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. REMOVE INSERT Chapter 00 Section Page(s) Chapter 00 Section Page(s) 00 LEP 1 00 LEP 1 Chapter 01 Section Page(s) Chapter 01 Section Page(s) 01 LEP 1 01 LEP 1 Chapter 02 Section Page(s) Chapter 02 Section Page(s) 02 LEP 1-2 02 LEP 1-2 2.4 1-2 2.4 1-2 2.15 3-16 2.15 3-14 2.17 3-4 2.17 3-4 2.17 23-28 2.17 23-28 2.17 39-40 2.17 39-40 2.17 43-44 2.17 43-44 2.17 47-48 2.17 47-48 PSM 1-84-1 - DOT - METRIC Effectivity: **ALL Transmittal Letter Page 1 Nov 21/2016 B AEROPLANE OPERATING MANUAL REMOVE INSERT Chapter 03 Section Page(s) Chapter 03 Section Page(s) 03 LEP 1-2 03 LEP 1-2 ToC 3 3-4 ToC 3 3-4 3.1 13-14 3.1 13-14 3.1 21-22 3.1 21-22 3.1 31-36 3.1 31-36 3.1 49-50 3.1 49-50 3.1 65-72 3.1 65-72 3.2 19-20 3.2 19-20 3.3 3-4 3.3 3-4 Chapter 04 Section Page(s) Chapter 04 Section Page(s) 04 LEP 1-5 04 LEP 1-5 4.7 1-2 4.7 1-2 Chapter 05 Section Page(s) Chapter 05 Section Page(s) 05 LEP 1-2 05 LEP 1-2 Chapter 06 Section Page(s) Chapter 06 Section Page(s) 06 LEP 1-12 06 LEP 1-12 6.3 41-44 6.3 41-44 6.6 7-8 6.6 7-8 6.6 11-12 6.6 11-12 6.6 21-22 6.6 21-22 ToC 6.7 1-2 ToC 6.7 1-2 6.7 1-2 6.7 1-2 6.7 23-24 6.7 23-24 PSM 1-84-1 - DOT - METRIC Effectivity: **ALL Transmittal Letter Page 2 Nov 21/2016 BOMBARDIER Series 400 AEROPLANE OPERATING MANUAL PSM 1-84-1 BOMBARDIER INC. BOMBARDIER AEROSPACE COMMERCIAL AIRCRAFT 123 GARRATT BLVD, TORONTO, ONTARIO CANADA M3K 1Y5 Copyright ©2000 - 2015 by Bombardier Inc. All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission by Bombardier Inc. The Bombardier logo and de Havilland are registered trademarks of Bombardier Inc. * The information, technical data and the designs disclosed herein are the exclusive property of Bombardier, or contain proprietary rights of others and are not to be used or disclosed to others without the written consent of Bombardier. The recipient of this document, by its retention and use, agrees to hold in confidence the technical data and designs contained herein. The foregoing shall not apply to persons having proprietary rights to such information, technical data or such designs to the extent that such rights exist.* Technical Publications Manual Change Request TO: MCR FOCAL, TECHNICAL PUBLICATIONS BOMBARDIER AEROSPACE 123 GARRATT BLVD. TORONTO, ONTARIO, CANADA, M3K 1Y5 MAIL STOP: N42−25 FAX: (416) 375−4538 E−MAIL ADDRESS: mcrfocal@aero.bombardier.com B Name of Airline: Bombardier Reference #: Date: ALL fields marked with an asterisk * are required Contact Information *Name: *Corporation Name: *Dept Name/Code: Address: City: State/Province: Postal Code / Zip: Country: *Telephone: Mobile/Cell Phone: Fax Number: *E−Mail: I would like to receive notification of actions on this request. NOTE: Responses will only be sent by electronic mail. Publication Information *Aircraft Type: *Publication Name/Revision: *Aircraft Model: *Media Type: Paper CD−ROM Originator’s reference number: *PSM/CSP: *Chapter/Section/Subject/Task (or) Page Block/Page Number: DVD IFLY Impact on other programs: *Description of Change Request: Reason for change: Reference data provided: Yes No Description: NOTE: Electronic submissions of MCRs are available on www.iflybombardier.com Oct 4/2013 AEROPLANE OPERATING MANUAL !"# !"# $ %& $ %& '! '! ( ) ) $ * '+, * '+, - $ !"# $ !"# * * * . &) &) / . 0& ( . 0& ( ) ( ) ( ( '+, ( ( '+, ( &) ( &) ( '! $ '! $ ( * $ * $ $ "1 $ "1 $ - * - * - * '+! - '+! - . !"# - !"# - AEROPLANE OPERATING MANUAL AEROPLANE OPERATING MANUAL ! "!#" $ %% &' TR NO. ( Chapter/Section/ Subject/Task (% ) ** # +, +-./ DATE BOMBARDIER AEROPLANE OPERATING MANUAL !" " !" # BOMBARDIER AEROPLANE OPERATING MANUAL !" " !" # 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 BLANK 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 AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK CHAPTER 0 GENERAL INFORMATION AND UNITS OF MEASUREMENT 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 AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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) THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK CHAPTER 2 LIST OF EFFECTIVE PAGES 02 - Effective Pages 1 2 02 - Contents ToC 2-1 ToC 2-2 ToC 2-3 ToC 2-4 21 Nov 2016 21 Nov 2016 30 Jan 2015 30 Jan 2015 30 Jan 2015 07 Mar 2016 Chapter 2 2.0-1 31 May 2011 2.0-2 31 May 2011 2.0-3 31 May 2011 2.0-4 31 May 2011 2.0-5 21 Nov 2011 2.1-1 31 May 2011 2.1-2 31 May 2011 2.2-1 31 May 2011 2.3-1 31 May 2011 2.4-1 21 Nov 2016 2-4-2 28 Feb 2014 2.4-3 28 Feb 2014 2.4-4 28 Feb 2014 2.4-5 28 Feb 2014 2.5-1 28 Feb 2014 2.5-2 28 Feb 2014 2.6-1 31 May 2011 2.6-2 31 May 2011 2.7-1 28 Feb 2014 2.7-2 28 Feb 2014 2.7-3 28 Feb 2014 2.8-1 27 May 2015 2.9-1 31 May 2011 2.9-2 31 May 2011 2.9-3 31 May 2011 2.10-1 28 Feb 2014 2.10-2 27 May 2015 2.10-3 28 Feb 2014 2.10-4 28 Feb 2014 2.10-5 28 Feb 2014 2.10-6 28 Feb 2014 2.10-7 28 Feb 2014 2.10-8 28 Feb 2014 AOM DASH 8-Q400 02 LEP - Page 1 (Rev 18) 21 NOV 2016 2.10-9 28 Feb 2014 2.10-10 28 Feb 2014 2.10-11 28 Feb 2014 2.10-12 28 Feb 2014 2.10-13 28 Feb 2014 2.11-1 28 Feb 2014 2.11-2 28 Feb 2014 2.11-3 31 May 2011 2.11-4 31 May 2011 2.12-1 30 Jun 2016 2.12-2 30 Jun 2016 2.13-1 07 Mar 2013 2.13-2 28 Feb 2014 2.13-3 28 Feb 2014 2.14-1 28 Feb 2014 2.14-2 28 Feb 2014 2.14-3 28 Feb 2014 2.14-4 28 Feb 2014 2.15-1 30 Jan 2015 2.15-2 30 Jan 2015 2.15-3 21 Nov 2016 2.15-4 30 Oct 2015 2.15-5 21 Nov 2016 2.15-6 21 Nov 2016 2.15-7 21 Nov 2016 2.15-8 21 Nov 2016 2.15-9 21 Nov 2016 2.15-10 21 Nov 2016 2.15-11 21 Nov 2016 2.15-12 21 Nov 2016 2.15-13 21 Nov 2016 2.15-14 21 Nov 2016 2.16-1 30 Jan 2015 2.16-2 30 Jan 2015 2.16-3 30 Jan 2015 2.16-4 30 Jan 2015 2.17-1 30 Jan 2015 2.17-2 30 Jan 2015 2.17-3 30 Jan 2015 2.17-4 21 Nov 2016 2.17-5 30 Jan 2015 2.17-6 30 Jan 2015 2.17-7 07 Mar 2016 DOT 02 LEP - Page 2 (Rev 18) 21 NOV 2016 CHAPTER 2 LIST OF EFFECTIVE PAGES 2.17-8 07 Mar 2016 2.17-51 07 Mar 2016 2.17-9 07 Mar 2016 2.17-52 07 Mar 2016 2.17-10 07 Mar 2016 2.17-53 07 Mar 2016 2.17-11 07 Mar 2016 2.17-12 07 Mar 2016 2.17.13 07 Mar 2016 2.17-14 07 Mar 2016 2.17-15 07 Mar 2016 2.17-16 07 Mar 2016 2.17-17 07 Mar 2016 2.17-18 07 Mar 2016 2.17-19 07 Mar 2016 2.17-20 07 Mar 2016 2.17-21 07 Mar 2016 2.17-22 07 Mar 2016 2.17-23 21 Nov 2016 2.17-24 07 Mar 2016 2.17-25 21 Nov 2016 2.17-26 21 Nov 2016 2.17-27 21 Nov 2016 2.17-28 21 Nov 2016 2.17-29 07 Mar 2016 2.17-30 07 Mar 2016 2.17-31 07 Mar 2016 2.17-32 07 Mar 2016 2.17-33 07 Mar 2016 2.17-34 07 Mar 2016 2.17-35 07 Mar 2016 2.17-36 07 Mar 2016 2.17-37 07 Mar 2016 2.17-38 07 Mar 2016 2.17-39 07 Mar 2016 2.17-40 21 Nov 2016 2.17-41 07 Mar 2016 2.17-42 07 Mar 2016 2.17-43 07 Mar 2016 2.17-44 21 Nov 2016 2.17-45 07 Mar 2016 2.17-46 07 Mar 2016 2.17-47 07 Mar 2016 2.17-48 21 Nov 2016 2.17-49 07 Mar 2016 2.17-50 07 Mar 2016 DOT 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" THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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. AOM DASH 8-Q400 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 07 Mar 2016 3.1-31 21 Nov 2016 3.1-32 21 Nov 2016 3.1-33 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 3.1-46 07 Mar 2016 3.1-4 07 Mar 2016 3.1-47 07 Mar 2016 3.1-5 07 Mar 2016 3.1-48 07 Mar 2016 3.1-6 07 Mar 2016 3.1-49 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 3.1-53 07 Mar 2016 3.1-11 07 Mar 2016 3.1-54 07 Mar 2016 3.1-12 07 Mar 2016 3.1-55 07 Mar 2016 3.1-13 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 3.1-18 07 Mar 2016 3.1-61 07 Mar 2016 3.1-19 07 Mar 2016 3.1-62 07 Mar 2016 3.1-20 07 Mar 2016 3.1-63 07 Mar 2016 3.1-21 21 Nov 2016 3.1-64 07 Mar 2016 3.1-22 07 Mar 2016 3.1-65 21 Nov 2016 3.1-23 07 Mar 2016 3.1-66 07 Mar 2016 3.1-24 07 Mar 2016 3.1-67 21 Nov 2016 3.1-25 07 Mar 2016 3.1-68 21 Nov 2016 3.1-26 07 Mar 2016 3.1-69 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 3.4-18 30 Jan 2015 3.2-7 30 Jan 2015 3.4-19 30 Jan 2015 3.2-8 30 Jan 2015 3.4-20 30 Jan 2015 3.2-9 30 Jan 2015 3.4-21 30 Jan 2015 3.2-10 30 Jan 2015 3.4-22 30 Jan 2015 3.2-11 30 Jan 2015 3.4-23 30 Jan 2015 3.2-12 30 Jan 2015 3.4-24 30 Jan 2015 3.2-13 30 Jan 2015 3.2-14 30 Jan 2015 3.2-15 30 Jan 2015 3.2-16 30 Jan 2015 3.2-17 30 Jan 2015 3.2-18 30 Jan 2015 3.2-19 21 Nov 2016 3.2-20 30 Jan 2015 3.2-21 30 Jan 2015 3.2-22 30 Jan 2015 3.2-23 30 Jan 2015 3.2-24 30 Jan 2015 3.2-25 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 3.3-6 30 Jan 2015 3.4.1 30 Jan 2015 3.4-2 30 Jan 2015 3.4-3 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 THIS PAGE I NT E N T ION A L L Y LEFT BLANK 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 AOM DASH 8-Q400 3.4-2 [Rev. 13] 30 JAN 2015 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 4.1-31 31 May 2011 4.1-32 31 May 2011 1 21 Nov 2016 4.1-33 31 May 2011 2 21 Nov 2016 4.1-34 31 May 2011 3 21 Nov 2016 4.1-35 31 May 2011 4 21 Nov 2016 4.1-36 31 May 2011 4.1-37 31 May 2011 4.1-38 31 May 2011 04 - Contents ToC 4-1 13 Apr 2012 4.1-39 31 May 2011 ToC 4-2 30 Oct 2015 4.1-40 31 May 2011 4.1-41 31 May 2011 4.1-42 31 May 2011 Chapter 4 4.0-1 31 May 2011 4.1-43 31 May 2011 4.1-1 31 May 2011 4.1-44 31 May 2011 4.1-2 31 May 2011 4.1-45 31 May 2011 4.1-3 31 May 2011 4.1-46 31 May 2011 4.1-4 31 May 2011 4.1-47 31 May 2011 4.1-5 31 May 2011 4.1-48 31 May 2011 4.1-6 13 Apr 2012 4.1-49 31 May 2011 4.1-7 13 Apr 2012 4.1-50 31 May 2011 4.1-8 13 Apr 2012 4.1-51 31 May 2011 4.1-9 13 Apr 2012 4.1-52 31 May 2011 4.1-10 13 Apr 2012 4.1-53 31 May 2011 4.1-11 13 Apr 2012 4.1-54 31 May 2011 4.1-12 13 Apr 2012 4.1-55 31 May 2011 4.1-13 13 Apr 2012 4.1-56 31 May 2011 4.1-14 13 Apr 2012 4.1-57 31 May 2011 4.1-15 13 Apr 2012 4.1-58 31 May 2011 4.1-16 13 Apr 2012 4.1-59 31 May 2011 4.1-17 13 Apr 2012 4.1-60 31 May 2011 4.1-18 31 May 2011 4.1-61 31 May 2011 4.1-19 31 May 2011 4.1-62 31 May 2011 4.1-20 31 May 2011 4.1-63 31 May 2011 4.1.21 31 May 2011 4.1-64 31 May 2011 4.1-22 31 May 2011 4.1-65 31 May 2011 4.1.23 31 May 2011 4.1-66 31 May 2011 4.1-24 31 May 2011 4.1-67 31 May 2011 4.1-25 31 May 2011 4.1-68 31 May 2011 4.1-26 31 May 2011 4.1-69 31 May 2011 4.1-27 31 May 2011 4.1-70 31 May 2011 4.1-28 31 May 2011 4.1-71 31 May 2011 4.1-29 31 May 2011 4.1-72 31 May 2011 4.1-30 31 May 2011 4.1-73 31 May 2011 AOM DASH 8-Q400 (METRIC) 04 LEP - Page 2 (Rev 18) 21 NOV 2016 CHAPTER 4 LIST OF EFFECTIVE PAGES 4.1-74 31 May 2011 4.1-117 31 May 2011 4.1-75 31 May 2011 4.1-118 31 May 2011 4.1-76 31 May 2011 4.1-119 31 May 2011 4.1-77 31 May 2011 4.1-120 31 May 2011 4.1-78 31 May 2011 4.1-121 31 May 2011 4.1-79 31 May 2011 4.1-122 31 May 2011 4.1-80 31 May 2011 4.1-123 31 May 2011 4.1-81 31 May 2011 4.1-124 31 May 2011 4.1-82 31 May 2011 4.1-125 31 May 2011 4.1-83 31 May 2011 4.1-126 31 May 2011 4.1-84 31 May 2011 4.1-127 31 May 2011 4.1-85 31 May 2011 4.1-128 31 May 2011 4.1-86 31 May 2011 4.1-129 31 May 2011 4.1-87 31 May 2011 4.1-130 31 May 2011 4.1-88 31 May 2011 4.1-131 31 May 2011 4.1-89 31 May 2011 4.1-132 31 May 2011 4.1-90 31 May 2011 4.1-133 31 May 2011 4.1-91 31 May 2011 4.1-134 31 May 2011 4.1-92 31 May 2011 4.1-135 31 May 2011 4.1-93 31 May 2011 4.1-136 31 May 2011 4.1-94 31 May 2011 4.1-137 31 May 2011 4.1-95 31 May 2011 4.1-138 31 May 2011 4.1-96 31 May 2011 4.1-139 31 May 2011 4.1-97 31 May 2011 4.1-140 31 May 2011 4.1-98 31 May 2011 4.1-141 31 May 2011 4.1-99 31 May 2011 4.1-142 31 May 2011 4.1-100 31 May 2011 4.1-143 31 May 2011 4.1-101 31 May 2011 4.1-144 31 May 2011 4.1-102 31 May 2011 4.1-145 31 May 2011 4.1-103 31 May 2011 4.1-146 31 May 2011 4.1-104 31 May 2011 4.1-147 31 May 2011 4.1-105 31 May 2011 4.1-148 31 May 2011 4.1-106 31 May 2011 4.1-149 31 May 2011 4.1-107 31 May 2011 4.1-150 31 May 2011 4.1-108 31 May 2011 4.1-151 07 Mar 2013 4.1-109 31 May 2011 4.1-152 07 Mar 2013 4.1-110 31 May 2011 4.1-153 07 Mar 2013 4.1-111 31 May 2011 4.1-154 31 May 2011 4.1-112 31 May 2011 4.1-155 31 May 2011 4.1-113 31 May 2011 4.1-156 31 May 2011 4.1-114 31 May 2011 4.1-157 31 May 2011 4.1-115 31 May 2011 4.1-158 31 May 2011 4.1-116 31 May 2011 4.1-159 31 May 2011 (METRIC) AOM DASH 8-Q400 CHAPTER 4 LIST OF EFFECTIVE PAGES 04 LEP - Page 3 (Rev 18) 21 NOV 2016 4.1-160 31 May 2011 4.1-203 13 Sep 2013 4.1-161 31 May 2011 4.1-204 13 Sep 2013 4.1-162 31 May 2011 4.2-1 13 Sep 2013 4.1-163 31 May 2011 4.2-2 13 Sep 2013 4.1-164 31 May 2011 4.2-3 31 May 2011 4.1-165 31 May 2011 4.2-4 31 May 2011 4.1-166 31 May 2011 4.2-5 31 May 2011 4.1-167 31 May 2011 4.2-6 31 May 2011 4.1-168 31 May 2011 4.2-7 31 May 2011 4.1-169 31 May 2011 4.2-8 31 May 2011 4.1-170 31 May 2011 4.2-9 13 Sep 2013 4.1-171 31 May 2011 4.2-10 31 May 2011 4.1-172 31 May 2011 4.3-1 31 May 2011 4.1-173 31 May 2011 4.3-2 31 May 2011 4.1-174 31 May 2011 4.3-3 31 May 2011 4.1-175 31 May 2011 4.3-4 31 May 2011 4.1-176 31 May 2011 4.3-5 31 May 2011 4.1-177 31 May 2011 4.3-6 31 May 2011 4.1-178 31 May 2011 4.3-7 31 May 2011 4.1-179 31 May 2011 4.3-8 31 May 2011 4.1-180 31 May 2011 4.3-9 31 May 2011 4.1-181 31 May 2011 4.3-10 31 May 2011 4.1-182 31 May 2011 4.3-11 31 May 2011 4.1-183 31 May 2011 4.3-12 31 May 2011 4.1-184 31 May 2011 4.3-13 31 May 2011 4.1-185 31 May 2011 4.3-14 31 May 2011 4.1-186 31 May 2011 4.3-15 31 May 2011 4.1-187 31 May 2011 4.3-16 31 May 2011 4.1-188 31 May 2011 4.3-17 31 May 2011 4.1-189 31 May 2011 4.4-1 31 May 2011 4.1-190 31 May 2011 4.4-2 31 May 2011 4.1-191 31 May 2011 4.4-3 31 May 2011 4.1-192 31 May 2011 4.4-4 31 May 2011 4.1-193 31 May 2011 4.4-5 31 May 2011 4.1-194 31 May 2011 4.4-6 31 May 2011 4.1-195 31 May 2011 4.4-7 31 May 2011 4.1-196 31 May 2011 4.4-8 31 May 2011 4.1-197 31 May 2011 4.4-9 31 May 2011 4.1-198 31 May 2011 4.4-10 31 May 2011 4.1-199 31 May 2011 4.4-11 31 May 2011 4.1-200 13 Sep 2013 4.4-12 31 May 2011 4.1-201 13 Sep 2013 4.4-13 31 May 2011 4.1-202 13 Sep 2013 4.4-14 31 May 2011 AOM DASH 8-Q400 (METRIC) 04 LEP - Page 4 (Rev 18) 21 NOV 2016 CHAPTER 4 LIST OF EFFECTIVE PAGES 4.4-15 31 May 2011 4.6-7 31 May 2011 4.4-16 31 May 2011 4.6-8 31 May 2011 4.4-17 31 May 2011 4.6-9 31 May 2011 4.4-18 31 May 2011 4.6-10 31 May 2011 4.4-19 07 Mar 2013 4.6-11 31 May 2011 4.4-20 13 Sep 2013 4.6-12 31 May 2011 4.4-21 13 Sep 2013 4.6-13 31 May 2011 4.4-22 07 Mar 2013 4.6-14 31 May 2011 4.5-1 31 May 2011 4.6-15 31 May 2011 4.5-2 31 May 2011 4.6-16 31 May 2011 4.5-3 31 May 2011 4.6-17 31 May 2011 4.5-4 31 May 2011 4.6-18 31 May 2011 4.5-5 31 May 2011 4.6-19 31 May 2011 4.5-6 31 May 2011 4.6-20 07 Mar 2016 4.5-7 31 May 2011 4.7-1 21 Nov 2016 4.5-8 31 May 2011 4.7-2 21 Nov 2016 4.5-9 31 May 2011 4.8-1 21 Nov 2011 4.5-10 31 May 2011 4.8-2 21 Nov 2011 4.5-11 31 May 2011 4.8-3 21 Nov 2011 4.5-12 31 May 2011 4.8-4 21 Nov 2011 4.5-13 31 May 2011 4.9-1 31 May 2011 4.5-14 31 May 2011 4.9-2 31 May 2011 4.5-15 31 May 2011 4.9-3 31 May 2011 4.5-16 31 May 2011 4.9-4 31 May 2011 4.5-17 31 May 2011 4.9-5 31 May 2011 4.5-18 31 May 2011 4.9-6 31 May 2011 4.5-19 31 May 2011 4.10-1 30 Oct 2015 4.5-20 31 May 2011 4.10-2 31 May 2011 4.5-21 31 May 2011 4.10-3 31 May 2011 4.5-22 31 May 2011 4.10-4 30 Oct 2015 4.5-23 31 May 2011 4.10-5 30 Oct 2015 4.5-24 31 May 2011 4.10-6 30 Oct 2015 4.5-25 13 Apr 2012 4.10-7 30 Oct 2015 4.5-26 13 Apr 2012 4.10-8 30 Oct 2015 4.5-27 13 Apr 2012 4.10-9 30 Oct 2015 4.5-28 13 Apr 2012 4.10-10 30 Oct 2015 4.5-29 13 Apr 2012 4.10-11 30 Oct 2015 4.6-1 31 May 2011 4.11-1 31 May 2011 4.6-2 31 May 2011 4.12-1 31 May 2011 4.6-3 31 May 2011 4.6-4 31 May 2011 4.6-5 31 May 2011 4.6-6 31 May 2011 (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 22