
-1 and above
30 and above
below -1 to -3
below 30 to 27
below -3 to -10
below 27 to 14
below -10 to -14
below 14 to 7
below -4 to -21
below 7 to -6
below -21 to LOUT below -6 to LOUT
Outside Air Temperature
(OAT) 2, 3
[°C]
[°F]
-1 and above
30 and above
below -1 to -3
below 30 to 27
below -3 to -10
below 27 to 14
below -10 to -14
below 14 to 7
below -14 to -21
below -21 to -25
below -25
below 7 to -6
below -6 to -13
below -13
AOM DASH 8-Q400
Approximate HOLDOVER Times
[h:min]
Active Frost
Type I
Concentration Neat
Fluid / Water
[Vol % / Vol %]
100 / 0
75 / 25
50 / 50
100 / 0
75 / 25
50 / 50
100 / 0
75 / 25
100 / 0
75 / 25
100 / 0
100 / 0
100 / 0
0:45
Approximate HOLDOVER Times
[h:min]
Active Frost
Type II
Type III 4
Type IV
8:00
2:00
12:00
5:00
1:00
5:00
3:00
0:30
3:00
8:00
2:00
12:00
5:00
1:00
5:00
1:30
0:30
3:00
8:00
2:00
10:00
5:00
1:00
5:00
6:00
2:00
6:00
1:00
1:00
1:00
6:00
2:00
6:00
2:00
2:00
4:00
No HOT Guidelines exist
CHAPTER 2
2.15-6
NORMAL PROCEDURES
[Rev. 18] 21 NOV 2016
NOTES:
1
2
3
4
Type I Fluid / Water Mixture must be selected so that the freezing point of the mixture is at least 10°C
(18°F) below OAT.
Ensure that the LOUT is respected
Changes in OAT over the course of longer frost events can be significant; the appropriate HOT to use is the one provided for the coldest OAT that has occurred in the time between the de / anti-icing fluid application and take-off.
To use Type III Fluid frost holdover times, the fluid brand being used must be known.
AllClear AeroClear MAX must be applied unheated.
CAUTION: Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
2.15.4.3
Generic SAE TYPE I Fluid HOLDOVER Guidelines on Aluminum Wing Surfaces
for Winter 2016 - 2017 1
Guideline for Holdover Times (HOT) anticipated for SAE TYPE I Fluid Mixture as a Function of Weather Conditions and Outside Air Temperature (OAT)
Table 1-C (SAE TYPE I Fluid Holdover Guidelines on Composite Wing Surfaces) from Holdover Time (HOT)
Guidelines - Transport Canada, is not applicable.
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
Approximate HOLDOVER Times under Various Weather Conditions
[min]
OAT 2
[°C]
[°F]
Snow, Snow Grains or
Snow Pellets 3
Freezing
Fog
or
Ice
Crystals
Very
Light 4
Light
4
Light
Freezing
5 Freezing
Drizzle
Rain
Moderate
-3 and
above
27 and
above
11 - 17
18
11 - 18
6 - 11
9 - 13
4-6
below
-3 to -6
below
27 to 21
8 - 13
14
8 - 14
5-8
5-9
4-6
below
-6 to -10
below
21 to 14
6 - 10
11
6 - 11
4-6
4-7
2-5
below -10 below 14
5-9
7
4-7
2-4
Rain on
Cold
Soaked
Wing 6
Other 7
2-5
CAUTION:
No HOT Guidelines exist
NOTES:
1
2
3
4
5
6
7
Type I Fluid / Water Mixture must be selected so that the freezing point of the mixture is at least 10°C
(18°F) below OAT
Ensure that the LOUT is respected
To determine snowfall intensity, the ‘Snowfall Intensities as a Function of Prevailing Visibility’ table (SubChapter 2.15.4.10) is required.
Use light freezing rain HOT in conditions of very light or light snow mixed with light rain.
Use light freezing rain HOT if positive identification of freezing drizzle is not possible.
No HOT Guidelines exist for this condition for 0°C (32°F) and below
Heavy snow, ice pellets, moderate and heavy freezing rain, small hail and hail.
CAUTIONS:
•
•
•
•
•
The only acceptable decision-making criterion, for take-off without a pre-take-off contamination
inspection, is the shorter time within the applicable HOT table cell.
The time of protection will be shortened in heavy weather conditions, heavy precipitation rates or
high moisture content.
High wind velocity or jet blast may reduce HOT.
HOT may be reduced when aircraft skin temperature is lower than OAT.
Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
AOM DASH 8-Q400
CHAPTER 2
2.15-7
NORMAL PROCEDURES
2.15.4.4
[Rev. 18] 21 NOV 2016
SAE TYPE I De-Icing / Anti-Icing Fluid Application PROCEDURES
Guidelines for the application of SAE TYPE I Fluid Mixtures at minimum concentrations for the prevailing Outside Air Temperature (OAT)
OAT 1
One-Step PROCEDURE
De-Icing / Anti-Icing
Two-Step PROCEDURE
First Step: De-Icing
Second Step: Anti-Icing 2
Heated water or a heated
fluid / water mixture
Heated mix of fluid and water
Heated mix of fluid and water
with a freezing point of at Heated fluid / water mixture with a freezing point of at
below
least 10°C (18°F) below OAT with a freezing point at OAT least 10°C (18°F) below OAT
0°C (32°F) to LOUT
or below
0°C (32°F)
and above
1
Fluids must not be used at temperatures below their Lowest Operational Use Temperature (LOUT).
2
To be applied before first step fluid freezes, typically within 3 min.
(This time may be higher than 3 min in some conditions, but potentially lower in heavy precipitation or
colder temperatures.
If necessary, the second step shall be applied area by area.)
NOTES:
•
This table is applicable for the use of Type I HOT Guidelines in all conditions including active frost.
If HOT are not required, a temperature of 60°C (140°F) at the nozzle is desirable.
•
If HOT are required, the temperature of water or fluid / water mixtures shall be at least 60°C (140°F) at the
nozzle.
Upper temperature limit shall not exceed fluid and aircraft manufacturers’ recommendations.
•
To use Type I HOT Guidelines in all conditions including active frost, an additional minimum of
1 L/m2 (~ 2 gal/100 ft2) of heated Type I fluid mixture must be applied to the surfaces after all frozen contamination is removed.
This application is necessary to heat the surfaces, as heat contributes significantly to the Type I fluid HOT.
The required protection can be provided using a 1-step method by applying more fluid than is strictly
needed to just remove all of the frozen contamination (the same additional amount stated above is
required).
•
The LOUT for a given Type I fluid is the higher (warmer) of:
a) The lowest temperature at which the fluid meets the aerodynamic acceptance test for a given
aircraft type, or
b) The actual freezing point of the fluid plus its freezing point buffer of 10°C (18°F)
CAUTION: Wing skin temperatures may differ and in some cases may be lower than OAT;
a stronger mix (more glycol) may be needed under these conditions.
AOM DASH 8-Q400
CHAPTER 2
2.15-8
NORMAL PROCEDURES
[Rev. 18] 21 NOV 2016
2.15.4.5
Generic SAE TYPE II Fluid HOLDOVER Guidelines for Winter 2016 - 2017
Guideline for Holdover Times (HOT) anticipated for SAE TYPE II Fluid Mixture as a Function of Weather Conditions and Outside Air Temperature (OAT)
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
OAT 1
[°C]
[°F]
Type II
Fluid Concentration
Neat Fluid /
Water
Freezing
Fog
or
Ice
Crystals
Snow,
Snow Grains
or
Snow
Pellets 2, 3
Freezing
Drizzle 4
100 / 0
0:35 - 1:30
0:20 - 0:45
0:30 - 1:00
0:15 - 0:30 0:07 - 0:40
75 / 25
0:25 - 0:55
0:15 - 0:25
0:15 - 0:40
0:10 - 0:20 0:04 - 0:25
50 / 50
0:15 - 0:25
0:05 - 0:10
0:08 - 0:15
0:05 - 0:09
[Vol % / Vol %]
-3 and
above
below
-3 to -14
27 and
above
below
27 to 7
below
below
-14 to LOUT 7 to LOUT
Approximate HOLDOVER TIMES under Various Weather Conditions
[h:min]
100 / 0
75 / 25
100 / 0
0:20 - 1:05
0:25 - 0:50
Light
Freezing
Rain
0:15 - 0:30 0:20 - 0:45
7
0:10 - 0:20 7
0:08 - 0:20 0:15 - 0:25
7
0:08 - 0:15 7
0:20 - 0:35 8 0:08 - 0:10 8
Rain on
Cold
6
Soaked Other
Wing 5
CAUTION:
No HOT Guidelines exist
NOTES:
1
Ensure that the LOUT is respected.
Consider use of Type I when Type II fluid cannot be used.
2
To determine snowfall intensity, the ‘Snowfall Intensities as a Function of Prevailing Visibility’ table (SubChapter 2.15.4.10) is required.
3
Use light freezing rain HOT in conditions of very light or light snow mixed with light rain.
4
Use light freezing rain HOT if positive identification of freezing drizzle is not possible.
5
No HOT Guidelines exist for this condition for 0°C (32°F) and below.
6
Heavy snow, snow pellets, ice pellets, moderate and heavy freezing rain, small hail and hail.
7
No HOT Guidelines exist for this condition below - 10°C (14°F).
8
If the LOUT is unknown, no holdover time guidelines exist below - 22.5°C (- 8.5°F).
CAUTIONS:
•
The only acceptable decision-making criterion, for take-off without a pre-take-off contamination
inspection, is the shorter time within the applicable HOT table cell.
•
The time of protection will be shortened in heavy weather conditions, heavy precipitation rates or
high moisture content.
•
High wind velocity or jet blast may reduce HOT.
•
HOT may be reduced when aircraft skin temperature is lower than OAT.
•
Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
AOM DASH 8-Q400
CHAPTER 2
2.15-9
NORMAL PROCEDURES
2.15.4.6
[Rev. 18] 21 NOV 2016
SAE TYPE III Fluid HOLDOVER Guidelines for Winter 2016 - 2017
2.15.4.6.1 LOW SPEED TYPE III Fluid 1
ALLCLEAR AEROCLEAR MAX FOR AIRCRAFT CONFORMING TO THE SAE AS 5900
LOW SPEED AERODYNAMIC TEST CRITERION
Guideline for Holdover Times (HOT) anticipated for SAE TYPE III Fluid Mixture as a Function of Weather Conditions and Outside Air Temperature (OAT)
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
OAT 2
[°C]
[°F]
-3 and
above
27 and
above
Approximate HOLDOVER TIMES under Various Weather Conditions
Type III
[h:min]
Fluid Conor
centration Freezing Snow, Snow Grains
Rain on
Snow Pellets 3
Fog
Neat Fluid /
Freezing Light
Cold
7
or
Water
5 Freezing Soaked Other
Drizzle
Very
4
Rain
Ice
Moderate
4 Light
[Vol% / Vol%]
Wing 6
Crystals Light
100 / 0
0:45-1:10
1:00
0:30-1:00 0:14-0:30 0:20-0:45 0:14-0:20 0:06-0:40
0:45-1:25
1:00
0:30-1:00 0:14-0:30 0:20-0:40 0:15-0:25
0:30-1:05
1:00
0:30-1:00 0:14-0:30
75 / 25
50 / 50
below
below 100 / 0
-3 to -10 27 to 14
75 / 25
below
below
-10 to -16 14 to 3.2
100 / 0
CAUTION:
No HOT Guidelines exist
NOTES:
1
Fluid must be applied unheated to use these holdover times.
No HOT exist for Type III fluid applied heated
2
Ensure that the LOUT is respected.
Consider use of Type I when Type III fluid cannot be used.
3
To determine snowfall intensity, the ‘Snowfall Intensities as a Function of Prevailing Visibility’ table (SubChapter 2.15.4.10) is required.
4
Use light freezing rain HOT in conditions of very light or light snow mixed with light rain.
5
Use light freezing rain HOT if positive identification of freezing drizzle is not possible.
6
No HOT Guidelines exist for this condition for 0°C (32°F) and below.
7
Heavy snow, ice pellets, moderate and heavy freezing rain, small hail and hail.
CAUTIONS:
•
The only acceptable decision-making criterion, for take-off without a pre-take-off contamination
inspection, is the shorter time within the applicable HOT table cell.
•
The time of protection will be shortened in heavy weather conditions, heavy precipitation rates or
high moisture content.
•
High wind velocity or jet blast may reduce HOT.
•
HOT may be reduced when aircraft skin temperature is lower than OAT.
•
Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
For other SAE TYPE III fluids, check Transport Canada Guidelines for Holdover Times.
AOM DASH 8-Q400
CHAPTER 2
2.15-10
[Rev. 18] 21 NOV 2016
NORMAL PROCEDURES
2.15.4.6.2 HIGH SPEED TYPE III Fluid 1
ALLCLEAR AEROCLEAR MAX FOR AIRCRAFT CONFORMING TO THE SAE AS 5900
HIGH SPEED AERODYNAMIC TEST CRITERION
Guideline for Holdover Times (HOT) anticipated for SAE TYPE III Fluid Mixture as a Function of Weather Conditions and Outside Air Temperature (OAT)
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
OAT 2
[°C]
[°F]
-3 and
above
27 and
above
Approximate HOLDOVER TIMES under Various Weather Conditions
Type III
[h:min]
Fluid Conor
centration Freezing Snow, Snow Grains
Rain on
Fog
Snow Pellets 3
Neat Fluid /
Freezing Light
Cold
7
or
Water
5 Freezing Soaked Other
Drizzle
Very
4
Ice
Rain
Moderate
4 Light
[Vol% / Vol%]
Wing 6
Crystals Light
100 / 0
0:45-1:10
1:00
0:30-1:00 0:14-0:30 0:20-0:45 0:14-0:20 0:06-0:40
0:45-1:25
1:00
0:30-1:00 0:14-0:30 0:20-0:40 0:15-0:25
0:30-1:05
1:00
0:30-1:00 0:14-0:30
75 / 25
50 / 50
below
below 100 / 0
-3 to -10 27 to 14
75 / 25
below
below
-10 to -25 14 to -13
below
below
-25 to -35 -13 to -31
100 / 0
CAUTION:
No HOT Guidelines exist
100 / 0
0:15-0:40
0:40
0:19-0:40 0:09-0:19
NOTES:
1
Fluid must be applied unheated to use these holdover times.
No HOT exist for Type III fluid applied heated
2
Ensure that the LOUT is respected.
Consider use of Type I when Type III fluid cannot be used.
3
To determine snowfall intensity, the ‘Snowfall Intensities as a Function of Prevailing Visibility’ table (SubChapter 2.15.4.10) is required.
4
Use light freezing rain HOT in conditions of very light or light snow mixed with light rain.
5
Use light freezing rain HOT if positive identification of freezing drizzle is not possible.
6
No HOT Guidelines exist for this condition for 0°C (32°F) and below.
7
Heavy snow, ice pellets, moderate and heavy freezing rain, small hail and hail.
CAUTIONS:
•
The only acceptable decision-making criterion, for take-off without a pre-take-off contamination
inspection, is the shorter time within the applicable HOT table cell.
•
The time of protection will be shortened in heavy weather conditions, heavy precipitation rates or
high moisture content.
•
High wind velocity or jet blast may reduce HOT.
•
HOT may be reduced when aircraft skin temperature is lower than OAT.
•
Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
For other SAE TYPE III fluids, check Transport Canada Guidelines for Holdover Times.
AOM DASH 8-Q400
CHAPTER 2
2.15-11
NORMAL PROCEDURES
2.15.4.7
[Rev. 18] 21 NOV 2016
UNHEATED SAE TYPE III Fluid APPLICATION Procedures
Guidelines for the application of unheated SAE TYPE III fluid (minimum concentrations in % by volume) as a
function of Outside Air Temperature (OAT)
OAT 1
One-Step PROCEDURE
Two-Step PROCEDURE
Anti-Icing (only) 4
100 / 0, 75 / 25 or 50 / 50
Unheated Type III
fluid / water mixture
First Step: De-Icing
Second Step: Anti-Icing
Heated 3 water or
a Heated 3 Type I, II, III, or IV
fluid / water mixture
100 / 0, 75 / 25 or 50 / 50
Unheated Type III
fluid / water mixture
below
0°C (32°F)
to -3°C (27°F)
100 / 0, 75 / 25 or 50 / 50
Unheated Type III
fluid / water mixture
Heated 3 Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0, 75 / 25 or 50 / 50
Unheated Type III
fluid / water mixture
below
-3°C (27°F)
to -10°C (14°F)
100 / 0 or 75 / 25
Unheated Type III
fluid / water mixture
Heated 3 Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0 or 75 / 25
Unheated Type III
fluid / water mixture
below
-10°C (14°F)
to LOUT
100 / 0
Unheated Type III
fluid / water mixture
Heated 3 Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0
Unheated Type III
fluid / water mixture
0°C (32°F)
and above
1
Fluids must not be used at temperatures below their LOUT.
Consider the use of Type I when Type III fluid cannot be used (see Sub-Chapter 2.15.4.4).
The LOUT for a given Type III fluid is the higher (warmer) of:
a) The lowest temperature at which the fluid meets the aerodynamic acceptance test for a given aircraft
type;
b) The actual freezing point of the fluid plus its freezing point buffer of 7°C (13°F); or
c) For diluted Type III fluid, the coldest temperature for which holdover times are published.
2
To be applied before first step fluid freezes, typically within 3 min.
(This time may be longer than 3 min in some conditions, but potentially shorter in heavy precipitation, in
colder temperatures or for critical surfaces constructed of composite materials.
If necessary, the second step shall be applied area by area.)
3
For heated fluids, a fluid temperature not less than 60°C (140°F) at the nozzle is desirable.
4
One-step procedure with unheated Type III fluid is only possible on a clean aircraft.
If de-icing is required, a two-step procedure must be used.
NOTES:
•
Upper temperature limit shall not exceed fluid and aircraft manufactures’ recommendations.
CAUTIONS:
•
Wing skin temperatures may differ and in some cases may be lower than OAT;
a stronger mix (more glycol) may be needed under these conditions.
•
Whenever frost or ice occurs on the lower surface of the wing in the area of the fuel tank, indicating
a cold soaked wing, the 50 / 50 dilutions of Type III should not be used for the anti-icing step
because fluid freezing may occur.
•
An insufficient amount of anti-icing fluid may cause a substantial loss of HOT.
This is particularly true when using a Type I fluid mixture for the first step in a two-step procedure.
AOM DASH 8-Q400
CHAPTER 2
2.15-12
[Rev. 18] 21 NOV 2016
2.15.4.8
NORMAL PROCEDURES
Generic SAE TYPE IV Fluid HOLDOVER Guidelines for Winter 2016 - 2017
Guideline for Holdover Times (HOT) anticipated for SAE TYPE IV Fluid Mixture as a Function of Weather Conditions and Outside Air Temperature (OAT).
THE RESPONSIBILITY FOR THE APPLICATION OF THESE DATA REMAINS WITH THE USER
OAT 1
[°C]
[°F]
-3 and
above
27 and
above
Approximate HOLDOVER TIMES under Various Weather Conditions
Type IV
[h:min]
Fluid ConSnow, Snow Grains or
centration Freezing
Rain on
Snow Pellets 2
Fog
Light
Neat Fluid /
Freezing
Cold
6
or
Water
4 Freezing Soaked Other
Drizzle
Very
3
Ice
Rain
Moderate
3 Light
[Vol% / Vol%]
Wing 5
Crystals Light
100 / 0
below
below
-3 to -14 27 to 7
1:15-2:40
2:00
1:10-2:00 0:35-1:10 0:40-1:30 0:35-0:40 0:08-1:25
75 / 25
1:25-2:40
2:00
1:15-2:00 0:45-1:15 0:50-1:20 0:30-0:45 0:09-1:15
50 / 50
0:25-0:50
0:40
0:25-0:40 0:15-0:25 0:15-0:30 0:09-0:15
0:20-1:35
1:20
0:45-1:20 0:25-0:45 0:25-1:20 70:20-0:25 7
1:40
70:15-0:25 7
100 / 0
75 / 25
below -14 below 7
to LOUT to LOUT 100 / 0
0:30-1:10
0:45-1:40 0:20-0:45 0:15-1:05
0:20-0:40 8 0:20 8 0:10-0:20 80:08-0:10 8
CAUTION:
No HOT Guidelines exist
NOTES:
1
Ensure that the LOUT is respected.
Consider use of Type I when Type IV fluid cannot be used.
2
To determine snowfall intensity, the ‘Snowfall Intensities as a Function of Prevailing Visibility’ table (SubChapter 2.15.4.10) is required.
3
Use light freezing rain HOT in conditions of very light or light snow mixed with light rain.
4
Use light freezing rain HOT if positive identification of freezing drizzle is not possible.
5
No HOT Guidelines exist for this condition for 0°C (32°F) and below.
6
Heavy snow, ice pellets, moderate and heavy freezing rain, small hail and hail.
7
No HOT Guidelines exist for this condition below - 10°C (14°F)
8
If the LOUT is unknown, no HOT Guidlines exist below - 22.5°C (- 8.5°F).
CAUTIONS:
•
The only acceptable decision-making criterion, for take-off without a pre-take-off contamination
inspection, is the shorter time within the applicable HOT table cell.
•
The time of protection will be shortened in heavy weather conditions, heavy precipitation rates or
high moisture content.
High wind velocity or jet blast may reduce HOT.
HOT may be reduced when aircraft skin temperature is lower than OAT.
•
Fluids used during ground de-icing / anti-icing do not provide in-flight icing protection.
AOM DASH 8-Q400
CHAPTER 2
2.15-13
NORMAL PROCEDURES
2.15.4.9
[Rev. 18] 21 NOV 2016
SAE TYPE II and TYPE IV Fluid APPLICATION Procedures
Guidelines for the application of SAE TYPE II and IV fluid mixtures (minimum concentrations in % by volume)
as a function of Outside Air Temperature (OAT)
OAT 1
One-Step PROCEDURE
Two-Step PROCEDURE
De-Icing / Anti-Icing
First Step: De-Icing
0°C (32°F)
and above
100 / 0, 75 / 25 or 50 / 50
Heated 3 Type II or IV
fluid / water mixture
Heated water or
a Heated Type I, II, III, or IV
fluid / water mixture
Second Step: Anti-Icing 2
100 / 0, 75 / 25 or 50 / 50
Type II or IV
fluid / water mixture
below
0°C (32°F)
to -3°C (27°F)
100 / 0, 75 / 25 or 50 / 50
Heated 3 Type II or IV
fluid / water mixture
Heated Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0, 75 / 25 or 50 / 50
Type II or IV
fluid / water mixture
below
-3°C (27°F)
to -14°C (7°F)
100 / 0 or 75 / 25
Heated 3 Type II or IV
fluid / water mixture
Heated Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0 or 75 / 25
Type II or IV
fluid / water mixture
below
-14°C (7°F)
to LOUT
100 / 0
Heated 3 Type II or IV
fluid / water mixture
Heated Type I, II, III, or IV
fluid / water mixture with a
freezing point at OAT or below
100 / 0
Type II or IV
fluid / water mixture
1
Fluids must not be used at temperatures below their LOUT.
Consideration to be given to the use of Type I / III when Type II / IV fluid cannot be used due to LOUT limitations.
The LOUT for a given Type II / IV fluid is the higher (warmer) of:
a) The lowest temperature at which the fluid meets the aerodynamic acceptance test for a given aircraft
type;
b) The actual freezing point of the fluid plus its freezing point buffer of 7°C (13°F); or
c) For diluted Type II / IV fluid, the coldest temperature for which holdover times are published.
2
To be applied before first step fluid freezes, typically within 3 min.
(This time may be higher than 3 min in some conditions, but potentially lower in heavy precipitation or
colder temperatures.
If necessary, the second step shall be applied area by area.)
3
Clean aircraft may be anti-iced with unheated fluid.
NOTES:
•
For heated fluids, a fluid temperature not less than 60°C (140°F) at the nozzle is desirable.
•
Upper temperature limit shall not exceed fluid and aircraft manufactures’ recommendations.
CAUTIONS:
•
Wing skin temperatures may differ and in some cases may be lower than OAT;
a stronger mix (more glycol) may be needed under these conditions.
•
Whenever frost or ice occurs on the lower surface of the wing in the area of the fuel tank, indicating
a cold soaked wing, the 50 / 50 dilutions of Type II or IV shall not be used for the anti-icing step
because fluid freezing may occur.
•
An insufficient amount of anti-icing fluid may cause a substantial loss of HOT.
This is particularly true when using a Type I fluid mixture for the first step in a two-step procedure.
AOM DASH 8-Q400
CHAPTER 2
2.15-14
NORMAL PROCEDURES
[Rev. 18] 21 NOV 2016
2.15.4.10
SNOWFALL INTENSITIES as a FUNCTION of PREVAILING VISIBILITY 1
Lighting
[°C]
[°F]
Heavy
Moderate
Light
Very Light
-1
and above
30
and above
≤ 1.6
(≤ 1)
> 1.6 to 4.0
(> 1 to 21/2)
> 4.0 to 6.4
(> 21/2 to 4)
> 6.4
(> 4)
below
-1
below
30
≤ 1.2
(≤ 3/4)
> 1.2 to 2.4
(> 3/4 to 11/2)
> 2.4 to 4.8
(> 11/2 to 3)
> 4.8
(> 3)
-1
and above
30
and above
≤ 0.8
(≤ 1/2)
> 0.8 to 2.4
(> 1/2 to 11/2)
> 2.4 to 4.8
(> 11/2 to 3)
> 4.8
(> 3)
below
-1
below
30
≤ 0.6
(≤ 3/8)
> 0.6 to 1.4
(> 3/8 to 7/8)
> 1.4 to 3.2
(> 7/8 to 2)
> 3.2
(> 2)
Darkness
Daylight
1
VISIBILITY in Snow
[km (SM)]
Temperature Range
Based on:
- Relationship between Visibility and Snowfall Intensity (TP 14151E), TC, Nov 2003 and
- Theoretical Considerations in the Estimation of Snowfall Rate Using Visibility (TP 12893E), TC, Nov 1998.
HOW TO READ THE TABLE
This visibility table applies to all fluid Types I, II, III and IV.
Assume that the daytime visibility in snowfall is 1.6 km (1 SM) and the temperature is - 7°C (19°F).
Based on these conditions, the snowfall intensity is light.
This snowfall intensity is used to determine which HOT Guideline value is appropriate for the fluid in use.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.16
2.16-1
[Rev. 13] 30 JAN 2015
Operating in Icing Conditions
ICING CONDITIONS exist when:
•
the Static Air Temperature (SAT) on the ground and for take-off is 10°C (50°F) or below, or
•
the SAT in flight is 5°C (41°F) or below, and
•
visible moisture in any form is present (such as clouds, fog with visibility of one statute mile or less, rain,
snow, sleet or ice crystals).
•
ice accretion on aerodynamic surfaces is not considered to exist at temperatures of - 40°C or below.
Icing Conditions also exist when:
•
the SAT on the ground and for take-off is 10°C or below when operating on ramps, taxiways or runways
where surface snow, ice, standing water or slush may be ingested by the engines or freeze on engines,
nacelles or engine sensor probes.
As with any meteorological hazard, the most effective procedure is to stay away from the known areas
involved.
WARNING:
SEVERE ICING CONDITIONS:
Flight into freezing rain, freezing drizzle or mixed icing conditions (super-cooled liquid water and ice
crystals) may result in ice build-up on protected surfaces, exceeding the capability of the ice protection system or may result in ice forming aft of the protected surfaces.
This ice may not be shed using the ice protection systems and may seriously degrade the performance
and controllability of the airplane.
Severe icing conditions may be encountered during flight in visible rain with the SAT below 0°C ambient temperature and specifically with droplets that are large enough to splash or splatter on impact.
Severe icing may be identified by unusually extensive ice accreted on the airframe in areas not normally observed to collect ice or ice is accreted on the side windows of the flight compartment aft of the
leading edge.
An Accumulation of ice on lifting surfaces of the airplane may change the stall characteristics, stall
speed or warning margin provided by the stall warning system.
The presence of ice on the airframe increases airplane drag and mass.
Ice on the propellers decreases their efficiency and thus the thrust available from the engines.
Ice build-up on engine probes can result in erroneous engine FADEC operation or flight compartment
indications.
Finally, ice ingestion by the engine or inlet flow distortions due to ice build-up on the intakes, can
cause engine surging or flameouts.
To provide the largest safety margin possible for the airplane encountering icing conditions, it is necessary to operate the de-icing / anti-icing systems and fly the airplane as per the procedures of Chapter 2 of this AOM.
Details of performance penalties in icing condition are provided in Chapter 4.
Elaboration on the AOM procedures is provided below.
AOM DASH 8-Q400
CHAPTER 2
2.16-2
[Rev. 13] 30 JAN 2015
2.16.1
NORMAL PROCEDURES
Taxi
Ensure the following anti-ice systems are selected
PITOT STATIC STBY, 1 & 2 ...................................................................................................................... ON
ENG INTAKE BYPASS DOORS ................................................................................................ OPEN / HTR
During taxi on slush covered surfaces, where possible, minimize taxi speeds to below 10 kt.
Faster taxi speeds increase the chance of slush / contaminate entering the nose wheel bay.
Where possible, avoid taxiing through deep slush.
Avoid using excessive power to taxi airplane as this may tend to displace any anti-icing fluid applied.
Also, avoid using reverse power on snow or slush covered runways, taxiways or ramps unless absolutely necessary, as snow, slush or water can become airborne and adhere to wing surfaces.
Allow a greater than normal distance between airplane to account for poor braking and turning performance on
slippery surfaces.
This will also reduce the possibility of snow or slush being blown back into the airplane or hot exhaust gases
melting snow on your airplane from which re-freezing may occur.
2.16.2
Take-Off
Before take-off into icing conditions, select all anti-ice systems, except airframe de-ice, as follows:
ENG INTAKE BYPASS DOORS ................................................................................................ OPEN / HTR
PROP TMR ............................................................................................................................................... ON
DEICE PRESS ................................................................................................................... Check 18 ± 3 psi
WINDSHIELD HEAT ........................................................................................................................... NORM
Selection of the REF SPEEDS switch raises the stall warning threshold, therefore, airspeed must be
INCREASED to maintain adequate margin over stall warning following take-off and prior to selection of the
switch to ON at 400 ft AGL.
Refer to Sub-Chapter 4.7 of the AOM for the appropriate values.
Failure to increase speed may result in stall warning.
Before moving into position, re-check that the airplane is free of ice, snow or frost.
Before brake release, check for stable engine operation.
After setting take-off power, check to see that flight compartment indicators are normal.
NOTE:
The following performance implications must be considered for take-offs into icing conditions:
-
The AC generator electrical demand by the anti-icing systems takes power away from the propeller gear
box, reducing net engine power available to the airplane.
This results in increased take-off field lengths and reduced climb gradients and MAT limits.
-
In addition to the reduction in net engine power due to electrical loads, the increased take-off speeds
above 400 ft due to stall warning margins also degrade airplane performance.
The combination of these factors results in decreased Final Take-off Climb gradients and increased 3rd
segment distances.
For take-off on slush covered surfaces, accelerate through 40 kt IAS as rapidly as possible
NOTE:
Following ground manoeuvering on taxiways and runways contaminated with slush, where the
taxi and take-off precautions, as described in Sub-Chapters 3.3.6.1 and 3.3.6.2, were not
followed and Nose Wheel Bay contamination is suspected, consider cycling the landing gear a
minimum of 2 times after take-off.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.16.3
2.16-3
[Rev. 13] 30 JAN 2015
Enroute, Climb, Cruise and Descent
Before entering icing conditions or when “ICE DETECTED” message appears on the ED select all anti-ice systems and REF SPEEDS to INCR.
In Icing Conditions monitor accumulation of ice on the airframe.
Operate the airframe de-ice system in FAST or SLOW depending on the rate of accumulation.
Do not wait for ice to build up before selecting airframe de-ice.
Climb no slower than Enroute Climb Speed (VCLIMB) + 20 KIAS and, cruise and descend no slower than Flap
1.23 VS + 25 KIAS to account for the increase in stall speed of the airplane with ice accumulated on the boot
surfaces between cycles and on unprotected surfaces.
These speed increments must be added whenever the REF SPEEDS switch is selected, regardless of whether
or not ice has actually accumulated on the airplane.
Monitor airplane climb rate and airspeed closely.
Be prepared to increase propeller RPM and engine power if a significant loss of performance is noted.
By acting early in a significant icing encounter, the ultimate performance loss may be minimized and if conditions are sufficiently severe to require a change in flight plan, the decision can be made before sustaining an
unacceptable decrease in airplane performance.
Note that a small weight and drag penalty on the airplane, due to accumulated ice on the airframe, combined
with decreased net engine power due to electrical loads and the increased climb speed result in a reduction in
Enroute Climb Gradient and One Engine Inoperative Climb Ceiling.
After flight in icing conditions leave the airframe de-ice system operating.
Monitor the left and right wing leading edges and wing tips.
The airplane is not considered to be aerodynamically clean until all ice is removed from the visible leading
edges and wing tips.
Once ice is no longer visible deselect de-icing and anti-icing systems and select the REF SPEEDS switch OFF
2.16.4
Holding and Approach
Before entering the hold or commencing approach, re-confirm all anti-icing systems are selected.
The AIRFRAME selector must be selected to FAST for the entire hold, approach and landing.
When holding in icing conditions, the landing gear must be retracted and flaps at Flap 0° setting.
Hold at an airspeed no slower than 190 KIAS.
The increased airspeed ensures an adequate airspeed margin above stall speed and the increased airspeed
and Flap 0° configuration decrease the angle of attack on the wing, maximizing the efficiency of the boot deicing system.
Prior to commencing approach, revised approach, landing and go-around speeds must be calculated.
Refer to Chapter 4 of the AOM for the appropriate values.
Again, all increases account for actual stalling speeds with ice on protected surfaces of the airplane and raised
stall warning thresholds.
Accumulated ice on the airframe extracts a small mass penalty on the airplane and combined with the
increased approach and landing speeds, result in an increase in Landing Field Lengths and Brake Energies.
The mass penalty on the airplane, as well as decreased net engine power due to electrical loads, combined
with the increased go-around speed result in a reduction in Landing MAT limits and Approach and Balked
Landing Climb gradients.
AOM DASH 8-Q400
CHAPTER 2
2.16-4
[Rev. 13] 30 JAN 2015
2.16.5
NORMAL PROCEDURES
Landing
The airplane should be flown to a firm touchdown at the aiming point.
Immediately after main wheel touchdown, retard the Power Levers to DISC and lower the nose wheel to the
runway to enhance directional control. Apply anti-skid brakes as required.
On landing on slush covered surfaces, decelerate through 40 kt IAS to taxi speed 10 kt, as rapidly as possible.
Let the anti-skid system do its work. Do Not pump the brake pedals.
The anti-skid system will monitor the onset of tire skidding and modulate brake pressures to achieve maximum
braking.
Avoid the use of reverse thrust on icy or slippery runways.
If reverse thrust is used in a crosswind, be prepared for a possible down-wind drift on slippery runways.
To correct back to the runway centerline, advance the Power Levers toward Flight Idle and reduce braking.
After regaining directional control, increase braking and select DISC.
Do Not select reverse thrust unless required.
If the Water Equivalent Depth (WED) of contaminant on the runway surface is greater than 3 mm (0.125 in),
selection of Power Levers aft of DISC is prohibited to avoid ingesting contaminant into the engines and suffering a possible flame-out.
Do Not attempt to turn off the runway until speed has been reduced to a manageable level.
2.16.6
Parking
2.16.6.1
Cold Weather Parking
1.
Remove the snow, slush, or ice from the area where you will park the airplane.
NOTE:
If this is not possible, remove the contamination around the tires of the main and the nose
landing gear only.
If you do not do this, the tires can freeze to the ground
2.
Park the airplane.
3.
Remove all snow, slush, or ice from the engine intakes and exhausts.
4. Install all plugs and covers supplied for the airplane.
NOTE:
In very cold weather, apply a thin brush layer of anti-icing fluid to the covers or they can freeze
to the airplane.
5. If you will park the airplane in the cold for a long time, do the steps that follow:
a. Drain the fluid from the lavatory tank and the warm water wash system.
b. Drain the galley liquid containers.
c. Close all airplane doors.
6. If you park the airplane in ambient temperatures lower than - 20°C (- 4°F), the battery temperatures shown
on the electrical page of the multi-function display (written as the “MFD” in this procedure) must be equal to
or greater than - 20°C (- 4°F) prior to dispatch.
NOTE:
There is no battery temperature limitation to start the engines or the auxiliary power unit.
7. If you park the airplane in temperatures lower than - 15°C (5°F) for longer than 3 h, you must permit a
warm-up period for the displays that follow before they become functional:
i)
PFD
ii)
MFD
iii) ED
iv) ARCDU
v) Standby VHF # 1 Control Panel
vi) FMS (if installed)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17
2.17-1
[Rev. 13] 30 JAN 2015
NORMAL EXPANDED PROCEDURES and CHECKLISTS
This section presents the abbreviated flight compartment checklist (QRH - Quick Reference Handbook), provided with each Q400, in expanded form.
Should any conflict exist between this information and the checklist in the Airplane Flight Manual, the Flight
Manual shall take priority.
Any implied techniques presented assume that proper pilot skill and judgement are exercised.
All items shown in bold are reproduced from the QRH.
Items marked with stars are part of the ‘SYSTEMS CHECK ONCE EVERY 24 HOURS – FLYING DAY’.
2.17.1
FLIGHT COMPARTMENT PREPARATION
2.17.1.1
PREFLIGHT
All checklists should be completed early enough so as to allow both pilots to monitor their surroundings while
taxiing to the active runway, especially the line-up checklist.
External Check ............................................................................................................................... Completed
Documentation ....................................................................................................................................... Check
Check all required aircraft documents are on-board.
Locking Devices .................................................................................................................................. Remove
Ensure the following are removed:
•
Main gear safety lock pins,
•
Nose landing gear lock is disengaged,
•
Airstair and baggage door external locking devices,
•
Forward right hand, aft left and aft right hand emergency door internal locking devices.
2.17.2
FLIGHT COMPARTMENT PREPARATION – POWER OFF
Safety Equipment .............................................................................................. Check Serviceable & Secure
Safety equipment includes:
•
Observer’s Life Vest stowed above observer’s seat.
Make sure life jacket is secured, serviceable and not damaged,
•
Co-Pilot’s Life Vest, stowed above the co-pilot’s seat.
Make sure life jacket is secured, serviceable and not damaged,
•
Hydraulic Pump Handle - stowed on the bulkhead behind the co-pilot’s seat,
•
Protective Breathing Equipment - stowed and seal unbroken,
•
Observer’s Smoke Goggles - stowed on the bulkhead behind the co-pilot’s seat.
•
Portable Fire Extinguisher - stowed on the bulkhead behind the captain’s seat.
Check pressure gauge indicates in the green range,
•
Two Flashlights - stowed on the bulkhead behind the captain’s seat. Check serviceability,
•
Fire Axe - securely stowed on the bulkhead behind the captain’s seat,
•
Captain’s Life Vest - stowed above the captain’s seat.
Make sure life jacket is secured, serviceable and not damaged,
•
Emergency Rope - stowed at left of the escape hatch above the captain’s seat.
Make sure rope is secured to the airplane.
Escape Hatch ......................................................................................................................................... Secure
Make sure FLIGHT COMPARTMENT EMERGENCY EXIT HATCH is closed, secured and
the handle is selected to CLOSED position before starting engines.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-2
[Rev. 13] 30 JAN 2015
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION – POWER OFF (cont’d)
Oxygen Mask / QTY ................................................................................................................................ Check
For the captain’s, co-pilot’s and observer’s (if installed) oxygen masks, check the following:
• Make sure the oxygen mask is clean and in good condition.
• Make sure hose is correctly attached and flow indicator shows green.
• The mask microphone jack must be inserted in the correct jack position on the audio jack panel.
• Check the oxygen gauge on the co-pilot’s panel. The Minimum Dispatch Pressure at 21°C (70°F) is:
(Option - CR 835 SO 90241)
2 crew
1300 psi
1050 psi
3 crew
1800 psi
1450 psi
Circuit Breakers ...................................................................................................................................... Check
Before entering the seats, make sure all circuit breakers are closed (pushed in).
Check for open circuit breakers visibly from the side.
Landing Gear Alternate Release and Extension Doors ..................................................................... Closed
Make sure the LANDING GEAR ALTERNATE RELEASE DOOR (above the co-pilot’s seat)
and LANDING GEAR ALTERNATE EXTENSION DOOR (on the floor, left of the co-pilot’s seat)
are completely closed before each flight.
L/G Inhibit Switch .................................................................................................................................. NORM
Make sure the LANDING GEAR EXTENTION INHIBIT SWITCH is set to NORMAL with the red guard closed.
If using DC External Power, proceed with For DC External Power (Sub-Chapter 2.17.2.1)
If using APU Power, proceed with For APU Power (Sub-Chapter 2.17.2.2)
If using Battery Power, proceed with For Battery Power Only (Sub-Chapter 2.17.2.3)
2.17.2.1
FOR DC EXTERNAL POWER
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ ON
• The BATTERY MASTER switch connects main, auxiliary and standby batteries
to the right and left essential buses.
• The MAIN BATT switch connects the main battery to the right main feeder bus.
• The AUX BATT switch connects the auxiliary battery to the left main feeder bus.
• The STBY BATT switch connects the standby battery to the left main feeder bus.
Main Bus Tie ................................................................................................................................................ Tie
Manually connects the left and right main buses together.
All Displays .................................................................................................................................................. ON
Check voltages on Electrical page of MFD.
DC EXT Power .............................................................................................................................................. ON
With DC external power available, set DC EXT PWR switch to EXT PWR position and confirm that:
• DC EXT POWER in green font appears on the MFD Electrical Systems page.
NOTE:
With External Power (EP) charge feature, the main, auxiliary and standby batteries remain
connected to the main buses.
Bus Voltage ............................................................................................................................................. Check
Check voltages on Electrical page of MFD.
• If external DC voltage is less than 27.5 V:
- MAIN BATT, AUX BATT and STBY BATT switches - OFF.
- Check MAIN BATTERY, AUX BATTERY and STBY BATTERY caution lights illuminate.
• If external DC voltage is greater than 31.5 V, external power will automatically de-energize.
Recirc Fan (MS 4-126236 Not Incorporated) ............................................................................................... ON
Continue with FLIGHT COMPARTMENT PREPARATION – POWER ON - CAPTAIN, Sub-Chapter 2.17.3.1.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.2.2
NOTE:
2.17-3
[Rev. 13] 30 JAN 2015
FOR APU POWER
This procedure corresponds to AFM Supplement 6.
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ......................................................................... On
• The BATTERY MASTER switch connects main, auxiliary and standby batteries
to the right and left essential buses.
• The MAIN BATT switch connects the main battery to the right main feeder bus.
• The AUX BATT switch connects the auxiliary battery to the left main feeder bus.
• The STBY BATT switch connects the standby battery to the left main feeder bus.
MAIN BUS TIE ............................................................................................................................................... Tie
All Displays ................................................................................................................................................... On
Check voltages on Electrical page of MFD.
Caution / Advisory Lights .......................................................................................................................... Test
Hold CAUT / ADVSY LIGHTS TEST switch at TEST CAUT and make sure:
• Master CAUTION and WARNING lights flash,
• APU caution and CHECK FIRE DET warning lights illuminate and all remaining warning lights flash,
• Press master CAUTION light and check light goes out,
• Press master WARNING light and check light goes out and warning lights cease flashing,
Hold at ADVSY - Check all advisory lights illuminate.
APU PWR ...................................................................................................................................................... On
Push APU PWR switchlight on the APU CONTROL panel.
Check APU FUEL VALVE OPEN advisory light illuminates.
* APU FIRE Detection ............................................................................................................................... TEST
Press and hold APU FIRE TEST switch and check:
• APU FUEL VALVE OPEN advisory light out,
• APU caution light and CHECK FIRE DET warning light illuminate,
• APU FIRE, APU FAULT, APU BLT ARM, APU FUEL VALVE CLOSED, APU EXTG and APU FAIL advisory
lights illuminate,
• Master CAUTION and master WARNING lights flash.
Release APU FIRE TEST switch and check:
• APU FUEL VALVE OPEN advisory light illuminates,
• APU caution light and CHECK FIRE DET warning light go out,
• APU FIRE, APU FAULT, APU BLT ARM, APU FUEL VALVE CLOSED, APU EXTG and APU FAIL advisory
lights go out,
• Master CAUTION and master WARNING lights go out.
Position Lights ............................................................................................................................................. On
CAUTION: Ensure ground personnel and equipment are clear of the APU exhaust port.
APU START Switch ................................................................................................................................. Press
Push and release the START switchlight. Check STARTER advisory light (amber) illuminates then goes out.
Confirm STARTER amber light goes off and green RUN advisory light in APU PWR switchlight illuminates to
show APU is operating. GEN WRN light illuminates.
APU GEN ................................................................................................................................................. Press
Check GEN ON advisory light illuminates.
NOTE:
If external power is selected, APU GEN WARN advisory light will remain illuminated.
APU Generator Volts / Load .................................................................................................................. Check
Read voltages on the MFD Electrical Systems page.
Confirm APU load decreasing as the batteries re-charge (maximum continuos load 1.0).
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-4
[Rev. 18] 21 NOV 2016
NORMAL PROCEDURES
FOR APU POWER (cont’d)
Battery Temperature ............................................................................................................................... Check
Monitor battery temperature after APU start on the MFD - Electrical Systems page.
BLEED AIR 1 and 2 ........................................................................................................................... MIN / OFF
TEMP CONTROL ............................................................................................................................. AUTO / Set
The setting of these switches may vary depending on temperature requirements:
• Set both PACK CONTROL switches to the AUTO position.
• Turn the PASSENGER CABIN TEMPERATURE knob counter-clockwise to the FA position or as required.
• Turn the FLT COMP TEMPERATURE knob as required.
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... On
APU Bleed (20 s) ................................................................................................................................ As Req’d
Push and release the APU BL AIR switchlight. Make sure the BL AIR OPEN light illuminates.
NOTES:
1. Wait 20 s after APU RUN advisory light illuminates before selecting APU BL AIR switch on.
2. The APU consumes approximately 188 lb/h of fuel.
Ensure there is a minimum of 1000 lb of fuel in # 1 tank plus the quantity required for the
duration of APU operation.
Continue with FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN, Sub-Chapter 2.17.3.1.
2.17.2.3
FOR BATTERY POWER ONLY
DC GEN 1 and 2 ............................................................................................................................................ On
MAIN BUS TIE .............................................................................................................................................. Tie
Manually connects right main feeder bus to the left main feeder bus.
ICE PROTECTION ...................................................................................................................................... OFF
Make sure all switches on the ICE PROTECTION panel are set to OFF.
External Lighting ....................................................................................................................................... OFF
All switches on the EXTERIOR LIGHTING CONTROL panel are set to OFF.
IGNITION 1 and 2 ..................................................................................................................................... NORM
Set IGNITION CONTROL 1 and 2 switches to NORM position.
RECIRC Fan [with MS 4-126236 Not Incorporated] ................................................................................... OFF
BLEED AIR 1 and 2 ........................................................................................................................... MIN / OFF
• Turn the BLEED AIR FLOW CONTROL to MIN.
• Set BLEED CONTROL switches to OFF.
Emergency Lights .................................................................................................................................... ARM
Set EMER LIGHTS switch to ARM and
make sure the EMER LTS DISARMED caution light goes off.
Passenger Signs .......................................................................................................................................... ON
Set passenger signs switches to FASTEN BELTS and NO SMOKING.
POWER Levers ......................................................................................................................................... DISC
Condition Levers ............................................................................................................................. FUEL OFF
Briefing .................................................................................................................................................. Review
Continue with START APPROVED, in the following Sub-Chapter.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.2.4
2.17-5
[Rev. 13] 30 JAN 2015
START APPROVED
(Battery Power Only)
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ ON
•
The BATTERY MASTER switch connects main, auxiliary and standby batteries to the right and left essential busses.
•
The MAIN BATT switch connects the main battery to the right main feeder bus.
•
The AUX BATT switch connects the auxiliary battery to the left main feeder bus.
•
The STBY BATT switch connects the standby battery to the left main feeder bus.
All Displays .................................................................................................................................................. ON
Check voltages on Electrical page of MFD.
* Fire Detection ........................................................................................................................................... Test
ENGINE 1 and ENGINE 2 FIRE TEST DETECTION switch
Hold alternately, for a minimum of 1 s, at ENGINE 1 and ENGINE 2 positions and check:
•
PULL FUEL / HYD OFF handle light illuminates.
•
FAULT A and FAULT B advisory lights illuminate.
•
CHECK FIRE DET warning light illuminate.
•
MASTER WARNING light flashes.
•
ENGINE FIRE lights flash.
•
Fire warning tone sounds.
Press ENGINE FIRE light and check:
•
Check ENGINE FIRE lights stop flashing and fire warning tone is silenced.
Emerg Brake / Pressure ................................................................................................................. ON / Check
Make sure the EMERGENCY / PARKING BRAKE LEVER is set to PARK.
Make sure the PK BRK gauge on the MFD indicates hydraulic pressure above 500 psi (minimum dispatch).
If not, replenish pressure above 500 psi, then set the EMERGENCY / PARKING BRAKE LEVER to PARK.
NOTE:
When starting engine # 1 first, a minimum park brake pressure of 1000 psi is required.
Doors / Fueling Lights ................................................................................................................................ Out
Make sure the following lights are off:
•
FUSELAGE DOORS warning light
•
FUELING ON caution light
When engine-start clearance has been received, proceed as follows:
Anti-Collision .............................................................................................................................................. Red
Engines ...................................................................................................................................... Clear for Start
The captain normally starts the # 2 engine first and communicates with ground crew.
The first officer looks out to make sure the propeller area is clear of personnel and equipment before starting
the engine.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-6
NORMAL PROCEDURES
[Rev. 13] 30 JAN 2015
START APPROVED (cont’d)
CAPTAIN
FIRST OFFICER
ENGINE START SELECT Switch ... Pull out then Set to # 2
Observes SELECT Light illuminates.
Calls “CLEAR # 2”.
Makes sure the area is clear.
Calls “# 2 CLEAR”.
ENGINE START Switch ............................................ Press
Makes sure START Light illuminates.
NOTE:
Starts stopwatch running to time the start.
When conducting an engine start using
external power or the APU, # 2 engine oil
pressure may momentarily indicate full scale
deflection upon selection of the ENGINE
START Switch for # 1 or # 2 engine.
# 2 engine oil pressure should immediately
return to normal values.
At 1st indication of NH:
Sets condition lever to START / FEATHER.
NOTE:
Fuel flow indication on ED is not accurate until the engine is stable at idle NH.
Check that engine accelerates to above 64.2% NH and ITT does not exceed 920°C.
Check ENGINE START and ENGINE START SELECT Switches off
Observe SELECT and START Lights out
For the appropriate engine, make sure oil pressure is greater than 44 psi, ENG OIL PRESS Warning Light,
ENG FUEL PRESS and ENG HYD PUMP Caution Lights off.
Make sure DC GEN Caution Light is off.
NOTES:
1. ENGINE SELECT Light will remain illuminated for approximately 15 s after ENGINE START and
SELECT Switches off.
2. When starting on aircraft batteries, ensure MAIN, AUX and STBY battery loads are 0.4 or less prior to
starting the 2nd engine.
Repeat start procedure for other engine.
NOTE:
Complete FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN,
Sub-Chapter 2.17.3.1, before proceeding to AFTER START CHECKLIST.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.3
FLIGHT COMPARTMENT PREPARATION - POWER ON
2.17.3.1
CAPTAIN
2.17-7
[Rev. 16] 7 MAR 2016
DC GEN 1 and 2 ........................................................................................................................................... ON
ICE PROTECTION / WS Heat & Wipers ..................................................................................................... OFF
Set all switches on the ice protection panel to OFF position.
PITOT / STATIC Switches ........................................................................................................................... OFF
LANDING / TAXI Lights .............................................................................................................................. OFF
ELT .............................................................................................................................................................. Auto
With 3 Frequency ELT System [with MS 4-423100 Incorporated]:
ELT .......................................................................................................................................................... Armed
NOTE:
Ensure ELT mode switch is fully in the ARMED position.
* Fire Detection ........................................................................................................................................... Test
ENGINE 1 and ENGINE 2 FIRE TEST DETECTION switch
Hold alternately, for a minimum of 1 s, at ENGINE 1 and ENGINE 2 positions and check:
• PULL FUEL / HYD OFF handle light illuminates.
• FAULT A and FAULT B advisory lights illuminate.
• CHECK FIRE DET warning light illuminate.
• Master WARNING light flashes.
• ENGINE FIRE lights flash.
• Fire warning tone sounds.
Press ENGINE FIRE light and check:
• Check ENGINE FIRE lights stop flashing and fire warning tone is silenced.
FUEL / HYD Valves ................................................................................................................................... Open
Make sure fuel and hydraulic valves are open and
the green FUEL VALVE OPEN and HYD VALVE OPEN advisory lights are on.
* Baggage Smoke Warning (AFT and FWD) ............................................................................................. Test
NOTE:
Direct sunlight on the smoke detectors in the forward and aft baggage compartments can
affect the BAGGAGE FWD SMOKE and BAGGAGE AFT SMOKE test.
The forward baggage and aft baggage compartment doors should be closed prior to
conducting the forward baggage and aft baggage compartments smoke test.
Select Baggage AFT TEST switch to position 1 and check:
• Master warning tone sounds, master WARNING and SMOKE warning lights flash and
SMOKE / EXTG, VENT INLT, VENT OTLT and AFT BTL ARM advisory lights illuminate.
Repeat with Baggage AFT TEST switch to position 2.
Select Baggage FWD TEST switch to TEST and check:
• Master warning tone sounds, master WARNING and SMOKE warning lights flash and
SMOKE / EXTG and FWD BTL ARM advisory lights illuminate.
[with Option - CR 825 CH 03262 Incorporated]
* Cargo Compartment Smoke Warning .................................................................................................... Test
Rotate CARGO SMOKE TEST Selector through positions 1, 2, 3 and 4.
At each position observe illumination of the master WARNING and SMOKE warning lights, VENT INLT
CLOSED and VALVE OTLT CLOSED advisory lights.
NOTE:
Pause for approximately 2 s at each position.
Rotate CARGO SMOKE TEST Selector to OFF. Check master WARNING and SMOKE warning lights out,
VENT INLT CLOSED and VALVE OTLT CLOSED advisory lights out.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-8
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
Panel Lighting .................................................................................................................................... As Req’d
Set the panel lighting intensity to the appropriate intensity.
IGNITION 1 and 2 .................................................................................................................................... NORM
CABIN ALTITUDE Controls ......................................................................................................................... Set
Set the controls as follows:
•
AUTO / MAN / DUMP switch – Set at AUTO.
•
CABIN ALTITUDE FWD OUTFLOW knob – Rotate fully counter-clockwise to CLSD.
Forward outflow valve is closed.
•
LDG ALT control knob – Rotate to set the destination airport elevation on the LDG ALT indicator.
EXTERIOR Lights .............................................................................................................................. As Req’d
Emergency Lights .................................................................................................................................... ARM
Make sure the EMER LTS DISARMED caution light goes off.
Passenger Signs ................................................................................................................................ As Req’d
Set fasten belts and no smoking switches to FASTEN BELTS and NO SMOKING position.
Caution / Advisory Lights ......................................................................................................................... Test
Hold CAUTION / ADVISORY LIGHTS TEST switch at CAUT and make sure:
•
Master CAUTION and master WARNING lights flash.
•
All caution lights steady on.
•
# 1 ENG OIL PRESS and # 2 ENG OIL PRESS warning lights turn on steady.
•
All remaining warning lights flash.
•
Push master CAUTION light and make sure it goes off.
•
Push master WARNING light and make sure it goes off and warning lights stop flashing.
NOTE:
FUSELAGE DOORS warning light will not flash with passenger or baggage door(s) open.
Hold CAUTION / ADVISORY LIGHTS TEST switch at ADVSY and make sure:
•
All advisory lights and AP DISENG light illuminate.
•
Particular attention must be given to the following advisory lights:
-
Fire detection panel lights.
-
De-ice and anti-ice lights.
-
POWERED FLIGHT CONTROL SWITCHLIGHTS on the Glareshield panel, all 4 switchlights read
PUSH OFF.
-
Landing gear lights.
NOTE:
ENGINE SELECT, ENGINE START, CABIN ALTITUDE FAULT and ALTERNATE PILOT
WIPER ON lights do not illuminate with the advisory light test.
Caution / Advisory Lights Dimming Switch .................................................................................... As Req'd
•
Set to DIM for minimum brightness of all caution and advisory lights.
•
Set to BRT for maximum brightness of all caution and advisory lights.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-9
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
TEMP CONTROLs ........................................................................................................................................ Set
The setting of these switches may vary depending on temperature requirements:
•
Set both PACK CONTROL switches to the AUTO position.
•
Turn the PASSENGER CABIN TEMPERATURE knob counter-clockwise to the FA position or as required.
•
Turn the FLT COMP TEMPERATURE knob as required.
BLEED AIR 1 and 2 ............................................................................................................................ As Req’d
AC External ................................................................................................................................................. OFF
AC GEN 1 and 2 ........................................................................................................................................... ON
GPWS Override ...................................................................................................................................... NORM
Make sure the GPWS FLAP OVERRIDE switchlight is off and the plastic guard is in place.
Nosewheel STEERING ............................................................................................................................... OFF
* Stall Warning 1 and 2 ............................................................................................................................... Test
[with MS 4-457056, MS 4-126263 or MS 4-126307 Not Incorporated]
Set and hold STALL WARNING TEST switch at TEST 1 position and observe:
•
RA increases to greater than 500 ft and
rising runway (with tape display of altitude incorporated, rising ground) disappears.
•
RA decreases to 50 ft and
rising runway (with tape display of altitude incorporated, rising ground) reappears.
•
Stick shaker activates
•
# 1 STALL SYST FAIL and PUSHER SYST FAIL Caution Lights illuminate.
Release STALL WARNING TEST Switch and check # 1 STALL SYST FAIL and PUSHER SYST FAIL Caution Lights out and Stick Shaker off.
NOTE:
Hold STALL WARN TEST Switch for a minimum of 10 s prior to release.
Repeat with STALL WARN TEST Switch at TEST 2
(except in item 4 - # 2 STALL SYST FAIL Caution Light illuminates).
NOTE:
TCAS FAIL may momentarily flash on PFD’s and MFD’s during the Stall Warning test.
[with MS 4-457056, MS 4-126263 or MS 4-126307 Incorporated]:
STALL WARN TEST switch - Select TEST 1 and release. Observe:
•
# 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights illuminate.
•
Stick shaker activates.
•
# 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights out and stick shaker off.
Repeat with STALL WARN TEST switch to TEST 2
(except in item - # 2 STALL SYST FAIL caution light illuminates).
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-10
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN
(cont’d)
* ADC 1 and 2 ............................................................................................................................................. Test
Check ALT FAIL, IAS FAIL and IVSI FAIL flags are out on pilot’s and co-pilot’s PFD’s and
valid SAT is displayed on ED.
ADC test switch - Hold at TEST 1 and check:
• The barometric altimeter shows 14360 ft on pilot’s PFD.
• The altimeter barometric setting changes to 990 hPa (29.23 in Hg) on pilot’s PFD.
• The maximum operating airspeed (VMO) is displayed as 284 KIAS on pilot’s PFD.
• The airspeed indicator displays 285 KIAS in red on pilot’s PFD.
• The indicated SAT is - 15°C and WTG 2 FAIL appears on ED.
• IAS, IAS MISMATCH and ALT appears on PFD’s.
• PITCH TRIM and ELEVATOR FEEL and AVIONICS caution lights illuminate.
• The overspeed warning horn is activated after 5 s.
NOTE:
TCAS FAIL may momentarily flash on PFD’s and MFD’s during the ADC functional test.
ADC test switch - Hold at TEST 2 and check previous items above on co-pilot’s PFD except SAT does not
change and WTG 1 FAIL advisory message appears on ED.
CB & Panel Lighting .......................................................................................................................... As Req’d
Operate circuit breaker and panel light switch to make sure the bulb operates then
set the flight instrument panel lighting intensity as required.
[with MS 4-429586 Incorporated]:
NOSE GEAR LOCK Advisory Light ........................................................................................................... Out
Smoke Goggles ...................................................................................................................................... Check
Make sure goggles are not scratched, are in good condition and properly stored.
FLIGHT / TAXI ............................................................................................................................................ TAXI
Make sure the FLIGHT / TAXI switch on the GLARESHIELD is in the TAXI position.
STICK PUSHER / ELEVATOR TRIM SHUT OFF ................................................................................... NORM
Make sure the ELEVATOR TRIM & STICK PUSHER SHUT OFF switchlights are in the out position
and the amber PUSH OFF lights are not on.
Clock ........................................................................................................................................................ Check
Make sure clock is serviceable and the correct time is set and reset the flight time to 0 before each flight.
GPWS .......................................................................................................................................................... Test
•
# 1 NAV receiver - Tune to any VOR frequency
•
GPWS FLAP OVERRIDE switch - Normal and guarded
•
GPWS caution light - Out
•
PULL UP GPWS TEST switch - Press and hold
Check that the GPWS caution light, GPWS FLAP OVERRIDE, PULL UP and BELOW G/S advisory lights illuminate and the “GLIDESLOPE” and “PULL UP” voice warnings are audible.
NOTE:
If Test response is unsatisfactorily, wait at least 30 s before repeating Test.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-11
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
PFCS ........................................................................................................................................................ NORM
Make sure all 4 POWERED FLIGHT CONTROL SHUTOFFS Switchlights on the glareshield
are in the out position and both the amber PUSH OFF or OFF switchlights are not illuminated.
Flight Guidance Controller .................................................................................................................... Check
•
Select left and right EHSI navigation data sources as required, using the corresponding NAV SOURCE
knobs.
•
Select HSI SEL to side of pilot flying.
SPEED BUGS ............................................................................................................................................... Set
Set as required.
Altimeters ..................................................................................................................................................... Set
Set the local altimeter setting using the BARO SET knob on the INDEX CONTROL panel and
confirm the altimeter reading with the field elevation.
PFD ......................................................................................................................................................... Check
The following flight instruments should be checked for serviceability then set for departure or SID.
•
EADI - Set display intensity to a comfortable level.
Make sure no red flags are in view and all displays are correct.
•
EHSI (HSI) - Set display intensity to a comfortable level.
Make sure no red flags are in view and all displays are correct.
MFD ......................................................................................................................................................... Check
Confirm MFD Selector function on the Engine & System Integrated Display Control Panel
by cycling through each of ENG, NAV, SYS and PFD.
PFCS Indicator ....................................................................................................................................... Check
Make sure all spoiler needles on the MFD indicate actual spoiler position.
The rudder may indicate a deflection left or right of center if a crosswind exists.
STBY Attitude Indicator ........................................................................................................................... Erect
Make sure instrument is erect and red flag is not in view.
STBY Airspeed Indicator ....................................................................................................................... Check
Standby Altimeter ....................................................................................................................................... Set
Set the local altimeter setting and confirm the altimeter reading with the field elevation.
ED ............................................................................................................................................................ Check
ED Messages .......................................................................................................................................... Check
NOTE:
If messages appear in the Engine Display advisory area, maintenance action is required
before dispatch.
Fuel Quantity .......................................................................................................................................... Check
Make sure the quantity of fuel indicated on the MFD – Fuel page, is sufficient for the flight.
Maximum fuel imbalance between contents of main fuel tanks is 272 kg (600 lb).
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-12
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
Landing Gear Sel / Lights / Horn ........................................................................................................... Check
•
Make sure landing gear selector is selected down.
•
Green LEFT / NOSE / RIGHT undercarriage lights are on.
•
The L DOOR and R DOOR and / or N DOOR amber lights may be on if the landing gear doors are open.
•
Hold the gear-warning horn test switch at TEST and make sure the horn sounds.
•
Release TEST switch and horn should stop sounding.
GPWS Landing Flap .......................................................................................................................... As Req’d
STBY HYD PRESS / PTU / HYD # 3 ISOL Valve ................................................................................... NORM
Make sure all 3 switchlights are off.
Flap Indication ........................................................................................................................................ Check
Make sure the flap selection indicated on the MFD agrees with the FLAPS lever position.
AHRS ....................................................................................................................................................... Check
FMS .............................................................................................................................................. Programmed
EFIS Control Panel ...................................................................................................................................... Set
•
Set the dimming control knobs for nominal intensity on the PFD and MFD.
•
Set desired Navaids (VOR, ADF or FMS) using the bearing selector knob.
NOTE:
[with MS 4-126104 Not Incorporated]:
On the ADF expanded page, if the line select key is pressed to select TEST, the ADF may
latch in test mode after passing the ADF test.
To exit test mode, change frequency by pressing the line select key twice and the again to
return to the original frequency.
* PFD / MFD OFF / BRT Selectors ............................................................................................ OFF then BRT
Carry out an electrical power reset on each of the PFD and MFD displays.
NOTE:
The removal of all aircraft electrical power will accomplish the intent of the power reset of the
PFDs, MFDs and ED
Pitch & Roll DISC ........................................................................................................................................... In
Make sure both PITCH and ROLL disconnect handles are pushed in.
TANK AUX PUMPs 1 and 2 ........................................................................................................................ OFF
Make sure the TANK 1 and TANK 2 AUX PUMP switchlights are off.
This can also be confirmed on the MFD – Fuel Systems page.
FUEL TRANSFER ....................................................................................................................................... OFF
Make sure the FUEL TRANSFER switch is OFF and
make sure that both green VALVE OPEN lights are off on the MFD Fuel Systems page.
POWER Levers ......................................................................................................................................... DISC
Condition Levers ........................................................................................ FUEL OFF or START / FEATHER
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-13
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
* AUTOFEATHER ............................................................................................................................. Test / OFF
AUTOFEATHER Switch ........................................................................................................................... Press
Check SELECT advisory light illuminates.
[with MS 4-113558 Not Incorporated] observe the following appear on ED:
• A/F SELECT,
• A/F TEST IN PROG,
• UPTRIM appears,
• ITT and NH red radials increase,
• NTOP changes to MTOP and torque rating and torque bugs increase,
• A/F ARM appears twice,
• A/F TEST PASS,
• MTOP changes to NTOP and torque rating and torque bugs decrease.
NOTE:
During the test # 1 or # 2 ALT FTHR advisory lights may illuminate momentarily.
If autofeather test is aborted, A/F TEST ABORT message will appear on ED.
If autofeather test fails, A/F TEST FAILED message will appear on ED.
If either A/F TEST ABORT or A/F TEST FAILED appears on ED, repeat the autofeather test
AUTOFEATHER Switch ....................................................................................................................... Press
Check SELECT advisory out and A/F SELECT message disappears on ED.
[with MS 4-113558 Incorporated] observe the following appear on ED:
•
•
A/F SELECT,
A/F TEST IN PROG,
Observe the following sequence appears twice on ED:
• UPTRIM appears,
• ITT and NH red radials increase,
• NTOP changes to MTOP and torque rating and torque bugs increase,
• A/F ARM appears,
• A/F SELECT appears,
• UPTRIM disappears,
• MTOP changes to NTOP and torque rating and torque bugs decrease,
• MTOP changes to NTOP and torque rating and torque bugs decrease,
Observe the following appear on ED:
• A/F TEST PASS.
NOTE:
During the test # 1 or # 2 ALT FTHR advisory lights may illuminate momentarily.
If autofeather test is aborted, A/F TEST ABORT message will appear on ED.
If autofeather test fails, A/F TEST FAILED message will appear on ED.
If A/F TEST ABORT appears on ED, repeat the Autofeather test.
AUTOFEATHER Switch ........................................................................................................................... Press
Check SELECT advisory out and A/F SELECT message disappears on ED.
Alternate Feather 1 and 2 ....................................................................................................................... NORM
Make sure the white FTHR pushbutton indicator lights are off.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-14
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
EMERG BRAKE / Pressure ............................................................................................................ On / Check
Make sure the emergency / parking brake lever is set to PARK.
Make sure the PK BRK gauge on the MFD – Hydraulic page indicates hydraulic pressure above 500 psi
(minimum dispatch).
NOTE:
When starting engine # 1 first, a minimum park brake pressure of 1000 psi is required.
Control Lock ................................................................................................................................................ ON
ARCDU ................................................................................................................................................. ON / Set
Select frequencies as req’d.
NOTE:
[with MS 4-126104 Not Incorporated]:
For night flying, either one of the pilot's or co-pilot's reading light must be aimed at the ARCDU
radio selector knob to enable determination of the selector position.
NOTE:
Avoid transmission on VHF radios on frequencies within 200 kHz of any other tuned
frequency.
Set selector switches to required COMM channels.
• EMERGENCY switch to NORM
• Set MIC switch to BOOM
• HOT MIC switch as required
• Push the required rotary selectors down (ON) and set volume to a comfortable level.
NOTE:
If BAD CONF message on ARCDU, cycle power off, then on.
* TCAS ........................................................................................................................................................ Test
Perform the appropriate TCAS system test.
NOTE:
The following procedures correspond to:
- AFM Supplement 33 (ACAS II / TCAS II - HONEYWELL)
- AFM Supplement 106 (ACAS II / TCAS II - ACSS)
(Option: ACAS II / TCAS II - HONEYWELL)
Select TA / RA on the ARCDU TCAS / ATC Page.
NOTE:
The ACAS II / TCAS II mode of operation is displayed on the PFD and ND / MFD.
Selecting TA / RA enables TA / RA mode for take-off.
TCAS is in STBY mode when the transponder is in SBY mode.
ACAS II / TCAS II will indicate FAIL on ARCDU with onside ATC set to SBY and offside ATC
failed. Select ATC ON to confirm ACAS II / TCAS II function.
Select TEST on the ARCDU TCAS / ATC Page and observe the following:
• TCAS TEST appears on EHSI / PFD,
• Intruder symbol test pattern is displayed on the ND / MFD,
• IVSI test indication is displayed,
• No failures are annunciated,
• “TCAS SYSTEM TEST OK” is announced.
If a fault is identified at the completion of the test, “TCAS SYSTEM TEST FAIL” is announced.
Select SBY on the ARCDU TCAS / ATC Page.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-15
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
(Option: ACAS II / TCAS II - ACSS)
[with MS 4-903190 or MS 4-458698 Not Incorporated]:
Select ATC ON on the ARCDU TCAS / ATC Page.
Select ATC SBY on the ARCDU TCAS / ATC Page.
NOTE:
The ACAS II / TCAS II mode of operation is displayed on the PFD and ND / MFD.
After initial power-up, momentarily selecting ATC to ON and back to SBY ensures
consistent TCAS mode indication on the PFD, MFD and ARCDU.
Subsequent selections are as desired.
Select ATC ON (using appropriate code) on the ARCDU TCAS / ATC Page.
Select TA / RA on the ARCDU TCAS / ATC Page.
NOTE:
Selecting TA / RA enables TA / RA mode for take-off.
TCAS is in STBY mode when the transponder is in SBY mode.
ACAS II / TCAS II will indicate STBY on PFD and ND / MFD with onside ATC set to SBY and
offside ATC failed.
Select TEST on the ARCDU TCAS / ATC Page and observe the following:
•
TCAS TEST appears on EHSI / PFD,
•
“TCAS TEST” is announced,
•
Intruder symbol test pattern is displayed on the ND / MFD,
•
“TCAS TEST PASS” is announced.
If a fault is identified at the completion of the test:
•
“TCAS TEST FAIL” or “TCAS LRU PASS, TCAS SYSTEM FAIL” is announced.
[with MS 4-903190 or MS 4-458698 Not Incorporated]:
Select SBY on the ARCDU TCAS / ATC Page.
Confirm ATC SBY on the ARCDU TCAS / ATC Page.
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-16
NORMAL PROCEDURES
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
TRIMs .............................................................................................................................................. Check / Set
•
Release control lock then cycle the aileron trim throughout its range then set trim needle to center position.
Re-engage control lock.
•
Cycle the rudder trim throughout its range then set trim needle to center position.
•
Cycle the elevator trim throughout its range then set trim needle to the required position for take-off.
TAKE-OFF ELEVATOR TRIM vs CG
CG - % MAC
NOTES:
TAKE-OFF RANGE
FORWARD 13.8%
AFT END
AFT 36%
FORWARD END
1. When setting the elevator trim, holding the elevator trim switch for greater than 3 s will
cause the “elevator trim in motion” audio tone to sound and the ELEVATOR TRIM SHUT
OFF switch PUSH OFF advisory light to illuminate.
2. [with MS 4-126383 Not Incorporated]:
To avoid possible activation of the Take-off Configuration aural warning, with a Centre of
Gravity at or near the FWD or AFT Limit, set the ELEVATOR TRIM with the trim pointer
“one half of the pointer's width” inside the forward edge (with AFT CG) or inside the aft
edge (with FWD CG) of the TO trim band.
ESID Control Panel ...................................................................................................................................... Set
* ED OFF / BRT Selectors ......................................................................................................... OFF then BRT
Carry out an electrical power reset on the ED display.
NOTE:
The removal of all aircraft electrical power will accomplish the intent of the power reset of the
PFDs, MFDs and ED.
EFIS ATT / HDG Source ......................................................................................................................... NORM
EFIS ADC Source ................................................................................................................................... NORM
Radar .......................................................................................................................................................... OFF
* Flight Compartment Door Emergency Access ..................................................................................... Test
[with MS 4-309218 or MS 4-309221 Incorporated]:
Confirm Flight Compartment Door is closed and locked and check:
•
BAGG DOOR, CKPT DOOR, AUTO UNLK and FAIL advisory lights are out,
•
INTERNAL DOORS caution light is out.
Momentarily press FLIGHT ATTENDANT emergency access switch and check:
•
INTERNAL DOORS caution light illuminates,
•
AUTO UNLK advisory light illuminates.
Select INTERNAL DOORS switch to DENY and check:
•
INTERNAL DOORS caution light goes out,
•
AUTO UNLK advisory light goes out.
•
Flight Compartment Door is closed and locked.
* System Check Once Every 24 h Flying Day.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.3.2
2.17-17
[Rev. 16] 7 MAR 2016
FIRST OFFICER
ARCDU ................................................................................................................................................. ON / Set
Select frequencies as req’d.
NOTE:
[with MS 4-126104 Not Incorporated]:
For night flying, either one of the pilot's or co-pilot's reading light must be aimed at the ARCDU
radio selector knob to enable determination of the selector position.
Set Selector switches to required COMM channels:
• EMERGENCY switch to NORM
• Set MIC switch to BOOM
• HOT MIC switch as required
• Push the required rotary selectors down (ON) and set volume to comfortable level.
EFIS Control Panel ...................................................................................................................................... Set
• Set the dimming control knobs for nominal intensity on the PFD and MFD.
• Set desired Navaids (VOR, ADF or FMS) using the bearing selector knobs.
NOTE:
[with MS 4-126104 Not Incorporated]:
On the ADF expanded page, if the line select key is pressed to select TEST, the ADF may
latch in test mode after passing the ADF test.
To exit test mode, change frequency by pressing the line select key twice and the again to
return to the original frequency.
FMS (if applicable) ........................................................................................................................ Programmed
AHRS ....................................................................................................................................................... Check
Clock ............................................................................................................................................................ Set
Make sure clock is serviceable, the correct time is set and the flight time is set to 0 before each flight.
STICK PUSHER / ELEVATOR TRIM SHUT OFF .................................................................................... NORM
Make sure the ELEVATOR TRIM & STICK PUSHER SHUT OFF switchlights are in the out position
and the amber PUSH OFF lights are not on.
ANTI SKID .................................................................................................................................................... ON
Turning the ANTI SKID TEST switch on will cause it to do a self test.
Make sure INBD ANTI-SKID and OUTBD ANTI-SKID caution lights go off after 6 s,
indicating the test is complete.
MFD ......................................................................................................................................................... Check
Confirm MFD Selector function on the Engine & System Integrated Display Control Panel by cycling through
each of ENG, NAV, SYS and PFD.
PFD .......................................................................................................................................................... Check
The following flight instruments should be checked for serviceability then set for departure or SID.
• EADI - Set display intensity to a comfortable level.
Make sure no red flags are in view and all displays are correct.
• EHSI (HSI) - Set display intensity to a comfortable level.
Make sure no red flags are in view and all displays are correct.
SPEED BUGS .............................................................................................................................................. Set
Set as required.
Altimeter ....................................................................................................................................................... Set
Set the local altimeter setting using the BARO SET knob on the index control panel and
confirm the altimeter reading with the field elevation. Altimeters should be within 50 ft of field elevation.
Smoke Goggles ...................................................................................................................................... Check
Make sure goggles are not scratched, are in good condition and properly stowed.
CB and Panel Lighting ...................................................................................................................... As Req’d
Operate circuit breaker panel lights switch to make sure the bulb operates then set the flight instrument panel
lighting intensity as required.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-18
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - FIRST OFFICER (cont’d)
OXYGEN PRESS ..................................................................................................................................... Check
Make sure the oxygen pressure gauge indicates in the green range.
Forward Outflow Valve Lever ......................................................................................... NORMAL / Guarded
Make sure the forward safety valve lever is set to NORMAL and guarded.
2.17.4
FLIGHT COMPARTMENT PREPARATION CHECKLIST
PREFLIGHT
External Check ................................................................................................................................ Completed
Documentation ....................................................................................................................................... Check
Locking Devices ................................................................................................................................. Remove
FLIGHT COMPARTMENT PREPARATION – POWER OFF
Safety Equipment ............................................................................................. Check Serviceable & Secure
Escape Hatch ........................................................................................................................................ Secure
Oxygen Masks / QTY .............................................................................................................................. Check
Circuit Breakers ...................................................................................................................................... Check
Alt Gear Doors / L/G Inhibit Switch ....................................................................................... Closed / NORM
For DC External Power
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ ON
MAIN BUS TIE .............................................................................................................................................. TIE
All Displays .................................................................................................................................................. ON
DC EXT POWER ........................................................................................................................................... ON
BUS Voltage ............................................................................................................................................ Check
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... ON
For APU Power
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ ON
MAIN BUS TIE .............................................................................................................................................. TIE
All Displays .................................................................................................................................................. ON
Caution / Advisory Lights ......................................................................................................................... Test
APU PWR ...................................................................................................................................................... ON
APU Fire Detection .................................................................................................................................... Test
Position Lights ............................................................................................................................................. ON
APU Start .................................................................................................................................................. Press
CAUTION: Ensure ground personnel and equipment are clear of the APU exhaust port.
APU Gen ................................................................................................................................................... Press
APU Generator Volts / Load ................................................................................................................... Check
Battery Temperature ............................................................................................................................... Check
BLEED AIR 1 and 2 .................................................................................................................................... OFF
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... ON
APU Bleed (20 s) ................................................................................................................................ As Req’d
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-19
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION – POWER OFF (cont’d)
For Battery Power Only
DC GEN 1 and 2 ........................................................................................................................................... ON
MAIN BUS TIE .............................................................................................................................................. TIE
ICE PROTECTION ....................................................................................................................................... OFF
External Lighting ........................................................................................................................................ OFF
IGNITION 1 and 2 .................................................................................................................................... NORM
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... ON
BLEED AIR 1 and 2 ........................................................................................................................... MIN / OFF
EMER LIGHTS ............................................................................................................................................ ARM
Passenger Signs ......................................................................................................................................... ON
POWER Levers ......................................................................................................................................... DISC
Condition Levers ............................................................................................................................. FUEL OFF
Briefing .................................................................................................................................................. Review
START APPROVED
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ ON
All Displays .................................................................................................................................................. ON
* Fire Detection ........................................................................................................................................... Test
EMERG BRAKE / Pressure ............................................................................................................ ON / Check
Doors / Fueling Lights ................................................................................................................................ Out
Anti-Collision .............................................................................................................................................. Red
Engines ...................................................................................................................................... Clear for Start
NOTE:
Complete Flight COMPARTMENT Preparation before proceeding to AFTER START checklist.
* System Check Once Every 24 h Flying Day.
AOM DASH 8-Q400
CHAPTER 2
2.17-20
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN
DC GEN 1 and 2 ............................................................................................................................................ ON
ICE PROTECTION / WS Heat & Wipers .................................................................................................... OFF
LANDING / TAXI Lights .............................................................................................................................. OFF
ELT ............................................................................................................................................... Auto / Armed
* Fire Detection .......................................................................................................................................... Test
FUEL Valves ............................................................................................................................................. Open
* Baggage Smoke Warning (Aft and Forward) .......................................................................................... Test
* Cargo Compartment Smoke Warning [with Option - CR 825 CH 03262 Incorporated] ....................... Test
Panel Lighting .................................................................................................................................... As Req’d
IGNITION 1 and 2 .................................................................................................................................... NORM
Cabin Altitude Controls .............................................................................................................................. Set
EXTERIOR Lights .............................................................................................................................. As Req’d
Emergency Lights ..................................................................................................................................... Arm
Passenger Signs ................................................................................................................................ As Req’d
Caution / Advisory Lights ......................................................................................................................... Test
TEMP CONTROLs ........................................................................................................................................ Set
BLEED AIR 1 and 2 ............................................................................................................................ As Req’d
AC External ................................................................................................................................................ OFF
AC GEN 1 and 2 ............................................................................................................................................ ON
GPWS Override ...................................................................................................................................... NORM
Nosewheel STEERING .............................................................................................................................. OFF
* Stall Warning 1 and 2 .............................................................................................................................. Test
* ADC 1 and 2 ............................................................................................................................................. Test
CB and Panel Lighting ....................................................................................................................... As Req’d
Smoke Goggles (if applicable) ................................................................................................................ Check
FLIGHT / TAXI ............................................................................................................................................ TAXI
STICK PUSHER / ELEVATOR TRIM SHUT OFF ................................................................................... NORM
Clock ........................................................................................................................................................ Check
GPWS .......................................................................................................................................................... Test
PFCS ....................................................................................................................................................... NORM
Flight Guidance Controller .................................................................................................................... Check
SPEED BUGS ............................................................................................................................................... Set
Altimeters ..................................................................................................................................................... Set
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-21
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT PREPARATION - POWER ON - CAPTAIN (cont’d)
PFD .......................................................................................................................................................... Check
MFD ......................................................................................................................................................... Check
PFCS Indicator ....................................................................................................................................... Check
STBY Attitude Indicator ........................................................................................................................... Erect
STBY Airspeed Indicator ....................................................................................................................... Check
STBY Altimeter ............................................................................................................................................ Set
ED ............................................................................................................................................................ Check
ED Messages .......................................................................................................................................... Check
Fuel Quantity .......................................................................................................................................... Check
Landing Gear Sel / Lights / Horn .......................................................................................................... Check
GPWS Landing Flap .......................................................................................................................... As Req’d
STBY HYD PRESS / PTU / HYD # 3 ISOL VLV ...................................................................................... NORM
AHRS ....................................................................................................................................................... Check
FMS ............................................................................................................................................... Programmed
EFIS Control Panel ...................................................................................................................................... Set
* PFD / MFD OFF / BRT Selector .............................................................................................. OFF then BRT
Pitch and Roll DISC ........................................................................................................................................ In
TANK AUX PUMPS 1 and 2 ........................................................................................................................ OFF
Fuel Transfer ............................................................................................................................................... OFF
Condition Levers ............................................................................................................................. FUEL OFF
POWER Levers ......................................................................................................................................... DISC
* Autofeather .................................................................................................................................... Test / OFF
Alternate Feather 1 and 2 ....................................................................................................................... NORM
EMERG BRAKE / Pressure ............................................................................................................ ON / Check
Control Lock ................................................................................................................................................ ON
ARCDU ................................................................................................................................................. ON / Set
* TCAS ......................................................................................................................................................... Test
TRIMs .............................................................................................................................................. Check / Set
ESID Control Panel ..................................................................................................................................... Set
EFIS ATT / HDG Source ......................................................................................................................... NORM
EFIS ADC Source ................................................................................................................................... NORM
Radar ........................................................................................................................................................... OFF
* Flight Compartment Door Emergency access ...................................................................................... Test
* System Check Once Every 24 h Flying Day.
AOM DASH 8-Q400
2.17-22
[Rev. 16] 7 MAR 2016
CHAPTER 2
NORMAL PROCEDURES
FLIGHT COMPARTMENT PREPARATION - FIRST OFFICER
ARCDU ................................................................................................................................................. ON / Set
EFIS Control Panel ...................................................................................................................................... Set
FMS (if applicable) ........................................................................................................................ Programmed
AHRS ....................................................................................................................................................... Check
Clock ............................................................................................................................................................. Set
STICK PUSHER / ELEVATOR TRIM SHUT OFF ................................................................................... NORM
ANTI SKID ..................................................................................................................................................... ON
MFD .......................................................................................................................................................... Check
PFD .......................................................................................................................................................... Check
SPEED BUGS ............................................................................................................................................... Set
Smoke Goggles (if applicable) ................................................................................................................ Check
Altimeter ....................................................................................................................................................... Set
CB and Panel Lighting ....................................................................................................................... As Req’d
OXYGEN PRESS ..................................................................................................................................... Check
FWD OUTFLOW Valve .......................................................................................................... NORM / Guarded
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5
NORMAL CHECKLIST
2.17.5.1
ORIGINATING BEFORE START
2.17-23
[Rev. 18] 21 NOV 2016
GPU / APU ..................................................................................................................................................... On
External Check ............................................................................................................................... Completed
Alt Gear Door / L/G Inhibit Switch ......................................................................................... Closed / NORM
Check that:
•
MAIN LANDING GEAR ALTERNATE RELEASE door is closed,
•
LANDING GEAR ALTERNATE EXTENSION door is closed.
•
LANDING GEAR EXTENTION INHIBIT switch is set to NORMAL and the red guard is closed.
Flight Compartment Preparation .................................................................................................. Completed
Briefing ............................................................................................................................................ Completed
Ensure the take-off briefing has been completed.
ORIGINATING BEFORE START
GPU / APU ..................................................................................................................................................... On
External Check ............................................................................................................................... Completed
Alt Gear Doors / L/G Inhibit Switch ....................................................................................... Closed / NORM
Flight Compartment Preparation .................................................................................................. Completed
Briefing ............................................................................................................................................ Completed
AOM DASH 8-Q400
CHAPTER 2
2.17-24
[Rev. 16] 7 MAR 2016
2.17.5.2
NORMAL PROCEDURES
BEFORE START
Escape Hatch ........................................................................................................................................ Closed
Circuit Breakers ...................................................................................................................................... Check
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ On
• Check MAIN BATTERY, AUX BATTERY and STBY BATTERY caution lights out
• Check voltages on the MFD Electrical Systems page.
Passenger Signs .......................................................................................................................................... On
Make sure the passenger signs are to the FASTEN BELTS and NO SMOKING positions.
Emergency Lights .................................................................................................................................... ARM
• Make sure EMER LIGHTS switch is in the ARM position.
• Make sure EMER LTS DISARMED caution light is off.
ANTI SKID ..................................................................................................................................................... ON
Set ANTI SKID switch to ON position and check:
• INBD ANTI-SKID and OUTBD ANTI-SKID caution lights are off.
FUEL TRANSFER / QTY .............................................................................................................. OFF / Check
• Make sure the FUEL TRANSFER switch is OFF.
• Make sure that both green VALVE OPEN lights are off on the MFD – Fuel Systems page.
• Make sure the quantity of fuel indicated on the MFD – Fuel page, is sufficient for the flight.
Maximum fuel imbalance between contents of main fuel tanks is 272 kg (600 lb).
EMERG BRAKE / Pressure ............................................................................................................ On / Check
• Make sure the EMERGENCY / PARKING BRAKE LEVER is set to PARK.
• Make sure the PK BRK gauge on the MFD indicates hydraulic pressure above 500 psi for starting
engine # 2 and 1000 psi if starting engine # 1 first.
If not, replenish pressure above 1500 psi, then set the EMERGENCY / PARKING BRAKE LEVER to PARK.
POWER Levers ......................................................................................................................................... DISC
Make sure POWER Levers are at DISC.
Condition Levers ............................................................................................................................. FUEL OFF
Take-off Data ..................................................................................................................................... Reviewed
Review take-off data, mass.
BEFORE START
Escape Hatch ........................................................................................................................................ Closed
Circuit Breakers ...................................................................................................................................... Check
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ........................................................................ On
Passenger Signs .......................................................................................................................................... On
EMER LIGHTS ........................................................................................................................................... ARM
ANTI SKID ..................................................................................................................................................... ON
FUEL TRANSFER / QTY .............................................................................................................. OFF / Check
EMERG BRAKE / Pressure ............................................................................................................ On / Check
POWER Levers ......................................................................................................................................... DISC
Condition Levers ............................................................................................................................. FUEL OFF
Take-off Data ..................................................................................................................................... Reviewed
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.3
2.17-25
[Rev. 18] 21 NOV 2016
START APPROVED
Door / Fueling Lights .................................................................................................................................. Out
Make sure the following lights are off:
• FUSELAGE DOORS warning light
• FUELING ON caution light
APU Bleed ................................................................................................................................................... OFF
Check APU BL AIR OPEN advisory light goes off.
RECIRC Fan [with MS 4-126236 Not Incorporated] .................................................................................... OFF
A/COL Lights ............................................................................................................................................. RED
Make sure the FLT DATA RECORDER caution light is off.
Engines ..................................................................................................................................... Clear For Start
The captain normally starts the # 2 engine first and communicates with ground crew.
The first officer looks out to make sure the propeller area is clear of all personnel and equipment before starting
the engine.
CAPTAIN
FIRST OFFICER
ENGINE START SELECT Switch .... Pull out then Set to # 2
Observes SELECT Light illuminates.
Makes sure the area is clear.
Calls “CLEAR # 2”.
Calls “# 2 CLEAR”.
ENGINE START Switch button ................................ Press
Makes sure START Light illuminates.
Starts stopwatch running to time the start.
NOTE:
When conducting an engine start using
external power or the APU, # 2 engine oil
pressure may momentarily indicate full scale
deflection upon selection of the ENGINE
START Switch for # 1 or # 2 engine.
# 2 engine oil pressure should immediately
return to normal values.
At 1st indication of NH:
Sets condition lever to START FEATHER.
NOTE:
Fuel flow indication on ED is not accurate until the engine is stable at idle NH.
Check that engine accelerates to above 64.2% NH and ITT does not exceed 920°C.
Check ENGINE START and ENGINE START SELECT Switches off.
Observe SELECT and START Lights out.
For the appropriate engine, make sure oil pressure is greater than 44 psi, ENG OIL PRESS Warning Light,
ENG FUEL PRESS and ENG HYD PUMP Caution Lights out.
If APU starting, check DC GEN Caution Light out.
NOTES:
1. ENGINE SELECT Light will remain illuminated for approximately 15 s after ENGINE START
and SELECT Switches off.
2. Check # 2 Generator and Main Battery load, both should be decreasing after engine start.
It is suggested that a MAIN BATT load of 0.4 or less should be achieved before attempting the
start of the 2nd engine.
Repeat start procedure for other engine.
START APPROVED
Doors / Fueling Lights ................................................................................................................................ Out
APU Bleed ................................................................................................................................................... OFF
RECIRC Fan [with MS 4-126236 Not Incorporated] .................................................................................... OFF
A/COL Lights ............................................................................................................................................. RED
Engines ...................................................................................................................................... Clear for Start
AOM DASH 8-Q400
CHAPTER 2
2.17-26
[Rev. 18] 21 NOV 2016
2.17.5.4
NORMAL PROCEDURES
AFTER START
EXT PWR / APU .......................................................................................................................................... OFF
After both engines have started and stabilized, set the DC EXT PWR switch to OFF and make sure:
• DC EXTERNAL POWER advisory light on the MFD – Electrical Systems page goes off.
• Signal ground crew to remove external power cable.
• # 1 DC GEN and # 2 DC GEN caution lights go off.
If the APU was used, shut it down as follows:
• Push APU GEN Switch.
Make sure the GEN ON advisory light goes out and the GEN WARN advisory light illuminates.
• Push APU PWR Switch. Make sure APU RUN, APU GEN WARN and APU FUEL VALVE OPEN advisory
lights out and FUEL VALVE CLOSED advisory light illuminates.
MAIN BUS TIE ............................................................................................................................................ OFF
BLEED Air 1 and 2 ..................................................................................................................... On / As Req’d
•
•
Set BLEED AIR CONTROL switches to 1 and 2 positions.
Turn the BLEED FLOW CONTROL rotary knob to the desired position.
BATTERY TEMPS .................................................................................................................................... Check
Monitor the battery temperatures after engine start on the MFD – Electrical Systems page.
Condition Levers ...................................................................................................................................... MAX
Move CONDITION LEVERS to MAX position and make sure:
• Propellers unfeather and
• # 1 AC GEN, # 2 AC GEN, L TRU and R TRU caution lights go off.
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... On
STBY HYD PRESS and PTU CNTRL ........................................................................................................... ON
Check STBY HYD PRESS ON, PTU CNTRL ON and PTU pressure
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated]
advisory lights illuminate.
HYD Press & QTY ................................................................................................................................... Check
Make sure the following hydraulic indicators on the MFD show:
• Standby Pressure – 2800 - 3000 psi
• Main Pressure 1 & 2 – 2900 - 3100 psi
• System Quantity (minimum):
# 1 System 40%
# 2 System 40%
# 3 System 45%
HYD # 3 ISOL VLV Switch ....................................................................................................................... Press
Check OPEN advisory and ELEVATOR PRESS caution lights illuminate and
# 3 HYD PRESS indication on # 2 MFD (2400 - 3100 psi)
ELEVATOR Travel ............................................................................................................................ Full Travel
Operate Elevator Control through full travel and
check PFCS indication on # 1 MFD for full deflection nose-up and nose-down.
NOTE:
Full nose-up elevator travel is indicated by a pointer position defined by assuming the nose-up
index mark is shifted 1/2 arc width down.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-27
[Rev. 18] 21 NOV 2016
AFTER START (cont’d)
HYD # 3 ISOL VLV Switch ....................................................................................................................... Press
Check OPEN advisory and ELEVATOR PRESS caution lights out.
NOTE:
It will require a small elevator input to extinguish the ELEVATOR PRESS caution light and
bring # 3 HYD PRESS indicator to zero.
SPOILERS CHECK
[with MS 4-113783 (Outboard Spoilers) and MS 4-113785 (Inboard Spoilers) Not Incorporated]:
FLIGHT / TAXI Switch ................................................................................................................ FLIGHT / TAXI
•
Set the Switch to FLIGHT. Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights illuminate and
PFCS indication on # 1 MFD shows LI, RI and LO, RO SPOILERS extended.
•
Set the Switch to TAXI. Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights out and PFCS
indication on # 1 MFD shows LI, RI and LO, RO SPOILERS retracted.
FLAPS ..................................................................................................................................................... Select
Set flap selector lever to desired take-off position and confirm correct indication on # 2 MFD.
DEICE PRESS Indicator ......................................................................................................................... Check
Confirm DEICE PRESSURE indicator shows 18 ± 3 psi on each dial.
RUDDER Travel ............................................................................................................................... Full Travel
Monitor the PFCS indicator on # 1 MFD for full and free rudder travel.
Ensure that PFCS indicator pointer travels full left and full right to index marks.
NOTE:
Any observed restriction or abnormal force detected during the Rudder Control check must be
addressed by maintenance action prior to flight.
* RUDDER Actuator .................................................................................................................................... Test
[with MS 4-113655 Not Incorporated]
Push RUD 1 PUSH OFF switch to OFF and check # 1 RUD HYD caution light illuminates.
Move rudder pedals left to right and check PFCS indication on # 1 MFD for rudder travel.
Push RUD 1 PUSH OFF switch to ON and check # 1 RUD HYD caution light goes out.
Push RUD 2 PUSH OFF switch to OFF and check # 2 RUD HYD caution light illuminates.
Move rudder pedals left to right and check PFCS indication on # 1 MFD for rudder travel.
Push RUD 2 PUSH OFF switch to ON and check # 2 RUD HYD caution light goes out.
Nose Wheel STEERING ............................................................................................................................... On
Check NOSE STEERING caution light out.
CAUTION: [with MS 4-113272 or MS 4-113275 Not Incorporated]:
Nose steering is not available for approximately 8 s after selection of STEERING Switch
to STEERING.
WINDSHIELD HEAT ........................................................................................................................... As Req’d
Set windshield heat selector to OFF or NORM. Check WSHLD CTRL caution light out.
NOTE:
Do Not select windshield heat to NORM when SAT is greater than 20°C.
PLT SIDE WDO / HT Switch .............................................................................................................. As Req’d
Under conditions of slush or wet snow covered taxiways:
* System Check Once Every 24 h Flying Day.
(cont’d on next page)
AOM DASH 8-Q400
2.17-28
[Rev. 18] 21 NOV 2016
CHAPTER 2
NORMAL PROCEDURES
AFTER START (cont’d)
RADAR / NAV / COM .................................................................................................................................... Set
Set WX Radar rotary selector to STBY.
• Check required "TO / FROM" and "NEXT" legs for departure are indicated on the pilot and co-pilot FMS
CDU's
• Check required VHF Comm, VHF Nav and ADF frequencies are programmed for taxi, take-off and departure
Transponder ....................................................................................................................................... As Req’d
If required to squawk an assigned transponder code during taxi:
• Set required ATC code and select ATC ON.
PFD / MFD / ED ........................................................................................................................................ Check
Check Primary Flight Display, Multi-Function Display and Engine Display for failure messages.
Check required nav source, course, distance-to-go, heading and map information is correctly displayed on pilot
and co-pilot displays for departure.
Yaw Damper ................................................................................................................................................. On
Check YD advisory pointers illuminate.
AFTER START
EXT PWR / APU .......................................................................................................................................... OFF
MAIN BUS TIE ............................................................................................................................................ OFF
BLEED AIR 1 and 2 .................................................................................................................... On / As Req’d
BATTERY TEMPS .................................................................................................................................... Check
Condition Levers ...................................................................................................................................... MAX
RECIRC Fan [with MS 4-126236 Not Incorporated] ..................................................................................... On
STBY HYD PRESS and PTU CNTRL ........................................................................................................... ON
HYD PRESS & QTY ................................................................................................................................. Check
HYD # 3 ISOL VLV .................................................................................................................................... Open
Elevator Travel ................................................................................................................................. Full Travel
HYD # 3 ISOL VLV .................................................................................................................................. NORM
FLIGHT / TAXI Switch [with MS 4-113783 and MS 4-113785 Not Incorporated] ...................... FLIGHT / TAXI
FLAPS ...................................................................................................................................................... Select
DEICE PRESS ......................................................................................................................................... Check
RUDDER Travel ................................................................................................................................ Full Travel
Nose Wheel STEERING ............................................................................................................................... On
WINDSHIELD HEAT / PLT SIDE WDO / HT ....................................................................................... As Req’d
Radar / NAV / COMM .................................................................................................................................... Set
Transponder ....................................................................................................................................... As Req’d
PFD / MFD / ED ........................................................................................................................................ Check
Yaw Damper ................................................................................................................................................. On
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.5
2.17-29
[Rev. 16] 7 MAR 2016
* SYSTEM CHECKS ONCE EVERY 24 h (FLYING DAY)
AUTOFEATHER TEST
Condition Levers ....................................................................................... FUEL OFF or START & FEATHER
POWER Levers ......................................................................................................................................... DISC
AUTOFEATHER Switch ........................................................................................................................... Press
Check SELECT advisory light illuminates.
Observe the following appear on ED:
• A/F SELECT
• A/F TEST IN PROG
[with MS 4-113558 Not Incorporated]:
• UPTRIM appears,
• ITT and NH red radials increase,
• NTOP changes to MTOP and torque rating and torque bugs increase,
• A/F ARM appears twice,
• A/F TEST PASS,
• MTOP changes to NTOP and torque rating and torque bugs decrease
[with MS 4-113558 Incorporated]:
Observe the following sequence appears twice on ED:
• UPTRIM appears,
• ITT and NH red radials increase,
• NTOP changes to MTOP and torque rating and torque bugs increase,
• A/F ARM appears,
• A/F SELECT appears,
• UPTRIM disappears,
• MTOP changes to NTOP and torque rating and torque bugs decrease,
Observe the following appears on ED:
• A/F TEST PASS,
NOTE:
During the test # 1 or # 2 ALT FTHR advisory lights may illuminate momentarily.
If autofeather test is aborted, A/F TEST ABORT will be appear on ED.
If autofeather test fails, A/F TEST FAILED will appear on ED.
If A/F TEST ABORT or A/F TEST FAILED [with MS 4-113558 Not Incorporated],
appear(s) on ED, repeat the AUTOFEATHER TEST.
AUTOFEATHER Switch ........................................................................................................................... Press
Check SELECT advisory light out and A/F SELECT message disappears on ED.
[END]
ENGINE FIRE DETECTION TEST
ENGINE 1 and ENGINE 2 FIRE TEST DETECTION Switch ................................................................... HOLD
Hold alternately, for a minimum of 1 s, at ENGINE 1 and ENGINE 2 position and check:
• Pull FUEL / HYD OFF handle light illuminates
• FAULT A and FAULT B advisory light illuminate
• CHECK FIRE DET warning light illuminates
• Master WARNING light flashes
• ENGINE FIRE lights flash
• Fire warning tone sounds
ENGINE FIRE Light ................................................................................................................................. Press
Check ENGINE FIRE lights stop flashing and fire warning tone is silenced.
[END]
AOM DASH 8-Q400
CHAPTER 2
2.17-30
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
APU FIRE TEST
APU PWR Switch ..................................................................................................................................... Press
Check APU FUEL VALVE OPEN advisory light illuminates
APU FIRE TEST Switch ........................................................................................................... Press and Hold
Check:
•
APU FUEL VALVE OPEN advisory light out
•
APU caution and
•
CHECK FIRE DET warning and
•
APU FIRE and
•
APU FAULT and
•
APU BTL ARM and
•
APU FUEL VALVE CLOSED and
•
APU EXTG and
•
APU FAIL advisory lights illuminate
•
Master CAUTION and master WARNING lights flash.
APU FIRE TEST Switch ....................................................................................................................... Release
Check:
•
APU FUEL VALVE OPEN advisory light illuminates
•
APU caution and
•
CHECK FIRE DETECT warning and
•
APU FIRE and
•
APU FAULT and
•
APU BTL ARM and
•
APU FUEL VALVE CLOSED and
•
APU EXTG and
•
APU FAIL advisory lights out
•
Master CAUTION and master WARNING lights out.
[END]
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-31
[Rev. 16] 7 MAR 2016
BAGGAGE AFT and BAGGAGE FWD SMOKE TEST
BAGGAGE AFT TEST Switch ....................................................................................................... Position 1/2
Note master warning tone and check master WARNING and SMOKE warning lights flash
and SMOKE / EXTG, VENT INLT, VENT OTLT and AFT BTL ARM advisory lights illuminate.
BAGGAGE FWD TEST Switch ................................................................................................................. TEST
Note master warning tone and check master WARNING and SMOKE warning lights flash
and SMOKE / EXTG and FWD BTL ARM advisory lights illuminate.
NOTE:
The BAGGAGE AFT and BAGGAGE FWD smoke test should be conducted with the aft
external, forward internal and forward external baggage doors closed.
[END]
CARGO COMPARTMENT SMOKE WARNING TEST
[with Option - CR 825 CH 03262 Incorporated]
CARGO SMOKE TEST Selector ........................................................................ Rotate through 1, 2, 3 and 4
At each position observe illumination of the master WARNING and SMOKE warning lights,
VENT INLT CLOSED and VALVE OTLT CLOSED advisory lights.
NOTE:
Pause for approximately 2 s at each position.
CARGO SMOKE TEST Selector ................................................................................................................ OFF
Check master WARNING and SMOKE warning lights out,
VENT INLT CLOSED and VALVE OTLT CLOSED advisory lights out.
[END]
ADC FUNCTIONAL TEST
EFIS ADC SOURCE Switch ................................................................................................................... NORM
Check ALT FAIL, IAS FAIL and IVSI FAIL flags are out on pilot’s and co-pilot’s PFD and
valid SAT is displayed on ED.
ADC Test Switch (at TEST 1) .................................................................................................................... Hold
Check indications:
•
Barometric altimeter reading changes to 14360 ft on pilot’s PFD.
•
Altimeter barometric setting changes to 29.23 in Hg (990 hPa) on pilot’s PFD.
•
Maximum operating airspeed (VMO) is displayed as 284 KIAS on pilot’s PFD.
•
The airspeed indicator displays 285 KIAS in red on pilot’s PFD.
•
SAT indicated is - 15°C and WTG2 FAIL appears on ED.
•
IAS, IAS MISMATCH and ALT appear on PFDs.
•
PITCH TRIM, ELEVATOR FEEL and AVIONICS caution lights illuminate.
•
Overspeed warning horn is activated after 5 s.
NOTE:
TCAS FAIL may momentarily flash on PFDs and MFDs during the ADC functional test.
ADC Test Switch (at TEST 2) .................................................................................................................... Hold
Check for indications equal to ‘TEST 1’, except SAT does not change and
WTG1 FAIL advisory message appears on ED.
[END]
AOM DASH 8-Q400
CHAPTER 2
2.17-32
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
STALL WARNING TEST [with MS 4-457056, MS 4-126263 or MS 4-126307 Not Incorporated]
STALL WARN TEST Switch (at TEST 1) .............................................................................................. Hold
• Observe RA increases to greater than 500 ft and
rising runway (with tape display of altitude incorporated, rising ground) disappears.
• RA decreases to 50 ft and
rising runway (with tape display of altitude incorporated, rising ground) reappears.
• Stick shaker activates.
• # 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights illuminate.
STALL WARN TEST Switch ............................................................................................................ Release
Check # 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights out and stick shaker off.
NOTE:
Hold STALL WARN TEST switch for a minimum of 10 s prior to release.
STALL WARN TEST Switch (at TEST 2) .............................................................................................. Hold
Check for indications equal to ‘TEST 1’, except # 2 STALL SYST FAIL caution light illuminates.
NOTE:
TCAS FAIL may momentarily flash on PFDs and MFDs during the Stall Warning test.
[END]
STALL WARNING TEST [with MS 4-457056, MS 4-126263 or MS 4-126307 Incorporated]
STALL WARN TEST Switch .................................................................................................. TEST 1, Release
• # 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights illuminate.
• Stick shaker activates.
• # 1 STALL SYST FAIL and PUSHER SYST FAIL caution lights out and stick shaker off.
STALL WARN TEST Switch .................................................................................................. TEST 2, Release
Check for indications equal to ‘TEST 1’, except # 2 STALL SYST FAIL caution lights illuminates.
[END]
RUDDER ACTUATOR TEST
[with MS 4-113655 Not Incorporated]
NOSEWHEEL STEERING Switch ............................................................................................................. OFF
RUD 1 PUSH OFF Switch ................................................................................................................ Push OFF
Observe illumination of # 1 RUD HYD caution light.
Rudder Pedals ............................................................................................................... Move Left and Right
Check PFCS indication on # 1 MFD for rudder travel.
RUD 1 PUSH OFF Switch .................................................................................................................. Push ON
Observe # 1 RUD HYD caution light out
RUD 2 PUSH OFF Switch ................................................................................................................ Push OFF
Observe illumination of # 2 RUD HYD caution light.
Rudder Pedals ................................................................................................................ Move Left and Right
Check PFCS indication on # 1 MFD for rudder travel.
RUD 2 PUSH OFF Switch .................................................................................................................. Push ON
Observe # 2 RUD HYD caution light out
NOSEWHEEL STEERING Switch ............................................................................................................... ON
END]
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-33
[Rev. 16] 7 MAR 2016
FLIGHT COMPARTMENT DOOR EMERGENCY ACCESS TEST
[with MS 4-309218 or MS 4-309221 Incorporated]
Flight Compartment Door ................................................................................................ Closed and Locked
Check BAGG DOOR, CKPT DOOR, AUTO UNLK and FAIL advisory lights
and INTERNAL DOORS caution light out.
FLIGHT ATTENDANT Emergency Access Switch .......................................................... Momentarily Press
Check INTERNAL DOORS caution and AUTO UNLK advisory lights illuminate.
INTERNAL DOORS Switch ..................................................................................................................... DENY
Check AUTO UNLK advisory and INTERNAL DOORS caution lights out
and flight compartment door closed and locked.
[END]
[with Option - CR 825 CH 03262 Incorporated]
Flight Compartment Door ................................................................................................ Closed and Locked
Check CKPT DOOR, AUTO UNLK and FAIL advisory lights
and COCKPIT DOOR caution light out.
FLIGHT ATTENDANT Emergency Access Switch .......................................................... Press Momentarily
Check COCKPIT DOOR caution and AUTO UNLK advisory lights illuminate.
INTERNAL DOORS Switch ..................................................................................................................... DENY
Check AUTO UNLK advisory and COCKPIT DOOR caution lights out
and flight compartment door closed and locked.
[END]
PRIMARY, MULTI-FUNCTION and ENGINE DISPLAYS POWER RESET
Pilot’s and Co-Pilot’s PFD OFF / BRT Selectors (EFIS Control Panel) .................................. OFF then BRT
Pilot’s and Co-Pilot’s MFD OFF / BRT Selectors (EFIS Control Panel) .................................. OFF then BRT
ED OFF / BRT Selector (ESID Control Panel) ........................................................................... OFF then BRT
NOTE:
The removal of all aircraft electrical power will accomplish the intent of the power reset of the
PFD’s, MFD’s and ED.
[END]
AOM DASH 8-Q400
CHAPTER 2
2.17-34
NORMAL PROCEDURES
[Rev. 16] 7 MAR 2016
The following tests are not 24 h System Checks, however they are to be done as required if flight into icing
conditions is anticipated.
ICE PROTECTION CHECKS
AIRFRAME
DEICE PRESS Indicator .................................................................................. Check 18 ± 3 psi on each Dial
AIRFRAME MODE SELECT Switch ........................................................................................................ FAST
During one complete cycle (60 s) execute the following checks:
• Make sure the WING advisory lights illuminate and go off sequentially in pairs, commencing with the outboard pair and ending with the inboard pair, followed by the inboard TAIL then the outboard TAIL.
NOTE:
The sequence of the WING 3rd and 4th advisory lights on the left side is reversed.
The correct sequence is as follows:
ICE PROTECTION
6
5
TAIL
5
6
AIRFRAME
OFF MANUAL
SELECT
AIRFRAME MODE SELECT
OFF
SLOW
MANUAL
FAST
1
2
4
3
WING
4
5
3
2
1
6
NOTE
Manual switch positions and
related indicator light
sequence correspond with
deice boot inflation sequence
shown below. Numbers do
not actually appear on panel.
6
5
1
2
3
6 4
3
•
•
•
5 4
2
1
f
b
Check the DEICE PRESS indicator needles fluctuate in phase with the indicator lights.
Check that the left engine intake boot advisory light illuminates with the inboard tail advisory lights and the
right engine intake boot advisory light illuminates with the outboard tail advisory light in the TAIL boot
sequence.
Check that the cycle recommences after 24 s dwell period then AIRFRAME MODE SELECT - OFF.
AIRFRAME MANUAL SELECT Switch ................................................................................................. Rotate
Observe WING, TAIL and ENGINE INTAKE advisory lights illuminate as selected.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-35
[Rev. 16] 7 MAR 2016
ICE PROTECTION CHECKS (cont’d)
PROPELLER
PROP Selector .......................................................................................................................................... TEST
Check PROPS advisory lights illuminate individually and go out in sequence through one cycle.
The normal operating (green arc) on the OIL temperature Indication on ED changes to 55 to 107°C.
NOTE:
In the event that the PROP selector is released early from the TEST position, wait 30 s before
repeating test.
PROP Selector ............................................................................................................................................ OFF
Check the normal operating (green arc) on the Oil Temperature indicator changes to 0 to 107°C.
ENGINE INTAKE DOORS
ENGINE INTAKE DOORS Switches ....................................................................................................... Press
Check CLOSED advisory lights go out and the OPEN / HTR advisory lights illuminate.
ENGINE INTAKE Switches ....................................................................................................................... Push
Check CLOSED advisory lights turn on.
NOTE:
The HTR advisory light may not turn on if SAT is > 15°C.
WINDSHIELD HEAT
WINDSHIELD HEAT Selector ................................................................................................................. NORM
Check WSHLD CTRL caution light out.
NOTE:
It will require a period of 5 min in NORM to confirm correct windshield heat operation.
STALL PROTECTION SYSTEM
REF SPEEDS Switch ................................................................................................................................ INCR
Check [INCR REF SPEED] appears on ED.
REF SPEEDS Switch .................................................................................................................................. OFF
Check [INCR REF SPEED] disappears on ED.
* SYSTEM CHECK ONCE EVERY 24 h (FLYING DAY)
Autofeather ................................................................................................................................................. Test
Fire Detection ............................................................................................................................................. Test
BAGGAGE SMOKE Warning (AFT and FWD) .......................................................................................... Test
STALL WARNing 1 and 2 ........................................................................................................................... Test
ADC 1 and 2 ................................................................................................................................................ Test
RUDDER Actuator ...................................................................................................................................... Test
Flight Compartment Door Emergency Access ............................................................................... As Req’d
PFD / MFD / ED Power Reset ............................................................................................................ As Req’d
ICE PROTECTION .............................................................................................................................. As Req'd
AOM DASH 8-Q400
CHAPTER 2
2.17-36
[Rev. 16] 7 MAR 2016
2.17.5.6
NORMAL PROCEDURES
TAXI CHECK
The following items are to be checked during the taxi phase.
However, they should be completed early enough so as to allow both pilots to monitor their surroundings while
taxiing to the active runway.
TAXI Light ........................................................................................................................................... As Req’d
Altimeters ..................................................................................................................................................... Set
Make sure the current altimeter setting is on
the pilot’s and co-pilot’s barometric altimeters and the standby altimeter.
Compare altitude indications on pilot’s and co-pilot’s PFD.
NOTE:
Altimeter altitude readout must be within 60 ft below 5000 ft and
vary linearly to 100 ft at 10000 ft cross check with standby altimeter in case of mismatch.
Flight Instruments .................................................................................................................................. Check
Check and set as required.
NOTE:
[with MS 4-126211 Not Incorporated] the standby compass is unreliable with landing approach
and flare lights selected on.
TANK 1 AUX PUMP / TANK 2 AUX PUMP Switches .................................................................................. ON
Check TANK 1 AUX PUMP ON and TANK 2 AUX PUMP ON advisory lights illuminate.
AUTOFEATHER Switch .......................................................................................................................... Select
Check autofeather SELECT advisory light illuminates on PROPELLER CONTROL panel and
A/F SELECT appears on ED
CAUTION: If A/F ARM advisory fails to appear on ED when Power Levers are advanced to the
Rating detent, take-off must be rejected.
FLAPS Lever ....................................................................................................................................... Set / IND
Confirm desired take-off setting on FLAP indication on # 2 MFD.
TRIMs ......................................................................................................................................................... 3 Set
Set the 3 trim controls:
• Aileron and rudder trim indicators to 0 position
• Elevator trim indicator within the white take-off (TO) range.
TAKE-OFF ELEVATOR TRIM vs CG
CG - % MAC
TAKE-OFF RANGE
FORWARD 13.8%
AFT END
AFT 36%
FORWARD END
NOTES:
1. When setting the elevator trim, holding the elevator trim switch for greater than 3 s will
cause the “elevator trim in motion’ audio tone to sound and the ELEVATOR TRIM SHUT
OFF switch PUSH OFF advisory light to illuminate.
2. [with MS 4-126383 Not Incorporated]: To avoid possible activation of the Take-off Configuration aural warning, with a Centre of Gravity at / or near the FWD or AFT Limit, set the
ELEVATOR TRIM with the trim pointer “one half of the pointer's width” inside the forward
edge (with AFT CG) or inside the aft edge (with FWD CG) of the TO trim band.
Condition Levers ...................................................................................................................................... MAX
Move CONDITION LEVERS to MAX position and set friction as required. Check NTOP appears on ED.
T/O WARN ................................................................................................................................................... Test
Select T/O WARN switch to TEST and hold.
Confirm take-off warning horn does not sound then release switch.
NOTE:
The take-off warning horn will sound if any of the following conditions are not met:
- Inboard or outboard spoilers are extended,
- Elevator trim is outside of the take-off range,
- Emergency Brake lever set to Park,
- One or both Condition Levers not set to MAX,
- Flap position outside the range of 5o to 15o.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-37
[Rev. 16] 7 MAR 2016
TAXI CHECK (cont’d)
PITOT STATIC Heat Switches .................................................................................................................... ON
Set PITOT STATIC PORTS switches to STBY, 1 and 2 positions.
ICE PROTECTION .............................................................................................................................. As Req’d
Make sure de-icing and anti-icing switches are set as required for take-off in the ambient conditions.
For Ice Protection Procedures refer to Sub-Chapter 2.17.5.16
CAUTION / WARNING Lights ................................................................................................................. Check
Make sure all caution and warning light annunciators are off unless stated in MEL.
Flight Clearances ............................................................................................................................. Reviewed
Cabin ...................................................................................................................................................... Secure
Notify the cabin crew member(s) on the PA system to secure the cabin for take-off.
TAXI CHECK
TAXI Light .......................................................................................................................................... As Req’d
Altimeters ..................................................................................................................................................... Set
Flight Instruments .................................................................................................................................. Check
TANK AUX PUMPS 1 and 2 ......................................................................................................................... ON
Autofeather ............................................................................................................................................. Select
FLAPS ................................................................................................................................................. Set / IND
TRIMs ......................................................................................................................................................... 3 Set
Condition Levers ....................................................................................................................................... MAX
T/O WARN ................................................................................................................................................... Test
PITOT STATIC Heat ..................................................................................................................................... ON
ICE PROTECTION .............................................................................................................................. As Req’d
CAUTION / WARNING Lights ................................................................................................................. Check
Flight Clearances ............................................................................................................................. Reviewed
Cabin ...................................................................................................................................................... Secure
AOM DASH 8-Q400
CHAPTER 2
2.17-38
[Rev. 16] 7 MAR 2016
2.17.5.7
NORMAL PROCEDURES
LINE-UP
These items should be done as early as possible after being cleared to line up on to the active runway.
This allows both pilots to monitor runway surroundings before and while entering the active runway.
Flight Attendant Notification ............................................................................................................ As Req’d
Notify the cabin crew members that the clearance for take-off has been received.
BLEED AIR 1 and 2 ................................................................................................................... MIN / As req’d
•
Turn the BLEED FLOW CONTROL rotary knob to MIN.
•
Set the BLEED switches to OFF
(if take-off with Bleed “ON”, AOM Supplement 2 and / or AFM Supplement 21, set BLEED 1 and 2 to ON).
Anti-Collision ........................................................................................................................................... White
Transponder / TCAS .................................................................................................................................... ON
Make sure the correct transponder code is inserted, then
set the transponder to ON / ALT on the ARCDU panel by pressing line select key 4R (ATC) on ARCDU for
more than 2 s.
Observe TA ONLY is annunciated on EHSI / PFD and TA ONLY AUTO is annunciated on the ND / MFD.
Flight Controls ............................................................................................................................. Check / Free
Check the operation and freedom of movement of flight controls and spoilers through full travel and
note appropriate PFCS indications on # 1 MFD.
NOTE:
Full spoiler extension is indicated by a pointer position defined by assuming the full extension
index mark is shifted 1 arc width down.
FLIGHT / TAXI Switch .............................................................................................................................. Flight
Make sure the FLIGHT / TAXI switch on the GLARESHIELD is in the FLIGHT position.
Check SPOILERS ROLL OUTBD and ROLL INBD advisory lights turn on and the PFCS indication on # 1 MFD
shows LI, RI and LO, RO spoilers extend.
NOTE:
Full spoiler extension is indicated by a pointer position defined by assuming the full extension
index mark is shifted 1 arc width down.
LANDING / TAXI Lights ...................................................................................................................... ON / OFF
The taxi light may be turned off at this time.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-39
[Rev. 16] 7 MAR 2016
LINE-UP
F/A Notification .................................................................................................................................. As Req’d
BLEED AIR 1 and 2 ................................................................................................................... MIN / As Req’d
Anti-Collision ........................................................................................................................................... White
Transponder / TCAS .................................................................................................................................... ON
Flight Controls ............................................................................................................................. Check / Free
FLIGHT / TAXI Switch .............................................................................................................................. Flight
LANDING / TAXI Lights ..................................................................................................................... ON / OFF
NOTE:
Before Entering Icing Conditions, see Sub-Chapter 2.17.5.16.
AOM DASH 8-Q400
CHAPTER 2
2.17-40
[Rev. 18] 21 NOV 2016
2.17.5.8
NORMAL PROCEDURES
AFTER TAKE-OFF
Landing Gear ................................................................................................................................................ Up
At a positive rate of climb, (indicated on the altimeter and IVSI), select the landing gear selector UP
and make sure the landing gear retracts.
Amber light in the selector handle, amber and red undercarriage advisory lights turn on then go off.
All lights should be off when the gear is up and locked.
FLAPS ............................................................................................................................................................. 0°
After commencement of 3rd segment (minimum 400 ft AGL) and
at or above Flap Retraction Initiation speed (VFRI), set flap selector lever to 0°.
Check flap indicator and make sure flaps retract to 0°.
Autofeather ................................................................................................................................................ OFF
Push the AUTOFEATHER switchlight and make sure:
•
Autofeather SELECT advisory light turns off on the PROPELLER CONTROL panel,
•
A/F SELECT indication on the ED turns off.
Climb Power ................................................................................................................................................. Set
CLIMB at 900 RPM:
•
Set the CONDITION LEVERS to 900 RPM.
CLIMB at 850 RPM:
•
Set the CONDITION LEVERS to 850 RPM and then push the MCL pushbutton on the ENGINE CONTROL
panel.
BLEED AIR 1 and 2 ................................................................................................................... ON / As Req’d
•
Set BLEED CONTROL switches to 1 and 2 positions.
•
Turn BLEED AIR FLOW CONTROL rotary selector to NORM or MAX.
STBY HYD PRESS and PTU CNTRL Switches .................................................................................... NORM
Check STBY HYD PRESS ON, PTU CNTRL ON and PTU pressure
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated] advisory lights out.
TANK AUX PUMPS 1 and 2 ........................................................................................................................ OFF
Check TANK 1 AUX PUMP ON and TANK 2 AUX PUMP ON advisory lights out.
Engine Temps & Pressures .................................................................................................................... Check
Check all engine instruments on the ED are within limits (no red or yellow indication).
ICE PROTECTION .............................................................................................................................. As Req’d
Make sure de-icing and anti-icing switches are set as required for the ambient conditions.
For Ice Protection Procedures refer to Sub-Chapter 2.17.5.16
Cabin Press & Temp Controls ............................................................................................................... Check
Monitor the cabin pressurization panel to make sure the cabin is pressurizing.
Set Cabin and Flight COMPARTMENT Temperature controls as required.
Passenger Signs ................................................................................................................................ As Req’d
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-41
[Rev. 16] 7 MAR 2016
AFTER TAKE-OFF
Landing Gear ................................................................................................................................................ Up
FLAPS ............................................................................................................................................................ 0°
BLEED AIR 1 and 2 .................................................................................................................... ON / As Req'd
Autofeather ................................................................................................................................................. OFF
Climb Power ................................................................................................................................................ Set
STBY HYD PRESS and PTU CNTRL ..................................................................................................... NORM
TANK AUX PUMPS 1 and 2 ........................................................................................................................ OFF
Engine Temps & Pressures ................................................................................................................... Check
ICE PROTECTION .............................................................................................................................. As Req’d
Cabin Press & Temp Controls ............................................................................................................... Check
Passenger Signs ............................................................................................................................... As Req’d
AOM DASH 8-Q400
CHAPTER 2
2.17-42
[Rev. 16] 7 MAR 2016
2.17.5.9
NORMAL PROCEDURES
CRUISE
Altimeters ..................................................................................................................................................... Set
When required, set current altimeter setting on standby altimeter, pilot’s and co-pilot’s altimeters.
Set the current altimeter setting on the Barometric Correction Indicator on the cabin altitude control panel.
Cross-check all altimeters.
NOTE:
Altimeter altitude readout must be within 60 ft below 5000 ft and
vary linearly to 170 ft at 25000 ft.
Cross-check with standby altimeter in case of mismatch.
With Integrated Standby Instrument [with MS 4-432835 or MS 4-456883 Not Incorporated],
the standby altimeter readings have to be within the tolerances specified in the Table
published in Sub-Chapter 2.3 (ALTIMETER SETTING AND CHECKING).
POWER ......................................................................................................................................................... Set
NORMAL CRUISE with 850 RPM:
•
Set the CONDITION LEVERS to 850 RPM.
MAX CRUISE with 900 RPM:
•
Set the CONDITION LEVERS to 900 RPM and then push the MCR pushbutton on the ENGINE CONTROL
panel.
Cabin Press ............................................................................................................................................. Check
Monitor the Cabin Pressurization Panel and make sure:
•
Cabin Altitude Rate of Climb has stabilized at 0.
•
Cabin Altimeter indicates correct cabin altitude for ambient altitude.
•
Cabin Differential pressure indicates a maximum of 5.46 ± 0.1 psi.
Lights .................................................................................................................................................. As Req’d
CRUISE
Altimeters ..................................................................................................................................................... Set
POWER ......................................................................................................................................................... Set
Cabin Press ............................................................................................................................................. Check
Lights .................................................................................................................................................. As Req’d
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.10
2.17-43
[Rev. 16] 7 MAR 2016
DESCENT
Altimeters ..................................................................................................................................................... Set
When required, set current altimeter setting on standby altimeter, pilot’s and co-pilot’s altimeters.
Set the current altimeter setting on the Barometric Correction Indicator on the cabin altitude control panel.
Cross-check all altimeters.
NOTE:
Altimeter altitude readout must be within ± 60 ft at SL and vary linearly to ± 170 ft at 25000 ft.
Cross-check with standby altimeter in case of mismatch.
Approach / Landing Briefing ............................................................................................................... Review
Ensure the approach and landing briefing has been completed.
CABIN ALTITUDE Controls ........................................................................................................................ Set
Set the destination field elevation on the Cabin Altitude Indicator.
ICE PROTECTION .............................................................................................................................. As Req’d
If icing conditions exist or are anticipated, make sure ice protection is selected for the ambient conditions.
Comply with Icing Procedures on Sub-Chapter 2.17.5.16
DESCENT
Altimeters ..................................................................................................................................................... Set
Approach / Landing Briefing ............................................................................................................... Review
CABIN ALTITUDE Controls ........................................................................................................................ Set
ICE PROTECTION .............................................................................................................................. As Req’d
NOTE:
Before Entering Icing Conditions see Sub-Chapter 2.17.5.16
AOM DASH 8-Q400
CHAPTER 2
2.17-44
[Rev. 18] 21 NOV 2016
2.17.5.11
NORMAL PROCEDURES
APPROACH
Altimeters ..................................................................................................................................................... Set
When required, set current altimeter setting on standby altimeter, pilot’s and co-pilot’s altimeters.
Set the current altimeter setting on the Barometric Correction Indicator on the cabin altitude control panel.
Cross-check all altimeters.
NOTE:
Altimeter altitude readout must be within ± 60 ft at SL and vary linearly to ± 170 ft at 25000 ft.
Cross-check with standby altimeter in case of mismatch.
LIGHTS ............................................................................................................................................... As Req’d
GPWS LANDING FLAP ........................................................................................................................... Select
Set the GPWS LANDING FLAP switch to the desired landing flap configuration
for correct GPWS performance and check appropriate 10°, 15° or 35° advisory light turns on.
FUEL TRANSFER Switch .......................................................................................................................... OFF
•
Make sure fuel asymmetry is within 272 kg (600 lb).
•
FUEL TRANSFER switch is OFF.
•
VALVE on MFD indicates CLOSED.
TANK AUX PUMP 1 and 2 ............................................................................................................................ ON
Make sure the TANK 1 and TANK 2 AUXILIARY FUEL PUMP switchlights are ON.
STBY HYD PRESS and PTU CNTRL Switches .......................................................................................... ON
Check STBY HYD PRESS ON, PTU CNTRL ON and PTU pressure
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated]
advisory lights illuminate.
HYD PRESS & QTY ................................................................................................................................. Check
Make sure the following hydraulic indicators on the MFD show:
•
Standby Pressure – 2800 - 3000 psi
•
Main Pressure 1 & 2 – 2900 - 3100 psi
•
System Quantity (minimum):
# 1 System 40%
# 2 System 40%
# 3 System 45%
Passenger Signs .......................................................................................................................................... ON
Set fasten belts and no smoking signs to FASTEN BELTS and NO SMOKING position.
CAUTION / WARNING Lights ................................................................................................................. Check
Check the caution / warning lights panel and make sure no caution or warning lights are on.
If due to a non-normal situation, one or more caution or warning lights are on, the lights and related system
considerations for landing must be reviewed before landing.
Cabin ...................................................................................................................................................... Secure
Confirm with the Cabin Crew that the cabin is secure for landing.
-
If icing conditions exist or are anticipated, make sure ice protection is selected for the ambient conditions.
Comply with the Icing Procedures on Sub-Chapter 2.17.5.16
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-45
[Rev. 16] 7 MAR 2016
APPROACH
Altimeters ..................................................................................................................................................... Set
LIGHTS ............................................................................................................................................... As Req’d
GPWS LANDING FLAP .......................................................................................................................... Select
FUEL TRANSFER Switch ........................................................................................................................... OFF
TANK AUX PUMP 1 and 2 ........................................................................................................................... ON
STBY HYD PRESS and PTU CNTRL ........................................................................................................... ON
HYD PRESS & QTY ................................................................................................................................. Check
Passenger Signs ......................................................................................................................................... ON
CAUTION / WARNING Lights ................................................................................................................. Check
Cabin ...................................................................................................................................................... Secure
NOTE:
Before Entering Icing Conditions see Sub-Chapter 2.17.5.16
AOM DASH 8-Q400
CHAPTER 2
2.17-46
[Rev. 16] 7 MAR 2016
2.17.5.12
NORMAL PROCEDURES
LANDING
ICE PROTECTION .............................................................................................................................. As Req’d
If icing conditions exist or are anticipated, make sure ice protection is selected for the ambient conditions.
For Ice Protection Procedures refer to Sub-Chapter 2.17.5.16.
LANDING GEAR ...................................................................................................................... Down / 3 Green
FLAP .................................................................................................................................................... Set / Ind
Check the flap selector lever and make sure it is set to 10°, 15° or 35° and
the flap indicator on the MFD shows 10°, 15° or 35°.
Condition Levers ...................................................................................................................................... MAX
BLEED AIR 1 and 2 ............................................................................................................................ As Req’d
•
Turn the BLEED FLOW CONTROL rotary knob to MIN.
•
Turn BLEED 1 and 2 off.
(If landing with Bleed “ON”, AOM Supplement 2 and / or AFM Supplement 21, turn BLEED 1 and 2 on).
•
Check Cabin Differential maximum 1.0 psi.
NOTE:
If Cabin Differential is greater than 1.0 psi refer to Sub-Chapter 3.1.1.12.
Flight Attendant Notification ............................................................................................................ As Req’d
LANDING
ICE PROTECTION .............................................................................................................................. As Req’d
LANDING GEAR ...................................................................................................................... Down / 3 Green
FLAP .................................................................................................................................................... Set / Ind
Condition Levers ...................................................................................................................................... MAX
BLEED AIR 1 and 2 .................................................................................................................. MIN / As Req’d
F/A Notification .................................................................................................................................. As Req’d
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.13
2.17-47
[Rev. 16] 7 MAR 2016
AFTER LANDING
CONTROL LOCK Lever ............................................................................................................................... ON
Pull FLIGHT CONTROL LOCK lever aft until it locks.
Transponder ...................................................................................................................................... As Req’d
Set the transponder to SBY on the ARCDU
by pressing line select key 4R on ARCDU for more than 2 s, when required.
Radar .......................................................................................................................................................... SBY
FLAPS Lever .................................................................................................................................................. 0°
Check FLAP indication on # 2 MFD.
TANK 1 AUX PUMP and TANK 2 AUX PUMP Switches ........................................................................... OFF
Check TANK 1 AUX PUMP ON and TANK 2 AUX PUMP ON advisory lights out.
Yaw Damper ................................................................................................................................................ OFF
FLIGHT / TAXI Switch ................................................................................................................................ TAXI
Check spoilers ROLL OUTBD and ROLL INBD advisory lights out and
PFCS indication shows LI, RI and LO, RO SPOILERS retracted.
Anti-Collision ............................................................................................................................................. RED
EXTERIOR LIGHTS ............................................................................................................................ As Req’d
Normally landing and flare lights are switched off, the taxi lights on.
ICE PROTECTION ............................................................................................................................. As Req’d
If icing conditions exist or are anticipated, make sure ice protection is selected for the ambient conditions.
For Ice Protection Procedures refer to Sub-Chapter 2.17.5.16.
MAIN BUS TIE .............................................................................................................................................. TIE
APU (if applicable) .............................................................................................................................. As Req’d
BLEED 1 and BLEED 2 Switches ..................................................................................................... As Req’d
AFTER LANDING
CONTROL LOCK ......................................................................................................................................... ON
Transponder ...................................................................................................................................... As Req’d
Radar .......................................................................................................................................................... SBY
FLAPS ............................................................................................................................................................ 0°
TANK AUX PUMPS 1 and 2 ........................................................................................................................ OFF
Yaw Damper ................................................................................................................................................ OFF
FLIGHT / TAXI Switch ................................................................................................................................ TAXI
Anti-Collision .............................................................................................................................................. Red
Lights ................................................................................................................................................. As Req’d
ICE PROTECTION .............................................................................................................................. As Req’d
MAIN BUS TIE ............................................................................................................................................... Tie
APU (if applicable) .............................................................................................................................. As Req’d
BLEED AIR 1 and 2 ............................................................................................................................ As Req’d
AOM DASH 8-Q400
CHAPTER 2
2.17-48
[Rev. 18] 21 NOV 2016
2.17.5.14
NORMAL PROCEDURES
SHUT-DOWN
TAXI Light ................................................................................................................................................... OFF
EMERG BRAKE ............................................................................................................................................ ON
STBY HYD PRESS and PTU CNTRL Switches .................................................................................... NORM
Check STBY HYD PRESS ON, PTU CNTRL ON and PTU pressure
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated] advisory lights out.
POWER Levers ......................................................................................................................................... DISC
Condition Levers ............................................................................................................. START & FEATHER
Allow engines to stabilize for 30 s minimum before shut-down.
Passenger Signs ........................................................................................................................................ OFF
Nosewheel Steering .................................................................................................................................. OFF
Radar .......................................................................................................................................................... OFF
Transponder ............................................................................................................................................. STBY
BLEED AIR 1 and 2 ........................................................................................................................... MIN / OFF
•
Turn the BLEED AIR Flow Control rotary knob to MIN.
•
Set BLEED 1 and 2 switches to OFF.
APU / GPU .......................................................................................................................................... As Req’d
Emergency Lights ..................................................................................................................................... OFF
Condition Levers (30 s) ................................................................................................................... FUEL OFF
Lights .................................................................................................................................................. As Req’d
BATTERY MASTER, MAIN, AUX & STBY BATT Switches .............................................................. As Req’d
If electrical power is to be removed from the aircraft prior to the next flight,
continue with the following Last Flight shut-down procedure:
2.17.5.15
LAST FLIGHT
RECIRC Fan [with MS 4-126236 Not Incorporated] ................................................................................... OFF
All Displays ................................................................................................................................................ OFF
ANTI SKID ................................................................................................................................................... OFF
Set ANTI SKID switch to OFF position and check:
•
INBD ANTI SKID and OUTBD ANTI SKID caution lights are illuminated.
BATTERY MASTER, MAIN, AUX & STBY BATT Switches ...................................................................... OFF
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17-49
[Rev. 16] 7 MAR 2016
SHUT-DOWN
TAXI Light ................................................................................................................................................... OFF
EMERG BRAKE ........................................................................................................................................... ON
STBY HYD PRESS and PTU CNTRL ..................................................................................................... NORM
POWER Levers ......................................................................................................................................... DISC
Condition Levers ..................................................................................................................... Start & Feather
Passenger Signs ........................................................................................................................................ OFF
Nosewheel Steering ................................................................................................................................... OFF
Radar ........................................................................................................................................................... OFF
Transponder ............................................................................................................................................ STBY
BLEED AIR 1 and 2 ........................................................................................................................... MIN / OFF
APU / GPU .......................................................................................................................................... As Req’d
EMER LIGHTS ............................................................................................................................................. OFF
Condition Levers (30 s) ................................................................................................................... FUEL OFF
Lights ................................................................................................................................................. As Req’d
BATTERY MASTER, MAIN, AUX & STBY BATT Switches .............................................................. As Req’d
LAST FLIGHT
RECIRC Fan [with MS 4-126236 Not Incorporated] .................................................................................... OFF
All Displays ................................................................................................................................................. OFF
ANTI SKID ................................................................................................................................................... OFF
MAIN, AUX & STBY BATT Switches ......................................................................................................... OFF
BATTERY MASTER .................................................................................................................................... OFF
AOM DASH 8-Q400
CHAPTER 2
2.17-50
[Rev. 16] 7 MAR 2016
NORMAL PROCEDURES
2.17.5.16
ICE PROTECTION PROCEDURES
2.17.5.16.1
TAKE-OFF IN or INTO ICING CONDITIONS
PRE TAKE-OFF CHECKS:
ENGINE INTAKE DOORS Switches ........................................................................................................ Press
Check OPN / HTR advisory lights illuminate.
WINDSHIELD HEAT Selector ................................................................................................................ NORM
DEICE PRESS Indicator .................................................................................. Check 18 ± 3 psi on each Dial
PROP Selector ............................................................................................................................................. ON
Observe the normal operating (green arc) on the OIL temperature indication on ED changes to 55°C to 107°C.
NOTE:
With SAT greater than + 5°C, the PROPS advisory lights will not illuminate.
NOTE:
[with MS 4-113553 Not Incorporated]:
To ensure engine air inlet ice protection, it is acceptable to set take-off power with a minimum
oil temperature of 55°C (OIL temperature indication on ED in the yellow arc).
Oil temperature must reach 65°C or greater (OIL temperature indication on ED in the green
arc) within 3 min after take-off power is set.
AFTER TAKE-OFF:
At 400 ft AGL, commencement of 3rd Segment:
Increase Airspeed to VCLIMB + 20 kt.
FLAPS Lever ...................................................................................................................................... 0° at VFRI
At flap retraction initiation speed flap 5° and 10° or flap 15°.
REF SPEEDS ............................................................................................................................................. INCR
Check [INCR REF SPEED] appears on ED.
CAUTION: If airspeed is not increased before REF SPEEDS switch is set to INCR, stall warning
may occur.
At 400 ft AGL, continuation of 2nd Segment:
Airspeed .............................................................................................................................................. Increase
Increase airspeed to V2 + 20 kt (Flap 5°, 10° and 15°).
REF SPEEDS Switch ................................................................................................................................ INCR
Check [INCR REF SPEED] appears on ED.
CAUTION: If airspeed is not increased before REF SPEEDS switch is set to INCR, stall warning
may occur.
On initial detection of ice:
AIRFRAME Mode Selector ...................................................................................................................... FAST
At commencement of 3rd segment:
Increase Airspeed to VCLIMB + 20 kt
FLAPS Lever ...................................................................................................................................... 0° at VFRI
At flap retraction initiation speed flap 5° and 10° or flap 15° + 20 kt.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.16.2
2.17-51
[Rev. 16] 7 MAR 2016
FLIGHT IN ICING CONDITIONS
BEFORE ENTERING ICING CONDITIONS or WHEN ICE IS DETECTED or WHEN FLASHING “ICE
DETECTED” ADVISORY APPEARS ON ED
ENGINE INTAKE Door Switches ............................................................................................................ Press
Check OPN / HTR advisory lights illuminate.
PROP Selector ............................................................................................................................................. ON
Observe PROPs advisory lights illuminate individually and go out in sequence and
the normal operating (green arc) on the oil temperature indication on ED change to 65°C to 107°C.
NOTE:
The effectiveness of the propeller de-icing system can be improved and propeller vibration
reduced by operation of the propellers at 1020 RPM.
REF SPEEDS Switch ................................................................................................................................ INCR
Check [INCR REF SPEED] appears on ED.
WINDSHIELD HEAT Selector ................................................................................................................. NORM
If ice forms on the forward edge of pilot’s side window:
PLT SIDE WDO / HT Switch ........................................................................................................................ ON
DEICE PRESS Indicator ................................................................................... Check 18 ± 3 psi on each Dial
NOTE:
To ensure de-ice pressure is maintained at 15 psi or greater during descent, holding and
approach, it may be necessary to increase NL by advancing POWER levers.
CLIMB, CRUISE and DESCENT IN ICING CONDITIONS
On initial detection of ice:
Minimum Airspeed:
• Climb - Final Take-off Climb Speed + 20 kt.
• Descend - 1.23 VSR flap 0° + 25 kt.
AIRFRAME MODE SELECT Selector ...................................................................................... FAST or SLOW
Depending on the rate of ice accumulation.
Check WING and TAIL advisory lights illuminate sequentially in pairs.
NOTE:
Monitor ice accumulation between boot cycles to confirm that the selected AIRFRAME MODE
rate (FAST or SLOW) is appropriate.
When using the wing inspection lights, the inboard boot area only, visible from the flight
compartment, is sufficiently illuminated for assessing ice accumulation.
CAUTION: An accumulation of ice on the airplane may change the stall characteristics, stall speed,
or warning margin provided by the stall warning system.
Monitor WING and TAIL advisory lights for normal operation.
When ice accumulation is no longer detected and the ICE DETECTED advisory is not present on the ED:
- Continue to operate the boots for 2 complete cycles.
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 2
2.17-52
NORMAL PROCEDURES
[Rev. 16] 7 MAR 2016
FLIGHT IN ICING CONDITIONS (cont’d)
Then:
AIRFRAME MODE SELECT Selector ....................................................................................................... OFF
When the aircraft is aerodynamically clean:
NOTE:
The aircraft can only be considered aerodynamically clean when all ice is removed from the
visible leading edges and wing tips.
REF SPEEDS Switch ................................................................................................................................. OFF
Check [INCR REF SPEED] disappears on ED.
Minimum airspeed 1.23 VSR flap 0° or Approach and VREF flap 5°, 10° and 15°.
HOLDING, APPROACH and LANDING IN ICING CONDITIONS
NOTES:
1. When holding in icing conditions flap must be at 0°.
2. To maintain the minimum engine oil temperature of 65°C during descent, holding and
approach, in icing conditions, it may be necessary to increase engine power.
The increase in engine power will be limited by the allowable maximum airspeed appropriate to VMO, VLO, VFE, aircraft system malfunctions, turbulence and ATC instructions.
On initial detection of ice:
•
Increase Speeds and Landing Field Length as follows:
FLAP
VAPP
VGA
VREF
LFL
HOLDING
0°
+ 25 kt
+ 20 kt
+ 25 kt
-
190 kt MIN
5°
+ 20 kt
+ 20 kt
+ 20 kt
-
-
10°
+ 20 kt
+ 20 kt
+ 20 kt
+ 25%
-
15°
+ 20 kt
+ 20 kt
+ 20 kt
+ 25%
-
35°
-
-
+ 15 kt
+ 20%
-
AIRFRAME MODE SELECT Selector ..................................................................................................... FAST
Check WING and TAIL advisory lights illuminate sequentially in pairs.
HOLDING, APPROACH and LANDING AFTER FLIGHT IN ICING CONDITIONS or ICING IS NO LONGER
DETECTED and THE ICE DETECTED ADVISORY DISAPPEARES ON ED
Minimum airspeed as above (Holding, Approach and Landing in Icing Conditions).
Continue to operate the boots for 2 complete cycles.
Then:
AIRFRAME MODE SELECT Selector ....................................................................................................... OFF
When the aircraft is aerodynamically clean:
NOTE:
The aircraft can only be considered aerodynamically clean when all ice is removed from the
visible leading edges and wing tips.
REF SPEEDS Switch ................................................................................................................................. OFF
Check [INCR REF SPEED] disappears on ED.
Minimum airspeed 1.23 VSR Flap 0° or Approach and VREF Flap 5°, 10° and 15°.
AOM DASH 8-Q400
CHAPTER 2
NORMAL PROCEDURES
2.17.5.16.3
2.17-53
[Rev. 16] 7 MAR 2016
FLIGHT IN SEVERE ICING
Autopilot ................................................................................................................... Disconnect Immediately
CAUTION: Be prepared for a possible roll force requirement by firmly holding the control wheel
prior to disconnecting the autopilot.
Condition Levers ............................................................................................................................ MAX / 1020
POWER Levers ......................................................................................................................... Adjust to MCP
Minimum Speed ................................................................................................................................ 190 kt IAS
Exit severe icing conditions by changing altitude and / or course as required.
CAUTION: Avoid aggressive maneuvering.
When clear of severe icing conditions:
NOTE:
It can be assumed that the airplane is no longer affected by the severe ice encounter when the
ice accumulated on the flight compartment side window is removed.
When visible, other surfaces, such as the propeller spinner and wing leading edges aft of the
de-ice boot, should also be used to confirm that the ice accumulated during the severe icing
encounter has cleared.
POWER Levers and Condition Levers ................................................................................. Adjust As Req’d
Airspeed ............................................................................................................................................. As Req’d
Autopilot ............................................................................................................................................ As Req’d
CAUTION: Prior to engaging the autopilot, ensure that in wings level steady state flight, there is no
abnormal roll control force and the required lateral trim is appropriate for the aircraft
configuration.
Refer to as appropriate Holding, Approach and Landing procedure (above).
If it cannot be determined that the aircraft is no longer affected by the severe icing encounter:
Refer to as appropriate Holding, Approach and Landing procedure (above).
CAUTION: Do Not engage Autopilot.
AOM DASH 8-Q400
THIS PAGE
I NT E N T ION A L L Y
LEFT
BLANK
CHAPTER 3
LIST OF EFFECTIVE PAGES
03 - Effective Pages
03 LEP - Page 1
(Rev 18) 21 NOV 2016
3.1-28
07 Mar 2016
1
21 Nov 2016
3.1-29
07 Mar 2016
2
21 Nov 2016
3.1-30
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3.1-31
21 Nov 2016
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21 Nov 2016
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21 Nov 2016
03 - Contents
ToC 3-1
07 Mar 2016
3.1-34
21 Nov 2016
ToC 3-2
07 Mar 2016
3.1-35
21 Nov 2016
ToC 3-3
21 Nov 2016
3.1-36
21 Nov 2016
ToC 3-4
21 Nov 2016
3.1-37
07 Mar 2016
ToC 3-5
30 Jan 2015
3.1-38
07 Mar 2016
ToC 3-6
30 Jan 2015
3.1-39
07 Mar 2016
3.1-40
07 Mar 2016
3.1-41
07 Mar 2016
Chapter 3
3.0-1
30 Jan 2015
3.1-42
07 Mar 2016
3.0-2
30 Jan 2015
3.1-43
07 Mar 2016
3.1-1
30 Jan 2015
3.1-44
07 Mar 2016
3.1-2
07 Mar 2016
3.1-45
07 Mar 2016
3.1-3
07 Mar 2016
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07 Mar 2016
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07 Mar 2016
3.1-5
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07 Mar 2016
3.1-6
07 Mar 2016
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07 Mar 2016
3.1-7
07 Mar 2016
3.1-50
21 Nov 2016
3.1-8
07 Mar 2016
3.1-51
07 Mar 2016
3.1-9
07 Mar 2016
3.1-52
07 Mar 2016
3.1-10
07 Mar 2016
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07 Mar 2016
3.1-11
07 Mar 2016
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07 Mar 2016
3.1-12
07 Mar 2016
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07 Mar 2016
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21 Nov 2016
3.1-56
07 Mar 2016
3.1-14
07 Mar 2016
3.1-57
07 Mar 2016
3.1-15
07 Mar 2016
3.1-58
07 Mar 2016
3.1-16
07 Mar 2016
3.1-59
07 Mar 2016
3.1-17
07 Mar 2016
3.1-60
07 Mar 2016
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07 Mar 2016
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07 Mar 2016
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07 Mar 2016
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07 Mar 2016
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07 Mar 2016
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07 Mar 2016
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21 Nov 2016
3.1-64
07 Mar 2016
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07 Mar 2016
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21 Nov 2016
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21 Nov 2016
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07 Mar 2016
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21 Nov 2016
3.1-26
07 Mar 2016
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21 Nov 2016
3.1-27
07 Mar 2016
3.1-70
21 Nov 2016
AOM DASH 8-Q400
DOT
03 LEP - Page 2
(Rev 18) 21 NOV 2016
CHAPTER 3
LIST OF EFFECTIVE PAGES
3.1-71
21 Nov 2016
3.4-7
27 May 2015
3.1-72
07 Mar 2016
3.4-8
27 May 2015
3.1-73
07 Mar 2016
3.4-9
27 May 2015
3.1-74
07 Mar 2016
3.4-10
27 May 2015
3.1-75
07 Mar 2016
3.4-11
27 May 2015
3.1-76
07 Mar 2016
3.4-12
27 May 2015
3.2-1
30 Jan 2015
3.4-13
27 May 2015
3.2-2
30 Jan 2015
3.4-14
30 Jan 2015
3.2-3
30 Jan 2015
3.4-15
30 Jan 2015
3.2-4
30 Jan 2015
3.4-16
30 Oct 2015
3.2-5
30 Jan 2015
3.4-17
30 Oct 2015
3.2-6
30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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21 Nov 2016
3.2-20
30 Jan 2015
3.2-21
30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
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30 Jan 2015
3.3-1
30 Jan 2015
3.3-2
30 Jan 2015
3.3-3
21 Nov 2016
3.3-4
30 Jan 2015
3.3-5
30 Jan 2015
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30 Jan 2015
3.4.1
30 Jan 2015
3.4-2
30 Jan 2015
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30 Jan 2015
3.4-4
30 Jan 2015
3.4-5
30 Jan 2015
3.4-6
30 Jan 2015
DOT
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ToC 3-1
[Rev. 16] 7 MAR 2016
- TABLE OF CONTENTS 3.0
NON-NORMAL, SPECIAL and SUPPLEMENTAL PROCEDURES ..................................... 3.0-1
3.0.1
Introduction ............................................................................................................................. 3.0-1
3.1
EXPANDED EMERGENCY and ABNORMAL PROCEDURES CHECKLISTS .................... 3.1-1
3.1.1
AIR CONDITIONING, PRESSURIZATION and PNEUMATICS ............................................ 3.1-1
3.1.1.1
RAPID DEPRESURIZATION / EMERGENCY DESCENT ..................................................... 3.1-1
3.1.1.2
UNPRESSURIZED FLIGHT (Bleeds ON) .............................................................................. 3.1-1
3.1.1.3
RAM VENTILATION (Bleeds OFF) ......................................................................................... 3.1-2
3.1.1.4
FUSELAGE DOORS (Warning Light) ..................................................................................... 3.1-2
3.1.1.5
INTERNAL BAGGAGE DOOR UNLOCKED .......................................................................... 3.1-3
3.1.1.6
FAILURE OF REMOTE LATCH OF FLIGHT COMPARTMENT DOOR ................................. 3.1-3
3.1.1.7
EMERGENCY OPENING OF FLIGHT COMPARTMENT DOOR
(Door Jammed) ...................................................................................................................... 3.1-3
3.1.1.8
AIRSTAIR DOOR, FAILURE TO OPEN ................................................................................. 3.1-4
3.1.1.9
CABIN PRESS (Warning Light) .............................................................................................. 3.1-4
3.1.1.10
FAULT (Annunciation Light) .................................................................................................... 3.1-5
3.1.1.11
LOSS OF CABIN ALTITUDE, CABIN RATE and CABIN DIFF INDICATORS
(All Indicators at Zero) ........................................................................................................... 3.1-5
3.1.1.12
CABIN DIFFERENTIAL GREATER THAN 1.0 PSI ON APPROACH ..................................... 3.1-5
3.1.1.13
CRACKED WINDSHIELD ....................................................................................................... 3.1-5
3.1.1.14
CABIN PACK HOT or FLT COMPT PACK HOT (Caution Lights) ........................................... 3.1-5
3.1.1.15
CABIN PACK HOT and FLT COMPT PACK HOT (Caution Lights) ........................................ 3.1-6
3.1.1.16
FLT COMPT PACK HOT and CABIN DUCT HOT or
CABIN PACK HOT and FLT COMPT DUCT HOT (Caution Lights)......................................... 3.1-6
3.1.1.17
CABIN DUCT HOT or FLT COMPT DUCT HOT (Caution Lights) .......................................... 3.1-6
3.1.1.18
# 1 BLEED HOT or # 2 BLEED HOT (Caution Lights) ........................................................... 3.1-7
3.1.1.19
# 1 BLEED HOT and # 2 BLEED HOT (Caution Lights) ......................................................... 3.1-7
3.1.1.20
# 1 BLEED HOT and # 2 BLEED HOT (Caution Lights) ON TAKE-OFF ................................ 3.1-7
3.1.2
APU, ENGINES and PROPELLERS ...................................................................................... 3.1-8
3.1.2.1
ABORTED ENGINE START ................................................................................................... 3.1-8
3.1.2.2
NO STARTER CUT OUT ........................................................................................................ 3.1-8
3.1.2.3
STARTER FAILURE ON THE GROUND ................................................................................ 3.1-8
3.1.2.4
CLEARING AN ENGINE ........................................................................................................ 3.1-9
3.1.2.5
APU FIRE ............................................................................................................................... 3.1-9
3.1.2.6
POST APU AUTOMATIC SHUT-DOWN ................................................................................ 3.1-9
3.1.2.7
APU START FAILURE .......................................................................................................... 3.1-10
3.1.2.8
APU STARTER FAILURE ..................................................................................................... 3.1-10
3.1.2.9
APU (Caution Light) .............................................................................................................. 3.1-10
3.1.2.10
APU GEN WARN (Advisory Light) ........................................................................................ 3.1-10
3.1.2.11
APU BLEED AIR OVERHEAT
(FLT COMPT DUCT HOT or CABIN DUCT HOT or CABIN PACK HOT or FLT COMPT PACK HOT Caution Lights) ...................................................................................................................... 3.1-11
(cont’d on next page)
AOM DASH 8-Q400
ToC 3-2
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
- TABLE OF CONTENTS - (cont’d)
3.1.2.12
ON-GROUND EMERGENCIES ............................................................................................ 3.1-11
3.1.2.13
ENGINE AIRSTART .............................................................................................................. 3.1-12
3.1.2.14
STARTER FAILURE IN FLIGHT ........................................................................................... 3.1-14
3.1.2.15
ABNORMAL OIL PRESSURE .............................................................................................. 3.1-14
3.1.2.16
ABNORMAL OIL TEMPERATURE IN FLIGHT
(OIL TEMPERATURE EXCEEDS 107°C).............................................................................. 3.1-15
3.1.2.17
ENGINE OIL TEMPERATURE BELOW 65°C (Propeller De-Icing ON In Flight) .................. 3.1-15
3.1.2.18
CHECK FIRE DET (Warning Light) and FAULT A or FAULT B (Advisory Light)
(Fire Detector Loop Failure) ................................................................................................. 3.1-16
3.1.2.19
CHECK FIRE DET (Warning Light) and BTL LOW (Advisory Light)
(Fire Bottle Pressure Low) ................................................................................................... 3.1-16
3.1.2.20
# 1 ENG FADEC FAIL or # 2 ENG FADEC FAIL (Warning Light) ......................................... 3.1-16
3.1.2.21
# 1 ENG FADEC or # 2 ENG FADEC (Caution Light) ........................................................... 3.1-16
3.1.2.22
POWERPLANT (ED Advisory) .............................................................................................. 3.1-16
3.1.2.23
PROPELLER OVERSPEED ................................................................................................. 3.1-17
3.1.2.24
DUAL PROPELLER OVERSPEED
(Both Propellers increase above 1020 RPM and
# 1 PEC and # 2 PEC Caution Lights illuminate)................................................................... 3.1-18
3.1.2.25
# 1 PEC or # 2 PEC (Caution Light) ...................................................................................... 3.1-19
3.1.2.26
UNSCHEDULED PROPELLER FEATHERING .................................................................... 3.1-19
3.1.2.27
PROPELLER GROUND RANGE ADVISORY LIGHT CYCLING .......................................... 3.1-19
3.1.2.28
ENGINE FAIL / FIRE / SHUT-DOWN (In Flight) ................................................................... 3.1-20
3.1.2.29
ENGINE FAILURE ON APPROACH GO-AROUND ............................................................. 3.1-22
3.1.3
AUTOFLIGHT - FLIGHT INSTRUMENTS and NAVIGATION .............................................. 3.1-23
3.1.3.1
MISTRIM [TRIM NOSE UP or TRIM NOSE DN or
TRIM L WING DN or TRIM R WING DN] (Message on PFD)................................................ 3.1-23
3.1.3.2
AP PITCH TRIM FAIL (Message on PFD) ............................................................................ 3.1-23
3.1.3.3
AUTO TRIM FAIL (Message on PFD) ................................................................................... 3.1-23
3.1.3.4
AP DISENGAGED or AP / YD DISENGAGED
(Flashing PFD Message and Red AP DISENG Light)
3.1.3.5
........................................................ 3.1-23
YD DISENGAGED (Flashing PFD Message) ....................................................................... 3.1-24
3.1.3.6
AFCS CONTROLLER INOP (Message on PFD) .................................................................. 3.1-24
3.1.3.7
AFCS FAIL (Message on PFD) ............................................................................................. 3.1-24
3.1.3.8
L FD FAIL or R FD FAIL (Message on PFD) ......................................................................... 3.1-25
3.1.3.9
YD NOT CENTERED (Message on PFD) ............................................................................. 3.1-25
3.1.3.10
HDG FAIL (Message on affected PFD) ................................................................................. 3.1-25
3.1.3.11
ATT FAIL (Messages on PFD) .............................................................................................. 3.1-26
3.1.3.12
PITCH MISMATCH or ROLL MISMATCH (Messages on PFD) ............................................ 3.1-26
3.1.3.13
IAS FAIL and / or ALT FAIL (Messages on PFD) .................................................................. 3.1-26
3.1.3.14
PRIMARY FLIGHT DISPLAY FAILURE ................................................................................ 3.1-27
3.1.3.15
MULTIFUNCTION DISPLAY FAILURE ................................................................................. 3.1-27
3.1.3.16
ENGINE DISPLAY FAILURE ................................................................................................ 3.1-27
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ToC 3-3
[Rev. 18] 21 NOV 2016
- TABLE OF CONTENTS - (cont’d)
3.1.3.17
CHECK ED (Message on ED) .............................................................................................. 3.1-27
3.1.3.18
CHECK PFD 1 or CHECK PFD 2 (Message on PFD) .......................................................... 3.1-27
3.1.3.19
HOT DISPLAYS or FANS FAIL (Message on ED - In Flight) ................................................ 3.1-28
3.1.3.20
ENGINE DISPLAY ADVISORIES ......................................................................................... 3.1-28
3.1.3.21
AIR DATA SYSTEM FAILURE (Loss of both AIRSPEED and
both ALTITUDE INDICATIONS on PILOT'S and CO-PILOT'S PFD)..................................... 3.1-29
3.1.3.22
LOSS OF PILOT, CO-PILOT and STANDBY AIRSPEED and
ALTITUDE INDICATIONS .................................................................................................... 3.1-29
3.1.3.23
ALT MISMATCH (Message on PFD) .................................................................................... 3.1-30
3.1.3.24
IAS MISMATCH (Message on PFD) ..................................................................................... 3.1-30
3.1.3.25
FLIGHT DATA RECORDER (Caution Light) ......................................................................... 3.1-30
3.1.3.26
GPWS (Caution Light) .......................................................................................................... 3.1-30
3.1.4
FUSELAGE FIRE, SMOKE or FUMES ................................................................................ 3.1-31
3.1.4.1
FUSELAGE FIRE, SMOKE or FUMES EMERGENCIES ..................................................... 3.1-31
3.1.4.1.1
General Procedures ............................................................................................................. 3.1-31
3.1.4.1.2
Known Source of Fire, Smoke or Fumes .............................................................................. 3.1-32
3.1.4.1.3
Unknown Source of Fire, Smoke or Fumes .......................................................................... 3.1-34
3.1.4.1.4
Smoke or Fumes Removal (Unknown Source) .................................................................... 3.1-36
3.1.5
EMERGENCY LANDING / DITCHING, FORCED LANDING, EMERGENCY EVACUATION 3.1-36
3.1.5.1
EMERGENCY LANDING (Both Engines Operating) ............................................................ 3.1-36
3.1.5.2
FORCED LANDING (Both Engines Inoperative) .................................................................. 3.1-39
3.1.5.3
DITCHING ............................................................................................................................ 3.1-41
3.1.6
ELECTRICAL SYSTEMS ..................................................................................................... 3.1-43
3.1.6.1
BATTERY ............................................................................................................................. 3.1-43
3.1.6.2
BUS ...................................................................................................................................... 3.1-43
3.1.6.3
LOSS OF GENERATED POWER ........................................................................................ 3.1-46
3.1.7
FLIGHT CONTROLS ............................................................................................................ 3.1-49
3.1.7.1
ROLL .................................................................................................................................... 3.1-49
3.1.7.2
PITCH ................................................................................................................................... 3.1-53
3.1.7.3
FLAPS .................................................................................................................................. 3.1-55
3.1.7.4
RUDDERS ............................................................................................................................ 3.1-57
3.1.8
FUEL SYSTEM .................................................................................................................... 3.1-59
3.1.8.1
# 1 TANK FUEL LOW or # 2 TANK FUEL LOW (Caution Light) .......................................... 3.1-59
3.1.8.2
# 1 ENG FUEL PRESS or # 2 ENG FUEL PRESS (Caution Light) ...................................... 3.1-59
3.1.8.3
ABNORMAL FUEL TEMPERATURE ................................................................................... 3.1-60
3.1.8.4
ABNORMAL FUEL TANK TEMPERATURE ......................................................................... 3.1-60
3.1.8.5
FUEL TRANSFER FAILURE ................................................................................................ 3.1-60
3.1.8.6
# 1 FUEL FLTR BYPASS or # 2 FUEL FLTR BYPASS (Caution Light) ................................ 3.1-60
3.1.8.7
FUELING ON (Caution Light) ............................................................................................... 3.1-60
(cont’d on next page)
AOM DASH 8-Q400
ToC 3-4
[Rev. 18] 21 NOV 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
- TABLE OF CONTENTS - (cont’d)
3.1.9
HYDRAULIC POWER .......................................................................................................... 3.1-61
3.1.9.1
# 1 AND # 2 HYDRAULIC SYSTEMS FAILURE ................................................................... 3.1-61
3.1.9.2
# 1 HYDRAULIC SYSTEM FAILURE
(# 1 ENG HYD PUMP and # 1 HYD ISO VLV - Caution Lights) .......................................... 3.1-62
3.1.9.3
# 2 HYDRAULIC SYSTEM FAILURE
(# 2 ENG HYD PUMP and # 2 HYD ISO VLV - Caution Lights) .......................................... 3.1-63
3.1.9.4
# 1 HYDRAULIC SYSTEM QUANTITY BELOW NORMAL
(# 1 HYD ISO VLV - Caution Light) ...................................................................................... 3.1-64
3.1.9.5
# 1 ENG HYD PUMP (Caution Light) .................................................................................... 3.1-64
3.1.9.6
# 2 HYDRAULIC SYSTEM QUANTITY BELOW NORMAL
(# 2 HYD ISO VLV - Caution Light) ...................................................................................... 3.1-65
3.1.9.7
# 2 ENG HYD PUMP (Caution Light) .................................................................................... 3.1-65
3.1.9.8
# 1 HYD FLUID HOT or # 2 HYD FLUID HOT (Caution Light) ............................................. 3.1-66
3.1.9.9
# 1 STBY HYD PUMP HOT (Caution Light) .......................................................................... 3.1-66
3.1.9.10
# 3 HYD PUMP (Caution Light) ............................................................................................. 3.1-66
3.1.9.11
PTU FAILURE
[with MS 4-126425 or MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated] .... 3.1-66
3.1.10
ICE and RAIN PROTECTION ............................................................................................... 3.1-67
3.1.10.1
DEICE PRESS (Caution Light) ............................................................................................. 3.1-67
3.1.10.2
ENGINE INTAKE BOOT FAILURE ....................................................................................... 3.1-68
3.1.10.3
DEICE TIMER (Caution Light) .............................................................................................. 3.1-68
3.1.10.4
PROP DEICE (Caution Light) ............................................................................................... 3.1-69
3.1.10.5
WSHLD HOT (Caution Light) ................................................................................................ 3.1-69
3.1.10.6
SIDE WDO HOT (Caution Light) ........................................................................................... 3.1-69
3.1.10.7
WSHLD CTRL (Caution Light) .............................................................................................. 3.1-70
3.1.10.8
WINDSHIELD WIPER SWITCH FAILURE ............................................................................ 3.1-70
3.1.10.9
ICE DETECT FAIL (Caution Light) ........................................................................................ 3.1-70
3.1.10.10
ENG ADPT HEAT 1 or ENG ADPT HEAT 2 (Caution Light) ................................................. 3.1-70
3.1.10.11
ENGINE OIL TEMPERATURE BELOW 65°C (Propeller De-Icing ON In Flight) .................. 3.1-70
3.1.10.12
PITOT HEAT 1 or PITOT HEAT 2 or PITOT HEAT STBY (Caution Light) ............................ 3.1-70
3.1.10.13
# 1 STALL SYST FAIL or # 2 STALL SYST FAIL and PUSHER SYST FAIL (Caution Lights) 3.1-70
3.1.10.14
PUSHER SYST FAIL (Caution Light) .................................................................................... 3.1-71
3.1.10.15
FLIGHT IN SEVERE ICING .................................................................................................. 3.1-71
3.1.11
LANDING GEAR .................................................................................................................. 3.1-72
3.1.11.1
ALTERNATE LANDING GEAR EXTENSION or LDG GEAR INOP (Caution Light) ............. 3.1-72
3.1.11.2
LANDING GEAR DOOR MALFUNCTIONS .......................................................................... 3.1-73
3.1.11.3
ALL LANDING GEAR FAIL TO RETRACT ........................................................................... 3.1-74
3.1.11.4
LANDING GEAR INDICATOR MALFUNCTION ................................................................... 3.1-74
3.1.11.5
NOSEWHEEL STEERING (Caution Light) ........................................................................... 3.1-75
3.1.11.6
TOUCHED RUNWAY (Warning Light) .................................................................................. 3.1-76
3.1.11.7
INBD ANTI-SKID and / or OUTBD ANTI-SKID (Caution Light) ............................................. 3.1-76
3.1.11.8
WT ON WHEELS (Caution Light) ......................................................................................... 3.1-76
(cont’d on next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ToC 3-5
[Rev. 13] 30 JAN 2015
- TABLE OF CONTENTS - (cont’d)
3.2
MISCELLANEOUS ABNORMAL and EMERGENCY PROCEDURES ................................. 3.2-1
3.2.1
Ground Failures / Aborted Take-off ......................................................................................... 3.2-1
3.2.2
Evacuation .............................................................................................................................. 3.2-3
3.2.3
Blocked Exit Procedure .......................................................................................................... 3.2-3
3.2.4
Crew Incapacitation ................................................................................................................ 3.2-4
3.2.5
In-Flight Failures ..................................................................................................................... 3.2-4
3.2.6
Propeller Overspeed and Unscheduled Feathering .............................................................. 3.2-10
3.2.7
Flapless Approach and Landing ........................................................................................... 3.2-12
3.2.8
Control Jams ........................................................................................................................ 3.2-13
3.2.9
Smoke / Depressurization / Emergency Descent ................................................................. 3.2-14
3.2.10
High Angle of Attack Recovery Procedures .......................................................................... 3.2-17
3.2.11
Overweight Landing .............................................................................................................. 3.2-17
3.2.12
Enhanced Ground Proximity Warning System (EGPWS) - Honeywell MK V ....................... 3.2-18
3.2.13
Traffic Alert & Collision Avoidance System (TCAS) .............................................................. 3.2-20
3.2.14
Flight Management System (FMS) ....................................................................................... 3.2-20
3.2.15
Operation With One Inoperative Stall Warning and / or Stick Pusher System ...................... 3.2-21
3.2.16
Operation with Inoperative Nosewheel Steering System ...................................................... 3.2-22
3.2.17
Operation with Inoperative Anti-Skid Brake Control System ................................................ 3.2-23
3.2.18
Operation with Inoperative Flight Spoilers in Ground Mode ................................................. 3.2-24
3.2.19
Operation with Landing Gear Extended ............................................................................... 3.2-25
3.3
ADVERSE WEATHER CONDITIONS .................................................................................... 3.3-1
3.3.1
General ................................................................................................................................... 3.3-1
3.3.2
Windshear .............................................................................................................................. 3.3-1
3.3.3
Turbulence .............................................................................................................................. 3.3-4
3.3.4
Wake Turbulence .................................................................................................................... 3.3-5
3.3.5
Volcanic Ash ........................................................................................................................... 3.3-6
(cont’d on next page)
AOM DASH 8-Q400
ToC 3-6
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
- TABLE OF CONTENTS - (cont’d)
3.4
SPECIAL PROCEDURES ...................................................................................................... 3.4-1
3.4.1
FLIGHT TEST PROCEDURES ............................................................................................... 3.4-1
3.4.1.1
Introduction ............................................................................................................................. 3.4-1
3.4.1.2
General ................................................................................................................................... 3.4-1
3.4.1.3
Aileron Trim Flight Test Procedures ........................................................................................ 3.4-1
3.4.2
SUPPLEMENTAL PROCEDURES ........................................................................................ 3.4-2
3.4.2.1
Introduction ............................................................................................................................. 3.4-2
3.4.2.2
General ................................................................................................................................... 3.4-2
3.4.2.3
Air Conditioning, Pressurization and Pneumatics ................................................................... 3.4-2
3.4.2.4
APU, Engines and Propellers .................................................................................................. 3.4-4
3.4.2.5
Autoflight, Flight Instruments and Navigation .......................................................................... 3.4-6
3.4.2.6
Electrical .................................................................................................................................. 3.4-9
3.4.2.7
Flight Controls ....................................................................................................................... 3.4-10
3.4.2.8
Hydraulic Power .................................................................................................................... 3.4-12
3.4.2.9
Ice and Rain Protection / Stall Protection .............................................................................. 3.4-13
3.4.2.10
Landing Gear ........................................................................................................................ 3.4-14
3.4.2.11
Single Engine Taxi Operations .............................................................................................. 3.4-15
3.4.2.11.1
General ................................................................................................................................. 3.4-15
3.4.2.11.2
Operational Considerations ................................................................................................... 3.4-15
3.4.2.11.3
Engine and Propeller Ground Operating Limitations ............................................................. 3.4-16
3.4.2.11.4
Normal Procedures ............................................................................................................... 3.4-16
3.4.2.11.5
Abnormal Procedures ........................................................................................................... 3.4-17
3.4.3
SAFETY OF FLIGHT SUPPLEMENT, ABNORMAL and EMERGENCY CHECKLISTS .... 3.4-18
3.4.3.1
Introduction ........................................................................................................................... 3.4-18
3.4.3.2
Abnormal / Emergency Checklist Guidlines .......................................................................... 3.4-18
3.4.3.3
Troubleshooting .................................................................................................................... 3.4-19
3.4.3.4
Abnormal Contaminated Runway Operations ....................................................................... 3.4-19
3.4.3.5
Landing Gear Failures ........................................................................................................... 3.4-20
Normal Extension / Retraction
Alternate Extension
Nose Gear - UP, Main Gear - DOWN and LOCKED
All Gear - UP
One Main Gear - UP, Nose Gear and Opposite Main Gear - DOWN and LOCKED
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.0-1
[Rev. 13] 30 JAN 2015
3.0
NON-NORMAL, SPECIAL AND SUPPLEMENTAL PROCEDURES
3.0.1
Introduction
3.0.1.1
General Use of Expanded Emergency and Abnormal Procedures (Non-Normal) Checklists
The Expanded Emergency and Abnormal Procedures (Non-Normal) checklists are intended to be used in conjunction with the QRH Abnormal Checklist and the AFM.
Each non-normal situation should be dealt with in the following sequence:
1.
Memory items, enclosed in a BOX;
2.
Checklist items specific to the malfunction;
3.
Warnings, Cautions and Notes (lost services, etc.); and
4.
Landing Precautions.
This information is specific to the malfunction and is used to supplement the normal operations of the airplane. The landing precautions must be reviewed as part of the approach briefing.
Following completion of the appropriate Non-Normal Checklist, the Normal Checklist will be used giving due
regard to those items modified by the abnormality for the remainder of the flight.
NOTE:
For failures not addressed in the Non-Normal Checklist, refer to the AFM.
− The statement “Land immediately at the nearest suitable airport” is defined as:
Land at the nearest airport that offers sufficient landing distance available and if required, emergency
services to support the emergency or abnormality.
− The statement “Land at the nearest suitable airport” is defined as:
The airplane may continue to the destination airport or the nearest airport where maintenance services are
available.
− The statement “Maintenance action required prior to next flight” is defined as:
“Next Flight” is referring to the immediate or imminent take-off after discovery.
3.0.1.2
Crew Coordination during Emergencies
In the event of a non-normal situation, the primary objective of the flight crew is to control the airplane.
The crew will assess the problem, when vertical and lateral flight path control is established and ground contact
is no longer a threat.
Once the nature of the problem has been established, the PF will call for the appropriate memory items if applicable.
The PNF actions the memory items which are confirmed by the PF.
When the memory items are complete, the PF will call for the appropriate non-normal checklist.
The PNF actions the checklist items using the “read and do” method.
AOM DASH 8-Q400
3.0-2
[Rev. 13] 30 JAN 2015
3.0.1.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Communication Flight Compartment and Cabin Crew
The PF will normally handle all communications with the cabin crew.
For normal communication use the CALL button to contact the cabin crew.
The Senior Cabin Crew Member will come to the flight compartment or respond on the interphone.
During emergency situations, standardized communication between the Pilots and the Cabin Crew Member(s)
is essential.
The following is a list of the standard communications to be used during emergency operations.
Table 3.0-1 Pilot / Cabin Crew Communications
Action Required
Signal
Notify cabin crew of an emergency
PA:
“SENIOR CABIN ATTENDANT TO THE FLIGHT DECK”
Alternate: Emergency Lights ON
Evacuate airplane
PA: EVACUATE LEFT (or RIGHT) SIDE”
Alternate: More than 3 Chimes.
Passengers to brace prior to an emergency land- PA: “BRACE BRACE BRACE"
ing (this call should be made approximately 1 min
Alternate: More than 3 Chimes.
prior to landing)
Cabin Crew Members to resume duties after an PA: "CABIN CREW RESUME YOUR DUTIES"
emergency descent
Prevent evacuation
3.0.1.4
PA: "REMAIN SEATED"
Distress Communication and Alerting ATC to Emergencies
Do Not hesitate to send “MAYDAY” calls as early as posssible to give the ground staff as much time as possible for their preparations.
A “MAYDAY” call can always be cancelled.
In your transmission give a technical status of the airplane or type of emergency, Position, FL, Heading, Endurance and Intentions.
Make clear requests.
3.0.1.5
Guidance for Diversion in Case of Serious Technical Failure
Especially in case of a serious technical failure, to conduct a safe landing must always be the highest priority.
Furthermore the following has to be taken into consideration:
•
Technical condition of the airplane, actual grossmass, endurance
•
Weather conditions and terrain enroute and at alternate
•
Aerodrome facilities
•
Passenger and maintenance facilities
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-1
[Rev. 13] 30 JAN 2015
3.1
EXPANDED EMERGENCY and ABNORMAL PROCEDURES CHECKLISTS
3.1.1
AIR CONDITIONING, PRESSURIZATION and PNEUMATICS
3.1.1.1
RAPID DEPRESSURIZATION / EMERGENCY DESCENT
Oxygen Masks ................................................................................................................................. ON / 100%
• Remove headset.
• Remove quick donning oxygen mask from the quick release holder and put it over nose and mouth.
• Set oxygen to 100%.
• Breathe normally to start oxygen flow.
• Put headset back on.
MIC Switch ................................................................................................................................................ Mask
Set BOOM / MASK switch to MASK and check communications.
Passenger Signs ......................................................................................................................................... ON
• Set FASTEN BELTS SIGN switch to FASTEN BELTS.
• Set NO SMOKING SIGN switch to NO SMOKING.
EMERGENCY DESCENT .............................................................................................. Accomplish As Req’d
POWER Levers ............................................................................................................................ FLIGHT IDLE
Move POWER Levers to FLIGHT IDLE.
Condition Levers ....................................................................................................................................... MAX
Move Condition Levers to MAX / 1020.
Airspeed ...................................................................................................................................................... VMO
Increase airspeed to Maximum Operating Speed (VMO) Pointer.
If an immediate descent to an altitude where oxygen is not required cannot be conducted;
within 5 min of donning oxygen masks:
Oxygen Masks ........................................................................................................................................ NORM
NOTE:
If structural integrity is in doubt, limit airspeed as much as possible and avoid high
maneuvering loads.
[END]
3.1.1.2
UNPRESSURIZED FLIGHT
(Bleeds ON)
AUTO / MAN / DUMP .............................................................................................................................. DUMP
Move the REAR OUTFLOW VALVE CONTROL switch to the DUMP position.
BLEED 1 and 2 .................................................................................................................................. ON / MAX
• Set BLEED control switches to 1 and 2.
• Turn BLEED airflow control rotary switch fully clockwise to MAX.
Oxygen Masks ................................................................................................................................... As Req’d
If above 14000 ft, put on oxygen masks and set oxygen to 100%.
• Remove headset.
• Remove quick donning oxygen mask from the quick release holder and put it over nose and mouth.
• Set oxygen to 100%.
• Breathe normally to start oxygen flow.
• Put headset back on.
-
For flight with bleed air supply selected off, use RAM VENTILATION (Sub-Chapter 3.1.1.3).
[END]
AOM DASH 8-Q400
3.1-2
[Rev. 16] 7 MAR 2016
3.1.1.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
RAM VENTILATION (Bleeds OFF)
RECIRC Fan [with MS 4-126236 Not Incorporated] ................................................................................... OFF
Set RECIRC Fan switch to OFF.
BLEED 1 and 2 .................................................................................................................................. MIN / OFF
•
Turn BLEED airflow control rotary switch fully counter-clockwise to the MIN position.
•
Set BLEED control 1 and 2 switches to OFF.
AUTO / MAN / DUMP ................................................................................................................................. MAN
Move the REAR OUTFLOW VALVE CONTROL switch to the MAN position.
MAN DIFF ....................................................................................................................................... INCR (50 s)
Hold the MAN DIFF switch to the INCR position for 50 s.
CABIN ALTITUDE FWD OUTFLOW ........................................................................... Fully Clockwise (OPN)
Turn CABIN ALTITUDE FWD OUTFLOW rotary switch fully clockwise to OPN.
FWD OUTFLOW VALVE ........................................................................................................................... Open
Turn FWD OUTFLOW VALVE lever clockwise to OPEN.
NOTE:
Ram ventilation is most effective above 150 KIAS.
[END]
3.1.1.4
FUSELAGE DOORS
(Warning Light)
ON THE GROUND
-
Confirm affected door on DOORS page of MFD.
NOTE:
-
A failed condition may also exist where NO unsafe DOOR is indicated on the DOORS page of
the MFD.
Inspect and secure affected door.
FUSELAGE DOORS warning light remains illuminated:
-
Maintenance action required prior to flight.
IN FLIGHT
FASTEN BELTS and NO SMOKING Switches ....................................... FASTEN BELTS and NO SMOKING
-
Confirm affected door on DOORS page of MFD
NOTE:
A failed condition may also exist where NO unsafe DOOR is indicated on the DOORS page of
the MFD.
If pressurized:
-
Confirm normal pressure differential, cabin altitude and rate are indicated on the CABIN indicator.
With normal pressurization confirmed:
FASTEN BELTS and NO SMOKING Switches .................................................................................. As Req’d
-
Land at the nearest suitable airport.
If there is a loss of pressurization or operating unpressurized and the security of the affected door cannot be
confirmed or the operating handle of the affected door is not in the closed position:
WARNING: Do Not attempt to secure affected door.
-
Land immediately at the nearest suitable airport.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.1.5
3.1-3
[Rev. 16] 7 MAR 2016
INTERNAL BAGGAGE DOOR UNLOCKED
[with Options - CR 825 SO 90485 and CR 825 CH 03262 Not Incorporated]
(Illumination of INTERNAL BAGG DOOR Caution Light or
[with MS 4-309221 or MS 4-309218 Incorporated],
INTERNAL DOORS Caution and BAGG DOOR Advisory Lights)
IN FLIGHT or ON THE GROUND
Internal Baggage Door ............................................................................................................ Check / Secure
Confirm INTERNAL BAGG DOOR caution light out, or
[with MS 4-309221 or MS 4-309218 Incorporated]
confirm INTERNAL DOORS caution and BAGG DOOR advisory lights out.
[END]
3.1.1.6
FAILURE OF REMOTE LATCH ON FLIGHT COMPARTMENT DOOR
[with MS 4-309218 or MS 4-309221 Incorporated]
(Illumination of INTERNAL DOORS Caution and INTERNAL DOORS FAIL Advisory Lights)
[with Options - CR 825 SO 90485 and CR 825 CH 03262 Incorporated]
(Illumination of COCKPIT DOOR Caution and INTERNAL DOORS FAIL Advisory Lights)
Lower Deadbolt Latch ............................................................................................................................ Rotate
to mechanically secure the door
LOCK ISOLATE Switch ........................................................................................................................... Press
Check LOCK ISOLATE switch advisory light illuminates.
[END]
3.1.1.7
EMERGENCY OPENING OF FLIGHT COMPARTMENT DOOR
(Door Jammed)
[with MS 4 - 309209 or MS 4 - 309218 or MS 4-309219 Incorporated]
•
Unlock and push or step down on bottom hinge pin.
•
Unlock and pull down upper hinge pin.
•
Unlock and lift middle hinge pin.
•
Push flight compartment door at hinge side.
NOTE:
•
It may require a large force to open the flight compartment door.
Rotate the flight compartment door counter-clockwise and stow against the lavatory.
NOTE:
Upon forcing the flight compartment door open, it may fall straight aft and lay flat on the cabin
floor.
[END]
AOM DASH 8-Q400
3.1-4
[Rev. 16] 7 MAR 2016
3.1.1.8
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
AIRSTAIR DOOR, FAILURE TO OPEN
[with MS 4-126512 or MS 4-126513 or MS 4-123564 Not Incorporated]
With aircraft electrical power on:
AIRSTAIR DOOR SOV CB (Left Lower CB Panel - E1) .............................................................................. Pull
NOTE:
The airstair door failure to open may be associated with a failure of IOM 1 or IOM 2.
Airstair Door ............................................................................................................................................. Open
If airstair door remains inoperative:
BATTERY MASTER Switch ....................................................................................................................... OFF
Airstair Door ............................................................................................................................................. Open
-
If airstair door remains inoperative, exit via the Aft Passenger Access door.
[END]
3.1.1.9
CABIN PRESS
(Warning Light)
CAB ALT Indicator .................................................................................................................................. Check
Check CABIN ALTITUDE indicator, to confirm cabin altitude is more than 8000 ft.
BLEED 1 and 2 .................................................................................................................................. ON / MAX
•
Set BLEED CONTROL 1 and 2 switches to 1 and 2.
•
Turn BLEED AIR FLOW CONTROL rotary switch fully clockwise to MAX.
CABIN PACK and FLT COMP PACK Switches ...................................................................................... AUTO
Set CABIN and FLIGHT COMP PACK CONTROL switches to AUTO.
AUTO / MAN / DUMP ............................................................................................................................... AUTO
Move the REAR OUTFLOW VALVE CONTROL switch to the AUTO position.
CABIN ALTITUDE FWD OUTFLOW .......................................................... Fully Counter-Clockwise (CLSD)
Turn CABIN ALTITUDE FWD OUTFLOW rotary switch fully counter-clockwise to CLSD.
FWD OUTFLOW Valve Lever ................................................................................................................ NORM
Turn FWD OUTFLOW VALVE lever counter-clockwise to NORMAL.
If cabin altitude is NOT decreasing:
AUTO / MAN / DUMP ................................................................................................................................. MAN
Move the REAR OUTFLOW VALVE CONTROL switch to the MAN position.
MAN DIFF ........................................................................................................................................... As Req’d
Use Cabin Altitude differential placard to achieve appropriate cabin altitude (5.46 psid maximum).
NOTE:
Maximum altitude in manual mode is 25000 ft.
If cabin altitude is not decreasing:
Descend ................................................................................................................................ to below 14000 ft
Descend to below 14000 ft as soon as possible (see UNPRESSURIZED FLIGHT in Sub-Chapter 3.1.1.2).
If control of cabin altitude is regained:
Prior to landing:
BLEED 1 and 2 .................................................................................................................................. MIN / OFF
•
Turn BLEED AIR FLOW CONTROL rotary switch fully counter-clockwise to the MIN position.
•
Set BLEED CONTROL 1 and 2 switches to OFF.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.1.10
3.1-5
[Rev. 16] 7 MAR 2016
FAULT (Annunciation Light)
(Alternate Mode Pressurization)
AUTO / MAN / DUMP ................................................................................................................................. MAN
MAN DIFF .................................................................................................................. INCR / DECR (As Req’d)
Use Cabin Altitude Differential placard to achieve appropriate cabin altitude.
NOTE:
Maximum altitude in manual mode is 25000 ft.
Prior to landing:
BLEED 1 and 2 Switches ........................................................................................................................... OFF
[END]
3.1.1.11
LOSS OF CABIN ALTITUDE, CABIN RATE and CABIN DIFF INDICATORS
(All Indicators at Zero)
Descend ................................................................................................................................ to below 14000 ft
AUTO / MAN / DUMP ................................................................................................................................. MAN
MAN DIFF ................................................................................................................................................. DECR
-
See UNPRESSURIZED FLIGHT in Sub-Chapter 3.1.1.2.
[END]
3.1.1.12
CABIN DIFFERENTIAL GREATER THAN 1.0 PSI ON APPROACH
CABIN ALTITUDE FWD OUTFLOW ............................................................................ Fully Clockwise (OPN)
NOTE:
-
If cabin differential does not decrease, assume indication failure.
Prior to landing, refer to procedure RAM VENTILATION in Sub-Chapter 3.1.1.3
[END]
3.1.1.13
CRACKED WINDSHIELD
Airspeed .................................................................................................................... Reduce (210 KIAS MAX)
AUTO / MAN / DUMP ................................................................................................................................. MAN
MAN DIFF .............................................................................................................. DECR (2.5 to 3.0 psid MAX)
- Descend to below 14000 ft, if practical.
- Use MAN DIFF control to maintain 2.5 - 3.0 psid or less in descent.
Prior to landing:
BLEED 1 and 2 Switches ................................................................................................................. MIN / OFF
[END]
3.1.1.14
CABIN PACK HOT or FLT COMPT PACK HOT
(Caution Lights)
CABIN PACK or FLT COMP PACK Switches ............................................................................................ OFF
Set CABIN or FLIGHT COMP PACK CONTROL Switch to OFF
(Depending on which caution light comes on).
BLEED Selector ......................................................................................................................................... MAX
Turn BLEED AIR FLOW CONTROL rotary switch fully clockwise to MAX.
[END]
AOM DASH 8-Q400
3.1-6
[Rev. 16] 7 MAR 2016
3.1.1.15
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
CABIN PACK HOT and FLT COMPT PACK HOT
(Caution Lights)
CABIN PACK and FLT COMP PACK Switches ......................................................................................... OFF
Set CABIN and FLIGHT COMP PACK CONTROL switches to OFF.
Descend ................................................................................................................................ to below 14000 ft
Descend to below 14000 ft as soon as possible.
-
When cabin pressure differential had decreased to 0.5 psi or below,
complete RAM VENTILATION procedure in Sub-Chapter 3.1.1.3.
[END]
3.1.1.16
FLT COMPT PACK HOT and CABIN DUCT HOT or
CABIN PACK HOT and FLT COMPT DUCT HOT
(Caution Lights)
CABIN PACK and FLT COMP PACK Switches ......................................................................................... OFF
Descend ................................................................................................................................ to below 14000 ft
Descend to below 14000 ft as soon as possible.
BLEED 1 and 2 Switches .................................................................................................................. MIN / OFF
NOTE:
-
ECS pack airflow is lost and cabin will depressurize.
When cabin pressure differential had decreased to 0.5 psi or below,
complete RAM VENTILATION procedure in Sub-Chapter 3.1.1.3.
[END]
3.1.1.17
CABIN DUCT HOT or FLT COMPT DUCT HOT
(Caution Lights)
CAB DUCT / CABIN / FC DUCT Gauge ................................................................................................. Check
Confirm abnormal temperature and select CAB DUCT or FC DUCT appropriate to caution light.
CABIN PACK or FLT COMP PACK Switches ........................................................................................... OFF
Set CABIN or FLIGHT COMP PACK CONTROL switch to OFF
(Depending on which caution light comes on).
BLEED Selector ........................................................................................................................................ MAX
Turn Bleed Air Flow Control rotary switch fully clockwise to MAX.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.1.18
3.1-7
[Rev. 16] 7 MAR 2016
# 1 BLEED HOT or # 2 BLEED HOT
(Caution Lights)
BLEED Air (affected side) ........................................................................................................................... OFF
Set affected side BLEED CONTROL switch to OFF.
NOTE:
It may be necessary to monitor airplane pressurization and heating closely for the remainder
of the flight with only one bleed operating.
[END]
3.1.1.19
# 1 BLEED HOT and # 2 BLEED HOT
(Caution Lights)
BLEED 1 and 2 .................................................................................................................................. MIN / OFF
Turn Bleed Air Flow Control rotary switch fully counter-clockwise to the MIN position.
Descend ............................................................................................................................... to below 14000 ft.
Descend to below 14000 ft as soon as possible.
NOTE:
-
ECS pack airflow is lost and cabin will depressurize.
When cabin pressure differential had decreased to 0.5 psi or below,
complete RAM VENTILATION procedure in Sub-Chapter 3.1.1.3.
[END]
3.1.1.20
# 1 BLEED HOT and # 2 BLEED HOT ON TAKE-OFF
(Caution Lights)
(with BLEED 1 and BLEED 2 Switches in the OFF position)
[with MS 4-113636 Not Incorporated]
NOTE:
Conduct the following procedure during the take-off climb.
BLEED 1 and 2 Switches ............................................................................................................................ ON
After 10 s:
BLEED 1 and 2 Switches ........................................................................................................................... OFF
Check # 1 BLEED HOT and # 2 BLEED HOT caution lights out.
BLEED 1 and 2 Switches ............................................................................................................................ ON
If # 1 BLEED HOT and # 2 BLEED HOT caution lights remain illuminated:
-
Complete # 1 BLEED HOT and # 2 BLEED HOT (Caution Lights) procedure in Sub-Chapter 3.1.1.19.
[END]
AOM DASH 8-Q400
3.1-8
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2
APU, ENGINES and PROPELLERS
3.1.2.1
ABORTED ENGINE START
Condition Lever ............................................................................................................................... FUEL OFF
Move Condition Lever of affected engine to FUEL OFF.
ENGINE START SELECT Switch .............................................................................................................. OFF
Make sure SELECT and START lights on the ENGINE START switchlight go off.
-
Complete CLEARING AN ENGINE procedure (Sub-Chapter 3.1.2.4):
[END]
3.1.2.2
NO STARTER CUT OUT
(ENGINE START Light remains illuminated)
ENGINE START SELECT Switch .............................................................................................................. OFF
Check START and SELECT lights out after approximately 15 s.
DC CONTROL EXT PWR Switch (if connected) ........................................................................................ OFF
If affected DC GEN caution light out:
GEN LOAD (affected side) ....................................................................................................................... Check
If DC GEN caution light remains illuminated:
DC CONTROL GEN Switch ......................................................................................................... OFF then ON
If DC GEN caution light does not extinguish:
DC CONTROL GEN Switch (affected) ....................................................................................................... OFF
-
Maintenance Action required prior to flight.
[END]
3.1.2.3
STARTER FAILURE ON THE GROUND
(ENGINE SELECT Light remains illuminated)
MAIN, AUX and STBY BATT Switches ..................................................................................................... OFF
DC EXT PWR .............................................................................................................................................. OFF
AC EXT PWR .............................................................................................................................................. OFF
Condition Levers ............................................................................................................................. FUEL OFF
APU PWR .................................................................................................................................................... OFF
-
Carry out remaining portions of normal engine SHUT-DOWN procedure (Sub-Chapter 2.17.5.14)
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2.4
3.1-9
[Rev. 16] 7 MAR 2016
CLEARING AN ENGINE
(To Remove Internally Trapped Fuel)
Condition Lever ............................................................................................................................... FUEL OFF
Move Condition Lever of affected engine to FUEL OFF.
POWER Lever ........................................................................................................................................... DISC
Make sure POWER Lever of affected engine is at DISC.
IGNITION (affected engine) ......................................................................................................................... OFF
Set IGNITION control switch of affected engine to OFF.
START SELECT (affected engine) .......................................................................................................... Select
• Set ENGINE START SELECT switch to 1 or 2.
• Make sure the amber SELECT light on the ENGINE START switchlight illuminates.
ENGINE START Switch ........................................................................................................................... Press
Push the ENGINE START switchlight and make sure the START illuminates.
CAUTION: Observe Starter Cranking Limits.
Starter Cranking Limits
START
1
2
3
MAX Time ON
70 s
70 s
70 s
... Followed by Time OFF
2 min
2 min
30 min
After desired engine rotation complete:
START SELECT .......................................................................................................................................... OFF
• Set ENGINE START SELECT switch to OFF.
• Make sure the amber SELECT and START lights on the ENGINE START switchlight go off.
If a subsequent engine start is to be attempted:
IGNITION (affected engine) ..................................................................................................................... NORM
[END]
3.1.2.5
-
APU FIRE
(Illumination of CHECK FIRE DET Warning Light,
APU Caution Light and APU FIRE Advisory Light)
Check APU automatically shuts down (APU RUN advisory light out and APU BTL LOW, APU FUEL VALVE
CLOSED and APU FAIL advisory lights illuminate).
If APU BTL ARM or APU FIRE advisory lights remain illuminated after 7 s:
APU EXTG Switch ................................................................................................................................... Press
Pull the guard down, then push the EXTG switch.
Check APU BTL ARM and APU FIRE advisory lights out.
- Proceed with POST APU AUTOMATIC SHUT-DOWN check as follows (Sub-Chapter 3.1.2.6):
[END]
3.1.2.6
POST APU AUTOMATIC SHUT-DOWN
APU BL AIR Switch ...................................................................................................................................... Off
Push APU BL AIR switch and make sure the BL AIR OPEN advisory light goes off.
APU GEN Switch .......................................................................................................................................... Off
Push APU GEN switch and make sure the GEN ON light goes off.
APU PWR Switch .......................................................................................................................................... Off
• Make sure the APU caution light and APU FUEL VALVE OPEN advisory light go out.
• Make sure the APU FUEL VALVE CLOSED advisory light illuminates.
CAUTION: Do Not restart the APU following an automatic shut-down if
the FIRE Advisory Light is illuminated.
[END]
AOM DASH 8-Q400
3.1-10
[Rev. 16] 7 MAR 2016
3.1.2.7
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
APU START FAILURE
(APU FAIL Advisory Light illuminates and APU STARTER Advisory Light extinguishes)
APU PWR Switch ........................................................................................................................... Off then On
Push APU PWR switch off then on. Check APU FAIL advisory light out.
NOTE:
After an APU start attempt, APU Start will remain disabled for approximately 7 s
(Control Panel Advisory lights illuminate with FADEC BIT test)
APU START Switch .................................................................................................................................. Press
APU Starter Cranking Limits:
START
1
2
NOTE:
MAX Time ON
60 s
60 s
... Followed by Time OFF
5 min
Maintenance Action Required
Including the time taken for the maintenance action following the second start attempt, a
minimum of 30 min off must elapse prior to the next start attempt.
[END]
3.1.2.8
APU STARTER FAILURE
(APU START Light remains illuminated)
MAIN, AUX and STBY BATT Switches ..................................................................................................... OFF
DC CONTROL (if connected) ...................................................................................................................... OFF
AC CONTROL (if connected) ...................................................................................................................... OFF
Engine Shut-Down (if applicable) ..................................................................................................... Complete
APU Shut-Down ................................................................................................................................ Complete
[END]
3.1.2.9
APU
(Caution Light)
If APU Failure (APU FAIL advisory light illuminates):
• Confirm APU Automatic Shut-down.
• Proceed with POST APU AUTOMATIC SHUT-DOWN checklist in Sub-Chapter 3.1.2.6.
If APU GEN Overheat (AUP GEN OHT advisory light illuminates):
• Confirm Automatic Shut-down.
• Proceed with POST APU AUTOMATIC SHUT-DOWN checklist in Sub-Chapter 3.1.2.6.
[END]
3.1.2.10
APU GEN WARN
(Advisory Light)
(APU Generator failure)
APU GEN ........................................................................................................................................ Off then On
• Push APU GEN switch to off.
• Push APU GEN switch again to on.
• Make sure the APU GEN ON advisory light illuminates on and the APU GEN WARN light goes out.
If APU GEN WARN (advisory lights remain on, Generator fails to come on line):
APU GEN ...................................................................................................................................................... Off
Push APU GEN switch off.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2.11
3.1-11
[Rev. 16] 7 MAR 2016
APU BLEED AIR OVERHEAT
(FLT COMPT DUCT HOT or CABIN DUCT HOT or CABIN PACK HOT or FLT COMPT PACK HOT
Caution Lights)
APU BL AIR OPEN Switch ........................................................................................................................... Off
Check APU BL AIR OPEN advisory light out.
[END]
3.1.2.12
ON-GROUND EMERGENCIES
EMERG Brake .............................................................................................................................................. ON
Set EMERGENCY / PARKING BRAKE lever to PARK when airplane comes to a complete stop.
POWER Levers ......................................................................................................................................... DISC
Move POWER Levers 1 and 2 to FLIGHT IDLE.
Then squeeze Flight Idle Gate Triggers and move POWER Levers aft of FLIGHT IDLE gate to DISC detent.
Condition Levers ............................................................................................................................. FUEL OFF
Move Condition Levers 1 and 2 to FUEL OFF.
PULL FUEL / HYD OFF Handle (affected engine) ...................................................................................... Pull
Check FUEL VALVE CLOSED and HYD VALVE CLOSED white advisory lights illuminate.
TANK AUX PUMP (1 and 2) ........................................................................................................................ OFF
Check TANK 1 and TANK 2 AUX PUMP ON advisory lights are off.
If Fire:
EXTG Switch ...................................................................................................................................... FWD BTL
Set EXTG switch of affected engine to FWD BTL and check EXTG FWD BTL arm advisory light goes off.
Wait up to 30 s, if fire persists:
EXTG Switch ......................................................................................................................................... Aft BTL
Set EXTG switch of affected engine to AFT BTL and check EXTG AFT BTL arm advisory light goes off.
If Evacuation:
EMER LIGHTS ............................................................................................................................................... ON
Pull and set the Eemergency Lights switch to the ON position.
Make sure the PORTABLE EMERGENCY LIGHT on the flight compartment ceiling turns on.
FASTEN Seat BELTS .................................................................................................................................. OFF
Evacuate ............................................................................................................................................ As Req’d
After the airplane comes to a stop and propellers have stopped turning, the captain starts the evacuation by
using the PA to shout the command “EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE).
The 1st officer leaves the flight compartment and helps with the evacuation.
AC / DC EXT PWR and APU ....................................................................................................................... OFF
If airplane is at the gate, set AC EXT PWR or DC EXT PWR switches to OFF.
Push APU PWR switchlight off.
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
[END]
AOM DASH 8-Q400
3.1-12
[Rev. 16] 7 MAR 2016
3.1.2.13
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ENGINE AIRSTART
Engine Airstart Envelope
NOTE:
Minimum SAT for engine relight is - 40°C.
Affected Engine:
POWER Lever ............................................................................................................................. FLIGHT IDLE
Set POWER Lever of affected engine to FLIGHT IDLE.
Condition Lever ............................................................................................................................... FUEL OFF
Move Condition Lever of affected engine to FUEL OFF.
PULL FUEL / HYD OFF Handle ........................................................................................................... Push In
Push in the PULL FUEL / HYD OFF handle and
make sure the FUEL and HYD VALVES OPEN advisory lights illuminate.
IGNITION 1 or 2 ...................................................................................................................................... NORM
Set IGNITION 1 or 2 switch to NORM.
BLEED Air .................................................................................................................................................. OFF
Set BLEED switch of affected engine to OFF.
TANK AUX PUMP 1 or 2 ............................................................................................................................... ON
Push the TANK 1 or TANK 2 AUX PUMP switchlight and
make sure the green ON advisory light illuminates.
AUTOFEATHER SELECT Switchlight ........................................................................................................ Off
ALT FTHR Switchlight ................................................................................................................................. Off
MAIN BUS TIE .............................................................................................................................................. Tie
Set MAIN BUS TIE switch to MAIN BUS TIE.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-13
[Rev. 18] 21 NOV 2016
ENGINE AIRSTART (cont’d)
Conduct Normal Start:
Captain
First Officer
ENGINE START SELECT Switch ...Pull Out then Set to 1 or 2
Observes SELECT light turns on.
ENGINE START Switch .................................................. Press Starts stopwatch running to time the start
Makes sure START light illuminates.
At first indication of NH:
Sets condition lever to START & FEATHER.
NOTE: Fuel flow indication on ED is not accurate until the engine is stable at NH.
Check that engine accelerates to above 64.2% NH and ITT does not exceed 920°C.
Check ENGINE START and ENGINE START SELECT Switches off.
Make sure SELECT and START Lights go out.
For appropriate engine, make sure oil pressure is greater than 44 psi, ENG OIL PRESS Warning
Light, ENG FUEL PRESS, ENG HYD PUMP and DC GEN Caution Lights go out.
ENGINE SELECT Light will remain illuminated for approximately 15 s after ENGINE START and
SELECT Switches off.
When engine stabilizes:
Maximum Airspeed [with MS 4-113264 Not Incorporated] ............................................................... 200 KIAS
Condition Lever ................................................................................................................................. MIN / 850
When propeller RPM stabilizes:
Condition Lever ................................................................................................................................. As Req’d
CAUTION: [with MS 4-113264 Not Incorporated]: if the condition lever is advanced before propeller
RPM is stabilized, a propeller overspeed may occur.
POWER Lever .................................................................................................................................... As Req’d
Move POWER Lever to the RATING detent position, or as req'd.
Check AC GEN Caution Light .................................................................................................................... Out
DC and AC VOLTS and LOAD ................................................................................................................ Check
Check on ELECTRICAL page of MFD.
TANK AUX PUMP 1 and 2 .......................................................................................................................... OFF
Check TANK 1 and TANK 2 AUX PUMP ON advisory lights out.
STBY HYD PRESS and PTU CNTRL ................................................................................................ As Req’d
Check STBY HYD PRESS ON, PTU CNTRL ON advisory lights out and
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated], PTU pressure advisory light out.
Following an airstart of # 1 engine:
PTU CNTRL ............................................................................................................................. ON then Normal
NOTE:
Cycling the PTU CNTRL switch ensure the PTU auto logic is enabled.
PTU CNTRL ........................................................................................................................................ As Req’d
BLEED 1 and 2 ................................................................................................................................... As Req’d
•
Set BLEED 1 and BLEED 2 switches to ON, or as required.
•
Turn BLEED AIR FLOW CONTROL rotary switch to NORM, or as required.
MAIN BUS TIE ............................................................................................................................................. OFF
Set MAIN BUS TIE switch to OFF position.
[END]
AOM DASH 8-Q400
3.1-14
[Rev. 16] 7 MAR 2016
3.1.2.14
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
STARTER FAILURE IN FLIGHT
(ENGINE SELECT Light remains illuminated)
BATTERY Switches (MAIN, AUX, STBY) .................................................................................................. OFF
DC BUS TIE CONT Circuit Breaker (Right Lower CB Panel - G8) ............................................................ Pull
-
Land immediately at the nearest suitable airport.
CAUTION: Do Not connect External Power or select APU generator on shut-down.
[END]
3.1.2.15
ABNORMAL OIL PRESSURE
Low Oil Pressure
If oil pressure is between 44 and 60 psi:
POWER Lever (affected engine) ................................................................................................. FLIGHT IDLE
Move POWER Lever of affected engine to the FLIGHT IDLE position.
Condition Lever (affected engine) .................................................................................... START & FEATHER
Move Condition Lever of affected engine to START & FEATHER to reduce in-flight drag.
If propeller does not feather:
ALT FTHR Switch ..................................................................................................................................... Press
Check FTHR advisory light illuminates.
Indicated oil pressure below 44 psi or continuous illumination of # 1 ENG OIL PRESS or # 2 ENG OIL PRESS
warning light:
-
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
NOTE:
Should the Main Oil Pressure indication fail (dashes replace the digits and the needle is
removed), provided the # 1 ENG OIL PRESS or # 2 ENG OIL PRESS warning light is not
Illuminated, there is no requirement to shut down the affected engine.
Maintenance action is required before next flight.
High Oil Pressure
Continuous oil pressure above 72 psi:
POWER ................................................................................................................................................. Reduce
NOTE:
•
A power reduction of 20% torque should produce a decrease in oil pressure.
Power reduction will be dependant on aircraft performance, including icing and airspeed
requirements.
Minimum airspeed must be appropriate to flap configuration and flight conditions.
At pilot’s discretion, power may be reduced on the affected engine only.
Monitor oil pressure for 2 min.
Oil pressure decreases to 72 psid or less:
-
Maintain power at or below the adjusted torque setting for remainder of the flight.
-
Maintenance action required prior to next flight.
Oil pressure remains above 72 psid:
-
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2.16
3.1-15
[Rev. 16] 7 MAR 2016
ABNORMAL OIL TEMPERATURE IN FLIGHT
(OIL TEMPERATURE EXCEEDS 107°C)
NOTE:
1.
With an Oil Temperature greater than 107°C, the affected oil temperature indication will be red.
POWER - Reduce Torque by 20%
NOTE:
A reduction of 20% torque should produce a decrease in oil temperature.
Power reduction will be dependant on aircraft performance, including icing and airspeed
requirements.
Minimum airspeed must be appropriate to flap configuration and flight conditions.
At pilot’s discretion, power may be reduced on the affected engine only.
2.
Monitor Oil Temperature.
Oil Temperature at or below 115°C:
1. POWER - Maintain at or below the reduced torque setting for remainder of the flight
2. Monitor Oil Temperature.
3. Maintenance action required prior to next flight.
Oil Temperature above 115°C:
1. POWER Lever (affected engine) - FLIGHT IDLE
2. Condition Lever (affected engine) - START & FEATHER
3. Monitor Oil Temperature.
Oil Temperature decreases immediately to or below 115°C:
4. Flight may be continued with affected engine at FLIGHT IDLE / START & FEATHER.
Oil Temperature remains above 115°C:
4. Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
3.1.2.17
ENGINE OIL TEMPERATURE BELOW 65°C
(Propeller De-Icing ON In Flight)
•
Monitor affected engine performance.
-
Exit icing conditions as soon as possible.
[END]
AOM DASH 8-Q400
3.1-16
[Rev. 16] 7 MAR 2016
3.1.2.18
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
CHECK FIRE DET (Warning Light) and FAULT A or FAULT B (Advisory Light)
(Fire Detector Loop Failure)
•
No crew action required
NOTE:
Maintenance action required prior to next flight.
[END]
3.1.2.19
CHECK FIRE DET (Warning Light) and BTL LOW (Advisory Light)
(Fire Bottle Pressure Low)
•
No crew action required.
NOTE:
Maintenance action required prior to next flight.
[END]
3.1.2.20
# 1 ENG FADEC FAIL or # 2 ENG FADEC FAIL
(Warning Light)
NOTE:
-
A FADEC failure may cause the affected engine to shut down automatically.
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
3.1.2.21
# 1 ENG FADEC or # 2 ENG FADEC
(Caution Light)
Affected Engine:
POWER Lever ................................................................................................... Adjust Slowly and Smoothly
Move POWER Lever of affected engine to the req'd position.
NOTE:
Symmetric torque may require asymmetric POWER Lever positions.
CAUTION: Do Not retard affected POWER Lever below DISC on landing.
[END]
3.1.2.22
POWERPLANT
(ED Advisory)
•
Monitor engine performance
NOTE:
Maintenance action required prior to next flight.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2.23
3.1-17
[Rev. 16] 7 MAR 2016
PROPELLER OVERSPEED
(Propeller increases above 1020 RPM and # 1 PEC or # 2 PEC Caution Light illuminates)
Above 400 ft AGL:
Airspeed ................................................................................................................................................ Reduce
Reduce airspeed to help reduce propeller speed.
NOTE:
Minimum airspeed will be appropriate to flap configuration and flight conditions.
Affected Engine:
POWER Lever ............................................................................................................. Retard to FLIGHT IDLE
Move POWER Lever of the affected engine to FLIGHT IDLE position to control propeller RPM.
Condition Lever ................................................................................................................ START & FEATHER
Move Condition Lever of the affected engine to START / FEATHER.
ALT FTHR Switchlight (if req’d) .............................................................................................................. FTHR
Check FTHR advisory light goes out.
If propeller does not feather:
- Do Not shut down the engine
ALT FTHR Switchlight .................................................................................................................................. Off
Check FTHR advisory light illuminates.
Condition Levers ............................................................................................................................ MAX / 1020
POWER Lever (non-affected engine) ................................................................................................. As Req’d
As required to maintain the desired flight profile.
POWER Lever (affected engine) ......................................................................................................... Advance
Advance to match the POWER lever of the non-affected engine.
Operate together as required to maintain the desired flight profile.
NOTE:
-
Symmetric POWER levers will give approximately symmetric power.
During overspeed governor control, an increase in power or turbulence encounter may cause
the speed of the affected propeller to temporarily exceed 1080 RPM.
Land immediately at the nearest suitable airport.
Landing Considerations:
-
Do Not retard affected POWER Lever below FLIGHT IDLE on landing.
-
Anticipate greater than normal braking requirements due to increased propeller thrust at FLT IDLE setting.
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
1.35
1.35
REF SPEED INCR ON
1.69
1.62
If propeller feathers:
-
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
NOTE:
If engine is not shut down immediately after feathering the propeller with the Alternate Feather
system, the propeller may unfeather.
Re-select the ALT FTHR switch to feather the propeller.
[END]
AOM DASH 8-Q400
3.1-18
[Rev. 16] 7 MAR 2016
3.1.2.24
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
DUAL PROPELLER OVERSPEED
(Both Propellers increase above 1020 RPM and
# 1 PEC and # 2 PEC Caution Lights illuminate)
-
Land at the nearest suitable airport.
NOTES:
1. During overspeed governor control, an increase in power of turbulence encounter may
cause the propeller speed to temporarily exceed 1080 RPM.
2, With POWER levers in the RATING detent, the TRQ indication will be less than the calculated rated torque presented at the top of the ED.
Landing Considerations:
-
Do Not retard affected POWER Lever below FLIGHT IDLE on landing and during taxi, as propellers will
feather.
-
Anticipate greater than normal braking requirements due to increased propeller thrust at FLT IDLE setting.
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
NOTE:
1.35
1.35
REF SPEED
INCR ON
1.69
1.62
During the landing roll, propeller RPM will decrease to approximately 500 to 550 and may
cause the AC generators to drop off-line, as indicated by the illumination of # 1 AC GEN and #
2 AC GEN caution lights.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.2.25
3.1-19
[Rev. 16] 7 MAR 2016
# 1 PEC or # 2 PEC
(Caution Light)
Landing Considerations:
-
Do Not select affected POWER Lever below FLIGHT IDLE on landing.
-
Anticipate greater than normal braking requirements due to increased propeller thrust at FLT IDLE setting.
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
1.35
1.35
REF SPEED
INCR ON
1.69
1.62
[END]
3.1.2.26
UNSCHEDULED PROPELLER FEATHERING
(May be indicated by High Torque)
Above 400 ft AGL:
POWER Lever (affected engine) .................................................................................................. FLIGHT IDLE
Move POWER Lever of affected engine to FLIGHT IDLE position.
-
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
3.1.2.27
PROPELLER GROUND RANGE ADVISORY LIGHT CYCLING
POWER Levers ................................................................................................ Advance above FLIGHT IDLE
Advance POWER Levers forward to a position that turns the GROUND RANGE light off.
CAUTION: Avoid POWER Lever positions that cause in the GROUND RANGE lights to illuminate.
Landing Considerations:
-
Do Not select affected POWER Lever below FLIGHT IDLE on landing.
-
Anticipate greater than normal braking requirements due to increased propeller thrust at FLT IDLE setting.
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
[END]
AOM DASH 8-Q400
1.35
1.35
REF SPEED
INCR ON
1.69
1.62
3.1-20
[Rev. 16] 7 MAR 2016
3.1.2.28
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ENGINE FAIL / FIRE / SHUT-DOWN (In Flight)
POWER Lever (non-affected engine) ..................................................................................... Adjust As Req’d
Adjust POWER Lever of non-affected engine as required to maintain the desired flight profile.
Affected Engine:
POWER Lever ............................................................................................................................. FLIGHT IDLE
Move POWER Lever of affected engine to FLIGHT IDLE position.
Condition Lever ................................................................................................................................FUEL OFF
Move Condition Lever of affected engine to FUEL OFF position.
If propeller does not feather:
ALT FTHR ................................................................................................................................................. FTHR
Press the # 1 or # 2 ALT FTHR switchlight.
Make sure the green FTHR light illuminates.
PULL FUEL / HYD OFF Handle .................................................................................................................. Pull
Check respective FUEL VALVES CLOSED and HYD VALVES CLOSED,
EXTG FWD BTL and EXTG AFT BTL arm advisory lights illuminate.
TANK AUX PUMP ....................................................................................................................................... OFF
Make sure the respective green TANK AUX PUMP ON light is out.
If fire:
EXTG Switch .................................................................................................................................... FWD BTL
Set EXTG switch of affected engine to FWD BTL. Check EXTG FWD BTL arm advisory light out.
NOTE:
If the fire is extinguished, ENGINE FIRE and PULL FUEL / HYD OFF handle lights will go out
and fire warning tone is silenced.
The engine fire warning tone can be silenced by pressing the ENGINE FIRE light.
Wait up to 30 s, if fire persists:
EXTG Switch ....................................................................................................................................... Aft BTL
Set EXTG switch of affected engine to AFT BTL. Check EXTG AFT BTL arm advisory light out.
AUTOFEATHER SELECT ............................................................................................................................. Off
Press the AUTOFEATHER SELECT switchlight.
Check A/F SELECT and ARM off, on ED and SELECT advisory light out.
CAUTION: Propeller may unfeather if AUTOFEATHER switch is selected off before condition lever
is selected to FUEL OFF.
NOTE:
[with MS 4-126150 or MS 4-126172 or MS 4-121109 or MS 4-121281 Not Incorporated]:
With an engine shut down and propeller de-ice selected, the PROP DEICE caution light will
illuminate.
Confirm functioning of the propeller de-ice system of the operating engine by observing
PROPS advisory light (operating engine) illuminates and goes out repeatedly.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-21
[Rev. 18] 21 NOV 2016
ENGINE FAIL / FIRE / SHUT-DOWN (In Flight) (cont’d)
POWER Levers ................................................................................................................... Operate Together
Operate together as required to maintain the desired flight profile.
NOTES:
1. If the POWER lever of the non-affected engine was selected forward of the RATING detent,
it must be retarded to the RATING detent or below when the 2 POWER levers are operated
together.
2. If the start SELECT light illuminates, see Sub-Chapter 3.1.2.3
IGNITION (affected engine) ......................................................................................................................... OFF
Set IGNITION 1 or IGNITION 2 switch of failed engine to OFF.
BLEED Air (operating engine) ............................................................................................................ As Req’d
•
Set BLEED CONTROL Switch of operating engine to BLEED 1 or 2.
•
Turn BLEED AIR FLOW CONTROL as required.
BLEED Air (affected engine) ....................................................................................................................... OFF
Set BLEED CONTROL Switch of affected engine to the OFF position.
STBY HYD PRESS Switch ...................................................................................................................... Press
Check STBY HYD PRESS ON advisory light illuminates and
STBY HYD PRESS (2800 - 3000 psi) indication on # 2 MFD.
TANK AUX PUMP (operating engine) ........................................................................................................... ON
Push the TANK 1 or TANK 2 AUX PUMP Switchlight and
make sure the respective green ON advisory light illuminates.
•
Transfer fuel as required to maintain fuel balance.
If # 2 Engine Inoperative:
STBY HYD PRESS and PTU CNTRL Switches .......................................................................................... ON
Check STBY HYD PRESS ON, PTU CNTRL ON and PTU pressure
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated]:
advisory lights illuminate and STBY HYD PRESS (2800 - 3000 psi) indication on # 2 MFD.
If # 1 engine inoperative:
STBY HYD PRESS Switch .......................................................................................................................... ON
Check STBY HYD PRESS ON advisory light illuminates and
STBY HYD PRESS (2800 - 3000 psi) indication on # 2 MFD.
Landing Considerations:
-
With # 1 engine inoperative Do Not select PTU CNTRL to ON
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
[END]
AOM DASH 8-Q400
1.40
1.50
REF SPEED
INCR ON
1.75
1.80
3.1-22
[Rev. 16] 7 MAR 2016
3.1.2.29
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ENGINE FAILURE ON APPROACH GO-AROUND
Condition Levers ............................................................................................................................ MAX / 1020
POWER Levers ........................................................................................................................ RATING Detent
Advance POWER levers to RATING detent to achieve maximum take-off power.
If landing flap selected:
FLAPS Lever ................................................................................................................................ 5°, 10° or 15°
Check FLAP indication on # 2 MFD.
Minimum Airspeed .............................................................................. Go-Around Speed Flap 5°, 10° or 15°
If REF SPEED INCR ON:
Minimum Airspeed ................................................................. Go-Around Speed Flap 5°, 10° or 15° + 20 kt
Positive rate of climb:
LANDING GEAR Lever .................................................................................................................................. UP
Check all gear, door and LANDING GEAR advisory lights out.
Affected engine:
POWER Lever ............................................................................................................................. FLIGHT IDLE
Condition Lever ............................................................................................................................... FUEL OFF
If propeller does not feather:
ALT FTHR ................................................................................................................................................. FTHR
Press the # 1 or # 2 ALT FTHR switch.
Make sure the green FTHR light illuminates.
When clear of obstacles, but not below 400 ft AGL:
Airspeed ........................................................................................ Accelerate to final Take-off Climb Speed
FLAPS Lever .................................................................................................................................................. 0°
At Flap Retraction Initiation Speed for Flap 5°, 10° or 15° ................. Check FLAP indication on # 2 MFD
Confirm maximum continuous power and continue climb.
-
Complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-23
[Rev. 16] 7 MAR 2016
3.1.3
AUTOFLIGHT - FLIGHT INSTRUMENTS and NAVIGATION
3.1.3.1
MISTRIM (TRIM NOSE UP or TRIM NOSE DN or TRIM L WING DN or TRIM R WING DN)
(Message on PFD)
(Autopilot Pitch or Roll Mistrim)
Autopilot .......................................................................................................................................... Disengage
CAUTION: Prior to disengaging the autopilot, firmly hold the control wheel and be prepared for a
control force in pitch or roll as appropriate.
Trim ..................................................................................................................................................... As Req’d
NOTE:
Observe the Slip / Skid indication on the PFD.
If required, adjust the rudder trim to center the Slip / Skid indication prior to applying aileron trim
Autopilot ............................................................................................................................................ As Req’d
[END]
3.1.3.2
AP PITCH TRIM FAIL
(Message on PFD)
(Autopilot Pitch Trim Failure)
CAUTION: Prior to disengaging the autopilot, firmly hold the control wheel and be prepared for a
control force in pitch.
Autopilot .......................................................................................................................................... Disengage
Pitch Trim ...................................................................................................................... Adjust (As Necessary)
Autopilot ................................................................................................................................. Do Not Engage
NOTE:
The auto pitch trim function will also be inoperative when either the AFCS FAIL or AP PITCH
TRIM FAIL message is displayed.
[END]
3.1.3.3
AUTO TRIM FAIL
(Message on PFD)
(Auto Pitch Trim Failure)
Autopilot ................................................................................................................................. Do Not Engage
NOTE:
When selecting Flap 15° to Flap 35° or Flap 35° to Flap 15°, there will be an increase in the
pitch trim adjustment.
The auto pitch trim function will also be inoperative when either the AFCS FAIL or AP PITCH
TRIM FAIL message is displayed.
[END]
3.1.3.4
AP DISENGAGED or AP / YD DISENGAGED
(Flashing PFD Message and Red AP DISENG Light)
(Autopilot has automatically disengaged)
A/P DIS Switch ............................................................................................................. Press to Cancel Alerts
Pitch, Aileron and Rudder Trim ................................................................................... Adjust (As Necessary)
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
If associated AFCS failure message goes out:
Autopilot ............................................................................................................................. Engage (As Req’d)
[END]
AOM DASH 8-Q400
3.1-24
[Rev. 16] 7 MAR 2016
3.1.3.5
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
YD DISENGAGED
(Flashing PFD Message)
(Yaw Damper has automatically disengaged)
A/P DIS Switch ............................................................................................................ Press to Cancel Alerts
Rudder Trim .................................................................................................................. Adjust (As Necessary)
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
If associated AFCS failure message goes out:
Yaw Damper ....................................................................................................................... Engage (As Req’d)
[END]
3.1.3.6
AFCS CONTROLLER INOP
(Message on PFD)
(A failed FGCP or stuck button has been detected)
If Autopilot remains engaged:
NOTE:
It may not be possible to disengage the autopilot or yaw damper using the FGCP AP or YD
buttons.
- Use the control wheel AP DIS button or GA button to disengage the autopilot when required.
If Flight Director modes remain active:
NOTE:
It may not be possible to select or de-select certain flight director modes.
The Pitch Wheel may be inoperative.
- Use alternate Flight Director modes or fly aircraft by reference to raw data to accomplish remainder of flight.
If a Nav Source, Course or HDG knob is inoperative:
HSI SEL ...................................................................................................... Unaffected Side L or R (As Req’d)
- Use PFD source data from the selected side to accomplish the remainder of the flight.
[END]
3.1.3.7
AFCS FAIL
(Message on PFD)
(Both Flight Guidance Modules have failed)
Lost Services:
Autopilot and Yaw Damper
Flight Director
Flap Automatic Pitch Trim
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
NOTE:
Note: When selecting Flap 15 to Flap 35 or Flap 35 to Flap 15, there will be an increase in the
pitch trim requirement.
If message goes out:
Autopilot or Yaw Damper .................................................................................................. Engage (As Req’d)
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.3.8
3.1-25
[Rev. 16] 7 MAR 2016
L FD FAIL or R FD FAIL
(Message on PFD)
(Left or Right Flight Guidance Module has failed)
Lost Services:
Autopilot and Yaw Damper
Dual FD Approach Mode
Flap Automatic Pitch Trim
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
NOTE:
When selecting Flap 15 to Flap 35 or Flap 35 to Flap 15, there will be an increase in the pitch
trim requirement.
If message disappears:
Autopilot or Yaw Damper .............................................................................................. Engage (As Required)
[END]
3.1.3.9
YD NOT CENTERED
(Message on PFD)
(Yaw Damper has disengaged in a non-centered position)
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
If associated AFCS failure message goes out:
Wait 15 s:
Yaw Damper .......................................................................................................................................... Engage
If YD NOT CENTERED message remains:
Rudder Trim .................................................................................................................. Adjust (As Necessary)
Yaw Damper .......................................................................................................................................... Engage
If YD NOT CENTERED message remains:
Autopilot or Yaw Damper ........................................................................................................ Do Not Engage
[END]
3.1.3.10
HDG FAIL
(Message on affected PFD)
(Source of heading data to PFD has failed)
EFIS ATT / HDG SOURCE ............................................................................................ 1 or 2 (As Appropriate)
- Fly the aircraft by reference to the remaining source of heading data.
Lost Services:
Autopilot and Yaw Damper
NOTE:
If a malfunction of the flux valve is the cause of the heading failure, the SLAVE advisory light,
on the AHRS controller, will also illuminate.
[END]
AOM DASH 8-Q400
3.1-26
[Rev. 16] 7 MAR 2016
3.1.3.11
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ATT FAIL
(Message on PFD)
(Source of pitch and roll data to PFD has failed)
EFIS ATT / HDG SOURCE ............................................................................................ 1 or 2 (As Appropriate)
- Fly the aircraft by reference to the remaining source of attitude data.
Airspeed .................................................................................................................................. 200 KIAS (MAX)
Lost Services:
Autopilot and Yaw Damper
NOTE:
ELEVATOR FEEL Caution Light will illuminate.
Elevator forces may be higher or lower than usual.
[END]
3.1.3.12
PITCH MISMATCH or ROLL MISMATCH
(Messages on PFD)
(AHRS 1 and 2 attitudes do not match)
- Determine valid attitude source by comparing pitch and roll displayed on PFD 1 and 2 against the standby
instrument.
EFIS ATT / HDG SOURCE ............................................................................................ 1 or 2 (As Appropriate)
- Fly aircraft by reference to the selected attitude source.
Airspeed .................................................................................................................................. 200 KIAS (MAX)
Lost Services:
Autopilot and Yaw Damper
NOTE:
ELEVATOR FEEL Caution Light will illuminate.
Elevator forces may be higher or lower than usual.
END]
3.1.3.13
IAS FAIL and / or ALT FAIL
(Message on PFD)
(Selected air data source has failed)
EFIS ADC SOURCE ...................................................................................................... 1 or 2 (As Appropriate)
- Fly aircraft by reference to the selected air data source.
Airspeed .................................................................................................................................. 200 KIAS (MAX)
Lost Services:
Autopilot and Yaw Damper
NOTE:
ELEVATOR FEEL, PITCH TRIM, SPLR OUTBD and RUD CTRL Caution Lights will illuminate.
Elevator forces, roll rate and rudder sensitivity may be higher or lower than usual.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.3.14
3.1-27
[Rev. 16] 7 MAR 2016
PRIMARY FLIGHT DISPLAY FAILURE
Affected Side:
MFD ............................................................................................................................................................. PFD
Select PFD using either the MFD 1 or MFD 2 switch on the ESID control panel.
PFD .............................................................................................................................................................. OFF
Turn the PFD BRT knob on the affected EFIS control panel counter-clockwise to the OFF position.
[END]
3.1.3.15
MULTIFUNCTION DISPLAY FAILURE
Affected Side:
MFD ............................................................................................................................................................. OFF
Turn the MFD BRT knob on the affected EFIS control panel counter-clockwise to the OFF position.
MFD (operating MFD) ............................................................................................................ Select (As Req'd)
Select operating MFD to display desired information using either
the MFD 1 or MFD 2 switch on the ESID control panel.
[END]
3.1.3.16
NOTE:
ENGINE DISPLAY FAILURE
(No Data Displayed on ED Screen)
ED display will automatically transfer to MFD 1 in flight.
MFD 1 or 2 (As Req'd) ................................................................................................................................ ENG
Select either MFD to display engine information (ENG) using
the MFD 1 or MFD 2 switch on the ESID control panel.
ED BRT ........................................................................................................................................................ OFF
Turn the ED BRT knob on the ESID control panel counter-clockwise to the OFF position.
[END]
3.1.3.17
CHECK ED
(Message on ED)
(Critical Data on the ED May Be Displayed Incorrectly)
MFD 1 or 2 (As Appropriate) ....................................................................................................................... ENG
•
Monitor MFD display data for incorrectly displayed engine information.
[END]
3.1.3.18
-
CHECK PFD 1 or CHECK PFD 2
(Message on PFD)
(Critical Data on the ED May Be Displayed Incorrectly)
Fly the aircraft by reference to the operative PFD.
MFD (affected side) ...................................................................................................................................... PFD
Select affected MFD to display PFD information
by turning either the MFD 1 or MFD 2 control switch on the ESID control panel to the PFD position.
NOTE:
Monitor PFD data for incorrect information and report to maintenance.
[END]
AOM DASH 8-Q400
3.1-28
[Rev. 16] 7 MAR 2016
3.1.3.19
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
HOT DISPLAYS or FANS FAIL
(Message on ED)
(Two or More EIS Display Units Are Overheating)
-
Land at nearest suitable airport.
If a PFD or ED should subsequently fail:
MFD 1 or 2 (As Appropriate) .......................................................................................................... PFD or ENG
[END]
3.1.3.20
NOTE:
ENGINE DISPLAY ADVISORIES
Maintenance action is required prior to next flight if any of the following advisory messages
appear on the ED.
If AVIONICS Caution Light illuminated:
IFC Messages:
IOP 1 FAIL or IOP 2 FAIL or IOPS FAIL
IOM 1 FAIL or IOM 2 FAIL or IOMS FAIL
WTG 1 FAIL or WTG 2 FAIL or WTGS FAIL
WOW / IOP 1 FAIL or WOW / IOP 2 FAIL or WOW / IOPS FAIL
IOP BAD CONF
Display Messages:
DU BAD CONF
FANS FAIL
HOT DISPLAYS
ED MON FAIL
PFD 1 MON FAIL or PFD 2 MON FAIL or PFDS MON FAIL
HOT PFD 1 or HOT PFD 2
HOT MFD 1 or HOT MFD 2
HOT ED
NOTE:
Avionics Caution Light illuminates on the ground only.
If AVIONICS Caution Light not illuminated:
IFC Messages:
GPWS I/F FAIL
RA1 FAIL or RA2 FAIL or RAS FAIL
Powerplant Messages:
POWERPLANT
FADEC 1 / DU or FADEC 2 / DU or FADECS / DU
Display Messages:
PFD 1 LINK FAIL or PFD 2 LINK FAIL
MFD 1 LINK FAIL or MFD 2 LINK FAIL
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-29
[Rev. 16] 7 MAR 2016
3.1.3.21 AIR DATA SYSTEM FAILURE
(Loss of both AIRSPEED and both ALTITUDE INDICATIONS on PILOT'S and CO-PILOT'S PFD)
(Simultaneous Failure of Air Data Systems 1 and 2)
ELEVATOR FEEL and PITCH TRIM and SPLR OUTBD and RUD CTRL
(Caution Lights)
-
Use Standby Airspeed Indicator and Standby Altimeter to control airplane.
Maximum Airspeeds:
Flap 0° ................................................................................................................................................... 1.8 VSR
Flap 5°, 10° or 15° ................................................................................................................................. 1.6 VSR
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence using Flap 15°.
Approach and VREF Speeds:
Flap 15° ..................................
VREF + 5
REF SPEED
INCR ON
VREF + 25
1.45
REF SPEED
INCR ON
1.80
Landing Distance Factor:
Flap 15° ..................................
[END]
3.1.3.22
LOSS OF PILOT, CO-PILOT and STANDBY AIRSPEED and ALTITUDE INDICATIONS
(Loss of both Pitot Static probes on the right side due to a suspected Bird Strike)
Pitot Static Isolation Valve ..................................................................................................................... Press
Check ISOL advisory light illuminates and valid airspeed and altitude information is displayed on # 1 PFD.
-
Land immediately at nearest suitable airport.
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence using Flap 15°.
Approach and VREF Speeds:
Flap 15° ..................................
VREF + 5
REF SPEED
INCR ON
VREF + 25
1.45
REF SPEED
INCR ON
1.80
Landing Distance Factor:
Flap 15° ..................................
[END]
AOM DASH 8-Q400
3.1-30
[Rev. 16] 7 MAR 2016
3.1.3.23
•
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ALT MISMATCH
(Message on PFD)
(Abnormal Altitude Indication)
Compare PFD 1 and PFD 2 altitude indications with the altitude indications on the Standby Altimeter.
With Integrated Standby Instrument [with MS 4-432835 or MS 4-456883 Not Incorporated]:
Using the following standby altimeter correction table, compare the altimeter readings of PFD 1 and PFD 2.
STANDBY ALTITUDE CORRECTION - [with MS 4-432835 or MS 4-456883 Not Incorporated]:
FLAP
0°
5°, 10°, 15° and 35°
ALT
(ft)
IAS (kt)
150 or lower
VMO
VAPP or VREF
VFE
SL
Subtract (ft)
0
0
0
100
15000
Subtract (ft)
0
300
0
100
20000 and above
Subtract (ft)
0
400
-
-
NOTE:
Altimeter correction varies linearly between minimum and maximum airspeeds shown.
EFIS ADC SOURCE ............................................................................................................... 1 or 2 (As Req’d)
Select the EFIS ADC SOURCE switch to 1 or 2 as required on the ESID control panel.
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
3.1.3.24
•
IAS MISMATCH
(Message on PFD)
(Abnormal Airspeed Indication)
Compare PFD 1 and PFD 2 with Standby Airspeed Indicators and determine the valid air data source.
EFIS ADC SOURCE ............................................................................................................... 1 or 2 (As Req’d)
Select the EFIS ADC SOURCE switch to 1 or 2 as required, on the ESID control panel.
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
3.1.3.25
FLIGHT DATA RECORDER
(Caution Light)
Anti-Collision Light ..................................................................................................................... Red or White
If Caution Light remains on:
•
Maintenance action required prior to next flight.
[END]
3.1.3.26
•
GPWS
(Caution Light)
(Loss of EGPWS Terrain Display and Audible Warnings)
Establish and use alternate means to ensure required clearance from terrain is maintained.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.4
FUSELAGE FIRE, SMOKE or FUMES
3.1.4.1
FUSELAGE FIRE, SMOKE or FUMES EMERGENCIES
NOTE:
3.1-31
[Rev. 18] 21 NOV 2016
In the event of fire, smoke or fumes, prepare to land the aircraft without delay while completing
fire suppression and / or smoke or fumes evacuation procedures.
If it cannot be visually verified that the fire has been completely extinguished, whether the
smoke or fumes have cleared or not, land immediately at the nearest suitable airfield or landing site.
3.1.4.1.1
General Procedures
Oxygen Masks .................................................................................................................................. On / 100%
•
Remove headset.
•
Remove quick donning oxygen mask from the quick release holder and put it over nose and mouth.
•
Set oxygen to 100%.
•
Breathe normally to start oxygen flow.
Smoke Goggles (if applicable) ...................................................................................................................... On
•
Remove Smoke Goggles from side console storage and put on over mask.
•
Put headset back on.
MIC Switch .............................................................................................................................................. MASK
Set BOOM / MASK switch to MASK on the ARCDU AUDIO panel and check communications.
RECIRC Fan [with MS 4-126236 Not Incorporated] .................................................................................... OFF
Set the RECIRC FAN switch on the AIR CONDITIONING panel to OFF.
If emergency lights are required:
Emergency Lights ........................................................................................................................................ On
Pull and set EMER LIGHTS switch to the ON position.
AOM DASH 8-Q400
3.1-32
[Rev. 18] 21 NOV 2016
3.1.4.1.2
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Known Source of Fire, Smoke or Fumes
FLIGHT COMPARTMENT
NOTE:
If an electrical source of fire, smoke or fumes is positively identified, remove power to source if
possible.
•
Extinguish fire with portable fire extinguishers.
•
If it cannot be visibly verified that the fire has been extinguished following fire suppression, land immediately
at the nearest suitable airport.
Remove portable fire extinguisher from flight compartment bulkhead, hold upright, slide the safety latch down
with thumb, point nozzle at base of fire and squeeze trigger
CABIN ALTITUDE FWD OUTFLOW Selector ............................................................ Fully Clockwise (OPN)
Turn the CABIN ALTITUDE FWD OUTFLOW selector clockwise towards OPN to exhaust smoke forward.
NOTE:
Flight compartment airflow will carry the smoke or fumes forward.
If additional assistance to remove smoke or fumes is required:
NOTE:
This step will depressurize the aircraft rapidly.
FWD OUTFLOW VALVE Lever ................................................................................................................ Open
Turn the FORWARD OUTFLOW VALVE lever fully clockwise to OPEN.
-
Descend to below 14000 ft as soon as possible.
[END]
CABIN
Emergency Lights ............................................................................................................................... If Req’d
•
Evacuate passengers from affected area.
•
Extinguish fire with portable fire extinguishers
Remove fire extinguisher from right forward cabin area and use in conjunction with flight compartment and
baggage compartment extinguishers if necessary.
NOTE:
•
If a pilot is required to fight the fire, protective breathing equipment must be donned prior to
exiting the flight compartment.
If it cannot be visibly verified that the fire has been extinguished following fire suppression, land immediately
at the nearest suitable airport.
If assistance to remove smoke or fumes from the cabin is required:
NOTE:
This step will depressurize the aircraft rapidly.
AUTO / MAN / DUMP Switch .................................................................................................................. DUMP
Move the REAR OUTFLOW VALVE CONTROL switch to the DUMP position.
-
Descend to below 14000 ft as soon as possible.
[END]
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-33
[Rev. 18] 21 NOV 2016
Known Source of Fire, Smoke or Fumes (cont’d)
BAGGAGE FWD COMPARTMENT
(Illumination of SMOKE Warning Light and BAGGAGE FWD SMOKE and EXTG Advisory Lights)
•
Check for illumination of FIRE BOTTLE FWD ARM advisory light.
Illuminated SMOKE / EXTG Switch ........................................................................................................ Press
Check FIRE BOTTLE FWD LOW advisory light illuminates and FIRE BOTTLE FWD ARM advisory light out.
NOTE:
-
The FIRE BOTTLE AFT LOW advisory light may illuminate after FIRE BOTTLE FWD LOW
advisory light illuminates.
Land immediately at the nearest suitable airport.
[END]
BAGGAGE AFT COMPARTMENT
(Illumination of SMOKE Warning Light and BAGGAGE AFT SMOKE and EXTG Advisory Lights):
•
Check for illumination of VENT INLT CLOSED and VENT OTLT CLOSED and FIRE BOTTLE AFT ARM
advisory lights.
Illuminated SMOKE / EXTG Switch ........................................................................................................ Press
Check FIRE BOTTLE AFT LOW advisory light illuminates and FIRE BOTTLE AFT ARM advisory light out.
NOTE:
-
The FIRE BOTTLE FWD LOW advisory light may illuminate after FIRE BOTTLE AFT LOW
advisory light illuminates.
Land immediately at nearest suitable airport.
[END]
[with Options - CR 825 CH 03262 Incorporated]
CARGO COMPARTMENT
(Illumination of SMOKE Warning Light and SMOKE and EXTG Advisory Switchlights):
•
Check for illumination of VENT INLT CLOSED, VALVE OTLT CLOSED, FIRE BOTTLE HRD / LRD2 ARM
and FIRE BOTTLE LRD1 ARM advisory lights.
SMOKE / EXTG Switch ............................................................................................................................ Press
•
Check FIRE BOTTLE HRD / LRD2 ARM and FIRE BOTTLE LRD1 ARM advisory lights out and illumination
of FIRE BOTTLE HRD LOW advisory light.
After approximately 3 h:
•
FIRE BOTTLE LRD2 LOW and FIRE BOTTLE LRD1 LOW advisory lights will illuminate.
NOTE:
With the requirement to land immediately at the nearest suitable airport, the FIRE BOTTLE
LRD2 LOW and FIRE BOTTLE LRD1 LOW advisory lights will not normally be observed.
[END]
AOM DASH 8-Q400
3.1-34
[Rev. 18] 21 NOV 2016
3.1.4.1.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Unknown Source of Fire, Smoke or Fumes
NOTE:
To prepare for and manage a landing immediately at the nearest suitable airport, the
procedures given in this Sub-Chapter, may be terminated prior to completion.
Bleed Source or Air Conditioning Suspected:
BLEED 1 Switch ............................................................................................................................ OFF
Wait up to 1 min.
If improvement:
Leave BLEED 1 in the OFF position
If necessary to assist in removal of smoke or fumes:
Smoke or Fumes Removal (Sub-Chapter 3.1.4.1.4) ....................................................... Accomplish
[END]
If no improvement:
BLEED 1 ........................................................................................................................................... ON
BLEED 2 ......................................................................................................................................... OFF
Wait up to 1 min.
If improvement:
Leave BLEED 2 in the OFF position
If necessary to assist in removal of smoke or fumes:
Smoke or Fumes Removal (Sub-Chapter 3.1.4.1.4) ....................................................... Accomplish
[END]
If no improvement:
BLEED 2 .......................................................................................................................................... ON
FLT COMP PACK ........................................................................................................................... OFF
Wait up to 1 min.
If improvement:
Leave FLT COMP PACK in the OFF position
If necessary to assist in removal of smoke or fumes:
Smoke or Fumes Removal (Sub-Chapter 3.1.4.1.4) ....................................................... Accomplish
[END]
If no improvement:
FLT COMP PACK .......................................................................................................... AUTO or MAN
CABIN PACK .................................................................................................................................. OFF
Wait up to 1 min.
If improvement:
Leave CABIN PACK in the OFF position
If necessary to assist in removal of smoke or fumes:
Smoke or Fumes Removal (Sub-Chapter 3.1.4.1.4) ....................................................... Accomplish
[END]
If no improvement:
CABIN PACK ................................................................................................................. AUTO or MAN
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-35
[Rev. 18] 21 NOV 2016
Source of Fire, Smoke or Fumes Cannot Be Identified:
DC GEN 1 and 2 .......................................................................................................................................... OFF
Set DC CONTROL GEN 1 and 2 switches to OFF.
Confirm the # 1 DC GEN and # 2 DC GEN caution lights turn on.
AC GEN 1 and 2 .......................................................................................................................................... OFF
Set AC CONTROL GEN 1 and 2 switches to OFF.
Confirm the # 1 AC GEN and # 2 AC GEN caution lights turn on.
STORM / DOME Lights ......................................................................................................... STORM (If Req'd)
MAIN, AUX & STBY Batteries .................................................................................................................... OFF
Set MAIN, AUX and STBY BATT switches to OFF.
Confirm the MAIN BATTERY, AUX BATTERY and STBY BATTERY caution lights turn on.
Emergency Lights ................................................................................................................. OFF (Until Req’d)
•
Pull and set FLIGHT COMPARTMENT EMERGENCY LIGHTS switch to OFF.
•
If the EMERGENCY LIGHTS are necessary, pull and set FLIGHT COMPARTMENT EMERGENCY LIGHTS
switch to the ON position.
-
Land immediately at nearest suitable airport.
CAUTION: Battery duration for operation of Essential Services is 60 min.
NOTE:
Engine bleed air flow to ECS packs is lost. The aircraft will depressurize.
If necessary to remove smoke or fumes from the flight compartment:
NOTE:
This procedure will depressurize the aircraft rapidly.
AUTO / MAN / DUMP ................................................................................................................................. MAN
Move the REAR OUTFLOW VALVE CONTROL switch to the MAN position.
MAN DIFF ........................................................................................................................................ INCR (50 s)
Hold the MAN DIFF switch to the INCR position for 50 s.
Cabin ALT FWD OUTFLOW ........................................................................................ Fully Clockwise (OPN)
Turn CABIN ALTITUDE FWD OUTFLOW rotary switch fully clockwise to OPN.
FWD OUTFLOW VALVE ........................................................................................................................... Open
Turn FWD OUTFLOW VALVE lever clockwise to OPEN.
NOTE:
Ram ventilation is most effective above 150 KIAS.
-
Descend to below 14000 ft as soon as possible.
-
See Sub-Chapter 3.1.6.3.8, BATTERY ESSENTIAL SERVICES, for powered services.
[END]
AOM DASH 8-Q400
3.1-36
[Rev. 18] 21 NOV 2016
3.1.4.1.4
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Smoke or Fumes Removal
(Unknown Source)
-
If it cannot be visibly verified that the fire has been extinguished following fire suppression, land immediately
at nearest suitable airport.
NOTE:
Carry out this procedure only when directed by the Unknown Source of Fire, Smoke or Fumes
checklist (Sub-Chapter 3.1.4.1.3).
RECIRC Fan [with MS 4-126236 Not Incorporated] ................................................................................... OFF
Set RECIRC Fan switch to OFF.
BLEED (unaffected) ........................................................................................................................... ON / MAX
Set unaffected BLEED control switch to 1 or 2.
Turn BLEED airflow control rotary switch fully clockwise to MAX.
NOTE:
Leave affected BLEED or affected PACK switches in the OFF position.
If necessary to remove smoke or fumes from the flight compartment:
CABIN ALTITUDE FWD OUTFLOW ........................................................................... Fully Clockwise (OPN)
Turn the CABIN ALTITUDE FWD OUTFLOW selector clockwise towards OPN to exhaust smoke forward.
If additional assistance to remove smoke or fumes is required:
NOTE:
This step will depressurize the aircraft rapidly.
FWD OUTFLOW VALVE Lever ................................................................................................................ Open
Turn the FORWARD OUTFLOW VALVE lever fully clockwise to OPEN.
-
Descend to below 14000 ft as soon as possible.
[END]
3.1.5
EMERGENCY LANDING / DITCHING, FORCED LANDING, EMERGENCY EVACUATION
3.1.5.1
EMERGENCY LANDING (Both Engines Operating)
•
Instruct cabin crew members to brief and prepare passengers for the emergency.
•
Make sure all items on flight compartment and in cabin are put in a safe place.
•
Complete all radio communications with the ground relative to the intended landing.
•
Review the procedures to be done by the crew.
•
Think about possible practice approach and overshoot.
•
If possible, make sure no passengers are seated in the plane of the propellers.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-37
[Rev. 16] 7 MAR 2016
EMERGENCY LANDING (Both Engines Operating) (cont’d)
EGPWS CB (Left Upper CB Panel – A1) ..................................................................................................... Pull
Emergency Lights ....................................................................................................................................... ON
Pull and set FLIGHT COMPARTMENT EMERGENCY LIGHTS switch to the ON position.
Make sure the PORTABLE EMERGENCY LIGHT on the flight compartment ceiling turns on (optional).
AUTO / MAN / DUMP .............................................................................................................................. DUMP
ELT ................................................................................................................................................................ ON
Activate the Emergency Locator Transmitter manually.
Shoulder Harness .................................................................................................................................... Lock
Move INERTIA REEL LOCK lever, on inboard side of seat, to the lock position.
LANDING GEAR EXTENDED:
•
Proceed with normal approach.
Landing Considerations:
When airplane comes to a stop:
EMERG Brake .............................................................................................................................................. ON
Set EMERGENCY / PARKING BRAKE lever to PARK when airplane comes to a complete stop.
Condition Levers ............................................................................................................................. FUEL OFF
Move Condition Levers to FUEL OFF.
PULL FUEL / HYD OFF Handles ................................................................................................................ Pull
•
Pull the red PULL FUEL / HYD OFF handle of the affected engine.
•
Make sure both related AFT and FWD yellow EXTINGUISHER ARM lights turn on.
•
Make sure the FUEL VALVE CLOSED white light turns on.
•
Make sure the FUEL VALVE OPEN green light goes off.
•
Make sure the HYD VALVE CLOSED white light turns on.
•
Make sure the HYD VALVE OPEN green light goes off.
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
•
Evacuate airplane
After propellers have stopped, the captain will start the evacuation by using the PA to shout the command
“EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE, if one side is blocked.)
The first officer will leave the flight compartment and help with the evacuation.
(cont’d on the next page)
AOM DASH 8-Q400
3.1-38
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
EMERGENCY LANDING (Both Engines Operating) (cont’d)
LANDING GEAR RETRACTED:
Landing Considerations:
- Plan on Flap 35° landing.
- Maintain VREF until immediately prior to flare.
- Do Not exceed 6° nose-up during flare.
- Touch down with minimum speed and minimum rate of descent without stalling.
After ground contact:
Condition Levers ............................................................................................................................. FUEL OFF
Move Condition Levers to FUEL OFF.
PULL FUEL / HYD OFF Handles ................................................................................................................ Pull
Pull # 1 and # 2 PULL FUEL / HYD OFF handles.
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
When airplane comes to a stop:
•
Evacuate airplane
After propellers have stopped, the captain will start the evacuation by using the PA to shout the command
“EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE, if one side is blocked.)
The first officer will leave the flight compartment and help with the evacuation.
DITCHING:
• Broadcast emergency and distress signals.
• Instruct cabin crew members to review ditching procedures with passengers.
• Deploy ditching dam at airstair door and configure forward right hand exit for ditching.
• Make sure all cargo and baggage is prevented from moving.
• Put on crew life jackets.
• Move INERTIA REEL LOCK lever to lock position.
• Set FASTEN BELTS and NO SMOKING sign switches to FASTEN BELTS and NO SMOKING.
• Set AUTO / MAN / DUMP switch to DUMP.
• Set EMER LIGHTS switch to the ON position.
Condition Levers ...................................................................................................................................... MAX
BLEED 1 and 2 ........................................................................................................................................... OFF
Flaps ............................................................................................................................................................. 35°
-
Use VREF airspeed for flap 35°.
Landing Considerations:
- Do Not select landing gear down.
- In rolling swell surface conditions attempt to ditch along and parallel to the crests as much into wind as swell
line permits. In other water surface conditions land into wind.
- Maintain VREF until immediately prior to flare.
Commence flare to achieve zero vertical velocity immediately prior to water contact.
- Give order to “BRACE” on PA system.
- Prior to touchdown maintain a pitch attitude of 10° nose up.
- Touch down with minimum speed and rate of descent without stalling.
NOTE:
A transient nose-up pitching motion may result following touchdown.
Over-correction of this tendency could result in porpoising or nosing in.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-39
[Rev. 16] 7 MAR 2016
EMERGENCY LANDING (Both Engines Operating) (cont’d)
After water contact:
Condition Levers ............................................................................................................................. FUEL OFF
Move Condition Levers to FUEL OFF.
If any engine is not shut down by use of condition lever:
Appropriate PULL FUEL / HYD OFF Handle ............................................................................................ Pull
Pull # 1 and / or # 2 FUEL / HYD OFF handles.
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
When airplane comes to a stop:
•
Evacuate airplane
After the airplane comes to a stop and propellers have stopped turning, the captain starts the evacuation by
using the PA to shout the command “EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE).
The first officer leaves the flight compartment and helps with the evacuation.
NOTE:
After the completion of the ditching run, the airplane will float with one wing in the water.
The upper portion of the right forward emergency exit and / or the airstair door shall be used
for evacuation.
The airstair door ditching dam must be in place prior to opening the door.
WARNING: Do Not open the Aft Doors or the lower portion of the right Forward Emergency Exit.
3.1.5.2
FORCED LANDING (Both Engines Inoperative)
HYD # 3 ISOL VLV .................................................................................................................................... Open
Check the HYD # 3 ISOL VLV OPEN advisory light illuminates and # 3 hydraulic pressure on # 1 MFD.
After all attempts to achieve a successful airstart have failed, proceed as follows:
Airspeed .............................................................................................................................................. 1.23 VSR
NOTES:
1. With FLAP 0°, landing gear retracted, propellers feathered and zero wind conditions,
2.5 NM can be traveled for every 1000 ft of altitude loss.
This distance will increase in a tailwind and decrease in a headwind.
2. All hydraulic (except for elevator control), pneumatic and non-essential electrical services
will be inoperative.
MAIN, AUX & STBY Batteries .................................................................................................................... OFF
Set MAIN, AUXILIARY and STANDBY BATTERY switches to OFF.
Make sure the MAIN, AUX and STBY BATTERY caution lights turn on.
NOTE:
The following services will be inoperative:
HYDRAULIC
Flap
Roll Spoilers
Rudder
Anti-skid braking
Normal landing gear operation
Nosewheel steering
(cont’d on the next page)
AOM DASH 8-Q400
PNEUMATIC
Airframe deicing
Pressurization
ELECTRIC
All variable frequency AC services
All non-essential DC services
(see Sub-Chapter 3.1.6.3.8
for powered services)
3.1-40
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
FORCED LANDING (Both Engines Inoperative) (cont’d)
Passenger Signs .......................................................................................................................................... ON
•
Set FASTEN BELTS SIGN switch to FASTEN BELTS.
•
Set NO SMOKING SIGN switch to NO SMOKING.
Emergency Lights ....................................................................................................................................... ON
Pull and set EMER LIGHTS switch to ON position.
Make sure the PORTABLE EMERGENCY LIGHT on the flight compartment ceiling turns on (optional).
ELT ................................................................................................................................................................ ON
Push the ELT switchlight to the ON position and make sure the red indicator light in the rocker switch turns on.
Shoulder Harness ..................................................................................................................................... Lock
Move INERTIA REEL LOCK lever to lock.
-
Make approach and landing into wind.
Select Appropriate Landing Considerations (see next Paragraphs):
- Landing Gear Extended
- Landing Gear Retracted
- Ditching
LANDING GEAR EXTENDED:
Landing Considerations:
If the available surface is appropriate:
- Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1).
Allow sufficient time for alternate gear extension.
- Extending landing gear will steepen glide angle and decrease glide distance.
- Maintain 1.23 VSR until immediately prior to flare.
- Commence flare to achieve zero vertical velocity immediately prior to ground contact.
- Do Not exceed 6° nose up during flare.
- Touch down with minimum speed and rate of descent without stalling.
After touchdown:
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
EMERG Brake .................................................................................................................. Apply Intermittently
Use the EMERGENCY / PARKING LEVER to stop the airplane.
When airplane comes to a stop:
•
Evacuate airplane.
After propellers have stopped, the commander will start the evacuation by using the PA to shout the command
“EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE, if one side is blocked).
The first officer will leave the flight compartment and help with the evacuation.
LANDING GEAR RETRACTED:
Landing Considerations:
- Maintain 1.23 VSR until immediately prior to flare.
- Commence flare to achieve zero vertical velocity immediately prior to ground contact.
- Do Not exceed 5° nose-up during flare.
- Touch down with minimum speed and rate of descent without stalling.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-41
[Rev. 16] 7 MAR 2016
FORCED LANDING (Both Engines Inoperative) (cont’d)
When airplane comes to a stop:
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
• Evacuate airplane.
After propellers have stopped, the commander will start the evacuation by using the PA to shout the command
“EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE, if one side is blocked.)
The first officer will leave the flight compartment and help with the evacuation.
DITCHING:
Landing Considerations:
- Do Not select landing gear down.
- In rolling swell surface conditions attempt to ditch along and parallel to the crests as much into wind as swell
line permits. In other water surface conditions land into wind.
- Maintain 1.23 VSR until immediately prior to flare.
- Commence flare to achieve zero vertical velocity immediately prior to water contact.
- Maintain pitch attitude of 10° nose-up.
- Touch down with minimum speed and minimum rate of descent without stalling.
- A transient nose-up pitching motion may result following touchdown.
Over-correction of this tendency could result in porpoising or nosing in.
After water contact:
BATTERY MASTER .................................................................................................................................... OFF
Pull out the BATTERY MASTER switch and set to OFF.
When airplane comes to a stop:
• Evacuate airplane.
After propellers have stopped, the commander will start the evacuation by using the PA to shout the command
“EVACUATE, EVACUATE, EVACUATE” (LEFT or RIGHT SIDE, if one side is blocked.)
The first officer will leave the flight compartment and help with the evacuation.
NOTE:
After the completion of ditching run, the airplane will float with one wing in the water.
The upper portion of the right forward emergency exit and / or the airstair door shall be used
for evacuation.
The airstair door ditching dam must be in place prior to opening the door.
WARNING: Do Not open the Aft Doors or the lower portion of the right Forward Emergency Exit.
[END]
3.1.5.3
DITCHING
Preparations:
•
•
•
Broadcast emergency and distress signals.
Alert cabin crew to review ditching procedures with passengers.
Deploy ditching dam at airstair door and configure forward right hand exit for ditching.
NOTE:
•
[with Options - CR 825 CH 03163 and CR 825 CH 03200 Not Incorporated]:
Configuring the forward right-hand emergency exit for ditching may require the aircraft to be
depressurized to reduce the force on the lower exit door handle.
Check security of cargo and baggage and restrain if necessary.
Check Life Jackets ...................................................................................................................................... ON
Pilot and Co-Pilot Harness .............................................................................................. Secure and Locked
FASTEN BELTS and NO SMOKING Sign Switches .............................. FASTEN BELTS and NO SMOKING
(cont’d on the next page)
AOM DASH 8-Q400
3.1-42
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
DITCHING (cont’d)
Operational Conditions:
The 2 factors which bear most directly upon a successful ditching are airplane ground speed and the water
surface condition.
Under all circumstances the airplane should be brought onto the water surface as gently as possible.
In rolling swell surface conditions, the generally recommended technique is to ditch along and parallel to the
crest of a swell, as much into wind as the swell line permits. In all other conditions land into wind.
Approach:
EGPWS CB (Left Upper CB Panel – A1) ..................................................................................................... Pull
Condition Levers ........................................................................................................................... MAX / 1020
BLEED 1 and BLEED 2 Switches .............................................................................................................. OFF
AUTO / MAN / DUMP Switch .................................................................................................................. DUMP
LANDING GEAR Lever ................................................................................................................................ UP
Check all gear, door and LANDING GEAR lever advisory lights out.
FLAP Lever ................................................................................................................................................... 35°
Check FLAP indication on # 2 MFD.
Airspeed ..................................................................................................................................... VREF Flap 35°
Rate of Descent ..................................................................................................................... 200 to 300 ft/min
EMER LIGHTS Switch ................................................................................................................................. ON
LANDING APPROACH and LANDING FLARE Light Switches........................................................ As Req’d
ELT Switch ................................................................................................................................................... ON
Order to Brace .......................................................................................................................... on PA System
Prior to Touchdown .............................................................................. Achieve Pitch Attitude 10° Nose-Up
•
Touch down with minimum speed and rate of descent. Do Not STALL.
NOTE:
A transient nose-up pitching motion may result following touchdown.
Over-correction of this tendency could result in porpoising or nosing in.
After Touchdown:
Condition Levers .............................................................................................................................. FUEL OFF
If any engine is not shut down by use of condition lever:
Appropriate PULL FUEL / HYD OFF Handle ............................................................................................. Pull
BATTERY MASTER Switch ....................................................................................................................... OFF
PASSENGER EVACUATION .............................................................................. After Airplane Has Stopped
NOTE:
After completion of the ditching run, the aircraft will float with one wing in the water.
The upper portion of the right forward emergency exit and / or the airstair door shall be used for
evacuation.
The airstair door ditching dam must be in place prior to opening the door.
WARNING: Do Not open the Aft Doors or the lower portion of the right Forward Emergency Exit.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.6
ELECTRICAL SYSTEMS
3.1.6.1
BATTERY
3.1.6.1.1
MAIN BATTERY or AUX BATTERY or STBY BATTERY
(Caution Light)
3.1-43
[Rev. 16] 7 MAR 2016
Battery (affected) .......................................................................................................................... OFF then ON
Set MAIN, AUX or STBY BATT switch to OFF and then to MAIN, AUX or STBY BATT position
If caution light remains on:
Battery (affected) ......................................................................................................................................... OFF
Set MAIN, AUX or STBY BATT switch to OFF.
[END]
3.1.6.1.2
MAIN BAT HOT or AUX BAT HOT or STBY BAT HOT
(Warning Light)
Electrical Page of MFD ...................................................................................................... Confirm Overheat
See if the BATTERY TEMPERATURE display on the MFD Electrical Systems page, is showing a red value.
Battery (affected) ......................................................................................................................................... OFF
Set MAIN, AUX or STBY BATT switch to OFF.
Check if MAIN, AUX or STBY BATTERY caution lights turn ON.
Continue to monitor affected battery temperature.
If battery temperature continues to rise:
-
Land immediately at the nearest suitable airport.
[END]
3.1.6.1.3
EMER LTS DISARMED
(Caution Light)
Emergency Lights ..................................................................................................................................... ARM
Pull and set EMERGENCY LIGHTS switch to ARM.
[END]
3.1.6.2
BUS
3.1.6.2.1
MAIN DC BUS FAULT
Left MAIN DC BUS:
(DC BUS, # 1 DC GEN, STBY BATTERY and AUX BATTERY - Caution Lights)
AUX and STBY BATT Switches ................................................................................................................. OFF
DC GEN 1 .................................................................................................................................................... OFF
Bus Fault Reset ....................................................................................................................................... Reset
Hold the BUS FAULT RESET switch at BUS FAULT RESET and release to OFF.
NOTE:
If power to the failed DC bus is restored (DC BUS caution light goes off), leave the selected
switches in the OFF position.
If DC BUS Caution Light remains illuminated:
•
Leave selected switches in the OFF position.
NOTE:
Automatic cabin pressure control is lost.
The FAULT advisory light on the pressurization control panel will be illuminated.
(cont’d on the next page)
AOM DASH 8-Q400
3.1-44
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
MAIN DC BUS FAULT (cont’d)
[with MS 4-113581 or IS 4Q2150011 Not Incorporated]:
NOTE:
ECS pack airflow is lost and cabin will depressurize.
Descend ........................................................................................................................... To below 14000 ft
Descend to below 14000 ft as soon as possible.
AUTO / MAN / DUMP Switch ................................................................................................................ MAN
Move the Rear Outflow Valve Control Switch to the MAN position.
MAN DIFF ................................................................................................................................... INCR (30 s)
Hold the MAN DIFF switch to the INCR position for 30 s.
Complete RAM VENTILATION (Sub-Chapter 3.1.1.3).
-
Land at the nearest suitable airport.
Right MAIN DC BUS:
(DC BUS, # 2 DC GEN and MAIN BATTERY - Caution Lights)
MAIN BATT Switch .................................................................................................................................... OFF
DC GEN 2 .................................................................................................................................................... OFF
Bus Fault Reset ....................................................................................................................................... Reset
Hold the BUS FAULT RESET switch at BUS FAULT RESET and release to OFF.
NOTE:
If power to the failed DC bus is restored, leave the selected switches in the OFF position.
If Bus Fault remains:
•
Leave selected switches in the OFF position.
[with MS 4-113581 or IS 4Q2150011 Not Incorporated]:
NOTE:
ECS pack airflow is lost and cabin will depressurize.
Descend ........................................................................................................................... To below 14000 ft
Descend to below 14000 ft as soon as possible.
Complete RAM VENTILATION (Sub-Chapter 3.1.1.3).
-
Land at the nearest suitable airport.
-
Anti-Skid will be inoperative, complete procedure INBD ANTI-SKID and / or OUTBD ANTI-SKID (Caution
Light) (Sub-Chapter 3.1.11.7).
[END]
Left MAIN DC BUS or Right MAIN DC BUS Failure:
(No Illumination of DC BUS - Caution Light)
NOTE:
A failure of the Left Main DC Bus or Right Main DC Bus will result in the loss of some or all of
the services powered by the affected Main DC Bus.
Illumination of caution lights and presentation of messages associated with the lost systems
will occur.
DC GEN 1 (Left Main DC Bus) or DC GEN 2 (Right Main DC Bus) ......................................................... Check
Confirm a zero ( 0 ) LOAD on ELECTRICAL page of functioning MFD
AUX BATT (Left Main DC Bus) or MAIN BATT (Right Main DC Bus) ..................................................... Check
Confirm a negative ( - ) LOAD on ELECTRICAL page of functioning MFD
DC GEN Switch (affected) .......................................................................................................................... OFF
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.6.2.2
3.1-45
[Rev. 16] 7 MAR 2016
DC BUS
(Caution Light)
If no other associated lights:
Bus Fault Reset ....................................................................................................................................... Reset
Hold the BUS FAULT RESET switch at BUS FAULT RESET and release to OFF.
[END]
3.1.6.2.3
LOSS OF AC BUS POWER
Lost Services:
AC bus failure results in loss of the following left or right bus services:
L AC BUS
R AC BUS
L Aux Fuel Pump
L Prop Deicing
L Alpha Vane Heater
L TRU
L Ice Detection Sensor
Pilot’s Windshield Heat (NORM & WARM UP)
L Engine Intake Heater
L Pitot Static Heater
Stick Pusher System
R Aux Fuel Pump
R Prop Deicing
R Alpha Vane Heater
R TRU
R Ice Detection Sensor
Standby Hydraulic Pump
Co-pilot’s Windshield Heat (NORM)
Pilot’s Side Window Heat
R Engine Intake Heater
R Pitot Static Heater
Stick Pusher System
[END]
3.1.6.2.4
L AC BUS or R AC BUS
(Caution Light)
STICK PUSHER SHUT OFF ............................................................................................................ Press OFF
Airspeed ........................................................................................................................................... VREF (MIN)
- Maintain airspeed appropriate for icing conditions and other failures if applicable.
-
Fuel transfer from the tank associated with the affected fuel aux pump is unavailable.
-
Affected windshield will not be de-misted or anti-iced.
-
Avoid icing conditions.
-
Refer to LOSS OF AC BUS POWER (Sub-Chapter 3.1.6.2.3) for a list of lost services.
IF there are abnormal indications of airspeed or altitude on the pilot’s or co-pilot’s PFD:
EFIS ADC Source ................................................................................................................... 1 or 2 (As Req’d)
If icing conditions are encountered:
Condition Levers ....................................................................................................................................... MAX
-
Affected propeller and engine intake will not be anti-iced.
-
Monitor affected engine performance.
-
Exit icing conditions as soon as possible.
[END]
AOM DASH 8-Q400
3.1-46
[Rev. 16] 7 MAR 2016
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.6.3
LOSS OF GENERATED POWER
3.1.6.3.1
# 1 DC GEN and # 2 DC GEN and either # 1 AC GEN and # 2 AC GEN or L TRU or R TRU
(Caution Lights)
(Loss of Both DC Generators and Both AC Generators or
loss of Both DC Generators and One or Both TRUs)
DC, AC GEN Switch (affected) ............................................................................... OFF then On (Individually)
If caution lights remain on:
DC, AC GEN Switch (affected) ................................................................................................................... OFF
STORM / DOME Lights ......................................................................................................... STORM (If Req'd)
MAIN, AUX & STBY Batteries ................................................................................................................... OFF
Set MAIN, AUX and STBY BATTERY switches to OFF.
Check if MAIN, AUX and STBY BATTERY caution lights turn ON.
Emergency Lights ............................................................................................................................. As Req'd
Pull and set EMER LIGHTS switch to ON position if required.
-
Land immediately at the nearest suitable airport.
CAUTION: Battery duration for operation of Essential Services is 60 min.
-
See Sub-Chapter 3.1.6.3.8 for powered services.
NOTE:
ECS pack air flow is lost and cabin will depressurize.
-
When below 14000 ft, complete RAM VENTILATION, in Sub-Chapter 3.1.1.3.
-
Anti-Skid will be inoperative, complete procedure INBD ANTI-SKID and / or OUTBD ANTI-SKID (Caution
Light) (Sub-Chapter 3.1.11.7).
[END]
3.1.6.3.2
NOTE:
-
# 1 DC GEN or # 2 DC GEN and L TRU and R TRU
(Caution Lights)
(Loss of One DC Generator and Both TRUs)
All secondary bus services are inoperative.
Land at the nearest suitable airport.
[END]
3.1.6.3.3
# 1 DC GEN and # 2 DC GEN and # 1 AC GEN or # 2 AC GEN
(Caution Lights)
(Loss of Both DC Generators and One AC Generator)
DC, AC GEN Switch (affected) ............................................................................... OFF then On (Individually)
If caution lights remain on:
DC, AC GEN Switch (affected) ................................................................................................................... OFF
AC GEN (operative) ..................................................................................................................... Monitor Load
-
Land immediately at the nearest suitable airport.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.6.3.4
3.1-47
[Rev. 16] 7 MAR 2016
# 1 DC GEN and # 2 DC GEN
(Caution Lights)
(Loss of Both DC Generators)
DC GEN Switch (affected) ..................................................................................... OFF then On (Individually)
If caution lights remain on:
DC GEN Switch (affected) .......................................................................................................................... OFF
L TRU and R TRU ....................................................................................................................... Monitor Load
Monitor the TRU load indications on the MFD - Electrical System page.
[END]
3.1.6.3.5
L TRU or R TRU or L TRU HOT or R TRU HOT
(Caution Light)
(Loss or Overheat of One TRU)
L TRU or R TRU CB (Right Upper CB Panel) (affected) ............................................................................ Pull
[END]
3.1.6.3.6
# 1 DC GEN or # 2 DC GEN or # 1 AC GEN or # 2 AC GEN
(Caution Light)
(Loss of One Generator)
GEN (affected) ............................................................................................................................... OFF then On
Set affected DC or AC GENERATOR switch to OFF, then to GEN 1 or GEN 2.
Check # 1 DC GEN or # 2 DC GEN or # 1 AC GEN or # 2 AC GEN caution light out and
affected DC or AC generator VOLTS and LOAD on ELECTRICAL page of MFD.
If caution light remains on:
GEN (affected) ............................................................................................................................................. OFF
Set affected GENERATOR switch to OFF.
[END]
3.1.6.3.7
# 1 DC GEN HOT or # 2 DC GEN HOT or # 1 AC GEN HOT or # 2 AC GEN HOT
(Caution Light)
(Overheat of One Generator)
GEN Switch (affected) ................................................................................................................................. OFF
Set affected DC CONTROL GEN or AC CONTROL GEN switch to OFF.
Check for illumination of appropriate DC GEN or AC GEN caution light.
NOTE:
Continued operation of the associated engine is permissible for the remainder of the flight.
The affected GEN HOT light may remain illuminated for the remainder of the flight.
[END]
AOM DASH 8-Q400
3.1-48
[Rev. 16] 7 MAR 2016
3.1.6.3.8
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
AC GENERATOR FAILURE
(Illumination of # 1 AC GEN or # 2 AC GEN - Caution Light)
AC CONTROL GEN Switch (affected) ......................................................................................... OFF then On
Check # 1 AC GEN or # 2 AC GEN caution light out and affected AC generator VOLTS and
LOAD on ELECTRICAL page of MFD.
If caution light remains on:
AC CONTROL GEN Switch (affected) ....................................................................................................... OFF
[END]
3.1.6.3.8.1 FAILURE of # 1 and # 2 AC GENERATORS with PROPELLER DE-ICING SYSTEM ON
(Illumination of # 1 AC GEN and # 2 AC GEN - Caution Light)
NOTE:
The PROP DEICE caution light may also be illuminated.
PROP Selector ........................................................................................................................................... OFF
Condition Levers ...................................................................................................................................... MAX
Operate propellers at MAX / 1020 NP until clear of icing conditions.
AC GEN 1 and 2 Switches ...................................................................................... OFF then On (Individually)
If caution light remains on:
AC GEN Switch (affected) .......................................................................................................................... OFF
-
Exit icing conditions as soon as possible.
[END]
3.1.6.3.9
BATTERY ESSENTIAL SERVICES
CAUTION: Battery duration for operation of Essential Services is 60 min.
The following services are powered with the BATTERY
AUX BATT and MAIN BATT switches OFF:
• ADC 1
• Standby Pitot Heat
• Engine Fire Detection and Extinguishing
• Smoke Detectors
• Aileron Trim Actuation and Indication
• Rudder Trim Actuation and Indication
• Elevator Trim Actuation and Indication
• Flap Control and Indication
• PFCS Indication
• AHRS 1 and 2
• VHF COMM 1
• VHF NAV 1
• Pilot and Co-Pilot Audio
• PA and Cabin Interphone Audio
• Clock 1
• Standby Attitude Indicator or Integrated
Standby Instrument (if installed)
• Circuit Breaker Panel Lights
• Emergency Lights
NOTE:
MASTER switch at BATTERY MASTER, STBY BATT,
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Passenger Signs
Position Lights
Baggage Lights
Storm Lights
Flight compartment Dome Lights
Landing Gear Control and Indication
Engine Ignition and Start
# 1 and # 2 engine oil pressure
# 1 engine fuel temperature
# 1 and # 2 FADECs
# 1 and # 2 PECs
Fuel and Hydraulic Shut-Off Valves
# 1 and # 3 Hydraulic Quantity Indications
# 1, # 2 and # 3 Hydraulic Pressure Indications
# 3 Hydraulic System
# 1 MFD
ED
ICP 1
The following Advisory Lights are inoperative:
RUD 1 PUSH OFF, RUD 2 PUSH OFF, PULL UP GPWS TEST, BELOW G/S, GPWS FLAP
OVERRIDE, TANK 1 AUX PUMP, TANK 2 AUX PUMP and Boot Inflation.
When operating on battery essential services only, # 1 PFD information must be selected on
the # 1 MFD.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.7
FLIGHT CONTROLS
3.1.7.1
ROLL
3.1.7.1.1
ROLL CONTROL JAM
3.1-49
[Rev. 16] 7 MAR 2016
Autopilot .......................................................................................................................................... Disengage
ROLL DISC Handle ............................................................................................................... Pull and Turn 90°
Pull out the ROLL DISC disconnect T-handle and turn it 90°.
Control Wheels ........................................................................................... Both Pilots Attempt Roll Control
-
Pilot with free control wheel will fly the aircraft.
CAUTION: With the ROLL DISC handle pulled, the AP must not be engaged.
If Right Control Wheel free:
-
Roll control will be degraded and forces will be normal.
If continuous illumination of SPLR 1 and SPLR 2 PUSH OFF switchlights:
Illuminated Switchlights ......................................................................................................... Push Both OFF
Check ROLL SPLR INBD HYD and ROLL SPLR OUTBD HYD Caution Lights illuminate and
PFCS indicator shows all spoilers retracted.
NOTE:
The SPLR OUTBD caution light will illuminate below 150 kt IAS, the ROLL SPLR INBD GND
and ROLL SPLR OUTBD GND caution lights will illuminate on landing.
Landing Considerations:
-
Land at airport with minimum crosswind and turbulence using Flap 10° or 15°.
Approach and VREF Speeds:
Flap 10° & 15°.........................
VREF
REF SPEED
INCR ON
VREF + 20
1.40
REF SPEED
INCR ON
1.75
Landing Distance Factor:
Flap 10° & 15°.........................
If Left Control Wheel free:
-
Roll control forces will be low and tendency to over-control should be avoided.
With flap 5°, 10° or 15° selected, if roll control is inadequate:
Airspeed .......................................................................................................................................... 165 kt MAX
Landing Considerations:
-
Land at airport with minimum crosswind and turbulence using Flap 15° or 35°.
[END]
AOM DASH 8-Q400
3.1-50
[Rev. 18] 21 NOV 2016
3.1.7.1.2
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
AILERON TRIM RUNAWAY
Airspeed ............................................................................................................................................... Reduce
Aileron Trim ................................................................................................................... Opposite to Runaway
Push AILERON TRIM switch in direction opposite to runaway.
When trim is at neutral position or if trim actuator cannot be reversed:
Ail Trim Act CB (Left Lower CB Panel - G8) ............................................................................................... Pull
[END]
3.1.7.1.3
ROLL CONTROL MALFUNCTION
(Airplane Rolls with No Control Wheel Input)
•
Apply Roll Control to hold wings level.
If continuos illumination of SPLR 1 or SPLR 2 PUSH OFF switchlights in wings-level flight:
Illuminated Switchlight ................................................................................................................... Push OFF
Check ROLL SPLR INBD HYD or ROLL SPLR OUTBD HYD caution and OFF advisory lights illuminate,
PUSH advisory light out and PFCS indicator on the MFD shows all spoilers retracted.
NOTE:
The SPLR OUTBD caution light will illuminate below 150 kt IAS, the ROLL SPLR INBD GND
or ROLL SPLR OUTBD GND caution light will illuminate on landing.
Landing Considerations:
-
Land at airport with minimum crosswind and turbulence using Flap 10°, 15° or 35°.
Approach and VREF Speeds:
Flap 10° & 15° .........................
Flap 35° ...................................
VREF
VREF
REF SPEED INCR ON
VREF + 20
VREF + 15
1.35
1.35
REF SPEED INCR ON
1.69
1.62
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
If SPLR 1 or SPLR 2 PUSH OFF switchlights do not illuminate continuously in wings-level flight:
Power ....................................................................................................................................................... Apply
Move POWER Levers forward as required
to compensate for increased drag due to a permanently deflected spoiler.
Airspeed .............................................................................................................................................. Increase
Increase airspeed as required to compensate for degraded roll control due to a permanently deflected spoiler.
Landing Considerations:
-
Land at airport with minimum crosswind and turbulence using Flap 10°, 15° or 35°.
Approach and VREF Speeds:
Flap 10° & 15° .........................
Flap 35° ...................................
1.3 VSR
1.3 VSR
REF SPEED INCR ON
1.3 VSR + 20
1.3 VSR + 15
1.50
1.50
REF SPEED INCR ON
1.89
1.80
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.7.1.4
3.1-51
[Rev. 16] 7 MAR 2016
ROLL SPLR INBD HYD or ROLL SPLR OUTBD HYD
(Caution Light)
NOTE:
[with MS 4-110066 or MS 4-126385 Not Incorporated]:
illumination of the ROLL SPLR INBD HYD caution light, at an airspeed of 165 kt IAS or
greater, may be indicative of a spoiler cable failure
(see Sub-Chapter 3.1.7.1.5 next).
Landing Considerations:
Approach and VREF Speeds:
Flap 10° & 15°.........................
Flap 35° ..................................
VREF + 10
VREF + 10
REF SPEED
INCR ON
VREF + 20
VREF + 25
1.50
1.50
REF SPEED
INCR ON
1.69
1.80
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
[END]
3.1.7.1.5
SPOILER CABLE FAILURE - ROLL SPLR INBD HYD and ROLL SPLR OUTBD HYD
(Caution Light)
NOTE:
[with MS 4-110066 or MS 4-126385 Not Incorporated]:
the ROLL SPLR OUTBD HYD caution light will not illuminate until the airspeed is less than
165 kt IAS.
SPLR 1 and 2 Push OFF Switchlights ............................................................................................ Push OFF
Check PFCS indicator shows all spoilers retracted.
NOTE:
The SPLR OUTBD caution light will illuminate below 150 kt IAS, the ROLL SPLR INBD GND
and ROLL SPLR OUTBD GND caution lights will illuminate on landing.
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence using Flap 10° or 15°.
Approach and VREF Speeds:
Flap 10° & 15°.........................
VREF
REF SPEED
INCR ON
VREF + 20
1.40
REF SPEED
INCR ON
1.75
Landing Distance Factor:
Flap 10° & 15°.........................
[END]
AOM DASH 8-Q400
3.1-52
[Rev. 16] 7 MAR 2016
3.1.7.1.6
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ROLL SPLR INBD GND or ROLL SPLR OUTBD GND
(Caution Light)
Landing Considerations:
-
Affected Inboard or Outboard Roll Spoilers may not extend at touch-down.
Approach and VREF Speeds:
Flap 10° & 15° .........................
Flap 35° ...................................
VREF
VREF
REF SPEED
INCR ON
VREF + 20
VREF + 15
1.35
1.35
REF SPEED
INCR ON
1.69
1.62
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
[END]
3.1.7.1.7
SPLR OUTBD
(Caution Light)
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.7.2
PITCH
3.1.7.2.1
PITCH CONTROL JAM
3.1-53
[Rev. 16] 7 MAR 2016
Autopilot .......................................................................................................................................... Disengage
Flap and Airspeed .................................................................................................... Maintain at Time of Jam
Maintain flap setting and approximate airspeed at time pitch jam occurred.
Control Columns .................................................................................................. Attempt to Overcome Jam
Both pilots should attempt to maintain control by increased column force against the jam.
If unable to overcome jam:
• Relax control column force.
PITCH Disconnect Handle ................................................................................................... Pull and Turn 90°
Pull out the PITCH disconnect T-handle and turn it 90°.
Elevator forces will be lighter than normal and pitch control degraded.
Control Columns ...................................................................................... Both Pilots Attempt Pitch Control
- Pilot with free control column will have pitch control.
CAUTION: With the PITCH disconnect handle pulled, the AP must not be engaged.
NOTE:
MAX airspeed is 170 KIAS or speed at which jam occurred, whichever is higher.
Landing Considerations:
- Land at an airport with minimum crosswind and turbulence using Flap 10° or 15°.
Approach and VREF Speeds:
Flap 10° & 15°.........................
VREF
REF SPEED INCR ON
VREF + 20
1.35
REF SPEED INCR ON
1.69
Landing Distance Factor:
Flap 10° & 15°.........................
[END]
3.1.7.2.2
ELEVATOR FEEL and PITCH TRIM and SPLR OUTBD and RUD CTRL (Caution Lights)
Autopilot .......................................................................................................................................... Disengage
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
3.1.7.2.3
ELEVATOR ASYMMETRY (Caution Light)
Autopilot .......................................................................................................................................... Disengage
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
3.1.7.2.4
ELEVATOR PRESS (Caution Light)
HYD Press # 3 ......................................................................................................................................... Check
Check the # 3 system hydraulic pressure on the MFD - Hydraulic systems page.
If pressure indicated:
HYD # 3 ISOL VLV .................................................................................................................................. NORM
Make sure the green OPEN light on the HYD # 3 ISOL VLV switchlight is not on.
If caution light remains illuminated:
- Maintenance action required prior to next flight.
[END]
3.1.7.2.5
ELEVATOR FEEL (Caution Light)
Autopilot .......................................................................................................................................... Disengage
Airspeed .................................................................................................................................. 200 KIAS (MAX)
[END]
AOM DASH 8-Q400
3.1-54
[Rev. 16] 7 MAR 2016
3.1.7.2.6
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
PITCH TRIM
(Caution Light)
Autopilot .......................................................................................................................................... Disengage
ELEVATOR TRIM ................................................................................................................................ Activate
Select a small amount of NOSE UP or NOSE DN elevator trim
while maintaining the airplane in steady state and confirm change in elevator force.
NOTE:
Elevator Trim pointer may indicate full NU trim position with caution light illuminated.
If Elevator Trim is operative:
Autopilot ............................................................................................................................... Engage As Req’d
If Elevator Trim is inoperative:
• Maintain airplane configuration and airspeed as long as practicable.
NOTE:
If the pitch trim fails on take-off with Flap 10° or 15°, it is recommended that the landing be
conducted with the take-off flap setting.
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence.
Minimum Approach and VREF Speeds .............................................................................................. 1.23 VSR
NOTE:
During the airspeed deceleration to VFE, the elevator force will increase.
When decelerating from VMO with flap 0°, the elevator force may be as high as 18 kg (40 lb)
until flap is extended.
[END]
3.1.7.2.7
ELEVATOR TRIM SWITCH FAILURE
(Illumination of ELEVATOR TRIM SHUT OFF Switchlight and
Audio Tone for ELEVATOR TRIM in motion)
ELEVATOR TRIM SHUT OFF ......................................................................................................... Press OFF
Observe OFF advisory light remains illuminated and PUSH advisory light out.
NOTE:
•
Maintain airplane configuration and airspeed as long as practicable.
NOTE:
•
ELEVATOR TRIM indicator will indicate full NU trim position.
If pitch trim fails on take-off with Flap 10° or 15°, it is recommended that the landing be
conducted with the take-off flap-setting.
Do Not engage autopilot.
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence.
Minimum Approach and VREF Speeds .............................................................................................. 1.23 VSR
NOTE:
During the airspeed deceleration to VFE, the elevator force will increase.
When decelerating from VMO with flap 0°, the elevator force may be as high as 18 kg (40 lb)
until flap is extended.
[END]
3.1.7.2.8
ELEVATOR TRIM INDICATOR FAILURE
(Elevator Trim Pointer indicates off-scale ND)
ELEVATOR TRIM ....................................................................................................................... Use As Req’d
NOTE:
Maintenance action required prior to next flight.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.7.3
FLAPS
3.1.7.3.1
ABNORMAL FLAP LANDING
3.1-55
[Rev. 16] 7 MAR 2016
(FLAP 0° or FLAP 5°)
GPWS Flap Override ............................................................................................................................... Press
Lift the plastic guard and push the GPWS Flap Override switchlight.
Make sure the amber light turns on.
At 1000 ft AGL:
Autopilot .......................................................................................................................................... Disengage
Landing Considerations:
Approach and VREF Speeds:
Flap 0° ....................................
Flap 5° ....................................
VREF
VREF
REF SPEED
INCR ON
VREF + 25
VREF + 20
2.0
2.0
REF SPEED
INCR ON
2.50
2.50
Landing Distance Factor:
Flap 0° (use Flap 35° chart) ....
Flap 5° (use Flap 35° chart) ....
CAUTION: Pitch attitudes greater than 6° in the landing flare may cause the fuselage to contact the
runway.
Do Not select POWER levers below FLIGHT IDLE until IAS is below 150 kt.
NOTES:
Power should be reduced gradually to achieve FLIGHT IDLE at or just prior to touchdown.
To decrease the landing descent rate and not exceed a pitch attitude of 6° when the landing
descent rate is higher than desired, power will be required in the landing flare through to touchdown.
To decrease the landing descent rate at airport altitudes greater than 5000 ft, it may be necessary to maintain power in the landing flare through to touchdown.
High landing speeds, due to this abnormal procedure, may result in Brake Kinetic Energy limits
being exceeded.
The nosewheel should be promptly brought into contact with the runway following mainwheel
contact.
[END]
3.1.7.3.2
ABNORMAL FLAP LANDING
(FLAP INDICATED POSITION between 10°, 15° or 35°)
Landing Considerations:
Calculate performance and reference airspeeds appropriate to the smaller flap angle.
[END]
AOM DASH 8-Q400
3.1-56
[Rev. 16] 7 MAR 2016
3.1.7.3.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
FLAP DRIVE
(Caution Light)
•
No crew action required.
NOTE:
Flap may continue to operate normally and may be used to complete the flight.
If Flap fails between gated positions, the smaller flap angle must be used when calculating
landing performance.
Landing Considerations:
-
See appropriate ABNORMAL FLAP LANDING procedure above (Sub-Chapter 3.1.7.3.1 & 2).
[END]
3.1.7.3.4
FLAP POWER
(Caution Light)
(Flap System Failure)
FLAPS Lever ................................................................................................... Select to match Flap Position
Select FLAPS Lever to the flap gate appropriate to the FLAP indication on # 2 MFD.
NOTE:
Ensure the FLAPS lever release trigger is fully engaged in the appropriate flap gate.
FLAPS CONT CB (Left Lower CB Panel - L7) ............................................................................................. Pull
Pull out FLAPS CONT circuit breaker, wait 2 s, then push in.
Check FLAP POWER caution light out.
NOTE:
FLAPS CONT circuit breaker (L7) is limited to one reset.
FLAPS Lever ........................................................................................................................................... Select
Select FLAPS Lever to the desired flap setting.
Check for appropriate FLAP indication on # 2 MFD.
NOTE:
Delay the selection of the FLAPS lever for a minimum of 20 s following reset of the FLAPS
CONT circuit breaker.
Ensure the FLAPS lever release trigger is fully engaged in the appropriate flap gate.
If the FLAP POWER caution light remains illuminated:
•
No operation of flap is available and flap will remain in last selected position.
NOTE:
-
If flap fails between gated positions, the smaller flap angle must be used when calculating
landing performance.
See appropriate ABNORMAL FLAP LANDING procedure (Sub-Chapter 3.1.7.3.1 & 2).
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.7.4
RUDDERS
3.1.7.4.1
RUDDER JAM
3.1-57
[Rev. 16] 7 MAR 2016
(Restricted Rudder Pedal Movement)
Affected Rudder Pedal ....................................................................................... Apply a normal Push Force
If rudder pedal moves as required:
Affected Rudder Pedal .......................................... Reduce Push Force and Allow Rudder Pedal to Centre
WARNING: Should the rudder pedal (rudder jam) suddenly break free,
Do Not apply rudder pedal input in the opposite direction.
•
Use rudder pedals as required.
If rudder pedal does not respond to normal push force (rudder remains jammed or rudder jam re-occurs):
•
Use Roll Control as req’d for directional control.
MIN Airspeed ...................................................................................................................................... 1.23 VSR
Nosewheel Steering ................................................................................................................................... OFF
Land at an airport with no known or forecast icing conditions and
with minimum crosswind and turbulence using Flap 10°, 15° or 35°.
NOTE:
If rudder jam occurs on take-off and conditions permit, return for landing on the take-off
runway.
Landing Distance Factor:
Flap 10°, 15° & 35° .................
1.40
REF SPEED
INCR ON
N/A
Power ................................................................................................... Maintain As Required to Touchdown
NOTE:
Small amounts of asymmetric power may be used to maintain directional control on approach.
After landing, use asymmetric braking and power, as required, to maintain directional control.
After the airplane has come to a stop:
Nosewheel Steering .................................................................................................................................... ON
Use tiller for directional control.
[END]
3.1.7.4.2
RUD 1 PUSH OFF or RUD 2 PUSH OFF
(Switchlight ON)
Illuminated Switchlight ........................................................................................................................... Press
Push illuminated RUD 1 or RUD 2 switchlight.
Observe illumination of # 1 RUD HYD or # 2 RUD HYD caution lights turn on.
[END]
AOM DASH 8-Q400
3.1-58
[Rev. 16] 7 MAR 2016
3.1.7.4.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
# 1 RUD HYD or # 2 RUD HYD
(Caution Light)
If Not associated with an engine shut-down or hydraulic system failure or Rudder Push OFF switchlight:
•
No crew action required.
NOTE:
Maintenance action required prior to next flight.
If associated with other caution lights, then follow procedures for those appropriate caution
lights.
[END]
3.1.7.4.4
RUD CTRL
(Caution Light)
Airspeed ................................................................................................................................. 200 KIAS (MAX)
Landing Considerations:
-
Maximum crosswind for landing is 20 kt.
[END]
3.1.7.4.5
RUDDER TRIM ACTUATOR RUNAWAY
RUDDER TRIM ............................................................................................................... Opposite to Runaway
Apply opposite rudder and attempt to reverse trim with RUDDER TRIM switch.
When trim is at the neutral position or if the trim actuator cannot be reversed:
RUD TRIM ACT CB (Left Lower CB Panel - F7) .......................................................................................... Pull
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.8
FUEL SYSTEM
3.1.8.1
# 1 TANK FUEL LOW or # 2 TANK FUEL LOW
3.1-59
[Rev. 16] 7 MAR 2016
(Caution Light)
Fuel Quantity .......................................................................................................................................... Check
Check the fuel quantity on the MFD - Fuel page.
Affected tank fuel content is low:
•
Check for external and internal fuel leaks.
NOTE:
A check of the cabin will be necessary to identify a possible internal fuel leak.
No indication of a fuel leak:
•
Transfer fuel from unaffected tank.
See Fuel Transfer (Sub-Chapter 2.5.5.2).
•
Monitor fuel quantity.
Fuel leak confirmed:
•
Shut down engine on affected side.
See ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
Affected tank fuel content is normal:
•
Maintain level attitude as much as possible.
TANK 1 or 2 AUX PUMP Switch (affected side) .......................................................................................... ON
Check appropriate TANK AUX PUMP ON advisory light illuminates.
•
Monitor fuel quantity.
When associated ENG FUEL PRESS caution light illuminates:
•
Shut down engine on affected side.
See ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
3.1.8.2
# 1 ENG FUEL PRESS or # 2 ENG FUEL PRESS
(Caution Light)
TANK 1 or 2 AUX PUMP Switch (affected side) .......................................................................................... ON
Check selected TANK AUX PUMP ON advisory light illuminates and
affected ENG FUEL PRESS caution light out.
If Caution Light remains on:
TANK 1 or 2 AUX PUMP Switch (affected side) ......................................................................................... OFF
Check appropriate TANK AUX PUMP ON advisory light out.
•
Check for external leaks and for fuel odor within airplane.
If either is confirmed, complete ENGINE FAIL / FIRE / SHUT-DOWN (Sub-Chapter 3.1.2.28).
[END]
AOM DASH 8-Q400
3.1-60
[Rev. 16] 7 MAR 2016
3.1.8.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ABNORMAL FUEL TEMPERATURE
(Fuel Temperature Indication on ED Above or Below Normal Operating Range)
TANK 1 or 2 AUX PUMP Switch (affected side) .......................................................................................... ON
-
Check appropriate TANK AUX PUMP ON advisory light illuminates.
-
Continue flight. Monitor affected engine performance.
-
Maintenance action required prior to next flight.
[END]
3.1.8.4
-
ABNORMAL FUEL TANK TEMPERATURE
(Fuel Tank Temperature Colder than Allowable Minimum Fuel Temperature)
Monitor Fuel Tank Temperature indication on MFD.
Where conditions permit:
-
Maneuver to a warmer air mass
-
Increase engine power
3.1.8.5
FUEL TRANSFER FAILURE
If failure of TANK AUX PUMP advisory light to illuminate:
TANK 1 or 2 AUX PUMP Switch (affected side) .......................................................................................... ON
Check selected TANK AUX PUMP ON advisory light illuminates and
appropriate TANK AUX PUMP indication appears on FUEL page of MFD.
When Transfer is complete:
TANK 1 or 2 AUX PUMP Switch (affected side) ........................................................................................ OFF
Check appropriate TANK AUX PUMP ON advisory light out and
appropriate TANK AUX PUMP indication off, on FUEL page of MFD.
If failure of One or Both TRANSFER VALVES to open:
FUEL TRANSFER ....................................................................................................................................... OFF
NOTE:
Consider the effects of fuel maximum lateral asymmetry or fuel low level.
Maximum fuel imbalance is indicated by the FUEL quantity readout on ED and fuel gauge
pointers on FUEL page of MFD changing from white to amber and [BALANCE] appears
flashing on ED.
[END]
3.1.8.6
•
# 1 FUEL FLTR BYPASS or # 2 FUEL FLTR BYPASS
(Caution Light)
No crew action required.
NOTE:
Monitor fuel flow, ITT and NH.
If erratic, may indicate contamination has passed filter.
[END]
3.1.8.7
•
FUELING ON
(Caution Light)
No crew action required.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.9
HYDRAULIC POWER
3.1.9.1
# 1 and # 2 HYDRAULIC SYSTEMS FAILURE
3.1-61
[Rev. 16] 7 MAR 2016
(# 1 HYD PRESS and # 2 HYD PRESS indicating no pressure)
Pre-landing:
Autopilot / Yaw Damper .................................................................................................................. Disengage
Maximum Airspeed ........................................................................................................................... 200 KIAS
Use aileron, elevator and
if required for directional control, small inputs of asymmetric power, to control the aircraft.
If Flap a 0° or 5°:
GPWS .......................................................................................................................................... Flap Override
Lift the plastic guard and push the GPWS Flap Override switchlight.
Make sure the amber light illuminates.
Lost Services:
-
All hydraulically powered services except elevator.
Landing Considerations:
-
Land at an airport with minimum crosswind and turbulence.
-
Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1)
when required.
-
Align aircraft with runway using asymmetric power prior to lowering the nosewheel to the runway.
-
Nosewheel steering will be inoperative.
To maintain directional control, significant asymmetric power will be required.
-
Emergency braking only with limited applications available.
Use of maximum reverse power for stopping may cause directional deviation.
Approach and VREF Speeds:
Flap 0° ..........................................
Flap 5° ..........................................
Flap 10° & 15°...............................
Flap 35° ........................................
1.23 VSR + 10
1.23 VSR + 10
VREF + 10
VREF + 10
REF SPEED
INCR ON
1.23 VSR + 25
1.23 VSR + 20
VREF + 20
VREF + 25
2.65
1.85
1.85
REF SPEED
INCR ON
2.90
2.10
2.20
Landing Distance Factor:
Flap 0° & 5° (use Flap 35° chart) ..
Flap 10° & 15°...............................
Flap 35° ........................................
CAUTION: Pitch attitudes greater than 6° in the landing flare may cause the fuselage to contact the
runway.
Unless required for immediate directional control,
Do Not select Power Levers below Flight Idle until IAS is below 150 kt.
Excessive application of emergency braking can result in skidding and tire failure.
[END]
AOM DASH 8-Q400
3.1-62
[Rev. 16] 7 MAR 2016
3.1.9.2
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
# 1 HYDRAULIC SYSTEM FAILURE
(Loss of All Fluid from the # 1 Hydraulic System)
(# 1 ENG HYD PUMP and # 1 HYD ISO VLV - Caution Lights and
ENGINE 1 HYD valve CLOSED Advisory Light and no Quantity indicated on # 1 HYD QTY)
NOTE:
# 1 HYD ISO VLV caution light may go out with very low hydraulic fluid quantity in the # 1
hydraulic system.
HYD # 3 ISOL VLV .................................................................................................................................... Open
Push the HYD # 3 ISOL VLV switchlight and confirm the OPEN advisory light illuminates and
pressure is indicated on # 3 HYD PRESS indication on # 2 MFD.
STBY HYD PRESS ................................................................................................................................ Normal
If Flap a 0° or 5°:
GPWS .......................................................................................................................................... Flap Override
Lift the plastic guard and push the GPWS Flap Override switchlight.
Make sure the amber light illuminates.
At 1000 ft AGL:
Autopilot .......................................................................................................................................... Disengage
Lost Services:
-
Inboard Roll Spoilers
-
Flap
-
Wheel brakes and Anti-Skid
-
# 1 Rudder system
-
# 1 Elevator system
Landing Considerations:
-
Emergency braking only.
Approach and VREF Speeds:
Flap 0° .....................................
Flap 5°, 10° & 15°....................
Flap 35° ...................................
VREF + 10
VREF + 10
VREF + 10
REF SPEED
INCR ON
VREF + 25
VREF + 20
VREF + 25
2.65
1.85
1.85
REF SPEED
INCR ON
2.90
2.10
2.20
Landing Distance Factor:
Flap 0° & 5° (use Flap 35° chart) .
Flap 10° & 15° ..............................
Flap 35° ........................................
CAUTION: Pitch attitudes greater than 6° in the landing flare may cause the fuselage to contact the
runway.
Do Not select Power Levers below Flight Idle until IAS is below 150 kt.
Excessive application of emergency braking can result in skidding and tire failure.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.9.3
3.1-63
[Rev. 16] 7 MAR 2016
# 2 HYDRAULIC SYSTEM FAILURE
(Loss of All Fluid from the # 2 Hydraulic System)
(# 2 ENG HYD PUMP and # 2 HYD ISO VLV - Caution Lights and
ENGINE 2 HYD valve CLOSED Advisory Light and no Quantity indicated on # 2 HYD QTY)
NOTE:
# 2 HYD ISO VLV caution light may go out with very low hydraulic fluid quantity in the # 2
hydraulic system.
HYD # 3 ISOL VLV .................................................................................................................................... Open
Push the HYD # 3 ISOL VLV switchlight and confirm the OPEN advisory light illuminates and
pressure is indicated on # 3 HYD PRESS indication on # 2 MFD.
PTU CNTRL ........................................................................................................................................... Normal
Push the PTU CNTRL switchlight and make sure the green ON light goes off.
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473) Not Incorporated] carry out the
following 2 steps:
HYD PWR XFER CB (Right Lower CB Panel - L8) ................................................................................. Pull
STBY HYD PRESS ................................................................................................................................... ON
Push the STBY HYD PRESS switchlight and confirm the green ON light illuminates.
Check STBY HYD PRESS (2800 - 3000 psi) on # 2 MFD.
NOTE:
The standby hydraulic pump must remain selected on for the duration of the flight.
Lost Services:
-
Outboard Roll Spoilers
-
Normal Landing Gear Retraction and Extension
-
Nosewheel Steering
-
Emergency / Parking Brake (if PK BRK indication shows depleted pressure)
-
# 2 Rudder system
-
# 2 Elevator system
Landing Considerations:
-
Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1)
when required.
Approach and VREF Speeds:
Flap 10° & 15°.........................
Flap 35° ..................................
VREF + 10
VREF + 10
REF SPEED
INCR ON
VREF + 20
VREF + 25
1.85
1.85
REF SPEED
INCR ON
2.10
2.20
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
[END]
AOM DASH 8-Q400
3.1-64
[Rev. 16] 7 MAR 2016
3.1.9.4
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
# 1 HYDRAULIC SYSTEM QUANTITY BELOW NORMAL
(# 1 HYD ISO VLV - Caution Light)
•
Monitor quantity in # 1 Hydraulic system for further loss of fluid.
Lost Services:
-
Inboard Roll Spoilers
-
Wheel brakes and Anti-Skid
Landing Considerations:
-
Emergency braking only.
Approach and VREF Speeds:
Flap 10° & 15° .........................
Flap 35° ...................................
VREF + 10
VREF + 10
REF SPEED
INCR ON
VREF + 20
VREF + 25
1.85
1.85
REF SPEED
INCR ON
2.10
2.20
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
CAUTION: Excessive application of emergency braking can result in skidding and tire failure.
[END]
3.1.9.5
# 1 ENG HYD PUMP
(Caution Light)
(No Pressure may be indicated in the # 1 Hydraulic System)
STBY HYD PRESS ....................................................................................................................................... ON
Push the STBY HYD PRESS switchlight and confirm the green ON light illuminates.
Check STBY HYD PRESS (2800 - 3000 psi) on # 2 MFD.
•
Monitor pressure and quantity in # 1 Hydraulic system for normal indications.
NOTES:
1. Prior to the selection of the Standby Hydraulic Pump, the # 1 HYD ISO VLV caution light
may illuminate following the loss of the # 1 Engine Hydraulic Pump.
2. With # 1 hydraulic system pressure from the standby hydraulic pump only, the rate of flap
extension and retraction is decreased.
3. Hydraulic pressure will be indicated on the # 3 Hydraulic system until normal pressure is
restored in the # 1 Hydraulic system.
Landing Considerations:
-
Flap extension and retraction is slower than normal.
CAUTION: With # 1 ENG HYD PUMP caution light illuminated, Do Not select PTU CNTRL to ON.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.9.6
3.1-65
[Rev. 18] 21 NOV 2016
# 2 HYDRAULIC SYSTEM QUANTITY BELOW NORMAL
(# 2 HYD ISO VLV - Caution Light)
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Not Incorporated] carry out the
following 2 steps:
PTU CNTRL ....................................................................................................................................... Normal
Push the PTU CNTRL switchlight and make sure the green ON light goes off
HYD PWR XFER CB (Right Lower CB Panel - L8) ................................................................................. Pull
•
Monitor quantity in # 2 Hydraulic system for further loss of fluid.
Lost Services:
-
Outboard Roll Spoilers
-
Normal Landing Gear retraction and extension
-
Nosewheel steering
-
Emergency / Parking Brake (if PK BRK indication shows depleted pressure)
Landing Considerations:
-
Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1)
when required.
Approach and VREF Speeds:
Flap 10° & 15°.........................
Flap 35° ..................................
VREF + 10
VREF + 10
REF SPEED
INCR ON
VREF + 20
VREF + 25
1.85
1.85
REF SPEED
INCR ON
2.10
2.20
Landing Distance Factor:
Flap 10° & 15°.........................
Flap 35° ..................................
[END]
3.1.9.7
# 2 ENG HYD PUMP
(Caution Light)
(No Pressure may be indicated in the # 2 Hydraulic System)
PTU CNTRL .................................................................................................................................................. ON
Push the PTU CNTRL switchlight and make sure the green ON light illuminates and
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated]:
PTU pressure (green bars) illuminates.
•
Monitor pressure and quantity in # 2 Hydraulic system for normal indications.
NOTES:
1. Prior to the selection of the PTU, the # 2 HYD ISO VLV caution light may illuminate
following the loss of the # 2 Engine Hydraulic Pump.
2. Hydraulic pressure will be indicated on the # 3 Hydraulic system until normal pressure is
restored in the # 2 Hydraulic system.
[END]
AOM DASH 8-Q400
3.1-66
[Rev. 16] 7 MAR 2016
3.1.9.8
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
# 1 HYD FLUID HOT or # 2 HYD FLUID HOT
(Caution Light)
Pressure and Quantity ......................................................................................................................... Monitor
Monitor pressure and quantity of affected hydraulic system on the MFD.
[END]
3.1.9.9
# 1 STBY HYD PUMP HOT
(Caution Light)
If flap selector lever set at 0°:
STBY HYD PRESS ................................................................................................................................... Norm
Push the STBY HYD PRESS switchlight and confirm the green ON light turns off.
If Flap Selector Lever is set > than 0°:
•
No crew action required.
[END]
3.1.9.10
# 3 HYD PUMP
(Caution Light)
•
No crew action required.
NOTE:
Maintenance action required prior to next flight.
[END]
3.1.9.11
PTU FAILURE
[with MS 4-126425 or (MS 4-126354 and (MS 4-901472 or MS 4-901473)) Incorporated]
(Illumination of PTU CNTRL FAIL advisory light)
PTU CNTRLNorm
Push the PTU CNTRL switchlight and make sure the green ON light goes off
CAUTION: PTU CNTRL Must Not be selected ON following illumination of PTU CNTRL FAIL
advisory light.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.10
ICE and RAIN PROTECTION
3.1.10.1
DEICE PRESS
(Caution Light)
3.1-67
[Rev. 18] 21 NOV 2016
AIRFRAME MODE SELECT Selector ............................................................................................... MANUAL
After 10 s:
AIRFRAME MODE SELECT Selector ........................................................................................ SLOW / FAST
If the DEICE PRESS Caution light persists:
BOOT AIR Switch ........................................................................................................................................ ISO
Move the BOOT AIR ISOLATE Switch to ISO.
DEICE PRESS Indicator ......................................................................................................................... Check
Check the pressure in the # 1 and # 2 system on the co-pilot's side console.
ICE PROTECTION Panel ................................................................................... Check Boot Advisory Lights
If the indicated pressure on each dial Is Not 18 ± 3 psi or 2 or more Deice Boot lights, on the same side, fail to
illuminate:
AIRFRAME MODE SELECT Selector ............................................................................................... MANUAL
AIRFRAME MANUAL SELECT Selector ................................................................................ Tail and Engine
Rotate through Tail and Engine Intake positions.
CAUTION: Do Not select the WING positions during manual de-icing of the tail and engine intake.
NOTE:
-
Only the Engine Intake Boot on the side with normal pressure will be de-iced.
For the failed side, refer to ENGINE INTAKE BOOT FAILURE below (Sub-Chapter 3.1.10.2).
Dwell period at each Tail and Engine Intake position should be approximately 6 s.
Exit and Avoid icing conditions as soon as possible.
If the indicated pressure on each dial Is 18 ± 3 psi and only 1 of the Deice Boot advisory lights # 1 or # 2 fails to
illuminate or both # 3 de-ice advisory lights fail to illuminate or both # 4 advisory lights fail to illuminate:
NOTE:
-
If the failed Deice Boot is associated with an Engine Intake Boot, refer to ENGINE INTAKE
BOOT FAILURE below (Sub-Chapter 3.1.10.2).
Exit and Avoid icing conditions as soon as possible.
Holding, Approach and Landing Considerations for BOTH of the above failures:
If landing in icing conditions or the aircraft is not aerodynamically clean after leaving icing conditions:
- Land with Flaps 10° or 15°
Minimum Holding Speed (Flap 0°) ......................................................................................................... 190 kt
Speed Corrections:
Flap
0°
5°
10°
15°
Landing Distance Factor:
Flap 10° & 15°.........................
[END]
AOM DASH 8-Q400
VAPP
(kt)
+ 30
+ 30
+ 25
1.80
VGA
(kt)
+ 30
+ 30
+ 25
VREF
(kt)
+ 30
+ 25
HOLDING
(kt)
≥ 190
-
3.1-68
[Rev. 18] 21 NOV 2016
3.1.10.2
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ENGINE INTAKE BOOT FAILURE
For remainder of flight (affected engine):
Engine Intake Door .................................................................................................................................. Open
Push ENGINE INTAKE BYPASS switchlight.
Make sure that the affected OPEN / HTR advisory light illuminates.
-
Exit icing conditions as soon as possible.
[END]
3.1.10.3
DEICE TIMER (Caution Light)
De-ice Boots Advisory Lights ............................................................................................................. Monitor
The correct sequence is as follows:
ICE PROTECTION
6
5
TAIL
5
6
AIRFRAME
OFF MANUAL
SELECT
AIRFRAME MODE SELECT
OFF
SLOW
MANUAL
FAST
1
2
4
3
WING
4
5
3
2
1
6
NOTE
Manual switch positions and
related indicator light
sequence correspond with
deice boot inflation sequence
shown below. Numbers do
not actually appear on panel.
6
5
1
2
3
6 4
3
5 4
2
1
fs numb
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-69
[Rev. 18] 21 NOV 2016
DEICE TIMER (Caution Light) (cont’d)
If Sequencing is NOT correct:
AIRFRAME MODE SELECT Selector ............................................................................................... MANUAL
Turn the AIRFRAME MODE SELECT switch to the manual position.
AIRFRAME MANUAL SELECT Selector .............................................................................. Cycle (As Req'd)
De-ice manually positions 1 through 6 using the AIRFRAME MANUAL SELECT switch on the ICE AND RAIN
PROTECTION panel. Pause for approximately 6 s at each position.
-
Exit icing conditions as soon as possible.
NOTE:
Dwell period at each position should be approximately 6 s.
Allow for a dwell period of not less than 24 s before commencing subsequent inflation of boots.
[END]
3.1.10.4
PROP DEICE
(Caution Light)
PROP Selector ............................................................................................................................. OFF then ON
NOTE:
Only one reset of the PROP selector switch is allowed.
If PROP DEICE caution light out:
•
Monitor PROPS advisory light for normal operation.
If PROP DEICE caution light remains illuminated:
Condition Levers ....................................................................................................................................... MAX
Operate propellers at MAX / 1020 NP until clear of icing conditions.
-
Exit icing conditions as soon as possible.
NOTES:
1. PROP selector must remain ON until clear of icing conditions.
2. [with MS 4-126150 or MS 4-126172 or MS 4-121109 or MS 4-121281 Not Incorporated]:
With an engine shut-down and propeller de-ice selected, the PROP DEICE caution light will
illuminate.
Confirm functioning of the propeller de-ice system of the operating engine by observing
PROPS advisory light (operating engine) illuminates and goes out repeatedly.
[END]
3.1.10.5
WSHLD HOT
(Caution Light)
WINDSHIELD HEAT ......................................................................................................................... WARM UP
Turn the WINDSHIELD HEAT selector to WARM UP.
-
Exit and avoid icing conditions as soon as possible.
[END]
3.1.10.6
SIDE WDO HOT
(Caution Light)
Pilot Side WDO / HT ................................................................................................................................... OFF
Set PLT SIDE WDO / HT switch to the OFF position.
[END]
AOM DASH 8-Q400
3.1-70
[Rev. 18] 21 NOV 2016
3.1.10.7
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
WSHLD CTRL
(Caution Light)
-
Exit and avoid icing conditions as soon as possible.
[END]
3.1.10.8
WINDSHIELD WIPER SWITCH FAILURE
ALTERNATE PILOT WIPER Switch ............................................................................................................ ON
Check pilot’s side windshield wiper operates in high mode.
[END]
3.1.10.9
ICE DETECT FAIL
(Caution Light)
•
Monitor windshield wipers’ ice detection posts and wing leading edge to determine icing conditions.
[END]
3.1.10.10
ENG ADPT HEAT 1 or ENG ADPT HEAT 2
(Caution Light)
•
Monitor affected engine performance.
-
Exit and avoid icing conditions as soon as possible.
[END]
3.1.10.11
ENGINE OIL TEMPERATURE BELOW 65°C
(Propeller De-Icing ON In Flight)
•
Monitor affected engine performance.
-
Exit icing conditions as soon as possible.
[END]
3.1.10.12
PITOT HEAT 1 or PITOT HEAT 2 or PITOT HEAT STBY
(Caution Light)
Pitot-Static Switch (affected) .................................................................................................... 1 or 2 or STBY
Make sure affected PITOT-STATIC switch is to 1, 2 or STBY ON.
If caution light remains on or if there are abnormal indications of airspeed or altitude on the pilot’s or co-pilot’s
PFD:
EFIS ADC SOURCE Selector ..................................................................................... Select 1 or 2 (As Req’d)
[END]
3.1.10.13
# 1 STALL SYST FAIL or # 2 STALL SYST FAIL and PUSHER SYST FAIL
(Caution Light)
Minumum Airspeed (exception GA and Enroute Climb) .................................................................... 1.23 VSR
for all flap settings OR maintain airspeed appropriate for icing conditions and other failures if applicable
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.10.14
3.1-71
[Rev. 18] 21 NOV 2016
PUSHER SYST FAIL
(Caution Light)
STICK PUSHER SHUT OFF Switch ................................................................... Press OFF (Pilot or Co-Pilot)
Observe illumination of OFF advisory light.
Minumum Airspeed (exception GA and Enroute Climb) .................................................................... 1.23 VSR
for all flap settings OR maintain airspeed appropriate for icing conditions and other failures if applicable
[END]
3.1.10.15
FLIGHT IN SEVERE ICING
Autopilot ................................................................................................................... Disconnect Immediately
CAUTION: Be prepared for a possible roll force requirement by firmly holding the control wheel
prior to disconnecting the autopilot.
Condition Levers ............................................................................................................................ MAX / 1020
POWER Levers ......................................................................................................... Adjust As Req’d to MCP
Minimum Airspeed ............................................................................................................................ 190 KIAS
•
Exit severe icing conditions by changing altitude and / or course as required.
CAUTION: Avoid aggressive maneuvering.
When clear of icing conditions:
NOTE:
It can be assumed that the airplane is no longer affected by the severe ice encountered when
the ice accumulated on the flight compartment side window is removed.
When visible, other surfaces, such as the propeller spinner and wing leading edges aft of the
deicer boots, should also be used to confirm that the ice accumulated during the severe icing
encounter has cleared.
POWER Levers and Condition Levers ................................................................................. Adjust As Req’d
Airspeed ............................................................................................................................................. As Req’d
Autopilot ............................................................................................................................................ As Req’d
CAUTION: Prior to engaging the autopilot, ensure that in wings level steady state flight, there is no
abnormal roll control force and the required lateral trim is appropriate for the aircraft
configuration.
Refer to Sub-Chapter 2.16, Ice Protection Procedures, as appropriate for holding, approach and landing.
If it cannot be determined that the aircraft is no longer affected by the severe icing encounter:
Autopilot .................................................................................................................................. Do Not Engage
[END]
AOM DASH 8-Q400
3.1-72
[Rev. 16] 7 MAR 2016
3.1.11
NOTE:
3.1.11.1
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
LANDING GEAR
Following any landing gear retraction or extension malfunction not covered by a specific
procedure in this section, the landing gear must be extended using the Alternate Landing Gear
Extension procedure that follows.
ALTERNATE LANDING GEAR EXTENSION or LDG GEAR INOP (Caution Light)
(One or more Landing Gear fail to extend)
Airspeed ................................................................................................................................. 185 KIAS (MAX)
L/G Down Select Inhibit Switch .......................................................................................................... INHIBIT
Lift switch guard and
set L/G DOWN SELECT INHIBIT SW, on the co-pilot’s flight compartment ceiling, to INHIBIT.
NOTE:
If LDG GEAR INOP caution light was out, it will illuminate when the L/G DOWN SELECT
INHIBIT SW is selected to INHIBIT.
Landing Gear Selector ................................................................................................................................ DN
Landing Gear Alternate Release Door .......................................................................................... Open Fully
Pull open fully the MAIN LANDING GEAR ALTERNATE RELEASE door, on the flight compartment ceiling.
NOTE:
Door must stay fully open after alternate landing gear extension.
Main Gear Release Handle ..................................................................................................... Pull Fully Down
Pull the MAIN LANDING GEAR RELEASE handle fully down
to release main gear door uplocks and main gear.
Check L DOOR and R DOOR amber doors open and
LEFT and RIGHT green locked down advisory lights illuminate.
NOTE:
The Main Gear release handle pull force will be significantly higher than experienced during
practice alternate landing gear extensions.
The required pull force, to release the Main Gear uplocks, can be as high as 41 kg (90 lb).
It may require a repeated pull effort to achieve a Main Landing Gear down and locked indication.
Landing Gear Alternate Extension Door ...................................................................................... Open Fully
Open fully the LANDING GEAR ALTERNATE EXTENSION door on the flight compartment floor,
aft left of the co-pilot’s seat.
NOTE:
If LH and / or RH green gear locked advisory lights do not illuminate, insert the Hydraulic
Pump handle in the socket and operate pump until LH and RH green advisory lights illuminate.
Door must stay fully open after alternate landing gear extension.
Nose Gear Release Handle ......................................................................................................... Pull Fully Up
Pull the NOSE GEAR RELEASE handle fully up to release nose gear door uplocks and nose gear.
Check N DOOR amber doors open and NOSE green gear locked down advisory lights illuminate.
NOTE:
The Nose Gear release handle pull force will be significantly higher than experienced during
practice alternate landing gear extensions.
The required pull force, to release the Nose Gear uplocks, can be as high as 41 kg (90 lb).
It may require a repeated pull effort to achieve a Nose Landing Gear down and locked indication.
LANDING GEAR ALTERNATE RELEASE and
LANDING GEAR ALTERNATE EXTENSION Doors ........................................................... Leave Fully Open
L/G INHIBIT Switch ............................................................................................................... Leave at INHIBIT
CAUTION: Landing gear cannot be retracted following extension by alternate extension
procedure.
CAUTION: Nosewheel steering is inoperative following extension by alternate extension
procedure.
(cont’d on the next page)
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1-73
[Rev. 16] 7 MAR 2016
ALTERNATE LANDING GEAR EXTENSION or LDG GEAR INOP (cont’d)
ANTI SKID Switch ..................................................................................................................................... TEST
Hold the ANTI SKID switch at TEST, then release to ON.
Make sure INBD ANTI-SKID and OUTBD ANTI-SKID caution lights go off after 3 s.
After Landing:
-
Consider stopping on the runway.
Install main gear pins and engage nose gear lock as soon as possible after engine shut-down.
[END]
3.1.11.2
LANDING GEAR DOOR MALFUNCTIONS
3.1.11.2.1 MAIN LANDING GEAR DOOR MALFUNCTIONS with LANDING GEAR UP
(Continuous illumination of amber Main Gear DOOR open advisory light with Landing Gear up)
Airspeed .................................................................................................................................... MAX 185 KIAS
FLAPS Lever .................................................................................................................................................. 0°
If amber Main Gear DOOR open advisory light goes out:
•
Continue flight at normal airspeed.
If amber Main Gear DOOR open advisory light remains illuminated:
Airspeed .................................................................................................................................... MAX 185 KIAS
-
Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1).
NOTE:
Intermittent illumination of amber Main Gear DOOR open advisory light must be reported to
maintenance.
[END]
3.1.11.2.2 NOSE LANDING GEAR DOOR MALFUNCTIONS with LANDING GEAR UP
(Continuous illumination of amber Main Gear DOOR open advisory light with Landing Gear up)
Airspeed .................................................................................................................................... MAX 185 KIAS
-
Extend landing gear using ALTERNATE LANDING GEAR EXTENSION procedure (Sub-Chapter 3.1.11.1).
If Landing Gear is selected Down:
NOTE:
Intermittent illumination of amber Main Gear DOOR open advisory light must be reported to
maintenance.
[END]
3.1.11.2.3 NOSE or MAIN LANDING GEAR DOOR MALFUNCTIONS with LANDING GEAR DOWN
(Continuous illumination of amber Nose or Main Gear DOOR open advisory light with Landing Gear DN)
Airspeed .................................................................................................................................... MAX 185 KIAS
-
Complete flight with landing gear down.
[END]
AOM DASH 8-Q400
3.1-74
[Rev. 16] 7 MAR 2016
3.1.11.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ALL LANDING GEAR FAIL TO RETRACT
[with MS 4-126420 Not Incorporated]
(3 Green Gear Locked Down Advisory Lights illuminated with Landing Gear Lever selected UP)
NOTE:
Landing Gear Doors may be open or closed
(Amber Doors Open Advisory Lights illuminated or out)
Landing Gear Lever ..................................................................................................................................... DN
Confirm 3 Green gear locked down Advisory Lights remain illuminated.
NOTE:
If the Landing Gear Alternate Release door is open, the landing gear will not retract.
•
Do Not re-select Landing Gear up.
-
Land at the nearest suitable airport.
[END]
[with MS 4-126420 Incorporated]
(3 Red Gear Unsafe Advisory Lights illuminated with Landing Gear Lever selected UP)
NOTE:
Landing Gear Doors may be open or closed
(Amber Doors Open Advisory Lights illuminated or out)
Landing Gear Lever ..................................................................................................................................... DN
Confirm 3 Green gear locked down Advisory Lights illuminate.
NOTE:
If the Landing Gear Alternate Release door is open, the landing gear will not retract.
•
Do Not re-select Landing Gear up.
-
Land at the nearest suitable airport.
[END]
3.1.11.4
LANDING GEAR INDICATOR MALFUNCTION
If any of the Green gear–locked–down advisory lights fail to illuminate:
Landing Gear Alternate Extension Door ............................................................................................... Open
Open the LANDING GEAR ALTERNATE EXTENSION door on the flight compartment floor,
to aft left of the co-pilot’s seat.
Gear-Locked-Down Indicator ............................................................................................. ON / Check / OFF
Hold LANDING GEAR DOWNLOCK VERIFICATION switch in the ON position and
make sure the 3 green LANDING GEAR DOWNLOCK VERIFICATION lights turn on.
Landing Gear Alternate Extension Door ............................................................................................... Close
Close the LANDING GEAR ALTERNATE EXTENSION door.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.1.11.5
3.1-75
[Rev. 16] 7 MAR 2016
NOSEWHEEL STEERING
(Caution Light)
IN FLIGHT:
Steering Tiller .................................................................................................................................... Centered
Move the Nosewheel Steering Control Handle (Tiller) to the center position.
If Caution Light remains illuminated:
Nosewheel Steering ................................................................................................................................... OFF
Set nosewheel STEERING Switch to OFF.
Landing Considerations:
- Land at an airport with minimum crosswind and turbulence.
After Touchdown:
- Use asymetric braking and power, as required, to maintain directional control.
ON THE GROUND:
- Taxi the airplane forward to centre the Nosewheel
With the airplane stopped:
Steering Tiller and Rudder Pedals ................................................................................................... Centered
Nosewheel Steering .................................................................................................................... OFF then ON
Set nosewheel STEERING Switch to OFF then ON.
- Wait 7s for Nosewheel Steering to re-engage.
If Caution Light remains on:
Nosewheel Steering ................................................................................................................................... OFF
Set nosewheel STEERING Switch to OFF.
- Use asymetric braking and power, as required, to taxi the airplane.
- Maintenance action required prior to flight.
If Caution Light remains off:
- Check Nosewheel for correct response to Steering inputs prior to flight.
[END]
AOM DASH 8-Q400
3.1-76
[Rev. 16] 7 MAR 2016
3.1.11.6
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
TOUCHED RUNWAY
(Warning Light)
(Fuselage Contact with Runway on Landing)
Due to the possibility of runway debris:
•
Advise ATC and airport operations of the fuselage / runway contact.
-
Aircraft must not be flown prior to inspection and maintenance approval.
[END]
3.1.11.7
INBD ANTI-SKID and / or OUTBD ANTI-SKID
(Caution Light)
ANTI SKID Switch ........................................................................................................................................ ON
Set ANTI SKID switch on co-pilot’s GLARESHIELD to ON.
Pedal Brakes ................................................................................................. Apply using Manual Technique
Landing Considerations:
-
Anti-Skid wil be inoperative, use Manual Technique (below) for braking.
CAUTION: Excessive brake application can result in skidding and tire failure.
Manual Technique - for maximum deceleration, brakes should be applied intermittently with momentary
release at about 1 s intervals.
Landing Distance Factor:
Flap 10° & 15° .........................
Flap 35° ...................................
1.70
1.70
REF SPEED
INCR ON
2.10
2.0
[END]
3.1.11.8
WT ON WHEELS
(Caution Light)
•
No crew action is required.
-
Complete flight with WT ON WHEELS Caution Light illuminated.
CAUTION: Landing gear may not retract with WT ON WHEELS Caution Light illuminated.
NOTE:
Caution Light may extinguish after landing.
However, rectification will be required prior to next flight.
[END]
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2
MISCELLANEOUS ABNORMAL and EMERGENCY PROCEDURES
3.2.1
GROUND FAILURES / ABORTED TAKE-OFF
3.2-1
[Rev. 13] 30 JAN 2015
Ground failures are defined as any malfunction that occurs on the ground prior to V1 or after touchdown.
In the event of a ground failure, regardless of whether it happens while at the gate, taxiing or during take-off,
the primary objective of the crew is to stop the airplane, assess the problem, take the appropriate action and
evacuate if required.
A take-off shall be aborted for any Caution or Warning light prior to V1.
There are many reasons other than Caution or Warning lights for discontinuing a take-off.
It is therefore, left to the discretion of the PIC as to what additional situations demand an aborted take-off.
At V1 or above, the take-off will be continued regardless of the malfunction.
If a rejected take-off becomes necessary the call “ABORT” will be made by either pilot.
If the PF is in the right seat, the left seat pilot will normally assume control at approximately 50 kt.
The PNF (right seat) will advise ATC of the abort and the crew will then assess the situation.
If the reason for the abort is fire or smoke, the PF will set the parking brake and complete the memory items for
shutdown and evacuation.
The PNF will advise ATC of the problem, request emergency equipment, state the number of persons on board
and quantity of fuel.
Table 3.2-1
Ground Failures / Aborted Take-Off
PF (Left Seat)
PNF (Right Seat)
Either pilot will call “ABORT”
SIMULTANEOUSLY:
Selects POWER levers to disc / reverse
Applies maximum braking
Advises ATC of the “ABORT”
Once the airplane has stopped the crew will assess the problem
If Fire or Smoke
EMERG Brake ................................................... ON
POWER Levers .............................................. DIDC
Condition Levers ..................................... Fuel OFF
Pull Fuel Off (affected engine) ........................... Pull
EXTG ................................ FWD BTL and AFT BTL
............................................................. (as required)
Confirm ATC advised
Advises ATC
Commands on PA: “Evacuate (3x) ... Side”
Emergency Lights ............................................... ON
External Power / APU ....................................... OFF
Battery Master .................................................. OFF
Assist in evacuation as required
Leaves the flight compartment to assist in the evacuation
NOTES:
a) requirement for emergency equipment
b) number of persons on board
c) amount of fuel
1. All accelerate-stop performance is based upon the use of full anti-skid braking until the
airplane has stopped.
2. Reverse thrust may be used, commensurate with directional control.
AOM DASH 8-Q400
3.2-2
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Ground Failures / Aborted Take-Off
Figure 3.2-1
Ground Failure
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.2
EVACUATION
3.2.2.1
Catastrophic Accident
3.2-3
[Rev. 13] 30 JAN 2015
If a catastrophic accident occurs which precludes any formal preparation or announcements each crew member should immediately initiate an evacuation.
When initiating an evacuation communicate this using the following shouted command / PA:
“EVACUATE, EVACUATE, EVACUATE”
(“... SIDE”, if required to restrict evacuation to that side of the airplane.)
This notifies other crew members and your passengers that you are initiating an evacuation.
3.2.2.2
Non-Catastrophic Accident
At any time the airplane comes to a stop following a planned or unplanned emergency landing that is not catastrophic, the Cabin Crew Member(s) will wait for engine shut down plus 15 s.
If there is no communication from the flight compartment by this point the:
•
Senior Cabin Crew Member will attempt to call the flight compartment using the “EMER” call button on the
Interphone.
If there is no response, she / he will attempt to enter the flight compartment.
If all communication with the flight compartment fails, the Senior Cabin Crew Member will initiate evacuation.
•
Cabin Crew Member(s) will maintain control in the cabin and wait for direction from the flight compartment or the
Senior Cabin Crew Member.
If this is not possible, the Cabin Crew Member(s) will initiate evacuation.
3.2.3
Blocked Exit Procedure
If during the assessment of an exit it is determined that the exit is unsafe or unusable then the following procedure should be used:
• Have 2 passengers hold people back while you assess the exit opposite (e.g. “you 2 hold people back”);
• If this exit is also unusable then redirect passengers to operable exits - elevate yourself, cross arms in an X
in front of you and shout the problem (e.g. “blocked exit, fire, go that way”).
3.2.3.1
Pilot Duties - Evacuation
(After Landing)
3.2.3.1.1
2IC Duties
(Senior Cabin Crew Member and / or Cabin Crew Member is conducting evacuation)
1) Complete flight compartment duties,
2) Exit flight compartment and
3) 2IC will exit airplane with passengers and assist from outside.
3.2.3.1.2
2IC Duties
(Senior Cabin Crew Member Incapacitated or no Cabin Crew Member on board)
In addition to items 1) and 2) above, the 2IC will assess and open exits and conduct evacuation.
3.2.3.1.3
PIC Duties
(Senior Cabin Attendant and / or Cabin Attendant and / or PNF is conducting evacuation)
1) Complete flight compartment duties,
2) Exit flight compartment, and
3) PIC will exit airplane with passengers and assist from outside.
3.2.3.1.4
PIC Duties
(Senior Cabin Crew Member Incapacitated or
no Cabin Crew Member on board or
PNF incapacitated)
In addition to items 1) to 3) above, the PIC will assess and open exits and conduct evacuation.
NOTE:
Any crew member may assume the duties of any other crew member as the circumstance
require.
AOM DASH 8-Q400
3.2-4
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.4
CREW INCAPACITATION
3.2.4.1
Pilot Incapacitation
Incapacitation occurs in many forms ranging from sudden death to subtle, partial loss of mental or physical performance.
Subtle incapacitation is the most dangerous and is the most common type encountered.
One of the keys to early and effective recognition of pilot incapacitation is the strict adherence to standard
operating procedures, call-outs and flight profiles.
Suspicion of some degree of incapacitation should be considered when a crew member does not respond to
verbal communication associated with a significant departure from a standardized procedure or profile.
Failure of that crew member to respond to a 2nd request or challenge is cause for immediate action on the part
of the challenging crew member.
Whenever the PNF advises the PF of a deviation from the intended flight profile, the PF shall take immediate
action and announce, “CORRECTING”.
If the PF does not respond immediately, the PNF shall call the deviation a 2nd time, and if there is still no
response from the PF, the PNF shall assume pilot incapacitation, assume immediate control of the airplane
and announce, “I HAVE CONTROL”.
If carrying additional crew members i.e. Cabin Crew Member(s), call for their assistance in securing the incapacitated pilot away from the controls and to administer first aid as necessary.
3.2.5
IN-FLIGHT FAILURES
In-flight failures are defined as any malfunction that occurs at or above V1 and prior to touch down.
During an in-flight failure the primary responsibility of the crew is to control the airplane.
Checklists must not be called for until the airplane is under full control and in a steady state of flight.
If a failure occurs at or above V1 and prior to flap retraction (3rd segment), the crew will not action any memory
items or checklist until the flaps are retracted.
In an extreme situation (such as engine failure during a GA), the PIC may elect to action the checklist memory
items prior to reaching 3rd segment (prior to flap retraction).
In any event, no action will be taken until the airplane is under full control and in a steady state of flight.
In the event of an in-flight failure, the crew will assess the problem.
Once the nature of the problem has been established, the PF will call for the appropriate memory items if applicable, e.g. “SHUTDOWN ENGINE NUMBER 2".
The PNF actions the memory items which are confirmed by the PF (Challenge and Response).
When the memory items are complete, the PF will at his discretion (but not less than 1000 ft above the airport
elevation), call for the appropriate non-normal checklist.
The PNF actions the checklist items using the Read and Do method.
Once the checklist has been completed, the crew will advise ATC of the problem and declare an emergency if
applicable.
The PIC will advise the Cabin Crew of the nature of the problem and the intentions of the flight crew.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Table 3.2-2
3.2-5
[Rev. 13] 30 JAN 2015
Engine Failure / Fire During Take-Off After V1
PF
At V1 / VR calls:
Confirms airspeed and rotates at VR to 8° nose up.
After lift-off continues rotation to a minimum pitch atti- “V1 ROTATE”
tude of 10° to achieve V2 at 35 ft.
PNF
Observes positive rate of climb
Calls “POSITIVE RATE”
Commands “GEAR UP”
Selects Landing Gear Lever Up
Announces “ENGINE FAILURE (or “FIRE) # 1 (or # 2) ENGINE”
Cancels all Caution and Warning Lights
At minimum 400 ft (or appropriate obstacle clearance
height) *
Calls “400 FEET”
(or appropriate obstacle clearance height) *
Accelerates through VFR
Commands “FLAPS 0"
Confirms speed VFRI or above
Selects FLAPS 0
Continues acceleration to VFTO
Assesses the problem and
Verifies the affected engine
Commands “SHUTDOWN ENGINE # 1 (or # 2 )”
Completes Engine Shutdown procedure
Confirms airspeed is VCLIMB or higher
Commands
“BLEED ON / MAX CONTINUOUS POWER”
Continues climb
Selects bleed on operating engine to ON / NORM.
Confirms MCP power rating on ED
Calls “POWER SET”
CAUTION: Nose up pitch attitudes > 8° prior to lift-off may cause the tail to contact the runway.
NOTES:
1. Unless otherwise specified in the ENGINE FAILURE PROCEDURE for a particular airport /
runway the following standard is recommended:
2. CLIMB TO 1000 ft AIRPORT ELEVATION WITH V2;
ACCELERATE TO VFR AND TURN (LEFT or RIGHT) TO THAT NAVAID SERVING AS
THE MAIN NAVAID FOR APP PURPOSES.
CONTINUE CLIMB WITH VFTO.
Table 3.2-3
Engine Failure / Fire in Flight Procedure
PF
Sets power as required to maintain steady flight
Assesses problem and
Verifies the affected engine
Commands “SHUTDOWN ENGINE # 1 (or # 2)”
AOM DASH 8-Q400
PNF
Announces “ENGINE FAILURE (or FIRE)
# 1 (or # 2) ENGINE”
Cancels all Caution and Warning Lights
Completes Engine Shutdown procedure
3.2-6
[Rev. 13] 30 JAN 2015
Table 3.2-4
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Engine Shutdown Procedure
PF
PNF
Commands “SHUTDOWN ENGINE # 1 (or # 2)”
Calls “POWER LEVER # 1 (or # 2)”
Responds “CONFIRMED, FLIGHT IDLE”
Selects POWER Lever to Flight Idle
Calls “CONDITION LEVER # 1 (or # 2)”
Responds “CONFIRMED, FUEL-OFF”
Selects Condition Lever to FUEL-OFF
Confirms propeller feathers
If propeller Does Not feather:
Calls “NO FEATHER”
“ALTERNATE FEATHER # 1 (or # 2)”
Selects appropriate Alternate Feather switch to
FEATHER
Calls “PULL FUEL OFF # 1 (or #2)”
Responds “CONFIRMED, PULL”
Pulls Fuel Off Handle
Calls “# 1 (or # 2) TANK AUX PUMP OFF”
Selects Tank Aux Pump to OFF
If Engine Fire
Calls “EXTINGUISHER FWD BTL”
Selects Forward Bottle
If Fire persists (wait up to 30 s)
Calls “EXTINGUISHER AFT BTL”
Selects Aft Bottle
Once the Engine is shut down and at a minimum of 1000 ft AGL:
Confirms airspeed is VCLIMB or higher
Commands
“BLEED ON / MAX CONTINUOUS POWER”
Selects bleed on operating engine to ON / NORM.
Continues climb
Calls “POWER SET”
Confirms MCP power rating on ED
Commands “ENGINE SHUTDOWN CHECKLIST”
Completes ENGINE SHUTDOWN CHECKLIST
Calls
“ENGINE SHUTDOWN CHECKLIST COMPLETE”
NOTES:
1. If fire is extinguished, ENGINE FIRE and PULL FUEL OFF handle light will go out and
engine fire warning tone is silenced
2. The engine fire warning tone can be silenced by pressing the ENGINE FIRE light.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Engine Failure / Fire During Take-Off After V1
Figure 3.2-2
Engine Failure / Fire During Take-Off After V1
AOM DASH 8-Q400
3.2-7
[Rev. 13] 30 JAN 2015
3.2-8
[Rev. 13] 30 JAN 2015
Table 3.2-5
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Single Engine Missed Approach Procedure
PF
PNF
Simultaneously
“GO-AROUND, MAX POWER”
Advances POWER Levers to the detent
Sets Condition Levers to MAX
Confirms MTOP power on ED
Calls “MAX POWER SET”
If Landing Flap selected
Commands “FLAPS 5°, 10° or 15°”
Selects flap as requested
Rotates to a pitch attitude to maintain a minimum airspeed of VGA
Observes positive rate of climb
Calls “POSITIVE RATE”
Commands “GEAR UP”
Selects Landing Gear Lever Up
At a minimum 400 ft AGL
(or appropriate obstacle clearance height)
Calls “400 FEET”
(or appropriate obstacle clearance height)
Accelerates to a minimum of VFRI
Commands “FLAPS 0"
Confirms speed VFRI or above:
Continues acceleration to VCLIMB
Selects Flaps to 0
Confirms airspeed is VCLIMB or higher
Commands
“BLEED ON / MAX CONTINUOUS POWER”
Selects bleed on operating engine to ON / NORM.
Continues climb
Calls “POWER SET”
Confirms MCP power rating on ED
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Single Engine Missed Approach Procedure
Figure 3.2-3
Single Engine Missed Approach
AOM DASH 8-Q400
3.2-9
[Rev. 13] 30 JAN 2015
3.2-10
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.6
PROPELLER OVERSPEED and UNSCHEDULED FEATHERING
3.2.6.1
Propeller Overspeed
The checklist is considered to be a memory item; propeller RPM above 1020 should be viewed as an overspeed.
Any prop that cannot be controlled must be treated the same as an overspeed.
The checklist procedures are essentially the same as “Engine Shutdown” except with the clear understanding
that the engine is not to be shutdown until the propeller feathers.
The Condition Lever remains in the “START & FEATHER” position until the propeller feathers.
Table 3.2-6
Propeller Overspeed Procedure
PF
PNF
Announces “PROP OVERSPEED # 1 (or # 2)”
Above 400 ft AGL
Reduces airspeed toward minimum speed appropriate to flap configuration and flight conditions
Retards POWER lever (affected engine) to FLIGHT
IDLE
Commands
“CONDITION LEVER # 1 (or # 2)
START FEATHER”
Calls “CONDITION LEVER # 1 (or # 2)”
Responds “CONFIRMED, START FEATHER”
Selects Condition Lever to START / FEATHER
Confirms propeller feathers
If Propeller Does Not Feather
Calls “NO FEATHER” /
“ALTERNATE FEATHER # 1 (or # 2)”
Selects appropriate Alternate Feather switchlight to
FTHR
If Propeller Does Not Feather
Calls “NO FEATHER” /
“ALTERNATE FEATHER # 1 (or # 2) OFF”
Commands “CONDITION LEVERS MAX”
Selects appropriate Alternate Feather switchlight to
OFF
Sets both Condition Levers to the MAX detent.
Operates POWER Levers together to maintain the
desired flight profile
Land Immediately a the Nearest Suitable Airport.
If Propeller Feathers
Commands
“CONDITION LEVER # 1 (or # 2) FUEL OFF”
Calls “CONDITION LEVER # 1 (or # 2)”
Responds “CONFIRMED, FUEL OFF”
Selects Condition Lever to FUEL OFF.
Completes ENGINE SHUTDOWN procedure
Once Propeller RPM is under control and at a minimum of 1000 ft AGL
Commands “PROP OVERSPEED CHECKLIST”
Completes PROP OVERSPEED CHECKLIST
Calls
“PROP OVERSPEED CHECKLIST COMPLETE”
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.6.2
3.2-11
[Rev. 13] 30 JAN 2015
Propeller Unscheduled Feathering
A propeller unscheduled feather should be viewed as an engine failure and actioned in the same way.
ED indications will show high values in torque and propeller RPM on the affected engine.
Table 3.2-7
Propeller Unscheduled Feathering
PF
Sets power as required to maintain steady flight
PNF
Announces
“UNSCHEDULED FEATHER # 1 (or # 2)”
Cancels all Caution and Warning lights
Assesses problem and verifies affected engine.
Commands “SHUTDOWN ENGINE # 1 (or # 2)”
Completes Engine shutdown Procedure
AOM DASH 8-Q400
3.2-12
[Rev. 13] 30 JAN 2015
3.2.7
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
FLAPLESS APPROACH and LANDING
During flapless approaches, fly a normal rectangular traffic pattern, but ensure that there is enough time / distance on final approach to stabilize in the flapless configuration.
The nose of the airplane will be higher than normal and the power setting will be lower than normal.
The GPWS flap override switch should be depressed to inhibit all flap warning signals.
The key to a successful flapless landing is to establish VREF for flaps 0° as soon as possible on final approach.
Care should be exercised not to under-shoot the runway as there might be a tendency to “flattern out” the
approach angle when in the flapless configuration.
Make adjustments quickly and precisely.
This should obviate the necessity to use large attitude and power changes especially on short final.
Power should be reduced gradually to achieve FLIGHT IDLE at or just prior to touchdown.
The POWER levers should be moved from FLIGHT IDLE into discing without delay.
Reverse may be used as required to reduce stopping distance.
The “flapless landing” checklist should be completed before execution of the normal approach and landing
checklists.
CAUTION: Pitch attitude > 6° in the landing flare may cause the fuselage to contact the RWY.
CAUTION: Do Not select POWER levers below FLIGHT IDLE
until indicated airspeed is below 150 kt IAS.
NOTE:
The nosewheel should be promptly brought into contact with the ground following mainwheel
contact.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.8
Table 3.2-8
3.2-13
[Rev. 13] 30 JAN 2015
CONTROL JAMS
Pitch Jam Procedures
PF
PNF
Calls “PITCH JAM”
Presses Auto-pilot Disconnect Button
Both pilots will try to overpower each control to dislodge jam.
If unable to control the airplane
Calls “PITCH DISCONNECT”
Relaxes Force
Pulls Pitch Disconnect handle and rotates 90°
Both Pilots will now attempt to control airplane.
Pilot with free control will call “I HAVE CONTROL”, the other will call “YOU HAVE CONTROL”.
The PF shall retain the flap setting and appropriate airspeed at the time of the jam.
Once airplane is under control and at minimum of 1000 AGL:
Commands “PITCH JAM CHECKLIST”
Completes “PITCH JAM CHECKLIST”
Calls “PITCH JAM CHECKLIST COMPLETE”
NOTE:
Limit speed to 170 kt, or speed at time of Jam, whichever is higher.
CAUTION: With the Pitch disconnect handle pulled, the autopilot must not be engaged.
Table 3.2-9
Roll Jam Procedures
PF
PNF
Calls “ROLL JAM”
Presses Auto-pilot Disconnect Button (if required)
Calls “ROLL DISCONNECT”
Pulls Roll Disconnect handle and rotates 90°
Both Pilots will now attempt to control airplane.
Pilot with free control will call “I HAVE CONTROL”, the other pilot will call “YOU HAVE CONTROL”.
Once airplane is under control and at minimum of 1000 AGL:
Commands “ROLL JAM CHECKLIST”
Completes “ROLL JAM CHECKLIST”
Calls “ROLL JAM CHECKLIST COMPLETE”
AOM DASH 8-Q400
3.2-14
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.9
SMOKE / DEPRESSURIZATION / EMERGENCY DESCENTS
3.2.9.1
Smoke
Smoke or fire within the airplane can quickly develop into a serious and life threatening situation.
Smoke can be carried into the fuselage via the air conditioning and pressurization system, or it can be generated within the airplane by overheated or burning electrical equipment or wiring.
It can also result from combustion within the cargo / baggage compartment, the cabin and the lavatory and galley areas.
Of immediate importance, upon detection of any smoke on the flight compartment, is PROTECTION of the
flight crew.
The appropriate smoke / fire procedures can then be carried out, the airplane descended to a safe altitude for
protection of the passengers and positioned for an immediate landing at the nearest suitable airport.
Smoke / fire procedures are addressed in the QRH under 2 basic headings:
- Known source of fire or smoke
- Unknown source of smoke
Table 3.2-10
Smoke Procedure
PF
PNF
Crew Member noting abnormality calls “SMOKE”
Both Pilots:
Don oxygen masks with 100% EMER oxygen selected
Don smoke goggles (if applicable)
Select BOOM / MASK switch to MASK and establish communications
Selects
RECIRC FAN to OFF
(MS 4-126236 Not Incorporated)
Emergency Lights ON
Pass Signs ON
If source of Smoke on flight compartment
Assesses flight compartment visibility and if Extinguishes fire if possible
determined to be necessary to clear smoke
Commands “FORWARD OUTFLOW OPEN”
Selects Cabin Alt Fwd Outflow fully clockwise to OPN to
exhaust smoke forward
Responds “FORWARD OUTFLOW OPEN”
All sources of Smoke
Commands “SMOKE CHECKLIST”
Commences descent to land immediately at
nearest possible airport
Determines source of smoke
Completes “FUSELAGE FIRE OR SMOKE CHECKLIST”
Extinguishes fire with portable extinguisher leaving flight
compartment if required
Calls “SMOKE CHECKLIST” complete
NOTES:
1. Whether or not smoke has cleared, if it cannot be visibly verified that the fire has been
extinguished following fire suppression and / or smoke evacuation procedures, continue to
land immediately at the nearest suitable airport.
2. If a pilot is required to fight the fire, protective breathing equipment must be donned prior to
exiting the flight compartment.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.9.2
3.2-15
[Rev. 13] 30 JAN 2015
Depressurization
Other than setting the altitude of the destination airfield on the cabin controller, pressurization occurs automatically and normally requires minimal crew involvement.
If the automatic features of the controller fail, cabin pressure can be controlled manually.
In the event of cabin depressurization or the inability to maintain adequate pressurization, the airplane should
be descended to below 14000 ft or the Minimum Enroute Altitude, whichever is higher.
When controlling the cabin pressure manually, do not exceed maximum cabin differential pressure stated on
the Cabin Altitude Differential placard.
A rapid decompression can result from loss of integrity of the pressure hull due to birdstrike, loss of a window,
sudden failure of a door seal, or other structural damage.
As with the case of smoke on the flight compartment, the prime consideration of the flight crew is self-protection, so the airplane can be flown safely to a lower altitude to protect the passengers.
Table 3.2-11
Depressurization Procedures
PF
PNF
Crew Member noting abnormality calls “CABIN PRESSURE”
If rapid Depressurization
Both Pilots:
Don oxygen masks with 100% EMER oxygen selected
Select BOOM / MASK switch to MASK and establish communications
Selects Passenger Signs ON
Commences Emergency Descent procedure to
Advises ATC of emergency descent
below 14000 ft or to MEA whichever is higher
Commands
Completes
“RAPID DEPRESSURIZATION CHECKLIST”
“RAPID DEPRESSURIZATION CHECKLIST”
Calls “RAPID DEPRESSURIZATION CHECKLIST
COMPLETE”
If slow Depressurization
Commands “CABIN PRESSURE CHECKLIST”
Completes “CABIN PRESSURE CHECKLIST”
Calls
“CABIN PRESSURE CHECKLIST COMPLETE”
Unpressurized Flight
Descends below 14000 ft or to MEA whichever is
higher
Commands
Completes
“UNPRESSURIZED FLIGHT CHECKLIST”
“UNPRESSURIZED FLIGHT CHECKLIST”
Calls “UNPRESSURIZED FLIGHT CHECKLIST
COMPLETE”
3.2.9.3
Emergency Descent
An Emergency Descent, if required, is normally carried out at VMO.
If the structural integrity of the airplane is in doubt, however, limit the descent airspeed as much as possible
and avoid high maneuvering loads. Moving the condition levers to MAX increases drag in order that the
descent to lower altitude may be done in a timely fashion.
Table 3.2-12
Emergency Descent Procedure
PF
POWER Levers ...... FLIGHT IDLE
Condition Levers ................. MAX
Airspeed ............................... VMO
NOTE:
PNF
If structural integrity is in doubt, limit airspeed as much as possible and avoid high
maneuvering loads.
AOM DASH 8-Q400
3.2-16
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Rapid Depressurization
Figure 3.2-4
Rapid Depressurization
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.10
3.2-17
[Rev. 13] 30 JAN 2015
HIGH ANGLE OF ATTACK RECOVERY PROCEDURES
(Recovery from stall warning and stall - stick shaker, unusual airframe buffet, uncommanded wing drop, activation of stick pusher and presentation of red low airspeed cue)
Autopilot .................................................................................................................................. Disengage, and
Pitch Attitude ........................................................................................................................................ Reduce
NOTE:
Relax any control column pull force and / or move the control column forward sufficient to
achieve a reduction in pitch attitude.
This action can result in a loss of altitude.
WARNING:
With the aircraft in close proximity to the ground, the degree of pitch attitude
reduction will be limited.
If the aircraft is not in a wings level attitude prior to or during stall warning or stall:
Lateral Control ...................................................................................................................... Roll Wings Level
Power .................................................................................................................................................. Increase
Advance Condition levers to MAX / 1020 and POWER levers to RATING detent (NTOP).
Airspeed .............................................................................................................................................. Increase
Increase airspeed to not less than the minimum reference airspeed appropriate to flap configuration
and any additional airspeed factors, if applicable.
CAUTION:
Do Not change the flap and landing gear configuration until the minimum reference
airspeed appropriate for the new configuration is achieved.
When aircraft recovers from stall and / or stall warning (minimum reference airspeed is achieved):
•
Return to the desired flight profile and assigned altitude.
3.2.11
OVERWEIGHT LANDING
If an immediate landing is required following take-offs at a mass / weight in excess of maximum landing mass /
weight, the following considerations apply:
1) Approach and landing speeds will be higher for a given flap setting as well as brake energy and landing
distance increased and MAT / WAT limit decreased.
Approach and landing flap selection may be determined by landing MAT / WAT considerations well as
available landing distance or brake energy.
2) Establish VREF as soon as possible on final approach.
Avoid the necessity to use large attitude and power changes especially on short final.
3) Note that airplane sink rate will be higher than normal on approach.
4) Adjust flare to reduce sink rate to normal values prior to touchdown.
Power may be required in the landing flare through to touchdown to decrease the landing descent rate.
5) After touchdown, the POWER levers should be moved from FLIGHT IDLE into discing without delay and
the nosewheel lowered to the runway.
Reverse may be used as required to reduce stopping distance.
NOTE:
Landing speeds, MAT / WAT limits, Landing Climb data, Landing Distance and Brake Energy
may be determined using the AOM tables for over-weight landing conditions.
AOM DASH 8-Q400
3.2-18
[Rev. 13] 30 JAN 2015
3.2.12
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) - Honeywell MK V
(Option - CR 831 CH 00064 or CR 831 SO 90180)
NOTE:
This procedure corresponds to Supplement 64 of the AFM.
In response to a EGPWS aural caution
(i.e. “SINK RATE”, “TERRAIN TERRAIN”, “DON’T SINK”, “TOO LOW - FLAPS”, “TOO LOW - GEAR”,
“CAUTION TERRAIN”, “CAUTION OBSTACLE”, “BANK ANGLE” or “GLIDESLOPE”)
the crew shall immediately assess the airplane flight path or configuration with respect to the proximity of the
ground and the PF shall take appropriate action to rectify the situation.
In response to a EGPWS aural warning
(i.e. “TOO LOW - TERRAIN”, “TERRAIN PULL UP”, “OBSTACLE PULL UP” or urgent “PULL UP”)
the PF shall immediately establish the maximum performance climb consistent with airplane configuration.
• Apply NTOP (detent) power
• Rotate to known GA attitude
• Do not change configuration until clear of terrain.
If aircraft continues to close on terrain, increase thrust and pitch attitude:
• Firewall power
• Increase pitch target sufficient to obtain positive separation from terrain, but do not allow airspeed to
decrease below V2 / VGA
• Maintain the pitch attitude that achieves V2 / VGA airspeed
If stick shaker activates and / or airspeed tape turns red (alternate symbology):
• Reduce pitch attitude sufficient to silence shaker
• Achieve an airspeed above the low speed cue.
• If close to ground, maintain pitch attitude to silence shaker
• When terrain contact no longer a factor, allow aircraft to accelerate back to V2 / VGA.
Continue to climb until clear of terrain, then:
• Reduce power and pitch attitude appropriate to the phase of flight.
• Reconfigure aircraft as necessary.
3.2.12.1
ABNORMAL APPROACH and LANDING
1) For planned abnormal approaches:
BELOW G/S Switchlight .......................................................................................................................... Press
-
Inhibits glideslope warning when airplane altitude is below 1000 ft AGL.
-
Confirm G/S advisory light is illuminated.
-
Glideslope warning is automatically reset on a climb through 2000 ft AGL or descent through 30 ft AGL.
2) When landing with flap other than selected by the GPWS LDG FLAP selector:
GPWS FLAP OVERRIDE Switchlight ..................................................................................................... Press
-
Inhibits “TOO LOW - FLAPS” announcement. Other modes not affected.
-
Confirm GPWS FLAP OVERRIDE advisory light on lower half of switch is illuminated.
3) When position accuracy inadequate or when operating at airports not in terrain database:
TERRAIN INHIBIT Switchlight ................................................................................................................ Press
-
Inhibits all TAD and TCF aural annunciations and visual indications on MFD
-
Check MFD for TERRAIN INHIBIT message.
-
Confirm INHIBIT advisory light on upper half of switch is illuminated.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Table 3.2-13
3.2-19
[Rev. 18] 21 NOV 2016
Terrain Recovery Procedure
PF
PNF
Commands “TERRAIN RECOVERY”
Simultaneously:
• Selects GA
• Advances Power Levers to detent
• Smoothly rotates aircraft to go-around attitude
•
•
•
•
Sets Condition Levers to MAX
Confirms NTOP power on ED
Calls “POWER SET”
Monitors radar altimeter and calls
“TERRAIN CLOSING”
if separation from the ground is still decreasing
If Aircraft Still Closing On Terrain
•
•
•
Advances Power Levers to maximum available
power (firewall)
Increases pitch attitude sufficient to obtain positive separation from terrain
Do Not allow airspeed to decrease below V2 / VGA
If Stick Shaker Occurs and / or Airspeed Tape Turns Red
•
•
•
Immediately reduces pitch attitude to silence
shaker
Achieves an airspeed above the low speed cue
Adjusts pitch to return to V2 / VGA
•
Continues climb as required to safe altitude
Aircraft Climbing Away From Terrain
•
•
Monitors radar altitude and baro altitude to determine when airplane is safely clear of obstacles or
terrain
Calls “<Obstacle Clearance Alt ASI> FEET”
Once Clear of Terrain
•
•
Reduces power and pitch attitude appropriate to •
the phase of flight
•
Reconfigures aircraft as necessary
Calls “CLEAR OF TERRAIN”
Advises ATC of any deviation to clearance
Do Not change gear or flap configuration until aircraft is clear of terrain.
Optimum aircraft performance (best angle of climb) occurs near 1.13 VS for the aircraft configuration, therefore,
Do Not allow the airspeed to decrease below this speed (Nominally V2 / VGA for the flap configuration).
Unlike a jet aircraft, it is not permissible to continue to increase pitch attitude until stick shaker occurs.
This is because at high power settings the propeller slipstream creates additional lift on the airframe. As a
result, the aircraft could reach a dangerously low indicated airspeed before the shaker activates.
At these very low airspeeds, the aircraft is operating on the extreme “back side” of the Lift / Drag curve with a
significant deterioration of climb capability.
Additionally, the flight controls may not retain sufficient authority to maintain control of the aircraft in turbulence
or following an engine flameout.
Jet aircraft can be flown to shaker because it provides an artificial barrier to reaching very low IAS.
Propeller aircraft normally “create” such a barrier using procedural means instead.
Restricting the aircraft to a minimum airspeed of V2 / VGA during the recovery is a natural choice as these
speeds are readily available to crew members and match optimal climb speed.
The Low Speed Cue on the Q400 aircraft has been designed to overcome the Limitations associated with the
stick shaker at high power settings and function as a visual airspeed barrier.
The cue will always display an appropriate minimum airspeed for control of the aircraft regardless of weight,
flap or power setting.
As a result, terrain recoveries can be flown using the low speed cue as an aid to preventing an unacceptable
low airspeed condition.
AOM DASH 8-Q400
3.2-20
[Rev. 13] 30 JAN 2015
3.2.13
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS)
In reference to a TCAS Traffic Advisory (TA), both pilots should locate the traffic on the MFD (yellow filled diamond) then the PNF should look outside for the traffic.
The PF will continue to monitor the MFD for any changes in traffic flight path or new traffic and direct the PNF
where to look for the traffic.
Should the PNF become visual with the traffic, the PNF should inform the PF and continue to monitor this traffic
as well as look for others.
The PF should continue to monitor the MFD for any changes in traffic flight path or new traffic.
The PNF should also request / advise ATC of any flight path changes requested by the PF in order to avoid the
traffic.
In the event the TA changes to a Resolution Advisory (RA), the PF should take whatever Resolution Advisory
climb or descent is directed by the TCAS.
Disconnect the autopilot and immediately adjust the flight profile.
The PNF should continue to look for the traffic and ensure the PF has met the RA directed by TCAS.
The PNF shall also advise ATC of any change in assigned altitude using the standard terminology:
“TCAS CLIMB (or DESCENT)”.
Once clear of the conflict and the RA is cancelled, the PF shall return the airplane to the original assigned altitude as promptly as possible.
The PNF will then report the completion of the maneuver to ATC using the terminology:
“TCAS CLIMB (or DESCENT) COMPLETED, (assigned clearance) RESUMED”.
NOTE:
The following procedures correspond to:
- AFM Supplement 33 (ACAS II / TCAS II - HONEYWELL)
- AFM Supplement 106 (ACAS II / TCAS II - ACSS)
[Option: ACAS II / TCAS II - HONEYWELL]
NOTE:
GPWS alert takes priority over an ACAS RA.
[Option: ACAS II / TCAS II - ACSS]
NOTE:
GPWS alert takes priority over an TCAS TA / RA.
CAUTION: If stall warning (stickshaker) occurs during an RA maneuver, take immediate stall
recovery action.
CAUTION: If a threat aircraft track or altitude information is lost during an RA, the RA will
terminate without a “CLEAR OF CONFLICT” announcement.
3.2.13.1
Mode S Transponder Failure
[Option: ACAS II / TCAS II - HONEYWELL]
(TCAS FAIL Displayed on PFD)
ATC / TCAS Page on ARCDU ........................................................................ ATC 1 or ATC 2 as appropriate
If TCAS FAIL message remains displayed on PFD:
ATC / TCAS Page on ARCDU ........................................................................................................ Select SBY
[Option: ACAS II / TCAS II - ACSS]
(TCAS STBY Displayed on PFD and ATC FAIL Displayed for Selected ATC on ARCDU)
TCAS / ATC Page on ARCDU ........................................................................ ATC 1 or ATC 2 as appropriate
3.2.14
FLIGHT MANAGEMENT SYSTEM (FMS)
For specific FMS operational information, please refer to the respective AFM Supplement and the FMS Operator’s Manual.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.15
NOTE:
3.2.15.1
3.2-21
[Rev. 13] 30 JAN 2015
OPERATION WITH ONE INOPERATIVE STALL WARNING and / or STICK PUSHER SYSTEM
This procedure corresponds to Supplement 11 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
This procedure is applicable only when used in conjunction with a Minimum Equipment List approved by the
appropriate authority.
3.2.15.2
Limitations
The Limitations in Chapter 1 are applicable with the addition of the following:
1.
One stall warning system must be operative.
2.
The inoperative stall warning system and / or stick pusher system must be disabled using an approved
MEL maintenance procedure.
NOTE:
Operation of the stick pusher system is dependent upon operation of both stall warning
systems.
In the event of an inoperative stall warning system, the stick pusher system must also be
disabled.
3.
The maximum aft center of gravity limit is 20% of MAC (Mean Aerodynamic Chord)
4.
With the exception of V2, Enroute Climb and Go Around speeds:
Minimum airspeed is 1.23 VSR for all flap settings or the appropriate airspeed for icing conditions and other
failures if applicable.
3.2.15.3
Abnormal Procedures
The abnormal procedures in this Chapter are applicable with the addition of the following:
# 1 STALL WARNING or # 2 STALL WARNING SYSTEM FAILURE
(Illumination of # 1 STALL SYST FAIL or # 2 STALL SYST FAIL Caution Light):
Autopilot .......................................................................................................................................... Disengage
-
Icing conditions should be avoided
-
Maintain a minimum airspeed of 1.23 VSR for all flap settings or the appropriate airspeed for icing conditions
and other failures if applicable
AOM DASH 8-Q400
3.2-22
[Rev. 13] 30 JAN 2015
3.2.16
NOTE:
3.2.16.1
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
OPERATION WITH INOPERATIVE NOSEWHEEL STEERING SYSTEM
This procedure corresponds to Supplement 8 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
This Supplement is applicable only when used in conjunction with a Minimum Equipment List approved by the
appropriate authority.
3.2.16.2
Limitations
The Limitations in Chapter 1 and the Supplement Compatibility Table in Sub-Section 1.5 of the AFM are applicable with the addition of the following:
1.
Take-off or landing in crosswinds exceeding 25 kt is prohibited.
2.
Take-off or landing on a contaminated runway is prohibited.
3.2.16.3
Normal Procedures
The normal procedures in Chapter 2 are applicable with the addition of the following:
STEERING Switch ...................................................................................................................................... OFF
Check NOSE STEERING caution light out.
-
Taxi the airplane using differential braking and power.
-
Maneuver the airplane at a reduced taxi speed.
-
Avoid tight turns.
CAUTION: Tight turns may cause the nosewheel to castor to a greater than desired steering angle,
making it difficult to return to the centre position.
NOTE:
3.2.16.4
During the initial take-off roll, aggressive asymmetric braking may be required to maintain the
desired aircraft heading.
This action is more likely to be required in crosswind conditions.
Abnormal Procedures
The abnormal procedures in this Chapter are applicable with the exception of the Sub-Chapter 3.1.11.5 NOSEWHEEL STEERING failure.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.17
[Rev. 13] 30 JAN 2015
OPERATION WITH INOPERATIVE ANTI-SKID BRAKE CONTROL SYSTEM
NOTE:
3.2.17.1
3.2-23
This Chapter corresponds to Supplement 7 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
This Supplement is applicable only when used in conjunction with a Minimum Equipment List approved by the
appropriate authority.
3.2.17.2
Limitations
The Limitations in Chapter 1 and the Supplement Compatibility Table in Sub-Section 1.5 of the AFM are applicable with the addition of the following:
•
Take-off on wet runways is not permitted.
3.2.17.3
Normal Procedures
The normal procedures in Chapter 2 are applicable with the addition of the following:
FLIGHT COMPARTMENT PREPARATION - POWER ON - FIRST OFFICER
ANTI-SKID Switch ...................................................................................................................................... OFF
NORMAL LANDING
Pedal Brakes .................................................................................... Apply Brakes using Manual Technique
NOTE:
For maximum deceleration with no anti-skid control, brake should be applied intermittently,
with the duration of each application approximately 1 s with intervals of reduced braking as
brief as possible.
CAUTION: Excessive application of pedal brakes can result in skidding and tire failure.
3.2.17.4
Abnormal Procedures
The abnormal procedures in Chapter 3 are applicable with the addition of the following:
BRAKE ANTI-SKID FAILURE (Illumination of INBD ANTI-SKID or OUTBD ANTI-SKID Caution Light)
This procedure is not applicable.
3.2.17.4.1 Engine Failure or Fire during Take-off before V1
Both POWER Levers ................................................................................................................................ DISC
Simultaneously:
BRAKING ............................................................................... Apply Pedal Brakes using Manual Technique
NOTE:
For maximum deceleration with no anti-skid control, brakes should be applied intermittently,
with the duration of each application approximately 1 s, with intervals of reduced braking as
brief as possible.
CAUTION: Excessive application of pedal brakes can result in skidding and tire failure.
NOTE:
Reverse thrust may be used, commensurate with directional control.
ENGINE FIRE
Carry out ON GROUND EMERGENCIES procedure after airplane has stopped (Sub-Chapter 3.1.2.12).
3.2.17.5
NOTE:
Performance Data
The performance data in Chapter 4.12 (AOM Supplement 11) and compatible AFM
Supplement 7 are applicable.
AOM DASH 8-Q400
3.2-24
[Rev. 13] 30 JAN 2015
3.2.18
NOTE:
3.2.18.1
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
OPERATION WITH INOPERATIVE FLIGHT SPOILERS IN GROUND MODE
This procedure corresponds to Supplement 17 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
This Supplement is applicable only when used in conjunction with a Minimum Equipment List approved by the
appropriate authority.
3.2.18.2
Limitations
The Limitations in Chapter 1 and the Supplement Compatibility Table in Sub-Section 1.5 of the AFM are applicable with the addition of the following:
1.
Take-off on a wet runway is prohibited.
3.2.18.3
Normal Procedures
The normal procedures in Chapter 2 are applicable with the addition of the following:
SPOILERS ROLL OUTBD and ROLL INBD advisory lights will not illuminate.
With the SPOILERS FLIGHT TAXI switch at FLIGHT, the INBD ROLL SPLR GND and OUTBD ROLL SPLR
GND caution lights will be illuminated.
3.2.18.4
Abnormal Procedures
The abnormal procedures in Chapter 3 are applicable with the addition of the following:
SPOILERS ROLL OUTBD and ROLL INBD advisory lights will not illuminate.
With the SPOILERS FLIGHT TAXI switch at FLIGHT, the INBD ROLL SPLR GND and OUTBD ROLL SPLR
GND caution lights will be illuminated.
3.2.18.5
Performance Data
The performance data in Chapter 4 and compatible Supplements are applicable with the addition of the following:
NOTE:
Compatible Supplement performance penalties are cumulative.
NOTE:
Where applicable, the performance factor of this Supplement must be applied to the
calculated performance data of a compatible Supplement.
ACCELEARATE-STOP DISTANCE REQUIRED
The accelerate stop distance required flap 5° is increased by 3%, flap 10° is increased by 4% and flap 15° is
increased by 5%.
LANDING FIELD LENGTH REQUIRED
The landing field length required flap 10° is increased by 8%, flap 15° is increased by 15% and flap 35° is
increased by 20%.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.2.19
NOTE:
3.2.19.1
3.2-25
[Rev. 13] 30 JAN 2015
OPERATION WITH LANDING GEAR EXTENDED
This procedure corresponds to Supplement 94 of the AFM.
General
The general information in Chapter 0 is applicable with the addition of the following:
In conjunction with a Minimum Equipment List, approved by local airworthiness authorities and subject to compliance with the limitations outlined in Sub-Chapter 1.10.3 and the operating procedures that follow, the airplane may be operated with the landing gear extended.
The performance penalties outlined in Sub-Chapter 4.8.2 will apply, likewise the Flight Planning Data of SubChapter 4.8.2.1.
NOTE:
3.2.19.2
The data as in Sub-Chapter 4.8.2 and 4.8.2.1 may also be used as a reference for those
situations, when the landing gear will fail to retract after take-off and when a landing at the
departure airport will not be possible.
In this case an in-flight calculation of Flight Time and Trip Fuel to the next suitable aerodrome
will be required.
Emergency Procedures
The emergency procedures in Chapter 3 are applicable with the addition of the following:
3.2.19.2.1 Engine Failure / Fire After V1
Positive rate of climb:
LANDING GEAR Lever ..................................................................................................................... Leave DN
3.2.19.2.2 Engine Failure on Approach-Go-Around
Positive rate of climb:
LANDING GEAR Lever ..................................................................................................................... Leave DN
3.2.19.3
Normal Procedures
The Normal Procedures in Chapter 2 are applicable with the addition of the following:
3.2.19.3.1 Before Entering the Airplane
-
Check landing gear pins are installed, secured and the flags removed.
Check nose gear lock is engaged.
Check landing gear doors closed.
3.2.19.3.2 After Take-Off
LANDING GEAR Lever ..................................................................................................................... Leave DN
Check 3 green gear locked down advisory lights are illuminated,
all amber doors open,
red gear unlocked and
selector lever advisory lights out.
3.2.19.3.3 Go-Around From Final Approach
Positive rate of climb:
LANDING GEAR Lever ..................................................................................................................... Leave DN
AOM DASH 8-Q400
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CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.3
ADVERSE WEATHER CONDITIONS
3.3.1
General
3.3-1
[Rev. 13] 30 JAN 2015
Airplane operations in adverse weather such as windshear, icing, severe turbulence, contaminated runways
and crosswinds add variables to the normal operations.
When applicable, follow the supplemental procedures in this section.
3.3.2
WINDSHEAR
3.3.2.1
Background
Windshear is defined as a sudden change in air mass direction and speed lasting for a measurable period of
time (as opposed to simple turbulence).
Knowledge of how windshear affects aircraft performance is essential to the application of the proper vertical
flight path control techniques during an inadvertent windshear encounter.
While many windshear encounters have been related to weather fronts, strong surface winds, mountain
waves, etc, the worst encounters have involved wet microburst / downburst phenomena associated with thunderstorms.
A microburst or downburst is a shaft of high velocity air moving down from the core of a convective cloud to the
ground where it spreads out in a gust front in all directions.
The wind component is mostly horizontal at altitudes below 500 ft.
Horizontal windshear may improve or degrade vertical flight path performance.
Performance improving windshear will first be indicated in the flight compartment by an increasing airspeed.
Performance improving windshear may be a precursor of a shear that will decrease airspeed and degrade vertical flight path performance.
Accordingly, when windshear is suspected, avoid large power reductions and excessive trim changes in
response to sudden airspeed increases as these may be followed quickly by sudden decreases.
All events will not be in the classic mould of symmetrical outflows as described above. In fact, they can vary to
the extent that the first recognizable encounter might be the decreasing performance tailwind shear.
Crew actions are divided into 3 areas: Avoidance, Precautions and Recovery.
3.3.2.2
Windshear Avoidance
Carefully assess all available information such as pilot reports of windshear or turbulence, low level windshear
alerts and weather reports, including thunderstorm and virga activity.
Avoid areas of known severe windshear.
If severe windshear is indicated, delay take-off or do not continue an approach until conditions improve.
All crews should broadcast any instances of airspeed fluctuation when shear is encountered.
One aircraft, upon entering the outflow area of a downburst, may encounter airspeed fluctuations, but no significant control problems.
Another aircraft on the same flight path a few minutes later, may experience airspeed changes many times
greater than the previous aircraft, accompanied by marked performance degradation and handling difficulties.
3.3.2.3
Windshear Precautions - Take-off
Do Not use a reduced power take-off; use normal take-off power if there are any reports of windshear in the
area.
Use the longest suitable runway, provided it is clear of areas of known windshear.
Be alert for airspeed fluctuations during take-off and initial climb.
Airspeed fluctuations may be the first indication of windshear.
Rotate at the normal pitch rate to the normal take-off pitch attitude.
Minimize reductions from this initial attitude until terrain and obstacle clearance is assured.
Crews should develop an awareness of the normal values of airspeed, attitude, vertical speed and acceleration.
Vertical flight path instruments such as vertical speed indicators and altimeters should be closely monitored.
The PNF (Pilot Not Flying) should call out any deviations from normal.
If the PF (Pilot Flying) feels that vertical flight path control is marginal at any time the PF will call “WINDSHEAR” and carry out the in-flight recovery maneuver outlined below.
AOM DASH 8-Q400
3.3-2
[Rev. 13] 30 JAN 2015
3.3.2.4
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Windshear Precautions - Approach
Utilize all available means in the flight compartment that might indicate the presence of windshear such as
visual indications, pilot reports, radar and flight instruments.
Select the minimum approach / landing flap position consistent with field length and WAT (Weight Altitude Temperature).
Limit and add an appropriate wind correction to VAPP (correction applied in the same manner as gust correction).
Avoid large power reductions or trim changes in response to sudden airspeed increases as these may be followed by airspeed decreases.
Closely monitor the vertical flight path instruments, specifically vertical speed, altimeters and glideslope indicators - increasing the normal cross check between these instruments and the flight director commands.
In this regard, crew coordination is most important, especially at night or in marginal weather conditions.
The PNF should be ready to promptly call out any deviation from normal.
If the PF feels that vertical flight path control is marginal at any time the PF will call “WINDSHEAR” and carry
out the in-flight recovery maneuver outlined below.
3.3.2.5
Windshear In-Flight Recovery - Maneuver
The flight crew must make the determination of marginal flight path control using all the information available in
the flight compartment and react promptly.
This determination is subjective and based on the pilots' judgment of the situation.
As a guideline, marginal flight path control may be indicated by uncontrolled changes from normal steady state
flight conditions in excess of:
•
10 kt indicated airspeed
•
500 ft/min vertical speed
•
5° pitch attitude
•
1 dot displacement from the glideslope
The following action is recommended when preventative action is not successful, or whenever flight path control becomes marginal below 500 ft above the ground on take-off or landing:
•
Initial response - Apply NTOP (detent) power / Rotate to known GA (Go Around) attitude
Provides a fixed pitch target in turbulence
•
Do Not change configuration unless flight path under control.
Aircraft still descending:
•
Increase thrust and pitch attitude
- Firewall power
- Increase pitch target sufficient to stop descent, but Do Not allow airspeed to decrease below V2 / VGA
- Maintain the pitch attitude that achieves V2 / VGA airspeed
•
Stick shaker activates and / or airspeed tape turns red:
Should the stick shaker activate and / or airspeed tape turn red in turbulence (Alternate Symbology aircraft), immediately reduce the pitch attitude sufficient to silence the shaker and achieve an airspeed above
the low speed cue.
In the event this should occur close to the ground, maintain the pitch attitude which silences the shaker,
until terrain contact is no longer a factor, then allow the aircraft to accelerate back to V2 / VGA.
•
Continue climb until clear of terrain.
Clear of terrain:
•
Reduce power and pitch attitude appropriate to the phase of flight.
•
Reconfigure aircraft as necessary.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.3.2.6
3.3-3
[Rev. 18] 21 NOV 2016
Windshear In-Flight Recovery Procedure
PF
Commands “WINDSHEAR”
Simultaneously select GA, advance Power Levers to
detent and smoothly rotate aircraft to GA attitude
PNF
Sets Condition Levers to MAX
Confirms NTOP power on ED
Calls “POWER SET”
Monitor radar altimeter and IVSI,
Calls “<radar altitude> FEET CLIMBING” or
“<radar altitude> FEET DESCENDING”
Aircraft Still Descending
Advance Power Levers to maximum available power
(firewall)
Increase pitch attitude sufficient to stop descent.
Do not allow airspeed to decrease below V2 / VGA
If Stick Shaker Occurs and / or Airspeed Tape Turns Red
Immediately reduce pitch attitude to silence shaker
and achieve an airspeed above the low speed cue
then adjust pitch to return to V2 / VGA
Aircraft Climbing Away From Terrain
Continue climb as required to safe altitude
Monitors radar altitude and baro altitude to determine when airplane is safely clear of obstacles or
terrain
Calls “<obstacle clearance alt ASL> FEET”
Once Clear of Terrain
Reduce power and pitch attitude appropriate to the
phase of flight
Reconfigure aircraft as necessary
Calls “CLEAR OF TERRAIN”
Advise ATC of any deviation to clearance
Do Not change gear or flap configuration if the vertical flight path is not under control.
Optimum aircraft performance (best angle of climb) occurs near 1.13 VS for the aircraft configuration, therefore,
Do Not allow the airspeed to decrease below this speed (Nominally V2 / VGA for the flap configuration).
Unlike a jet aircraft, it is not permissible to continue to increase pitch attitude until stick shaker occurs.
This is because at high power settings the propeller slipstream creates additional lift on the airframe. As a
result, the aircraft could reach a dangerously low indicated airspeed before the shaker activates.
At these very low airspeeds, the aircraft is operating on the extreme “back side” of the Lift / Drag curve with a
significant deterioration of climb capability.
Additionally, the flight controls may not retain sufficient authority to maintain control of the aircraft in turbulence
or following an engine flameout.
Jet aircraft can be flown to shaker because it provides an artificial barrier to reaching very low IAS.
Propeller aircraft normally “create” such a barrier using procedural means instead.
Restricting the aircraft to a minimum airspeed of V2 / VGA during the recovery is a natural choice as these
speeds are readily available to crew members and match optimal climb speed.
The Low Speed Cue on the Q400 aircraft has been designed to overcome the limitations associated with the
stick shaker at high power settings and function as a visual airspeed barrier.
The cue will always display an appropriate minimum airspeed for control of the aircraft regardless of weight,
flap or power setting.
As a result, windshear recoveries can be flown using the low speed cue as an aid to preventing an unacceptable low airspeed condition.
AOM DASH 8-Q400
3.3-4
[Rev. 13] 30 JAN 2015
3.3.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
TURBULENCE
Turbulence can be encountered at any flight level at any time of day or night.
The table below shows the FAA definition of the different levels of turbulence.
Table 3.3-1
Turbulence Definitions and Reports
INTENSITY
AIRPLANE REACTION
REACTION INSIDE AC
Turbulence that momentarily causes slight, erratic Occupants may feel a slight strain
against seat belts or shoulder straps.
changes in altitude and / or attitude.
Unsecured objects may be displaced
Report as Light Turbulence;*
slightly.
or
Light
Turbulence that causes slight, rapid and somewhat Food service may be conducted and
rhythmic bumpiness without appreciable changes in little or no difficulty is encountered in
walking.
altitude or attitude. Report as Light Chop.
Turbulence that is similar to Light Turbulence but of Occupants feel definite strains
against seat belts or shoulder straps.
greater intensity.
Changes in altitude and / or attitude occur but the Unsecured objects are dislodged.
Food service and walking are difficult
airplane remains in positive control at all times.
It usually causes variations in indicated airspeed.
Report as Moderate Turbulence *
Moderate
or
Turbulence that is similar to Light Chop but of
greater intensity. It causes rapid bumps or jolts without appreciable changes in altitude or attitude.
Report as Moderate Chop.
Occupants are forced violently
Turbulence that causes large, abrupt changes in
against seat belts or shoulder straps.
altitude and / or attitude.
Unsecured objects are tossed about.
It usually causes large variations in indicated airSevere
speed. Airplane may be momentarily out of control. Food service and walking are impossible.
Report as Severe Turbulence
Turbulence in which the airplane is violently tossed
about and is practically impossible to control.
Extreme
It may cause structural damage.
Report as Extreme Turbulence.
Occasional - Less than 1/3 of the time.
Intermittent - 1/3 to 2/3
Continuous - More than 2/3
* High level turbulence (normally above 15000 ft ASL) not associated with cumulus form clouds should be
reported as Clear Air Turbulence (CAT) preceded by the appropriate intensity or light or moderate chop.
3.3.3.1
Avoidance
As with all weather hazards, the best action is to stay away from turbulence.
Areas of severe or extreme turbulence may be reported by SIGMETS, ATC or pilot reports.
Areas of severe and extreme turbulence are known to exist:
•
Near Frontal Activity
•
Near the Jetstream
•
On the leeward side of mountains
•
In Areas of Convective Activity
Convective activity will produce turbulence within the convective formation, underneath the formation (sometimes in the form of a microburst), or above it.
Weather radar can be used to stay away from areas of heavy convective build up.
Areas of strong build up should be avoided by at least 20 NM and topped by at least 2000 ft.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.3.3.2
3.3-5
[Rev. 13] 30 JAN 2015
Severe Turbulence Encounter
If severe turbulence is encountered:
•
Disengage the autopilot.
•
Maintain control of the airplane by primary reference to attitude (ADI).
•
Allow airspeed and altitude to fluctuate as required.
•
Avoid sudden or large power and control inputs.
•
Reduce IAS to Rough Air Speed
•
Avoid use of large bank angles due to increased wing loading
Report any severe or extreme turbulence to so that other pilots know of the hazard.
3.3.4
WAKE TURBULENCE
Wake turbulence is caused by wing tip vortices.
When an airfoil creates lift, it causes wing tip vortices.
The higher pressure below the wing will try to equalize with the lower pressure on top.
The air will do this by moving around the wing tip from the bottom to the top in a swirling movement, causing
vortices.
The vortices are strongest when the airplane is heavy, slow and clean (flaps and slats retracted).
3.3.4.1
Induced Roll Control Factors
The usual hazard associated with induced rolling moments is exceeding the roll-control capability of the airplane.
The governing factor in the ability for the airplane to counter control the roll tendency is the wingspan and control responsiveness of the airplane.
The shorter the wingspan of the airplane relative to the generating airplane, the more difficult it will be to counteract the rolling tendencies.
3.3.4.2
Induced Pitch Control Factors
When an airplane crosses the wake of another airplane, it will experience pitching motions and vertical loads
quite similar to a gust encounter.
Crosstrack penetration, whether it is a clockwise vortex penetration or counter-clockwise vortex penetration,
typically lasts a very short time.
This minimizes the effects of the vortex.
Pilots normally do not lose control of the airplane, but structural loads and loss of altitude can create hazards.
AOM DASH 8-Q400
3.3-6
[Rev. 13] 30 JAN 2015
3.3.4.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Vortex Behavior
Because vortices are a by-product of lift, they are made from the time the airplane leaves the ground until it
touches down again.
Before take-off or touchdown, pilots should note the rotation or touchdown point of the preceding airplane.
Vortices from larger airplanes sink at a rate of several hundreds ft/min, slowing their descent and diminishing in
strength with time and distance behind the generating airplane.
Atmospheric turbulence hastens breakup.
Pilots should fly at or above the preceding airplane’s path, changing course as necessary to stay away from
the area behind and below the airplane.
A vertical separation of 1000 ft may be considered safe.
When vortices of larger airplanes sink close to the ground (within 100 to 200 ft), they move laterally over the
ground at a speed of about 5 kt.
A crosswind will slow the lateral movement of the upwind vortex and increase the movement of the downwind
vortex.
A light wind with a cross runway component of 1 to 5 kt could keep the upwind vortex in the touchdown zone
for a period of time and increase the drift of the downwind vortices toward another runway.
A tailwind condition can move the vortices of the preceding airplane forward into the touchdown zone.
The light quartering tailwind is the most concern.
Pilots should be alert to large airplanes upwind from their approach and take-off flight paths.
3.3.4.4
•
Considerations
Be aware of wake turbulence when holding near a runway.
•
Before crossing a runway, wait a few minutes after a large airplane has taken off or landed.
•
When taking off behind a larger airplane plan to rotate before the larger airplane’s rotation point.
•
Climb above and upwind of the larger airplane’s climb path until clear of its wake.
•
Do Not fly below and behind a large airplane’s flight path.
•
If landing after a departing airplane, touchdown before its rotation point.
•
If landing after a large airplane, stay above the other airplane’s path and land after its touchdown point.
•
When landing after a large airplane on a parallel runway closer than 2500 ft, beware of possible drifting of
the vortex to your runway.
NOTE:
3.3.5
ATC will provide separation for airplane, but it is still the pilot’s responsibility to avoid wake
turbulence.
VOLCANIC ASH
Flight in volcanic ash can cause damage to airplane surfaces and engines.
Engine failures are a common result of flight in volcanic ash.
Airplane heat, hydraulic and electrical systems can also be contaminated.
Volcanic ash is heavy, and large quantities of contamination can have an unwanted effect on airplane mass
and balance.
Aviation radar is not good at finding volcanic ash clouds.
Ash from volcanic eruptions can quickly reach 60000 ft and be blown more than 2400 NM.
Pilots must not enter visible volcanic ash clouds.
There is an increased risk of entering volcanic ash at night or in instrument conditions.
If a given area has any reported risk of volcanic ash, it must not be entered until it is found to be safe.
St. Elmo’s fire will usually occur if flying in volcanic ash at night.
Pilots must leave the area quickly if they fly into volcanic ash.
Report any volcanic ash or eruption seen to ATC.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4
SPECIAL PROCEDURES
3.4.1
FLIGHT TEST PROCEDURES
3.4.1.1
Introduction
3.4-1
[Rev. 13] 30 JAN 2015
Procedures presented under this Sub-Chapter may only be used for NON-COMMERCIAL FLIGHT OPERATIONS.
These procedures are not covered by approved supplements to the Airplane Flight Manual.
Depending upon local requirements, an individual flight permit may be needed from the competent authority.
3.4.1.2
General
Flight test procedures are special operating checks not routinely performed every flight and are accomplished
when certain airplane systems are to be tested for proper operation in flight.
The following recommended procedures must be adhered to, in order to ensure the safe conduct of the functional test to be performed.
3.4.1.3
Aileron Trim Flight Test Procedure
NOTE:
Paper measuring tape must be applied to control wheel as per AMM TASK 27-13-11- 830-803
to measure control wheel angle.
The paper measuring tape is an 82% reduction and consequently the increments are not true
inches.
Aircraft ................................................................................................................................ Straight and Level
Airspeed ................................................................................................................................................... 200 kt
AP / YD .............................................................................................................................................. Push OFF
SPLR 1 and SPLR 2 .......................................................................................................................... Push OFF
ROLL SPLR INBD HYD, ROLL SPLR OUTBD HYD and SPLR OUTBD caution lights illuminate.
Confirm inboard and outboard spoilers indicate fully retracted on PFCS display.
Rudder ........................................................................................................................................................ Trim
Trim ball centred with feet off the rudders.
Aileron ........................................................................................................................................................ Trim
Trim wings level with hands off the control wheel.
Record aileron trim and wheel position in the Table below:
Item
Flight #
Aileron Trim
Wheel Position
NOTE:
200 KIAS
260 KIAS
Limits
± 0.5 divisions
8 ± 1/32 in
The paper tape utilizes the 2 in section between 7 and 9 in.
8 in are used as a centre line reference only.
CAUTION: If aileron trim is greater than 0.75 division airspeed must be limited to 200 KIAS for
remainder of flight.
If aileron trim is between 0.5 and 0.75 divisions, airspeed must be limited to the
airspeed at which 1 1/2 divisions of trim is required to maintain wings level.
Airspeed .............................................................................................................................................. Increase
Increase airspeed to 260 kt in level flight.
Confirm no unusual airframe vibrations.
Record aileron trim and wheel position once again.
SPLR 1 and SPLR 2 ............................................................................................................................ Push ON
ROLL SPLR INBD HYD, ROLL SPLR OUTBD HYD and SPLR OUTBD caution lights go out.
YD ................................................................................................................................................................. ON
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3.4-2
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CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.2
SUPPLEMENTAL PROCEDURES
3.4.2.1
Introduction
Procedures presented under this Sub-Chapter are not covered by the approved Airplane Flight Manual.
Local regulatory approval may be required.
3.4.2.2
General
Where corrective action to the affected system, has not been implemented through a modification and / or Service Bulletin, the following procedures provide the means to reset specific nuisance caution lights, advisory
messages or system faults.
The following general procedures MUST be adhered to in order to ensure the continued safe operation of the
aircraft:
1.
These procedures may only be used during ground operations;
2.
Any procedure detailing the reset (pull out and push in) of circuit breakers may only be used one time for
each nuisance indication; and
3.
If these procedures are not sufficient to clear the nuisance indication, then the MEL must be used if applicable or the problem must be rectified prior to aircraft dispatch.
3.4.2.3
Air Conditioning, Pressurization and Pneumatics
Erroneous CABIN Temperature Indication
(Flight compartment indication of cabin temperature reads up to 9ºC higher than FA’s panel reading)
-
No maintenance action required.
Operation of the ECS system is unaffected.
Erroneous Single “BLEED HOT” Caution Light
(The respective “BLEED HOT” Caution light goes out after landing)
Under certain flight conditions, the bleed control system will open the High Pressure port (P3) for short periods,
causing the respective “BLEED HOT” Caution light to illuminate.
The following procedure may be used to determine if this is a momentary event:
If the respective “BLEED HOT” Caution light goes out after landing:
Bleed Air (affected engine) ........................................................................................................................... ON
Power Lever (affected engine) ............................................................................................................ Increase
Increase to above FLT IDLE until bleed stage switching occurs.
Bleed stage switching can be observed by monitoring the appropriate de-ice pressure gauge, on the co-pilot’s
side panel, for the pressure needle to move slightly.
If the respective “BLEED HOT” Caution light illuminates:
-
Maintenance action is required prior to next flight.
If the respective “BLEED HOT” Caution light does not illuminate:
-
Monitor the Bleed system on subsequent flights.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-3
[Rev. 13] 30 JAN 2015
Poor ECS Temperature Control
(Recommended procedure to improve temperature control throughout the aircraft)
RECIRC Fan ................................................................................................................................................. ON
CABIN / FLT COMP PACKS ...................................................................................................................... Auto
Temp Controls ................................................................................................................................ 12 O’Clock
Bleed Selector ........................................................................................................................... NORM or MAX
Flight Compartment Gasper Vents (4 places) .............................................................................. Fully Open
Flight Compartment / Side Window De-Mist Flow Control Levers ............................................ Fully Open
-
Wait at least 5 min for compartment temperatures to stabilize
If a temperature adjustment is required:
Temp Control ..................................................................................................... Adjust by a Small Increment
-
Wait at least 5 min for compartment temperatures to re-stabilize before making a further adjustment
Hot Cabin During Boarding
(Recommended procedure to minimize overheating the cabin during boarding in cold weather)
RECIRC Fan ................................................................................................................................................. ON
CABIN / FLT COMP PACKS ...................................................................................................................... Auto
Temp Controls ................................................................................................................................ 12 O’Clock
Bleed Selector ........................................................................................................................... NORM or MAX
Flight Compartment Gasper Vents (4 places) .............................................................................. Fully Open
Flight Compartment / Side Window De-Mist Flow Control Levers ............................................ Fully Open
Flight Compartment Door ..................................................................................................................... Closed
-
To avoid overheating the cabin, maintain temperature controls at 12 o’clock.
Compartment temperatures will stabilize after passenger doors are closed.
Cold Soaked Aircraft
(Recommended procedure to heat aircraft cabin after the aircraft has been cold-soaked overnight)
RECIRC Fan ................................................................................................................................................. ON
CABIN / FLT COMP PACKS ...................................................................................................................... Auto
Temp Controls ................................................................................................................................ 12 O’Clock
APU Bleed .................................................................................................................................................... ON
Flight Compartment Gasper Vents (4 places) .............................................................................. Fully Open
Flight Compartment / Side Window De-Mist Flow Control Levers ............................................ Fully Open
Flight Compartment Door ..................................................................................................................... Closed
-
Maintain temperature control at 12 o’clock until compartment temperatures have stabilized.
-
To avoid duct temperature overshoots and triggering a DUCT HOT caution light, Do Not select Packs to
MAN.
AOM DASH 8-Q400
3.4-4
[Rev. 13] 30 JAN 2015
3.4.2.4
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
APU, Engines and Propellers
Overspeed Governor Test
-
Position aircraft into wind.
Power Levers ................................................................................................................................... Flight Idle
Condition Levers ...................................................................................................................................... MAX
Prop O’Speed Governor Test ...................................................................................................... Hold at Test
-
Wait for OSG TEST IN PROG message on ED
Power Levers ......................................................... Slowly advance until OSG TEST PASS appears on ED
NOTE:
Test must be completed within 60 s of OSG TEST IN PROG appearing on ED.
Power Levers ................................................................................................................................... Flight Idle
Prop O’Speed Governor Test ............................................................................................................. Release
If POWERPLANT and OSG TEST ABORT or OSG TEST FAIL messages appear on the ED:
-
Repeat overspeed governor test to achieve pass.
NOTE:
If the overspeed governor test fails, the # 1 PEC or # 2 PEC caution light will come on in
addition to the OSG TEST FAIL message.
If POWERPLANT and OSG TEST FAIL messages appear again on the ED:
-
Maintenance action is required prior to next flight.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-5
[Rev. 13] 30 JAN 2015
Continuous Illumination of Engine SELECT Light
(Fault Isolation)
NOTE:
-
Pilots may perform this fault isolation procedure, on the ground only, to reset the Engine
SELECT Light, under the guidance of maintenance and in accordance with their approved
maintenance program.
With both engines running, ensure the electrical system is in normal configuration.
NOTE:
If SELECT Light illuminates after the start of the first engine, continue with the start sequence
of the second engine and then accomplish the procedure below.
DC External Power ..................................................................................................................................... OFF
AC External Power ..................................................................................................................................... OFF
-
Check # 1 and # 2 DC GEN Caution lights are not illuminated.
Bus Fault Reset Switch .......................................................................................................................... Reset
Engine SELECT Light remains illuminated:
Shutdown Procedure (below) ................................................................................................ Accomplish
- END Engine SELECT Light goes out:
# 1 DC Gen Switch ................................................................................................................ OFF then ON
Engine SELECT Light illuminates:
Shutdown Procedure (below) ......................................................................................... Accomplish
- END Engine SELECT Light does not illuminate:
# 2 DC Gen Switch ......................................................................................................... OFF then ON
Engine SELECT Light illuminates:
Shutdown Procedure (below) ................................................................................... Accomplish
- END Engine SELECT Light does not illuminate: Aircraft is serviceable.
------------- END ------------SHUTDOWN PROCEDURE (If Engine SELECT Light remains Illuminated)
Main, AUX and STBY Batteries ................................................................................................................. OFF
Condition Levers ............................................................................................................................. FUEL OFF
APU Power .................................................................................................................................................. OFF
-
Carry out the remaining portions of Normal Shutdown procedure.
NOTE:
Maintenance action required prior to next flight.
AOM DASH 8-Q400
3.4-6
[Rev. 13] 30 JAN 2015
3.4.2.5
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Autoflight, Flight Instruments and Navigation
“DU BAD CONF”
(Message on ED)
(Message appears after displays powering on)
PFD 1 and 2, MFD 1 and 2, and ED ...................................................................... OFF then ON (one at a time)
NOTE:
Wait 30 s for self-test to complete on each individual display before selecting the next display ON
If message remains on:
-
Maintenance action is required prior to next flight.
Erroneous SAT Indications
(SAT differs from reported OAT by more than ± 2°C)
Monitor SAT indication during taxi with # 1 engine operating and propeller selected out of feather.
If erroneous indications remain:
-
Maintenance action is required prior to next flight.
“ALT”
(Red annunciation on ARCDU ATC display area)
(Annunciation appeared on ARCDU main page ATC area during climb or descent.)
NOTE:
A red “FAIL” annunciation is also displayed in the ALT and TCAS display areas
on the TCAS / ATC expanded page.
If annunciation remained on after aircraft levelled off:
-
Maintenance action is required prior to next flight.
“FANS FAIL”
(Message on ED)
(Message appears after starting an engine in an aircraft with a cold flight compartment)
Monitor message as flight compartment warms.
If message remains on after flight compartment temperature rises:
-
Maintenance action is required prior to next flight.
NOTE:
FANS FAIL message will clear when flight compartment temperature sensors warm above 5°C.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-7
[Rev. 14] 27 MAY 2015
Weather Radar Display Frozen
(Weather radar data on MFD did not appear to update or respond to control panel inputs)
-
Position aircraft so as to ensure that no ground personnel, equipment, aircraft, vehicles or buildings are in
the radar scan area within 300 ft (100 m).
WARNING:
Exposure to microwave radiation may cause serious bodily injury to personnel or
ignite combustible materials.
WX Radar ............................................................................................................... OFF, Wait 20 s, then STBY
WX Radar .................................................................................................................................................... TST
-
Confirm yellow WX TEST and STAB OFF mode messages are annunciated and weather radar test pattern
is displayed on the MFD.
WX Radar ..................................................................................................................................................... ON
-
Confirm WX ON mode is annunciated.
NOTE:
A blue pattern may be displayed on the MFD, if the required 60 s warm up period has not
elapsed before the system will transmit.
TILT .......................................................................................................................................................... Adjust
-
Adjust tilt to obtain targets (weather or ground) for display on the MFD.
Confirm tilt angle display changes in response to inputs.
WX Radar ................................................................................................................................................. STBY
If display data did not update or respond:
-
Maintenance action is required prior to next flight.
Ghost or Mirror Images on Integrated Standby Instrument
(The ISI displays ghost or mirror images following initial application of power to the aircraft
after the aircraft has been cold-soaked)
-
Wait a minimum of 5 min for the ISI to warm up.
ISI CB (Left Lower CB Panel - H1) ........................................................................................................... Reset
NOTE:
Wait until ISI alignment sequence is complete.
If ghost or mirror images remain on the ISI:
-
Maintenance action is required prior to next flight.
AOM DASH 8-Q400
3.4-8
[Rev. 14] 27 MAY 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
“WX FAIL”
(Message on MFD)
(Message appeared during operation of WX radar)
-
Position aircraft so as to ensure that no ground personnel, equipment, aircraft, vehicles or buildings are in
the radar scan area within 300 ft (100 m).
WARNING:
Exposure to microwave radiation may cause serious bodily injury to personnel or
ignite combustible materials.
WX Radar ................................................................................................................ OFF, Wait 20 s, then STBY
WX Radar ..................................................................................................................................................... TST
- Confirm yellow WX TEST and STAB OFF mode messages are annunciated and
weather radar test pattern is displayed on the MFD.
WX Radar ...................................................................................................................................................... ON
- Confirm WX ON mode is annunciated.
NOTE:
A blue pattern may be displayed on the MFD, if the required 60 s warm up period has not
elapsed before the system will transmit.
TILT ......................................................................................................................................................... Adjust
- Adjust tilt to obtain targets (weather or ground) for display on the MFD.
Confirm tilt angle display changes in response to inputs.
WX Radar .................................................................................................................................................. STBY
If display data did not update or respond:
- Maintenance action is required prior to next flight.
Central Diagnostic System
(Procedure to retrieve faults logged by the Central Diagnostic System)
NOTE:
-
Pilots can interrogate the CDS and reset certain faults under the guidance of maintenance, in
accordance with their approved maintenance program.
Open the aircraft Maintenance Panel located above the wardrobe compartment.
System Rotary Selector ............................................................................................................................ OFF
CDS GND MAINT Switch .............................................................................................................................. Up
- Confirm the CDS GND MAINT light illuminates.
- Use either ARCDU to access the CDS.
ARCDU ......................................................................................................................................... Press MAINT
- The CDS main menu is shown as follows:
AVIONICS
OTHER SYSTEMS
AVIONIC DATA
ARCDU ............................................... Press corresponding line, Select key to access desired Sub-Menu
- Repeat as required to get to the desired system faults page.
After obtaining fault data:
ARCDU .................................................................................... Press PREV to return to the CDS Main Menu
ARCDU .................................................................................................................................... Press DIM / RTN
- The ARCDU display returns to the normal Radio Tuning Page 1 / 2.
CDS GND MAINT Switch ......................................................................................................................... Down
- Confirm the CDS GND MAINT light goes out.
- Close aircraft Maintenance Panel.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-9
[Rev. 14] 27 MAY 2015
Inoperative PA Chime
(During 1st flight of the day)
PA AMP CB (Left Upper CB Panel - B8) .................................................................................................. Reset
-
Ensure PA system is operational prior to boarding.
3.4.2.6
Electrical
Tripped Circuit Breaker
(Circuit breaker(s) tripped after initial power-up of aircraft on ground)
NOTE:
This procedure MUST not be used if there is a recent history of reported defects with the
system or related systems that are associated with the tripped circuit breaker(s) or if there is
other evidence of anomalies with these systems.
•
Pull out tripped circuit breaker to ensure it is fully disengaged.
•
Push in circuit breaker until it re-engages.
If the circuit breaker trips again:
•
-
Do Not attempt any further resets.
Maintenance action is required prior to next flight.
“DC BUS”
(Caution Light)
(Associated with attempted APU start from batteries)
APU PWR .................................................................................................................................................... OFF
Bus Fault Reset ....................................................................................................................................... Reset
If DC Bus Caution Light goes out:
-
Further APU start attempts may only be performed using an external DC power source.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-10
[Rev. 14] 27 MAY 2015
3.4.2.7
Flight Controls
“ROLL SPLR INBD GND” and “ROLL SPLR OUTBD GND”
(Caution Lights)
(Associated with reversal of the Flight / Taxi switch from Flight to Taxi back to Flight)
-
Clear active runway and park aircraft.
Flight / Taxi ................................................................................................................................................. Taxi
FCS ECU 1 and 2 CBs
(Left Lower CB Panel - M3 and Right Lower CB Panel - L6) ........................................ Reset Simultaneously
NOTE:
Wait 90 s until self-test sequence is complete before moving flight controls.
Flight Controls ................................................................................................................... Check / Full Travel
If Caution Lights remain on:
-
Maintenance action is required prior to next flight.
Erroneous Take-off Warning Horn
(Associated with elevator trim indication near the extreme ends of the take-off range)
Elevator Trim ............................................................... Reset to ensure indication is fully within T/O range
Flap .................................................................................................................................... 5, 10 or 15 Set / Ind
Condition Levers ...................................................................................................................................... MAX
Flight / Taxi ................................................................................................................................................. Taxi
-
Confirm all spoilers fully retracted.
Emerg Brake .............................................................................................................................................. OFF
T/O Warning ............................................................................................................................................... Test
If Take-off Warning Horn sounds:
-
Maintenance action is required prior to next flight.
Emerg Brake ................................................................................................................................................ ON
“FLAP POWER”
(Caution Light)
(Associated with movement of Flap Lever without # 1 hydraulic system pressure)
Flap Lever ..................................................................................................... Select to match Flap Indication
FLAPS CONT CB (Left Lower CB Panel - L7) .......................................................................................... Reset
NOTE:
Wait 10 s for self-test to complete.
With MS 4-113547 Incorporated:
NOTE:
In flight, wait 20 s for self-test to complete.
On the ground, wait 30 s for the self-test to complete.
If Caution Light remains on:
-
Maintenance action is required prior to next flight
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-11
[Rev. 14] 27 MAY 2015
“RUD HYD 1” or “RUD HYD 2”
(Caution Lights)
(Caution light remains illuminated after completion of engine start)
FCS ECU 1 and 2 CBs
(Left Lower CB Panel - M3 and Right Lower CB Panel - L6) ......................................... Reset Simultaneously
NOTE:
Wait 90 s until self-test sequence is complete before moving flight controls.
Flight Controls ................................................................................................................... Check / Full Travel
If Caution Light remains on:
-
Maintenance action is required prior to next flight.
AOM DASH 8-Q400
3.4-12
[Rev. 14] 27 MAY 2015
3.4.2.8
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Hydraulic Power
AVOIDANCE OF HYDRAULIC FLUID TRANSFER
(Recommended method to apply and release Park Brake
to avoid transfer of hydraulic fluid from System 1 to System 2)
System 1 and 2 Pressure ............................................................................................................ 2900 psi MIN
Pedal Brakes ........................................................................................................................................... Apply
Park / Emerg Brake ............................................................................................................... Apply or Release
Pedal Brakes ........................................................................................................................................ Release
With MS 4-126354 and (MS 4-901472 or MS 901473) Incorporated:
PTU “FAIL”
(Advisory Light)
(Associated with automatic or manual selection of PTU without # 1 hydraulic system pressure)
HYD PWR XFR CB (Right Lower CB Panel - L8) ..................................................................................... Reset
-
Wait 5 s.
If Advisory Light remains on:
-
Maintenance action is required prior to next flight.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.2.9
3.4-13
[Rev. 14] 27 MAY 2015
Ice and Rain Protection / Stall Protection
“PROP DEICE”
(Caution Light)
(Associated with selection of PROP DEICE after unfeathering propellers)
Prop Selector ............................................................................................................................... OFF then ON
If Caution Light remains on:
PROP DEICE CONT CBs
(Left Lower CB Panel - L6 and Right Lower CB Panel - E5) ......................................... Reset Simultaneously
If Caution Light remains on:
-
Maintenance action is required prior to next flight
“PUSHER SYST FAIL”
(Caution Lights)
(Associated with incomplete stall test)
-
Repeat stall test to achieve pass.
If Caution Light remains on:
-
Maintenance action is required prior to next flight.
With MS 4-457056 or MS 4-126263 or MS 4-125307 (V 710 Stall Protection Module) Incorporated:
“PUSHER SYST FAIL”
(Caution Light)
(Caution light illuminates 30 s after landing)
SPM 1 and SPM 2 CBs (Left Upper CB Panel - F2 and F5) ......................................... Reset Simultaneously
If Caution Light remains on:
-
Maintenance action is required prior to next flight.
If Caution Light goes out:
-
The flight may depart but check for illumination of the caution light after the next landing.
-
Should the light re-appear, maintenance action is required prior to subsequent flight.
AOM DASH 8-Q400
3.4-14
[Rev. 13] 30 JAN 2015
3.4.2.10
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Landing Gear
Brake Wear
(Braking Technique for Carbon Brakes)
The mechanisms affecting brake wear are very different for steel and carbon brake assemblies.
The number of brake applications has the biggest impact on carbon brake wear.
•
Taxi:
Flight crew should avoid riding the brakes during taxi operations.
Taxi speed should be regulated primarily through the use of power (DISC).
At slow speeds, if the brakes are required, they should be used smoothly and positively applied towards
maximum pressure to enable a complete stop.
•
Landing Ground Roll:
Deceleration techniques on landing will vary depending on the length of the runway and the type of available exits.
If the runway is short, it is recommended that Flight Crews apply the brakes immediately after touchdown,
coupled with aerodynamic braking through the use of DISC.
Strong, positive brake application is most effective and ensures the brakes reach their optimum operating
temperature when bringing the aircraft to an acceptable taxi speed or a complete stop.
Using the brakes for short duration and / or light application will cause premature wear.
If the runway is long, without a high speed turnoff, the aircraft will have to be at a very slow taxi speed in
order to make the 90° turn off the runway.
If the brakes are required, they should be applied ahead of the planned turn off at a distance sufficient to
achieve the desired taxi speed with the use of strong, positive brake application.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.2.11
Single Engine Taxi Operations
3.4.2.11.1
General
3.4-15
[Rev. 13] 30 JAN 2015
At the option of the operator, single engine taxi operations may be performed in accordance with the operational considerations and procedures contained in this section.
Operators may incorporate the information contained herein, into their flight operations documentation, as necessary.
This supplemental procedure does not constitute operational approval to conduct single engine taxi operations.
3.4.2.11.2
Operational Considerations
Single engine taxi operations may be considered for use on hard surfaced taxiways and ramps with the # 2
engine operating and the # 1 engine either shutdown or running in Start & Feather.
Aircraft ground handling characteristics during single engine taxi require greater anticipation of turn direction,
turn radius, wind and varying taxiway slopes to avoid large power changes.
Turns into the operating engine may require forward momentum prior to commencing the turn.
Application of power above flight idle may be required and should be performed with regard for the effect of
propeller slipstream on surrounding objects and personnel.
Contamination of taxiway or ramp surfaces will reduce the effectiveness of nose steering and single engine taxi
should be avoided where there is any possibility of nose tire skidding.
At any time deemed necessary by the Captain, single engine taxi operations should be discontinued and the #
1 engine started to continue taxi to the runway or parking.
Single engine taxi before take-off is commenced with # 2 engine start carried out in the parking position or
during push back.
# 1 engine start is delayed until an appropriate point during taxi allowing sufficient time remaining for Pre-Takeoff Checks to be performed and engine to reach stable internal temperatures before take-off.
Although there is no formal limitation defining time between engine start and application of take-off power, provided engine oil temperature is above 0°C, Pratt and Whitney Canada (PWC) recommend a warm-up period of
at least 5 min.
This protects the mission profile assumptions used to establish engine component life limits and inspection
intervals.
Single engine taxi after landing is carried out by shutting down the # 1 engine after the aircraft is clear of the
runway and preferably after the After Landing checks have been completed.
During single engine taxi operations, in the event of a loss of # 1 hydraulic system pressure, normal braking will
be lost.
In the event of the failure of the # 2 engine, both normal braking and nose steering will be lost.
In both instances, it will be necessary to use the Emergency Brake to bring the aircraft to a stop.
Single engine taxi operations are not compatible with:
1.
# 1 engine operating and # 2 engine either shutdown or running in Start & Feather;
2.
The following system failures:
a. Nose wheel Steering System inoperative
b. Any Hydraulic System failure
c.
Use of Alternate Landing Gear Extension
d. # 2 DC Generator inoperative
e. # 2 AC Generator inoperative
AOM DASH 8-Q400
3.4-16
[Rev. 15] 30 OCT 2015
3.4.2.11.3
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Engine and Propeller Ground Operating Limitations
The limitations in Chapter 1 are applicable.
3.4.2.11.4
Normal Procedures
The normal procedures in Chapter 2 are applicable with the addition of the following:
3.4.2.11.4.1
Engine Start Procedure
After the completion of # 2 Engine Start, carry out AFTER START procedure (Sub-Chapter 2.17.5.4) with the
the following substitutions:
EXT PWR / APU .......................................................................................................................................... OFF
After # 2 Engine has started and stabilized, set the DC EXT PWR switch to OFF and make sure:
•
DC EXTERNAL POWER advisory light on the MFD – Electrical Systems page goes off.
•
Signal ground crew to remove external power cable.
•
# 2 DC GEN caution lights goes off.
Main Bus Tie ................................................................................................................................................ ON
Bleed Air 2 ................................................................................................................................. ON / As Req’d
•
Set BLEED 2 AIR CONTROL switch to 2 position.
•
Turn the BLEED FLOW CONTROL rotary knob to the desired position.
Condition Lever 2 .......................................................................................................................... MAX / 1020
Move # 2 CONDITION LEVER to MAX / 1020 position and make sure:
•
Propeller unfeathers and
•
# 2 AC GEN, L TRU and R TRU caution lights go off.
STBY HYD PRESS ....................................................................................................................................... ON
Check STBY HYD PRESS ON advisory light illuminates.
NOTE:
Do Not select PTU on until after the completion of Flap selection and Rudder Control check.
Continue with the remaining items of Sub-Chapter 2.17.5.4, AFTER START.
After flap selection and completion of Rudder Control check:
PTU CNTRL .................................................................................................................................................. ON
Check PTU CNTRL ON and PTU pressure
(with MS 4-126354 and (MS 4-901472 or MS 4-901473)) PTU CNTRL ON advisory light illuminates.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.2.11.4.2
3.4-17
[Rev. 15] 30 OCT 2015
# 1 Engine Start Procedure
Carry out the start procedure for # 1 engine (Sub-Chapter 2.17.5.3, START APPROVED - boxed items) prior to
conducting Taxi checks.
After # 1 Engine has started and stabilized, make sure:
• # 1 DC GEN caution light goes out.
MAIN BUS TIE Switch ................................................................................................................................ OFF
Bleed Air 1 ................................................................................................................................. ON / As Req’d
MAIN, AUX and STBY BATT Temperature Indications ........................................................................ Check
Check on ELECTRICAL page of MFD
Condition Lever 1 ........................................................................................................................... MAX / 1020
Move # 1 CONDITION LEVER to MAX / 1020 position and make sure:
•
Propeller unfeathers and
•
# 1 AC GEN caution light goes out.
NOTE:
3.4.2.11.4.3
Operators may choose to commence the Taxi checks prior to starting the #1 engine, however,
Do Not select Autofeather ON or test the Take-off Warning system until after the Condition
Lever 1 is positioned to MAX/1020 following engine start.
After Landing
After completion of AFTER LANDING checks (Sub-Chapter 2.17.5.13) add the following items:
When ready to shut down the # 1 engine:
POWER Lever 1 ........................................................................................................................................ DISC
Condition Lever 1 ............................................................................................................. START & FEATHER
Allow engine to stabilize for 30 s minimum before shutdown.
BLEED 1 ...................................................................................................................................................... OFF
Condition Lever 1 ............................................................................................................................ FUEL OFF
NOTE:
Operators may choose to conduct the AFTER LANDING checks after selecting the Condition
Lever 1 – START & FEATHER
3.4.2.11.5 Abnormal Procedures
The abnormal procedures in Chapter 3 are applicable with the addition of the following:
3.4.2.11.5.1
# 2 Engine Failure or No Hydraulic Pressure Indicated in # 1 Hydraulic System
During Single Engine Taxi
Both POWER Levers ................................................................................................................................ DISC
Braking ............................................................................. Attempt Normal Braking until aircraft is stopped
If aircraft cannot be stopped using normal brake application:
EMERG BRAKE Lever ................................................................... Apply Smoothly until aircraft is stopped
NOTES:
1. With # 2 Engine failed, normal wheel brakes and nosewheel steering are inoperative.
2. Emergency brake application is proportional to lever travel with no differential braking.
3. The approximate number of EMERG / PARK BRAKE applications is 6.
CAUTION: Excessive application of emergency braking can result in skidding and tire failure.
After aircraft is stopped:
EMERG BRAKE Lever ............................................................................................................................. PARK
Carry out ENGINE SHUTDOWN procedure. See Sub-Chapter 3.1.2.27.
AOM DASH 8-Q400
3.4-18
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.3
SAFETY OF FLIGHT SUPPLEMENT, ABNORMAL and EMERGENCY CHECKLISTS
3.4.3.1
Introduction
The intent of this Safety of Flight Supplement is to recommend pilot techniques associated with accomplishing
selected Abnormal and Emergency Checklists (AECs) and provide guidance for situations beyond the scope of
AECs.
Aircrews are expected to accomplish AECs listed in the QRH.
These checklists ensure maximum safety until appropriate actions are completed and a safe landing is accomplished.
Techniques discussed in this Safety of Flight Supplement minimize workload, improve crew coordination,
enhance safety and provide a basis for standardization.
3.4.3.2
Abnormal / Emergency Checklist Guidelines
When a non-normal situation occurs, the following guidelines apply:
•
Non-Normal Recognition
-
•
The crew member recognizing the malfunction calls it out clearly and precisely.
Maintain Airplane Control
-
It is mandatory that the Pilot Flying (PF) flies the airplane while the Pilot Monitoring (PM) accomplishes
the AEC.
Maximum use of the Flight Director / Autopilot is recommended to reduce crew workload.
•
Analyze the Situation
-
AECs should be accomplished only after the malfunctioning system has been positively identified.
NOTE:
•
Pilots should don oxygen masks and establish communications anytime oxygen deprivation or
air contamination is suspected, even though an associated warning has not occurred.
Take the Proper Action
-
Although many in-flight non-normal situations may require immediate corrective action, difficulties can
be compounded by the rate the PF issues commands and the speed of execution of the PM.
-
Commands must be clear and concise, allowing time for acknowledgement of each command prior to
issuing further commands.
-
The PF must exercise positive control by allowing time for acknowledgment and execution.
-
The other crew members must be certain their reports to the PF are clear and concise, neither exaggerating nor understating the nature of the non-normal situation.
This eliminates confusion and ensures efficient, effective and expeditious handling of the non-normal
situation.
•
Evaluate the Need to Land
-
If the AEC directs the crew to land immediately at the nearest suitable airport or if the situation is so
identified in the QRH, diversion to the nearest airport where a safe landing can be accomplished is
required.
If the AEC does not direct landing immediately at the nearest suitable airport, the pilot must determine if
continued flight to destination may compromise safety.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4.3.3
3.4-19
[Rev. 13] 30 JAN 2015
Troubleshooting
Troubleshooting can be defined as taking steps beyond the published checklist in an effort to improve or correct a non-normal condition.
Examples of this are as follows:
-
Attempting to reset a system or cycling a circuit breaker when not prescribed by the AEC.
-
Using maintenance-level information to dictate crew actions.
-
Use of switches and controls intended only for maintenance.
NOTE:
With the availability of today’s communication channels, there seems to be a tendency that
flight crews request help from maintenance during abnormal situations.
Clearly, maintenance crew typically Do Not have the operational background or the situational
awareness of the flight crew’s non-normal environment.
Maintenance crews will use a different methodology to handle problems that may not be
appropriate for an in-flight non-normal situation.
Troubleshooting is rarely helpful and has caused further loss of system function or failure and in some cases,
accidents and incidents.
The crew should consider additional actions beyond the checklist only when completion of the published
checklist steps clearly result in an unacceptable situation.
In the case of airplane controllability problems, when a safe landing is considered unlikely, airplane-handling
evaluations with gear and / or flaps extended may be appropriate.
Also, attempting to free jammed flight controls should only be attempted, if the airplane cannot be safely
landed with the existing condition and then, according to the AEC to the extent possible.
Crew distraction, caused by preoccupation with troubleshooting, has been a key factor in fuel starvation and
CFIT accidents.
Completion of the AEC, as published, is strongly recommended.
3.4.3.4
Abnormal Contaminated Runway Operations
There have been incidents involving Dash 8 aircraft operating from a contaminated runway, where the nose
landing gear became frozen in the retracted position.
Attempts to lower the nose landing gear using the normal and the alternate systems were unsuccessful.
The aircraft sustained minor damage when landed with the nose landing gear retracted.
The operating guidance provided in the AFM Supplement 37
(SUPPLEMENTARY PERFORMANCE INFORMATION FOR OPERATION ON CONTAMINATED RUNWAYS)
limits the maximum Water Equivalent Depth (WED) to 15 mm (0.59 in) and the maximum contaminant depth to
6 cm (2.4 in).
AFM Figure 6-37-1 provides a mean to convert the Contaminant Depth to WED for take-off.
The maximum allowable depth of slush is approximately 15 mm (0.59 in).
AOM DASH 8-Q400
3.4-20
[Rev. 13] 30 JAN 2015
3.4.3.5
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Landing Gear Failures
Structural failure of the landing gear is not covered under Type Certification, therefore, no specific AFM procedure covering this malfunction is provided or required.
When it is known that a landing must be performed which could be identified as an emergency landing due to
the presence of factors which introduce a hazard to the airplane and its occupants, AFM Paragraph 3.16,
Emergency Landing, outlines the main points to be addressed as applicable.
The intent of the following is to provide a list of options that may assist the flight crew in their decision making
process.
The information presented will not always be appropriate for the conditions being experienced by the flight
crew.
Ultimately, the flight crew will have to make the final decisions given the information presented to them in the
particular emergency situation.
Normal Extension / Retraction
If the landing gear fails to extend or retract, assuming that the Normal Extension / Retraction procedures have
been actioned correctly, the following list contains known conditions that have presented the flight crew with an
abnormal landing gear configuration:
-
A burnt out landing gear advisory light bulb can give a false indication that the gear is not down.
If “3 green” gear down and locked advisory lights are not observed, ensure that the light bulbs in the gear
indicator panel have been checked utilizing the Advisory / Test switch.
-
Failing to use the Alternate Indication system for a landing gear down and locked confirmation.
-
The Alternate Release and Extension doors not in the fully closed position prior to a normal landing gear
selection.
-
The Landing Gear Inhibit switch is not in the Normal position.
Once it is determined that the normal system has failed to extend / retract the landing gear and the aircraft was
appropriately configured giving due regard to the above mentioned possible errors, the AFM directs the use of
the Alternate Extension system.
Alternate Extension
Unless covered by a specific procedure in the AFM, following a landing gear retraction or extension malfunction, the landing gear must be extended using the Alternate Landing Gear Extension procedure (see NOTE in
AFM Paragraph 4.21.1).
Cycling the landing gear as an intermediate step to achieve an all gear down and locked indication is not
approved or recommended.
As the root cause of the landing gear anomaly is unlikely to be known, cycling the landing gear may create a
more difficult landing gear configuration for the flight crew to manage.
The Alternate Extension procedure was created to provide a backup means of extending the landing gear
based on a standard set of common mode failures required for certification.
Multiple system failures, compounding failures, structural failures and / or the introduction of foreign objects are
not part of, nor required for showing certification compliance.
When using the Alternate Extension procedure, flight crews must ensure:
-
The Alternate Extension and Release doors are fully open and remain fully open.
-
The main and nose landing gear release handles are pulled with sufficient force (may exceed 41 kg / 90 lb)
to release the doors and uplocks (pull forces in the air will likely be greater than those experienced on the
ground or in a simulator).
Continue pulling with whatever force is necessary to achieve release of all landing gear uplocks.
NOTE:
A tower “flyby” technique may be useful for confirmation of landing gear position, but is not
suitable for confirmation of landing gear down and locked condition.
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-21
[Rev. 13] 30 JAN 2015
BEYOND THE NORMAL AND ALTERNATE:
There have been events where unique landing gear failures prevented the extension of the landing gear using
the normal and alternate extension systems.
These circumstances are beyond certification standards and existing AFM procedures are unlikely to provide
adequate direction for rectification of the abnormal landing gear condition.
The following flight crew procedures are offered for consideration.
NOTE:
The final decision with respect to the use of procedures outside those given in the AFM remain
with the Pilot In Command (PIC).
FLIGHT CREW PROCEDURAL CONSIDERATIONS:
When it is known that a landing must be performed which could be identified as an emergency landing due to
the presence of factors which introduce a hazard to the airplane and its occupants, AFM Paragraph 3.16 outlines the main points to be addressed as applicable.
With different potential landing gear failure scenarios, the following considerations may also be applicable:
Nose Gear - UP
Main Gear - DOWN and LOCKED
If the Alternate Gear Extension procedure has been completed and it cannot be verified that the nose landing
gear is down and locked by the normal and alternate systems, the flight crew must make a decision to perform
a landing with the nose landing gear not locked or reset the Alternate Extension system and cycle the landing
gear in an attempt to achieve all gears down and locked.
It is possible to safely land the Dash 8 Q400 airplane with the nose landing gear retracted.
The geometry of the airplane is such that the propellers will not come in contact with the ground with the main
landing gear extended and the nose landing gear retracted.
In addition to the direction given in the AFM Paragraph 3.16, Emergency Landing, the following items are
offered for consideration:
•
Reduce landing weight through fuel burn
•
Attempt to achieve an aft CG by re-seating passengers
•
Select a runway with minimal crosswind
•
Land with Flap 35º
•
Fly the appropriate VREF for the landing weight
•
Touchdown offset from the runway centreline if the runway is equipped with a centreline lighting system
•
On touchdown, hold the nose up off the runway as long as possible.
Prior to losing elevator effectivity, gently lower the nose onto the runway
•
If the nose landing gear is not extended or it collapses, maintain directional control with rudder until it is no
longer effective, at which point asymmetric braking may be used as required
•
If the nosewheel is on the ground and the nose landing gear appears to be locked, apply brakes and / or
reverse thrust.
If the nose landing gear is not extended or it collapses, apply brakes only.
AOM DASH 8-Q400
3.4-22
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
Opting to cycle the landing gear in an effort to extend the nose gear from this abnormal situation would require
a reset of Alternate Extension procedure.
This may be accomplished by utilizing the following procedure:
1.
Ensure # 2 hydraulic system pressure and quantity are normal and the following landing gear advisory
lights are illuminated:
- selector lever amber,
- gear green locked down (main gear only),
- red gear unlocked (nose gear) and
- all amber doors open.
2.
NOSE L/G RELEASE Handle – Return to stowed position.
3.
LANDING GEAR ALTERNATE EXTENSION Door – Close fully.
4.
MAIN L/G RELEASE Handle – Return to the stowed position.
5.
LANDING GEAR ALTERNATE RELEASE Door – Close fully.
6.
LANDING GEAR Lever – DN.
7.
L/G DOWN SELECT INHIBIT SW – Normal and Guarded.
Check amber doors open advisory lights out (main gear only) and LDG GEAR INOP caution light out.
NOTE:
8.
It may take up to 17 s for the doors to close.
LANDING GEAR Lever – UP.
Check all gears, doors and LANDING GEAR lever advisory lights out.
If the Flight Crew decides to cycle the landing gear in an effort to achieve all gears down:
9.
LANDING GEAR Lever – DN.
Check:
- 3 green gear locked down advisory lights illuminate,
- all amber doors open,
- red gear unlocked and
- selector lever amber advisory lights out.
10. Items 8 and 9 may be repeated in an effort to achieve 3 gear down and locked.
CAUTION:
Should the LDG GEAR INOP caution light illuminate, or
loss of # 2 hydraulic system pressure or quantity, or
any abnormality in landing gear system indication other than those associated with
the nose landing gear be experienced,
see AFM Paragraph 4.21.1 (ALTERNATE LANDING GEAR EXTENSION).
AOM DASH 8-Q400
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
3.4-23
[Rev. 13] 30 JAN 2015
All Gear - UP
It is possible to safely land the Dash 8 Q400 airplane with all landing gears retracted.
The geometry of the airplane is such that the propellers should not come in contact with the ground with all
landing gears retracted, if it is possible to maintain the wings level throughout the landing.
In addition to the direction given in the AFM Paragraph 3.16, Emergency Landing and Paragraph 3.15.1, Item
6, Note 1, the following items are offered for consideration:
•
Reduce landing weight through fuel burn
•
Passengers must be moved from the seats in the plane of the propellers and re-seated elsewhere in the
cabin
•
Select a runway with minimal crosswind
•
Land with Flap 35º
•
Fly the appropriate VREF for the landing weight
•
Touchdown offset from the runway centreline if the runway is equipped with a centreline lighting system
•
Maintain a nose-up pitch attitude not exceeding 5º prior to runway contact
•
On touchdown, maintain wings level using lateral control and directional control with rudder
•
Unless there is propeller / ground contact during the landing, requiring an immediate engine shutdown,
feather and secure engines once the aircraft has come to a stop.
One Main Gear - UP
Nose Gear and Opposite Main Gear - DOWN and LOCKED
If the Alternate Gear Extension procedure has been completed and it cannot be verified that both main landing
gears are down and locked by the normal and alternate systems, the flight crew may consider resetting the
alternate extension system and attempt to cycle the landing gear in order to achieve all gears down and locked
or to perform a landing with one main gear unsafe.
Opting to cycle the landing gear in an effort to extend the main gear from this abnormal situation would require
a reset of Alternate Extension procedure.
This may be accomplished by utilizing the following procedure:
1.
Visually confirm that the affected gear has not extended and that the associated doors have opened.
2.
Ensure # 2 hydraulic system pressure and quantity are normal and the following landing gear advisory
lights are illuminated:
- selector lever amber,
- gear green locked down (nose and unaffected main gear),
- red gear unlocked (affected main gear) and
- all amber doors open.
3.
NOSE L/G RELEASE handle – Return to stowed position.
4.
LANDING GEAR ALTERNATE EXTENSION door – Close fully.
5.
MAIN L/G RELEASE handle – Return to the stowed position.
6.
LANDING GEAR ALTERNATE RELEASE door – Close fully.
AOM DASH 8-Q400
3.4-24
[Rev. 13] 30 JAN 2015
CHAPTER 3
NON-NORMAL, SPECIAL AND SUPPLEMENTAL
PROCEDURES
7.
LANDING GEAR lever – DN.
8.
L/G DOWN SELECT INHIBIT SW – Normal and guarded.
Check amber doors open advisory lights out (nose and unaffected main gear) and LDG GEAR INOP caution light out.
9.
LANDING GEAR lever – UP.
Check all gears, doors and LANDING GEAR lever advisory lights out.
If the Flight Crew opt to land in this gear up configuration, see “All Gears - UP” paragraph above.
If the Flight Crew decides to cycle the landing gear in an effort to achieve all gears down:
10. LANDING GEAR lever – DN.
Check:
- 3 green gear locked down advisory lights illuminate,
- all amber doors open,
- red gear unlocked and
- selector lever amber advisory lights out.
11. Items 9 and 10 may be repeated in an effort to achieve 3 gear down and locked.
CAUTION:
Should the LDG GEAR INOP caution light illuminate, or
loss of # 2 hydraulic system pressure or quantity, or
any abnormality in landing gear system indication other than those associated with
the affected main landing gear be experienced,
see AFM Paragraph 4.21.1 (ALTERNATE LANDING GEAR EXTENSION).
The flight crew must assume and prepare for the affected main landing gear to collapse on landing.
In addition to the direction given in the AFM Paragraph 3.16, Emergency Landing, the following items are
offered for consideration:
•
Reduce landing weight through fuel burn
•
Passengers must be moved from the seats in the plane of the propellers and re-seated elsewhere in the
cabin.
Priority is to be given to the passengers seated on the side with the indicated unsafe main landing gear
•
Crosswind (if any) would be advantageous from the side with the unaffected main landing gear
•
Land with Flap 35º
•
Fly the appropriate VREF for the landing weight
•
Giving consideration to the specific approach to be flown: flight conditions and possible missed approach,
prior to commencing the final approach, feather and secure the engine on the side with the indicated
unsafe main landing gear.
•
On touchdown, maintain maximum wing down lateral control on the side with the unaffected main landing
gear
•
If the unsafe main landing gear collapses, in an effort to reduce the airplane turning moment in the direction of the failed main landing gear, apply maximum braking and reverse thrust on the side with the unaffected main landing gear.
•
Feather and secure the operative engine
•
Be prepared to action an engine fire.
AOM DASH 8-Q400
CHAPTER 4
LIST OF EFFECTIVE PAGES
04 - Effective Pages
04 LEP - Page 1
(Rev 18) 21 NOV 2016
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ToC 4-1
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(METRIC)
04 LEP - Page 2
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(METRIC)
AOM DASH 8-Q400
CHAPTER 4
LIST OF EFFECTIVE PAGES
04 LEP - Page 3
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(METRIC)
04 LEP - Page 4
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(METRIC)
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
ToC 4-1
[Rev. 4] 13 APR 2012
- TABLE OF CONTENTS 4.0
GENERAL .............................................................................................................................. 4.0-1
4.1
TAKE-OFF and CLIMB PERFORMANCE DATA .................................................................. 4.1-1
4.1.1
Mass, Altitude and Temperature Limits (MAT) ........................................................................ 4.1-1
4.1.2
Allowed Mass for Take-off on Dry Runway ............................................................................. 4.1-5
4.1.3
Allowed Mass for Take-off on Wet Runway ........................................................................ 4.1-151
4.1.4
Allowed Mass for Take-off on Contaminated Runway ........................................................ 4.1-152
4.1.5
Net Flight Path Data ........................................................................................................... 4.1-177
4.1.6
Bank Angles during Climb / Gradient Losses ..................................................................... 4.1-200
4.1.7
Radius of Turn for a 15° Banked Turn ................................................................................ 4.1-200
4.2
EN-ROUTE PERFORMANCE ................................................................................................ 4.2-1
4.2.1
General ................................................................................................................................... 4.2-1
4.2.2
Single Engine Service Ceiling ................................................................................................ 4.2-1
4.2.3
Driftdown Procedures ............................................................................................................. 4.2-2
4.2.4
Examples of Driftdown Profiles ............................................................................................... 4.2-9
4.3
APPROACH and LANDING CLIMB LIMITS ......................................................................... 4.3-1
4.3.1
General ................................................................................................................................... 4.3-1
4.3.2
Mass Limits for CAT I / Non Precision Approaches ................................................................ 4.3-1
4.3.3
Mass Limits for CAT II Operation ............................................................................................ 4.3-5
4.3.4
Missed Approach Climb Gradients (Gross Gradients) Available ............................................ 4.3-8
4.4
LANDING ............................................................................................................................... 4.4-1
4.4.1
General ................................................................................................................................... 4.4-1
4.4.2
Dispatch Requirements .......................................................................................................... 4.4-1
4.4.3
Requirements for Actual Landing .......................................................................................... 4.4-11
4.4.4
Unfactored Landing Distance in Abnormal Configurations ................................................... 4.4-22
4.5
SPEEDS ................................................................................................................................. 4.5-1
4.5.1
General ................................................................................................................................... 4.5-1
4.5.2
Take-off Speeds ...................................................................................................................... 4.5-1
4.5.3
Flap Retraction Initiation Speed (VFR) and Final Take-Off Speed (VFTO) ............................. 4.5-21
4.5.4
Approach Speeds ................................................................................................................. 4.5-22
4.5.5
Landing Speeds (VREF) - KIAS - ........................................................................................... 4.5-23
4.5.6
Stalling Speeds - KCAS - ...................................................................................................... 4.5-23
4.5.7
1,23 VSR - Speeds - KIAS - ................................................................................................... 4.5-24
4.5.8
Speed Booklet ...................................................................................................................... 4.5-24
4.5.9
Position Error Correction To Altimeter (Integrated Standby Instrument) ............................... 4.5-25
4.6
BRAKE ENERGY LIMITS ...................................................................................................... 4.6-1
4.6.1
Brake Energy in Accelerate-Stop ............................................................................................ 4.6-1
4.6.2
Brake Energy in Landing ...................................................................................................... 4.6-10
4.6.3
Minimum Turn-Around Time ................................................................................................. 4.6-20
(cont’d on next page)
AOM DASH 8-Q400
METRIC
CHAPTER 4
ToC 4-2
[Rev. 15] 30 OCT 2015
PERFORMANCE
- TABLE OF CONTENTS - (cont’d)
4.7
EFFECT OF DE-ICING and ANTI-ICING FLUIDS ................................................................. 4.7-1
4.7.1
General ................................................................................................................................... 4.7-1
4.7.2
Approved SAE Low Speed Type III Fluids .............................................................................. 4.7-1
4.7.3
Approved SAE Type I, SAE Type II and SAE Type IV Fluids .................................................. 4.7-1
4.7.4
Approved SAE Type I Fluids ................................................................................................... 4.7-2
4.7.5
Icing Precautions and Procedures .......................................................................................... 4.7-2
4.8
OPERATION WITH LANDING GEAR EXTENDED ............................................................... 4.8-1
4.8.1
General ................................................................................................................................... 4.8-1
4.8.2
Performance Data ................................................................................................................... 4.8-1
4.9
ALL ENGINE CLIMB GRADIENTS ........................................................................................ 4.9-1
4.9.1
General ................................................................................................................................... 4.9-1
4.10
TORQUE SETTING DATA .................................................................................................... 4.10-1
4.10.1
Torque Setting Tables ............................................................................................................ 4.10-1
4.11
FLIGHTS CONDUCTED UNDER THE PROVISION OF THE CDL ..................................... 4.11-1
4.11.1
General ................................................................................................................................. 4.11-1
4.11.2
CDL Items Influencing the AC Performance ......................................................................... 4.11-1
4.12
SUPPLEMENTAL PERFORMANCE DATA ......................................................................... 4.12-1
4.12.1
General ................................................................................................................................. 4.12-1
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1
4.1-1
[Rev. X] 31 MAY 2011
TAKE-OFF AND CLIMB PERFORMANCE DATA
The presentation of performance data in the AOM is made in a tabular form - compared to the graphical presentation in the Airplane Flight Manual.
The company will provide take-off mass limit tables for performance-critical airports / runways. Therefore not all
details of the AFM are presented in the AOM. The tables presented in the AOM should allow a quick determination of the allowed mass for the take-off and the accelerate - stop distance available in case no detailed takeoff mass limit is available for the runway concerned.
For reasons of simplification a V1 = VR is assumed!
Using V1 = VR there may be situations where the allowed mass for take-off is limited by the TODA or the
ASDA. Therefore the lower mass shall be depicted from either the table for:
•
Maximum mass for take-off - versus ASDA -
or
•
Maximum mass for take-off - versus TODA -
Under Sub-Chapter 4.1.5 the available Reference Gradients Available are given, followed by a table showing
the required reference gradient for a given obstacle height and obstacle distance (from end of TODA).
4.1.1
Mass, Altitude and Temperature Limits (MAT))
The mass limits as presented in the following tables do assure a minimum gross gradient of climb of 2.4% for
the relevant pressure altitude/OAT combination.
AOM DASH 8-Q400
METRIC
CHAPTER 4
4.1-2
PERFORMANCE
[Rev. X] 31 MAY 2011
Table 1 - MAT Limits (kg)
OAT
(°C)
50
48
46
44
42
40
38
36
34
32
30
28
26
24
22
20
18
16
14
12
10
8
6
4
2
0
-2
-4
-6
-8
-10
-12
-14
-16
-18
-20
-22
-24
-26
NOTE:
10000
24458
24918
25377
25818
26247
26676
27105
27536
27918
28283
28650
29016
( 29381 )
( 29733 )
( 30076 )
( 30413 )
( 30745 )
( 31087 )
( 31362 )
( 31593 )
( 31824 )
( 31993 )
( 32098 )
( 32203 )
( 32307 )
( 32412 )
( 32517 )
( 32622 )
-
9000
25060
25537
26014
26473
26918
27363
27808
28256
28660
29048
( 29439 )
( 29829 )
( 30218 )
( 30570 )
( 30897 )
( 31217 )
( 31533 )
( 31859 )
( 32039 )
( 32136 )
( 32242 )
( 32348 )
( 32453 )
( 32559 )
( 32664 )
( 32770 )
( 32875 )
( 32981 )
-
5° FLAPS
8000
25663
26160
26656
27133
27595
28058
28520
28985
( 29409 )
( 29822 )
( 30237 )
( 30653 )
( 31066 )
( 31392 )
( 31654 )
( 31913 )
( 32167 )
( 32311 )
( 32411 )
( 32512 )
( 32613 )
( 32714 )
( 32814 )
( 32918 )
( 33024 )
( 33130 )
( 33236 )
( 33342 )
-
7000
26247
26769
27291
27791
28274
28757
29240
( 29726 )
( 30176 )
( 30615 )
( 31057 )
( 31499 )
( 31939 )
( 32210 )
( 32352 )
( 32472 )
( 32570 )
( 32671 )
( 32772 )
( 32872 )
( 32973 )
( 33073 )
( 33174 )
( 33278 )
( 33384 )
( 33490 )
( 33596 )
( 33702 )
-
6000
26868
27405
27942
28462
28967
( 29472 )
( 29977 )
( 30485 )
( 30912 )
( 31290 )
( 31672 )
( 32053 )
( 32433 )
( 32655 )
( 32752 )
( 32847 )
( 32940 )
( 33036 )
( 33135 )
( 33235 )
( 33336 )
( 33437 )
( 33537 )
( 33640 )
( 33746 )
( 33852 )
( 33958 )
( 34065 )
-
Altitude (ft)
5000
27502
28058
28614
29157
( 29689 )
( 30221 )
( 30752 )
( 31288 )
( 31712 )
( 32060 )
( 32412 )
( 32763 )
( 32923 )
( 33020 )
( 33116 )
( 33211 )
( 33305 )
( 33401 )
( 33500 )
( 33600 )
( 33701 )
( 33801 )
( 33902 )
( 34005 )
( 34111 )
( 34217 )
( 34323 )
( 34429 )
-
4000
28153
28725
( 29297 )
( 29860 )
( 30416 )
( 30971 )
( 31526 )
( 32085 )
( 32506 )
( 32826 )
( 33095 )
( 33192 )
( 33288 )
( 33384 )
( 33481 )
( 33577 )
( 33670 )
( 33767 )
( 33865 )
( 33966 )
( 34067 )
( 34168 )
( 34269 )
( 34372 )
( 34478 )
( 34584 )
( 34690 )
( 34796 )
-
3000
28824
( 29412 )
( 29999 )
( 30580 )
( 31153 )
( 31726 )
( 32299 )
( 32875 )
( 33242 )
( 33364 )
( 33460 )
( 33557 )
( 33653 )
( 33750 )
( 33846 )
( 33942 )
( 34036 )
( 34132 )
( 34232 )
( 34333 )
( 34436 )
( 34538 )
( 34640 )
( 34744 )
( 34849 )
( 34954 )
( 35059 )
( 35164 )
-
2000
( 29505 )
( 30114 )
( 30722 )
( 31284 )
( 31802 )
( 32320 )
( 32839 )
( 33360 )
( 33653 )
( 33745 )
( 33837 )
( 33930 )
( 34022 )
( 34118 )
( 34216 )
( 34312 )
( 34407 )
( 34504 )
( 34603 )
( 34704 )
( 34805 )
( 34906 )
( 35007 )
( 35111 )
( 35218 )
( 35325 )
( 35432 )
( 35539 )
-
1000
( 30194 )
( 30839 )
( 31483 )
( 32030 )
( 32483 )
( 32935 )
( 33388 )
( 33843 )
( 34023 )
( 34115 )
( 34209 )
( 34303 )
( 34396 )
( 34491 )
( 34587 )
( 34683 )
( 34776 )
( 34872 )
( 34971 )
( 35072 )
( 35173 )
( 35275 )
( 35376 )
( 35480 )
( 35588 )
( 35696 )
( 35803 )
( 35911 )
-
0
( 30869 )
( 31539 )
( 32209 )
( 32749 )
( 33159 )
( 33570 )
( 33980 )
( 34311 )
( 34401 )
( 34493 )
( 34585 )
( 34677 )
( 34769 )
( 34864 )
( 34962 )
( 35058 )
( 35153 )
( 35251 )
( 35351 )
( 35452 )
( 35554 )
( 35656 )
( 35757 )
( 35861 )
( 35968 )
( 36074 )
( 36180 )
( 36287 )
-
Masses given in brackets are in excess of the maximum permitted structural mass and are for
interpolation purposes only.
Correction for Ice Protection Systems “ON”:
Subtract 1540 kg from the above masses when above 7500 ft ASL.
METRIC
AOM DASH 8-Q400
CHAPTER 4
4.1-3
PERFORMANCE
[Rev. X] 31 MAY 2011
Table 2 - MAT Limits (kg) 10° FLAPS
OAT
(°C)
50
48
46
44
42
40
38
36
34
32
30
28
26
24
22
20
18
16
14
12
10
8
6
4
2
0
-2
-4
-6
-8
-10
-12
-14
-16
-18
-20
-22
-24
-26
NOTE:
10000
23284
23716
24149
24566
24973
25379
25785
26194
26553
26892
27233
27574
27913
28238
28554
28864
29169
( 29484 )
( 29770 )
( 30039 )
( 30308 )
( 30496 )
( 30600 )
( 30704 )
( 30809 )
( 30913 )
( 31018 )
( 31122 )
-
9000
23861
24316
24770
25206
25628
26050
26472
26897
27273
27631
27991
28351
28709
29051
( 29382 )
( 29707 )
( 30027 )
( 30357 )
( 30550 )
( 30651 )
( 30754 )
( 30858 )
( 30961 )
( 31064 )
( 31167 )
( 31270 )
( 31373 )
( 31476 )
-
8000
24447
24919
25391
25841
26276
26711
27146
27584
27980
28362
28746
29130
( 29513 )
( 29838 )
( 30121 )
( 30400 )
( 30675 )
( 30823 )
( 30921 )
( 31020 )
( 31118 )
( 31217 )
( 31316 )
( 31417 )
( 31521 )
( 31625 )
( 31728 )
( 31832 )
-
7000
25023
25510
25997
26465
26920
27374
27829
28286
28703
29108
( 29516 )
( 29923 )
( 30329 )
( 30623 )
( 30832 )
( 30982 )
( 31079 )
( 31178 )
( 31276 )
( 31375 )
( 31474 )
( 31572 )
( 31671 )
( 31772 )
( 31875 )
( 31979 )
( 32082 )
( 32185 )
-
6000
25610
26113
26616
27103
27577
28052
28526
29004
( 29417 )
( 29797 )
( 30179 )
( 30562 )
( 30942 )
( 31164 )
( 31258 )
( 31352 )
( 31444 )
( 31538 )
( 31634 )
( 31732 )
( 31830 )
( 31928 )
( 32026 )
( 32129 )
( 32238 )
( 32346 )
( 32454 )
( 32563 )
-
ALTITUDE (FT)
5000
4000
26833
26213
27375
26740
27918
27267
28445
27775
28960
28266
( 29474 )
28758
( 29988 )
29249
( 30506 )
( 29744 ) ( 30933 )
( 30160 ) ( 31299 )
( 30527 ) ( 31602 )
( 30897 ) ( 31696 )
( 31267 ) ( 31789 )
( 31430 ) ( 31883 )
( 31524 ) ( 31976 )
( 31618 ) ( 32069 )
( 31711 ) ( 32160 )
( 31802 ) ( 32253 )
( 31896 ) ( 32351 )
( 31992 ) ( 32453 )
( 32089 ) ( 32555 )
( 32187 ) ( 32657 )
( 32285 ) ( 32759 )
( 32383 ) ( 32861 )
( 32485 ) ( 32962 )
( 32592 ) ( 33063 )
( 32699 ) ( 33165 )
( 32805 ) ( 33266 )
( 32912 )
-
3000
27489
28038
28588
29130
( 29665 )
( 30201 )
( 30736 )
( 31275 )
( 31691 )
( 31848 )
( 31946 )
( 32045 )
( 32143 )
( 32241 )
( 32340 )
( 32438 )
( 32534 )
( 32632 )
( 32729 )
( 32825 )
( 32922 )
( 33018 )
( 33115 )
( 33214 )
( 33316 )
( 33418 )
( 33520 )
( 33622 )
-
2000
28136
28704
( 29273 )
( 29812 )
( 30323 )
( 30833 )
( 31344 )
( 31857 )
( 32148 )
( 32243 )
( 32338 )
( 32434 )
( 32529 )
( 32622 )
( 32714 )
( 32805 )
( 32895 )
( 32987 )
( 33081 )
( 33179 )
( 33276 )
( 33374 )
( 33471 )
( 33571 )
( 33675 )
( 33778 )
( 33881 )
( 33985 )
-
1000
28790
( 29384 )
( 29978 )
( 30501 )
( 30957 )
( 31413 )
( 31869 )
( 32327 )
( 32509 )
( 32604 )
( 32700 )
( 32795 )
( 32890 )
( 32984 )
( 33076 )
( 33168 )
( 33257 )
( 33349 )
( 33444 )
( 33542 )
( 33640 )
( 33737 )
( 33835 )
( 33935 )
( 34037 )
( 34139 )
( 34241 )
( 34344 )
-
0
( 29438 )
( 30061 )
( 30683 )
( 31206 )
( 31628 )
( 32050 )
( 32472 )
( 32810 )
( 32897 )
( 32985 )
( 33074 )
( 33163 )
( 33252 )
( 33342 )
( 33435 )
( 33527 )
( 33617 )
( 33709 )
( 33804 )
( 33901 )
( 33999 )
( 34096 )
( 34193 )
( 34293 )
( 34395 )
( 34497 )
( 34600 )
( 34702 )
-
Masses given in brackets are in excess of the maximum permitted structural mass and are for interpolation purposes only!
Correction for Ice Protection Systems “ON”:
Subtract 225 kg from the above masses when above 7500 ft ASL (for a continued 2nd segment above 400 ft
AGL the penalty increases to 590 kg).
AOM DASH 8-Q400
METRIC
CHAPTER 4
4.1-4
PERFORMANCE
[Rev. X] 31 MAY 2011
Table 3 - MAT Limits (kg)
OAT
(°C)
50
48
46
44
42
40
38
36
34
32
30
28
26
24
22
20
18
16
14
12
10
8
6
4
2
0
-2
-4
-6
-8
-10
-12
-14
-16
-18
-20
-22
-24
-26
NOTE:
10000
22043
22445
22847
23235
23612
23990
24367
24747
25076
25384
25694
26004
26312
26607
26893
27174
27451
27736
28015
28292
28570
28765
28875
28985
29095
29205
( 29315 )
( 29425 )
-
9000
22586
23006
23426
23829
24221
24613
25005
25399
25747
26076
26407
26739
27068
27379
27679
27973
28263
28561
28804
28938
29047
29156
( 29265 )
( 29373 )
( 29482 )
( 29590 )
( 29699 )
( 29808 )
-
15° FLAPS
8000
23122
23570
24019
24442
24845
25249
25653
26059
26426
26779
27134
27489
27843
28154
28434
28709
28980
29131
29235
( 29338 )
( 29443 )
( 29546 )
( 29650 )
( 29754 )
( 29859 )
( 29963 )
( 30068 )
( 30173 )
-
7000
23676
24136
24596
25035
25458
25880
26303
26728
27116
27491
27868
28246
28622
28922
29166
( 29334 )
( 29430 )
( 29529 )
( 29627 )
( 29726 )
( 29824 )
( 29923 )
( 30021 )
( 30120 )
( 30219 )
( 30319 )
( 30418 )
( 30517 )
-
6000
24237
24711
25185
25643
26088
26533
26978
27426
27821
28190
28561
28933
( 29303 )
( 29519 )
( 29614 )
( 29707 )
( 29798 )
( 29892 )
( 29986 )
( 30080 )
( 30174 )
( 30268 )
( 30362 )
( 30460 )
( 30560 )
( 30660 )
( 30760 )
( 30860 )
-
Altitude (ft)
5000
24810
25299
25788
26263
26727
27192
27656
28124
28526
28892
( 29260 )
( 29628 )
( 29788 )
( 29879 )
( 29970 )
( 30059 )
( 30148 )
( 30238 )
( 30330 )
( 30425 )
( 30519 )
( 30614 )
( 30708 )
( 30804 )
( 30903 )
( 31001 )
( 31100 )
( 31198 )
-
4000
25398
25902
26406
26900
27385
27870
28355
28843
( 29264 )
( 29642 )
( 29955 )
( 30045 )
( 30135 )
( 30226 )
( 30317 )
( 30406 )
( 30494 )
( 30585 )
( 30677 )
( 30771 )
( 30866 )
( 30960 )
( 31054 )
( 31150 )
( 31248 )
( 31345 )
( 31443 )
( 31540 )
-
3000
26002
26529
27056
27570
28072
28574
29075
( 29580 )
( 30032 )
( 30210 )
( 30300 )
( 30391 )
( 30481 )
( 30571 )
( 30662 )
( 30751 )
( 30839 )
( 30929 )
( 31022 )
( 31116 )
( 31211 )
( 31306 )
( 31401 )
( 31497 )
( 31594 )
( 31691 )
( 31789 )
( 31886 )
-
2000
26621
27163
27705
28223
28717
29211
( 29705 )
( 30202 )
( 30480 )
( 30567 )
( 30654 )
( 30741 )
( 30828 )
( 30916 )
( 31007 )
( 31096 )
( 31184 )
( 31275 )
( 31367 )
( 31460 )
( 31553 )
( 31647 )
( 31740 )
( 31837 )
( 31936 )
( 32035 )
( 32134 )
( 32234 )
-
1000
27267
27822
28376
28875
( 29319 )
( 29763 )
( 30208 )
( 30654 )
( 30828 )
( 30914 )
( 31002 )
( 31090 )
( 31177 )
( 31266 )
( 31356 )
( 31445 )
( 31533 )
( 31623 )
( 31715 )
( 31808 )
( 31902 )
( 31996 )
( 32089 )
( 32187 )
( 32291 )
( 32394 )
( 32497 )
( 32600 )
-
0
27883
28465
29048
( 29543 )
( 29951 )
( 30359 )
( 30767 )
( 31094 )
( 31180 )
( 31266 )
( 31353 )
( 31441 )
( 31528 )
( 31616 )
( 31707 )
( 31797 )
( 31884 )
( 31975 )
( 32067 )
( 32161 )
( 32255 )
( 32349 )
( 32443 )
( 32541 )
( 32643 )
( 32745 )
( 32847 )
( 32949 )
-
Masses given in brackets are in excess of the maximum permitted structural mass and are for
interpolation purposes only!
Correction for Ice Protection Systems “ON”:
Subtract 160 kg from the above masses when above 5500 ft ASL (for a continued 2nd segment above 400 ft
AGL the penalty increases to 790 kg).
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1.2
4.1-5
[Rev. X] 31 MAY 2011
Allowed Mass for Take-Off / Dry Runway
The tables under this Sub-Chapter do allow the determination of the maximum mass for take-off for a given
ASDA and TODA.
To simplify the evaluation a V1 / VR - ratio of 1 has been used.
Using a V1 = VR means that in some instances it will not be the TODA, but the ASDA which limits the maximum
mass for take-off.
In case of very long stopways or clearways (approximately 150 m) a take-off may even be limited by the takeoff run.
In those very rare instances the TOR graphs have to be crosschecked in the AFM, as TOR data is not included
in the AOM.
In case there are no clearways and stopways available (TORA = TODA = ASDA) the limiting masses still need
to be crosschecked for the ASDA and the TODA maximum mass limit.
The lowest mass as obtained from the ASDA or TODA maximum mass limit has to be used as the take-off limit.
No correction will be required for Ice Protection Systems “ON”.
The corresponding take-off speeds will be found under Sub-Chapter 4.5.
Remember:
For this kind of presentation V1 is equal to VR.
The maximum mass limits for ASDA and TODA are based on a level (no slope) runway and zero wind condition.
Therefore the ASDA and the TODA must first be corrected for the wind and slope (Sub-Chapter 4.1.2.1).
Only then the tables for the ASDA and TODA mass limits must be used by entering the table with the wind /
slope corrected ASDA and TORA.
Sub-Chapter 4.1.2.2 gives the maximum allowed mass for the (corrected) ASDA and the (corrected) TODA.
4.1.2.1
Corrections of TODA / ASDA for Wind and Slope
Enter the table with the declared ASDA and find the corrected ASDA for wind and slope.
Likewise the declared TODA shall be corrected for wind and slope.
NOTE:
The declared ASDA / TODA shall - where applicable - be corrected by the line-up allowances
(Sub-Chapter 1.10.2).
The following tables show the ASDA and TODA corrected for wind and slope:
Table 1 - shows corrected ASDA for 5° Flaps.
Table 1A - shows corrected TODA for 5° Flaps.
Table 2 - shows corrected ASDA for 10° Flaps.
Table 2A - shows corrected TODA for 10° Flaps.
Table 3 - shows corrected ASDA for 15° Flaps.
Table 3A - shows corrected TODA for 15° Flaps.
AOM DASH 8-Q400
METRIC
METRIC
820
842
864
886
908
930
952
974
997
1019
1041
1063
1086
1108
1130
1153
1175
1198
1220
1243
1266
1288
1311
1333
1356
1379
1402
1425
1447
1470
1493
1516
1539
1562
1585
1608
1631
1655
821
843
865
888
910
932
955
977
1000
1023
1045
1068
1091
1114
1137
1160
1183
1206
1229
1252
1275
1298
1321
1345
1368
1392
1415
1439
1462
1486
1509
1533
1557
1581
1604
1628
1652
1676
819
840
862
884
905
927
949
970
992
1014
1036
1058
1079
1101
1123
1145
1167
1189
1211
1233
1255
1277
1299
1321
1343
1365
1387
1409
1431
1453
1475
1498
1520
1542
1565
1587
1609
1631
0%
808
829
850
871
892
913
934
955
976
997
1018
1040
1061
1082
1103
1124
1145
1166
1187
1208
1230
1251
1272
1293
1314
1335
1356
1378
1399
1420
1441
1462
1484
1505
1526
1547
1569
1590
1%
797
818
838
858
879
899
920
940
960
981
1001
1021
1042
1062
1082
1103
1123
1143
1163
1184
1204
1225
1245
1265
1285
1306
1326
1346
1366
1387
1407
1427
1447
1468
1488
1508
1529
1549
905
929
953
977
1001
1025
1049
1073
1097
1122
1146
1170
1195
1219
1244
1268
1293
1317
1342
1367
1391
1416
1441
1466
1490
1515
1540
1565
1590
1616
1641
1666
1691
1716
1741
1767
1792
1817
-2%
904
928
952
975
999
1023
1046
1070
1094
1118
1141
1165
1189
1213
1237
1261
1285
1309
1333
1357
1381
1405
1430
1454
1478
1502
1526
1551
1575
1599
1624
1648
1672
1697
1721
1746
1770
1795
-1%
903
926
949
973
996
1019
1042
1066
1089
1112
1136
1159
1182
1206
1229
1252
1276
1299
1323
1346
1370
1393
1417
1440
1463
1487
1511
1534
1558
1581
1605
1628
1652
1676
1699
1723
1747
1770
0%
891
914
937
959
982
1004
1027
1050
1072
1095
1117
1140
1162
1185
1207
1230
1253
1275
1298
1320
1343
1365
1388
1410
1433
1456
1478
1501
1523
1546
1568
1591
1613
1636
1659
1681
1704
1726
1%
880
902
923
945
967
989
1011
1033
1055
1077
1098
1120
1142
1164
1186
1207
1229
1251
1272
1294
1316
1337
1359
1381
1402
1424
1446
1467
1489
1510
1532
1553
1575
1597
1618
1640
1661
1683
2%
1002
1028
1054
1080
1105
1131
1157
1183
1209
1235
1261
1287
1313
1339
1366
1392
1418
1444
1470
1497
1523
1550
1576
1602
1629
1655
1682
1708
1735
1761
1788
1815
1841
1868
1895
1921
1948
1975
-2%
1002
1027
1052
1078
1103
1129
1154
1180
1205
1231
1256
1282
1307
1333
1359
1384
1410
1435
1461
1487
1512
1538
1564
1590
1615
1641
1667
1693
1718
1744
1770
1796
1822
1847
1873
1899
1925
1951
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
988
1012
1036
1061
1085
1109
1133
1158
1182
1206
1230
1254
1279
1303
1327
1351
1375
1399
1423
1447
1471
1496
1520
1544
1568
1592
1616
1640
1663
1687
1711
1735
1759
1783
1807
1831
1855
1879
0 - Wind
975
999
1022
1046
1069
1093
1116
1140
1163
1187
1210
1233
1257
1280
1303
1327
1350
1373
1396
1419
1443
1466
1489
1512
1535
1558
1581
1604
1627
1650
1673
1695
1718
1741
1764
1787
1810
1832
2%
1071
1098
1125
1152
1179
1206
1233
1260
1288
1315
1342
1369
1397
1424
1451
1479
1506
1533
1561
1588
1615
1643
1670
1698
1725
1753
1780
1808
1835
1863
1890
1918
1946
1973
2001
2028
2056
2084
-2%
1070
1097
1124
1150
1177
1204
1230
1257
1284
1310
1337
1364
1390
1417
1444
1471
1497
1524
1551
1577
1604
1631
1658
1684
1711
1738
1765
1792
1818
1845
1872
1898
1925
1952
1979
2006
2032
2059
-1%
1069
1095
1121
1147
1173
1200
1226
1252
1278
1304
1330
1357
1383
1409
1435
1461
1487
1513
1539
1565
1591
1617
1643
1669
1695
1721
1747
1773
1799
1825
1851
1877
1903
1929
1955
1981
2006
2032
0%
1056
1081
1107
1132
1158
1183
1208
1234
1259
1285
1310
1335
1360
1386
1411
1436
1461
1486
1511
1536
1562
1587
1612
1637
1662
1687
1711
1736
1761
1786
1811
1836
1861
1885
1910
1935
1960
1984
1%
10 kt Head Wind
1042
1067
1092
1117
1141
1166
1191
1215
1240
1264
1289
1313
1338
1362
1386
1411
1435
1459
1483
1507
1531
1556
1580
1604
1628
1652
1675
1699
1723
1747
1771
1795
1818
1842
1866
1889
1913
1937
2%
1144
1173
1201
1229
1258
1286
1314
1343
1371
1400
1428
1457
1485
1513
1542
1570
1599
1627
1656
1684
1713
1741
1770
1798
1827
1855
1884
1912
1941
1969
1998
2026
2055
2083
2112
2140
2169
2197
-2%
1143
1171
1199
1227
1255
1283
1311
1339
1367
1395
1423
1451
1479
1506
1534
1562
1590
1618
1646
1673
1701
1729
1757
1784
1812
1840
1868
1895
1923
1951
1978
2006
2034
2061
2089
2117
2144
2172
-1%
1142
1169
1197
1224
1252
1279
1307
1334
1361
1389
1416
1443
1471
1498
1525
1552
1579
1606
1634
1661
1688
1715
1742
1769
1796
1823
1850
1876
1903
1930
1957
1984
2011
2037
2064
2091
2117
2144
0%
1128
1155
1182
1208
1235
1262
1288
1315
1342
1368
1394
1421
1447
1474
1500
1526
1552
1578
1605
1631
1657
1683
1709
1735
1761
1787
1812
1838
1864
1890
1915
1941
1967
1992
2018
2044
2069
2095
1%
20 kt Head Wind
1114
1140
1166
1192
1218
1244
1270
1296
1321
1347
1372
1398
1423
1449
1474
1500
1525
1550
1575
1600
1626
1651
1676
1700
1725
1750
1775
1800
1825
1849
1874
1898
1923
1948
1972
1997
2021
2045
2%
[Rev. 4] 13 APR 2012
(cont’d on nect page
-1%
-2%
2%
5 kt Tail Wind
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
10 kt Tail Wind
5° FLAPS
Table 1 - shows the corrected ASDA (m) for
4.1-6
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
-1%
1678
1701
1724
1748
1771
1794
1818
1841
1864
1888
1911
1935
1958
1982
2006
2029
2053
2077
2100
2124
2148
2172
2196
2220
2244
2268
2292
2316
2340
2364
2388
2412
2436
2460
2485
2509
2533
2558
2582
-2%
1700
1724
1748
1772
1796
1821
1845
1869
1894
1918
1942
1967
1991
2016
2040
2065
2089
2114
2139
2164
2189
2213
2238
2263
2288
2313
2338
2363
2388
2413
2439
2464
2489
2514
2540
2565
2590
2616
2641
1654
1676
1699
1721
1743
1766
1788
1811
1833
1856
1879
1901
1924
1946
1969
1992
2014
2037
2060
2083
2105
2128
2151
2174
2197
2220
2243
2266
2289
2312
2335
2358
2381
2404
2427
2450
2473
2496
2520
0%
1611
1633
1654
1675
1697
1718
1739
1761
1782
1803
1825
1846
1868
1889
1911
1932
1954
1975
1997
2018
2040
2061
2083
2104
2126
2148
2169
2191
2213
2234
2256
2278
2299
2321
2343
2365
2387
2408
2430
1%
1569
1589
1610
1630
1650
1670
1691
1711
1731
1752
1772
1792
1812
1833
1853
1873
1894
1914
1934
1955
1975
1995
2016
2036
2056
2077
2097
2117
2138
2158
2179
2199
2220
2240
2261
2281
2301
2322
2343
2%
1843
1868
1894
1919
1945
1970
1996
2021
2047
2073
2098
2124
2150
2176
2202
2228
2253
2279
2305
2331
2357
2383
2409
2435
2462
2488
2514
2540
2566
2593
2619
2645
2671
2698
2724
2750
2777
2803
2830
-2%
1819
1844
1869
1893
1918
1942
1967
1992
2017
2041
2066
2091
2116
2140
2165
2190
2215
2240
2265
2290
2315
2340
2365
2390
2415
2440
2465
2490
2516
2541
2566
2591
2616
2641
2667
2692
2717
2743
2768
-1%
1794
1818
1841
1865
1889
1912
1936
1960
1984
2008
2031
2055
2079
2103
2127
2151
2174
2198
2222
2246
2270
2294
2318
2342
2366
2390
2414
2438
2462
2486
2510
2534
2558
2582
2607
2631
2655
2679
2703
0%
1749
1771
1794
1817
1839
1862
1884
1907
1930
1952
1975
1997
2020
2043
2065
2088
2110
2133
2156
2178
2201
2224
2246
2269
2292
2314
2337
2360
2382
2405
2428
2451
2473
2496
2519
2542
2564
2587
2610
1%
5 kt Tail Wind
10 kt Tail Wind
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
1704
1726
1747
1769
1790
1812
1833
1854
1876
1897
1919
1940
1962
1983
2005
2026
2047
2069
2090
2112
2133
2154
2176
2197
2219
2240
2261
2283
2304
2326
2347
2368
2390
2411
2433
2454
2476
2497
2518
2%
2002
2028
2055
2082
2109
2136
2163
2190
2217
2243
2270
2297
2324
2351
2378
2405
2433
2460
2487
2514
2541
2568
2595
2622
2650
2677
2704
2731
2758
2785
2813
2840
2867
2894
2922
2949
2976
3003
3030
-2%
(Continued)
5° FLAPS
Table 1 - shows the corrected ASDA (m) for
1977
2003
2029
2055
2081
2106
2132
2158
2184
2210
2236
2262
2288
2314
2340
2366
2393
2419
2445
2471
2497
2523
2549
2575
2601
2627
2653
2679
2705
2732
2758
2784
2810
2836
2862
2888
2914
2941
2967
-1%
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1902
1926
1950
1974
1998
2022
2045
2069
2093
2117
2141
2164
2188
2212
2236
2259
2283
2307
2330
2354
2378
2401
2425
2449
2472
2496
2520
2543
2567
2591
2614
2638
2662
2685
2709
2733
2756
2780
2803
0 - Wind
1855
1878
1901
1923
1946
1969
1991
2014
2036
2059
2082
2104
2127
2149
2172
2194
2217
2239
2262
2284
2307
2329
2351
2374
2396
2419
2441
2463
2486
2508
2530
2553
2575
2597
2619
2642
2664
2686
2708
2%
2111
2139
2167
2194
2222
2250
2278
2305
2333
2361
2388
2416
2444
2472
2499
2527
2555
2583
2610
2638
2666
2694
2721
2749
2777
2805
2833
2860
2888
2916
2944
2971
2999
3027
3054
3082
3110
3137
3165
-2%
2086
2113
2139
2166
2193
2220
2246
2273
2300
2327
2353
2380
2407
2434
2460
2487
2514
2541
2567
2594
2621
2647
2674
2701
2727
2754
2781
2808
2834
2861
2887
2914
2941
2967
2994
3021
3047
3074
3100
-1%
2058
2084
2110
2136
2161
2187
2213
2239
2264
2290
2316
2342
2367
2393
2419
2445
2470
2496
2521
2547
2573
2598
2624
2650
2675
2701
2726
2752
2778
2803
2829
2854
2880
2905
2931
2956
2982
3007
3032
0%
2009
2034
2058
2083
2108
2132
2157
2181
2206
2230
2255
2279
2304
2328
2353
2377
2401
2426
2450
2474
2499
2523
2547
2572
2596
2620
2644
2669
2693
2717
2741
2765
2789
2814
2838
2862
2886
2910
2934
1%
10 kt Head Wind
1960
1984
2007
2031
2054
2077
2101
2124
2147
2171
2194
2217
2241
2264
2287
2310
2333
2356
2379
2403
2426
2449
2472
2495
2518
2541
2564
2586
2609
2632
2655
2678
2701
2724
2746
2769
2792
2815
2837
2%
2226
2254
2283
2311
2339
2368
2396
2425
2453
2482
2510
2539
2567
2595
2624
2652
2680
2709
2737
2766
2794
2822
2850
2879
2907
2935
2963
2992
3020
3048
3076
3104
3132
3161
3189
3217
-
-2%
2199
2227
2254
2282
2310
2337
2364
2392
2419
2447
2474
2502
2529
2556
2584
2611
2638
2666
2693
2720
2748
2775
2802
2829
2856
2884
2911
2938
2965
2992
3019
3046
3073
3100
3127
3154
3181
3208
3235
-1%
2171
2197
2224
2251
2277
2304
2330
2357
2383
2409
2436
2462
2489
2515
2541
2568
2594
2620
2646
2673
2699
2725
2751
2777
2803
2829
2855
2881
2907
2933
2959
2985
3011
3037
3063
3089
3115
3141
3166
0%
2120
2146
2171
2196
2222
2247
2272
2297
2323
2348
2373
2398
2423
2448
2473
2498
2523
2548
2573
2598
2623
2648
2673
2698
2722
2747
2772
2796
2821
2846
2870
2895
2920
2944
2969
2993
3018
3042
3067
1%
20 kt Head Wind
2070
2094
2118
2142
2167
2191
2215
2239
2263
2287
2311
2335
2358
2382
2406
2430
2454
2477
2501
2525
2548
2572
2595
2619
2642
2666
2689
2713
2736
2759
2783
2806
2829
2852
2876
2899
2922
2945
2968
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-7
[Rev. 4] 13 APR 2012
METRIC
METRIC
-1%
828
849
871
892
914
936
957
979
1001
1022
1044
1066
1088
1110
1132
1153
1175
1198
1220
1242
1264
1286
1308
1330
1353
1375
1397
1419
1442
1464
1487
1509
1532
1554
1577
1599
1622
1645
-2%
865
888
911
935
958
982
1005
1028
1052
1076
1099
1123
1147
1171
1195
1219
1243
1267
1291
1316
1340
1365
1390
1414
1439
1464
1489
1514
1539
1564
1589
1614
1640
1665
1691
1716
1742
1767
789
809
829
849
869
889
908
928
948
968
988
1008
1027
1047
1067
1087
1107
1126
1146
1166
1186
1206
1225
1245
1265
1284
1304
1324
1344
1363
1383
1403
1422
1442
1462
1481
1501
1521
0%
729
747
765
783
801
818
836
854
871
889
907
924
941
959
976
993
1011
1028
1045
1062
1079
1096
1113
1130
1147
1163
1180
1197
1213
1230
1246
1263
1280
1296
1312
1329
1345
1361
1%
10 kt Tail Wind
636
653
669
685
701
717
732
748
764
780
795
810
825
840
855
870
885
900
915
929
943
957
971
985
999
1013
1027
1041
1055
1068
1081
1094
1108
1121
1134
1147
1161
1174
2%
967
993
1019
1045
1071
1097
1123
1149
1175
1201
1228
1255
1281
1307
1334
1361
1388
1415
1442
1470
1497
1524
1552
1579
1607
1635
1663
1691
1719
1747
1775
1803
1831
1860
1889
1917
1946
1974
-2%
926
950
973
997
1021
1045
1070
1094
1118
1142
1166
1191
1215
1240
1264
1288
1313
1337
1362
1387
1411
1436
1461
1486
1511
1535
1560
1585
1610
1636
1661
1686
1711
1736
1761
1786
1812
1837
-1%
883
905
927
949
971
993
1015
1037
1060
1082
1104
1126
1148
1170
1192
1214
1236
1258
1280
1302
1324
1346
1368
1390
1412
1434
1456
1478
1500
1522
1544
1566
1588
1610
1632
1654
1676
1698
0%
815
835
855
876
895
915
935
954
974
994
1013
1033
1052
1071
1091
1110
1129
1148
1167
1186
1205
1224
1243
1262
1281
1299
1318
1337
1355
1374
1392
1411
1429
1448
1466
1484
1502
1520
1%
5 kt Tail Wind
5° FLAPS
712
731
749
767
784
802
819
837
855
872
889
906
923
939
956
972
989
1006
1022
1038
1054
1069
1085
1101
1116
1132
1148
1163
1178
1193
1208
1222
1237
1252
1267
1281
1296
1311
2%
1096
1125
1154
1183
1213
1242
1272
1301
1331
1361
1391
1421
1451
1481
1511
1542
1573
1603
1634
1665
1696
1727
1758
1789
1821
1853
1885
1917
1948
1980
2012
2044
2077
2109
2142
2175
2207
2240
-2%
1049
1076
1103
1130
1157
1184
1211
1239
1266
1293
1321
1349
1376
1404
1431
1459
1487
1515
1543
1571
1599
1627
1655
1683
1711
1740
1768
1796
1825
1854
1882
1911
1940
1968
1997
2026
2054
2083
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
924
947
969
992
1014
1037
1059
1081
1103
1126
1148
1170
1192
1213
1235
1257
1279
1300
1322
1344
1365
1386
1408
1429
1450
1472
1493
1514
1535
1556
1577
1598
1619
1640
1660
1681
1702
1722
0 - Wind
808
829
849
869
889
909
929
949
968
988
1008
1026
1045
1064
1083
1101
1120
1139
1158
1176
1193
1211
1229
1246
1264
1282
1300
1317
1334
1351
1368
1384
1401
1418
1435
1451
1468
1485
2%
1170
1201
1232
1263
1294
1326
1357
1389
1421
1453
1485
1517
1549
1581
1614
1647
1680
1712
1745
1778
1812
1845
1879
1912
1946
1980
2014
2049
2083
2117
2151
2186
2221
2256
2291
2326
2361
2397
-2%
1119
1148
1177
1206
1235
1264
1293
1322
1352
1381
1410
1440
1469
1499
1529
1558
1588
1618
1648
1678
1708
1738
1768
1798
1828
1859
1889
1919
1950
1981
2012
2042
2073
2104
2135
2166
2197
2228
-1%
1068
1094
1121
1148
1174
1201
1228
1254
1281
1308
1334
1361
1388
1415
1441
1468
1495
1522
1548
1575
1602
1629
1655
1682
1709
1736
1763
1789
1816
1843
1870
1897
1923
1950
1977
2004
2031
2058
0%
987
1011
1035
1059
1083
1107
1130
1154
1178
1201
1225
1249
1272
1295
1319
1342
1365
1388
1412
1434
1457
1480
1503
1526
1549
1572
1594
1617
1639
1662
1684
1707
1729
1752
1774
1796
1818
1840
1%
10 kt Head Wind
863
885
907
928
949
970
992
1013
1034
1055
1076
1096
1116
1136
1156
1176
1196
1216
1236
1255
1274
1293
1312
1331
1350
1368
1387
1406
1424
1442
1460
1478
1496
1514
1532
1550
1568
1585
2%
1250
1283
1316
1349
1383
1416
1450
1484
1518
1552
1587
1621
1655
1690
1725
1760
1795
1831
1866
1901
1937
1973
2009
2045
2082
2118
2155
2192
2229
2266
2303
2340
2378
2415
2453
2491
2529
2567
-2%
1196
1226
1257
1288
1319
1350
1381
1413
1444
1475
1507
1538
1570
1602
1633
1665
1697
1729
1761
1793
1825
1858
1890
1923
1955
1988
2020
2053
2086
2119
2152
2185
2219
2252
2285
2318
2352
2385
-1%
1140
1169
1197
1226
1254
1283
1311
1340
1368
1397
1425
1454
1483
1511
1540
1569
1597
1626
1655
1683
1712
1741
1769
1798
1827
1856
1884
1913
1942
1971
2000
2028
2057
2086
2115
2144
2173
2202
0%
1054
1080
1105
1131
1157
1182
1207
1233
1258
1283
1309
1334
1359
1384
1408
1433
1458
1483
1508
1533
1557
1581
1606
1631
1655
1680
1704
1728
1752
1776
1800
1824
1848
1873
1896
1920
1944
1968
1%
20 kt Head Wind
922
946
969
992
1014
1037
1059
1082
1104
1127
1149
1170
1192
1213
1234
1256
1277
1299
1320
1340
1361
1381
1401
1421
1442
1462
1482
1502
1522
1541
1560
1579
1599
1618
1637
1656
1675
1694
2%
[Rev. 4] 13 APR 2012
(cont’d on next page)
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
Table 1A - shows the corrected TODA (m) for
4.1-8
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
-1%
1668
1690
1713
1736
1759
1781
1804
1827
1850
1873
1896
1919
1942
1965
1988
2012
2035
2058
2082
2105
2128
2151
2175
2198
2222
2245
2269
2292
2316
2339
2363
2386
2410
2434
2458
2481
2505
2529
2552
-2%
1793
1819
1845
1871
1897
1923
1949
1975
2002
2029
2055
2082
2108
2135
2162
2188
2216
2243
2270
2297
2324
2351
2379
2406
2434
2461
2489
2517
2544
2572
2600
2628
2656
2684
2712
2741
2769
2798
2826
1540
1560
1579
1599
1619
1638
1658
1677
1697
1716
1736
1756
1775
1795
1814
1834
1853
1873
1892
1912
1931
1951
1970
1989
2009
2028
2048
2067
2087
2106
2125
2145
2164
2184
2203
2222
2242
2261
2281
0%
1377
1394
1410
1426
1442
1458
1473
1489
1505
1521
1537
1553
1568
1584
1600
1616
1631
1646
1662
1677
1693
1708
1723
1739
1754
1770
1785
1800
1815
1830
1845
1860
1875
1890
1905
1920
1935
1950
1965
1%
10 kt Tail Wind
1186
1199
1211
1224
1236
1249
1261
1274
1286
1298
1310
1322
1334
1346
1357
1369
1381
1393
1405
1416
1428
1439
1450
1461
1472
1483
1494
1505
1516
1527
1538
1549
1560
1571
1581
1592
1603
1614
1624
2%
2003
2032
2061
2091
2120
2149
2178
2208
2237
2267
2297
2327
2357
2387
2417
2447
2477
2508
2538
2569
2599
2630
2661
2692
2723
2754
2785
2816
2847
2879
2910
2942
2974
3005
3037
3069
3101
3133
3165
-2%
Table 1A - shows the corrected TODA (m) for
1863
1888
1914
1939
1965
1990
2016
2042
2067
2093
2119
2145
2171
2197
2222
2249
2275
2301
2327
2353
2379
2405
2431
2458
2484
2511
2537
2564
2590
2616
2643
2669
2696
2723
2750
2776
2803
2830
2856
-1%
1720
1742
1764
1786
1808
1830
1852
1874
1896
1917
1939
1961
1983
2005
2027
2049
2071
2092
2114
2136
2158
2180
2202
2224
2245
2267
2289
2311
2333
2354
2376
2398
2420
2442
2463
2485
2507
2529
2550
0%
1325
1339
1353
1367
1381
1394
1408
1422
1436
1450
1463
1476
1490
1503
1516
1529
1542
1555
1569
1582
1595
1607
1619
1631
1644
1656
1668
1680
1693
1705
1717
1730
1742
1754
1766
1779
1791
1803
1814
2%
2273
2306
2340
2373
2406
2440
2473
2507
2541
2575
2609
2644
2678
2712
2746
2781
2816
2851
2886
2921
2956
2991
3027
3063
3098
3134
3170
3206
3242
3278
3315
3351
3387
3424
3460
3497
3534
3572
3609
-2%
2113
2142
2171
2200
2229
2258
2287
2317
2346
2376
2405
2435
2465
2494
2524
2554
2584
2613
2643
2673
2703
2733
2763
2794
2824
2854
2885
2915
2945
2976
3006
3037
3068
3098
3129
3160
3191
3221
3252
-1%
(Continued)
1538
1556
1574
1592
1610
1628
1646
1663
1681
1699
1716
1734
1752
1769
1787
1805
1822
1839
1856
1874
1891
1908
1925
1943
1960
1977
1994
2011
2028
2045
2062
2078
2095
2112
2129
2145
2162
2179
2196
1%
5 kt Tail Wind
5° FLAPS
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1743
1763
1784
1805
1825
1845
1865
1885
1905
1926
1946
1966
1986
2006
2026
2046
2066
2086
2105
2125
2145
2164
2184
2204
2223
2243
2263
2282
2301
2320
2340
2359
2378
2397
2416
2436
2455
2474
2493
0 - Wind
1500
1516
1532
1548
1564
1580
1595
1611
1627
1643
1658
1673
1688
1703
1718
1733
1748
1762
1777
1792
1807
1821
1835
1849
1863
1877
1891
1905
1919
1933
1947
1961
1975
1989
2003
2017
2031
2044
2057
2%
2432
2468
2504
2540
2576
2612
2648
2684
2721
2758
2795
2832
2869
2906
2943
2981
3019
3057
3094
3132
3170
3208
3247
3286
3324
3363
3402
3441
3480
3519
3559
3598
3638
3678
3717
3757
3798
3838
3879
-2%
2259
2291
2322
2353
2385
2416
2448
2479
2511
2543
2575
2607
2639
2670
2702
2735
2767
2799
2832
2864
2897
2929
2961
2994
3027
3060
3093
3126
3158
3191
3224
3258
3291
3324
3358
3391
3424
3458
3491
-1%
2085
2111
2138
2165
2192
2219
2246
2273
2300
2327
2353
2380
2407
2434
2461
2488
2515
2542
2569
2596
2623
2650
2677
2704
2731
2758
2785
2812
2839
2866
2893
2920
2947
2974
3001
3028
3055
3082
3109
0%
1862
1884
1906
1928
1950
1972
1993
2015
2037
2058
2080
2102
2123
2145
2167
2188
2209
2230
2251
2273
2294
2315
2336
2357
2378
2400
2421
2442
2463
2483
2504
2525
2545
2566
2587
2607
2628
2649
2669
1%
10 kt Head Wind
1602
1619
1636
1653
1670
1687
1704
1721
1738
1755
1771
1787
1803
1819
1835
1851
1867
1883
1899
1915
1931
1946
1961
1976
1991
2006
2021
2036
2051
2066
2081
2096
2111
2126
2141
2156
2171
2186
2200
2%
2605
2644
2683
2722
2761
2800
2839
2878
2918
2958
2998
3038
3078
3119
3159
3200
3241
3282
3323
3364
3406
3447
3489
3531
3573
3616
3658
3700
3743
3786
3829
3872
3916
3959
4002
4046
4090
4135
4179
-2%
2419
2453
2487
2520
2554
2588
2622
2657
2691
2725
2760
2794
2829
2863
2898
2933
2968
3003
3038
3073
3108
3143
3179
3214
3250
3286
3321
3357
3393
3429
3464
3501
3537
3573
3610
3646
3682
3719
3755
-1%
2231
2260
2288
2318
2347
2376
2405
2434
2463
2492
2521
2550
2579
2608
2637
2666
2695
2724
2753
2783
2812
2841
2870
2899
2929
2958
2987
3016
3046
3075
3104
3134
3163
3192
3222
3251
3280
3310
3339
0%
1991
2015
2039
2063
2086
2109
2132
2156
2179
2202
2226
2249
2272
2296
2319
2342
2365
2388
2411
2433
2456
2479
2502
2525
2548
2570
2593
2616
2639
2661
2683
2706
2728
2750
2773
2795
2817
2840
2862
1%
20 kt Head Wind
1712
1731
1749
1767
1785
1803
1822
1840
1858
1876
1893
1910
1928
1945
1962
1979
1997
2014
2031
2049
2065
2081
2098
2114
2130
2146
2162
2178
2195
2211
2227
2243
2259
2275
2292
2308
2324
2340
2355
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-9
[Rev. 4] 13 APR 2012
METRIC
METRIC
-1%
818
840
862
884
905
927
949
971
993
1015
1037
1059
1082
1104
1126
1148
1171
1193
1215
1238
1260
1283
1305
1328
1351
1373
1396
1419
1442
1465
1488
1511
1534
1557
1580
1603
1626
1650
-2%
821
843
864
887
909
931
953
976
998
1020
1043
1065
1088
1111
1134
1156
1179
1202
1225
1248
1271
1294
1317
1341
1364
1387
1411
1434
1458
1481
1505
1529
1552
1576
1600
1624
1648
1672
815
837
858
879
901
922
944
965
987
1009
1030
1052
1073
1095
1117
1139
1161
1182
1204
1226
1248
1270
1292
1314
1336
1358
1380
1402
1424
1446
1469
1491
1513
1535
1558
1580
1603
1625
0%
803
824
844
865
886
907
928
949
969
990
1011
1032
1053
1074
1095
1116
1137
1158
1179
1200
1221
1242
1264
1285
1306
1327
1348
1369
1390
1412
1433
1454
1475
1497
1518
1539
1561
1582
1%
10 kt Tail Wind
786
806
826
846
866
886
906
926
947
967
987
1007
1027
1047
1067
1088
1108
1128
1148
1168
1188
1208
1229
1249
1269
1289
1310
1330
1350
1370
1390
1411
1431
1451
1471
1491
1512
1532
2%
906
930
954
978
1002
1026
1050
1074
1098
1122
1146
1170
1195
1219
1243
1268
1292
1317
1341
1366
1390
1415
1440
1465
1490
1515
1539
1564
1590
1615
1640
1665
1690
1715
1741
1766
1792
1817
-2%
904
927
951
974
998
1022
1045
1069
1092
1116
1140
1164
1188
1211
1235
1259
1283
1307
1331
1355
1379
1403
1427
1452
1476
1500
1524
1548
1573
1597
1622
1646
1671
1695
1720
1744
1769
1793
-1%
900
924
947
970
993
1016
1039
1063
1086
1109
1132
1156
1179
1202
1225
1249
1272
1296
1319
1343
1366
1389
1413
1436
1460
1483
1507
1531
1554
1578
1601
1625
1649
1672
1696
1720
1744
1767
0%
887
909
932
954
977
999
1022
1044
1067
1089
1112
1134
1157
1180
1202
1225
1247
1270
1292
1315
1337
1360
1383
1405
1428
1450
1473
1495
1518
1541
1563
1586
1609
1631
1654
1677
1699
1722
1%
5 kt Tail Wind
868
890
912
934
956
977
999
1021
1042
1064
1086
1108
1129
1151
1172
1194
1216
1237
1259
1281
1302
1324
1345
1367
1389
1410
1432
1453
1475
1496
1518
1539
1561
1583
1604
1626
1647
1669
2%
1006
1032
1058
1083
1109
1135
1161
1187
1213
1239
1265
1291
1317
1343
1369
1395
1421
1448
1474
1500
1526
1552
1579
1605
1632
1658
1684
1711
1738
1764
1791
1817
1844
1870
1897
1924
1951
1977
-2%
1004
1029
1054
1080
1105
1131
1156
1182
1207
1233
1258
1284
1309
1335
1360
1386
1412
1437
1463
1488
1514
1540
1565
1591
1617
1643
1668
1694
1720
1746
1771
1797
1823
1849
1875
1901
1926
1952
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
985
1010
1034
1058
1083
1107
1131
1155
1180
1204
1228
1252
1276
1301
1325
1349
1373
1397
1421
1445
1470
1494
1518
1542
1566
1590
1614
1638
1662
1686
1710
1734
1758
1782
1805
1829
1853
1877
0 - Wind
965
989
1013
1036
1060
1083
1106
1130
1153
1177
1200
1223
1247
1270
1293
1316
1339
1363
1386
1409
1432
1455
1478
1501
1524
1547
1570
1593
1616
1639
1662
1685
1707
1730
1753
1776
1798
1821
2%
1077
1104
1131
1158
1185
1213
1240
1267
1294
1321
1348
1376
1403
1430
1457
1484
1512
1539
1566
1594
1621
1648
1676
1703
1730
1758
1785
1812
1840
1867
1895
1922
1950
1977
2005
2032
2060
2087
-2%
1075
1101
1128
1155
1181
1208
1235
1261
1288
1315
1341
1368
1395
1422
1448
1475
1502
1528
1555
1582
1608
1635
1662
1688
1715
1742
1768
1795
1822
1848
1875
1902
1928
1955
1982
2008
2035
2062
-1%
1071
1097
1123
1149
1176
1202
1228
1254
1281
1307
1333
1359
1385
1411
1437
1464
1490
1516
1542
1568
1594
1620
1646
1672
1698
1723
1749
1775
1801
1827
1853
1879
1904
1930
1956
1982
2008
2033
0%
1055
1081
1106
1132
1157
1183
1208
1234
1259
1285
1310
1335
1361
1386
1411
1436
1462
1487
1512
1537
1562
1587
1612
1637
1662
1687
1712
1737
1762
1786
1811
1836
1861
1885
1910
1935
1960
1984
1%
10 kt Head Wind
1034
1059
1084
1109
1133
1158
1182
1207
1232
1256
1281
1305
1329
1354
1378
1402
1426
1451
1475
1499
1523
1547
1571
1595
1619
1643
1666
1690
1714
1738
1761
1785
1809
1832
1856
1879
1903
1926
2%
1153
1182
1210
1238
1267
1295
1324
1352
1380
1409
1437
1466
1494
1522
1550
1579
1607
1636
1664
1692
1720
1749
1777
1805
1834
1862
1890
1918
1947
1975
2003
2032
2060
2088
2116
2145
2173
2201
-2%
1150
1178
1206
1234
1262
1290
1318
1346
1374
1402
1430
1458
1486
1513
1541
1569
1597
1624
1652
1680
1707
1735
1763
1790
1818
1845
1873
1900
1928
1955
1983
2010
2038
2065
2093
2120
2147
2175
-1%
1146
1174
1202
1229
1257
1284
1311
1339
1366
1394
1421
1448
1475
1503
1530
1557
1584
1611
1638
1665
1692
1719
1746
1773
1800
1826
1853
1880
1907
1934
1960
1987
2013
2040
2066
2093
2119
2146
0%
1130
1157
1184
1211
1237
1264
1291
1317
1344
1371
1397
1423
1450
1476
1502
1529
1555
1581
1607
1633
1659
1685
1711
1737
1763
1789
1815
1840
1866
1892
1917
1943
1968
1994
2019
2045
2070
2095
1%
20 kt Head Wind
1108
1134
1160
1186
1212
1238
1264
1289
1315
1341
1366
1392
1417
1443
1468
1493
1518
1544
1569
1594
1619
1644
1669
1693
1718
1743
1768
1792
1817
1841
1866
1890
1915
1939
1963
1987
2011
2036
2%
[Rev. 4] 13 APR 2012
(cont’d on next page)
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
Table 2 - shows the corrected ASDA (m) for 10° FLAPS
4.1-10
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
-1%
1673
1696
1720
1743
1767
1790
1814
1838
1861
1885
1909
1933
1957
1981
2005
2029
2053
2077
2101
2125
2150
2174
2199
2223
2247
2272
2297
2321
2346
2371
2396
2421
2446
2471
2496
2521
2546
2571
2596
-2%
1696
1720
1745
1769
1794
1818
1843
1867
1892
1917
1941
1966
1991
2016
2042
2067
2092
2117
2142
2168
2193
2219
2245
2270
2296
2322
2348
2374
2400
2426
2452
2479
2505
2532
2558
2584
2611
2638
2665
1648
1670
1693
1715
1738
1760
1783
1806
1829
1851
1874
1897
1920
1943
1966
1989
2012
2035
2058
2081
2104
2127
2150
2174
2197
2220
2243
2267
2290
2314
2337
2361
2384
2408
2432
2455
2479
2503
2527
0%
1603
1625
1646
1668
1689
1711
1732
1754
1775
1797
1818
1840
1862
1883
1905
1926
1948
1970
1992
2013
2035
2057
2079
2100
2122
2144
2166
2188
2210
2232
2254
2276
2298
2320
2342
2364
2386
2408
2430
1%
10 kt Tail Wind
1552
1572
1593
1613
1633
1653
1674
1694
1714
1735
1755
1775
1796
1816
1836
1857
1877
1897
1918
1938
1958
1979
1999
2020
2040
2060
2081
2101
2122
2142
2163
2183
2203
2224
2244
2265
2285
2306
2326
2%
1843
1868
1894
1920
1945
1971
1997
2023
2049
2075
2101
2127
2153
2179
2206
2232
2258
2285
2311
2338
2364
2391
2417
2444
2471
2498
2525
2552
2578
2606
2633
2660
2687
2714
2742
2769
2796
2824
2852
-2%
1818
1843
1867
1892
1917
1942
1967
1992
2017
2042
2067
2092
2117
2142
2167
2192
2217
2243
2268
2293
2319
2344
2369
2395
2420
2446
2472
2497
2523
2548
2574
2600
2626
2652
2678
2703
2729
2755
2781
-1%
1791
1815
1839
1863
1886
1910
1934
1958
1982
2006
2030
2054
2078
2102
2126
2150
2174
2198
2223
2247
2271
2295
2319
2343
2368
2392
2416
2441
2465
2489
2514
2538
2562
2587
2611
2636
2660
2685
2709
0%
1745
1767
1790
1813
1835
1858
1881
1903
1926
1949
1971
1994
2017
2040
2062
2085
2108
2131
2153
2176
2199
2222
2244
2267
2290
2313
2336
2358
2381
2404
2427
2450
2473
2495
2518
2541
2564
2587
2610
1%
5 kt Tail Wind
1690
1712
1733
1754
1776
1797
1819
1840
1862
1883
1905
1926
1947
1969
1990
2012
2033
2054
2076
2097
2119
2140
2161
2183
2204
2225
2247
2268
2289
2311
2332
2353
2374
2396
2417
2438
2460
2481
2502
2%
2004
2031
2058
2085
2112
2139
2166
2192
2220
2247
2274
2301
2328
2355
2382
2410
2437
2464
2491
2519
2546
2574
2601
2629
2656
2684
2711
2739
2766
2794
2822
2849
2877
2905
2933
2961
2988
3016
3044
-2%
Table 2 - shows the corrected ASDA (m) for 10° FLAPS (Continued)
1978
2004
2030
2056
2082
2108
2134
2160
2186
2212
2238
2264
2290
2316
2342
2369
2395
2421
2447
2473
2499
2526
2552
2578
2604
2630
2657
2683
2709
2736
2762
2788
2815
2841
2867
2894
2920
2947
2973
-1%
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1901
1925
1949
1972
1996
2020
2044
2068
2091
2115
2139
2163
2186
2210
2234
2257
2281
2305
2328
2352
2375
2399
2423
2446
2470
2493
2517
2540
2564
2587
2611
2634
2658
2681
2705
2728
2751
2775
2798
0 - Wind
1844
1866
1889
1911
1934
1957
1979
2002
2024
2047
2069
2091
2114
2136
2159
2181
2203
2225
2248
2270
2292
2314
2337
2359
2381
2403
2425
2447
2469
2491
2513
2535
2557
2579
2601
2623
2645
2666
2688
2%
2115
2142
2170
2198
2225
2253
2280
2308
2336
2364
2391
2419
2447
2474
2502
2530
2558
2585
2613
2641
2669
2697
2725
2752
2780
2808
2836
2864
2892
2920
2948
2976
3004
3032
3060
-
-2%
2088
2115
2142
2168
2195
2222
2248
2275
2301
2328
2355
2381
2408
2435
2461
2488
2515
2541
2568
2595
2621
2648
2674
2701
2728
2754
2781
2807
2834
2861
2887
2914
2941
2967
2994
3021
3047
-
-1%
2059
2085
2111
2136
2162
2188
2213
2239
2265
2290
2316
2341
2367
2392
2418
2444
2469
2494
2520
2545
2571
2596
2622
2647
2673
2698
2723
2749
2774
2799
2825
2850
2875
2901
2926
2951
2976
3001
3027
0%
2009
2033
2058
2082
2107
2131
2156
2180
2204
2229
2253
2278
2302
2326
2350
2374
2399
2423
2447
2471
2495
2519
2543
2567
2591
2615
2639
2663
2687
2711
2734
2758
2782
2806
2829
2853
2877
2900
2924
1%
10 kt Head Wind
1950
1973
1996
2019
2043
2066
2089
2112
2136
2158
2181
2204
2227
2250
2273
2296
2319
2342
2365
2387
2410
2433
2455
2478
2500
2523
2545
2568
2590
2613
2635
2657
2680
2702
2724
2746
2769
2791
2813
2%
2229
2258
2286
2314
2342
2370
2399
2427
2455
2483
2512
2540
2568
2596
2624
2652
2681
2709
2737
2765
2793
2821
2850
2878
2906
2934
2962
2990
3019
3047
-
-2%
2202
2229
2257
2284
2311
2338
2366
2393
2420
2447
2474
2502
2529
2556
2583
2610
2637
2664
2691
2718
2745
2772
2799
2826
2853
2880
2907
2934
2960
2987
3014
3041
-
-1%
2172
2199
2225
2251
2278
2304
2330
2356
2382
2409
2435
2461
2487
2513
2539
2565
2591
2617
2642
2668
2694
2720
2746
2771
2797
2823
2848
2874
2900
2925
2951
2976
3002
3027
3053
-
0%
2120
2146
2171
2196
2221
2246
2271
2296
2321
2346
2371
2396
2421
2445
2470
2494
2519
2544
2568
2593
2617
2642
2666
2690
2715
2739
2763
2787
2811
2836
2860
2884
2908
2932
2956
2979
3003
3027
3051
1%
20 kt Head Wind
2060
2084
2108
2132
2155
2179
2203
2227
2251
2274
2298
2321
2345
2368
2391
2415
2438
2461
2484
2507
2531
2554
2577
2600
2623
2645
2668
2691
2714
2737
2759
2782
2804
2827
2849
2872
2894
2917
2939
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-11
[Rev. 4] 13 APR 2012
METRIC
METRIC
-1%
824
846
867
889
910
931
953
974
996
1017
1039
1060
1082
1103
1125
1146
1168
1190
1212
1233
1255
1276
1298
1320
1342
1363
1385
1407
1429
1451
1473
1494
1516
1538
1560
1582
1604
1626
-2%
864
887
910
933
956
979
1002
1026
1049
1072
1096
1119
1143
1166
1190
1214
1237
1261
1284
1309
1333
1357
1381
1405
1429
1453
1478
1502
1526
1551
1575
1600
1625
1649
1674
1700
1725
1750
782
802
822
842
862
881
901
921
940
960
979
999
1019
1038
1058
1077
1097
1116
1135
1155
1174
1194
1213
1232
1252
1271
1290
1309
1329
1348
1367
1386
1406
1425
1444
1463
1482
1501
0%
718
736
753
771
789
806
824
841
858
876
893
911
928
945
962
979
996
1013
1030
1047
1063
1080
1097
1113
1130
1146
1163
1179
1196
1212
1228
1244
1260
1277
1293
1308
1324
1340
1%
10 kt Tail Wind
621
636
651
666
681
695
710
725
739
754
768
783
797
811
825
839
854
868
882
896
910
924
937
951
964
978
991
1005
1018
1032
1045
1057
1070
1083
1096
1109
1121
1134
2%
969
995
1020
1046
1072
1098
1124
1150
1176
1202
1228
1254
1281
1307
1334
1360
1387
1413
1440
1467
1494
1521
1548
1575
1602
1630
1657
1685
1712
1740
1768
1796
1824
1852
1880
1908
1937
1965
-2%
925
949
973
996
1020
1044
1068
1092
1116
1140
1164
1189
1213
1237
1261
1285
1309
1334
1358
1382
1407
1431
1455
1480
1504
1529
1553
1578
1602
1627
1652
1676
1701
1726
1751
1776
1800
1825
-1%
879
901
923
945
966
988
1010
1032
1054
1076
1098
1120
1142
1164
1186
1207
1229
1251
1273
1294
1316
1338
1360
1381
1403
1425
1446
1468
1490
1511
1533
1555
1576
1598
1619
1641
1662
1684
0%
807
826
846
866
885
905
924
944
963
982
1002
1021
1040
1059
1078
1097
1116
1135
1154
1173
1192
1210
1229
1248
1266
1285
1303
1322
1340
1358
1377
1395
1413
1431
1449
1467
1485
1503
1%
5 kt Tail Wind
699
716
733
749
765
782
798
814
830
847
863
879
895
911
926
942
958
973
989
1005
1021
1036
1051
1066
1081
1096
1111
1126
1141
1156
1171
1185
1200
1214
1228
1243
1257
1271
2%
1103
1132
1161
1191
1220
1250
1279
1309
1339
1369
1399
1429
1459
1489
1520
1551
1581
1612
1643
1674
1705
1736
1767
1799
1831
1862
1894
1926
1958
1990
2023
2056
2088
2121
2154
2187
2220
2254
-2%
1053
1080
1107
1134
1161
1189
1216
1243
1271
1298
1326
1353
1381
1409
1436
1464
1492
1520
1548
1576
1604
1632
1660
1688
1717
1745
1773
1802
1830
1859
1888
1916
1945
1974
2003
2032
2061
2090
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
919
941
963
986
1008
1030
1052
1074
1096
1118
1140
1162
1184
1206
1227
1249
1271
1292
1314
1336
1357
1378
1400
1421
1443
1464
1485
1506
1527
1548
1569
1590
1611
1632
1653
1674
1694
1715
0 - Wind
797
816
835
853
872
890
909
927
945
964
982
1001
1018
1036
1054
1072
1090
1108
1126
1144
1162
1179
1196
1213
1230
1248
1265
1282
1299
1317
1333
1350
1366
1382
1399
1415
1432
1448
2%
1182
1213
1244
1276
1308
1339
1371
1403
1435
1468
1500
1533
1566
1598
1632
1665
1698
1731
1765
1799
1833
1867
1901
1935
1970
2004
2039
2074
2109
2145
2180
2216
2252
2288
2324
2361
2397
2434
-2%
1127
1157
1186
1215
1244
1274
1303
1333
1362
1392
1421
1451
1481
1511
1541
1571
1601
1632
1662
1692
1723
1753
1784
1815
1846
1876
1907
1938
1969
2001
2032
2063
2095
2126
2158
2190
2222
2254
-1%
1071
1098
1125
1151
1178
1205
1232
1259
1286
1313
1340
1367
1394
1421
1448
1475
1502
1529
1556
1583
1610
1637
1664
1691
1718
1746
1773
1800
1827
1855
1882
1909
1936
1964
1991
2018
2046
2073
0%
984
1008
1032
1055
1079
1103
1127
1150
1174
1198
1221
1245
1268
1292
1315
1339
1362
1385
1409
1432
1455
1478
1501
1525
1548
1571
1594
1617
1640
1662
1685
1708
1731
1754
1776
1799
1821
1844
1%
10 kt Head Wind
854
874
894
914
934
953
973
993
1012
1032
1052
1071
1091
1110
1129
1148
1168
1187
1206
1225
1244
1263
1281
1300
1319
1337
1356
1374
1393
1411
1429
1447
1465
1483
1500
1518
1536
1554
2%
1267
1300
1334
1368
1403
1437
1472
1506
1541
1577
1612
1647
1683
1718
1754
1791
1827
1863
1900
1937
1974
2011
2049
2086
2124
2163
2201
2239
2278
2317
2356
2396
2435
2475
2515
2556
2597
2637
-2%
1208
1240
1271
1303
1334
1366
1398
1430
1462
1494
1526
1558
1591
1623
1656
1689
1721
1754
1788
1821
1854
1887
1921
1954
1988
2022
2056
2090
2124
2159
2193
2227
2262
2297
2332
2367
2402
2437
-1%
1148
1177
1205
1234
1263
1292
1321
1350
1379
1408
1438
1467
1496
1525
1554
1584
1613
1642
1672
1701
1731
1760
1790
1820
1849
1879
1909
1938
1968
1998
2028
2058
2088
2118
2148
2178
2208
2238
0%
1054
1080
1105
1131
1157
1182
1208
1233
1259
1284
1310
1335
1361
1386
1411
1436
1462
1487
1513
1538
1563
1588
1613
1638
1663
1688
1714
1738
1763
1788
1813
1838
1863
1888
1912
1937
1961
1986
1%
20 kt Head Wind
915
937
958
979
1000
1021
1042
1064
1085
1106
1127
1148
1169
1190
1210
1231
1252
1272
1293
1314
1335
1355
1375
1395
1415
1435
1455
1475
1495
1515
1535
1554
1573
1593
1612
1631
1650
1670
2%
[Rev. 4] 13 APR 2012
(cont’d on next page)
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
Table 2A - shows the corrected TODA (m) for 10° FLAPS
4.1-12
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
-1%
1648
1670
1692
1715
1737
1759
1781
1803
1826
1848
1870
1892
1915
1938
1960
1982
2005
2028
2050
2073
2096
2118
2141
2164
2187
2210
2233
2256
2279
2302
2326
2349
2372
2395
2418
2442
2466
2489
2513
-2%
1775
1800
1826
1851
1876
1902
1928
1954
1980
2006
2032
2059
2085
2111
2138
2165
2192
2219
2246
2273
2301
2329
2356
2384
2411
2440
2468
2497
2526
2554
2583
2612
2642
2671
2701
2731
2760
-
1520
1539
1558
1577
1596
1615
1634
1653
1672
1690
1709
1728
1747
1766
1784
1803
1822
1840
1859
1878
1897
1915
1934
1952
1971
1990
2008
2027
2045
2064
2082
2101
2119
2137
2156
2174
2193
2211
2229
0%
1356
1372
1388
1404
1419
1435
1450
1466
1481
1496
1512
1527
1542
1557
1572
1587
1602
1617
1632
1647
1662
1676
1691
1706
1720
1735
1749
1764
1778
1792
1806
1821
1835
1849
1863
1877
1891
1905
1919
1%
10 kt Tail Wind
1147
1160
1172
1184
1196
1208
1220
1232
1244
1256
1268
1280
1291
1303
1314
1325
1337
1348
1359
1370
1382
1393
1404
1415
1425
1436
1446
1457
1467
1478
1488
1499
1509
1519
1530
1540
1549
1559
1569
2%
1994
2023
2051
2080
2109
2138
2168
2197
2227
2256
2287
2317
2347
2377
2407
2438
2469
2500
2530
2562
2594
2625
2657
2689
2720
2753
2786
2819
2852
2885
2917
2951
2985
3020
3054
-
-2%
1850
1875
1900
1925
1951
1976
2001
2026
2052
2077
2102
2128
2153
2179
2204
2230
2256
2281
2307
2333
2359
2385
2411
2437
2463
2490
2516
2542
2569
2596
2622
2649
2675
2702
2728
2756
2783
2810
2837
-1%
1705
1727
1748
1770
1791
1812
1834
1855
1877
1898
1919
1941
1962
1983
2005
2026
2047
2068
2090
2111
2132
2153
2175
2196
2217
2238
2259
2280
2301
2322
2344
2365
2386
2407
2428
2449
2470
2491
2512
0%
1521
1538
1556
1574
1591
1609
1626
1644
1661
1679
1696
1713
1730
1747
1764
1781
1798
1815
1832
1849
1866
1882
1899
1915
1932
1948
1965
1981
1997
2014
2030
2046
2062
2078
2094
2110
2126
2142
2157
1%
5 kt Tail Wind
1285
1300
1313
1327
1340
1354
1367
1381
1395
1408
1421
1435
1448
1461
1473
1486
1499
1511
1524
1537
1549
1562
1575
1586
1598
1610
1622
1634
1646
1657
1669
1681
1693
1705
1716
1727
1738
1749
1760
2%
2287
2321
2355
2389
2423
2457
2492
2527
2562
2597
2632
2668
2704
2739
2776
2812
2849
2885
2922
2960
2998
3036
-
-2%
Table 2A - shows the corrected TODA (m) for 10° FLAPS (Continued)
2119
2148
2178
2207
2236
2266
2295
2325
2355
2385
2415
2445
2475
2505
2535
2565
2596
2626
2657
2688
2718
2749
2780
2811
2842
2874
2905
2936
2968
3000
3032
-
-1%
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1736
1756
1777
1798
1818
1838
1858
1878
1899
1919
1939
1959
1979
1999
2019
2038
2058
2078
2098
2118
2137
2156
2176
2195
2214
2234
2253
2272
2292
2310
2329
2348
2367
2386
2405
2424
2443
2461
2480
0 - Wind
1465
1481
1497
1512
1528
1543
1559
1574
1590
1606
1621
1637
1652
1666
1681
1696
1710
1725
1740
1754
1769
1784
1798
1812
1826
1839
1853
1867
1881
1894
1908
1922
1936
1949
1963
1976
1988
2001
2014
2%
2471
2508
2546
2584
2621
2659
2698
2736
2775
2814
2854
2893
2933
2973
3013
3054
-
-2%
2286
2318
2350
2383
2415
2448
2480
2513
2546
2579
2612
2645
2679
2712
2746
2779
2813
2847
2881
2915
2949
2984
3018
3053
-
-1%
2100
2128
2155
2183
2210
2237
2265
2292
2320
2347
2375
2402
2430
2458
2485
2513
2540
2568
2596
2623
2651
2679
2706
2734
2762
2790
2818
2845
2873
2901
2929
2957
2985
3013
3040
-
0%
1866
1889
1911
1934
1956
1978
2000
2022
2044
2066
2088
2110
2132
2154
2176
2197
2219
2241
2262
2284
2306
2327
2348
2369
2391
2412
2433
2455
2476
2497
2518
2539
2559
2580
2601
2622
2643
2663
2684
1%
10 kt Head Wind
1572
1589
1606
1623
1640
1657
1674
1691
1708
1725
1741
1758
1775
1791
1806
1822
1838
1854
1870
1886
1902
1918
1934
1949
1964
1979
1994
2009
2024
2039
2054
2069
2084
2099
2114
2128
2142
2156
2171
2%
2678
2720
2762
2804
2846
2888
2932
2975
3018
-
-2%
2473
2509
2544
2580
2616
2652
2689
2725
2762
2799
2836
2872
2910
2947
2985
3023
-
-1%
2268
2298
2328
2359
2389
2419
2450
2480
2511
2541
2572
2602
2633
2664
2694
2725
2756
2787
2817
2848
2879
2910
2941
2972
3003
3035
-
0%
2011
2035
2060
2085
2109
2133
2158
2182
2206
2230
2255
2279
2303
2327
2351
2375
2399
2423
2447
2471
2495
2518
2542
2566
2589
2613
2637
2660
2684
2707
2730
2754
2777
2800
2824
2847
2870
2893
2916
1%
20 kt Head Wind
1689
1709
1727
1745
1764
1782
1801
1819
1837
1856
1874
1893
1911
1928
1945
1963
1980
1998
2015
2033
2050
2068
2085
2102
2119
2135
2152
2168
2185
2201
2218
2234
2251
2267
2283
2299
2314
2330
2345
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-13
[Rev. 4] 13 APR 2012
METRIC
METRIC
817
838
860
881
903
925
946
968
990
1012
1034
1056
1078
1100
1122
1144
1166
1189
1211
1233
1256
1278
1301
1324
1346
1369
1392
1415
1438
1461
1484
1508
1531
1554
1578
1601
1625
1649
819
841
863
884
906
928
950
972
994
1017
1039
1061
1083
1106
1128
1151
1173
1196
1218
1241
1264
1287
1310
1333
1357
1380
1403
1427
1451
1474
1498
1522
1546
1570
1595
1619
1644
1668
813
835
856
877
898
920
941
963
984
1006
1027
1049
1071
1092
1114
1136
1158
1180
1202
1224
1246
1268
1290
1312
1334
1357
1379
1401
1424
1446
1469
1491
1514
1536
1559
1582
1605
1627
0%
801
821
842
863
883
904
925
946
967
988
1009
1030
1051
1072
1093
1115
1136
1157
1178
1200
1221
1243
1264
1285
1307
1328
1350
1371
1393
1414
1436
1458
1479
1501
1523
1544
1566
1588
1%
776
796
815
835
855
875
895
915
935
955
975
996
1016
1036
1056
1077
1097
1117
1137
1158
1178
1199
1219
1240
1260
1280
1301
1321
1342
1362
1383
1403
1424
1444
1464
1485
1505
1526
905
929
953
976
1000
1024
1048
1071
1095
1119
1143
1167
1191
1215
1239
1263
1288
1312
1336
1361
1385
1410
1434
1459
1484
1508
1533
1558
1583
1608
1634
1659
1684
1710
1736
1762
1787
1813
-2%
903
926
950
973
996
1020
1043
1067
1091
1114
1138
1161
1185
1209
1233
1256
1280
1304
1328
1352
1376
1400
1424
1448
1473
1497
1521
1546
1570
1595
1619
1644
1668
1693
1718
1743
1768
1793
-1%
899
922
945
968
992
1015
1038
1061
1084
1108
1131
1154
1178
1201
1224
1248
1271
1295
1318
1342
1365
1389
1412
1436
1460
1483
1507
1531
1555
1579
1602
1626
1650
1674
1698
1722
1746
1770
0%
885
908
930
953
975
998
1020
1043
1066
1088
1111
1134
1156
1179
1202
1225
1248
1270
1293
1316
1339
1362
1385
1408
1430
1453
1476
1499
1522
1545
1568
1591
1614
1637
1660
1683
1705
1728
1%
858
880
901
923
945
966
988
1010
1031
1053
1075
1097
1118
1140
1162
1184
1206
1227
1249
1271
1293
1315
1337
1359
1380
1402
1424
1446
1468
1490
1511
1533
1555
1576
1598
1620
1641
1663
2%
1007
1032
1058
1084
1109
1135
1160
1186
1212
1237
1263
1289
1314
1340
1366
1392
1418
1443
1469
1495
1521
1547
1573
1599
1625
1651
1677
1704
1730
1756
1783
1809
1836
1862
1889
1916
1943
1970
-2%
1004
1029
1055
1080
1105
1131
1156
1181
1207
1232
1257
1283
1308
1333
1359
1384
1410
1435
1461
1486
1511
1537
1562
1588
1614
1639
1665
1690
1716
1742
1767
1793
1819
1845
1871
1897
1923
1948
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
985
1009
1034
1058
1082
1107
1131
1156
1180
1204
1229
1253
1277
1302
1326
1351
1375
1399
1423
1448
1472
1496
1521
1545
1569
1593
1617
1642
1666
1690
1714
1738
1762
1786
1810
1834
1858
1881
0 - Wind
956
979
1002
1026
1049
1073
1096
1119
1143
1166
1190
1213
1237
1260
1283
1307
1330
1353
1377
1400
1423
1447
1470
1493
1516
1539
1562
1585
1608
1631
1654
1677
1700
1723
1745
1768
1791
1814
2%
1079
1106
1133
1160
1186
1213
1240
1267
1294
1320
1347
1374
1401
1427
1454
1481
1508
1535
1561
1588
1615
1642
1669
1695
1722
1749
1776
1803
1830
1857
1884
1911
1938
1966
1993
2020
2048
2075
-2%
1076
1103
1129
1156
1182
1209
1235
1262
1288
1315
1341
1368
1394
1420
1447
1473
1500
1526
1552
1579
1605
1631
1658
1684
1710
1737
1763
1789
1816
1842
1868
1895
1921
1948
1974
2000
2027
2053
-1%
1072
1098
1124
1151
1177
1203
1229
1255
1281
1307
1334
1360
1386
1412
1438
1464
1490
1516
1541
1567
1593
1619
1645
1671
1696
1722
1748
1774
1799
1825
1851
1876
1902
1927
1953
1978
2004
2029
0%
1056
1081
1107
1133
1158
1184
1209
1235
1260
1286
1311
1337
1362
1388
1413
1438
1464
1489
1514
1539
1564
1589
1614
1639
1664
1689
1714
1739
1764
1789
1813
1838
1863
1887
1912
1936
1961
1985
1%
10 kt Head Wind
1025
1050
1074
1099
1123
1148
1173
1197
1222
1246
1271
1295
1320
1344
1368
1393
1417
1441
1465
1490
1514
1538
1562
1586
1610
1634
1657
1681
1705
1729
1752
1776
1799
1823
1846
1869
1892
1916
2%
1156
1184
1212
1240
1268
1297
1324
1352
1380
1408
1436
1464
1491
1519
1547
1574
1602
1629
1657
1684
1712
1740
1767
1795
1822
1850
1877
1905
1932
1960
1987
2014
2042
2070
2098
2125
2153
2181
-2%
1153
1181
1209
1236
1264
1292
1320
1347
1375
1402
1430
1457
1484
1512
1539
1566
1593
1621
1648
1675
1702
1729
1756
1783
1810
1837
1864
1891
1918
1944
1971
1998
2025
2052
2079
2105
2132
2159
-1%
1149
1176
1204
1231
1258
1286
1313
1340
1367
1395
1422
1449
1476
1503
1529
1556
1583
1610
1637
1663
1690
1716
1743
1769
1796
1822
1848
1875
1901
1927
1953
1979
2005
2031
2057
2083
2109
2135
0%
1132
1159
1186
1212
1239
1266
1293
1319
1346
1372
1399
1425
1451
1478
1504
1530
1556
1582
1608
1634
1660
1686
1712
1737
1763
1788
1814
1839
1865
1890
1915
1940
1965
1990
2015
2040
2065
2090
1%
20 kt Head Wind
1099
1125
1151
1177
1203
1228
1254
1280
1305
1331
1356
1382
1407
1432
1458
1483
1508
1533
1558
1583
1608
1633
1658
1682
1707
1731
1756
1780
1804
1829
1853
1877
1901
1925
1948
1972
1996
2019
2%
[Rev. 4] 13 APR 2012
(cont’d on next page)
-1%
-2%
2%
5 kt Tail Wind
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
10 kt Tail Wind
15° FLAPS
Table 3 - shows the corrected ASDA (m) for
4.1-14
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
-1%
1673
1697
1721
1745
1769
1794
1818
1843
1868
1893
1917
1942
1968
1993
2019
2044
2070
2096
2121
2148
2174
2201
2227
2254
2281
2308
2335
2363
2390
2418
-
-2%
1693
1719
1744
1769
1795
1820
1846
1872
1899
1925
1951
1978
2006
2033
2061
2088
2116
2144
2173
2202
2231
2260
2289
2320
2350
2381
2412
-
1650
1673
1696
1719
1743
1766
1789
1812
1835
1859
1882
1906
1929
1953
1977
2001
2024
2048
2072
2096
2120
2144
2168
2192
2217
2241
2265
2290
2314
2339
2363
2388
2412
-
0%
1609
1631
1653
1675
1696
1718
1740
1762
1784
1806
1828
1849
1871
1893
1915
1937
1959
1981
2003
2024
2046
2068
2090
2112
2134
2156
2178
2199
2221
2243
2265
2287
2309
2331
2352
2374
2396
2418
-
1%
1546
1567
1587
1607
1628
1648
1669
1689
1709
1729
1750
1770
1790
1810
1831
1851
1871
1891
1911
1931
1951
1971
1991
2011
2030
2050
2070
2089
2109
2129
2149
2168
2188
2207
2226
2246
2265
2285
2304
2%
1839
1866
1892
1919
1945
1972
1999
2026
2054
2081
2109
2136
2165
2193
2221
2250
2278
2307
2337
2367
2396
-
-2%
1818
1843
1868
1894
1919
1944
1970
1996
2022
2047
2073
2099
2125
2152
2178
2204
2231
2257
2284
2311
2338
2365
2392
2420
-
-1%
1794
1818
1842
1867
1891
1915
1939
1964
1988
2012
2037
2061
2086
2110
2135
2159
2184
2208
2233
2258
2282
2307
2332
2357
2381
2406
-
0%
1751
1774
1797
1820
1843
1865
1888
1911
1934
1957
1980
2003
2025
2048
2071
2093
2116
2139
2161
2184
2206
2229
2252
2274
2297
2319
2342
2364
2386
2409
-
1%
5 kt Tail Wind
10 kt Tail Wind
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
1685
1706
1728
1749
1771
1792
1814
1835
1856
1877
1898
1919
1941
1962
1983
2004
2025
2045
2066
2087
2108
2129
2149
2170
2190
2210
2231
2251
2272
2292
2312
2332
2352
2372
2392
2411
-
2%
1997
2024
2051
2079
2106
2133
2161
2189
2217
2245
2273
2302
2330
2359
2388
2417
-
-2%
(Continued)
15° FLAPS
Table 3 - shows the corrected ASDA (m) for
1974
2000
2027
2053
2079
2105
2131
2158
2184
2211
2237
2264
2290
2317
2344
2371
2398
-
-1%
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1905
1929
1953
1977
2000
2024
2047
2071
2094
2118
2142
2165
2188
2211
2235
2258
2281
2304
2327
2350
2373
2396
2419
-
0 - Wind
1836
1858
1881
1903
1925
1948
1970
1992
2014
2036
2058
2079
2101
2123
2145
2166
2187
2209
2230
2251
2273
2294
2315
2336
2356
2377
2398
2418
-
2%
2103
2130
2158
2186
2213
2241
2269
2298
2326
2354
2383
2411
-
-2%
2080
2106
2133
2159
2186
2213
2239
2266
2293
2319
2346
2373
-
-1%
2055
2080
2106
2131
2157
2182
2207
2233
2258
2283
2308
2334
2359
2384
2409
-
0%
2009
2033
2058
2082
2106
2130
2154
2178
2202
2226
2249
2273
2296
2320
2343
2367
2390
2414
-
1%
10 kt Head Wind
1939
1961
1984
2007
2030
2053
2075
2098
2120
2142
2164
2186
2209
2231
2253
2274
2296
2317
2339
2360
2382
2403
-
2%
2208
2237
2265
2292
2320
2348
2376
2405
-
-2%
2185
2212
2239
2266
2293
2319
2346
2373
2400
-
-1%
2160
2186
2212
2237
2263
2289
2314
2339
2365
2390
2416
-
0%
2114
2139
2163
2188
2212
2236
2260
2284
2308
2332
2356
2380
2404
-
1%
20 kt Head Wind
2043
2066
2089
2112
2135
2158
2181
2204
2226
2249
2271
2293
2315
2338
2360
2381
2403
-
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-15
[Rev. 4] 13 APR 2012
METRIC
METRIC
-1%
818
838
859
880
901
922
943
964
985
1006
1027
1048
1069
1090
1111
1132
1154
1175
1196
1217
1239
1260
1281
1302
1324
1345
1366
1388
1409
1431
1452
1474
1495
1517
1539
1560
1582
1604
-2%
851
873
896
918
941
963
986
1009
1031
1055
1078
1100
1123
1146
1170
1193
1216
1240
1263
1286
1310
1334
1358
1381
1405
1430
1454
1478
1502
1526
1551
1576
1600
1625
1650
1675
1700
1725
777
796
816
835
854
873
893
912
931
950
969
988
1007
1026
1046
1065
1084
1102
1121
1140
1159
1178
1197
1216
1235
1253
1272
1291
1309
1328
1347
1366
1384
1403
1421
1440
1459
1477
0%
714
732
749
766
783
800
817
834
851
868
885
902
919
935
952
969
985
1002
1018
1035
1051
1067
1083
1099
1115
1131
1147
1163
1179
1195
1211
1226
1242
1257
1273
1288
1304
1319
1%
10 kt Tail Wind
637
652
667
682
697
712
727
742
757
772
787
801
815
830
844
859
873
888
902
916
929
943
957
971
985
998
1012
1026
1039
1052
1065
1078
1091
1104
1117
1130
1143
1155
2%
957
982
1007
1033
1059
1084
1110
1135
1161
1187
1213
1239
1265
1291
1317
1344
1370
1397
1423
1450
1477
1504
1531
1558
1585
1613
1640
1668
1695
1723
1752
1780
1808
1836
1865
1893
1922
1951
-2%
920
943
967
990
1014
1038
1061
1085
1109
1132
1156
1180
1204
1228
1251
1275
1299
1323
1347
1371
1396
1420
1444
1468
1492
1517
1541
1565
1590
1614
1639
1663
1688
1713
1737
1762
1787
1812
-1%
874
896
918
939
961
983
1004
1026
1047
1069
1091
1112
1134
1155
1177
1198
1220
1241
1263
1284
1305
1327
1348
1370
1391
1412
1434
1455
1476
1497
1519
1540
1561
1582
1603
1625
1646
1667
0%
803
823
842
862
881
900
920
939
958
977
996
1015
1034
1053
1071
1090
1109
1127
1146
1164
1183
1201
1219
1238
1256
1274
1292
1310
1328
1346
1364
1381
1399
1417
1435
1452
1469
1487
1%
5 kt Tail Wind
717
735
751
768
785
802
818
835
852
869
885
901
917
934
950
966
982
998
1015
1030
1046
1061
1077
1092
1108
1123
1139
1154
1169
1184
1199
1213
1228
1243
1258
1272
1287
1301
2%
1096
1125
1154
1183
1213
1242
1272
1302
1332
1362
1392
1422
1453
1483
1514
1545
1576
1607
1638
1669
1701
1733
1764
1796
1829
1861
1894
1926
1959
1992
2025
2059
2092
2126
2160
2194
2229
2263
-2%
1053
1080
1107
1134
1161
1189
1216
1243
1271
1298
1326
1354
1381
1409
1437
1465
1493
1521
1549
1577
1605
1633
1662
1690
1719
1748
1776
1805
1834
1863
1892
1921
1950
1979
2008
2038
2067
2097
-1%
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
0%
1%
919
941
964
986
1008
1030
1052
1074
1096
1118
1140
1162
1184
1206
1227
1249
1271
1293
1314
1336
1357
1378
1399
1421
1442
1463
1485
1505
1526
1547
1568
1589
1610
1631
1651
1672
1692
1712
0 - Wind
820
840
859
878
898
917
936
955
974
994
1012
1031
1050
1069
1087
1106
1125
1143
1162
1180
1198
1216
1234
1252
1270
1288
1306
1324
1341
1358
1375
1393
1410
1427
1444
1461
1479
1495
2%
1179
1210
1241
1274
1306
1338
1370
1402
1435
1468
1501
1534
1567
1600
1634
1668
1702
1736
1770
1805
1839
1874
1909
1944
1980
2016
2052
2088
2124
2161
2198
2235
2272
2309
2347
2386
2424
2462
-2%
1132
1161
1191
1220
1249
1279
1309
1339
1369
1399
1429
1459
1489
1520
1550
1580
1611
1642
1673
1703
1734
1765
1796
1828
1859
1891
1922
1954
1986
2018
2050
2082
2114
2146
2179
2212
2244
2277
-1%
1075
1102
1129
1156
1183
1210
1237
1265
1292
1319
1346
1373
1400
1428
1455
1482
1510
1537
1564
1591
1619
1646
1674
1701
1728
1756
1783
1811
1838
1866
1893
1921
1948
1976
2004
2031
2059
2087
0%
987
1012
1036
1060
1084
1108
1132
1155
1179
1203
1227
1251
1275
1298
1322
1345
1369
1392
1416
1439
1462
1486
1509
1532
1555
1579
1602
1625
1648
1670
1693
1716
1739
1762
1785
1807
1830
1852
1%
10 kt Head Wind
881
902
923
944
964
985
1006
1027
1047
1068
1088
1109
1129
1149
1169
1190
1210
1230
1250
1270
1290
1309
1329
1348
1368
1387
1407
1427
1445
1464
1483
1501
1520
1539
1558
1577
1595
1613
2%
1269
1303
1337
1372
1407
1442
1477
1512
1548
1584
1620
1656
1693
1729
1766
1803
1841
1878
1916
1954
1992
2031
2070
2108
2148
2188
2228
2267
2308
2349
2390
2431
2473
2514
2557
2600
2643
2686
-2%
1218
1250
1282
1314
1346
1378
1411
1443
1476
1508
1541
1574
1607
1641
1674
1707
1741
1775
1809
1842
1876
1910
1945
1980
2014
2049
2084
2119
2154
2190
2225
2261
2297
2333
2369
2406
2442
2479
-1%
1157
1186
1215
1244
1274
1303
1333
1362
1392
1421
1451
1481
1510
1540
1570
1600
1630
1660
1689
1719
1749
1780
1810
1840
1870
1900
1930
1961
1991
2022
2052
2082
2113
2144
2174
2205
2236
2266
0%
1062
1088
1114
1140
1166
1192
1218
1244
1270
1296
1322
1348
1373
1399
1424
1450
1476
1502
1527
1553
1578
1603
1629
1654
1680
1705
1731
1756
1781
1806
1831
1857
1882
1907
1932
1957
1982
2006
1%
20 kt Head Wind
947
970
992
1015
1037
1059
1082
1104
1127
1149
1171
1193
1215
1237
1259
1281
1303
1325
1347
1368
1389
1411
1432
1453
1475
1496
1518
1539
1559
1580
1600
1621
1641
1662
1682
1703
1724
1743
2%
[Rev. 4] 13 APR 2012
(cont’d on next page)
Wind
ASDA
Slope
(m)
1000
1025
1050
1075
1100
1125
1150
1175
1200
1225
1250
1275
1300
1325
1350
1375
1400
1425
1450
1475
1500
1525
1550
1575
1600
1625
1650
1675
1700
1725
1750
1775
1800
1825
1850
1875
1900
1925
Table 3A - shows the corrected TODA (m) for 15° FLAPS
4.1-16
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
Wind
ASDA
Slope
(m)
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
-1%
1625
1647
1669
1691
1713
1735
1757
1779
1801
1823
1845
1868
1890
1912
1935
1957
1980
2002
2025
2048
2070
2093
2116
2139
2162
2185
2208
2232
2255
2278
2302
2325
2349
2373
2396
2420
2444
2469
2493
-2%
1751
1777
1802
1828
1853
1880
1906
1933
1959
1985
2013
2040
2067
2094
2122
2150
2178
2206
2235
2263
2292
2321
2351
2381
2410
2441
2472
2503
2535
2566
-
1496
1514
1532
1551
1569
1588
1606
1624
1643
1661
1679
1698
1716
1734
1752
1770
1789
1807
1825
1843
1861
1879
1897
1915
1933
1951
1969
1987
2005
2023
2041
2059
2076
2094
2112
2130
2148
2165
2183
0%
1334
1349
1365
1380
1395
1410
1425
1439
1454
1469
1484
1498
1513
1527
1542
1556
1570
1585
1599
1613
1627
1641
1655
1669
1683
1697
1711
1724
1738
1752
1765
1779
1792
1805
1819
1832
1845
1859
1872
1%
10 kt Tail Wind
1168
1180
1192
1204
1217
1229
1241
1253
1265
1277
1288
1300
1311
1323
1334
1346
1357
1368
1380
1391
1401
1412
1423
1433
1444
1454
1465
1476
1486
1497
1507
1517
1527
1537
1546
1556
1566
1576
1585
2%
1980
2010
2039
2069
2098
2129
2159
2189
2220
2251
2282
2313
2344
2376
2408
2440
2473
2505
2539
2572
2605
2639
2674
2708
2743
2778
2815
2851
2888
2924
-
-2%
1836
1862
1887
1912
1937
1962
1987
2013
2038
2064
2089
2115
2140
2166
2192
2218
2244
2270
2296
2322
2348
2375
2401
2428
2455
2481
2508
2535
2562
2589
2616
2644
2671
2699
2726
2754
2782
2811
2839
-1%
1688
1709
1730
1751
1772
1793
1814
1835
1856
1877
1898
1919
1940
1961
1982
2003
2024
2045
2065
2086
2107
2128
2149
2169
2190
2211
2232
2252
2273
2294
2314
2335
2355
2376
2397
2417
2438
2458
2479
0%
1504
1521
1539
1556
1573
1590
1607
1624
1641
1658
1674
1691
1708
1724
1741
1757
1774
1790
1806
1823
1839
1855
1871
1886
1902
1918
1934
1950
1966
1981
1997
2012
2028
2043
2058
2074
2089
2104
2119
1%
5 kt Tail Wind
1315
1329
1343
1357
1371
1385
1398
1412
1426
1439
1452
1465
1478
1491
1504
1517
1530
1543
1556
1569
1581
1593
1605
1617
1629
1641
1653
1665
1677
1689
1701
1712
1724
1735
1746
1757
1768
1780
1791
2%
2298
2333
2369
2404
2439
2476
2513
2549
2586
2623
2661
2699
2736
2775
2814
2853
2892
2932
2973
3013
3054
-
-2%
Table 3A - shows the corrected TODA (m) for 15° FLAPS (Continued)
2126
2156
2186
2216
2246
2276
2306
2337
2367
2398
2428
2459
2490
2521
2552
2583
2615
2646
2678
2710
2741
2773
2806
2838
2870
2903
2935
2968
3002
3035
-
-1%
1950
1975
2000
2025
2050
2075
2100
2125
2150
2175
2200
2225
2250
2275
2300
2325
2350
2375
2400
2425
2450
2475
2500
2525
2550
2575
2600
2625
2650
2675
2700
2725
2750
2775
2800
2825
2850
2875
2900
0%
1%
1733
1753
1774
1794
1814
1834
1854
1874
1894
1914
1934
1954
1973
1993
2012
2032
2051
2071
2090
2110
2129
2148
2167
2186
2205
2224
2243
2262
2281
2299
2318
2336
2355
2373
2392
2410
2428
2447
2465
0 - Wind
1511
1527
1544
1560
1576
1592
1609
1625
1641
1656
1672
1687
1702
1718
1733
1748
1763
1779
1794
1809
1823
1837
1852
1866
1880
1894
1909
1923
1937
1952
1966
1979
1992
2005
2019
2032
2045
2059
2072
2%
2501
2541
2580
2620
2660
2701
2742
2783
2824
2866
2908
2951
2994
3037
-
-2%
2310
2343
2377
2410
2443
2477
2511
2545
2579
2613
2647
2682
2716
2751
2786
2821
2856
2892
2928
2964
2999
3036
-
-1%
2114
2142
2170
2197
2225
2253
2281
2308
2336
2364
2392
2420
2448
2476
2503
2531
2559
2587
2615
2643
2671
2699
2727
2755
2784
2812
2840
2868
2896
2924
2953
2981
3009
3037
-
0%
1875
1897
1919
1942
1964
1986
2008
2030
2052
2074
2096
2119
2140
2162
2183
2205
2227
2248
2270
2291
2313
2334
2355
2376
2397
2418
2440
2461
2482
2503
2523
2544
2565
2585
2606
2627
2647
2668
2688
1%
10 kt Head Wind
1631
1649
1667
1685
1702
1720
1738
1756
1774
1790
1807
1824
1841
1858
1875
1891
1908
1925
1942
1958
1974
1990
2005
2021
2037
2053
2069
2084
2100
2116
2131
2146
2161
2176
2190
2205
2220
2235
2249
2%
2730
2774
2819
2864
2909
2955
3002
3048
-
-2%
2515
2553
2590
2627
2665
2702
2741
2779
2818
2856
2894
2934
2973
3013
3052
-
-1%
2297
2328
2359
2390
2420
2452
2483
2514
2545
2576
2607
2639
2670
2701
2733
2764
2796
2827
2859
2890
2922
2954
2986
3017
3049
-
0%
2031
2056
2081
2106
2130
2155
2179
2204
2228
2253
2277
2302
2326
2350
2374
2398
2422
2446
2471
2495
2519
2542
2566
2590
2613
2637
2661
2685
2708
2732
2755
2778
2801
2825
2848
2871
2895
2918
2941
1%
20 kt Head Wind
1763
1782
1802
1822
1841
1861
1881
1900
1920
1938
1957
1975
1994
2013
2031
2050
2068
2087
2106
2124
2141
2159
2176
2194
2211
2229
2246
2264
2281
2299
2316
2333
2349
2366
2382
2398
2415
2431
2448
2%
CHAPTER 4
PERFORMANCE
AOM DASH 8-Q400
4.1-17
[Rev. 4] 13 APR 2012
METRIC
CHAPTER 4
4.1-18
[Rev. X] 31 MAY 2011
4.1.2.2
PERFORMANCE
Maximum Mass for ASDA and TODA
The tables shall be entered with the corrected ASDA and TODA (Sub-Chapter 4.1.2.1).
Find the limiting mass for the corresponding pressure altitude and temperature.
Remember:
NOTE:
The lowest mass - either for ASDA or for TODA - shall be used for determination of the
allowed mass for take-off!
The so obtained mass limit may be further restricted by obstacles (see Sub-Chapter 4.1.5).
A higher mass limit may be obtained by using a lower V1, however those relevant data are not
given in the AOM for reasons of simplification and as a conservation.
The following tables are made out for a pressure altitude of 0 up to 10000 ft in intervals of 1000 ft:
Table 4 - shows the maximum mass for ASDA for 5° Flaps.
Table 4A - shows the maximum mass for TODA for 5° Flaps.
Table 5 - shows the maximum mass for ASDA for 10° Flaps.
Table 5A - shows the maximum mass for TODA for 10° Flaps.
Table 6 - shows the maximum mass for ASDA for 15° Flaps.
Table 6A - shows the maximum mass for TODA for 15° Flaps.
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg)
4.1-19
[Rev. X] 31 MAY 2011
5° FLAPS
PA (ft)
Sea Level
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
50
1000
22946
22623
22317
22023
21670
21298
20946
20504
20100
18835
Min
Min
1025
23319
22986
22670
22367
22080
21720
21355
20897
20477
19761
18366
Min
1050
23693
23349
23023
22710
22414
22109
21764
21289
20854
20264
19186
Min
1075
24055
23712
23376
23053
22748
22433
22133
21681
21231
20619
20002
18221
1100
24367
24062
23729
23396
23082
22757
22448
22057
21608
20975
20336
18912
1125
24680
24366
24069
23739
23416
23081
22763
22360
21985
21330
20669
19604
1150
24992
24669
24364
24069
23750
23406
23078
22663
22280
21686
21003
20130
1175
25304
24973
24659
24356
24070
23730
23393
22965
22572
22032
21336
20434
1200
25617
25276
24955
24643
24349
24045
23708
23268
22864
22308
21670
20738
1225
25929
25580
25250
24930
24628
24316
24019
23571
23156
22584
22003
21043
1250
26230
25883
25545
25217
24907
24587
24283
23874
23447
22861
22263
21347
1275
26529
26178
25840
25504
25186
24858
24546
24148
23739
23137
22523
21651
1300
26827
26468
26129
25791
25465
25129
24809
24401
24026
23413
22783
21955
1325
27125
26757
26411
26074
25744
25400
25072
24654
24270
23689
23043
22203
1350
27424
27047
26692
26347
26022
25671
25336
24907
24513
23965
23303
22442
1375
27722
27337
26973
26620
26288
25942
25599
25160
24757
24201
23563
22680
1400
28020
27626
27254
26893
26553
26203
25862
25414
25001
24432
23823
22918
1425
28319
27916
27536
27166
26818
26460
26119
25667
25245
24663
24069
23157
1450
28617
28205
27817
27439
27083
26717
26368
25920
25489
24894
24286
23395
1475
28864
28495
28098
27712
27348
26974
26618
26164
25733
25124
24503
23633
1500
29117
28763
28379
27985
27614
27231
26867
26403
25976
25355
24720
23872
1525
(29389) 28994
28661
28258
27879
27488
27117
26642
26208
25586
24938
24092
1550
Max
29243
28884
28531
28144
27745
27366
26882
26438
25817
25155
24291
1575
Max
(29521) 29121
28777
28409
28003
27616
27121
26668
26044
25372
24490
1600
Max
Max
(29374) 28995
28674
28260
27865
27361
26898
26262
25589
24689
1625
Max
Max
Max
29228
28881
28517
28115
27600
27129
26479
25806
24888
1650
Max
Max
Max
(29485) 29103
28754
28364
27839
27359
26696
26022
25087
1675
Max
Max
Max
Max
(29337) 28955
28614
28079
27589
26913
26226
25286
1700
Max
Max
Max
Max
Max
29173
28822
28318
27819
27131
26430
25485
1725
Max
Max
Max
Max
Max
(29406) 29023
28558
28049
27348
26634
25684
1750
Max
Max
Max
Max
Max
Max
29234
28772
28280
27565
26838
25883
1775
Max
Max
Max
Max
Max
Max
(29467) 28958
28510
27782
27042
26077
1800
Max
Max
Max
Max
Max
Max
Max
29160
28728
28000
27246
26263
1825
Max
Max
Max
Max
Max
Max
Max
(29375) 28903
28217
27450
26449
1850
Max
Max
Max
Max
Max
Max
Max
Max
29095
28434
27653
26635
1875
Max
Max
Max
Max
Max
Max
Max
Max
(29294) 28651
27857
26822
1900
Max
Max
Max
Max
Max
Max
Max
Max
(29510) 28825
28061
27008
1925
Max
Max
Max
Max
Max
Max
Max
Max
Max
28998
28265
27194
1950
Max
Max
Max
Max
Max
Max
Max
Max
Max
29182
28469
27380
1975
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29378) 28673
27566
2000
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28831
27752
2025
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28993
27938
2050
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29167
28124
2075
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29349) 28311
2100
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29541) 28497
2125
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28683
2150
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28824
2175
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28971
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-20
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg)
CHAPTER 4
PERFORMANCE
5° FLAPS (cont’d)
PA (ft)
Sea Level
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
50
2200
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29131
2225
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29295)
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29471)
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-21
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
1000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
1000
22331
22026
21647
21265
20903
20564
20198
19459
18354
Min
Min
1025
22684
22369
22063
21685
21310
20959
20579
20163
19241
Min
Min
1050
23038
22713
22396
22081
21718
21353
20960
20528
20050
18644
Min
1075
23391
23056
22729
22405
22096
21748
21341
20894
20398
19423
18007
1100
23745
23399
23062
22728
22410
22110
21722
21259
20745
20084
18682
1125
24082
23743
23396
23051
22724
22414
22079
21624
21093
20408
19357
1150
24378
24072
23729
23375
23037
22719
22373
21990
21441
20732
20014
1175
24673
24359
24052
23698
23351
23024
22668
22275
21788
21057
20314
1200
24969
24646
24331
24018
23665
23328
22962
22559
22106
21381
20614
1225
25265
24933
24609
24288
23979
23633
23257
22842
22376
21706
20914
1250
25560
25220
24888
24558
24245
23937
23551
23125
22646
22024
21214
1275
25856
25507
25167
24829
24507
24202
23846
23408
22917
22277
21515
1300
26144
25794
25445
25099
24769
24456
24117
23692
23187
22530
21815
1325
26426
26077
25724
25369
25031
24711
24363
23975
23458
22784
22090
1350
26708
26350
26002
25640
25294
24965
24609
24216
23728
23037
22325
1375
26989
26623
26267
25910
25556
25220
24855
24452
23998
23290
22561
1400
27271
26896
26532
26171
25818
25474
25102
24689
24224
23544
22796
1425
27552
27170
26797
26427
26076
25729
25348
24926
24450
23797
23031
1450
27834
27443
27061
26684
26325
25984
25594
25162
24676
24042
23267
1475
28116
27716
27326
26940
26573
26225
25840
25399
24902
24253
23502
1500
28397
27989
27591
27197
26822
26466
26081
25636
25128
24465
23737
1525
28679
28262
27855
27453
27070
26707
26314
25872
25354
24677
23973
1550
28898
28535
28120
27710
27319
26947
26546
26103
25580
24888
24174
1575
29137
28781
28385
27966
27567
27188
26779
26326
25806
25100
24370
1600
(29393)
28999
28650
28223
27816
27429
27011
26549
26030
25311
24567
1625
Max
29231
28862
28479
28064
27670
27243
26772
26242
25523
24763
1650
Max
(29489)
29081
28725
28313
27911
27476
26995
26455
25735
24960
1675
Max
Max
(29312)
28921
28561
28151
27708
27219
26667
25946
25156
1700
Max
Max
(29564)
29139
28781
28392
27941
27442
26880
26148
25353
1725
Max
Max
Max
(29367)
28977
28633
28173
27665
27092
26346
25549
1750
Max
Max
Max
Max
29187
28830
28406
27888
27305
26545
25746
1775
Max
Max
Max
Max
(29413)
29024
28638
28111
27517
26743
25942
1800
Max
Max
Max
Max
Max
29227
28827
28334
27729
26942
26130
1825
Max
Max
Max
Max
Max
(29451)
29013
28557
27942
27140
26313
1850
Max
Max
Max
Max
Max
Max
29210
28759
28154
27339
26497
1875
Max
Max
Max
Max
Max
Max
(29423)
28929
28367
27537
26681
1900
Max
Max
Max
Max
Max
Max
Max
29117
28579
27735
26864
1925
Max
Max
Max
Max
Max
Max
Max
(29312)
28767
27934
27048
1950
Max
Max
Max
Max
Max
Max
Max
(29521)
28929
28132
27232
1975
Max
Max
Max
Max
Max
Max
Max
Max
29109
28331
27415
2000
Max
Max
Max
Max
Max
Max
Max
Max
(29293)
28529
27599
2025
Max
Max
Max
Max
Max
Max
Max
Max
(29493)
28718
27783
2050
Max
Max
Max
Max
Max
Max
Max
Max
Max
28868
27966
2075
Max
Max
Max
Max
Max
Max
Max
Max
Max
29030
28150
2100
Max
Max
Max
Max
Max
Max
Max
Max
Max
29200
28334
2125
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29381)
28517
2150
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29568)
28698
2175
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28836
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-22
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
1000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
2200
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28982
2225
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29141
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29304)
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29477)
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-23
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
2000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
1000
21652
21266
20890
20534
20198
19684
18715
Min
Min
Min
Min
1025
22066
21686
21296
20928
20579
20251
19631
18691
Min
Min
Min
1050
22400
22082
21703
21321
20960
20620
20211
19537
18199
Min
Min
1075
22733
22405
22085
21715
21341
20989
20565
20153
18943
Min
Min
1100
23066
22729
22398
22084
21721
21358
20918
20492
19687
18381
Min
1125
23400
23052
22712
22387
22079
21727
21272
20831
20183
19034
Min
1150
23733
23376
23025
22691
22373
22074
21626
21170
20500
19687
18243
1175
24056
23699
23338
22995
22668
22359
21980
21509
20816
20153
18801
1200
24334
24019
23652
23298
22962
22645
22259
21848
21133
20448
19359
1225
24613
24289
23965
23602
23257
22931
22533
22145
21450
20742
19918
1250
24892
24559
24233
23906
23551
23217
22808
22409
21766
21037
20229
1275
25171
24829
24495
24175
23846
23502
23083
22673
22065
21332
20499
1300
25449
25100
24757
24429
24117
23788
23358
22937
22312
21626
20768
1325
25728
25370
25019
24683
24363
24062
23632
23201
22560
21921
21037
1350
26007
25640
25281
24936
24609
24300
23907
23465
22807
22169
21306
1375
26271
25911
25543
25190
24855
24539
24152
23729
23055
22400
21576
1400
26536
26172
25805
25444
25101
24778
24381
23993
23303
22632
21845
1425
26801
26428
26063
25698
25348
25017
24611
24215
23550
22863
22090
1450
27066
26685
26311
25952
25594
25255
24840
24435
23798
23094
22302
1475
27331
26941
26560
26195
25840
25494
25070
24656
24038
23326
22515
1500
27595
27198
26808
26435
26081
25733
25299
24877
24245
23557
22727
1525
27860
27454
27056
26675
26313
25972
25529
25097
24451
23788
22940
1550
28125
27711
27304
26915
26546
26198
25759
25318
24658
24016
23152
1575
28390
27967
27552
27155
26778
26424
25988
25538
24865
24209
23365
1600
28655
28223
27800
27395
27011
26649
26205
25759
25072
24403
23577
1625
28866
28480
28049
27635
27243
26874
26421
25979
25278
24596
23790
1650
29085
28725
28297
27875
27476
27099
26637
26188
25485
24789
24002
1675
(29317)
28922
28545
28115
27708
27324
26853
26395
25692
24982
24179
1700
(29569)
29139
28769
28355
27940
27550
27069
26602
25899
25175
24356
1725
Max
(29368)
28963
28595
28173
27775
27285
26809
26099
25368
24534
1750
Max
Max
29172
28801
28405
28000
27501
27017
26293
25561
24711
1775
Max
Max
(29397)
28991
28638
28225
27717
27224
26486
25754
24888
1800
Max
Max
Max
29194
28827
28450
27933
27431
26680
25948
25066
1825
Max
Max
Max
(29413)
29013
28675
28150
27638
26874
26131
25243
1850
Max
Max
Max
Max
29209
28850
28366
27845
27067
26312
25420
1875
Max
Max
Max
Max
(29423)
29032
28582
28053
27261
26492
25598
1900
Max
Max
Max
Max
Max
29222
28771
28260
27455
26672
25775
1925
Max
Max
Max
Max
Max
(29430)
28937
28467
27648
26853
25952
1950
Max
Max
Max
Max
Max
Max
29120
28674
27842
27033
26121
1975
Max
Max
Max
Max
Max
Max
(29308)
28835
28036
27213
26285
2000
Max
Max
Max
Max
Max
Max
(29511)
29000
28229
27394
26450
2025
Max
Max
Max
Max
Max
Max
Max
29176
28423
27574
26615
2050
Max
Max
Max
Max
Max
Max
Max
(29362)
28617
27754
26780
2075
Max
Max
Max
Max
Max
Max
Max
(29557)
28780
27935
26945
2100
Max
Max
Max
Max
Max
Max
Max
Max
28927
28115
27110
2125
Max
Max
Max
Max
Max
Max
Max
Max
29093
28295
27275
2150
Max
Max
Max
Max
Max
Max
Max
Max
(29260)
28476
27440
2175
Max
Max
Max
Max
Max
Max
Max
Max
(29442)
28656
27605
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-24
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
2000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
2200
Max
Max
Max
Max
Max
Max
Max
Max
Max
28799
27770
2225
Max
Max
Max
Max
Max
Max
Max
Max
Max
28937
27935
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
29094
28100
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
29250
28264
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29421)
28429
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28594
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28742
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28865
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29001
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29147
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29295)
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29453)
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-25
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
3000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
1000
21285
20893
20526
20176
19593
18808
18105
Min
Min
Min
Min
1025
21707
21300
20919
20556
20216
19731
18971
18306
Min
Min
Min
1050
22098
21707
21312
20936
20583
20252
19838
19121
Min
Min
Min
1075
22422
22087
21705
21316
20951
20607
20279
19936
18522
Min
Min
1100
22746
22401
22076
21696
21318
20962
20622
20306
19236
Min
Min
1125
23070
22715
22379
22058
21686
21317
20966
20639
19949
18581
Min
1150
23394
23028
22683
22352
22041
21672
21309
20971
20287
19203
18034
1175
23718
23342
22986
22646
22326
22021
21653
21304
20597
19825
18578
1200
24035
23655
23290
22940
22610
22297
21996
21636
20907
20206
19122
1225
24305
23969
23593
23234
22895
22573
22264
21968
21216
20493
19666
1250
24576
24236
23897
23528
23180
22849
22532
22235
21526
20779
20102
1275
24847
24498
24167
23822
23465
23125
22799
22494
21835
21066
20367
1300
25118
24760
24421
24096
23749
23400
23066
22753
22113
21353
20632
1325
25388
25022
24675
24342
24028
23676
23333
23012
22355
21639
20897
1350
25659
25284
24928
24588
24266
23952
23601
23271
22598
21926
21163
1375
25930
25546
25182
24833
24504
24190
23868
23530
22840
22167
21428
1400
26190
25808
25435
25079
24742
24421
24113
23790
23082
22393
21693
1425
26447
26066
25689
25324
24980
24651
24336
24041
23325
22618
21958
1450
26704
26315
25943
25570
25218
24882
24560
24257
23567
22843
22176
1475
26961
26563
26186
25816
25456
25112
24783
24474
23809
23069
22386
1500
27218
26811
26426
26058
25694
25342
25006
24690
24043
23294
22595
1525
27475
27059
26666
26290
25932
25573
25229
24907
24245
23520
22804
1550
27732
27308
26905
26522
26160
25803
25453
25123
24448
23745
23014
1575
27989
27556
27145
26753
26384
26032
25676
25340
24650
23970
23223
1600
28245
27804
27385
26985
26609
26249
25899
25556
24853
24163
23433
1625
28502
28052
27625
27217
26833
26466
26115
25773
25055
24352
23642
1650
28743
28301
27865
27449
27058
26683
26325
25990
25257
24540
23851
1675
28942
28549
28105
27681
27282
26900
26535
26193
25460
24728
24051
1700
29159
28772
28345
27913
27506
27117
26745
26397
25662
24916
24225
1725
(29391)
28966
28585
28145
27731
27334
26955
26600
25864
25104
24400
1750
Max
29176
28792
28377
27955
27551
27165
26803
26062
25293
24575
1775
Max
(29401)
28982
28609
28179
27768
27375
27007
26252
25481
24750
1800
Max
Max
29184
28805
28404
27985
27585
27210
26441
25669
24924
1825
Max
Max
(29402)
28988
28628
28202
27795
27413
26631
25857
25099
1850
Max
Max
Max
29184
28813
28419
28005
27616
26820
26042
25274
1875
Max
Max
Max
(29394)
28991
28636
28215
27820
27009
26218
25449
1900
Max
Max
Max
Max
29180
28813
28425
28023
27199
26393
25623
1925
Max
Max
Max
Max
(29383)
28984
28634
28226
27388
26569
25798
1950
Max
Max
Max
Max
Max
29168
28807
28430
27577
26744
25973
1975
Max
Max
Max
Max
Max
(29362)
28971
28633
27767
26920
26137
2000
Max
Max
Max
Max
Max
(29566)
29149
28800
27956
27095
26300
2025
Max
Max
Max
Max
Max
Max
(29335)
28958
28145
27271
26462
2050
Max
Max
Max
Max
Max
Max
(29532)
29131
28335
27446
26625
2075
Max
Max
Max
Max
Max
Max
Max
(29309)
28524
27622
26787
2100
Max
Max
Max
Max
Max
Max
Max
(29500)
28708
27797
26949
2125
Max
Max
Max
Max
Max
Max
Max
Max
28850
27973
27112
2150
Max
Max
Max
Max
Max
Max
Max
Max
29003
28148
27274
2175
Max
Max
Max
Max
Max
Max
Max
Max
29166
28324
27437
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-26
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
3000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
2200
Max
Max
Max
Max
Max
Max
Max
Max
(29335)
28499
27599
2225
Max
Max
Max
Max
Max
Max
Max
Max
(29514)
28675
27761
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
28810
27924
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
28945
28086
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
29098
28249
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
29251
28411
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29417)
28574
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28724
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28845
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28976
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29120
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29265)
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29421)
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-27
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
4000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
1000
20536
20177
19560
18742
18019
Min
Min
Min
Min
Min
Min
1025
20930
20557
20203
19660
18878
18197
Min
Min
Min
Min
Min
1050
21323
20937
20570
20223
19737
19002
18353
Min
Min
Min
Min
1075
21717
21317
20936
20577
20237
19808
19109
18101
Min
Min
Min
1100
22085
21697
21303
20931
20579
20252
19865
18783
Min
Min
Min
1125
22389
22059
21670
21285
20921
20582
20262
19466
18179
Min
Min
1150
22693
22353
22029
21639
21263
20913
20582
20065
18774
Min
Min
1175
22996
22647
22313
21994
21605
21243
20901
20367
19369
18241
Min
1200
23300
22941
22597
22270
21947
21574
21220
20669
19964
18764
Min
1225
23604
23235
22882
22545
22225
21904
21540
20971
20262
19286
18136
1250
23908
23529
23166
22820
22491
22183
21859
21273
20542
19808
18588
1275
24177
23822
23451
23095
22757
22441
22139
21575
20821
20163
19039
1300
24431
24097
23735
23370
23024
22699
22389
21877
21100
20422
19491
1325
24684
24343
24016
23645
23290
22956
22639
22140
21380
20681
19942
1350
24938
24588
24254
23920
23556
23214
22888
22377
21659
20940
20206
1375
25192
24834
24491
24163
23822
23472
23138
22613
21938
21198
20443
1400
25446
25080
24729
24393
24074
23730
23387
22850
22171
21457
20680
1425
25700
25325
24967
24623
24296
23987
23637
23087
22391
21716
20917
1450
25954
25571
25204
24852
24518
24205
23887
23324
22611
21975
21154
1475
26196
25816
25442
25082
24741
24420
24114
23560
22831
22185
21391
1500
26437
26058
25679
25312
24963
24635
24322
23797
23051
22389
21628
1525
26677
26290
25917
25542
25186
24851
24531
24028
23271
22594
21866
1550
26917
26522
26146
25772
25408
25066
24739
24226
23491
22798
22081
1575
27157
26754
26370
26001
25630
25281
24948
24423
23711
23003
22270
1600
27397
26986
26594
26218
25853
25497
25156
24621
23931
23208
22458
1625
27637
27218
26818
26434
26071
25712
25365
24819
24126
23412
22646
1650
27877
27450
27042
26650
26280
25927
25573
25016
24309
23617
22835
1675
28117
27682
27266
26867
26489
26134
25782
25214
24493
23822
23023
1700
28358
27914
27490
27083
26698
26336
25990
25412
24677
24022
23211
1725
28598
28146
27714
27299
26907
26538
26186
25609
24860
24193
23400
1750
28803
28378
27938
27516
27116
26740
26381
25807
25044
24363
23588
1775
28993
28610
28162
27732
27325
26942
26577
26004
25228
24534
23776
1800
29196
28805
28386
27948
27534
27144
26772
26189
25411
24705
23965
1825
(29415)
28989
28610
28165
27743
27346
26967
26374
25595
24876
24128
1850
Max
29185
28799
28381
27952
27548
27163
26558
25778
25046
24285
1875
Max
(29395)
28975
28597
28161
27751
27358
26743
25962
25217
24442
1900
Max
Max
29165
28784
28370
27953
27553
26928
26136
25388
24599
1925
Max
Max
(29365)
28951
28579
28155
27749
27113
26307
25559
24756
1950
Max
Max
Max
29134
28764
28357
27944
27297
26478
25730
24913
1975
Max
Max
Max
(29324)
28923
28559
28140
27482
26649
25900
25070
2000
Max
Max
Max
(29527)
29100
28743
28335
27667
26820
26066
25227
2025
Max
Max
Max
Max
(29280)
28896
28530
27852
26991
26225
25384
2050
Max
Max
Max
Max
(29476)
29065
28717
28036
27162
26383
25542
2075
Max
Max
Max
Max
Max
29237
28864
28221
27333
26542
25699
2100
Max
Max
Max
Max
Max
(29425)
29023
28406
27504
26700
25856
2125
Max
Max
Max
Max
Max
Max
29191
28591
27675
26859
26012
2150
Max
Max
Max
Max
Max
Max
(29368)
28754
27846
27017
26157
2175
Max
Max
Max
Max
Max
Max
(29552)
28892
28017
27176
26302
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-28
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
4000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
2200
Max
Max
Max
Max
Max
Max
Max
29048
28188
27334
26448
2225
Max
Max
Max
Max
Max
Max
Max
29208
28359
27493
26593
2250
Max
Max
Max
Max
Max
Max
Max
(29378)
28530
27651
26738
2275
Max
Max
Max
Max
Max
Max
Max
(29553)
28698
27810
26884
2300
Max
Max
Max
Max
Max
Max
Max
Max
28826
27969
27029
2325
Max
Max
Max
Max
Max
Max
Max
Max
28960
28127
27174
2350
Max
Max
Max
Max
Max
Max
Max
Max
29110
28286
27320
2375
Max
Max
Max
Max
Max
Max
Max
Max
(29260)
28444
27465
2400
Max
Max
Max
Max
Max
Max
Max
Max
(29423)
28603
27610
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
28743
27756
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
28861
27901
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
28992
28046
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
29133
28192
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29276)
28337
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29429)
28482
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28628
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-29
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
5000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
40
1000
20190
19567
18727
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
20570
20206
19644
18837
18139
Min
Min
Min
Min
Min
Min
Min
1050
20951
20573
20216
19693
18940
18266
Min
Min
Min
Min
Min
Min
1075
21331
20940
20570
20219
19741
19015
18372
Min
Min
Min
Min
Min
1100
21711
21307
20924
20560
20223
19764
19075
18192
Min
Min
Min
Min
1125
22071
21674
21278
20901
20552
20217
19778
18831
Min
Min
Min
Min
1150
22365
22031
21632
21243
20882
20535
20210
19471
18389
Min
Min
Min
1175
22659
22316
21985
21584
21211
20853
20517
20050
18957
Min
Min
Min
1200
22954
22600
22263
21925
21541
21171
20824
20341
19526
18379
Min
Min
1225
23248
22885
22538
22207
21870
21489
21131
20632
20045
18876
Min
Min
1250
23542
23169
22813
22473
22156
21807
21438
20923
20317
19373
18388
Min
1275
23836
23454
23088
22739
22413
22097
21745
21214
20589
19871
18827
Min
1300
24109
23738
23363
23005
22670
22346
22040
21505
20861
20186
19266
18170
1325
24355
24019
23638
23270
22927
22594
22281
21797
21133
20437
19704
18546
1350
24601
24256
23912
23536
23184
22843
22521
22069
21405
20689
20076
18921
1375
24847
24494
24156
23802
23441
23091
22762
22297
21677
20940
20309
19297
1400
25093
24732
24386
24056
23698
23340
23002
22526
21950
21191
20542
19672
1425
25339
24969
24616
24278
23955
23588
23242
22755
22175
21443
20775
20027
1450
25584
25207
24845
24500
24177
23836
23483
22984
22389
21694
21008
20238
1475
25830
25445
25075
24722
24391
24071
23723
23212
22604
21945
21241
20449
1500
26072
25683
25305
24944
24606
24278
23964
23441
22818
22156
21474
20661
1525
26304
25920
25534
25166
24821
24486
24170
23670
23033
22355
21707
20872
1550
26536
26149
25764
25388
25035
24693
24371
23898
23247
22554
21940
21083
1575
26769
26373
25994
25610
25250
24901
24572
24106
23462
22753
22137
21295
1600
27001
26597
26210
25832
25465
25108
24772
24297
23677
22952
22323
21506
1625
27233
26821
26426
26051
25679
25316
24973
24488
23891
23151
22508
21718
1650
27465
27045
26643
26259
25894
25523
25174
24679
24088
23351
22693
21929
1675
27698
27270
26859
26468
26102
25731
25375
24870
24267
23550
22878
22112
1700
27930
27494
27075
26677
26304
25938
25576
25061
24446
23749
23064
22281
1725
28162
27718
27291
26885
26505
26137
25776
25252
24625
23948
23249
22450
1750
28394
27942
27507
27094
26706
26331
25977
25443
24805
24123
23434
22619
1775
28627
28166
27724
27303
26908
26526
26166
25634
24984
24289
23620
22788
1800
28818
28390
27940
27511
27109
26720
26354
25825
25163
24455
23805
22957
1825
29003
28614
28156
27720
27311
26914
26542
26014
25342
24621
23990
23126
1850
29199
28802
28372
27928
27512
27109
26730
26193
25521
24787
24146
23295
1875
(29411) 28979
28588
28137
27714
27303
26917
26371
25700
24953
24301
23464
1900
(Max)
29168
28777
28346
27915
27498
27105
26549
25879
25119
24455
23633
1925
(Max) (29369) 28943
28554
28117
27692
27293
26727
26054
25286
24610
23802
1950
(Max)
Max
29126
28745
28318
27886
27481
26905
26221
25452
24765
23971
1975
(Max)
Max
(29315) 28903
28520
28081
27669
27084
26387
25618
24919
24117
2000
Max
Max
(29518) 29078
28713
28275
27856
27262
26554
25784
25074
24258
2025
Max
Max
Max
29255
28865
28470
28044
27440
26721
25950
25228
24399
2050
Max
Max
Max
(29451) 29030
28664
28232
27618
26887
26108
25383
24540
2075
Max
Max
Max
Max
29202
28817
28420
27796
27054
26262
25537
24681
2100
Max
Max
Max
Max
(29386) 28969
28608
27975
27221
26416
25692
24821
2125
Max
Max
Max
Max
Max
29136
28769
28153
27387
26570
25846
24962
2150
Max
Max
Max
Max
Max
(29307) 28910
28331
27554
26724
26001
25103
2175
Max
Max
Max
Max
Max
(29490) 29071
28509
27720
26878
26144
25244
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-30
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
5000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
2200
Max
Max
Max
Max
Max
Max
29232
28687
27887
27032
26287
2225
Max
Max
Max
Max
Max
Max
(29407) 28821
28054
27186
26429
2250
Max
Max
Max
Max
Max
Max
Max
28961
28220
27340
26572
2275
Max
Max
Max
Max
Max
Max
Max
29116
28387
27494
26715
2300
Max
Max
Max
Max
Max
Max
Max
(29272) 28554
27648
26858
2325
Max
Max
Max
Max
Max
Max
Max
(29441) 28713
27802
27001
2350
Max
Max
Max
Max
Max
Max
Max
Max
28837
27956
27144
2375
Max
Max
Max
Max
Max
Max
Max
Max
28969
28110
27287
2400
Max
Max
Max
Max
Max
Max
Max
Max
29116
28264
27429
2425
Max
Max
Max
Max
Max
Max
Max
Max
(29264) 28418
27572
2450
Max
Max
Max
Max
Max
Max
Max
Max
(29423) 28573
27715
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
28717
27858
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
28832
28001
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
28952
28144
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
29091
28287
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
29230
28429
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29377) 28572
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29526)
MAT
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
40
25385
25526
25667
25808
25949
26082
26212
26342
26471
26601
26731
26860
26990
27120
27250
27379
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
MAT
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-31
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
6000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
1000
18764
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
19684
18845
18113
Min
Min
Min
Min
Min
Min
Min
Min
1050
20232
19702
18912
18214
Min
Min
Min
Min
Min
Min
Min
1075
20587
20222
19711
18959
18284
Min
Min
Min
Min
Min
Min
1100
20941
20564
20210
19704
18981
18342
Min
Min
Min
Min
Min
1125
21296
20905
20539
20191
19678
18993
18211
Min
Min
Min
Min
1150
21650
21247
20868
20508
20164
19643
18809
Min
Min
Min
Min
1175
22004
21588
21197
20825
20470
20133
19406
18406
Min
Min
Min
1200
22279
21930
21526
21142
20775
20426
20001
18939
18027
Min
Min
1225
22554
22211
21855
21459
21080
20720
20281
19472
18501
Min
Min
1250
22829
22477
22143
21776
21386
21014
20561
20002
18975
18043
Min
1275
23105
22743
22400
22072
21691
21308
20841
20264
19449
18460
Min
1300
23380
23008
22657
22320
21997
21602
21121
20526
19923
18877
Min
1325
23655
23274
22913
22568
22236
21896
21401
20788
20204
19294
18350
1350
23931
23540
23170
22816
22476
22149
21681
21050
20448
19711
18715
1375
24172
23806
23426
23063
22715
22380
21961
21311
20693
20069
19079
1400
24402
24060
23683
23311
22954
22611
22189
21573
20937
20295
19443
1425
24632
24282
23940
23559
23193
22841
22410
21835
21181
20520
19807
1450
24862
24504
24164
23807
23433
23072
22630
22077
21425
20746
20097
1475
25092
24726
24378
24045
23672
23303
22851
22284
21669
20972
20305
1500
25322
24948
24593
24252
23911
23534
23071
22491
21914
21198
20512
1525
25552
25170
24807
24459
24126
23765
23291
22698
22125
21423
20719
1550
25782
25392
25022
24666
24325
23995
23512
22905
22319
21649
20927
1575
26011
25614
25236
24873
24525
24189
23732
23112
22513
21875
21134
1600
26228
25836
25450
25080
24725
24381
23953
23319
22706
22080
21341
1625
26444
26055
25665
25287
24925
24574
24144
23526
22900
22260
21549
1650
26661
26263
25879
25494
25125
24767
24328
23733
23094
22440
21756
1675
26878
26472
26088
25701
25324
24960
24512
23940
23288
22620
21963
1700
27094
26681
26289
25908
25524
25152
24696
24122
23482
22800
22137
1725
27311
26890
26490
26108
25724
25345
24880
24295
23675
22979
22303
1750
27527
27098
26691
26302
25924
25538
25064
24468
23869
23159
22469
1775
27744
27307
26893
26495
26116
25730
25248
24641
24052
23339
22635
1800
27960
27516
27094
26689
26302
25923
25432
24813
24214
23519
22800
1825
28177
27724
27295
26883
26489
26108
25616
24986
24376
23699
22966
1850
28393
27933
27496
27077
26676
26288
25800
25159
24537
23879
23132
1875
28610
28142
27697
27271
26863
26468
25984
25331
24699
24049
23298
1900
28793
28351
27898
27465
27050
26648
26157
25504
24860
24199
23464
1925
28962
28559
28100
27659
27237
26828
26328
25677
25022
24349
23630
1950
29145
28749
28301
27852
27424
27008
26500
25850
25184
24499
23796
1975
(29337)
28906
28502
28046
27610
27187
26671
26021
25345
24649
23962
2000
(29540)
29082
28700
28240
27797
27367
26842
26181
25507
24799
24107
2025
Max
(29260)
28851
28434
27984
27547
27014
26342
25669
24949
24245
2050
Max
(29456)
29014
28628
28171
27727
27185
26502
25830
25099
24383
2075
Max
Max
29186
28789
28358
27907
27357
26663
25992
25249
24522
2100
Max
Max
(29368)
28937
28545
28087
27528
26823
26142
25399
24660
2125
Max
Max
(29557)
29103
28721
28267
27699
26984
26292
25549
24798
2150
Max
Max
Max
(29271)
28861
28447
27871
27144
26442
25699
24937
2175
Max
Max
Max
(29454)
29014
28627
28042
27304
26591
25849
25075
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-32
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
6000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
2200
Max
Max
Max
Max
29175
28777
28214
27465
26741
25999
25213
2225
Max
Max
Max
Max
(29344)
28912
28385
27625
26891
26137
25352
2250
Max
Max
Max
Max
(29520)
29067
28556
27786
27040
26276
25490
2275
Max
Max
Max
Max
Max
29223
28718
27946
27190
26414
25628
2300
Max
Max
Max
Max
Max
(29391)
28846
28107
27340
26552
25766
2325
Max
Max
Max
Max
Max
(29562)
28984
28267
27490
26691
25905
2350
Max
Max
Max
Max
Max
Max
29134
28428
27639
26829
26040
2375
Max
Max
Max
Max
Max
Max
(29287)
28588
27789
26968
26167
2400
Max
Max
Max
Max
Max
Max
(29450)
28734
27939
27106
26294
2425
Max
Max
Max
Max
Max
Max
Max
28853
28088
27245
26421
2450
Max
Max
Max
Max
Max
Max
Max
28984
28238
27383
26549
2475
Max
Max
Max
Max
Max
Max
Max
29126
28388
27522
26676
2500
Max
Max
Max
Max
Max
Max
Max
(29270)
28537
27660
26803
2525
Max
Max
Max
Max
Max
Max
Max
(29424)
28687
27798
26930
2550
Max
Max
Max
Max
Max
Max
Max
Max
28799
27937
27057
2575
Max
Max
Max
Max
Max
Max
Max
Max
28910
28075
27185
2600
Max
Max
Max
Max
Max
Max
Max
Max
29045
28214
27312
2625
Max
Max
Max
Max
Max
Max
Max
Max
29181
28352
MAT
2650
Max
Max
Max
Max
Max
Max
Max
Max
(29321)
28491
MAT
2675
Max
Max
Max
Max
Max
Max
Max
Max
(29466)
28629
MAT
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
28747
MAT
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
28850
MAT
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
28961
MAT
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-33
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
7000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
1000
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
18131
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1050
18931
18214
Min
Min
Min
Min
Min
Min
Min
Min
Min
1075
19732
18959
18269
Min
Min
Min
Min
Min
Min
Min
Min
1100
20219
19705
18965
18325
Min
Min
Min
Min
Min
Min
Min
1125
20548
20191
19660
18974
18375
Min
Min
Min
Min
Min
Min
1150
20877
20508
20156
19623
18984
18275
Min
Min
Min
Min
Min
1175
21207
20825
20461
20123
19592
18836
Min
Min
Min
Min
Min
1200
21536
21142
20766
20417
20093
19396
18447
Min
Min
Min
Min
1225
21865
21459
21071
20710
20376
19957
18949
18110
Min
Min
Min
1250
22152
21776
21376
21004
20659
20249
19451
18559
Min
Min
Min
1275
22409
22072
21681
21297
20942
20519
19953
19009
18124
Min
Min
1300
22666
22320
21987
21591
21225
20789
20229
19459
18521
Min
Min
1325
22922
22568
22228
21885
21508
21059
20481
19908
18918
18120
Min
1350
23179
22816
22467
22140
21791
21328
20734
20188
19314
18470
Min
1375
23436
23064
22707
22370
22058
21598
20987
20425
19711
18821
Min
1400
23693
23311
22946
22601
22281
21868
21240
20661
20059
19172
18286
1425
23950
23559
23185
22831
22503
22109
21492
20897
20278
19522
18589
1450
24173
23807
23424
23062
22726
22322
21745
21134
20497
19873
18892
1475
24387
24046
23663
23292
22948
22535
21998
21370
20716
20129
19195
1500
24602
24252
23902
23523
23171
22748
22198
21607
20935
20331
19498
1525
24817
24459
24117
23754
23394
22961
22399
21843
21153
20534
19802
1550
25031
24666
24317
23984
23616
23173
22599
22063
21372
20736
20063
1575
25246
24873
24517
24179
23839
23386
22799
22251
21591
20938
20248
1600
25460
25080
24716
24372
24051
23599
22999
22439
21810
21141
20432
1625
25675
25287
24916
24564
24237
23812
23199
22627
22023
21343
20616
1650
25890
25494
25116
24757
24423
24021
23399
22815
22198
21546
20800
1675
26098
25701
25315
24949
24609
24199
23599
23003
22372
21748
20984
1700
26299
25908
25515
25142
24795
24376
23800
23191
22547
21950
21168
1725
26500
26108
25714
25334
24981
24554
24000
23379
22722
22122
21352
1750
26702
26302
25914
25527
25167
24732
24167
23567
22896
22284
21536
1775
26903
26495
26106
25719
25353
24910
24334
23755
23071
22447
21720
1800
27105
26689
26293
25912
25538
25087
24501
23943
23245
22609
21904
1825
27306
26883
26480
26097
25724
25265
24668
24109
23420
22771
22071
1850
27507
27077
26666
26277
25910
25443
24835
24265
23595
22933
22220
1875
27709
27271
26853
26457
26090
25620
25002
24422
23769
23095
22368
1900
27910
27465
27040
26636
26263
25798
25169
24579
23944
23258
22516
1925
28111
27659
27226
26816
26436
25976
25335
24736
24099
23420
22664
1950
28313
27852
27413
26996
26609
26143
25502
24892
24245
23582
22813
1975
28514
28046
27600
27175
26782
26308
25669
25049
24390
23744
22961
2000
28709
28240
27786
27355
26956
26473
25836
25206
24536
23906
23109
2025
28861
28434
27973
27535
27129
26639
26003
25363
24681
24057
23258
2050
29025
28628
28160
27714
27302
26804
26158
25519
24827
24192
23406
2075
29197
28789
28346
27894
27475
26969
26313
25676
24973
24327
23554
2100
(29380)
28937
28533
28074
27649
27135
26468
25833
25118
24463
23703
2125
(29570)
29103
28712
28254
27822
27300
26623
25990
25264
24598
23851
2150
Max
(29271)
28852
28433
27995
27465
26778
26135
25409
24733
23999
2175
Max
(29454)
29004
28613
28168
27631
26932
26280
25555
24868
24123
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-34
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
7000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
2200
Max
Max
29164
28767
28342
27796
27087
26425
25701
25003
24246
2225
Max
Max
(29332)
28901
28515
27961
27242
26570
25846
25138
24370
2250
Max
Max
(29508)
29055
28688
28126
27397
26715
25992
25273
24493
2275
Max
Max
Max
29211
28818
28292
27552
26860
26127
25409
24617
2300
Max
Max
Max
(29377)
28953
28457
27707
27005
26261
25544
24740
2325
Max
Max
Max
(29548)
29104
28622
27862
27150
26395
25679
24864
2350
Max
Max
Max
Max
29256
28763
28017
27295
26530
25814
24987
2375
Max
Max
Max
Max
(29420)
28886
28171
27440
26664
25949
25111
2400
Max
Max
Max
Max
Max
29027
28326
27585
26798
26078
25234
2425
Max
Max
Max
Max
Max
29173
28481
27730
26932
26202
25358
2450
Max
Max
Max
Max
Max
(29324)
28636
27875
27066
26326
25481
2475
Max
Max
Max
Max
Max
(29482)
28765
28020
27201
26450
25605
2500
Max
Max
Max
Max
Max
Max
28880
28165
27335
26574
25728
2525
Max
Max
Max
Max
Max
Max
29012
28310
27469
26699
25852
2550
Max
Max
Max
Max
Max
Max
29151
28455
27603
26823
25975
2575
Max
Max
Max
Max
Max
Max
(29293)
28600
27738
26947
26091
2600
Max
Max
Max
Max
Max
Max
(29442)
28731
27872
27071
26204
2625
Max
Max
Max
Max
Max
Max
Max
28838
28006
27195
MAT
2650
Max
Max
Max
Max
Max
Max
Max
28953
28140
27320
MAT
2675
Max
Max
Max
Max
Max
Max
Max
29085
28275
27444
MAT
2700
Max
Max
Max
Max
Max
Max
Max
29218
28409
27568
MAT
2725
Max
Max
Max
Max
Max
Max
Max
(29357)
28543
27692
MAT
2750
Max
Max
Max
Max
Max
Max
Max
(29499)
28677
MAT
MAT
2775
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
2800
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
2825
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
2850
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
2875
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
2900
Max
Max
Max
Max
Max
Max
Max
Max
MAT
MAT
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-35
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
8000
OAT (°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
1000
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1050
18250
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1075
18997
18279
Min
Min
Min
Min
Min
Min
Min
Min
Min
1100
19745
18975
18315
Min
Min
Min
Min
Min
Min
Min
Min
1125
20209
19672
18963
18326
Min
Min
Min
Min
Min
Min
Min
1150
20527
20161
19612
18931
18346
Min
Min
Min
Min
Min
Min
1175
20844
20467
20117
19536
18912
18208
Min
Min
Min
Min
Min
1200
21162
20772
20411
20066
19478
18728
Min
Min
Min
Min
Min
1225
21480
21077
20704
20348
20020
19248
18469
Min
Min
Min
Min
1250
21797
21382
20998
20630
20292
19768
18942
18114
Min
Min
Min
1275
22090
21688
21291
20912
20563
20143
19414
18535
Min
Min
Min
1300
22338
21993
21585
21194
20834
20401
19886
18957
18203
Min
Min
1325
22586
22234
21878
21476
21106
20659
20184
19378
18580
Min
Min
1350
22834
22473
22134
21758
21377
20917
20428
19799
18958
18159
Min
1375
23082
22712
22365
22031
21648
21175
20672
20119
19335
18491
Min
1400
23331
22951
22595
22253
21919
21433
20915
20346
19712
18824
18108
1425
23579
23190
22826
22475
22150
21691
21159
20573
20050
19156
18402
1450
23827
23429
23056
22697
22364
21949
21403
20801
20262
19489
18695
1475
24063
23669
23286
22919
22578
22164
21646
21028
20475
19821
18988
1500
24270
23908
23517
23141
22792
22368
21890
21255
20687
20090
19281
1525
24478
24123
23747
23363
23006
22572
22106
21482
20899
20286
19574
1550
24685
24322
23978
23585
23220
22777
22299
21710
21111
20481
19867
1575
24892
24522
24174
23807
23434
22981
22492
21937
21323
20677
20098
1600
25100
24722
24366
24024
23648
23185
22686
22131
21535
20872
20278
1625
25307
24922
24558
24209
23862
23389
22879
22312
21747
21068
20459
1650
25514
25121
24751
24395
24063
23593
23072
22493
21959
21263
20639
1675
25722
25321
24943
24580
24242
23797
23266
22674
22137
21459
20819
1700
25929
25521
25136
24765
24420
24001
23459
22855
22306
21654
20999
1725
26128
25721
25328
24951
24599
24172
23652
23036
22476
21850
21179
1750
26322
25920
25520
25136
24778
24342
23846
23217
22645
22036
21359
1775
26516
26112
25713
25321
24956
24512
24032
23398
22815
22193
21539
1800
26710
26299
25905
25507
25135
24683
24194
23579
22985
22350
21719
1825
26905
26486
26091
25692
25313
24853
24355
23760
23154
22507
21899
1850
27099
26673
26271
25877
25492
25023
24516
23941
23324
22664
22064
1875
27293
26859
26450
26058
25670
25194
24677
24101
23493
22821
22209
1900
27487
27046
26630
26231
25849
25364
24839
24252
23663
22978
22354
1925
27682
27233
26809
26404
26026
25534
25000
24403
23832
23135
22499
1950
27876
27420
26989
26576
26192
25705
25161
24554
24001
23292
22644
1975
28070
27607
27168
26749
26358
25875
25322
24705
24143
23449
22790
2000
28264
27793
27348
26922
26524
26042
25484
24856
24284
23606
22935
2025
28459
27980
27528
27094
26690
26200
25645
25007
24426
23763
23080
2050
28653
28167
27707
27267
26856
26359
25806
25158
24567
23920
23225
2075
28808
28354
27887
27440
27023
26517
25967
25309
24708
24064
23370
2100
28959
28541
28066
27612
27189
26675
26119
25460
24850
24195
23516
2125
29126
28718
28246
27785
27355
26833
26268
25611
24991
24326
23661
2150
(29296)
28858
28426
27958
27521
26991
26418
25762
25132
24457
23806
2175
(29479)
29010
28605
28130
27687
27149
26567
25913
25274
24588
23951
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-36
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
8000
OAT (°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
2200
Max
29171
28761
28303
27853
27307
26716
26059
25415
24718
24080
2225
Max
(29339)
28895
28476
28019
27466
26866
26198
25556
24849
24201
2250
Max
(29516)
29048
28649
28185
27624
27015
26337
25698
24980
24322
2275
Max
Max
29204
28788
28352
27782
27164
26477
25839
25111
24443
2300
Max
Max
(29369)
28917
28518
27940
27314
26616
25980
25242
24564
2325
Max
Max
(29540)
29068
28684
28098
27463
26755
26112
25372
24685
2350
Max
Max
Max
29219
28809
28256
27612
26895
26242
25503
24806
2375
Max
Max
Max
(29380)
28936
28415
27762
27034
26372
25634
24927
2400
Max
Max
Max
(29545)
29083
28573
27911
27173
26502
25765
25048
2425
Max
Max
Max
Max
29230
28720
28060
27313
26632
25896
25169
2450
Max
Max
Max
Max
(29386)
28838
28210
27452
26763
26024
25289
2475
Max
Max
Max
Max
(29545)
28964
28359
27592
26893
26144
25410
2500
Max
Max
Max
Max
Max
29105
28508
27731
27023
26264
25531
2525
Max
Max
Max
Max
Max
29246
28658
27870
27153
26384
25652
2550
Max
Max
Max
Max
Max
(29398)
28777
28010
27283
26504
25773
2575
Max
Max
Max
Max
Max
(29550)
28888
28149
27413
26624
25894
2600
Max
Max
Max
Max
Max
Max
29017
28288
27543
26744
26014
2625
Max
Max
Max
Max
Max
Max
29153
28428
27673
26864
26124
2650
Max
Max
Max
Max
Max
Max
(29291)
28567
27804
26984
26235
2675
Max
Max
Max
Max
Max
Max
(29436)
28702
27934
27104
26345
2700
Max
Max
Max
Max
Max
Max
Max
28805
28064
27225
26456
2725
Max
Max
Max
Max
Max
Max
Max
28908
28194
27345
26567
2750
Max
Max
Max
Max
Max
Max
Max
29036
28324
27465
MAT
2775
Max
Max
Max
Max
Max
Max
Max
29166
28454
27585
MAT
2800
Max
Max
Max
Max
Max
Max
Max
(29297)
28584
MAT
MAT
2825
Max
Max
Max
Max
Max
Max
Max
(29434)
28708
MAT
MAT
2850
Max
Max
Max
Max
Max
Max
Max
(29571)
28804
MAT
MAT
2875
Max
Max
Max
Max
Max
Max
Max
Max
28900
MAT
MAT
2900
Max
Max
Max
Max
Max
Max
Max
Max
29000
MAT
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-37
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
9000
OAT (°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
1000
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1050
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1075
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1100
18330
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1125
18980
18329
Min
Min
Min
Min
Min
Min
Min
Min
Min
1150
19629
18934
18338
Min
Min
Min
Min
Min
Min
Min
Min
1175
20126
19540
18903
18319
Min
Min
Min
Min
Min
Min
Min
1200
20419
20067
19468
18846
18100
Min
Min
Min
Min
Min
Min
1225
20713
20349
20016
19373
18579
Min
Min
Min
Min
Min
Min
1250
21007
20632
20287
19900
19058
18377
Min
Min
Min
Min
Min
1275
21301
20914
20558
20211
19537
18815
18107
Min
Min
Min
Min
1300
21594
21196
20829
20471
20008
19253
18503
Min
Min
Min
Min
1325
21888
21478
21100
20731
20254
19692
18898
18190
Min
Min
Min
1350
22143
21760
21371
20991
20499
20069
19294
18545
Min
Min
Min
1375
22373
22033
21642
21252
20745
20301
19690
18900
18189
Min
Min
1400
22604
22255
21913
21512
20991
20534
20047
19255
18504
Min
Min
1425
22834
22477
22145
21772
21237
20767
20265
19610
18820
18145
Min
1450
23065
22699
22359
22026
21482
21000
20484
19965
19135
18424
Min
1475
23296
22921
22573
22231
21728
21233
20702
20184
19451
18702
18018
1500
23526
23143
22787
22437
21974
21465
20921
20388
19766
18981
18260
1525
23757
23365
23001
22643
22174
21698
21139
20592
20049
19260
18503
1550
23987
23587
23214
22849
22369
21931
21358
20796
20238
19539
18745
1575
24182
23809
23428
23054
22564
22130
21576
21000
20427
19818
18987
1600
24375
24026
23642
23260
22759
22315
21795
21204
20616
20060
19229
1625
24567
24211
23856
23466
22954
22500
22010
21408
20805
20235
19471
1650
24760
24397
24058
23672
23149
22685
22185
21612
20994
20409
19714
1675
24952
24582
24237
23877
23344
22871
22359
21815
21183
20583
19956
1700
25145
24767
24415
24069
23538
23056
22534
22015
21372
20757
20129
1725
25337
24953
24594
24241
23733
23241
22708
22179
21561
20931
20288
1750
25530
25138
24772
24413
23928
23426
22882
22342
21750
21105
20446
1775
25722
25323
24951
24584
24103
23611
23057
22506
21939
21280
20604
1800
25915
25509
25129
24756
24265
23796
23231
22669
22103
21454
20763
1825
26100
25694
25308
24928
24428
23981
23405
22832
22255
21628
20921
1850
26280
25879
25486
25099
24590
24139
23580
22996
22407
21802
21079
1875
26460
26060
25665
25271
24753
24293
23754
23159
22559
21976
21238
1900
26640
26233
25843
25443
24916
24448
23928
23323
22711
22122
21396
1925
26819
26406
26020
25615
25078
24602
24086
23486
22863
22262
21555
1950
26999
26578
26186
25786
25241
24756
24231
23649
23015
22403
21713
1975
27179
26751
26352
25958
25403
24911
24376
23813
23167
22544
21871
2000
27359
26924
26518
26120
25566
25065
24522
23976
23319
22684
22024
2025
27538
27097
26684
26280
25729
25220
24667
24116
23471
22825
22153
2050
27718
27269
26850
26439
25891
25374
24813
24252
23623
22966
22281
2075
27898
27442
27016
26599
26050
25528
24958
24389
23775
23107
22410
2100
28078
27615
27182
26758
26200
25683
25103
24525
23927
23247
22538
2125
28257
27788
27348
26918
26351
25837
25249
24661
24065
23388
22667
2150
28437
27960
27514
27077
26502
25992
25394
24797
24192
23529
22795
2175
28617
28133
27680
27236
26652
26135
25539
24933
24319
23669
22924
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-38
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
9000
OAT (°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
2200
28770
28306
27846
27396
26803
26278
25685
25069
24445
23810
23052
2225
28904
28478
28012
27555
26954
26420
25830
25205
24572
23951
23181
2250
29059
28651
28178
27715
27104
26563
25976
25342
24699
24076
23310
2275
29215
28790
28344
27874
27255
26706
26112
25478
24825
24193
23438
2300
(29381)
28920
28511
28034
27405
26849
26246
25614
24952
24310
23567
2325
(29552)
29071
28677
28193
27556
26991
26380
25750
25078
24428
23695
2350
Max
29222
28804
28353
27707
27134
26514
25886
25205
24545
23824
2375
Max
(29383)
28930
28512
27857
27277
26648
26021
25332
24662
23952
2400
Max
(29548)
29076
28672
28008
27419
26782
26146
25458
24779
24067
2425
Max
Max
29223
28795
28159
27562
26916
26271
25585
24896
24174
2450
Max
Max
(29379)
28914
28309
27705
27050
26396
25712
25013
24281
2475
Max
Max
(29538)
29055
28460
27848
27184
26521
25838
25130
24388
2500
Max
Max
Max
29197
28611
27990
27318
26646
25965
25248
24495
2525
Max
Max
Max
(29346)
28743
28133
27452
26772
26084
25365
24602
2550
Max
Max
Max
(29499)
28855
28276
27586
26897
26200
25482
24709
2575
Max
Max
Max
Max
28978
28418
27720
27022
26316
25599
24816
2600
Max
Max
Max
Max
29114
28561
27854
27147
26432
25716
24923
2625
Max
Max
Max
Max
29251
28700
27988
27272
26548
25833
25030
2650
Max
Max
Max
Max
(29396)
28806
28122
27397
26664
25951
25137
2675
Max
Max
Max
Max
(29542)
28912
28256
27523
26780
26062
25244
2700
Max
Max
Max
Max
Max
29042
28390
27648
26896
26169
25351
2725
Max
Max
Max
Max
Max
29174
28524
27773
27012
26276
25458
2750
Max
Max
Max
Max
Max
(29308)
28658
27898
27128
26383
MAT
2775
Max
Max
Max
Max
Max
(29448)
28765
28023
27244
MAT
MAT
2800
Max
Max
Max
Max
Max
Max
28864
28148
27360
MAT
MAT
2825
Max
Max
Max
Max
Max
Max
28976
28274
27476
MAT
MAT
2850
Max
Max
Max
Max
Max
Max
29102
28399
27592
MAT
MAT
2875
Max
Max
Max
Max
Max
Max
29229
28524
27708
MAT
MAT
2900
Max
Max
Max
Max
Max
Max
(29360)
28649
MAT
MAT
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-39
[Rev. X] 31 MAY 2011
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
PA (ft)
10000
OAT (°C)
-25
-20
-15
-10
-5
0
5
10
15
20
25
30
1000
< Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1025
< Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1050
< Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1075
< Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1100
< Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1125
18343
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1150
18949
18316
Min
Min
Min
Min
Min
Min
Min
Min
Min
Min
1175
19555
18880
18275
Min
Min
Min
Min
Min
Min
Min
Min
Min
1200
20075
19443
18800
18205
Min
Min
Min
Min
Min
Min
Min
Min
1225
20357
20003
19324
18690
Min
Min
Min
Min
Min
Min
Min
Min
1250
20640
20274
19848
19176
18438
Min
Min
Min
Min
Min
Min
Min
1275
20922
20544
20184
19662
18880
18218
Min
Min
Min
Min
Min
Min
1300
21204
20815
20444
20075
19322
18621
18044
Min
Min
Min
Min
Min
1325
21487
21086
20703
20323
19764
19023
18412
Min
Min
Min
Min
Min
1350
21769
21356
20962
20571
20109
19425
18780
18106
Min
Min
Min
Min
1375
22040
21627
21222
20819
20343
19828
19147
18436
Min
Min
Min
Min
1400
22263
21898
21481
21067
20577
20126
19515
18765
18171
Min
Min
Min
1425
22485
22133
21741
21315
20811
20347
19883
19094
18468
Min
Min
Min
1450
22707
22346
22000
21562
21045
20568
20142
19424
18764
18093
Min
Min
1475
22929
22560
22205
21810
21279
20789
20351
19753
19061
18354
Min
Min
1500
23151
22773
22410
22046
21513
21009
20559
20049
19358
18614
18050
Min
1525
23374
22987
22615
22242
21747
21230
20768
20243
19655
18875
18281
Min
1550
23596
23200
22820
22439
21981
21451
20976
20437
19951
19136
18512
Min
1575
23818
23414
23026
22635
22171
21672
21185
20632
20152
19397
18742
18086
1600
24034
23627
23231
22832
22357
21893
21394
20826
20333
19657
18973
18283
1625
24219
23841
23436
23028
22543
22090
21602
21020
20515
19918
19204
18481
1650
24405
24045
23641
23225
22729
22267
21811
21215
20696
20114
19434
18678
1675
24590
24224
23846
23421
22915
22443
22016
21409
20878
20281
19665
18875
1700
24776
24402
24043
23618
23101
22619
22182
21603
21059
20447
19896
19073
1725
24961
24580
24214
23814
23287
22795
22349
21798
21241
20614
20084
19270
1750
25147
24758
24385
24009
23473
22971
22516
21992
21422
20780
20237
19467
1775
25332
24936
24556
24173
23659
23147
22683
22150
21603
20947
20390
19665
1800
25518
25115
24727
24337
23845
23323
22850
22306
21785
21113
20543
19862
1825
25703
25293
24899
24501
24026
23500
23017
22462
21966
21280
20697
20041
1850
25889
25471
25070
24665
24181
23676
23184
22618
22119
21446
20850
20179
1875
26069
25649
25241
24829
24336
23852
23351
22774
22266
21613
21003
20316
1900
26242
25828
25412
24993
24491
24023
23518
22930
22412
21779
21156
20454
1925
26415
26005
25583
25157
24647
24170
23685
23086
22558
21946
21309
20591
1950
26588
26171
25754
25321
24802
24317
23852
23242
22704
22091
21463
20729
1975
26761
26337
25926
25484
24957
24464
24015
23398
22851
22226
21616
20866
2000
26933
26503
26090
25648
25112
24611
24155
23554
22997
22360
21769
21003
2025
27106
26668
26249
25812
25267
24758
24294
23711
23143
22495
21922
21141
2050
27279
26834
26408
25976
25423
24904
24433
23867
23290
22630
22061
21278
2075
27452
27000
26567
26130
25578
25051
24572
24019
23436
22765
22186
21416
2100
27625
27166
26726
26282
25733
25198
24711
24149
23582
22900
22310
21553
2125
27798
27332
26885
26434
25888
25345
24850
24279
23729
23034
22435
21691
2150
27971
27497
27044
26586
26040
25492
24989
24409
23875
23169
22559
21828
2175
28143
27663
27202
26738
26184
25639
25129
24539
24018
23304
22684
21965
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-40
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4 - Maximum Mass for ASDA (kg) 5° FLAPS
(cont’d)
PA (ft)
10000
OAT (°C)
-25
-20
-15
-10
-5
0
5
10
15
20
25
30
2200
28316
27829
27361
26890
26327
25786
25268
24669
24139
23439
22808
22084
2225
28489
27995
27520
27041
26471
25933
25407
24799
24261
23574
22933
22196
2250
28662
28160
27679
27193
26614
26073
25546
24929
24383
23708
23058
22309
2275
28798
28326
27838
27345
26757
26209
25685
25059
24505
23843
23182
22421
2300
28930
28492
27997
27497
26901
26344
25824
25189
24627
23978
23307
22533
2325
29081
28658
28156
27649
27044
26480
25963
25319
24749
24094
23431
22646
2350
29232
28790
28315
27801
27188
26615
26094
25449
24870
24206
23556
22758
2375
(29394) 28913
28474
27953
27331
26750
26222
25580
24992
24318
23680
22870
2400
(29559) 29059
28633
28105
27475
26886
26350
25710
25114
24430
23805
22983
2425
Max
29206
28766
28257
27618
27021
26478
25840
25236
24543
23929
23095
2450
Max
(29360) 28884
28409
27762
27157
26606
25970
25358
24655
24045
23207
2475
Max
(29519) 29020
28561
27905
27292
26734
26091
25480
24767
24148
23320
2500
Max
Max
29161
28707
28049
27428
26862
26211
25602
24879
24252
23432
2525
Max
Max
(29307) 28820
28192
27563
26990
26330
25723
24992
24356
23544
2550
Max
Max
(29460) 28936
28336
27698
27118
26449
25845
25104
24459
23657
2575
Max
Max
Max
29073
28479
27834
27246
26569
25967
25216
24563
23769
2600
Max
Max
Max
29211
28623
27969
27374
26688
26081
25328
24666
23882
2625
Max
Max
Max
(29355) 28746
28105
27502
26807
26193
25440
24770
23994
2650
Max
Max
Max
(29502) 28853
28240
27630
26927
26304
25553
24874
24088
2675
Max
Max
Max
Max
28969
28376
27758
27046
26416
25665
24977
24182
2700
Max
Max
Max
Max
29101
28511
27886
27165
26527
25777
25081
24275
2725
Max
Max
Max
Max
29233
28647
28014
27285
26639
25889
25185
24368
2750
Max
Max
Max
Max
(29372) 28758
28142
27404
26750
26001
25288
MAT
2775
Max
Max
Max
Max
(29512) 28858
28270
27523
26862
26104
MAT
MAT
2800
Max
Max
Max
Max
Max
28969
28398
27642
26973
26206
MAT
MAT
2825
Max
Max
Max
Max
Max
29097
28526
27762
27085
26308
MAT
MAT
2850
Max
Max
Max
Max
Max
29224
28654
27881
27196
26410
MAT
MAT
2875
Max
Max
Max
Max
Max
(29356) 28758
28000
27307
26513
MAT
MAT
2900
Max
Max
Max
Max
Max
(29490) 28853
28120
27419
26615
MAT
MAT
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
ASDA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-41
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
Sea Level
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
50
1000
24000
23699
23414
23137
22876
22624
22383
22070
21721
21078
20403
19036
1025
24262
23997
23704
23419
23150
22891
22643
22320
22023
21366
20671
19515
1050
24525
24252
23994
23701
23425
23158
22903
22571
22265
21655
20939
19994
1075
24787
24507
24243
23983
23699
23425
23163
22822
22507
21944
21208
20237
1100
25050
24762
24491
24227
23973
23692
23423
23072
22749
22183
21476
20478
1125
25312
25017
24739
24468
24212
23959
23683
23323
22991
22409
21744
20718
1150
25574
25272
24987
24708
24446
24193
23943
23574
23233
22636
22010
20959
1175
25837
25527
25234
24949
24680
24421
24173
23824
23475
22862
22220
21199
1200
26079
25782
25482
25190
24915
24649
24395
24064
23717
23089
22430
21440
1225
26287
26029
25730
25431
25149
24877
24617
24278
23959
23316
22640
21680
1250
26496
26232
25978
25672
25383
25105
24839
24492
24171
23542
22850
21920
1275
26705
26435
26180
25913
25618
25333
25061
24705
24377
23769
23061
22126
1300
26914
26638
26378
26123
25852
25561
25282
24919
24584
23996
23271
22314
1325
27122
26841
26575
26315
26069
25789
25504
25133
24790
24189
23481
22502
1350
27331
27044
26773
26507
26256
26013
25726
25347
24996
24382
23691
22690
1375
27540
27247
26970
26699
26443
26195
25948
25560
25202
24575
23902
22878
1400
27749
27450
27168
26891
26630
26377
26136
25774
25409
24768
24095
23066
1425
27957
27653
27365
27083
26817
26559
26313
25988
25615
24961
24274
23254
1450
28166
27856
27563
27275
27004
26741
26490
26161
25821
25154
24453
23442
1475
28375
28059
27760
27467
27191
26923
26668
26332
26022
25347
24631
23630
1500
28583
28262
27958
27660
27378
27106
26845
26503
26187
25540
24810
23818
1525
28776
28465
28155
27852
27565
27288
27022
26674
26352
25733
24989
24005
1550
28952
28668
28353
28044
27752
27470
27199
26845
26518
25926
25168
24165
1575
29124
28841
28550
28236
27939
27652
27377
27016
26683
26095
25347
24324
1600
(29293) 29011
28738
28428
28125
27834
27554
27187
26848
26250
25525
24484
1625
(29452) 29179
28902
28620
28312
28016
27731
27358
27013
26405
25704
24644
1650
Max
(29339) 29067
28791
28499
28198
27909
27529
27178
26560
25883
24803
1675
Max
(29493) 29232
28950
28686
28380
28086
27700
27344
26715
26050
24963
1700
Max
Max
(29383) 29112
28841
28562
28263
27871
27509
26870
26194
25122
1725
Max
Max
(29531) (29271) 28996
28734
28441
28042
27674
27025
26337
25282
1750
Max
Max
Max
(29415) 29155
28883
28618
28213
27839
27179
26481
25442
1775
Max
Max
Max
(29558) (29306) 29036
28775
28384
28004
27334
26625
25601
1800
Max
Max
Max
Max
(29445) 29191
28920
28555
28170
27489
26769
25761
1825
Max
Max
Max
Max
Max
(29334) 29071
28719
28335
27644
26913
25921
1850
Max
Max
Max
Max
Max
(29469) 29223
28858
28500
27799
27056
26065
1875
Max
Max
Max
Max
Max
Max
(29359) 29002
28665
27954
27200
26194
1900
Max
Max
Max
Max
Max
Max
(29490) 29149
28803
28109
27344
26322
1925
Max
Max
Max
Max
Max
Max
Max
(29290) 28939
28263
27488
26451
1950
Max
Max
Max
Max
Max
Max
Max
(29417) 29081
28418
27632
26580
1975
Max
Max
Max
Max
Max
Max
Max
(29543) 29224
28573
27775
26709
2000
Max
Max
Max
Max
Max
Max
Max
Max
(29351) 28721
27919
26838
2025
Max
Max
Max
Max
Max
Max
Max
Max
(29473) 28846
28063
26967
2050
Max
Max
Max
Max
Max
Max
Max
Max
Max
28975
28207
27095
2075
Max
Max
Max
Max
Max
Max
Max
Max
Max
29110
28351
27224
2100
Max
Max
Max
Max
Max
Max
Max
Max
Max
29245
28494
27353
2125
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29362) 28638
27482
2150
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29477) 28765
27611
2175
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28882
27740
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-42
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
(cont’d)
PA (ft)
Sea Level
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
50
2200
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29005
27869
2225
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29131
27997
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29256
28126
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29365) 28255
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29474) 28384
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28513
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28642
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28757
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28864
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28974
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29086
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29198
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29305)
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29406)
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29508)
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-43
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
1000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
1000
23433
23146
22871
22607
22356
22120
21823
21453
20969
20237
19024
1025
23724
23428
23146
22874
22615
22372
22105
21753
21254
20500
19503
1050
24012
23710
23420
23140
22874
22625
22349
22042
21540
20763
19981
1075
24261
23993
23694
23407
23134
22877
22594
22277
21825
21027
20231
1100
24509
24235
23969
23674
23393
23129
22838
22513
22087
21290
20471
1125
24757
24476
24207
23940
23652
23381
23083
22749
22311
21553
20711
1150
25006
24717
24442
24177
23911
23633
23327
22984
22535
21816
20951
1175
25254
24958
24676
24404
24146
23885
23571
23220
22759
22062
21192
1200
25503
25200
24910
24632
24367
24117
23816
23455
22983
22268
21432
1225
25751
25441
25144
24859
24588
24332
24051
23691
23207
22474
21672
1250
25999
25682
25379
25087
24809
24547
24260
23927
23431
22680
21912
1275
26197
25923
25613
25314
25030
24763
24468
24138
23655
22886
22119
1300
26395
26131
25847
25542
25251
24978
24676
24339
23879
23093
22307
1325
26593
26323
26065
25769
25473
25193
24885
24540
24088
23299
22495
1350
26791
26515
26252
25997
25694
25408
25093
24741
24278
23505
22683
1375
26989
26708
26439
26179
25915
25623
25301
24942
24469
23711
22871
1400
27187
26900
26625
26361
26109
25838
25510
25142
24660
23917
23059
1425
27384
27092
26812
26543
26285
26042
25718
25343
24851
24105
23246
1450
27582
27284
26999
26724
26462
26214
25926
25544
25041
24280
23434
1475
27780
27477
27186
26906
26639
26386
26108
25745
25232
24455
23622
1500
27978
27669
27373
27088
26816
26558
26275
25946
25423
24631
23810
1525
28176
27861
27560
27270
26993
26730
26442
26117
25613
24806
23998
1550
28374
28053
27747
27451
27169
26902
26608
26278
25804
24981
24158
1575
28572
28246
27934
27633
27346
27074
26775
26439
25995
25156
24317
1600
28756
28438
28121
27815
27523
27247
26942
26600
26149
25332
24477
1625
28920
28630
28307
27996
27700
27419
27109
26761
26302
25507
24636
1650
29086
28799
28494
28178
27876
27591
27276
26922
26455
25682
24796
1675
29251
28959
28681
28360
28053
27763
27442
27083
26608
25857
24955
1700
(29400)
29121
28836
28542
28230
27935
27609
27244
26761
26026
25115
1725
(29549) (29279)
28992
28717
28407
28107
27776
27405
26914
26167
25274
1750
Max
(29423)
29150
28865
28583
28279
27943
27566
27068
26308
25434
1775
Max
(29567) (29302)
29018
28747
28451
28110
27727
27221
26449
25593
1800
Max
Max
(29441)
29173
28891
28623
28276
27888
27374
26591
25753
1825
Max
Max
Max
(29318)
29041
28775
28443
28049
27527
26732
25912
1850
Max
Max
Max
(29453)
29192
28914
28610
28209
27680
26873
26058
1875
Max
Max
Max
Max
(29331)
29062
28760
28370
27833
27014
26187
1900
Max
Max
Max
Max
(29462)
29210
28895
28531
27986
27155
26315
1925
Max
Max
Max
Max
Max
(29344)
29038
28692
28139
27296
26444
1950
Max
Max
Max
Max
Max
(29471)
29182
28822
28292
27437
26573
1975
Max
Max
Max
Max
Max
Max
(29316)
28954
28445
27578
26702
2000
Max
Max
Max
Max
Max
Max
(29439)
29094
28598
27719
26830
2025
Max
Max
Max
Max
Max
Max
(29563)
29233
28740
27860
26959
2050
Max
Max
Max
Max
Max
Max
Max
(29356)
28864
28001
27088
2075
Max
Max
Max
Max
Max
Max
Max
(29475)
28993
28142
27216
2100
Max
Max
Max
Max
Max
Max
Max
Max
29126
28283
27345
2125
Max
Max
Max
Max
Max
Max
Max
Max
(29259)
28424
27474
2150
Max
Max
Max
Max
Max
Max
Max
Max
(29373)
28565
27603
2175
Max
Max
Max
Max
Max
Max
Max
Max
(29488)
28703
27731
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-44
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS (cont’d)
PA (ft)
1000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
2200
Max
Max
Max
Max
Max
Max
Max
Max
Max
28819
27860
2225
Max
Max
Max
Max
Max
Max
Max
Max
Max
28935
27989
2250
Max
Max
Max
Max
Max
Max
Max
Max
Max
29058
28118
2275
Max
Max
Max
Max
Max
Max
Max
Max
Max
29181
28246
2300
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29298)
28375
2325
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29405)
28504
2350
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29513)
28632
2375
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28749
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28857
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28966
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29078
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29190
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29298)
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29399)
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29500)
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-45
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
2000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
1000
22886
22613
22353
22106
21833
21547
21189
20838
20139
18934
Min
1025
23161
22880
22612
22358
22113
21849
21482
21119
20399
19409
Min
1050
23435
23147
22871
22610
22358
22120
21774
21401
20659
19883
18405
1075
23710
23413
23130
22861
22603
22358
22052
21682
20919
20180
18818
1100
23985
23680
23389
23113
22847
22595
22281
21964
21179
20419
19231
1125
24222
23947
23649
23365
23092
22833
22510
22192
21440
20657
19645
1150
24456
24182
23908
23617
23337
23071
22740
22413
21700
20896
20030
1175
24691
24410
24142
23868
23581
23309
22969
22634
21960
21135
20245
1200
24925
24638
24363
24102
23826
23547
23198
22855
22172
21374
20460
1225
25160
24865
24584
24317
24060
23785
23428
23076
22376
21612
20675
1250
25395
25093
24806
24532
24269
24019
23657
23297
22579
21851
20890
1275
25629
25321
25027
24746
24477
24222
23886
23518
22783
22070
21105
1300
25864
25549
25248
24961
24686
24425
24098
23738
22987
22257
21320
1325
26078
25776
25469
25176
24894
24628
24294
23959
23191
22444
21535
1350
26266
26003
25690
25391
25103
24830
24489
24153
23394
22630
21751
1375
26453
26185
25911
25605
25311
25033
24684
24341
23598
22817
21966
1400
26640
26367
26106
25820
25520
25236
24880
24529
23802
23004
22141
1425
26827
26549
26282
26028
25729
25439
25075
24717
24005
23190
22309
1450
27014
26730
26459
26199
25937
25641
25270
24905
24178
23377
22476
1475
27201
26912
26636
26371
26117
25844
25466
25093
24351
23564
22644
1500
27389
27094
26812
26543
26284
26038
25661
25281
24524
23750
22812
1525
27576
27276
26989
26715
26451
26200
25856
25469
24697
23937
22980
1550
27763
27458
27166
26886
26618
26362
26041
25657
24870
24105
23148
1575
27950
27640
27342
27058
26784
26525
26198
25845
25044
24264
23315
1600
28137
27821
27519
27230
26951
26687
26355
26027
25217
24422
23483
1625
28325
28003
27696
27402
27118
26850
26511
26178
25390
24581
23651
1650
28512
28185
27873
27573
27285
27012
26668
26329
25563
24739
23819
1675
28697
28367
28049
27745
27452
27175
26825
26480
25736
24898
23986
1700
28851
28549
28226
27917
27619
27337
26981
26630
25909
25056
24131
1725
29007
28723
28403
28089
27786
27500
27138
26781
26067
25215
24273
1750
29166
28872
28579
28260
27953
27662
27295
26932
26206
25373
24415
1775
(29316)
29024
28744
28432
28120
27824
27451
27083
26345
25532
24557
1800
(29455)
29179
28887
28604
28287
27987
27608
27234
26485
25690
24699
1825
Max
(29324)
29037
28759
28454
28149
27765
27385
26624
25849
24842
1850
Max
(29459)
29188
28899
28621
28312
27921
27536
26764
26006
24984
1875
Max
Max
(29328)
29045
28769
28474
28078
27687
26903
26134
25126
1900
Max
Max
(29459)
29193
28904
28637
28235
27838
27042
26262
25268
1925
Max
Max
Max
(29329)
29048
28778
28391
27989
27182
26389
25410
1950
Max
Max
Max
(29456)
29192
28909
28548
28140
27321
26517
25552
1975
Max
Max
Max
Max
(29325)
29049
28702
28291
27461
26645
25695
2000
Max
Max
Max
Max
(29448)
29190
28829
28442
27600
26773
25837
2025
Max
Max
Max
Max
(29572) (29320)
28958
28593
27740
26901
25979
2050
Max
Max
Max
Max
Max
(29440)
29094
28734
27879
27029
26098
2075
Max
Max
Max
Max
Max
(29561)
29230
28856
28018
27157
26213
2100
Max
Max
Max
Max
Max
Max
(29351)
28983
28158
27285
26329
2125
Max
Max
Max
Max
Max
Max
(29467)
29115
28297
27413
26444
2150
Max
Max
Max
Max
Max
Max
Max
29246
28437
27541
26559
2175
Max
Max
Max
Max
Max
Max
Max
(29360)
28576
27669
26674
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-46
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
(cont’d)
PA (ft)
2000
OAT (°C)
-5
0
5
10
15
20
25
30
35
40
45
2200
Max
Max
Max
Max
Max
Max
Max
(29473)
28711
27797
26789
2225
Max
Max
Max
Max
Max
Max
Max
Max
28825
27925
26904
2250
Max
Max
Max
Max
Max
Max
Max
Max
28941
28053
27020
2275
Max
Max
Max
Max
Max
Max
Max
Max
29062
28181
27135
2300
Max
Max
Max
Max
Max
Max
Max
Max
29184
28309
27250
2325
Max
Max
Max
Max
Max
Max
Max
Max
(29299)
28436
27365
2350
Max
Max
Max
Max
Max
Max
Max
Max
(29406)
28564
27480
2375
Max
Max
Max
Max
Max
Max
Max
Max
(29512)
28692
27596
2400
Max
Max
Max
Max
Max
Max
Max
Max
Max
28799
27711
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
28906
27826
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
29016
27941
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
29128
28056
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
29239
28171
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29341)
28287
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29442)
28402
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29543)
28517
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28632
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28740
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28839
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28939
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29038
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29137
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29236
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29333)
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29428)
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29524)
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-47
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
3000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
1000
22634
22362
22105
21820
21522
21235
20959
20699
20050
18702
Min
1025
22902
22622
22357
22103
21824
21529
21244
20976
20308
19167
Min
1050
23169
22881
22609
22347
22099
21822
21529
21253
20565
19631
18366
1075
23437
23141
22860
22592
22337
22091
21815
21531
20823
20048
18778
1100
23704
23400
23112
22836
22574
22321
22078
21808
21080
20283
19189
1125
23972
23660
23364
23081
22811
22552
22302
22067
21337
20518
19601
1150
24204
23919
23616
23325
23049
22782
22526
22284
21595
20753
20006
1175
24432
24152
23867
23569
23286
23013
22750
22502
21852
20988
20220
1200
24660
24374
24102
23814
23523
23243
22973
22719
22086
21223
20435
1225
24889
24595
24316
24049
23761
23473
23197
22937
22287
21458
20649
1250
25117
24816
24531
24258
23998
23704
23421
23155
22489
21693
20864
1275
25345
25038
24746
24466
24201
23934
23645
23372
22690
21928
21078
1300
25573
25259
24960
24674
24403
24140
23868
23590
22892
22127
21293
1325
25802
25480
25175
24883
24605
24336
24078
23807
23093
22311
21507
1350
26024
25702
25390
25091
24807
24533
24269
24021
23295
22494
21721
1375
26206
25923
25604
25299
25010
24729
24459
24206
23496
22678
21936
1400
26388
26115
25819
25508
25212
24925
24650
24391
23698
22862
22117
1425
26570
26292
26027
25716
25414
25122
24840
24576
23899
23045
22284
1450
26753
26469
26199
25924
25616
25318
25031
24761
24086
23229
22452
1475
26935
26646
26370
26106
25819
25514
25222
24946
24257
23412
22619
1500
27117
26823
26542
26273
26017
25710
25412
25131
24428
23596
22786
1525
27299
27000
26714
26440
26179
25907
25603
25317
24600
23780
22953
1550
27482
27177
26886
26606
26341
26083
25793
25502
24771
23963
23121
1575
27664
27354
27057
26773
26503
26240
25984
25687
24942
24125
23288
1600
27846
27530
27229
26940
26665
26397
26140
25872
25113
24281
23455
1625
28028
27707
27401
27107
26827
26555
26293
26046
25285
24436
23622
1650
28211
27884
27572
27273
26989
26712
26446
26194
25456
24592
23790
1675
28393
28061
27744
27440
27151
26870
26599
26343
25627
24748
23957
1700
28575
28238
27916
27607
27313
27027
26751
26492
25799
24904
24105
1725
28745
28415
28088
27774
27475
27184
26904
26641
25970
25060
24247
1750
28894
28592
28259
27940
27637
27342
27057
26789
26114
25216
24389
1775
29048
28754
28431
28107
27799
27499
27210
26938
26252
25372
24530
1800
29203
28898
28603
28274
27961
27657
27363
27087
26390
25527
24672
1825
(29345 ) 29048
28758
28441
28123
27814
27516
27235
26527
25683
24814
1850
(29480 ) 29200
28898
28607
28285
27971
27669
27384
26665
25839
24955
1875
Max
(29338)
29044
28758
28448
28129
27822
27533
26803
25995
25097
1900
Max
(29469)
29192
28893
28610
28286
27975
27682
26941
26122
25239
1925
Max
Max
(29328)
29036
28756
28444
28128
27830
27079
26248
25381
1950
Max
Max
(29455)
29179
28887
28601
28281
27979
27217
26374
25522
1975
Max
Max
Max
(29314)
29025
28745
28434
28128
27355
26499
25664
2000
Max
Max
Max
(29437)
29166
28873
28587
28276
27493
26625
25806
2025
Max
Max
Max
(29561) (29299)
29006
28730
28425
27631
26751
25948
2050
Max
Max
Max
Max
(29419)
29143
28854
28574
27769
26877
26072
2075
Max
Max
Max
Max
(29539) (29276)
28982
28716
27907
27003
26187
2100
Max
Max
Max
Max
Max
(29393)
29115
28837
28045
27129
26302
2125
Max
Max
Max
Max
Max
(29510)
29249
28961
28183
27255
26417
2150
Max
Max
Max
Max
Max
Max
(29364)
29090
28321
27381
26532
2175
Max
Max
Max
Max
Max
Max
(29478)
29220
28459
27506
26646
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-48
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
(cont’d)
PA (ft)
3000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
2200
Max
Max
Max
Max
Max
Max
Max
(29337)
28597
27632
26761
2225
Max
Max
Max
Max
Max
Max
Max
(29448)
28727
27758
26876
2250
Max
Max
Max
Max
Max
Max
Max
(29560)
28840
27884
26991
2275
Max
Max
Max
Max
Max
Max
Max
Max
28955
28010
27106
2300
Max
Max
Max
Max
Max
Max
Max
Max
29076
28136
27221
2325
Max
Max
Max
Max
Max
Max
Max
Max
29196
28262
27335
2350
Max
Max
Max
Max
Max
Max
Max
Max
(29309)
28388
27450
2375
Max
Max
Max
Max
Max
Max
Max
Max
(29415)
28513
27565
2400
Max
Max
Max
Max
Max
Max
Max
Max
(29520)
28639
27680
2425
Max
Max
Max
Max
Max
Max
Max
Max
Max
28753
27795
2450
Max
Max
Max
Max
Max
Max
Max
Max
Max
28859
27909
2475
Max
Max
Max
Max
Max
Max
Max
Max
Max
28966
28024
2500
Max
Max
Max
Max
Max
Max
Max
Max
Max
29075
28139
2525
Max
Max
Max
Max
Max
Max
Max
Max
Max
29185
28254
2550
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29291)
28369
2575
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29390)
28484
2600
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29490)
28598
2625
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28710
2650
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28810
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28909
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29008
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29107
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
29205
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29303)
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29398)
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29494)
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-49
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
4000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
1000
22121
21828
21516
21217
20929
20658
20400
19818
18487
Min
Min
1025
22373
22110
21818
21510
21214
20935
20668
20163
18942
Min
Min
1050
22625
22354
22094
21803
21498
21211
20936
20416
19397
18199
Min
1075
22877
22599
22331
22075
21783
21487
21205
20669
19851
18603
Min
1100
23129
22843
22568
22305
22052
21763
21473
20922
20155
19007
Min
1125
23382
23088
22806
22535
22275
22031
21741
21175
20387
19411
18133
1150
23634
23332
23043
22765
22499
22247
22007
21428
20618
19815
18486
1175
23886
23577
23280
22995
22722
22464
22217
21681
20849
20114
18839
1200
24118
23821
23517
23225
22945
22680
22427
21934
21080
20326
19192
1225
24333
24056
23754
23455
23168
22897
22638
22146
21312
20537
19545
1250
24548
24265
23991
23685
23391
23113
22848
22344
21543
20749
19898
1275
24763
24473
24195
23915
23614
23330
23058
22542
21774
20960
20135
1300
24978
24681
24397
24123
23837
23547
23268
22740
22004
21172
20326
1325
25193
24890
24599
24319
24051
23763
23478
22938
22185
21383
20517
1350
25408
25098
24801
24515
24241
23980
23688
23136
22366
21595
20708
1375
25623
25307
25003
24711
24431
24167
23899
23334
22546
21807
20899
1400
25838
25515
25205
24907
24621
24351
24092
23533
22727
22014
21090
1425
26043
25724
25408
25103
24811
24535
24271
23731
22908
22179
21281
1450
26215
25932
25610
25299
25001
24720
24450
23929
23088
22344
21472
1475
26387
26113
25812
25494
25190
24904
24629
24107
23269
22509
21663
1500
26559
26280
26011
25690
25380
25088
24807
24276
23450
22674
21854
1525
26731
26446
26173
25886
25570
25272
24986
24444
23630
22839
22035
1550
26903
26613
26335
26066
25760
25457
25165
24612
23811
23004
22183
1575
27075
26780
26497
26223
25950
25641
25344
24781
23992
23168
22332
1600
27247
26947
26659
26380
26112
25825
25522
24949
24146
23333
22480
1625
27419
27114
26821
26537
26265
26008
25701
25117
24300
23498
22629
1650
27591
27281
26983
26694
26417
26156
25880
25285
24453
23663
22777
1675
27763
27448
27145
26851
26570
26304
26047
25454
24606
23828
22926
1700
27935
27615
27307
27008
26722
26452
26191
25622
24760
23993
23074
1725
28107
27782
27469
27166
26875
26600
26335
25790
24913
24134
23223
1750
28279
27948
27631
27323
27027
26748
26478
25959
25066
24274
23371
1775
28451
28115
27793
27480
27180
26896
26622
26102
25219
24413
23520
1800
28623
28282
27955
27637
27332
27044
26766
26238
25373
24553
23668
1825
28775
28449
28116
27794
27484
27192
26910
26373
25526
24693
23817
1850
28915
28616
28278
27951
27637
27340
27053
26509
25679
24833
23965
1875
29063
28765
28440
28108
27789
27488
27197
26644
25833
24972
24096
1900
29211
28900
28602
28265
27942
27636
27341
26780
25986
25112
24222
1925
(29344 ) 29043
28750
28422
28094
27784
27485
26916
26113
25252
24347
1950
(29471 ) 29187
28881
28580
28247
27932
27628
27051
26236
25391
24473
1975
Max
(29321)
29019
28728
28399
28080
27772
27187
26360
25531
24598
2000
Max
(29444)
29159
28855
28552
28229
27916
27322
26484
25671
24724
2025
Max
(29568) (29293)
28987
28701
28377
28060
27458
26608
25811
24850
2050
Max
Max
(29413)
29123
28825
28525
28203
27594
26732
25950
24975
2075
Max
Max
(29533) (29259)
28951
28673
28347
27729
26856
26073
25101
2100
Max
Max
Max
(29376)
29083
28796
28491
27865
26980
26186
25226
2125
Max
Max
Max
(29493)
29216
28916
28635
28000
27104
26300
25352
2150
Max
Max
Max
Max
(29336)
29045
28762
28136
27228
26413
25478
2175
Max
Max
Max
Max
(29450)
29174
28879
28272
27351
26526
25603
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
(cont’d on next page)
AOM DASH 8-Q400
METRIC
4.1-50
[Rev. X] 31 MAY 2011
CHAPTER 4
PERFORMANCE
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
(cont’d)
PA (ft)
4000
OAT (°C)
-10
-5
0
5
10
15
20
25
30
35
40
2200
Max
Max
Max
Max
(29564) (29297)
29002
28407
27475
26639
25729
2225
Max
Max
Max
Max
Max
(29408)
29127
28543
27599
26753
25854
2250
Max
Max
Max
Max
Max
(29519)
29253
28678
27723
26866
25980
2275
Max
Max
Max
Max
Max
Max
(29362)
28792
27847
26979
26086
2300
Max
Max
Max
Max
Max
Max
(29471)
28904
27971
27092
26188
2325
Max
Max
Max
Max
Max
Max
Max
29021
28095
27206
26290
2350
Max
Max
Max
Max
Max
Max
Max
29139
28219
27319
26392
2375
Max
Max
Max
Max
Max
Max
Max
29257
28343
27432
26495
2400
Max
Max
Max
Max
Max
Max
Max
(29362)
28466
27545
26597
2425
Max
Max
Max
Max
Max
Max
Max
(29466)
28590
27659
26699
2450
Max
Max
Max
Max
Max
Max
Max
(29571)
28710
27772
26801
2475
Max
Max
Max
Max
Max
Max
Max
Max
28815
27885
26903
2500
Max
Max
Max
Max
Max
Max
Max
Max
28919
27998
27005
2525
Max
Max
Max
Max
Max
Max
Max
Max
29027
28112
27108
2550
Max
Max
Max
Max
Max
Max
Max
Max
29134
28225
27210
2575
Max
Max
Max
Max
Max
Max
Max
Max
29242
28338
27312
2600
Max
Max
Max
Max
Max
Max
Max
Max
(29342)
28452
27414
2625
Max
Max
Max
Max
Max
Max
Max
Max
(29441)
28565
27516
2650
Max
Max
Max
Max
Max
Max
Max
Max
(29540)
28678
27618
2675
Max
Max
Max
Max
Max
Max
Max
Max
Max
28778
27721
2700
Max
Max
Max
Max
Max
Max
Max
Max
Max
28877
27823
2725
Max
Max
Max
Max
Max
Max
Max
Max
Max
28975
27925
2750
Max
Max
Max
Max
Max
Max
Max
Max
Max
29072
28027
2775
Max
Max
Max
Max
Max
Max
Max
Max
Max
29169
28129
2800
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29266)
28231
2825
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29361)
28333
2850
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29457)
28436
2875
Max
Max
Max
Max
Max
Max
Max
Max
Max
(29552)
28538
2900
Max
Max
Max
Max
Max
Max
Max
Max
Max
Max
28640
NOTE: Masses given in brackets are in excess of the maximum permitted structural mass and are given for interpolation purposes.
Max
= Mass in excess of the maximum permitted structural mass
Min
= Mass is less than the minimum take-off mass
MAT
= Mass, Altitude and Temperature limit
TODA
(m)
METRIC
AOM DASH 8-Q400
CHAPTER 4
PERFORMANCE
4.1-51
[Rev. X] 31 MAY 2011
Table 4A - Maximum Mass for TODA (kg) 5° FLAPS
PA (ft)
5000
OAT (°C)
-15
-10
-5
0
5
10
15
20
25
30
35
40
1000
21850
21529
21222
20922
20640
20366
20106
19342
18287
Min
Min
Min
1025
22127
21832
21515
21206
20916
20633
20365
19834
18732
Min
Min
Min
1050
22373
22105
21808
21490
21192
20900
20624
20162
19178
Min
Min
Min
1075
22618
22343
22080
21774
21467
21168
20884
20408
19624
18369
Min
Min
1100
22863
22580
22310
22046
21743
21435
21143
20653
20035
18763
Min
Min
1125
23108
22818
22540
22269
22014
21702
21402
20898
20263
19158
18096
Min
1150
23353
23055
22770
22491
22231
21969
21661
21144
20491
19552
18447
Min
1175
23598
23293
23000
22714
22447
22185
21920
21389
20719
19946
18798
Min
1200
23843
23530
23230
22937
22663
22394
22140
21635
20946
20179
19149
Min
1225
24075
23768
23460
23160
22879
22603
22343
21880
21174
20387
19501
18184
1250
24284
24004
23690
23383
23095
22813
22546
22098
21402
20594
19852
18486
1275
24493
24207
23921
23606
23311
23022
22749
22290
21630
20802
20110
18787
1300
24702
24409
24128
23829
23527
23231
22952
22482
21857
21010
20300
19089
1325
24911
24612
24324
24044
23743
23441
23155
22674
22066
21217
20490
19391
1350
25120
24814
24520
24234
23959
23650
23357
22866
22244
21425
20681
19692
1375
25328
25017
24716
24423
24149
23859
23560
23058
22422
21632
20871
19994
1400
25537
25219
24912
24613
24333
24058
23763
23250
22600
21840
21061
20166
1425
25746
25421
25108
24803
24517
24236
23966
23442
22778
22037
21252
20336
1450
25955
25624
25304
24993
24701
24414
24144
23634
22956
22199
21442
20505
1475
26131
25826
25500
25182
24885
24592
24316
23826
23134
22361
21632
20675
1500
26299
26023
25696
25372
25069
24770
24489
24015
23312
22523
21822
20844
1525
26466
26185
25892
25562
25252
24948
24661
24178
23490
22684
22010
21014
1550
26633
26347
26071
25752
25436
25126
24834
24341
23668
22846
22158
21184
1575
26800
26509
26228
25941
25620
25304
25006
24504
23846
23008
22306
21353
1600
26968
26672
26385
26105
25804
25482
25179
24667
24020
23170
22454
21523
1625
27135
26834
26542
26258
25988
25660
25351
24830
24171
23332
22602
21692
1650
27302
26996
26700
26410
26138
25839
25524
24993
24322
23493
22750
21862
1675
27469
27158
26857
26562
26286
26013
25696
25156
24473
23655
22898
22024
1700
27637
27320
27014
26715
26434
26156
25868
25319
24624
23817
23046
22156
1725
27804
27482
27171
26867
26581
26300
26033
25482
24774
23979
23194
22287
1750
27971
27645
27328
27019
26729
26443
26172
25645
24925
24119
23342
22419
1775
28138
27807
27485
27172
26877
26586
26311
25808
25076
24256
23490
22550
1800
28306
27969
27643
27324
27025
26729
26450
25971
25227
24393
23638
22682
1825
28473
28131
27800
27476
27172
26872
26588
26108
25378
24530
23785
22813
1850
28640
28293
27957
27629
27320
27016
26727
26240
25529
24667
23933
22945
1875
28785
28455
28114
27781
27468
27159
26866
26371
25680
24804
24069
23076
1900
28921
28618
28271
27933
27616
27302
27005
26503
25831
24941
24194
23208
1925
29065
28762
28429
28086
27763
27445
27144
26634
25982
25078
24319
23339
1950
29209
28893
28586
28238
2791