AIRPLANE
OPERATIONS
MANUAL
AEROLITORAL, S.A. de C.V.
Bulletin No.:
Date :
Insert in Front of :
Effectivity :
AOM CODE Applicable :
01/18
20-FEB-18
Vol 1 – RBC
20-FEB-18
016
TEMPORAL REVISIONS EMBRAER
El presente tiene la finalidad de transmitir las siguientes revisiones temporales de
Embraer:
RECORD OF TEMPORARY REVISIONS
AOM-1502-016
TR 23.1 ........................................... OCT 30, 2017
TR 23.2 ........................................... NOV 30, 2017
TR 23.3 ............................................ JAN 26, 2018
Las cuales contienen las siguientes actualizaciones:
TR 23.1
- Block 8-30
INTERIOR ARRANGEMENTS
Added passenger cabin layout and balance arms applicable to
EMBRAER 190 AEROREPUBLICA Configuration.
- Block 11-05
EQUIPMENT CHECKLIST
Added emergency equipment configuration applicable to
EMBRAER 190 AEROREPUBLICA Configuration.
- Block 11-06
EMERGENCY EQUIPMENT PLAN VIEW
Included information of total number of passenger life vests for airplanes with NAC FAA PostMod. SB 0190-25-0122 configuration.
Added emergency equipment plan view applicable to EMBRAER 190 AEROREPUBLICA
Configuration.
- Block 11-08
PASSENGER OXYGEN MASKS LOCATION
Added configuration regarding the oxygen masks quantity and location applicable to
EMBRAER 190 AEROREPUBLICA Configuration.
NOTE:
Actual seat configuration and emergency equipment configuration is document in the
Manual de Despacho and Manual de Operaciones de Vuelo of the Company.
Bulletin 01/18
AOM CODE-016
Page 1/2
AIRPLANE
OPERATIONS
MANUAL
AEROLITORAL, S.A. de C.V.
TR 23.2
- Block 3-05:
Updated Power Up procedure due to Hydraulic PBIT changes on LOAD 25.7.
- Block 13-60:
Updated FLT CTRL BIT EXPIRED and FLT CTRL NO DISPATCH procedures due to Hydraulic
PBIT changes on LOAD 25.7.
NOTE:
Actual EPIC LOAD installed in each airplane can be consult in Master List of Current
Software and Hadware issued into AIT.
TR 23.3
- Block 2-40:
Updated the structure and the content of the limitation description to clearly state that
operation with T/O-2 and T/O-3 thrust modes are approved Derated Takeoff Thrust
procedures and to distinguish which statements are applicable to this kind of operation.
Updated Noise Levels according to AFM.
- Block 2-56:
Added ADS-B Out Statement of Compliance.
- Block 3-11:
Added one note to inform the conditions that allow one additional attempt for engine start.
NOTE:
ADS-B will be gradually incorporate in all fleet during 2018-2020.
Temporary revision pages are printed in yellow paper. They will be incorporated in the Revision
24 of AOM.
A T E N T A M E N T E
Cap. Antonio Gomez Iturbide
Ing. Benjamín Martínez Martínez
Jefe de Equipo E-JETS
E-JETS Fleet Chief
Gte. de Ingeniería de Operaciones
Operatios Engineering Director
BGM
Page 2/2
AOM CODE-016
Bulletin 01/18
AIRPLANE
OPERATIONS
MANUAL
REVISIONS AND BULLETINS
CONTROL
AEROLITORAL, S.A. de C.V.
AOM
REVISIONS CONTROL
REVISION
NUMBER
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DEC 10, 2003
FEB 20, 2004
MAY 31, 2004
DEC 23, 2004
SEP 05, 2005
JUL 28, 2006
MAY 15, 2007
SEP 28, 2007
APR 29, 2008
JUL 15, 2008
OCT 31, 2008
AUG 03, 2009
APR 30, 2010
SEP 30, 2010
MAY 30, 2011
SEP 19, 2011
JUL 16, 2012
JUL 02, 2013
JUL 02, 2014
OCT 17, 2014
MAY 04, 2015
OCT 20, 2016
FEB 13, 2017
MAY 13, 2017
DEC 01, 2017
BULLETINS CONTROL
BULLETIN
NUMBER
01/17
01/18
02/18
Revision 23.1
IN FRONT OF
DATE
CANCELED
DATE
3-07 PAGE 1
1°-JUL-17
Vol 1 - RBC
20-FEB-18
APPLICABLE ONLY AOM CODE 008
Vol. 1 - RBC
AOM CODE-016
Page 1
REVISIONS AND BULLETINS
CONTROL
AIRPLANE
OPERATIONS
MANUAL
AEROLITORAL, S.A. de C.V.
INTENTIONALLY BLANK
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Vol. 1 - RBC
AOM CODE-016
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AIRPLANE
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MANUAL
LIST OF EFFECTIVE PAGES
AEROLITORAL, S.A. de C.V.
AOM VOL 1
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AOM CODE-016
Page 1
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Vol. 1 - LEP
AOM CODE-016
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OPERATIONS
MANUAL
LIST OF EFFECTIVE PAGES
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Revision 23.1
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AOM CODE-016
Page 3
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Vol. 1 - LEP
AOM CODE-016
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OPERATIONS
MANUAL
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Revision 23.1
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Vol. 1 - LEP
AOM CODE-016
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MANUAL
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AOM CODE-016
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Page 14
Vol. 1 - LEP
AOM CODE-016
Revision 23.1
AIRPLANE
OPERATIONS
MANUAL
TABLE OF CONTENTS
AOM-1502-016
VOLUME 1
TABLE OF CONTENTS
SECTION 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
SECTION 2
LIMITATIONS
SECTION 3
NORMAL PROCEDURES
SECTION 4
EMERGENCY AND ABNORMAL
PROCEDURES
SECTION 5
PERFORMANCE
SECTION 6
FLIGHT PLANNING
SECTION 7
WEIGHT AND BALANCE
SECTION 8
LOADING
SECTION 9
CONFIGURATION DEVIATION LIST
SECTION 10
MINIMUM EQUIPMENT LIST
SECTION 11
EMERGENCY INFORMATION
SECTION 12
EMERGENCY EVACUATION
SECTION 13
GROUND SERVICING
Vol.1-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Table of Contents
Page 1
TABLE OF CONTENTS
AIRPLANE
OPERATIONS
MANUAL
Vol.1-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 9
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
SECTION 1
GENERAL INFORMATION AND DEFINITION OF TERMS
TABLE OF CONTENTS
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General Information............................................. 1-01 ...........
GENERAL.............................................................. 1-01 ...........
REVISIONS............................................................ 1-01 ...........
TEMPORARY REVISIONS.................................... 1-01 ...........
LIST OF EFFECTIVE PAGES............................... 1-01 ...........
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AOM-1502-016
Effectivity range to which this information is applicable
EFFECTIVITY........................................................ 1-01 ...........
OPERATIONAL REQUIREMENTS AND THE
AIRPLANE OPERATIONS MANUAL............... 1-01 ...........
EMBRAER AIRPLANE OPERATIONS MANUAL. . 1-01 ...........
AIRPLANE OPERATIONS MANUAL
STRUCTURE................................................... 1-01 ...........
2
Definition of Terms.............................................. 1-10 ...........
DEFINITION OF TERMS....................................... 1-10 ...........
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Abbreviations and Acronyms............................. 1-20 ...........
ABBREVIATIONS AND ACRONYMS.................... 1-20 ...........
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Units Conversion................................................. 1-25 ...........
UNITS CONVERSION........................................... 1-25 ...........
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SERVICE BULLETIN TABLE................................. 1-35 ...........
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1-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 10
Table of Contents
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
1-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 10
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
GENERAL
This Airplane Operations Manual provides useful information to
complement the Airplane Flight Manual, Weight and Balance Manual
and the Master Minimum Equipment List. It must be used in conjunction
with those publications to safe and efficiently operate the airplane.
Any difference found between the data in the Airplane Operations Manual
and the approved manuals is attributable to airplane modifications and
scheduling of amendments to publications. In the event of such a
difference, the data contained in the approved manuals must prevail.
REVISIONS
Embraer may periodically revise this manual as required to update
information or to provide information not available at the time of last
issue. Revised data may result from either airplane modifications or
improved techniques gained through operational experience.
Changes to the content are indicated by a vertical line in the outside
page margin, at the direction of revised text, graphic or table. A deleted
text, graph or table is marked by a vertical line in the outside margin, at
the direction of immediate previous line. A deleted table row is marked
by a vertical line in the outside margin, at the direction of immediate next
row.
For relocated or rearranged contents, the vertical line marker is drawn
adjacent to the page number.
The basic issue date of this Manual is presented on the title page.
Subsequent revisions are sequentially numbered (Revision 1, Revision
2, and so forth). The last Revision number is presented on the title page
and on the footer of every page affected, replacing the former number.
AOM-1502-016
The status of each page is presented in the List of Effective Pages
(LEP).
1-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
General Information
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
TEMPORARY REVISIONS
Temporary revisions may be issued when the need arises.
The temporary revision pages will be clearly identified and they are to be
inserted adjacent to the affected page.
Temporary revisions description are presented at the Log of Temporary
Revisions. Temporary revision pages status is not included in the List of
Effective Pages.
Temporary revision pages shall be removed when the changed content
is either incorporated or canceled by a Revision.
LIST OF EFFECTIVE PAGES
A List of Effective Pages (LEP) for all the sections is located at the
beginning of this Manual. The LEP presents the list of revision numbers
with the corresponding revision date, as well as the roll of pages with the
current revision number.
The LEP is updated at every revision, and it is the reference to verify
each Manual page for its proper updating status.
EFFECTIVITY
!Effectivity range to which this information is applicable
Texts, tables and graphics applicable to a specific airplane range are
identified by: a preceding start tag and text (presented in a different font
type) and an end tag at the final of the marked element. This paragraph
constitutes an example of effectivity text.
SUB-EFFECTIVITY
!!Sub-effectivity range to which this information is applicable
When the information is applicable to a specific range within a marked
range, they are identified by: a double start tag and text and a double
end tag at the final of the marked element. This paragraph constitutes
an example of sub-effectivity text.
1-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
General Information
REVISION 17
AOM-1502-016
""
"
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
OPERATIONAL REQUIREMENTS AND
AIRPLANE OPERATIONS MANUAL
THE
The existence of fleets composed of airplanes or other aircraft types
built by different manufacturers, led the Airworthiness Authorities to
require operators’ certification, in addition to the airplane’s certification.
The idea is to standardize manuals, training and operation, so as to
make it easier for a pilot to change equipment. As an example, if a pilot
used to fly an EMBRAER airplane (ERJ-145) is scheduled to fly another
EMBRAER airplane (EMBRAER 170/175/190/195), the training syllabus
required for both airplane families/models needs to be very similar; the
operator’s normal, abnormal and emergency procedures presentation
must be similar for all airplanes even when there are different AFMs with
different presentation for those procedures, as well as the manuals for
both airplanes. By doing so, the operator will assure that human
factors/errors are minimized.
Some Operation Requirements just define the main subjects that must
be presented in an Airplane Operations Manual. However, even detailing
the AOM at that level, all the requirements let the operators free to use
different Airplane Operations Manual structures, depending on the
manuals that have been already issued.
Therefore, EMBRAER has developed this AOM in an attempt to cover,
in the best possible manner, the most currently used requirements. By
doing so, it is possible for an operator to use the EMBRAER AOM by just
adding some missing information that is specific to that operator. Below
is a suggested Airplane Operations Manual structure to comply with
most of the Operation Requirements:
PART A
Presents operator’s administrative information, such as who are the
president, vice-president, the managers, who is the chief pilot for the
fleet, who is the responsible for revising manuals, where the offices and
bases are located, etc.
PART B
AOM-1502-016
Presents airplane related information, such as procedures, performance,
dispatch, Weight and Balance, bulletins and systems description.
1-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
General Information
Page 3
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
PART C
Presents the operator’s airport and route information (performance and
navigation).
PART D
Presents training information.
EMBRAER AIRPLANE OPERATIONS MANUAL
This Embraer Airplane Operations Manual covers only Part B. Parts A
and D should be generated by the operator only. Part C can be generated
by the operator with the help of Embraer operations softwares (runway
analysis, driftdown, and route analysis).
AIRPLANE OPERATIONS MANUAL STRUCTURE
The Embraer Airplane Operations Manual is organized in two volumes,
with the following contents:
Volume 1:
– 1 General
– 2 Limitations
– 3 Normal Procedures
– 4 Emergency and Abnormal Procedures
– 5 Performance
– 6 Flight Planning
– 7 Weight and Balance
–
–
–
–
–
8 Loading
9 Configuration Deviation List
10 Minimum Equipment List
11 Emergency Information
12 Emergency Evacuation
Volume 2:
– 14-01 Airplane Description
– 14-02 Air Management System
– 14-03 Automatic Flight
1-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
General Information
REVISION 17
AOM-1502-016
– 13 Ground Servicing
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
– 14-04 Auxiliary Power Unit
– 14-05 Electrical
– 14-06 Engine
– 14-07 Fire Protection
– 14-08 Flight Controls
– 14-09 Flight Instruments, Communication, Navigation and Flight
Management System
– 14-10 Fuel
– 14-11 Hydraulic
–
–
–
–
14-12
14-13
14-14
14-15
Ice and Rain Protection
Landing Gear and Brakes
Oxygen
Warning System
Each of the above sections may be divided into smaller parts, called
blocks. The number of the section followed by a two-digit number
identifies such blocks.
For example:
Section 14-03 can be divided as follows:
– 14-03-01 General Description
– 14-03-05 Controls and Indications
– 14-03-10 Flight Guidance Control System
– 14-03-20 Thrust Management
– 14-03-30 EICAS Messages
AOM-1502-016
The page numbering restarts at each block.
1-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
General Information
Page 5
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
1-01
Copyright © by Embraer. Refer to cover page for details.
Page 6
General Information
REVISION 17
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
DEFINITION OF TERMS
The following definitions apply to the terms below:
WARNING: OPERATING PROCEDURES, TECHNIQUES AND
OTHER RELATED INFORMATION, WHICH MAY RESULT
IN PERSONAL INJURY OR LOSS OF LIFE, IF NOT
FOLLOWED.
CAUTION: OPERATING PROCEDURES, TECHNIQUES AND OTHER
RELATED INFORMATION, WHICH MAY RESULT IN
DAMAGE OR DESTRUCTION OF EQUIPMENT, IF NOT
FOLLOWED.
Cautionary operating range: Cautionary operating range may indicate a
potential hazard or system malfunction.
AOM-1502-016
NOTE: Operating procedures, techniques and other related information,
which are considered essential to emphasize the safety of flight.
1-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 18
Definition of Terms
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
1-10
Copyright © by Embraer. Refer to cover page for details.
Page 2
Definition of Terms
REVISION 18
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
ABBREVIATIONS AND ACRONYMS
ABBREVIATION
°
°C
°F

A
A/C
A/I
ABC
ABM
ABV
AC
ACARS
AOM-1502-016
ACE
ACMP
ACN
ACP
ACT
ADA
ADC
ADF
ADI
ADS
ADSP
AEO
AFCS
AFE
AFM
AFT
AFU
AGL
AICC
AIOP
DESCRIPTION
Degree
Degree Celsius
Degree Fahrenheit
Liter
Ampere
Aircraft
Anti-Ice
Auxiliary Power Unit Start Bus Contactor
Auto Brake Control Module
Auxiliary Power-Unit Bleed-Valve
Advisory Circular
Aircraft Communication Addressing and
Reporting System
Actuator Control Electronics
Alternating-Current Motor-Driven Pump
Aircraft Classification Number
Audio Control Panel
Altitude Compensated Tilt
Air Data Application
Air Data Computer
Automatic Direction Finder
Attitude Director Indicator
Air Data System
Air Data Smart Probe
All Engines Operative
Automatic-Flight Control System
Above Field Elevation
Airplane Flight Manual
Afterward
Artificial Feel Unit
Above Ground Level
Auxiliary Integrated Control Center
Actuator Input-Output Processor
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 1
ABBREVIATION
AIP
ALD
ALT
AMI
AMM
AMS
ANR
AOA
AOC
AOD
AOM
AP
APM
APP
APPR
APR
APU
ARINC
ARM
ASC
ASCB
ASEL
ASTM
AT
ATC
ATIS
ATS
ATTCS
ATTND
AUTO
AVAIL
AVNX
AVOD
AZFW
B-RNAV
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Aeronautical Information Publication
Actual Landing Distance
Altitude
Airline Modifiable Information
Aircraft Maintenance Manual
Air Management System
Automatic Navigation Realignment
Angle of Attack
Airline Operational Communications
Audio on Demand
Airplane Operations Manual
Autopilot
Aircraft Personality Module
Approach
Approach
Approach
Auxiliary Power Unit
Aeronautical Radio Incorporated
Armed
APU Start Contactor
Avionics Standard-Communication Bus
Altitude Select
American Society of Testing Material
Autothrottle
Air Traffic Control
Automatic-Terminal-Information Service
Air Turbine Starter
Automatic Takeoff-Thrust Control-System
Attendant
Automatic
Available
Avionics
Audio and Video on Demand
Actual Zero Fuel Weight
Basic Required Navigation
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 2
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
BARO
BATT
BC
BCM
BEW
BFO
BIT
BITE
BOD
BRG
BRK
BRT
BTC
CAB
CAFM
CAGE
CAS
CAT I
CAT II
CAT III
CB
CCD
CDI
CDL
CFR
CG
CGD
CH
CKPT
CLB
CLR
cm
CMC
CMD
CMF
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Barometric Setting
Battery
Back Course
Brake Control Module
Basic Empty Weight
Beat Frequency Oscillator
Built-in Test
Built-in Test Equipment
Bottom of Descent
Bearing
Brake
Bright
Bus Tie Contactor
Cabin
Computerized Airplane Flight Manual
Commercial and Government Entity
Calibrated Airspeed
Category I Operation
Category II Operation
Category III Operation
Circuit Breaker
Cursor Control Device
Course Deviation Indicator
Configuration Deviation List
Code of Federal Regulations
Center of Gravity
Corrected Ground Distance
Channel
Cockpit
Climb
Clear
Centimeter
Central Maintenance Computer
Command
Communications Management Function
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 3
ABBREVIATION
CMS
COMM
CON
COND
CPC
CPCS
CPDLC
CRS
CRZ
CSS
CTRL
CVR
D-ROT
DB
DC
DDPM
DET
DGRAD
DH
DIM
DISC
DLK
DME
DMU
DN
DO
DOW
DR
DSU
DU
DVDR
E-BAY
EADI
EBV
ECAFM
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Configuration Management System
Communications
Continuous
Conditioning
Cabin Pressure Controller
Cabin Pressure Control-System
Controller Pilot Datalink Communication
Course
Cruise
Cabin Surveillance System
Control
Cockpit Voice Recorder
De-rotation
Database
Direct Current
Dispatch Deviation Procedures Manual
Detector
Degraded
Decision Height
Dimmer
Disconnect
Datalink
Distance Measuring Equipment
Data-Loader Management Unit
Down
RTCA Document
Dry Operating Weight
Dead Reckoning
Digital Server Unit
Display Unit
Digital Voice-Data Recorder
Electronic Bay
Electronic Attitude Director Indicator
Engine Bleed Valve
Electronic Computerized AFM
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 4
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
ECEF
ECL
ECS
EDP
EDS
EDU
EFB
EGPWM
EGPWS
EGT
EHSI
EICAS
EICC
ELPU
ELT
EMERG
ENG
EPNL
EPU
ESS
ESU
ETA
ETC
ETE
ETP
FAA
FADEC
FAF
FAP
FAR
FAWP
FBW
FCM
FCOC
FCP
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Earth-Centered Earth-Fixed
Electronic Checklist
Environmental Control System
Engine Driven Pump
Electronic Display System
Electronic Display Unit
Electronic Flight Bag
Enhanced Ground-Proximity Warning-Module
Enhanced Ground-Proximity Warning-System
Exhaust Gas Temperature
Electronic Horizontal Situation-Indicator
Engine Indication and Crew Alerting System
Emergency Integrated Control Center
Emergency Lights Power Unit
Emergency Locator Transmitter
Emergency
Engine
Effective Perceived Noise Level
Estimated Position Uncertainty
Essential
Ethernet Switching Unit
Estimated Time of Arrival
Elevator Thrust Compensation
Estimated Time Enroute
Equal Time Point
Federal Aviation Authority
Full-Authority Digital Electronic-Control
Final Approach Fix
Flight Attendant Panel
Federal Aviation Regulations
Final Approach Waypoint
Fly-by-wire
Flight Control Module
Fuel Cooled Oil Cooler
Flight Control Panel
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 5
ABBREVIATION
FCS
FCU
FCV
FD
FDR
FGCS
FIM
FIREX
FL
FLC
FLCH
FLEX
FMA
FMS
FMU
FOM
FPA
FPL
FPR
FSTN
ft
ft/min
ft3
FWD
g
G/A
G/S
GA
GB
GCU
GD
GEN
GMAP
GND
GNSS
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Flight Control System
Fuel Conditioning Unit
Flow Control Valve
Flight Director
Flight Data Recorder
Flight Guidance Control System
Fault Isolation Manual
Fire Extinguisher
Flight Level
Flight Level Change
Flight Level Change
Flexible
Flight Mode Annunciator
Flight Management System
Fuel Metering Unit
Figure of Merit
Flight Path Angle
Flight Plan
Flight Path Reference
Fasten
Foot
Foot per Minute
Cubic Foot
Forward
Gravity Acceleration
Go-Around
Glide Slope
Go Around
Gigabyte
Generator Control Unit
Ground Distance
Generator
Ground Map
Ground
Global Navigation Satellite System
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 6
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
GP
GPS
GPU
GPWS
GS
h
HDG
HDOP
HDPH
HF
HGS
HI
HP
hPa
HPU
AOM-1502-016
HS-ACE
HSA
HSI
HYD
Hz
I/O
IAF
IAS
IATA
IBIT
ICAO
ICC
iCMT
ID
IDG
IESS
IFE
IFR
IGN
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Guidance Panel
Global Positioning System
Ground Power Unit
Ground-Proximity Warning System
Glide Slope
Hour
Heading
Horizontal Dilution of Precision
Headphone
High Frequency
Head-up Guidance System
High
High Pressure
Hectopascal
High Pressure Unit
Horizontal-Stabilizer Actuator-Control
Electronics
Horizontal Stabilizer Actuator
Horizontal Situation Indicator
Hydraulic
Hertz
Input/Output
Initial Approach Fix
Indicated Air Speed
International Air Transport Association
Inflight Built In Test
International Civil Aviation Organization
Integrated Control-Center
Interactive Cabin Management Terminal
Identification
Integrated Drive Generator
Integrated Electronic Standby System
In Flight Entertainment
Instrument Flight Rules
Ignition
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 7
ABBREVIATION
ILS
in
in3
INBD
inHg
INHIB
INIT
INOP
INPH
INT
IRS
IRU
ISA
ITT
IU
IU/lb
KCAS
kg
kg/m2
KIAS
km
km/h
kPa
KPH
kt
kVA
LAN
LAT
LAV
lb
lb/ft2
lb/US gal
lb.in
lbf
LCD
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Instrument Landing System
Inch
Cubic Inch
Inboard
Inch of Mercury
Inhibition
Initialization
Inoperative
Interphone
Internal
Inertial Reference System
Inertial Reference Unit
International Standard Atmosphere
Interturbine Temperature
Index Unit
index Unit per Pound
Calibrated Airspeed in Knots
Kilogram
Kilogram per Square Meter
Indicated Airspeed in Knots
Kilometer
Kilometer per Hour
Kilopascal
Kilograms per Hour
Knot
Kilovolt-Ampere
Local Area Network
Latitude
Lavatory
Pound
Pound per Square Foot
Pound per Gallon
Pound Inch
Pound Force
Liquid-Crystal Display
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 8
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
LDA
LDG
LED
LEMAC
LFE
LG
LH
LICC
LIM
LNAV
LO
LOC
LOC-BC
LON
LP
LRC
LRM
LRU
LSA
LSK
LT
LVTO
m
m3
MAC
MAINT
MAN
MAP
MAU
MAX
MaxAT
mbar
MCDU
MDA
MEA
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Localizer Directional Aid
Landing Gear
Light-Emitting Diode
Leading Edge Aerodynamic Chord
Landing Field Elevation
Landing Gear
Left-Hand
Left Integrated Control Center
Limited Thrust
Lateral Navigation
Low
Localizer
Localizer-Back Course
Longitude
Low Pressure
Long Range Cruise
Line Replaceable Module
Line Replaceable Unit
Low Speed Awareness
Line Select Key
Light
Low Visibility Takeoff
Meter
Cubic Meter
Mean Aerodynamic Chord
Maintenance
Manual
Multiple Alarm Panel
Modular Avionics Unit
Maximum
Maximum Assumed Temperature
Milibar
Multifunction Control Display Unit
Minimum Descent Altitude
Minimum Enroute Altitude
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 9
ABBREVIATION
MEL
MEW
MFD
MHz
MIC
MID
min
MLG
MLS
MLW
mm
MMEL
MMO
MOW
MPEG
mph
MPP
MRC
MRW
MSA
MSL
MTOW
MTP
MZFW
N1
N2
NAD-83
NAS
NAV
NAVCOM
NBPT
NDB
NIC
NLG
NM
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Minimum Equipment List
Manufacture Empty Weight
Multi-Function Display
Megahertz
Microphone
Middle
Minute
Main Landing Gear
Microwave Landing System
Maximum Landing Weight
Millimeter
Master Minimum Equipment List
Maximum Mach Operation
Maximum Design Operating Weight
Moving Picture Experts Group
Mile per Hour
Maintenance Practices and Procedures
Modular Radio Cabinet
Maximum Ramp Weight
Minimum Safety Altitude
Mean Sea Level
Maximum Takeoff Weight
Maintenance Test Panel
Maximum Zero Fuel Weight
Fan Rotor Speed
Core Rotor Speed
North American Datum 1983
National Airspace System
Navigation
Navigation & Communication
No-Break Power Transfer
Non-Directional Beacon
Network Interface Controller
Nose Landing Gear
Nautical Miles
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 10
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
Notam
NPRV
NVM
OAT
OBV
ODS
OEI
OEW
OFV
OGV
OOOI
OUTBD
OVHT
OVRD
OVSP
OWE
OXY
P-ACE
P-RNAV
PA
PAMN
PAX
PBE
PBIT
PC
PCN
PCU
PDU
PED
Perf
PF
PFD
PIT
PLI
PM
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Notices to Airmen
Negative Pressure Relief Valve
Non-Volatile Memory
Outside Air Temperature
Operability Bleed Valve
Overheat Detection System
One Engine Inoperative
Operational Empty Weight
Outflow Valve
Outlet Guide Vane
Out, Off, On and In
Outboard
Overheat
Override
Overspeed
Overwing Emergency Exit
Oxygen
Primary Actuator Control Electronics
Precision Required Navigation
Passenger Address
Passenger Audio Matching Network
Passenger
Protective Breathing Equipment
Power Up Built in Test
Personal Computer
Pavement Classification Number
Passenger Control Unit
Power Drive Unit
Portable Electronic Device
Performance
Pilot Flying
Primary Flight Display
Pitch
Pitch Limit Indicator
Pilot Monitoring
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 11
ABBREVIATION
PMA
POS
PPH
PPOS
PPU
PRA
PRESN
PREV
PRI
PRN
PROX
PSEM
psi
psid
psig
PSU
PTT
PTU
PWR
QFE
QNH
QRH
QTY
RA
RAD
RAID
RAIM
RALT
RAM
RAMP
RAT
RCT
REACT
RECIRC
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Permanent Magnet Alternator
Position
Pounds per Hour
Present Position
Power Push Unit
Prerecorded Announcement
Pressurization
Previous
Primary
Pseudo-Random Noise
Proximity
Proximity Sensor Electronic Module
Pounds per Square Inch
Pound per Square Inch Differential
Pound per Square Inch Gauge
Passenger Service Unit
Push To Talk
Power Transfer Unit
Power
Local Station Barometric Pressure
Local Altimeter Setting
Quick Reference Handbook
Quantity
Resolution Advisory
Radio
Ram Air Inlet Door
Receiver Autonomous Integrity Monitor
Radio Altitude
Random Access Memory
Reliability Analysis and Motoring Program
Ram Air Turbine
Rain Echo Attenuation
Rain Echo Attenuation Compensation
Technique
Recirculation
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 12
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
REF.
RETD
REV
RH
RICC
RIPS
RLOUT
RNAV
RNP
rpm
RSV
RTA
RTO
RTS
RVSM
RWY
s
S-ACE
SAD
SAI
SAT
SATCOM
SB
SCV
SDF
SECT
SEL
SELCAL
SF-ACE
SFCL
SID
SLD
SMKG
SOV
SPD
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Reference
Retard
Reverse
Right-Hand
Right Integrated Control Center
Recorder Independent Power Supply
Roll Out
Area Navigation
Required Navigation Performance
Revolutions per Minute
Reserve
Receiver/Transmitter Antenna
Rejected Takeoff
Return To Service
Reduced Vertical Separation Minimum
Runway
Second
Spoiler Actuator-Control Electronics
Still Air Distance
Slat Anti-Ice
Static Air Temperature
Satellite Communications
Service Bulletin
Starter Control Valve
Simplified Directional Facility
Sector
Selector
Selective Call
Slat/Flap Actuator Control Electronics
Slat/Flap Control Lever
Standard Instrument Departures
Super Large Droplet
Smoking
Shutoff Valve
Speed
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 13
ABBREVIATION
SPDA
SPDE
SPDT
SPKR
SPS
SSPC
SSR
STAB
STAR
STBY
STD
SVC
SVDU
SW
SYS
T/O
T2
TA
TA/RA
TAS
TAT
TCAS
TCS
TDS
TEMP
TERM
TGL
TGT
TL
TLA
TMS
TO
TO/GA
TOC
TOD
AIRPLANE
OPERATIONS
MANUAL
DESCRIPTION
Secondary Power Distribution Assembly
Speed on Elevator
Speed on Thrust
Speaker
Stall Protection System
Solid State Power Controller
Secondary Surveillance Radar
Stabilizer
Standard Instrument Arrivals
Standby
Standard
Service
Smart Video Display Unit
Switch
System
Takeoff
Fan Inlet Temperature
Traffic Advisory
Traffic Advisory/ Resolution Advisory
True Airspeed
Total Air Temperature
Traffic Alert and Collision Avoidance System
Touch Control Steering
Takeoff Data Set
Temperature
Terminal
Temporary Guidance Leaflet
Target
Thrust Lever
Thrust Lever Angle
Thrust Management System
Takeoff
Takeoff/Go-Around
Top of Climb
Top of Descent
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 14
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
GENERAL INFORMATION AND
DEFINITION OF TERMS
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
ABBREVIATION
TOGA
TOW
TRS
TRU
TSO
TWIP
ULD
US gal
USB
UTC
V
V1
V2
VA
VAC
VALT
VAP
VAR
VARM
VASEL
VDC
VDOP
VDR
VEF
VFE
VFLCH
VFR
VFS
VGP
VHF
VLE
VLO
VLV
VMC
VMCA
GENERAL INFORMATION AND
DEFINITION OF TERMS
DESCRIPTION
Takeoff/Go Around
Takeoff Weight
Thrust Rating System
Transformer Rectifier Unit
Technical Standard Order
Terminal Weather Information for Pilots
Unfactored Landing Distance
Gallon
Universal Serial Bus
Universal Time Coordinated
Volt
Takeoff Decision Speed
Takeoff Safety Speed
Design Maneuvering Speed
Approach Climb Speed
VNAV Altitude Hold
Approach Speed
Variable
Vertical ARM
VNAV Altitude Select
Volt Direct Current
Vertical Dilution of Precision
VHF Data Radio
Critical Engine Failure Speed
Maximum Flaps Extended Speed
VNAV Flight Level Change
Visual Flight Rules
Final Segment Speed
VNAV Glide Path
Very High Frequency
Maximum Landing Gear Extended Speed
Maximum Landing Gear Operating Speed
Valve
Visual Meteorological Conditions
Minimum Control Speed in the Air
1-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Abbreviations and Acronyms
Page 15
GENERAL INFORMATION AND
DEFINITION OF TERMS
VREFXX
VS
VSI
VTA
W
WGS-84
WML
WOW
WRN
WSHR
WX
XBLEED
XFEED
XPDR
YD
DESCRIPTION
Minimum Control Speed on Ground
Minimum Control Speed During Landing
Maximum Operating Speed
Vertical Navigation
VHF Omnidirectional Range
VOR Localizer
VNAV Path
Rotation Speed
Reference Speed
Landing Reference Speed associated to the
flap setting XX
Stall Speed
Vertical Speed Indicator
Vertical Track Alert
Watt
World Geodetic System 1984
Windmilling
Weight-on-Wheels
Warning
Windshear
Weather Radar
Cross Bleed
Cross Feed
Transponder
Yaw Damper
1-20
Copyright © by Embraer. Refer to cover page for details.
Page 16
Abbreviations and Acronyms
REVISION 23
AOM-1502-016
ABBREVIATION
VMCG
VMCL
VMO
VNAV
VOR
VOR/LOC
VPATH
VR
Vref
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
UNITS CONVERSION
TO CONVERT
Degree Celsius
(°C)
Degree
Fahrenheit (°F)
Feet (ft)
Inches (in)
Inches of Mercury
(inHg)
Kilogram (kg)
Kilogram force per
Square meter
(kg/m2)
INTO
Degree
Fahrenheit (°F)
Degree Celsius
(°C)
Meter (m)
Millimeter (mm)
MULTIPLY BY
AND ADD
1.8000
+32
0.5556
-17.7778
0.3048
25.4000
–
–
Millibar (mbar)
33.8636
–
Pounds (lb)
2.2046
–
Pound per Square
Inch (psi)
0.0014
–
Kilometer (km)
Nautical Mile
(NM)
0.5399
–
Kilometer per
hour (km/h)
Knot (kt)
0.5399
–
1.852
–
0.4536
3.2808
–
–
0.0295
–
0.0394
–
1.852
–
703.0740
–
Knot (kt)
Pounds (lb)
Meter (m)
Millibar (mbar)
Millimeter (mm)
Nautical Mile
(NM)
Kilometer per
hour (km/h)
Kilogram (kg)
Feet (ft)
Inches of Mercury
(inHg)
Inches (in)
Kilometer (km)
AOM-1502-016
Kilogram force per
Pound per Square
Square meter
Inch (psi)
(kg/m2)
1-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 12
Units Conversion
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
1-25
Copyright © by Embraer. Refer to cover page for details.
Page 2
Units Conversion
REVISION 12
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
SERVICE BULLETIN TABLE
EMBRAER 190/195 models
SB
SB 190-00-0002
SB 190-00-0008
SB 190-00-0009
SB 190-00-0012
SB 190-00-0013
SB 190-21-0002
SB 190-23-0009
SB 190-24-0021
SB 190-31-0007
AOM-1502-016
SB 190-31-0009
SUBJECT
Installation of placard indicating
the Maximum Takeoff Weight
(MTOW) of 50000 kg.
Installation of placard indicating
the Maximum Takeoff Weight
(MTOW) of 46000 kg.
Installation of placard indicating
the Maximum Takeoff Weight
(MTOW) of 51800 kg.
Installation of placard indicating
the Maximum Takeoff Weight
(MTOW) of 47790 kg.
Installation of placard indicating
the Maximum Takeoff Weight
(MTOW) of 50300 kg.
Upgrade of AMS controller
operational software to black label
6.0 and replacement of the oxygen
cylinder servicing graphic placard.
Installation of Dual active HF (High
Frequency).
Modification of the electrical
connectors P0790 and P0791 of
SPDA 2
Update of Load 4.3 to Load 4.5
version of the PRIMUS EPIC
field-loadable software system into
the Primus Epic Integrated
Avionics System.
Update of Load 4.5 to Load 19.3
version of the PRIMUS EPIC
field-loadable software system into
the Primus Epic Integrated
Avionics System.
1-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Service Bulletins
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
SB 190-31-0015
SB 190-32-0006
SB 190-32-0022
SB 190-34-0010
SB 190-34-0015
SB 190-49-0001
SB 190-52-0013
SB 190-53-0040
SB 190-73-0004
SB 190-73-0010
SUBJECT
Update of current Load to Load
21.2 version of the PRIMUS EPIC
field-loadable software system into
the Primus Epic Integrated
Avionics System.
Installation of an Autobrake
electronic module in the MAU 2
channel A.
Installation of Nose Wheel
Steering Control Module new
version.
Upgrade of HGS software version
to 811.
Installation of HGS software 811
version
with
CAT
IIIa
functionalities.
Upgrade of APU FADEC software
version to FADEC 02.00.
Slide Mechanism Modification.
Replacement of the shear clip
rivets - cargo nets configuration
improvement.
Installation of placard in the cockpit
with new time limit for maximum
TO thrust.
Upgrade of engine FADEC
software version to 5.32.
1-35
Copyright © by Embraer. Refer to cover page for details.
Page 2
Service Bulletins
REVISION 17
AOM-1502-016
SB
AIRPLANE
OPERATIONS
MANUAL
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
EMBRAER 170/175 X 190/195
EMBRAER 170/175 and EMBRAER 190/195 models are classified as
common type rating, thus have a high level commonality and may use
almost the same AOM. The differences are customized in the manual
according to each airplane model and configuration. The following table
is presented to help identifying and finding the relevant differences
between models EMBRAER 170/175 and EMBRAER 190/195.
Difference
Section/
Subsection
Reference
Block
2-05
LIMITATIONS
Weight and
CG
Embraer
Embraer
170/175
190/195
Topic
MRW, MTOW, MLW and
SubTopic
–
–
–
–
–
–
Engine Parameter limits
ENGINE
–
Noise Levels
NOISE LEVELS
–
Ground Start ITT limitation
–
–
–
–
MZFW
2-05
LIMITATIONS
Weight and
Center of Gravity envelopes
CG
LIMITATIONS
LIMITATIONS
LIMITATIONS
Maximum Usable Fuel per
2-36
Tank/Unusable Fuel per
Fuel
Tank
2-40
Powerplant
2-40
Powerplant
NORMAL
3-11
PROCEDURES
Engine Start
NORMAL
3-16
Pitch Trim table for FD
PROCEDURES
Takeoff
inoperative
EMERGENCY
AND
ABNORMAL
PROCEDURES/
Abnormal landing factors for
4-01-01
ELECTRICAL SYSTEM
Smoke
FIRE OR SMOKE
procedure
SMOKE
ELECTRICAL
SYSTEM FIRE
–
OR SMOKE
EMERGENCY
AND
ABNORMAL
PROCEDURES/
AOM-1502-016
NON
4-02-01
Abnormal Landing factors
Non
for DUAL ENGINE
Annunciated
FAILURE procedure
DUAL ENGINE
FAILURE
–
ANNUNCIATED
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 1
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Section/
Subsection
Reference
Block
Embraer
Embraer
170/175
190/195
Sub-
Topic
Topic
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Non
Annunciated
Abnormal Landing factors
JAMMED
for JAMMED CONTROL
CONTROL
COLUMN - PITCH
COLUMN -
procedure
PITCH
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Abnormal Landing factors
JAMMED
Non
for JAMMED CONTROL
CONTROL
Annunciated
WHEEL - ROLL procedure
WHEEL - ROLL
Engine Airstart envelope
AIRSTART
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Non
ENGINE
Annunciated
–
ENVELOPE
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Abnormal Landing factors
LOSS OF
Non
for LOSS OF HYDRAULIC
HYDRAULIC
Annunciated
SYSTEM 1 procedure
SYSTEM 1
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Abnormal Landing factors
LOSS OF
Non
for LOSS OF HYDRAULIC
HYDRAULIC
Annunciated
SYSTEM 2 procedure
SYSTEM 2
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Non
Annunciated
Abnormal Landing factors
LOSS OF
for LOSS OF HYDRAULIC
HYDRAULIC
SYSTEM 1 AND 3
SYSTEM 1
procedure
AND 3
–
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 2
Airplane Models Differences
REVISION 23
AOM-1502-016
ANNUNCIATED
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Subsection
Reference
Block
Embraer
Embraer
170/175
190/195
Topic
SubTopic
EMERGENCY
AND
ABNORMAL
PROCEDURES/
NON
4-02-01
Non
Annunciated
Abnormal Landing factors
LOSS OF
for LOSS OF HYDRAULIC
HYDRAULIC
SYSTEM 2 AND 3
SYSTEM 2
procedure
AND 3
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-03
Autoflight
Abnormal Landing factors
for STALL PROT FAIL
STALL PROT
FAIL
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
Abnormal Landing factors
4-03-05
and Relevant Inoperative
ELEC
Electrical
Items list for ELEC
EMERGENCY
–
EMERGENCY procedure
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-05
Electrical
Relevant Inoperative Items
list for AC BUS 1 OFF
AC BUS 1 OFF
–
procedure
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-05
Electrical
Relevant Inoperative Items
list for AC ESS BUS OFF
AC ESS BUS
OFF
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-05
Electrical
Abnormal Landing factors
for DC BUS 1 OFF
DC BUS 1 OFF
–
DC BUS 2 OFF
–
procedure
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-05
Electrical
Abnormal Landing factors
for DC BUS 2 OFF
procedure
AOM-1502-016
ANNUNCIATED
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 3
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Section/
Subsection
Reference
Block
Embraer
Embraer
170/175
190/195
Sub-
Topic
Topic
EMERGENCY
AND
ABNORMAL
4-03-05
PROCEDURES/
Electrical
NON
Abnormal Landing factors
for DC ESS BUS 1 OFF
DC ESS BUS 1
OFF
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
Abnormal Landing factors
4-03-05
and Relevant Inoperative
DC ESS BUS 2
Electrical
Items list for DC ESS BUS
OFF
–
2 OFF procedure
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-05
Electrical
Relevant Inoperative Items
list for DC ESS BUS 3 OFF
DC ESS BUS 3
OFF
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
Flight Controls
Abnormal Landing factors
GROUND
for GROUND SPOILERS
SPOILERS
FAIL procedure
FAIL
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
Flight Controls
Abnormal Landing factors
SPOILERS
for SPOILERS NML MODE
NML MODE
FAIL procedure
FAIL
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
Flight Controls
Abnormal Landing factors
for ELEVATOR RH (LH)
FAIL procedure
ELEVATOR RH
(LH) FAIL
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
FLAP (SLAT) FAIL
FLAP (SLAT)
Flight Controls
performance table
FAIL
–
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 4
Airplane Models Differences
REVISION 23
AOM-1502-016
ANNUNCIATED
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Reference
Subsection
Block
Embraer
Embraer
170/175
190/195
Topic
SubTopic
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
Flight Controls
Abnormal Landing factors
for PITCH TRIM FAIL
PITCH TRIM
FAIL
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
4-03-08
Flight Controls
Abnormal Landing factors
for SPOILER FAULT
SPOILER
FAULT
procedure
–
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
ANNUNCIATED
EMERGENCY
AND
ABNORMAL
PROCEDURES/
AOM-1502-016
ANNUNCIATED
4-03-09
FMS/Nav/
Com & Flight
Instruments
4-03-09
FMS/Nav/
Com & Flight
Instruments
4-03-09
Abnormal Landing factors
for AVNX MAU 1A FAIL
AVNX MAU 1A
FAIL
procedure
Abnormal Landing factors
for AVNX MAU 1B FAIL
AVNX MAU 1B
FAIL
procedure
and Relevant Inoperative
AVNX MAU 2B
Com & Flight
Items list for AVNX MAU 2B
FAIL
Instruments
FAIL procedure
4-03-09
Com & Flight
Instruments
4-03-09
FMS/Nav/
Com & Flight
Instruments
–
Abnormal Landing factors
FMS/Nav/
FMS/Nav/
–
Abnormal Landing factors
for AVNX MAU 3A FAIL
AVNX MAU 3A
FAIL
procedure
Abnormal Landing factors
for AVNX MAU 3B FAIL
AVNX MAU 3B
procedure
FAIL
–
–
–
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 5
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Section/
Subsection
Reference
Block
Embraer
Embraer
170/175
190/195
Sub-
Topic
Topic
EMERGENCY
AND
4-03-12
Abnormal Landing factors
ABNORMAL
Ice and Rain
for A-I WING FAIL
PROCEDURES/
Protection
procedure
A-I WING FAIL
–
ANNUNCIATED
EMERGENCY
AND
4-03-13
Abnormal Landing factors
ABNORMAL
Landing Gear
for BRAKE LH (RH) FAIL
PROCEDURES/
and Brakes
procedure
BRAKE LH
(RH) FAIL
–
ANNUNCIATED
EMERGENCY
AND
4-03-13
Abnormal Landing factors
ABNORMAL
Landing Gear
for LG WOW SYS FAIL
PROCEDURES/
and Brakes
procedure
LG WOW SYS
FAIL
–
ANNUNCIATED
EMERGENCY
AND
4-03-13
Abnormal Landing factors
ABNORMAL
Landing Gear
for BRAKE LH (RH) FAULT
PROCEDURES/
and Brakes
procedure
5
Performance data
–
–
6
Flight Planning data
–
–
7
Weight and Balance data
–
–
–
–
BRAKE LH
(RH) FAULT
–
ANNUNCIATED
FLIGHT
PLANNING
WEIGHT AND
BALANCE
8-10
LOADING
External
Dimensions
External dimensions of the
airplane
8-10
LOADING
GROUND
External
Ground clearances
Dimensions
–
GRAPHIC
VERTICAL
8-10
LOADING
CLEARANCES
External
Ground clearances
Dimensions
GROUND
CLEARANCES
–
TABLE
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 6
Airplane Models Differences
REVISION 23
AOM-1502-016
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Subsection
LOADING
LOADING
LOADING
Reference
Block
cargo compartment door
Dimensions
clearances
8-30
Interior arrangement of
Interior
flight deck and passenger
Arrangement
cabin
8-30
Passenger balance arm and
Interior
furnishings and equipment
Arrangement
balance arms
Cargo
Cargo
Compartment
8-60
Cargo
Compartment
LOADING
EMERGENCY
INFORMATION
EMERGENCY
EVACUATION
190/195
External
8-60
LOADING
170/175
Passenger, service and
Compartment
LOADING
Embraer
8-10
8-60
LOADING
Embraer
Equipment
12-40
Doors and
Exits
–
–
AND LIMITS
Cargo compartments
DIMENSIONS
balance arms and volumes
AND LIMITS
Package size dimensions
PACKAGE
table
SIZE TABLES
positions
Emergency equipment
location
Emergency evacuation exits
for EMBRAER 190/195
GROUND
13-25
Fuel quantity according to
SERVICING
Fuel
magnetic level indication
GROUND
13-30
SERVICING
Engine Oil
–
–
DIMENSIONS
Cargo nets limitation and
SubTopic
–
dimensions
8-70
11-05
DOOR
CLEARANCES
Cargo compartments
Cargo Nets
Emergency
Topic
–
–
–
–
–
–
–
–
–
FUEL
MAGNETIC
–
LEVER
ENGINE OIL
Engine Oil Level Check
ENGINE OIL
LEVEL
SERVICING
CHECK -
AOM-1502-016
ENGINE
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 7
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Section/
Subsection
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
Reference
Block
Embraer
Embraer
170/175
190/195
14-01-05
Maximum seat capacity for
Airplane Basic
EMBRAER 190/195
Data
airplane models
14-01-05
Airplane Basic
Data
14-01-05
Airplane Basic
Data
–
EXTERNAL
DIMENSIONS
Antennas positioning along
AIRPLANE
the airplane
ANTENNAS
Main service points location
14-01-22
OWE door pictorial status
Controls and
page on MFD, for
Indications
EMBRAER 190/195
SYSTEMS
14-01-25
Electronic
AIRPLANE
Display
GENERAL
System (EDS)
–
airplane
MAIN SERVICE
POINTS
Data
DESCRIPTION/
Topic
External dimensions of the
14-01-05
Airplane Basic
Sub-
Topic
OWE door pictorial status
page on MFD, for
EMBRAER 190/195
SYNOPTIC
PAGE ON MFD
–
–
–
–
MULTI
FUNCTION
STATUS
DISPLAY
PAGE
(MFD)
WING
INSPECTION,
SYSTEMS
DESCRIPTION/
14-01-40
AIRPLANE
Lighting
Overwing emergency lights
EXTERNAL
LIGHTING
GENERAL
LOGOTYPE
AND
OVERWING
EMERGENCY
LIGHTS
DESCRIPTION/
14-01-40
Photoluminescent strips for
EMERGENCY
AIRPLANE
Lighting
EMBRAER 190/195
LIGHTING
GENERAL
PHOTOLUMINESCENT
STRIPS
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 8
Airplane Models Differences
REVISION 23
AOM-1502-016
SYSTEMS
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Subsection
Reference
Block
Embraer
Embraer
170/175
190/195
Topic
SYSTEMS
SubTopic
CARGO
DESCRIPTION/
14-01-40
Cargo compartment lights
AIRPLANE
Lighting
quantity and location
DESCRIPTION/
14-01-45
Overwing emergency exits
EMERGENCY
AIRPLANE
Doors
for EMBRAER 190/195
EXITS
COMPARTMENT
–
LIGHTS
GENERAL
SYSTEMS
–
GENERAL
SYSTEMS
DESCRIPTION/
AIRPLANE
GENERAL
14-01-80
EICAS messages
EICAS
applicable only for
Messages
EMBRAER 190/195
–
–
SYSTEMS
DESCRIPTION/
14-02-10
AIR
Bleed Air
MANAGEMENT
System
ENGINE
Engine bleed stage supply
and precooler
BLEED
–
SYSTEM
SYSTEM
SYSTEMS
DESCRIPTION/
AUTOMATIC
FLIGHT
14-03-10
Flight
Guidance
Control
Airplane pitch angle
FGCS
guidance for flaps 2
TAKEOFF
(TO)
System
SYSTEMS
DESCRIPTION/
14-03-10
Description of mach trim
AUTOMATIC
Mach Trim
function
–
–
FLIGHT
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
AOM-1502-016
ELECTRICAL
14-05-35
Electrical
Reading lights MID
Loads
Right/Left
Distribution
AC/DC
BUSSES LOAD
14-05-35
Electrical
Loads
AC/DC
Pitch Trim 1 Control
BUSSES LOAD
DISTRIBUTION
Distribution
DC BUS 2
DISTRIBUTION
DC ESS BUS
1
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 9
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Subsection
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
ELECTRICAL
SYSTEMS
DESCRIPTION/
ELECTRICAL
Reference
Block
Embraer
Embraer
170/175
190/195
14-05-35
Electrical
Right Smoke Detector
Loads
A3/F4 Cargo Bay
Distribution
Loads
AC/DC
DISTRIBUTION
AC/DC
Pitch Trim 2 Control
BUSSES LOAD
DISTRIBUTION
Distribution
14-05-35
Electrical
Loads
BUSSES LOAD
BUSSES LOAD
BUSSES LOAD
SYSTEMS
14-06-01
Engine model, graphic and
General
schematic for EMBRAER
ENGINE
Description
190/195
14-06-10
Engine Fuel
ENGINE
System
SYSTEMS
14-06-10
DESCRIPTION/
Engine Fuel
ENGINE
System
BUSSES LOAD
AC ESS BUS
DISTRIBUTION
DESCRIPTION/
SYSTEMS
AC BUS 2
AC/DC
Pitch Trim 2 AC power
Distribution
DESCRIPTION/
AC BUS 1
DISTRIBUTION
14-05-35
Loads
DC GND SVC
AC/DC
FAN AFT Avionics bay
Distribution
Electrical
3
DISTRIBUTION
14-05-35
Loads
DC ESS BUS
AC/DC
Pitch Trim 1 AC power
Distribution
Electrical
1
DISTRIBUTION
14-05-35
Loads
DC ESS BUS
AC/DC
AFT Lavatory Lights
Distribution
Electrical
Topic
BUSSES LOAD
14-05-35
Electrical
Sub-
Topic
Fuel system characteristics
Description of fuel flow into
the fuel pump
SYSTEMS
14-06-10
Variable
DESCRIPTION/
Engine Fuel
Geometric
ENGINE
System
Actuator
Variable
–
–
ENGINE FUEL
SYSTEM
FUEL PUMP
GENERAL
–
VARIABLE
Stator Vanes
STATOR
–
VANES
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 10
Airplane Models Differences
REVISION 23
AOM-1502-016
Section/
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Reference
Subsection
Block
SYSTEMS
14-06-10
DESCRIPTION/
Engine Fuel
ENGINE
System
SYSTEMS
14-06-15
DESCRIPTION/
Lubrication
ENGINE
System
14-06-20
SYSTEMS
Start and
DESCRIPTION/
Ignition
ENGINE
Embraer
170/175
190/195
Fuel schematic
Lubrication schematic
Logic to energize both
igniters
Topic
FUEL
SCHEMATIC
LUBRICATION
SCHEMATIC
IGNITION
SYSTEM
SubTopic
–
–
–
System
14-06-20
SYSTEMS
DESCRIPTION/
ENGINE
Start and
N2 speeds for ignition and
GROUND
Ignition
fuel flow during ground start
START
–
System
14-06-20
SYSTEMS
Start and
DESCRIPTION/
Ignition
ENGINE
System
N2 speeds for ignition and
fuel flow during IN FLIGHT
IN FLIGHT
START
START
–
14-06-30
SYSTEMS
DESCRIPTION/
ENGINE
Engine
Flexible takeoff reduction
FLEXIBLE
Control
limitation
TAKEOFF
–
System
14-06-30
SYSTEMS
DESCRIPTION/
ENGINE
Engine
Thrust ratings table for
Control
CF34-10E engines
System
ENGINE
THRUST
THRUST
RATINGS
RATINGS
TABLE
14-06-30
SYSTEMS
DESCRIPTION/
ENGINE
AOM-1502-016
Embraer
Engine
N2 speed for automatic
ENGINE
OVERSPEED
Control
engine shutdown
PROTECTION
PROTECTION
System
SYSTEMS
14-07-20
CARGO
DESCRIPTION/
Cargo
COMPARTMENT
FIRE
Compartment
PROTECTION
Fire Protection
Smoke detector quantity
SMOKE
–
DETECTION
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 11
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
Difference
Section/
Subsection
SYSTEMS
DESCRIPTION/
FLIGHT
CONTROLS
SYSTEMS
DESCRIPTION/
FLIGHT
CONTROLS
SYSTEMS
DESCRIPTION/
FLIGHT
CONTROLS
Reference
Block
Embraer
Embraer
170/175
190/195
14-08-05
Controls and
Sub-
Topic
Topic
SLAT/FLAP
SLAT/FLAP deflection
SELECTOR
Indications
–
LEVER
ROLL/
14-08-05
Controls and
Indications
PITCH/ YAW
Tic marks along pitch trim
EICAS
scale
INDICATIONS
TRIM
INDICATION
ON EICAS
14-08-10
FCS
Description
Mach Trim Function and
Configuration Trim
MODES OF
Compensation for
OPERATION
–
EMBRAER 190/195 only
SYSTEMS
ELEVATOR
TAIL STRIKE
CONTROL
AVOIDANCE
SYSTEM
(TSA)
DESCRIPTION/
14-08-15
Tail Strike Avoidance for
FLIGHT
Pitch Control
EMBRAER 190/195 only
DESCRIPTION/
14-08-15
Mach Trim for EMBRAER
STABILIZER
FLIGHT
Pitch Control
190/195 only
TRIM
2 water drains quantity
FUEL TANKS
–
Fuel Quantity
FUEL TANKS
–
CONTROLS
SYSTEMS
MACH TRIM
CONTROLS
14-10-10
Fuel System
FUEL
Description
SYSTEMS
14-10-10
DESCRIPTION/
Fuel System
FUEL
Description
SYSTEMS
14-10-10
DESCRIPTION/
Fuel System
FUEL
Description
SYSTEMS
14-10-15
DESCRIPTION/
EICAS
FUEL
Messages
Fuel LO LEVEL trigger
value
FUEL LOW
LEVEL
–
WARNING
Unusable fuel increase due
to fuel feed fault condition
–
–
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 12
Airplane Models Differences
REVISION 23
AOM-1502-016
SYSTEMS
DESCRIPTION/
AIRPLANE
OPERATIONS
MANUAL
GENERAL INFORMATION AND
DEFINITION OF TERMS
Difference
Section/
Subsection
SYSTEMS
DESCRIPTION/
HYDRAULIC
SYSTEMS
DESCRIPTION/
ICE AND RAIN
PROTECTION
SYSTEMS
DESCRIPTION/
ICE AND RAIN
PROTECTION
SYSTEMS
DESCRIPTION/
ICE AND RAIN
PROTECTION
SYSTEMS
DESCRIPTION/
LANDING GEAR
AOM-1502-016
AND BRAKES
Reference
Block
14-11-10
Hydraulic
System
Description
14-12-10
System
Description
Embraer
Embraer
170/175
190/195
Topic
SubTopic
EMBRAER 190/195
Hydraulic System 2
reservoir is bigger than
EMBRAER 170/175
HYDRAULIC
SYSTEM 2
HYDRAULIC
SYSTEM 2
RESERVOIR
hydraulic system 2 reservoir
Engine Anti
Engine Anti
Ice System
Ice System
Bleeds Air
Bleeds Air
from the
from the 5th
10th High
Low Stage
Stage Valve
Valve
ICE
PROTECTION
SYSTEM
ENGINE ANTI
ICE SYSTEM
14-12-10
System
Anti Ice System schematic
–
–
–
–
–
–
–
–
Description
EICAS
EICAS
14-12-20
message
EICAS
″A-I ENG 1
Messages
(2) LEAK″
Applicable
message
″A-I ENG 1
(2) LEAK″
Not
Applicable
14-13-05
Landing Gear Warning
Controls and
Inhibition reactivation TLA
Indication
values
SYSTEMS
14-13-25
DESCRIPTION/
Nosewheel
LANDING GEAR
Steering
AND BRAKES
System
Turning Radii
1-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Airplane Models Differences
Page 13
GENERAL INFORMATION AND
DEFINITION OF TERMS
AIRPLANE
OPERATIONS
MANUAL
1-40
Copyright © by Embraer. Refer to cover page for details.
Page 14
Airplane Models Differences
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
AOM-1502-016
Block
Page
Introduction.......................................................... 2-INTRO ....
1
Weight and CG..................................................... 2-05 ...........
WEIGHT................................................................. 2-05 ...........
LOADING............................................................... 2-05 ...........
CENTER OF GRAVITY ENVELOPE..................... 2-05 ...........
1
1
2
3
Operational Limitations....................................... 2-10 ...........
OPERATIONAL ENVELOPE.................................. 2-10 ...........
AIRSPEEDS........................................................... 2-10 ...........
MAXIMUM TIRE GROUND SPEED...................... 2-10 ...........
WIND LIMITATIONS............................................... 2-10 ...........
MAXIMUM RECOMMENDED CROSSWIND........ 2-10 ...........
KINDS OF OPERATION........................................ 2-10 ...........
MINIMUM CREW................................................... 2-10 ...........
MANEUVERING FLIGHT LOAD FACTORS.......... 2-10 ...........
RUNWAY................................................................ 2-10 ...........
TOWING................................................................. 2-10 ...........
1
1
2
5
5
5
5
6
6
6
6
Electronic Display................................................ 2-20 ...........
ELECTRONIC CHECKLIST................................... 2-20 ...........
1
1
Warning................................................................. 2-30 ...........
WARNING.............................................................. 2-30 ...........
1
1
Fuel........................................................................ 2-36 ...........
FUEL...................................................................... 2-36 ...........
FUEL SPECIFICATION.......................................... 2-36 ...........
FUEL ADDITIVES.................................................. 2-36 ...........
FUEL TANK TEMPERATURE................................ 2-36 ...........
CROSSFEED OPERATION................................... 2-36 ...........
1
1
1
1
1
1
2-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
Block
Page
Auxiliary Power Unit............................................ 2-38 ........... 1
APU SUNDSTRAND APS 2300............................ 2-38 ........... 1
APU STARTER LIMITS.......................................... 2-38 ........... 1
APU APPROVED OILS.......................................... 2-38 ........... 1
Powerplant............................................................ 2-40 ...........
ENGINE.................................................................. 2-40 ...........
STARTER............................................................... 2-40 ...........
ENGINE APPROVED OILS................................... 2-40 ...........
ENGINE THRUST.................................................. 2-40 ...........
NOISE LEVELS..................................................... 2-40 ...........
1
1
2
3
3
4
Pneumatic, Air Conditioning, Pressurization.... 2-48 ...........
PRESSURIZATION................................................ 2-48 ...........
1
1
Ice and Rain Protection....................................... 2-50 ...........
ICE AND RAIN PROTECTION.............................. 2-50 ...........
WINDSHIELD WIPER OPERATION...................... 2-50 ...........
1
1
2
Navigation, Communication, Autopilot.............. 2-56 ...........
NAVIGATION, COMMUNICATION AND
AUTOPILOT..................................................... 2-56 ...........
NAVIGATION EQUIPMENT................................... 2-56 ...........
INERTIAL REFERENCE SYSTEM........................ 2-56 ...........
1
CAT II Limitations................................................. 2-57 ...........
CAT II LIMITATIONS.............................................. 2-57 ...........
FLIGHT CONTROLS............................................. 2-57 ...........
AUTOPILOT SYSTEM........................................... 2-57 ...........
APPROACH AND LANDING FLAPS..................... 2-57 ...........
MAXIMUM WIND COMPONENTS........................ 2-57 ...........
DEMONSTRATED WIND COMPONENTS............ 2-57 ...........
1
1
1
1
2
2
2
Ozone Concentration........................................... 2-60 ...........
OZONE CONCENTRATION.................................. 2-60 ...........
1
1
Autoland................................................................ 2-61 ...........
AUTOLAND............................................................ 2-61 ...........
CENTER OF GRAVITY ENVELOPE..................... 2-61 ...........
OPERATIONAL LIMITATIONS............................... 2-61 ...........
LANDING FLAPS................................................... 2-61 ...........
1
1
1
1
2
2-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
1
1
1
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
AOM-1502-016
Block
Page
MINIMUM EQUIPMENT REQUIRED.................... 2-61 ........... 3
Flight Management System................................ 2-64 ...........
FLIGHT MANAGEMENT SYSTEM........................ 2-64 ...........
GENERAL LIMITATIONS....................................... 2-64 ...........
NAVIGATION LIMITATIONS.................................. 2-64 ...........
APPROACH LIMITATIONS.................................... 2-64 ...........
1
1
5
5
8
Electronic Flight Bag (EFB)................................ 2-66 ...........
ELECTRONIC FLIGHT BAG (EFB)....................... 2-66 ...........
APPROVAL OF THE APPLICATIONS AND
PROCEDURES TO MANAGE THEM.............. 2-66 ...........
INFORMATION INTEGRITY.................................. 2-66 ...........
QRH ON BOARD................................................... 2-66 ...........
1
1
RVSM Operation Limitations.............................. 2-68 ...........
RVSM OPERATION............................................... 2-68 ...........
1
1
1
1
2
2-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 4
Table of Contents
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
INTRODUCTION
The airplane must be operated in accordance with the limitations
presented in this Section. These limitations also apply to operations in
accordance with an approved Supplement or Appendix to the AFM,
except as modified by such Supplement or Appendix.
The information contained in this section is derived from the Approved
Airplane Flight Manual.
Flight crewmembers should have all limitations committed to memory
(except tables and charts). Some items may not be included herein, as
they may be identified in a panel/placard or annunciated by some kind of
alarm/warning. Compliance to the Emergency and Abnormal Procedures
will also assure that certain limitations are complied with.
In the event that a limitation in this manual disagrees with the AFM
limitation, the AFM must prevail.
AOM-1502-016
In the event that a placard or instrument marking disagrees with the
limitations shown in this manual, the more restrictive limitation must
prevail.
2-INTRO
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-INTRO
Copyright © by Embraer. Refer to cover page for details.
Page 2
REVISION 9
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
WEIGHT
The maximum structural weights are shown in the table below for the
models:
EMBRAER 190 LR
!190 LR, units in lb
Max. Ramp
Weight (MRW)
(lb)
111245
Max. Takeoff
Weight
(MTOW)
(lb)
110892
Max. Landing
Weight (MLW)
(lb)
94798
Max. Zero Fuel
Weight
(MZFW)
(lb)
89948
"
EMBRAER 190 AR
!190 AR, units in lb
Max. Ramp
Weight (MRW)
(lb)
114552
Max. Takeoff
Weight
(MTOW)
(lb)
114199
Max. Landing
Weight (MLW)
(lb)
97003
Max. Zero Fuel
Weight
(MZFW)
(lb)
90169
"
To comply with the performance and operating limitations of the
regulations, the maximum allowable takeoff and landing operational
weights may be equal to, but not greater than design limits.
The takeoff weight (weight at brake release or at start of takeoff run) is
the lowest between MTOW and the following weights:
– Maximum takeoff weight as calculated using the approved software,
and as limited by field length, climb and brake energy.
– Maximum takeoff weight, as limited by enroute, and landing operating
requirements.
The landing weight is the lowest among MLW and the following weights
calculated using the approved software:
AOM-1502-016
– Maximum landing weight as limited by runway.
CONTINUED...
2-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Weight and CG
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Maximum approach and landing weight as limited by altitude,
temperature and climb gradient.
LOADING
2-05
Copyright © by Embraer. Refer to cover page for details.
Page 2
Weight and CG
REVISION 22
AOM-1502-016
The airplane must be loaded in accordance with the information
contained in the Weight and Balance Manual.
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
CENTER OF GRAVITY ENVELOPE
The Weight and CG envelope is shown in the graphics below for the
models:
!190 LR, units in lb
INFLIGHT LIMITS (FLAPS AND GEAR UP)
TAKEOFF AND LANDING LIMITS
120000
115000
REGION
2
REGION
1
6.8%
MINIMUM WEIGHTS EXTENDED AREA
NOT ALLOWED FOR TAKEOFF
2
8.8%
27.6%
29.6%
MTOW
110892 lb
110000
31%
106020 lb
105000
103617 lb
100000
WEIGHT − lb
95000
90000
89067 lb
85000
81571 lb
80000
66358 lb
75000
70000
29%
22%
18.4%
1
65036 lb
69446 lb
4% 6%
61729 lb
60000
2
15%
17%
55000
−5
0
5
23.4%
25%
25.4%
10
20
15
25
CG POSITION − % MAC
30
35
40
EM170AOM020071D.DGN
67461 lb
65000
CG ENVELOPE - EMBRAER 190 LR
AOM-1502-016
"
CONTINUED...
2-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Weight and CG
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!190 AR, normal CG envelope, units in lb
INFLIGHT LIMITS (FLAPS AND GEAR UP)
TAKEOFF AND LANDING LIMITS
125000
120000
REGION
2
REGION
1
MINIMUM WEIGHTS EXTENDED AREA
NOT ALLOWED FOR TAKEOFF
2
29%
27%
8.7% 10.7%
MTOW
115000
114199 lb
110000
105000
106020 lb
103617 lb
WEIGHT − lb
100000
95000
90000
89067 lb
85000
81571 lb
80000
31%
66358 lb
75000
18.4%
70000
22%
1
29%
65036 lb
69446 lb
2
4% 6%
61729 lb
60000
15%
17%
55000
−5
0
5
25%
25.4%
23.4%
10
20
15
25
CG POSITION − % MAC
30
35
40
EM170AOM020070D.DGN
67461 lb
65000
CG ENVELOPE - EMBRAER 190 AR
2-05
Copyright © by Embraer. Refer to cover page for details.
Page 4
Weight and CG
REVISION 22
AOM-1502-016
"
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL ENVELOPE
55000
REGION
1
− TAKEOFF, LANDING
& GROUND START
50000
45000
−65°C
−21.5°C
41000 ft
40000
ALTITUDE − ft
35000
30000
25000
ISA + 35°C
20000
15000
10000 ft
1
5000
0
−1000 ft
−54°C −40°C
−5000
−80 −70 −60 −50 −40 −30 −20 −10 0
52°C
10 20 30 40 50 60
STATIC AIR TEMPERATURE − °C
EM170AOM020021D.DGN
10000
OPERATIONAL ENVELOPE
NOTE: In the event of a landing below -40°C, the airplane may not
takeoff without further maintenance inspection.
MAXIMUM ALTITUDE FOR FLAP EXTENDED
AOM-1502-016
Maximum Altitude For Flap Extended....................... 20000 ft
2-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Operational Limitations
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
AIRSPEEDS
LANDING GEAR OPERATION/EXTENDED SPEED (VLO
AND VLE)
VLO for retraction....................................................... 235 KIAS
VLO for extension....................................................... 265 KIAS
VLE............................................................................. 265 KIAS
NOTE: – VLO is the maximum speed at which the landing gear can
be safely extended and retracted.
– VLE is the maximum speed at which the airplane can be
safely flown with the landing gear extended and locked.
MAXIMUM SPEED TO OPEN THE DIRECT VISION
WINDOW
Maximum Speed to Open the Direct Vision
Window...................................................................... 160 KIAS
MINIMUM CONTROL SPEED
CONTINUED...
2-10
Copyright © by Embraer. Refer to cover page for details.
Page 2
Operational Limitations
REVISION 23
AOM-1502-016
Refer to Section 5 – Performance.
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MAXIMUM OPERATING SPEED
45000
40000
MMO = 0.82
35000
ALTITUDE − ft
30000
25000
VMO
20000
15000
5000
0
200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350
AIRSPEED − KIAS
EM170AOM020007D.DGN
10000
AOM-1502-016
NOTE: VMO/MMO may not be deliberated exceeded in any regime of
flight (climb, cruise, or descent).
CONTINUED...
2-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Operational Limitations
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MANEUVERING SPEED (VA)
45000
40000
M MO = 0.82
35000
ALTITUDE − ft
30000
25000
20000
15000
VA
EM170AOM020023D.DGN
10000
5000
0
220
230
240
250
260
270
AIRSPEED − KIAS
280
290
300
NOTE: Maneuvers that involve angle of attack near the stall or full
application of rudder, elevator, and aileron controls should be
confined to speeds below VA. In addition, the maneuvering flight
load factor limits, presented in this Section, should not be
exceeded.
WARNING: RAPID AND LARGE ALTERNATING CONTROL INPUTS,
ESPECIALLY IN COMBINATION WITH LARGE
CHANGES IN PITCH, ROLL, OR YAW (E.G. LARGE SIDE
SLIP ANGLES) MAY RESULT IN STRUCTURAL
FAILURES AT ANY SPEED, EVEN BELOW VA.
Flaps
Flaps
Flaps
Flaps
Flaps
1....................................................................... 230
2....................................................................... 215
3....................................................................... 200
4....................................................................... 180
5....................................................................... 180
KIAS
KIAS
KIAS
KIAS
KIAS
CONTINUED...
2-10
Copyright © by Embraer. Refer to cover page for details.
Page 4
Operational Limitations
REVISION 23
AOM-1502-016
MAXIMUM FLAP EXTENDED SPEED (VFE)
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Flaps Full................................................................... 165 KIAS
MAXIMUM TIRE GROUND SPEED
Maximum Tire Ground Speed................................... 225 mph (195 kt)
WIND LIMITATIONS
Maximum Takeoff and Landing Tailwind
Component................................................................ 10 kt
MAXIMUM RECOMMENDED CROSSWIND
The following maximum crosswinds are recommended for takeoff based
on aerodynamic analyses. Gust effects are not included and do not
affect the recommended crosswind values.
Dry Runway............................................................... 38 kt
Wet Runway.............................................................. 31 kt
Runway with Compacted Snow................................ 20 kt
Runway with Standing Water/Slush/Wet Snow/Dry
Snow.......................................................................... 18 kt
Runway with Ice (including Wet Ice)......................... 12 kt
For the maximum crosswind values recommended for landing, refer to
the Runway Condition Assessment Matrix presented in section 5-35.
NOTE: Due to engine compressor stall possibility, static takeoff is not
recommended with crosswind component greater than 30 kt.
KINDS OF OPERATION
This airplane may be flown day and night in the following conditions,
when the appropriate equipment and instruments required by
airworthiness and operating regulations are approved, installed and in
an operable condition:
– Visual (VFR);
– Instrument (IFR);
AOM-1502-016
– Icing conditions;
CONTINUED...
2-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Operational Limitations
Page 5
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Category I and II;
– RVSM.
– Extended Overwater Operation;
– RNP.
MINIMUM CREW
Minimum Flight Crew................................................ PILOT AND
COPILOT
MANEUVERING FLIGHT LOAD FACTORS
These corresponding accelerations limit the bank angle during turns and
limit the pull-up maneuvers.
LOAD FACTOR LIMIT
FLAPS UP
Positive
Negative
2.5 g
-1.00 g
FLAPS DOWN
(1, 2, 3, 4, 5 AND
FULL)
2.00 g
0g
RUNWAY
Runway Slope........................................................... -2% TO +2%
Runway Surface Type............................................... PAVED
TOWING
2-10
Copyright © by Embraer. Refer to cover page for details.
Page 6
Operational Limitations
REVISION 23
AOM-1502-016
Towbarless towing is prohibited, unless it is conducted in accordance
with the procedures presented in the AMM chapter 9.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
ELECTRONIC CHECKLIST
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
Operational approval is required in order to load database into the
airplane and use the electronic checklist.
AOM-1502-016
"
2-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 11
Electronic Display
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-20
Copyright © by Embraer. Refer to cover page for details.
Page 2
Electronic Display
REVISION 11
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
WARNING
ENHANCED GROUND PROXIMITY WARNING
The following limitations are applicable to the Enhanced Ground
Proximity Warning System (EGPWS):
– Navigation is not to be predicated on the use of the Terrain Awareness
System.
– The use of predictive EGPWS functions should be manually inhibited
when landing to an airport that is not in the EGPWS airport database
to avoid unwanted alerts.
– Pilots are authorized to deviate from their current Air Traffic Control
(ATC) clearance to the extent necessary to comply with an EGPWS
warning.
– The Terrain Display is intended to be used as a situational tool only
and may not provide the accuracy and/or fidelity on which to solely
base terrain avoidance maneuvering.
– The use of predictive EGPWS functions should be manually inhibited
during QFE operations if GPS data is unavailable or inoperative.
TRAFFIC ALERT AND COLLISION AVOIDANCE
The following limitations are applicable to the Traffic Alert and Collision
Avoidance System (TCAS):
– Deviation from the ATC assigned altitude is authorized only to extent
necessary to comply with a TCAS Resolution Advisory (RA);
AOM-1502-016
– Maneuvers must not be based solely on information presented in the
traffic display.
2-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 16
Warning
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-30
Copyright © by Embraer. Refer to cover page for details.
Page 2
Warning
REVISION 16
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
FUEL
AIRPLANE MODEL
Maximum usable quantity per wing tank
Unusable quantity per wing tank
EMBRAER 190/195
ALL MODELS
2134 US Gal
(14440 lb) [1]
15.0 US Gal
(101.5 lb) [1]
1. The weights above have been determined for an adopted fuel density
of 6.767 lb/US Gal. Different fuel densities may be used provided the
volumetric limits are not exceeded.
NOTE: Maximum fuel capacity is 4298 US Gal (29083 lb ).
Maximum permitted imbalance between wing
tanks.......................................................................... 794 lb
FUEL SPECIFICATION
Brazilian Specification............................................... QAV1
ASTM Specification................................................... D1655-JET A AND
JET A-1
American Specification.............................................. MIL-T-83133A-JP8
FUEL ADDITIVES
For approved additives refer to the GE Specification D50TF2 Manual,
latest revision.
FUEL TANK TEMPERATURE
Minimum.................................................................... -37°C
CROSSFEED OPERATION
AOM-1502-016
Crossfeed Selector Knob must be set OFF during takeoff and landing.
2-36
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Fuel
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-36
Copyright © by Embraer. Refer to cover page for details.
Page 2
Fuel
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
APU SUNDSTRAND APS 2300
OPERATIONAL LIMITS
PARAMETER
START:
TEMPERATURE
ALTITUDE
OPERATION:
TEMPERATURE
ALTITUDE:
ELECTRICAL GEN
BLEED
TO ASSIST ENGINE
START
ROTOR SPEED
EGT:
START
CONTINUOUS
MIN
-54°C
-
MAX
30000 ft
-
[1]
[1]
-
33000 ft
33000 ft
15000 ft
-
21000 ft
-
108 %
[1]
[2] [3]
1032°C
717°C
1. APU temperature matches the Airplane Operational Envelope
temperature.
2. In flight, there is no automatic shutdown if EGT exceeds the limits.
3. There is no time limitation for operating the APU on ground or in
flight in the amber range between 662°C and 717°C.
APU STARTER LIMITS
Cooling period after each starting attempt:
First and Second Attempts........................................ 60 s OFF
Third Attempt............................................................. 5 min OFF
APU APPROVED OILS
AOM-1502-016
For APU Oil Types/Brands/Servicing refer to the APU Model Specification
Manual (Hamilton Sundstrand, APU Model APS 2300) - ESR 1235,
latest revision.
2-38
Copyright © by Embraer. Refer to cover page for details.
REVISION 10
Auxiliary Power Unit
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-38
Copyright © by Embraer. Refer to cover page for details.
Page 2
Auxiliary Power Unit
REVISION 10
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
ENGINE
Two General Electric CF34-10E6
OPERATIONAL LIMITS
!CF34-10E6 engines with takeoff thrust time limited to 5 minutes OR PRE-MOD SB
190-73-0004
PARAMETER
N1
N2
ITT:
Ground Start
Inflight Start
Normal Takeoff and Go Around
Maximum Takeoff and Go
Around
Maximum Continuous
OIL PRESSURE
OIL TEMPERATURE:
Continuous
MIN
–
59.27%
–
–
–
–
–
25 psi
–
–
MAX
100%
100%
–
740°C
875°C
947°C [1]
983°C [1]
[2]
[3]
[2]
[4]
960°C
–
–
155°C
1. Time limited to 5 min.
2. ITT transients above the nominal ITT limits are allowed to Normal and
Maximum takeoff, up to 5.5°C for 2 s, 4.4°C for 5 s, 3.6°C for 15 s and
2.4°C for 30 s.
3. Automatically engaged mode in one engine inoperative or windshear
conditions, when the thrust lever is in the TOGA position.
4. During starts with oil temperature below -22°C the minimum oil
pressure is 5 psi, time limited to 2 min.
AOM-1502-016
"
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Powerplant
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Two General Electric CF34-10E6
OPERATIONAL LIMITS
!CF34-10E6 engines with takeoff thrust time limited to 10 minutes OR POST-MOD SB
190-73-0004
PARAMETER
N1
N2
ITT:
Ground Start
Inflight Start
Normal Takeoff and Go Around
Maximum Takeoff and Go
Around
Maximum Continuous
OIL PRESSURE
OIL TEMPERATURE:
Continuous
MIN
–
59.27%
–
–
–
–
–
25 psi
–
–
MAX
100%
100%
–
740°C
875°C
947°C [1]
983°C [1]
[2]
[3]
[4] [2]
[5]
960°C
–
–
155°C
1. Time limited to 5 min.
2. ITT transients above the nominal ITT limits are allowed to Normal and
Maximum takeoff, up to 5.5°C for 2 s, 4.4°C for 5 s, 3.6°C for 15 s and
2.4°C for 30 s.
3. The takeoff time limit is extended to 10 min with one engine inoperative
for airplanes Post-Mod. SB 190-73-0004 or equivalent factory
incorporated modification.
4. Automatically engaged mode in one engine inoperative or windshear
conditions, when the thrust lever is in the TOGA position.
5. During starts with oil temperature below -22°C the minimum oil
pressure is 5 psi, time limited to 2 min.
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 2
Powerplant
TEMP.
REVISION
23.3
AOM-1502-016
"
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
STARTER
DRY MOTORING DUTY CYCLE LIMITS
Motoring Number
1
2 through to 5 [1]
Maximum Time
90 Seconds
30 Seconds
Cool-Down Time
5 Minutes
5 Minutes
1. After five sequential motorings, cycle may be repeated following a
15-minute cool-down period.
STARTING DUTY CYCLE LIMITS
Motoring Number
1 and 2
3 through to 5
Maximum Time
90 Seconds (On ground)
120 seconds (In-flight)
90 Seconds (On ground)
120 seconds (In-flight)
Cool-Down Time
10 Seconds
5 Minutes
NOTE:– For ground starts, the maximum cumulative starter run time
per start attempt is 90 seconds (motoring plus start time).
– For in-flight starts, the maximum cumulative starter run time
per start attempt is 120 seconds (motoring plus start time).
ENGINE APPROVED OILS
AOM-1502-016
For Engines Oil Types/Brands/Servicing refer to the GE Specification
D50TF2 Manual, latest revision.
2-40
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Powerplant
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
ENGINE THRUST
POWERBACK
Powerback is prohibited.
REDUCED AND DERATED TAKEOFF THRUST PROCEDURES
Approved methods:
– Assumed Temperature.
– Derated Takeoff Thrust Modes other than T/O-1.
For both methods:
– Operations are allowed if the airplane meets all applicable
performance requirements at the planned takeoff weight.
– Operators must establish means to ensure that the engines are
capable of producing full takeoff thrust without exceeding any engine
operating limits. The system check can be periodically performed by
conducting a T/O-1 mode takeoff without using Assumed
Temperature. The Engine Performance Trend Monitoring program
may be used to extend the time intervals between takeoff
demonstrations.
– Application of reduced takeoff thrust is always at the pilot’s discretion.
For Assumed Temperature method only:
– Operation is not allowed on runways contaminated with standing
water, slush, snow, or ice, and is not allowed on wet runways unless
suitable performance accountability is made for the increased
stopping distance on the wet surface.
– The total thrust reduction is limited to 25% of each takeoff thrust
mode.
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 4
Powerplant
TEMP.
REVISION
23.3
AOM-1502-016
– The pilot may cancel the Assumed Temperature at any time during
the takeoff operation by setting the thrust lever to the MAX position.
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
THRUST REVERSER
!Airplanes ANAC, TCCA, FAA certification and Pre-Mod. SB0190-73-0010
After applying thrust reverser, do not move thrust levers back to the
forward thrust range, unless the REV icon on EICAS is shown amber or
green.
"
NOISE LEVELS
The following Effective Perceived Noise Levels (EPNL’s) comply with,
FAA Part 36, Appendix C, Stage 3 noise limits and were obtained by
analysis of approved data from noise tests conducted under the
provisions of ICAO Annex 16, Volume 1 - Chapter 3 and FAA Part 36.
For the airplanes equipped with both right and left hand side engines
with the following reference:
– EBUCF34-10E6G07
The noise levels are presented in the following table:
NOISE LEVEL IN EPNdB
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
91.5
Flyover
84.8
Approach
92.5
"
NOISE LEVEL IN dBA
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.0
Approach
84.3
AOM-1502-016
"
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Powerplant
Page 5
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NOISE LEVEL IN EPNdB
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
91.4
Flyover
85.7
Approach
92.5
"
NOISE LEVEL in dBA
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.4
Approach
84.4
"
Otherwise, the noise levels are:
NOISE LEVEL IN EPNdB
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
92.0
Flyover
86.0
Approach
92.7
"
NOISE LEVEL IN dBA
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
73.7
Approach
84.6
"
NOISE LEVEL IN EPNdB
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
Flyover
86.9
CONDITION
Lateral
91.9
Approach
92.8
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 6
Powerplant
TEMP.
REVISION
23.3
AOM-1502-016
"
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NOISE LEVEL IN dBA
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.8
Approach
84.7
"
The noise levels for EMBRAER 190 equipped with APU Hamilton
Sundstrand APS 2300 and two GE CF34-10E6, were established as
described below:
–
Flyover (takeoff): at maximum takeoff weight, flap setting 1 and
thrust power cutback;
–
Lateral: at maximum takeoff weight, flap setting 1 and with all
engines at maximum takeoff power setting;
–
Approach: at maximum landing weight, 3° glide slope, Vref +10 KIAS
and flap setting FULL.
AOM-1502-016
No determination has been made by the Federal Aviation Administration
that the noise levels in this manual are or should be acceptable or
unacceptable for operation at, into, or out of any airport.
2-40
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Powerplant
Page 7
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 8
Powerplant
TEMP.
REVISION
23.3
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
ENGINE
Two General Electric CF34-10E6
OPERATIONAL LIMITS
!CF34-10E6 engines with takeoff thrust time limited to 5 minutes OR PRE-MOD SB
190-73-0004
PARAMETER
N1
N2
ITT:
Ground Start
Inflight Start
Normal Takeoff and Go Around
Maximum Takeoff and Go
Around
Maximum Continuous
OIL PRESSURE
OIL TEMPERATURE:
Continuous
MIN
–
59.27%
–
–
–
–
–
25 psi
–
–
MAX
100%
100%
–
740°C
875°C
947°C [1]
983°C [1]
[2]
[3]
[2]
[4]
960°C
–
–
155°C
1. Time limited to 5 min.
2. ITT transients above the nominal ITT limits are allowed to Normal and
Maximum takeoff, up to 5.5°C for 2 s, 4.4°C for 5 s, 3.6°C for 15 s and
2.4°C for 30 s.
3. Automatically engaged mode in one engine inoperative or windshear
conditions, when the thrust lever is in the TOGA position.
4. During starts with oil temperature below -22°C the minimum oil
pressure is 5 psi, time limited to 2 min.
"
Two General Electric CF34-10E6
OPERATIONAL LIMITS
!CF34-10E6 engines with takeoff thrust time limited to 10 minutes OR POST-MOD SB
190-73-0004
AOM-1502-016
PARAMETER
MIN
–
N1
MAX
100%
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Powerplant
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
PARAMETER
MIN
59.27%
–
–
N2
ITT:
Ground Start
Inflight Start
Normal Takeoff and Go Around
Maximum Takeoff and Go
Around
Maximum Continuous
OIL PRESSURE
OIL TEMPERATURE:
Continuous
MAX
100%
–
740°C
875°C
947°C [1]
983°C [1]
–
–
–
25 psi
–
–
[2]
[3]
[4] [2]
960°C
–
–
155°C
[5]
1. Time limited to 5 min.
2. ITT transients above the nominal ITT limits are allowed to Normal and
Maximum takeoff, up to 5.5°C for 2 s, 4.4°C for 5 s, 3.6°C for 15 s and
2.4°C for 30 s.
3. The takeoff time limit is extended to 10 min with one engine inoperative
for airplanes Post-Mod. SB 190-73-0004 or equivalent factory
incorporated modification.
4. Automatically engaged mode in one engine inoperative or windshear
conditions, when the thrust lever is in the TOGA position.
5. During starts with oil temperature below -22°C the minimum oil
pressure is 5 psi, time limited to 2 min.
"
STARTER
DRY MOTORING DUTY CYCLE LIMITS
Motoring Number
1
2 through to 5 [1]
Maximum Time
90 Seconds
30 Seconds
Cool-Down Time
5 Minutes
5 Minutes
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 2
Powerplant
REVISION 23
AOM-1502-016
1. After five sequential motorings, cycle may be repeated following a
15-minute cool-down period.
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
STARTING DUTY CYCLE LIMITS
Motoring Number
1 and 2
3 through to 5
Maximum Time
90 Seconds (On ground)
120 seconds (In-flight)
90 Seconds (On ground)
120 seconds (In-flight)
Cool-Down Time
10 Seconds
5 Minutes
NOTE:– For ground starts, the maximum cumulative starter run time
per start attempt is 90 seconds (motoring plus start time).
– For in-flight starts, the maximum cumulative starter run time
per start attempt is 120 seconds (motoring plus start time).
ENGINE APPROVED OILS
For Engines Oil Types/Brands/Servicing refer to the GE Specification
D50TF2 Manual, latest revision.
ENGINE THRUST
Powerback is prohibited.
Operation at reduced takeoff thrust based on the assumed temperature
higher than the actual ambient temperature is permissible if the airplane
meets all applicable performance requirements at the planned takeoff
weight and reduced thrust setting. The total thrust reduction must not
exceed 25% of the full takeoff thrust. As a condition to the use of the
reduced thrust procedures, operators must establish a means to ensure
that the engines are capable of producing full takeoff thrust without
exceeding any engine operating limits. Use of reduced takeoff thrust
procedures is not allowed on runways contaminated with standing water,
slush, snow, or ice, and are not allowed on wet runways unless suitable
performance accountability is made for the increased stopping distance
on the wet surface. Application of reduced takeoff thrust is always at the
pilot discretion. When conducting a takeoff using reduced takeoff thrust,
normal takeoff thrust may be selected at any time during the takeoff
operation.
THRUST REVERSER
AOM-1502-016
!Airplanes ANAC, TCCA, FAA certification and Pre-Mod. SB0190-73-0010
After applying thrust reverser, do not move thrust levers back to the
forward thrust range, unless the REV icon on EICAS is shown amber or
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Powerplant
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
green.
"
NOISE LEVELS
The following Effective Perceived Noise Levels (EPNL’s) comply with,
FAA Part 36, Appendix C, Stage 3 noise limits and were obtained by
analysis of approved data from noise tests conducted under the
provisions of ICAO Annex 16, Volume 1 - Chapter 3 and FAA Part 36.
For the airplanes equipped with both right and left hand side engines
with the following reference:
– EBUCF34-10E6G07
The noise levels are presented in the following table:
NOISE LEVEL IN EPNdB
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
91.8
Flyover
85.6
Approach
92.4
"
NOISE LEVEL IN dBA
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.0
Approach
84.3
"
NOISE LEVEL IN EPNdB
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
Flyover
86.3
CONDITION
Lateral
91.8
Approach
92.4
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 4
Powerplant
REVISION 23
AOM-1502-016
"
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NOISE LEVEL in dBA
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.4
Approach
84.4
"
NOISE LEVEL IN EPNdB
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
92.0
Flyover
86.0
Approach
92.7
"
NOISE LEVEL IN dBA
!190 LR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
73.7
Approach
84.6
"
NOISE LEVEL IN EPNdB
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Lateral
91.9
Flyover
86.9
Approach
92.8
"
NOISE LEVEL IN dBA
!190 AR, CF34-10E6 engines, ANAC/TCCA/FAA certification
CONDITION
Flyover
74.8
Approach
84.7
AOM-1502-016
"
The noise levels for EMBRAER 190 equipped with APU Hamilton
Sundstrand APS 2300 and two GE CF34-10E6, were established as
described below:
CONTINUED...
2-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Powerplant
Page 5
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Flyover (takeoff): at maximum takeoff weight, flap setting 1 and thrust
power cutback;
– Lateral: at maximum takeoff weight, flap setting 1 and with all engines
at maximum takeoff power setting;
– Approach: at maximum landing weight, 3° glide slope, Vref +10 KIAS
and flap setting FULL.
2-40
Copyright © by Embraer. Refer to cover page for details.
Page 6
Powerplant
REVISION 23
AOM-1502-016
No determination has been made by the Federal Aviation Administration
that the noise levels in this manual are or should be acceptable or
unacceptable for operation at, into, or out of any airport.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
PRESSURIZATION
AOM-1502-016
Maximum differential pressure.................................. 8.4 psi
Maximum differential overpressure........................... 8.8 psi
Maximum differential negative pressure................... -0.5 psi
Maximum differential pressure for Takeoff and
Landing...................................................................... 0.2 psi
2-48
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Pneumatic, Air Conditioning,
Pressurization
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-48
Copyright © by Embraer. Refer to cover page for details.
Page 2
Pneumatic, Air Conditioning,
Pressurization
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
ICE AND RAIN PROTECTION
OPERATION IN ICING CONDITIONS
There is no temperature limitation for anti-icing system automatic
operation.
On ground:
– The TO DATASET MENU on the MCDU must be set to ENG when
OAT is from 5-10°C and:
– if there is any possibility of encountering visible moisture up to
1700 ft AFE, or
– 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.
– The TO DATASET MENU on the MCDU must be set to ALL when
OAT is less than 5°C:
– if there is any possibility of encountering visible moisture up to
1700 ft AFE, or.
– 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.
In flight:
– The engine and wing anti-ice systems operate automatically, in case
of ice encounter when the ice protection mode selector is in the
AUTO position. If either one or both ice detectors are failed, the crew
must set the mode selector to ON when icing conditions exist or are
anticipated below 10°C TAT with visible moisture.
AOM-1502-016
– Closely monitor the TAT indication and presence of moisture. If
environmental ice conditions exist, even intermittent, check the
windshield, windshield wiper (if installed), and wing surface for ice
accumulation. To visualize ice formation, if necessary, use a flashlight
CONTINUED...
2-50
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Ice and Rain Protection
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
on the windshield and the wing inspection light on the wing. If any ice
formation is detected or suspected, select the anti-ice protection
system override knob to ON. When flying in detected or suspected
ice conditions, use ice speeds as reference.
NOTE: – Icing conditions may exist whenever the Outside Air
Temperature (OAT) on ground or for takeoff, or Total Air
Temperature (TAT) in flight, is 10°C or less and visible
moisture in any form is present (such as clouds, fog with
visibility of one mile or less, rain, snow, sleet, and ice
crystals).
– Icing conditions may also exist when the OAT on ground or
for takeoff is 10°C or less 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.
CAUTION: ON GROUND, DO NOT RELY ON VISUAL ICING
EVIDENCE OR ICE DETECTOR ACTUATION TO TURN
ON THE ANTI-ICING SYSTEM. USE THE TEMPERATURE
AND VISUAL MOISTURE CRITERIA AS SPECIFIED
ABOVE. DELAYING THE USE OF THE ANTI-ICING
SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE
COCKPIT MAY RESULT IN ICE INGESTION AND
POSSIBLE ENGINE DAMAGE OR FLAMEOUT.
WINDSHIELD WIPER OPERATION
2-50
Copyright © by Embraer. Refer to cover page for details.
Page 2
Ice and Rain Protection
REVISION 21
AOM-1502-016
Maximum Airspeed for Windshield Wiper
Operation................................................................... 253 KIAS
AIRPLANE
OPERATIONS
MANUAL
NAVIGATION,
AUTOPILOT
COMMUNICATION
LIMITATIONS
AND
AUTOPILOT
Minimum Engagement Height................................... 400 ft
Minimum Use Height................................................. 50 ft
NAVIGATION EQUIPMENT
– TAS, TAT and SAT information are only valid above 60 KIAS.
– While transmitting in VHF1 the standby magnetic compass indication
is not valid.
– Baro altimeter minimums must be used for all Cat I approaches.
– Back course approaches using IESS are prohibited.
– The ACARS is limited to the transmission and receipt of messages
that will not create an unsafe condition if the message is improperly
received, unless they are verified per approved operational
procedures.
!190/195 models equipped with ADS-B Out Non Radar Area OR Post-Mod. SB
190-34-0026 OR Post-Mod. SB 190LIN-34-0004, FAA Certification
– The ADS-B Out system complies with EASA AMC 20-24 and was
implemented according to DO-260A, change 1 and change 2.
"
!190/195 models equipped with ADS-B Out Radar Area OR Post-Mod. SB
190-34-0030 OR Post-Mod. SB 190LIN-34-0005, FAA Certification
– The installed ADS-B Out system has been shown to meet the
equipment requirements of 14 CFR § 91.227 and EU 1207/2011.
AOM-1502-016
"
2-56
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Navigation, Communication,
Autopilot
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
INERTIAL REFERENCE SYSTEM
– The airplanes may be operated within the North and South magnetic
polar cut-out regions specified in the table below, but IRS magnetic
heading and track angle magnetic data will not be available.
MAGNETIC
CUT-OUT
REGIONS
North
South
LATITUDE
Between 73.125°N
and 82°N
North of 82°N
Between 60°S and
82°S
South of 82°S
LONGITUDE
Between 80°W and 130°W
Between 0° and 180°W/E
Between 120°E and 160°E
Between 0° and 180°W/E
NOTE: Whenever operating within North or South magnetic polar
cut-out regions, current airplane heading must be referenced to
true heading, if not already selected. Otherwise, the Heading
Failure Indication flag will be displayed.
Maximum latitude for stationary alignment:.............. 78.25° Northern
and Southern
– IRS stationary alignment will complete only after a valid airplane
present position (latitude and longitude) is received from the FMS or
automatically from GPS.
CONTINUED...
2-56
Copyright © by Embraer. Refer to cover page for details.
Page 2
Navigation, Communication,
Autopilot
TEMP.
REVISION
23.3
AOM-1502-016
– Time to stationary alignment completion:
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
15
10
5
0
0
5
10
15
20
25
30
35
40
45
50
55
60
65
70
AOM-1502-016
ALIGNMENT LATITUDE − degrees Northern and Southern
75
80
EM170AOM020009C.DGN
ALIGNMENT TIME − minutes
20
2-56
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Navigation, Communication,
Autopilot
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-56
Copyright © by Embraer. Refer to cover page for details.
Page 4
Navigation, Communication,
Autopilot
TEMP.
REVISION
23.3
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
NAVIGATION,
AUTOPILOT
COMMUNICATION
AND
AUTOPILOT
Minimum Engagement Height................................... 400 ft
Minimum Use Height................................................. 50 ft
NAVIGATION EQUIPMENT
– TAS, TAT and SAT information are only valid above 60 KIAS.
– While transmitting in VHF1 the standby magnetic compass indication
is not valid.
– Baro altimeter minimums must be used for all Cat I approaches.
– Back course approaches using IESS are prohibited.
– The ACARS is limited to the transmission and receipt of messages
that will not create an unsafe condition if the message is improperly
received, unless they are verified per approved operational
procedures.
INERTIAL REFERENCE SYSTEM
– The airplanes may be operated within the North and South magnetic
polar cut-out regions specified in the table below, but IRS magnetic
heading and track angle magnetic data will not be available.
MAGNETIC
CUT-OUT
REGIONS
North
AOM-1502-016
South
LATITUDE
Between 73.125°N
and 82°N
North of 82°N
Between 60°S and
82°S
South of 82°S
LONGITUDE
Between 80°W and 130°W
Between 0° and 180°W/E
Between 120°E and 160°E
Between 0° and 180°W/E
CONTINUED...
2-56
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Navigation, Communication,
Autopilot
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NOTE: Whenever operating within North or South magnetic polar
cut-out regions, current airplane heading must be referenced to
true heading, if not already selected. Otherwise, the Heading
Failure Indication flag will be displayed.
Maximum latitude for stationary alignment:.............. 78.25° Northern
and Southern
– IRS stationary alignment will complete only after a valid airplane
present position (latitude and longitude) is received from the FMS or
automatically from GPS.
– Time to stationary alignment completion:
15
10
5
0
5
10
15
20
25
30
35
40
45
50
55
60
65
70
ALIGNMENT LATITUDE − degrees Northern and Southern
75
80
2-56
Copyright © by Embraer. Refer to cover page for details.
Page 2
Navigation, Communication,
Autopilot
REVISION 9
AOM-1502-016
0
EM170AOM020009C.DGN
ALIGNMENT TIME − minutes
20
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
CAT II LIMITATIONS
MINIMUM EQUIPMENT REQUIRED
The performance of CAT II approaches has been demonstrated to meet
the airworthiness requirements of FAA AC 120-29A – Appendix 3 and
CS AWO Subpart 2 requirement, when the following equipments are
installed and operative:
– 2 Inertial Reference Systems;
– 2 Flight Director Systems;
– 2 Primary Flight Displays (PFD);
– Windshield Wipers;
– 2 VOR/ILS NAV System;
– 1 VHF/COMM System;
– 1 Radio Altimeter;
– 1 Ground Proximity Warning System (EGPWS);
– 2 Air Data System (ADS);
For CAT II operation with one engine inoperative, the following also
applies:
– 1 Autopilot System Channel;
– Manual FD Category II ILS approaches are prohibited.
FLIGHT CONTROLS
CAT II is prohibited with the SPOILER FAULT EICAS message displayed.
AUTOPILOT SYSTEM
AOM-1502-016
Minimum Use Height (MUH)..................................... 50 ft
NOTE: Coupled go-around height loss may be 50 ft.
2-57
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
CAT II Limitations
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
APPROACH AND LANDING FLAPS
CAT II approach and landing must be performed with flaps 5.
MAXIMUM WIND COMPONENTS
This limitation applies to manual FD (Flight Director) approaches only.
Headwind................................................................... 10 kt
Tailwind...................................................................... 5 kt
DEMONSTRATED WIND COMPONENTS
For manual FD (Flight Director) approaches:
Crosswind.................................................................. 16 kt
For coupled approaches:
Headwind................................................................... 37 kt
Tailwind...................................................................... 15 kt
Crosswind.................................................................. 16 kt
2-57
Copyright © by Embraer. Refer to cover page for details.
Page 2
CAT II Limitations
REVISION 23
AOM-1502-016
These demonstrated values are not considered to be limiting.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
OZONE CONCENTRATION
The tables below show the airplane altitude limitations due to ozone
concentration in atmosphere for airplanes not equipped with the Ozone
Converters.
Ozone limitations shall be considered any time a flight is planned to fly
at or above the latitudes specifically described in the applicable table for
each region. Flight outside of the latitudes referenced by the tables are
not altitude restricted in regard to ozone. The dashes in the tables mean
that the criteria does not impose an altitude limitation below the maximum
approved altitude for the airplane at that specific latitude and period of
the year.
Two criteria are presented:
1 - The Maximum Ozone Criteria is the limiting altitude for every flight
and does not depend on flight time.
2 - The Time Weighted Average (TWA) Ozone Criteria tables do not
represent the ceiling altitude, but the altitude above which the
airplane should not fly for more than 3 continuous hours (RBHA/FAR
§ 25.832 (a) (2)). This means that the TWA ozone chart shall only
be considered if both of the following conditions are met:
– The airplane is flying in a latitude range at or above the minimum
indicated in the table with an actual limitation (not a dash).
– The flight will be conducted at or above FL270 in that latitude
range for 3 or more hours.
If the latitude considered is in between the ones presented in the table,
the altitude value may be interpolated. For calculation purposes, the
dashes in the table should be considered the maximum altitude
presented in the approved operational envelope (FL410).
AOM-1502-016
For example, in a flight on the west side of the longitude reference line
CONTINUED...
2-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Ozone Concentration
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
(100°W), at any latitude above 45°N up to 50ºN on January, the
maximum flight level shall be limited to 407 (Maximum Ozone Criteria),
but the airplane shall not be above flight level 338 for more than 3 hours
(TWA Ozone Criteria).
NOTE: – These tables are based on FAA AC 120.38.
– The tables show altitude limitations calculated for constant
ozone concentration and cabin stabilized at 8000 ft.
However, ozone tables shall still be considered regardless
of the actual cabin altitude attained during a given flight.
– For conditions other than those specified in item 2 above,
an optimized flight plan must be approved by regulatory
agencies.
– For longitudes, the following apply:
W = Western
E = Eastern
Reference = 100°W longitude
CONTINUED...
2-60
Copyright © by Embraer. Refer to cover page for details.
Page 2
Ozone Concentration
REVISION 22
AOM-1502-016
•
•
•
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NORTH AMERICA - MAXIMUM OZONE CRITERIA
NOTE: The North America tables are approved by FAA as Airplane
Flight Manual Limitations.
FLIGHT
LEVEL
LATITUDE
80°N
75°N
70°N
65°N
60°N
55°N
50°N
45°N
40°N
35°N
AOM-1502-016
FLIGHT
LEVEL
LATITUDE
80°N
75°N
70°N
65°N
60°N
55°N
50°N
45°N
40°N
35°N
JAN
W
356
376
394
407
410
406
-
FEB
E
323
327
341
346
356
362
376
396
-
JUL
W
346
347
356
366
-
W
333
347
376
409
410
366
-
E
323
323
323
326
336
346
362
376
386
-
AUG
E
336
346
346
356
366
382
406
-
W
396
402
406
-
MAR
W
328
338
347
366
376
376
-
E
314
321
326
327
334
341
346
366
396
-
SEP
APR
W
328
327
327
327
346
382
-
E
313
314
321
321
326
334
336
346
366
-
OCT
MAY
W
326
327
327
334
346
402
-
E
307
314
314
321
326
327
336
362
396
-
NOV
E W E W E W E
382 - 394 - 382 - 346
396 - 386 - 382 - 362
406 - 396 - 382 - 382
406 406 406 382 394 406 386
- 396 401 407 394
- 407 401
- 406
-
JUN
W
338
341
347
356
376
-
E
326
327
334
336
336
356
366
396
-
DEC
W
376
386
401
-
E
346
356
356
366
382
396
-
CONTINUED...
2-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Ozone Concentration
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
NORTH AMERICA - TWA OZONE CRITERIA
NOTE: – Values below are the altitude limitations which the airplane
is allowed to fly more than 3 continuous hours.
– The North America tables are approved by FAA as Airplane
Flight Manual Limitations.
FLIGHT
LEVEL
LATITUDE
80°N
75°N
70°N
65°N
60°N
55°N
50°N
45°N
40°N
35°N
JAN
W
312
321
332
338
338
332
374
FEB
E
274
278
292
294
298
298
312
314
334
354
JUL
W
294
298
301
312
321
294
-
W
298
311
321
354
338
312
374
E
270
274
274
270
278
292
298
312
318
354
AUG
E
270
274
274
294
312
312
318
334
354
394
W
332
332
332
332
354
-
E
298
314
321
332
334
334
334
354
398
-
MAR
W
301
303
311
315
315
312
338
E
270
270
270
273
291
291
298
311
317
353
SEP
W
334
338
354
374
-
E
298
312
314
318
334
334
334
374
-
APR
W
292
274
270
270
274
312
354
E
270
270
270
270
270
274
274
294
311
334
OCT
W
321
323
334
354
374
-
E
298
298
312
314
318
334
354
354
374
-
MAY
W
270
270
270
274
294
318
374
E
270
270
270
270
270
270
274
294
318
334
NOV
W
334
334
338
338
353
394
-
E
292
294
298
298
298
314
334
334
354
398
JUN
W
303
311
311
311
318
334
392
E
270
270
274
274
274
292
312
318
334
374
DEC
W
318
321
334
354
354
354
-
E
298
298
298
301
312
318
334
334
334
374
CONTINUED...
2-60
Copyright © by Embraer. Refer to cover page for details.
Page 4
Ozone Concentration
REVISION 22
AOM-1502-016
FLIGHT
LEVEL
LATITUDE
80°N
75°N
70°N
65°N
60°N
55°N
50°N
45°N
40°N
35°N
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
...CONTINUED
JAPAN - MAXIMUM OZONE CRITERIA
FLIGHT
LEVEL
Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec
LATITUDE
43°N
356 341 341 356 346 401 - 386
36°N
406 - 382 396 32°N
JAPAN - TWA OZONE CRITERIA
NOTE: Values below are the altitude limitations which the airplane is
allowed to fly more than 3 continuous hours.
AOM-1502-016
FLIGHT
LEVEL
Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec
LATITUDE
43°N
298 298 300 311 373 313 353 - 353 353 353 311
36°N
331 313 311 320 333 398 - 393
32°N
- 391 373 -
CONTINUED...
2-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Ozone Concentration
Page 5
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
EUROPE - MAXIMUM OZONE CRITERIA
FLIGHT
LEVEL
Jan Feb Mar Apr
LATITUDE
52°N
394 356 354 336
47°N
401 376 366 356
39°N
- 396 356
May Jun Jul Aug Sep Oct Nov Dec
356 382 406
376 376 361 -
-
-
-
-
406
-
EUROPE - TWA OZONE CRITERIA
NOTE: Values below are the altitude limitations which the airplane is
allowed to fly more than 3 continuous hours.
Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec
331 311 311 273 298 315 320 353 353 373 353 331
333 320 311 311 315 311 333 373 393 398 373 338
393 351 331 311 311 333 393 - 358
2-60
Copyright © by Embraer. Refer to cover page for details.
Page 6
Ozone Concentration
REVISION 22
AOM-1502-016
FLIGHT
LEVEL
LATITUDE
52°N
47°N
39°N
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
Airplanes equipped with Autoland system
AUTOLAND
GENERAL
The following operations are prohibited:
•
MLS;
•
ILS beam not coincident with the central axis of the runway;
•
Autoland for an ILS CAT I, unless operators interrogate the airport
authorities on ILS ground equipment quality and on experience with
other operators. The operators should check with the authorities that
specific restrictions do not apply at airports with CAT I only capability.
Terrain profile before the runway threshold has also to be considered.
GLIDESLOPE ANGLES
The maximum and minimum glideslope angles are 3.25° and 2.5°
respectively.
!190 models equipped with Autoland system
CENTER OF GRAVITY ENVELOPE
WEIGHT
Autoland operation in the Center of Gravity Envelope minimum weights
extended area is prohibited.
"
OPERATIONAL LIMITATIONS
AIRPORT ALTITUDE LIMITS
AOM-1502-016
The Autoland system was demonstrated to meet the necessary
requirements under the following conditions:
Demonstrated Maximum Airport Altitude................... 7340 ft
CONTINUED...
2-61
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoland
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
RUNWAY
!190/195 models equipped with Autoland system
Runway Slope........................................................... -1% TO +1%
"
WIND LIMITATIONS
!Airplanes equipped with Autoland system and operation with tailwind up to 10 kt
Maximum wind components speed:
Headwind................................................................... 25 kt
Crosswind.................................................................. 15 kt
Tailwind...................................................................... 10 kt
"
CAT I AUTOLAND
The Autoland system has been demonstrated in CAT II/III facilities.
However, Autoland operation on CAT I facilities or when ILS sensitive
areas are not protected is possible if the following precautions are taken:
– The operator has checked that the ILS beam quality and the effect of
the terrain profile before the runway have no adverse effect on
autopilot guidance;
– The crew is aware that LOC or GS beam fluctuations independent of
the airplane system may occur;
– Autoland capability is displayed on FMA and the associated
procedures are used;
– The DH used is appropriate for CAT I or better weather conditions;
– The pilot flying is prepared to take immediate action should
unsatisfactory guidance occur;
– The operator has checked that it complies with the local authority
requirements.
Autoland operation must be performed with flaps 5.
2-61
Copyright © by Embraer. Refer to cover page for details.
Page 2
Autoland
REVISION 21
AOM-1502-016
LANDING FLAPS
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
MINIMUM EQUIPMENT REQUIRED
!Airplanes equipped with Autoland System, ANAC or FAA certification
The Autopilot System has been demonstrated to meet the airworthiness
requirements of Advisory Circular (AC) 120-28D Appendix 3 for a
fail-passive automatic landing system, when the following is installed
and operative:
– 2 Inertial Reference Systems;
– 2 Flight Director Systems;
– 2 Primary Flight Displays (PFD);
– Windshield Wipers;
– 2 Independent VOR/ILS NAV Systems;
– 1 VHF/COMM System;
– 2 Radio Altimeters (RA);
– 1 Enhanced Ground Proximity Warning System (EGPWS);
– 2 Air Data Systems (ADS);
– 1 Autopilot Channel;
AOM-1502-016
"
2-61
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoland
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-61
Copyright © by Embraer. Refer to cover page for details.
Page 4
Autoland
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
FLIGHT MANAGEMENT SYSTEM
NAVIGATION OPERATIONAL APPROVALS
Honeywell Primus Epic FMS installation has been demonstrated to be
capable of and has been shown to meet the requirements for the
following operations:
!Pre-mod MAU load 27.1
– Required Navigation Performance (RNP) Operations – The FMS
has been demonstrated compliant with the requirements of RTCA
DO–283, Minimum Operational Performance Specification for
Required Navigation Performance. The FMS has been demonstrated
to provide a minimum RNP level of RNP 0.3 when operated according
to the limitations and procedures described in FMS AFM supplement.
The airplane capability does not constitute RNP operation approval.
The operators must be granted local approval to conduct RNP
operations.
!!ANAC, TCCA, FAA Cetification, Pre-Mod MAU LOAD 27.1
– The airplane meets the performance and functional requirements of
FAA AC 90-101 for RNP AR approach operations requiring RNP not
less than 0.3 for approach and not less than 1.0 for missed approach.
""
"
!Pre-mod MAU load 27.1
– Navigation using GPS – The FMS has been demonstrated compliant
with the requirements of FAA AC 90-94, regarding the use of GPS for
IFR navigation in en-route, terminal, and non-precision approach
operations. The airplane GPS equipment is approved under
TSO-C129a.
"
AOM-1502-016
!Pre-mod MAU load 27.1
– Navigation using IRS – The FMS has been demonstrated compliant
with the requirements of AC 25-4, AC 121-13, and FAR 121, Appendix
G, regarding the use of IRS as a long range navigation system. Pilot
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Flight Management System
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
qualification is required to comply with operation under AC 121-13.
"
!Pre-mod MAU load 27.1
– Remote/Oceanic Operation – The FMS has been demonstrated
compliant with the requirements of AC 20-130A, regarding
multi-sensor system operation in remote/oceanic flight, when
operated as a dual system, with dual installed FMS, GPS, and IRS
operational prior to the start of flight.
The FMS has been demonstrated compliant with the requirements of
AC 121-13 and FAR 121, Appendix G, regarding use of IRS as a
primary means of navigation in remote/oceanic flight, with dual
installed FMS and IRS operational prior to the start of flight.
The FMS has been demonstrated compliant with the requirements of
FAA Notice 8110.60, regarding use of GPS as a primary means of
navigation in remote/oceanic flight, with dual installed FMS and GPS
operational prior to the start of flight. Compliance with Notice 8110.60
also requires the operator to use the Honeywell Sure Flight Off Line
RAIM and FDE prediction program prior to flight.
"
– North Atlantic Minimum Navigation Performance Specification
(NAT-MNPS) Airspace – The FMS has been demonstrated compliant
with the requirements of AC 120-33 when operated as a dual system,
with dual installed FMS, GPS , and IRS operational prior to the start
of flight.
!Pre-mod MAU load 27.1
– RNP 10 Airspace – FMS has been demonstrated compliant with the
requirements of FAA Order 8400.12A when operated as a dual
system, with dual installed FMS, GPS, and IRS operational prior to
the start of flight.
NOTE: The term RNP 10 must be understood as RNAV 10 as per ICAO
nomenclature.
"
– Enroute and Terminal Operation – The FMS has been
demonstrated compliant with the requirements of AC 20-130A and
AC 25-15, regarding multi-sensor system IFR operation in
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
Page 2
Flight Management System
REVISION 23
AOM-1502-016
!Pre-mod MAU load 27.1
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
...CONTINUED
en-route/terminal flight, with at least a single PFD, MFD, FMS, VOR,
DME, and IRS in NAV mode operational prior to the start of flight.
"
!Pre-mod MAU load 27.1
– Approach Operation – The FMS has been demonstrated compliant
with the requirements of AC 20-130A and AC 25-15, regarding
multi-sensor system instrument non-precision approach operation.
The FMS has been demonstrated compliant with AC 90-94, regarding
the use of GPS for non-precision approaches. The FMS must be
operated as at least a single system, with a minimum of one PFD,
MFD, and FMS operational prior to commencing the approach. The
signal source(s) used to define the approach and on-board equipment
must be verified operational prior to commencing the approach, as
explained in the General Limitations of this AOM block.
The FMS supports the following non-precision approach types:
– GPS only (type III FAA overlay definition);
– RNAV (including type II or type III FAA overlay definition);
– VOR;
– VOR-DME;
– NDB;
– NDB-DME.
NOTE: VOR and NDB based approaches include FAA type II GPS
overlays. AC 90-94 deals with the use of GPS in the US National
Airspace System (NAS). The general approval to use GPS to fly
overlay instrument approaches as described in the AC, is initially
limited to the NAS. Refer to General Limitations of this block, for
use of GPS for non-precision approaches outside the US NAS.
"
!Pre-mod MAU load 27.1
AOM-1502-016
– Barometric Vertical Navigation – For airplanes with VNAV enabled,
the FMS has been demonstrated compliant with the requirements of
AC 20-129, regarding the barometric vertical navigation in en-route,
terminal, and non-precision approach operations, when used in
accordance with the limitations and operational procedures contained
in the AFM FMS Supplement.
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Flight Management System
Page 3
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
– The FMS has been demonstrated compliant with the requirements of
AC 90-97, regarding the use of barometric vertical navigation for
instrument approach operations using decision altitude, when used in
accordance with the limitations and operational procedures contained
in the AFM FMS Supplement.
""
"
!Pre-Mod MAU LOAD 27.1, ANAC/FAA Certification
– Terminal and Enroute Area Navigation (RNAV) Operation – The
FMS has been demonstrated compliant with the requirements of AC
90-100A, using GPS and DME/DME/IRU sensors.
The airplane capability does not constitute RNAV operation approval.
The operators must be granted local approval to conduct RNAV
operations.
NOTE: For RNAV operations based only on DME/DME/IRU mode, it is
necessary for the pilot to enter Notam navaids on the FMS
Notam page.
– RNP Approach (RNP-APCH) Operation – According to AC 90-105,
airplane qualified by AC 90-101 are considered qualified for RNP
approach (RNP-APCH) operations (including BARO-VNAV) without
further examination.
The airplane capability does not constitute RNP operation approval.
The operators must be granted local approval to conduct RNP
operations.
2-64
Copyright © by Embraer. Refer to cover page for details.
Page 4
Flight Management System
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
GENERAL LIMITATIONS
FMS PILOT’S OPERATING MANUAL
!Pre-mod MAU load 27.1
– Pilot’s Operating Manual P/N A28-1146-179 or other approved
manual must be available to the flight crew.
"
– The Pilot’s Manual must match the FMS software version installed in
the airplane.
FMS DATABASE VERSION
!Pre-mod MAU load 27.1
– The Honeywell Primus Epic FMS Airplane Database configuration
must be that found on Limitations chapter of airplanes AFM.
"
NAVIGATION LIMITATIONS
– For RNP navigation, the pilots must compare any procedures/route
retrieved from the FMS database with those published on the charts.
Differences between the charts and the FMS information up to 3
degrees are acceptable.
!190/195 models, Pre-Mod MAU load 25.1.0.1
– RNP operations are prohibited after December 31, 2015 due to
magnetic variation tables’ expiration date.
"
!Pre-mod MAU load 27.1
– RNP operations are prohibited after December 31, 2020 due to
magnetic variation tables’ expiration date.
AOM-1502-016
"
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Flight Management System
Page 5
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!Pre-mod MAU load 27.1
– The RNP-RNAV airworthiness approval has not accounted for
database accuracy or compatibility as defined per AC 20-153.
"
!Embraer 190/195 models, Pre-mod MAU Load 27.1
– For operations using RNP 1 to RNP less than 2, the use of Flight
Director is required.
"
!Embraer 190/195 models, Pre-mod MAU Load 27.1
– For operations using RNP 0.3 to less than 1, the use of GPS and
Flight Director is required.
"
!Pre-mod MAU load 27.1
– Operations requiring RNP less than 0.3 are not approved.
"
!Pre-mod MAU load 27.1
– The use of speed mode in FMS is prohibited for one engine operative
condition.
"
!RNP AR operation, Airplanes PRE-MOD MAU LOAD 27.1.
– For operations requiring RNP AR, Embraer General Publication
GP-3801 must be used. Refer to the applicable AFM supplements for
limitations regarding RNP AR operations.
"
– The use of VNAV requires the respective FD vertical guidance mode
to be active.
– The use of VNAV is prohibited when the respective FD vertical
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
Page 6
Flight Management System
REVISION 23
AOM-1502-016
– The use of FMS Speed requires the respective FD vertical guidance
mode to be active.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
...CONTINUED
guidance mode is other than VNAV , unless pilots adjust the ALT SEL
to each altitude constraint in the Flight Plan.
– The use of GPS is limited to areas where GPS is approved.
Deselection of GPS should be performed in other non-approved
areas.
– Prior to flight using the FMS for IFR navigation, a minimum of one
VOR, DME, and IRS must be verified to be installed and operational.
Also, any appropriate ground facilities (VOR, DME) that are utilized
by the procedures to be flown must be verified as operational using
an approved method (NOTAM, etc.).
– If GPS RAIM is annunciated as not available during terminal, enroute,
or remote/oceanic operation, the pilot must monitor FMS guidance
data and crosscheck against raw data from an alternate source (i.e.
VOR, DME, or IRS).
– When a GPS Only Approach is planned prior to dispatch, the crew is
required to verify that the predictive RAIM at the destination ETA is
within the approach criteria. This information (RAIM AVAILABLE) is
displayed on the PREDICTIVE RAIM page on the MCDU.
– Due to priority use of GPS by the FMS, IFR Navigation using the
FMS is limited to use with procedures that are referenced to the
WGS-84 or NAD-83 datum, unless other appropriate authorized
procedures are used.
– IFR Navigation using the FMS is prohibited unless the pilot verifies
the currency of the selected navigation database cycle on the NAV
IDENT page.
– IFR Navigation using the FMS is limited to geographic regions
contained within the navigation database that is installed in the
airplane.
AOM-1502-016
– Operation above 72° 30.0’ north latitude and below 59° 30.0’ south
latitude is prohibited due to unreliable magnetic heading, unless at
least one Inertial Reference System (IRS) is verified operational as a
sensor to the FMS. In this case, the system will automatically switch
to TRUE.
– FMS performance management calculations have not been certified
by the Airworthiness Authority. FMS performance management
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Flight Management System
Page 7
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
information is advisory information only, and may not be used as a
basis for fuel load planning or airplane range predictions.
– Selection of FMS Position Update is prohibited during RNP
operations, including RNP 10 operations.
– The FMS does not correct the speed targets, including approach and
go around speeds, for ice conditions or non-normal conditions. It is
the pilot responsibility to ensure that the speeds are within the limits
in these conditions.
– Entry of a planned speed into the FMS which is below the minimum
safe maneuver speed prescribed in the basic AFM is prohibited.
– The selection of course interception to a conditional waypoint
(waypoints created automatically by FMS that is not part of nav
database, i.e. TOC) is prohibited.
– The pilot must ensure that displayed guidance data from non-usable
stations is not used for navigation purposes by the flight crew. The
Notam function in the FMS does not always inhibit tuning of a Notam
selected station by the FMS when in AUTO tune mode. Note that the
FMS will not use Notam selected station data for FMS position
determination.
!Pre-mod MAU load 27.1
– The use of the Step Climb function is prohibited.
– FMS LNAV may command bank angles above the local regulations
limits (i.e. There is no automatic protection for engine out situation).
"
APPROACH LIMITATIONS
– FMS instrument approaches must be accomplished in accordance
with approved instrument approach procedures that are retrievable
from the FMS navigation database (as displayed on the APPROACH
page on the MCDU). The pilot must review the complete procedure,
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
Page 8
Flight Management System
REVISION 23
AOM-1502-016
– ILS, LOC, LOC-BC, LDA, SDF, GLS, MLS, Visual, and Radar
approaches, using the FMS as the navigation source for guidance,
are prohibited. This limitation does not apply to RNAV Visual or FMS
Visual approaches.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
...CONTINUED
comparing the waypoints, speeds, and altitudes displayed on the
FMS with those on the published procedure charts. If any doubt
exists about the integrity of the coded procedure, the procedure
should not be used.
– Prior to commencing and during the final approach, the APPR
annunciator must be visible on the PFD. If the APPR annunciator is
not visible, and the appropriate runway visibility indications are not
observed, the pilot should request a missed approach.
– When using FMS guidance to conduct an instrument approach
procedure that does not include GPS in the title of the published
procedure, the flight crew must verify that the procedure specified
navaids(s) and associated avionics are operational (i.e. VOR, DME,
ADF). If GPS RAIM is annunciated as not available during the
approach, the pilot must monitor FMS guidance data and crosscheck
against raw data from the alternate source(s).
– When the reported station temperature exceeds the limits published
in the approach chart, the use of VNAV barometric procedures are
prohibited unless the pilot uses the VNAV temperature compensation
function.
– The pilot must rely on the altimeter as the primary vertical reference
during the final approach segment, including step down fixes. VNAV
path guidance is supplementary guidance information.
– Use of VNAV guidance below the published approach minimums is
prohibited.
!Airplanes Pre-mod MAU load 21.4
– When using VGP, use of Temperature Compensation is prohibited.
"
!Airplanes Post-mod MAU load 21.2 and Pre-mod MAU load 21.4
– VGP approaches are prohibited.
AOM-1502-016
"
– The use of temperature compensation feature must be coordinated
with ATC if Baro-VNAV operation is intended.
CONTINUED...
2-64
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Flight Management System
Page 9
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
2-64
Copyright © by Embraer. Refer to cover page for details.
Page 10
Flight Management System
REVISION 23
AOM-1502-016
– The use of temperature compensation feature is required if BaroVNAV operation outside the temperature limits published on approach
procedure chart is intended.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
ELECTRONIC FLIGHT BAG (EFB)
This supplement contains additional information about the use and
operational approval of the EFB applications.
SOFTWARE APPLICATIONS
Operators will be responsible to select, install and manage the
applications and functionalities used in the EFB platform.
Operators are solely responsible for:
•
Selection of applications to be used;
•
Installation of applications and functionalities and;
•
Management of the update process for each application.
APPROVAL OF THE APPLICATIONS
PROCEDURES TO MANAGE THEM
AND
It is the operators responsibility to obtain approval from the local authority
for use of the EFB including:
•
Installation process;
•
Software application functionalities and;
•
Update process.
The selection of applications and their operational approvals process
shall be based on applicable regulations such as the TGL-36 and
AC120-76A, referring to this platform as a Class II EFB System.
INFORMATION INTEGRITY
AOM-1502-016
The information provided by the Class II EFB platform shall be
considered advisory only and should not be used in place of any primary
flight display.
2-66
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electronic Flight Bag (EFB)
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
QRH ON BOARD
2-66
Copyright © by Embraer. Refer to cover page for details.
Page 2
Electronic Flight Bag (EFB)
REVISION 23
AOM-1502-016
The QRH with the latest revision incorporated must be on board in hard
copy format or in an equivalent electronic means. If Local Regulatory
Authority approval is required, it should be obtained by the Operator.
AIRPLANE
OPERATIONS
MANUAL
LIMITATIONS
RVSM OPERATION
MINIMUM EQUIPMENT REQUIRED
During RVSM operation it is necessary that the following equipment and
instruments be in proper operating condition:
– 2 RVSM Compliant Air Data Systems;
– 1 Autopilot with Altitude Hold Mode operative;
– 1 Altitude Alerter;
– 1 Transponder.
AOM-1502-016
NOTE: – The ADS 1, ADS 2 and ADS 3 are compliant with RVSM
operation.
– The ADS 3 is not considered RVSM compliant in case of
loss of sideslip compensation, i.e., with the EICAS message
ADS 3 SLIPCOMP FAIL displayed.
– The IESS must not be used for RVSM operation.
– Should any of the required equipment fail prior to the
airplane entering RVSM airspace, the pilot should request a
new clearance to avoid entering this airspace.
– An operating transponder may not be required for entry into
all designated RVSM airspace. The operator should
determine the requirement for an operational transponder
in each RVSM area where operations are intended. The
operator should also determine the transponder
requirements for transition areas next to RVSM airspace.
2-68
Copyright © by Embraer. Refer to cover page for details.
REVISION 12
RVSM Operation Limitations
Page 1
LIMITATIONS
AIRPLANE
OPERATIONS
MANUAL
2-68
Copyright © by Embraer. Refer to cover page for details.
Page 2
RVSM Operation Limitations
REVISION 12
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
SECTION 3
NORMAL PROCEDURES
TABLE OF CONTENTS
AOM-1502-016
Block
Page
Introduction.......................................................... 3-INTRO ....
1
Normal Checklist.................................................. 3-01 ...........
1
Supplementary Normal Checklist....................... 3-02 ...........
1
Internal Safety Inspection................................... 3-03 ...........
1
Power Up............................................................... 3-05 ...........
1
External Inspection.............................................. 3-07 ...........
1
Before Start........................................................... 3-09 ...........
1
Engine Start.......................................................... 3-11 ...........
1
After Start.............................................................. 3-13 ...........
1
Before Takeoff...................................................... 3-15 ...........
1
Takeoff................................................................... 3-16 ...........
1
After Takeoff......................................................... 3-17 ...........
1
Climb..................................................................... 3-18 ...........
1
Descent................................................................. 3-19 ...........
1
Approach............................................................... 3-21 ...........
1
Before Landing..................................................... 3-23 ...........
1
Go Around............................................................. 3-25 ...........
1
After Landing........................................................ 3-27 ...........
1
Shutdown.............................................................. 3-29 ...........
1
Leaving the Airplane............................................ 3-31 ...........
1
Required Equipment for Special Operations.... 3-60 ...........
1
3-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
Autoland................................................................ 3-69 ...........
1
Engine................................................................... 3-70 ...........
1
Bounced Landing................................................. 3-72 ...........
1
Environmental...................................................... 3-75 ...........
1
Communication.................................................... 3-76 ...........
1
Flight Instruments................................................ 3-80 ...........
1
RVSM OPERATION............................................... 3-94 ...........
1
Flight Patterns...................................................... 3-95 ...........
1
Category II............................................................. 3-97 ...........
1
3-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
Block
Page
Air Management System..................................... 3-68 ........... 1
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
INTRODUCTION
NORMAL PROCEDURES
The operating procedures defined in this section have been defined with
the purpose of providing expanded normal procedures that should be
used by trained flight crews to ensure that the airplane is in a proper
condition and correctly configured for each phase of flight.
In case any discrepancy between a procedure contained in this section
and the approved Airplane Flight Manual (AFM) occurs, the AFM
procedures must be followed. In the event that any of the procedures is
missing or unusable, operations may be continued provided the
approved AFM is available for use.
The normal procedures established are based on the assumption that all
equipment is operating normally. It is the crew’s responsibility to verify
proper system response. In case improper indications are observed,
verification of the appropriate controls position, checking of circuit
breakers and testing of the related system should be performed to
determine whether the condition affects dispatch or compliance with the
MMEL, and whether any maintenance action is required.
NORMAL CHECKLIST
The normal checklist is just a memory aid to assist the pilots so they do
not forget actions which, if not carried out, can result in some type of risk
to the airplane, to any of its systems, to its occupants, to the operational
environment or can affect passengers comfort. Specific regulations also
ask for items to be included in the checklist.
The normal checklist is named and divided according to each specific
phase of flight.
AOM-1502-016
The normal checklist further assumes that the pilots previously
accomplished the normal procedures.
3-INTRO
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-INTRO
Copyright © by Embraer. Refer to cover page for details.
Page 2
REVISION 9
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
INTERNAL SAFETY INSPECTION
Maintenance Status.............................................. CHECKED
Cockpit Emer Equip.............................................. CHECKED
ELECTRIC Panel.................................................. SET
FUEL Panel........................................................... CHECKED
PASSENGER SIGNS Panel................................. AS REQUIRED
Windshield Wiper.................................................. OFF
HYDRAULIC Panel............................................... CHECKED
AIR COND/PNEUMATIC Panel............................ CHECKED
PASSENGER OXYGEN Panel............................. CHECKED
ELT........................................................................ ARMED
Landing Gear Lever.............................................. DOWN
START/STOP Selectors........................................ STOP
Speed Brake Lever............................................... CLOSED
RAT Manual Deploy.............................................. STOWED
SLAT/FLAP Lever................................................. VERIFIED POS
Circuit Breakers.................................................... CHECKED
POWER UP
CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THE
IESS IS INITIALIZED.
Battery 1............................................................... ON
Battery 2............................................................... AUTO
CAUTION: VERIFY THAT ONLY DISPLAYS 2 AND 3 ARE AVAILABLE.
IF MORE THAN DISPLAYS 2 AND 3 ARE AVAILABLE, THE
AIRPLANE MUST NOT BE DISPATCHED.
Battery Voltage..................................................... CHECKED
GPU Button (if applicable).................................... PUSHED IN
AOM-1502-016
Emergency Lights Selector Knob......................... ON, THEN ARMED
FIRE EXTINGUISHER Panel............................... CHECKED
CONTINUED...
3-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Normal Checklist
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
APU....................................................................... AS REQUIRED
NAV Light.............................................................. ON
HYDRAULIC Panel............................................... AS REQUIRED
Electronic CBs...................................................... CHECKED
Electronic Checklist (if applicable)........................ CHECKED
DVDR Panel......................................................... CHECKED
Cockpit Reinforced Door Panel (if applicable)..... CHECKED
Photoluminescent Strips....................................... CHECKED
BEFORE START
PASSENGER SIGNS Panel................................. SET
PRESSURIZATION Panel.................................... SET
Oxygen Masks...................................................... CHECKED
Flight Instruments................................................. X-CHECKED
Thrust Levers........................................................ IDLE
..................................................................................................................
Fuel Quantity........................................................ CHECKED
MCDU................................................................... SET
TRIM Panel........................................................... _SET/ZERO/ZERO
Doors and Windows............................................. CLOSED
Red Beacon.......................................................... ON
Emergency/Parking Brake.................................... AS REQUIRED
AFTER START
Ground Equipment................................................ REMOVED
SLAT/FLAP........................................................... _SET
Flight Controls....................................................... CHECKED
Brakes Temperature............................................. CHECKED
CONTINUED...
3-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
Normal Checklist
REVISION 21
AOM-1502-016
BEFORE TAKEOFF
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
EICAS................................................................... CHECKED
Transponder.......................................................... TA/RA
Takeoff Configuration............................................ CHECKED
AFTER TAKEOFF
Landing Gear........................................................ UP
SLAT/FLAP........................................................... 0
APPROACH
PASSENGER SIGNS Panel................................. SET
Altimeters.............................................................. SET/X-CHECKED
BEFORE LANDING
Landing Gear........................................................ DOWN
SLAT/FLAP........................................................... _SET
SHUTDOWN
Emergency/Parking Brake.................................... SET
START/STOP Selectors........................................ STOP
Hydraulic Pump 3A............................................... OFF
LEAVING THE AIRPLANE
PASSENGER SIGNS Panel................................. OFF
GPU/APU.............................................................. OFF
AOM-1502-016
Batteries 1 and 2.................................................. OFF
3-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Normal Checklist
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
Normal Checklist
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ECS OFF TAKEOFF
SUPPLEMENTARY NORMAL CHECKLIST FOR ECS OFF TAKEOFF.
NOTE: – APU BLEED valve will supply bleed air for both PACKS
operation during takeoff until 500 ft. If APU BLEED is
unavailable the PACKS will remain OFF until 500 ft AGL.
– The APU bleed cannot be used for the anti-ice system
operation. If the REF A/I is set to ENG or ALL for takeoff or
ice is detected during takeoff with APU BLEED, the APU
BLEED VALVE will close and the PACKS will switch OFF.
BEFORE START
REF ECS................................................................ OFF
AFTER START
APU (if available).................................................... ON
AFTER TAKEOFF
AOM-1502-016
APU......................................................................... OFF
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENGINE CROSSBLEED START
SUPPLEMENTARY
NORMAL
CROSSBLEED START.
CHECKLIST
FOR
ENGINE
BEFORE START
Operating Engine Thrust Lever.............................. ADVANCE AS
REQUIRED
Bleed Pressure on ECS Synoptic Page................. CHECK
Engine Start............................................................ ACCOMPLISH
AFTER START
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 2
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
Thrust Levers.......................................................... AS REQUIRED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ENGINE GROUND PNEUMATIC START
SUPPLEMENTARY NORMAL CHECKLIST FOR ENGINE GROUND
PNEUMATIC START.
This procedure is used to start the RH engine. For LH engine perform a
crossbleed start.
BEFORE START
APU BLEED Button (if applicable)......................... PUSHED OUT
PACKS.................................................................... PUSHED OUT
Ground Cart............................................................ CONNECTED
Minimum Duct Pressure on ECS Synoptic Page... CHECK
Engine Start............................................................ ACCOMPLISH
AFTER START
AOM-1502-016
Ground Cart............................................................ DISCONNECTED
PACKS.................................................................... PUSHED IN
APU BLEED Button (if applicable)......................... PUSHED IN
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENGINE BATTERY START
SUPPLEMENTARY NORMAL CHECKLIST FOR ENGINE BATTERY
START.
BEFORE START
Internal Safety Inspection....................................... PERFORM
Battery 1.................................................................. ON
Battery 2.................................................................. AUTO
Batteries Voltage..................................................... CHECK
FIRE EXTINGUISHER Panel................................. CHECK
Hydraulic ENG PUMP SHUTOFF 1 and 2............. PUSH IN
Electric Hydraulic Pumps 1, 2, 3A and 3B............. OFF
PACKS.................................................................... PUSHED OUT
Pneumatic Source................................................... CHECK AVAILABLE
Minimum Duct Pressure on STATUS Synoptic
Page...................................................................... CHECK
Ignition Selector Knob............................................. AUTO
Red Beacon............................................................ ON
Engine Start............................................................ ACCOMPLISH
Ground Cart (If applicable)..................................... DISCONNECTED
AFTER START
.............................................Wait 2 minutes.............................................
PACKS.................................................................... PUSHED IN
After electrical PBIT is completed:
Hydraulic ENG PUMP SHUTOFF 1 and 2............. PUSHED OUT
Electric Hydraulic Pumps 1, 2 and 3B.................... AUTO
Electric Hydraulic Pumps 3A.................................. ON
SECOND ENGINE START
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 4
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
ENGINE CROSSBLEED START Procedure.......... PERFORM
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
SINGLE ENGINE TAXI
SUPPLEMENTARY NORMAL CHECKLIST FOR SINGLE ENGINE TAXI.
Engine 1 or 2 can be used for single engine taxi operation.
TAXI OUT
After one engine start up:
If using engine 2 for taxiing out:
Electric Hydraulic Pump 1 Selector Knob............ ON
Start the second engine with available time from takeoff to allow 2
minutes of thermal stabilization. Taxi time at or near IDLE can be
included in the engine warm up period.
Second Engine Start............................................... ACCOMPLISH
Electric Hydraulic Pump 1 Selector Knob.............. AUTO
TAXI IN
APU......................................................................... AS REQUIRED
If using engine 2 for taxiing in, before shutting down engine 1:
Electric Hydraulic Pump 1 Selector Knob............ ON
AOM-1502-016
After engines shutdown:
Electric Hydraulic Pump 1 Selector Knob............ AUTO
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
HOT WEATHER OPERATION
NOTE: When engine is shutdown, apply cool air from the air
conditioning cart whenever possible.
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 6
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
AIR COND RECIRC Button.................................... PUSHED IN
CKPT/PAX CABIN Temperature Controllers.......... MAX COLD
Doors and Windows................................................ KEEP CLOSED
Passenger Cabin Gasper and Cockpit Outlets...... OPEN
Window Shades on the Sun-exposed Side of the
Cabin..................................................................... CLOSED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ICING CONDITIONS, COLD WEATHER AND COLD
SOAK OPERATIONS
SUPPLEMENTARY NORMAL CHECKLIST FOR ICING CONDITIONS,
COLD WEATHER AND COLD SOAK OPERATIONS.
POWER UP
Batteries.................................................................. CHECK
INSTALLED/
CONDITIONS
External Power (if available)................................... CHECK
Accomplish a normal power up.
After the electric PBIT is done and the message FLT CTRL TEST IN
PROG disappears:
Hydraulic System Warm Up................................... ACCOMPLISH
Electric Hydraulic Pumps Sys 1 and 3A................. ON
PTU......................................................................... ON
..........................................Wait 30 seconds..........................................
PTU......................................................................... AUTO
Electric Hydraulic Pump Sys 2............................... ON
SLAT/FLAP............................................................. CHECKED
Fuel Temperature.................................................... CHECK
AOM-1502-016
EXTERNAL SAFETY INSPECTION
Wheel Chocks......................................................... IN PLACE
Smart Probes/TAT................................................... CHECK
Air Conditioning Inlets/Outlets................................ CLEAR OF ICE
All Protective Covers.............................................. CHECK REMOVED
Engine..................................................................... CLEAR OF ICE OR
SNOW
Landing Gear.......................................................... CLEAR OF ICE,
UNOBSTRUCTED
Fuselage, Wing, Tail and Control Surfaces............ FREE OF FROST,
ICE OR SNOW
APU Area................................................................ CLEAR OF ICE OR
SNOW
CONTINUED...
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Pressurization Static Port....................................... CLEAR OF ICE
CABIN WARM UP
Doors....................................................................... CLOSED
Air Conditioning Pneumatic Panel.......................... SET
BEFORE START
TO DATASET MENU.............................................. SET
ADS Probe Heaters................................................ AS REQUIRED
AFTER START
Engine Instruments................................................. MONITOR
Main Panel.............................................................. CHECK
Steering................................................................... ENGAGE
Electric Hydraulic Pumps SYS 1 & 2..................... AUTO
ADS Probe Heater.................................................. PUSHED OUT
AIRPLANE ANTI-ICING/DEICING FLUID APPLICATION
WITH ENGINES/APU RUNNING
CAUTION: APU OPERATION IS NOT RECOMMENDED DURING THE
AIRPLANE DEICING/ANTI-ICING PROCEDURE. IF APU
OPERATION IS ABSOLUTELY NECESSARY, MAKE SURE
THAT DEICING/ANTI-ICING FLUID IS NOT APPLIED
DIRECTLY TO OR NEAR THE APU AIR INLET, THE APU
BLEED AIR VALVE IS CLOSED, AND THE PACKS ARE
SET TO OFF.
After Deicing/Anti-icing Procedure is complete:
CONTINUED...
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 8
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
Parking Brake......................................................... ON
Doors....................................................................... CHECK CLOSED
Thrust Levers.......................................................... IDLE
SLAT/FLAP............................................................. CHECK UP
Pitch Trim................................................................ FULL NOSE DOWN
Engine Bleed........................................................... PUSHED OUT
APU Bleed.............................................................. PUSHED OUT
Packs...................................................................... PUSHED OUT
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
......................................Wait at least 1 minute......................................
APU Bleed Button................................................... PUSHED IN
Engine Bleed Buttons............................................. PUSHED IN
.....................................Wait at least 3 minutes.....................................
Packs Buttons......................................................... PUSHED IN
TAXI
Ground Speed Taxi................................................. AS LOW AS
PRACTICAL
Engine Run-Up....................................................... AS REQUIRED
SLAT/FLAP............................................................. AS REQUIRED
WARNING: IF FLAPS/SLATS WERE LEFT UP DURING TAXI,
COMPLETE AFTER START CHECKLIST BEFORE
TAKING OFF.
CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS
TO AVOID SKIDDING THE AIRPLANE. REDUCE SPEED
FOR ALL TURNS AND USE CAUTION WHEN TAXING
WITH HIGH CROSSWINDS.
BEFORE TAKEOFF
Flight Controls......................................................... CHECK
Pitch Trim................................................................ SET
SLAT/FLAP............................................................. SET
Takeoff Configuration.............................................. CHECK
Ice Accumulation..................................................... CHECK
Engine Run-Up....................................................... AS REQUIRED
IN FLIGHT
Engine Parameters................................................. MONITOR
Pitch Attitude and Airspeed..................................... MONITOR
AOM-1502-016
DESCENT
If engine vibration increases reduce the thrust to idle, advance thrust
levers to obtain 70% N1 for 10-30 s and then return to the desired
setting.
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
HOLDING
Landing Gear.......................................................... UP
SLAT/FLAP............................................................. UP
Minimum Airspeed.................................................. 210 KIAS
TAXI-IN AND PARKING
Engine and Wing Anti Ice Protection...................... AS REQUIRED
SLAT/FLAP............................................................. AS REQUIRED
CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS
TO AVOID SKIDDING THE AIRPLANE AND THROWING
SLUSH ON WHEEL AND BRAKE ASSEMBLIES.
NOTE: – Make sure the slat/flap are free from snow, ice or slush
before retracting them.
– If any difference is felt while taxiing, verify if tires present any
flat spot which may indicate that the brake was blocked at
touchdown.
THROUGH-FLIGHTS
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 10
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
Doors and Windows................................................ CLOSED
APU (if available).................................................... ON
Wing, Tail and Control Surfaces............................. FREE OF FROST,
ICE OR SNOW
Air Data Smart and TAT Probes............................. CLEAR OF ICE
Engine/APU Air Inlet............................................... CLEAR OF ICE OR
SNOW
Landing Gear.......................................................... CLEAR OF ICE,
UNOBSTRUCTED
Air Conditioning Inlets and Outlets......................... CLEAR OF ICE
Fuel Tank Vents...................................................... CLEAR OF ICE OR
SNOW
Pressurization Static Port....................................... CLEAR OF ICE
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
LEAVING THE AIRPLANE - SECURING FOR COLD
SOAK OR AN EXTENDED PERIOD
AOM-1502-016
SLAT/FLAP............................................................. UP
Pitch Trim................................................................ FULL DOWN
Wheel Chocks......................................................... CHECK IN PLACE
Emergency/Parking Brakes.................................... AS REQUIRED
Protective Covers.................................................... CHECK
INSTALLED
Water and Waste System....................................... CHECK DRAINED
Batteries.................................................................. CHECK REMOVED
Doors....................................................................... CHECK CLOSED
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 11
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
LIGHTNING STRIKE
SUPPLEMENTARY NORMAL CHECKLIST FOR LIGHTNING STRIKE.
ON GROUND - IF THE AIRPLANE HAS BEEN HIT BY
LIGHTNING
External Safety Inspection
Holes, Punctures, Discoloration and De-lamination
throughout the Whole Airframe............................. CHECK
Loose, Melted or Missing Rivets............................ VERIFY
Static Dischargers................................................... NUMBER AND
CONDITION
Nose Gear Landing and Taxi Lights....................... CONDITION
Wing Inspection, Landing and Taxi Lights.............. CONDITION
Navigation, Strobe and Red Beacon Lights........... CONDITION
Smart Probes/TAT Sensor/Ice Detectors................ CHECK
Radome................................................................... CHECK
Antennas................................................................. CONDITION
Maintenance proceeded in accordance with AMM
MPP 05-50-01/601 before flight............................ CONFIRM
IN FLIGHT - IF A LIGHTNING STRIKE IS LIKELY TO
OCCUR
Penetration of Thunderstorm.................................. AVOID
Visual Contact with Thunderstorm and Lightning... MAINTAIN
Weather Radar........................................................ CHECK FOR
PRECIPITATION
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 12
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
NOTE: Remember that radar detects only liquid droplets, not the cloud
itself.
Thundercloud Detected........................................... CIRCUMNAVIGATE
All Cockpit Lights.................................................... ON/FULL
BRIGHTNESS
Sunglasses.............................................................. CONSIDER WEAR
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
IN FLIGHT - IF THE AIRPLANE HAS BEEN HIT BY
LIGHTNING
Apply the associated emergency/abnormal procedure if any failure arises
after a lightning strike. If the situation is under control after a lightning
strike, apply the following procedure to ascertain whether the flight may
proceed safely.
Altitude.................................................................... MAINTAIN
If not required by performance, obstacle clearance or operational
contingencies, stop climbing during airplane check.
Circuit Breakers...................................................... CHECK
Navigation Systems................................................ CHECK
Engine Indication.................................................... CHECK
Pressurization......................................................... CHECK
Flight Controls......................................................... CHECK
Fuel System............................................................ CHECK
All Other Airplane Systems..................................... CHECK
Communication Systems........................................ CHECK
NOTE: Consider discontinuing the flight and land at the nearest suitable
airport if any unsafe condition is revealed after checking systems
operation. Report lightning strike to maintenance personnel by
filling out the LIGHTNING STRIKE INCIDENT REPORT form.
Report the difference between magnetic compass and PFD
heading indications. Report any effects on the airplane systems.
AFTER LANDING
AOM-1502-016
Lightning Strike Event............................................. REPORT TO
MAINTENANCE
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 13
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
TURBULENT AIR PENETRATION
Airspeed.................................................................. ADJUST
The recommended turbulent air penetration target speeds are:
Altitude
Below 10000 ft
At or above 10000 ft
Recommended speed
250 KIAS
MAX 270 KIAS/0.76 M
WHICHEVER IS LOWER
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 14
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
NOTE: – Do not extend flaps except for approach and landing.
– Do not chase altitude. Let both altitude and airspeed vary
and maintain attitude.
– If severe turbulence cannot be avoided disconnect
Autothrottle and make an initial thrust setting for the target
speed. Maintain Attitude and Pitch Trim setting.
– During climb or descent with variations in indicated airspeed,
the use of FLCH mode may result in airplane pitch changes.
The use of FPA mode is recommended to maintain airplane
attitude.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
CATEGORY II
SUPPLEMENTARY NORMAL CHECKLIST FOR CATEGORY II
OPERATION.
APPROACH
!Airplanes equipped with Autoland system
NOTE: (On airplanes equipped with autoland system) To accomplish
CAT II approach procedures without autoland, the autoland
function must be disabled on the MCDU.
"
Descent and Approach Checklists.......................... ACCOMPLISH
Approach Speeds................................................... SET
RA/BARO Selector Knob........................................ RA
CAT II Decision Height........................................... SET ON BOTH
SIDES
Radio Altimeter (if only one is available)................ TEST
ILS frequency.......................................................... SET ON BOTH
MCDU
BEFORE LANDING
Before Landing Checklist........................................ ACCOMPLISH
NOTE: – If the RA is set to OFF, there is no EGPWS approach call
outs.
– If no visual contact is made upon reaching the decision
height or if any malfunction could not be promptly identified
during approach, a missed approach must be immediately
initiated.
MISSED APPROACH
GO-AROUND Procedure........................................ ACCOMPLISH
LANDING
AOM-1502-016
Reaching the Decision Height with runway in sight:
Autopilot.................................................................. DISENGAGE
Landing................................................................... PERFORM
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 15
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
!Airplanes equipped with Autoland system
AUTOLAND
SUPPLEMENTARY
OPERATION.
NORMAL
CHECKLIST
FOR
AUTOLAND
"
!Airplanes equipped with Autoland system
BEFORE TAKEOFF
Autoland.................................................................. CHECK ENABLE
ON MCDU
"
!Airplanes equipped with Autoland system
DESCENT
RA/BARO Minimums.............................................. SET ON BOTH
SIDES
"
!Airplanes equipped with Autoland system
APPROACH
ILS frequency.......................................................... SET OR VERIFY
Flaps....................................................................... 5
"
!Airplanes equipped with Autoland system
MISSED APPROACH
Go-around procedure.............................................. ACCOMPLISH
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 16
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
!Airplanes equipped with Autoland system
LANDING
NOTE: Five seconds after touchdown, autopilot disengages and pilot
is responsible for speed and directional control.
AOM-1502-016
"
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 17
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
!RNP AR operation, Airplanes PRE-MOD MAU LOAD 27.1.
RNP AR OPERATION (PRE-MOD LOAD 27.1)
SUPPLEMENTARY NORMAL CHECKLIST FOR RNP AR OPERATION
APPLICABLE TO AIRPLANES PRE-MOD MAU LOAD 27.1.
"
PRIOR TO FLIGHT
Airplane Minimum Configuration............................. CHECK
FMS Position........................................................... INITIALIZE
NAV Database........................................................ VERIFY
CURRENCY
Flight Plan............................................................... ACTIVATE
Performance INIT.................................................... SET/CONFIRM
INIT
NOTAM NAVAIDS................................................... INSERT
GPS NOTAMS........................................................ INSERT
RNP Predictive RAIM............................................. CHECK
Approach Chart Notes............................................ CHECK
Takeoff Pages......................................................... SET/CONFIRM
INIT
PFD NAV Source.................................................... SELECT FMS
Speed Selector Knob.............................................. AS REQUIRED
LNAV....................................................................... AS REQUIRED
VNAV....................................................................... AS REQUIRED
APPROACH BRIEFING
Equipment Required............................................... VERIFY
VOR/DME and DME/DME Sensors........................ DESELECT
Approach Procedure............................................... CONFIRM
Temperature Compensation (if applicable)............. ACTIVATE
RNP Value.............................................................. VERIFY/SET
Landing Speeds...................................................... VERIFY
Approach Speeds................................................... VERIFY
CONTINUED...
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 18
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
APPROACH
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Go-around Speeds.................................................. VERIFY
.................................................At the IAF.................................................
Altimeters................................................................ SET/X-CHECK
..........................Throughout all the approach sequence..........................
Track Deviation....................................................... MONITOR
........................................2NM before the FAF........................................
APPR Annunciation................................................. CHECK
................................................At the FAF................................................
Speed Selector Knob.............................................. MAN
RNP APPROACH OPERATION (PRE-MOD LOAD 27.1)
SUPPLEMENTARY NORMAL CHECKLIST FOR RNP APPROACH
OPERATION APPLICABLE TO AIRPLANES PRE-MOD MAU LOAD
27.1.
PRE FLIGHT
Airplane Minimum Configuration............................. CHECK
Nav Database......................................................... VERIFY
CURRENCY
FMS Position........................................................... INITIALIZE
Approach Chart....................................................... CHECK
Flight Plan............................................................... ACTIVATE
Performance INIT.................................................... SET/CONFIRM
INIT
NOTAM NAVAIDS................................................... INSERT
GPS NOTAM........................................................... INSERT
GPS PREDICTIVE RAIM........................................ CHECK
Takeoff Page........................................................... SET/CONFIRM
PFD NAV Source.................................................... SELECT FMS
AOM-1502-016
APPROACH BRIEFING
Equipment Required............................................... VERIFY
Approach Procedure............................................... CONFIRM
Navigation Sensor................................................... CONFIRM
Temperature Compensation.................................... AS REQUIRED
3-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Supplementary Normal Checklist
Page 19
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
APPROACH
Landing Speeds...................................................... VERIFY
Approach Speeds................................................... VERIFY
Go-around Speeds.................................................. VERIFY
.................................................At the IAF.................................................
Altimeters................................................................ SET/X-CHECK
.........................During all the RNP approach procedure.........................
Track Deviation....................................................... MONITOR
........................................2 NM before the FAF........................................
APPR Annunciation................................................. CHECK
3-02
Copyright © by Embraer. Refer to cover page for details.
Page 20
Supplementary Normal Checklist
REVISION 23
AOM-1502-016
................................................At the FAF................................................
Speed Selector Knob.............................................. MAN
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
INTERNAL SAFETY INSPECTION
The Internal Safety Inspection procedures must be performed before the
Power Up on a particular airplane.
Maintenance Status................................................ CHECK
Cockpit Emergency Equipment.............................. CHECK
Check for the availability, status and proper location of the following
equipment:
– Protective Breathing Equipment (PBE).
– Fire Extinguishers.
– Crash Axe.
– Life Vests.
– Escape Ropes.
– Flashlights.
ELECTRIC Panel.................................................... SET
IDG 1 Selector...................................................... AUTO
IDG 2 Selector...................................................... AUTO
AC BUS TIES Selector......................................... AUTO
GPU Button........................................................... PUSH OUT
APU GEN Button.................................................. PUSH IN
TRU 1................................................................... AUTO
TRU ESS.............................................................. AUTO
TRU 2................................................................... AUTO
DC BUS TIES....................................................... AUTO
Battery 1 Selector................................................. OFF
Battery 2 Selector................................................. OFF
!190 Models Commercial Airplanes Non-ETOPS Configured - partially compliant or
not at all compliant with FAA CMP-2925 or ANAC CMP-2356
FUEL Panel............................................................. CHECK
Verify all fuel pumps knobs in AUTO position and XFEED in the
desired position.
"
AOM-1502-016
PASSENGER SIGNS Panel................................... AS REQUIRED
Set the NO SMOKE sign at ON during all flight phases.
CONTINUED...
3-03
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Internal Safety Inspection
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
WINDSHIELD WIPER Selector.............................. OFF
HYDRAULIC Panel................................................. CHECK
SYS 1 ENG PUMP SHUTOFF Button................. PUSH OUT
PTU Selector........................................................ AUTO
SYS 2 ENG PUMP SHUTOFF Button................. PUSH OUT
SYS 1 and 2 ELEC PUMP Selectors................... AUTO
SYS 3 ELEC PUMP A.......................................... OFF
SYS 3 ELEC PUMP B.......................................... AUTO
AIR COND/PNEUMATIC Panel.............................. CHECK
Verify all buttons pushed in.
PASSENGER OXYGEN Panel............................... CHECK
Verify Masks Deploy Selector Knob in Auto.
ELT.......................................................................... ARM
Landing Gear Lever................................................ DOWN
START/STOP Selectors.......................................... STOP
Speed Brake Lever................................................. CLOSE
RAT Manual Deploy................................................ STOW
SLAT/FLAP Lever................................................... VERIFY POSITION
Verify and make sure that the actual SLAT/FLAP Lever position
agrees with the surface position.
Circuit Breakers...................................................... CHECK
3-03
Copyright © by Embraer. Refer to cover page for details.
Page 2
Internal Safety Inspection
REVISION 20
AOM-1502-016
Verify both sidewall panels to ensure agreement with maintenance
status.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
POWER UP
The POWER UP procedures and checklist must be performed every
crew’s first flight of the day on a particular airplane or when a power
down was required.
If receiving the airplane already powered up, verify compliance with all
items and perform FIRE EXTINGUISHER panel, Electronic CBs and
DVDR CONTROL panel.
CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THE
IESS IS INITIALIZED.
Battery 1.................................................................. ON
Battery 2.................................................................. AUTO
CAUTION: – VERIFY THAT ONLY DISPLAYS 2 AND 3 ARE
AVAILABLE.
– IF MORE THAN DISPLAYS 2 AND 3 ARE AVAILABLE,
THE AIRPLANE MUST NOT BE DISPATCHED.
Batteries Voltage..................................................... CHECK
AOM-1502-016
CAUTION: EACH BATTERY VOLTAGE MUST BE AT LEAST 22
VOLTS.
IF BATTERIES VOLTAGE IS BETWEEN 21 VOLTS AND 22
VOLTS, RECHARGE THE BATTERIES PRIOR TO
TAKEOFF, THROUGH ANY AC SOURCE (INCLUDING
ENGINES DURING TAXI) FOR:
– 30 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE 0°C OR;
– 35 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE -5°C AND BELOW 0°C OR;
– 40 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE -10°C AND BELOW -5°C OR;
– 50 MINUTES IF BATTERIES TEMPERATURE IS
BELOW -10°C.
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.2
REVISION
Power Up
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
IF BATTERIES VOLTAGE IS BELOW 21 VOLTS REPORT
TO MAINTENANCE.
NOTE: Minimize the time the airplane is left with batteries as the unique
power source, to avoid discharging.
EICAS Messages.................................................... CHECK
DISPLAYED
NOTE: From the preflight to the taxiing phase, a transient power state
may prompt temporary EICAS messages such as:
AVNX MAU 1A FAIL
AVNX MAU 1B FAIL
AVNX MAU 2A FAIL
AVNX MAU 2B FAIL
AVNX MAU 3A FAIL
AVNX MAU 3B FAIL
Other EICAS messages may cascade. Also, display units may
blink, but these effects are transitory, disappearing within one
minute. They do not require action from the flight crew.
GPU Button (if applicable)...................................... PUSH IN
Verify AVAIL light illuminated before pushing in. When GPU is not
available, or is not necessary, maintain GPU Button pushed out.
NOTE: – The Electrical PBIT is automatically performed after the
airplane is powered by any AC source and takes about 3 min
to complete. The Electrical PBIT will be interrupted if any
electric hydraulic pump is running, or if the FLIGHT
CONTROL MODE Panel switches are cycled, or if AC power
is interrupted while the test is running.
– A FLT CTRL TEST IN PROG Status message is displayed to
inform the pilot that the Electrical PBIT is in progress.
– If the displays 2 and/or 4 are configured as PFD, set the
respective reversionary panel selector knob to MFD then to
AUTO. After 8 seconds, the affected display configuration
will return to MFD.
Emergency Lights Selector Knob........................... ON
Verify there are no fire protection fail messages displayed on the
EICAS after Power Up.
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 2
Power Up
TEMP.
REVISION
23.2
AOM-1502-016
Verify the EMER LT ON and EMER LT NOT ARMED messages
displayed on the EICAS.
Emergency Lights Selector Knob........................... ARMED
FIRE EXTINGUISHER Panel (Overhead).............. CHECK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Press and hold the TEST button and observe the following EICAS
messages, lights and warnings:
– Aural warning.
– Fire handles illuminated.
– CARGO SMOKE FWD/AFT Buttons illuminated.
– APU Button illuminated.
– Upper half of the APU EMER STOP Button illuminated.
– WARNING lights flashing.
– ″CARGO AFT SMOKE″ EICAS message.
– ″CARGO FWD SMOKE″ EICAS message.
– ″APU FIRE″ EICAS message.
– ″ENG 1 FIRE″ EICAS message.
– ″ENG 2 FIRE″ EICAS message.
– ″FIRE″ warning annunciation displayed inside ITT indicators.
APU CONTROL Panel............................................ AS REQUIRED
Verify EMER STOP Button is pushed out and not illuminated.
The APU FADEC is ready for use when APU rpm and EGT dashed
indications (--) are replaced by numbers.
NOTE: If AC source is lost due to unintentional GPU or APU generator
disconnection, power down the airplane and perform the power
up procedure.
Navigation Light...................................................... ON
HYDRAULIC Panel................................................. AS REQUIRED
Only after the electrical PBIT is completed and if the
FLT CTRL BIT EXPIRED EICAS message is displayed, perform the
hydraulic PBIT.
– Do not move any flight control surface.
!Pre-Mod LOAD 25.7
– Turn on the Electrical Hydraulic Pumps 1, 2 and 3A.
"
!Post-Mod LOAD 25.7 and on AND Pre-mod LOAD 27.1
– Turn on the Electrical Hydraulic Pumps within 6 s in the following
sequence: 3A, 1 and 2.
"
AOM-1502-016
– Wait 1 min. At this point the FLT CTRL BIT EXPIRED EICAS
message should extinguish.
– Turn Electrical Hydraulic Pumps 1 and 2 to AUTO.
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.2
REVISION
Power Up
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Turn Electrical Hydraulic Pump 3A to OFF.
NOTE: – The FLT CTRL TEST IN PROG Status message is
displayed while hydraulic PBIT is in progress.
– If the FLT CTRL BIT EXPIRED EICAS message is still
displayed, power down the airplane and perform a power
up procedure.
Electronic CBs........................................................ CHECK
– Select CB OUT/LOCK page on the MCDU and check the CBs status
to ensure agreement with maintenance status.
– If the NEW TRIP prompt is displayed on the MCDU press it to check
the electronic CBs status.
Electronic Checklist (if applicable).......................... CHECK
Verify that this ECL database corresponds to the paper QRH revision
present in the cockpit.
DVDR CONTROL Panel......................................... CHECK
Honeywell DVDR or L3 DVDR: Press and hold the TEST button for
three seconds and verify no fail messages displayed on EICAS.
Universal DVDR: Press and hold the TEST button for two seconds.
Verify no fail messages displayed on EICAS and observe the following
test result:
– The FDR 1 and CVR 1 PASS/FAIL lights flash during ten seconds.
After ten seconds the FDR 1 and CVR 1 PASS/FAIL lights illuminate
steady in green, indicating the completion of a successful test.
After DVDR 1 test finishes, the DVDR 2 test will automatically start.
Verify the following test result:
– The FDR 2 and CVR 2 PASS/FAIL lights flash during ten seconds.
After ten seconds the FDR 2 and CVR 2 PASS/FAIL lights illuminate
steady in green, indicating the completion of a successful test.
If a failure is found, the corresponding FDR/CVR fail light indicator will
illuminate steady in amber.
!Airplanes equipped with Electronic Flight Bag (EFB)
Electronic Flight Bag............................................... ON
Cockpit Door Control Panel.................................... CHECK
– Close the cockpit door;
– Press and hold the TEST button;
– Check DING-DONG alarm and UNLOCKED indication on;
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 4
Power Up
TEMP.
REVISION
23.2
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
– Push in the LOCK button and check the electromechanical latch
normal operation;
– Press the EMERG ENTRY button on the door control panel in the
passenger cabin. Check the UNLOCKED indication flashing and
check normal operation of the DING-DONG alarm sequence
according to the system logic (refer to AOM 14-01-22 and 14-01-60);
– Push out the LOCK button.
Photoluminescent Strips......................................... CHECK
AOM-1502-016
Be sure that at least 15 min of ceiling and entrance lighting exposure
in bright or daylight to charge the photoluminescent strips.
3-05
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.2
REVISION
Power Up
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 6
Power Up
TEMP.
REVISION
23.2
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
POWER UP
The POWER UP procedures and checklist must be performed every
crew’s first flight of the day on a particular airplane or when a power
down was required.
If receiving the airplane already powered up, verify compliance with all
items and perform FIRE EXTINGUISHER panel, Electronic CBs and
DVDR CONTROL panel.
CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THE
IESS IS INITIALIZED.
Battery 1.................................................................. ON
Battery 2.................................................................. AUTO
CAUTION:
•
•
VERIFY THAT ONLY DISPLAYS 2 AND 3 ARE
AVAILABLE.
IF MORE THAN DISPLAYS 2 AND 3 ARE AVAILABLE,
THE AIRPLANE MUST NOT BE DISPATCHED.
Batteries Voltage..................................................... CHECK
AOM-1502-016
CAUTION: EACH BATTERY VOLTAGE MUST BE AT LEAST 22
VOLTS.
IF BATTERIES VOLTAGE IS BETWEEN 21 VOLTS AND 22
VOLTS, RECHARGE THE BATTERIES PRIOR TO
TAKEOFF, THROUGH ANY AC SOURCE (INCLUDING
ENGINES DURING TAXI) FOR:
• 30 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE 0°C OR;
• 35 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE -5°C AND BELOW 0°C OR;
• 40 MINUTES IF BATTERIES TEMPERATURE IS AT OR
ABOVE -10°C AND BELOW -5°C OR;
• 50 MINUTES IF BATTERIES TEMPERATURE IS
BELOW -10°C.
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Power Up
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
IF BATTERIES VOLTAGE IS BELOW 21 VOLTS REPORT
TO MAINTENANCE.
NOTE: Minimize the time the airplane is left with batteries as the unique
power source, to avoid discharging.
EICAS Messages.................................................... CHECK
DISPLAYED
NOTE: From the preflight to the taxiing phase, a transient power state
may prompt temporary EICAS messages such as:
AVNX MAU 1A FAIL
AVNX MAU 1B FAIL
AVNX MAU 2A FAIL
AVNX MAU 2B FAIL
AVNX MAU 3A FAIL
AVNX MAU 3B FAIL
Other EICAS messages may cascade. Also, display units may
blink, but these effects are transitory, disappearing within one
minute. They do not require action from the flight crew.
GPU Button (if applicable)...................................... PUSH IN
Verify AVAIL light illuminated before pushing in. When GPU is not
available, or is not necessary, maintain GPU Button pushed out.
NOTE: – The Electrical PBIT is automatically performed after the
airplane is powered by any AC source and takes about 3 min
to complete. The Electrical PBIT will be interrupted if any
electric hydraulic pump is running, or if the FLIGHT
CONTROL MODE Panel switches are cycled, or if AC power
is interrupted while the test is running.
– A FLT CTRL TEST IN PROG Status message is displayed to
inform the pilot that the Electrical PBIT is in progress.
– If the displays 2 and/or 4 are configured as PFD, set the
respective reversionary panel selector knob to MFD then to
AUTO. After 8 seconds, the affected display configuration
will return to MFD.
Emergency Lights Selector Knob........................... ON
Verify there are no fire protection fail messages displayed on the
EICAS after Power Up.
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 2
Power Up
REVISION 23
AOM-1502-016
Verify the EMER LT ON and EMER LT NOT ARMED messages
displayed on the EICAS.
Emergency Lights Selector Knob........................... ARMED
FIRE EXTINGUISHER Panel (Overhead).............. CHECK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Press and hold the TEST button and observe the following EICAS
messages, lights and warnings:
– Aural warning.
– Fire handles illuminated.
– CARGO SMOKE FWD/AFT Buttons illuminated.
– APU Button illuminated.
– Upper half of the APU EMER STOP Button illuminated.
– WARNING lights flashing.
– ″CARGO AFT SMOKE″ EICAS message.
– ″CARGO FWD SMOKE″ EICAS message.
– ″APU FIRE″ EICAS message.
– ″ENG 1 FIRE″ EICAS message.
– ″ENG 2 FIRE″ EICAS message.
– ″FIRE″ warning annunciation displayed inside ITT indicators.
APU CONTROL Panel............................................ AS REQUIRED
Verify EMER STOP Button is pushed out and not illuminated.
The APU FADEC is ready for use when APU rpm and EGT dashed
indications (--) are replaced by numbers.
NOTE: If AC source is lost due to unintentional GPU or APU generator
disconnection, power down the airplane and perform the power
up procedure.
Navigation Light...................................................... ON
HYDRAULIC Panel................................................. AS REQUIRED
AOM-1502-016
Only after the electrical PBIT is completed and if the
FLT CTRL BIT EXPIRED EICAS message is displayed, perform the
hydraulic panel checks.
– Do not move any flight control surface.
– Turn the Electrical Hydraulic Pumps 1, 2 and 3A to ON.
– Wait 1 min. At this point the FLT CTRL BIT EXPIRED EICAS
message should extinguish.
– Turn Electrical Hydraulic Pumps 1 and 2 to AUTO.
– Turn Electrical Hydraulic Pump 3A to OFF.
NOTE: – The FLT CTRL TEST IN PROG Status message is
displayed while hydraulic PBIT is in progress.
– If the FLT CTRL BIT EXPIRED EICAS message is still
displayed, power down the airplane and perform a power
up procedure.
Electronic CBs........................................................ CHECK
– Select CB OUT/LOCK page on the MCDU and check the CBs
status to ensure agreement with maintenance status.
– If the NEW TRIP prompt is displayed on the MCDU press it to
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Power Up
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
check the electronic CBs status.
Electronic Checklist (if applicable).......................... CHECK
Verify that this ECL database corresponds to the paper QRH revision
present in the cockpit.
DVDR CONTROL Panel......................................... CHECK
Honeywell DVDR or L3 DVDR: Press and hold the TEST button for
three seconds and verify no fail messages displayed on EICAS.
Universal DVDR: Press and hold the TEST button for two seconds.
Verify no fail messages displayed on EICAS and observe the following
test result:
– The FDR 1 and CVR 1 PASS/FAIL lights flash during ten seconds.
After ten seconds the FDR 1 and CVR 1 PASS/FAIL lights
illuminate steady in green, indicating the completion of a successful
test.
After DVDR 1 test finishes, the DVDR 2 test will automatically start.
Verify the following test result:
– The FDR 2 and CVR 2 PASS/FAIL lights flash during ten seconds.
After ten seconds the FDR 2 and CVR 2 PASS/FAIL lights
illuminate steady in green, indicating the completion of a successful
test.
If a failure is found, the corresponding FDR/CVR fail light indicator will
illuminate steady in amber.
!Airplanes equipped with Electronic Flight Bag (EFB)
Electronic Flight Bag............................................... ON
Cockpit Door Control Panel.................................... CHECK
– Close the cockpit door;
– Press and hold the TEST button;
– Check DING-DONG alarm and UNLOCKED indication on;
– Push in the LOCK button and check the electromechanical latch
normal operation;
– Press the EMERG ENTRY button on the door control panel in the
passenger cabin. Check the UNLOCKED indication flashing and
check normal operation of the DING-DONG alarm sequence
according to the system logic (refer to AOM 14-01-22 and
14-01-60);
– Push out the LOCK button.
Photoluminescent Strips......................................... CHECK
CONTINUED...
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 4
Power Up
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
AOM-1502-016
Be sure that at least 15 min of ceiling and entrance lighting exposure
in bright or daylight to charge the photoluminescent strips.
3-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Power Up
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-05
Copyright © by Embraer. Refer to cover page for details.
Page 6
Power Up
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
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AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
EXTERNAL INSPECTION
While conducting the external inspection, pilots must be aware of moving
vehicles around the airplane and surroundings.
In case of suspicious object is identified, inform immediately the security
staff.
Prior to starting the external inspection:
External Lights........................................................ AS REQUIRED
If the external lights check was not performed by the maintenance,
turn the external lights ON and check them. Turn the lights OFF
immediately after checking them.
Emergency/Parking Brake...................................... ON
AOM-1502-016
Check if there is sufficient hydraulic pressure to activate the
Emergency/Parking Brake to check the Brake Wear Indicators.
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
External Inspection
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
EM170AOM980019.DGN
...CONTINUED
Recommended walk-around sequence
1. LEFT FWD FUSELAGE
FWD Pax Door........................................................ CHECKED
External Power Receptacle.................................... SECURED
Left Smart Probes/TAT Sensor/Ice Detector.......... CHECKED
Verify condition with no obstructions, covers or damage.
2. NOSE SECTION
Windshield Wipers.................................................. CHECKED
Radome................................................................... CONDITION,
LATCHED
Forward Avionics Compartment.............................. SECURED
If not in use, visibly secured.
Lower FWD Antenna............................................... CONDITION
3. NOSE LANDING GEAR
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
Page 2
External Inspection
REVISION 23
AOM-1502-016
Undamaged.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Nose Gear............................................................ CHECKED
Wheels and Tires.................................................. CONDITION
Up Lock Hook....................................................... UNLOCKED
Strut/Wheel Well/Doors........................................ CONDITION,
NO LEAKS
Ground Locking Pin.............................................. REMOVED
Landing and Taxi Lights........................................ CONDITION
Clean and undamaged.
Downlock Springs................................................. CONDITION
4. RIGHT FWD FUSELAGE
Right Smart Probes/TAT Sensor/Ice Detector........ CHECKED
Verify condition with no obstructions, covers or damage.
RAT Safety Lock Pin............................................... REMOVED
FWD Service Door.................................................. CHECKED
If not in use, visibly secured.
Oxygen Discharge Indicator................................... GREEN DISC
FWD Cargo Door.................................................... CHECKED
If not in use, visibly secured.
5. LOWER CENTER FUSELAGE
Lower FWD Antennas/FWD Drain Mast................. CONDITION
Undamaged.
Lower Red Beacon Light........................................ CONDITION
Clean and undamaged.
6. RIGHT CENTER WING
Wing Inspection Landing and Taxi Lights............... CONDITION
Clean and undamaged.
Right Ram Air Inlet.................................................. NO
OBSTRUCTION
AOM-1502-016
No obstruction or damage.
Air Inlets and Outlets.............................................. NO
OBSTRUCTION
No obstruction or damage.
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
External Inspection
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Collector Tank Water Drain Valve Door.................. SECURED
If not in use, visibly secured.
RH 1 and RH 2 Magnetic Level Indicators............. PUSHED IN,
NO LEAKS
Pylon....................................................................... CONDITION
7. ENGINE 2 LH SIDE
Turbine Exhaust...................................................... CLEAR, NO LEAKS
After engine shutdown the scavenge system is no longer effective. A
small amount of oil may leak through the aft sump drain and pool in
the engine chevron nozzle.
If the puddle size exceeds 9 in x 6 in (229 mm x 152 mm),
maintenance should be contacted. For airplanes equipped with
Improved Acoustic Chevron Nozzle (IACN) the puddle should not
exceed 7.50 in x 4.5 in (190 mm x 114 mm).
Core Pressure Relief Door..................................... CLOSED
LH Thrust Reverser................................................ CONDITION AND
LATCHED
LH Nacelle Strake................................................... CONDITION
LH Fan Cowl Doors................................................ CONDITION AND
LATCHED
Anti-ice Pressure Relief Door................................. CLOSED AND
LATCHED
Engine Inlet............................................................. CONDITION
Check for Foreign Objects and leaks inside air inlet. Ensure that there
is no damage to the T12 Sensor and that the FADEC Cooling Inlet is
clear.
Fan Blades.............................................................. CHECKED
Check for damaged Fan Blades and ensure Fan is free to rotate.
8. ENGINE 2 RH SIDE
RH Nacelle Strake.................................................. CONDITION
Oil Fill Access Door................................................ CLOSED
FADEC Cooling Vent.............................................. CLEAR
RH Fan Cowl Doors................................................ CONDITION AND
LATCHED
RH Thrust Reverser................................................ CONDITION AND
LATCHED
Core Pressure Relief Door..................................... CLOSED
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
Page 4
External Inspection
REVISION 23
AOM-1502-016
Check for damages on spinner.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
9. RIGHT WING LEADING EDGE
Wing Leading Edges............................................... CONDITION
Refueling Compartment Door................................. SECURED
RH 3 Magnetic Level Indicator............................... PUSHED IN,
NO LEAKS
Access Doors and Panels...................................... SECURED
Pressure Relief Valve............................................. CHECKED
Wing Vents.............................................................. NO
OBSTRUCTION
Navigation and Strobe Lights................................. CONDITION
Clean and undamaged.
10. RIGHT WING TRAILING EDGE
Static Dischargers................................................... NUMBER AND
CONDITION
Verify 3 static dischargers on the aileron and 6 static dischargers on
the winglet. Refer to the CDL for dispatch with missing items.
Flight Control Surfaces and Fairings...................... CONDITION
Surfaces clear and unobstructed.
11. RIGHT MAIN GEAR
Right Main Gear .................................................... CHECKED
Wheels and Tires.................................................... CONDITION
Up Lock Hook......................................................... UNLOCKED
Strut/Wheel Well/Doors........................................... CONDITION,
NO LEAKS
Ground Locking Pin................................................ REMOVED
Brakes Wear Indicators.......................................... CHECKED
Downlock Springs................................................... CONDITION
12. RIGHT AFT FUSELAGE
Access Doors and Panels...................................... SECURED
If not in use, visibly secured.
Drain Mast............................................................... CONDITION
No obstruction or damage.
AFT Cargo Door..................................................... CHECKED
AOM-1502-016
If not in use, visibly secured.
AFT Service Door................................................... CHECKED
If not in use, visibly secured.
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
External Inspection
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Lower AFT Antennas/AFT Drain Mast.................... CONDITION
Undamaged.
Battery Air Outlet..................................................... NO
OBSTRUCTION
No obstruction or damage.
13. TAIL SECTION
Flight Control Surfaces........................................... CONDITION
Surfaces Clear and Unobstructed.
Empennages Leading Edges.................................. CONDITION
Static Dischargers................................................... NUMBER AND
CONDITION
Verify 4 Static Dischargers on the rudder, 3 on each elevator, 3 on
each horizontal stabilizer and 1 on vertical stabilizer. Refer to the CDL
for dispatch with missing items.
APU......................................................................... CONDITION
14. LEFT AFT FUSELAGE
APU External Power Receptacle............................ CHECKED
If not in use, visibly secured.
Overboard Vent....................................................... NO
OBSTRUCTION
No obstruction or damage.
Pressurization Static Port....................................... NO
OBSTRUCTION
No obstruction or damage.
Potable Water Service Panel.................................. SECURED
If not in use, visibly secured.
AFT Pax Door......................................................... CHECKED
If not in use, visibly secured.
Lower AFT Antennas.............................................. CONDITION
Undamaged.
Access Doors and Panels...................................... SECURED
15. LEFT MAIN GEAR
Left Main Gear ....................................................... CHECKED
Wheels and Tires.................................................... CONDITION
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
Page 6
External Inspection
REVISION 23
AOM-1502-016
If not in use, visibly secured.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Up Lock Hook......................................................... UNLOCKED
Strut/Wheel Well/Doors........................................... CONDITION,
NO LEAKS
Ground Locking Pin................................................ REMOVED
Brakes Wear Indicators.......................................... CHECKED
Downlock Springs................................................... CONDITION
16. LEFT WING TRAILING EDGE
Flight Control Surfaces and Fairings...................... CONDITION
Surfaces clear and unobstructed.
Static Dischargers................................................... NUMBER AND
CONDITION
Verify 3 static dischargers on the aileron and 6 static dischargers on
the winglet. Refer to the CDL for dispatch with missing items.
Navigation, Strobe Lights and Upper Beacon
Lights..................................................................... CONDITION
Clean and undamaged.
Upper Antennas...................................................... CONDITION
Undamaged.
17. LEFT WING LEADING EDGE
Wing Leading Edges............................................... CONDITION
Wing Vents.............................................................. NO
OBSTRUCTION
Pressure Relief Valve............................................. CHECKED
Access Doors and Panels...................................... SECURED
LH 3 Magnetic Level Indicator................................ PUSHED IN,
NO LEAKS
18. ENGINE 1 LH SIDE
Turbine Exhaust...................................................... CLEAR, NO LEAKS
AOM-1502-016
After engine shutdown the scavenge system is no longer effective. A
small amount of oil may leak through the aft sump drain and pool in
the engine chevron nozzle.
If the puddle size exceeds 9 in x 6 in (229 mm x 152 mm),
maintenance should be contacted. For airplanes equipped with
Improved Acoustic Chevron Nozzle (IACN) the puddle should not
exceed 7.50 in x 4.5 in (190 mm x 114 mm).
Core Pressure Relief Door..................................... CLOSED
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
External Inspection
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
LH Thrust Reverser................................................ CONDITION AND
LATCHED
LH Nacelle Strake................................................... CONDITION
LH Fan Cowl Doors................................................ CONDITION AND
LATCHED
Anti-ice Pressure Relief Door................................. CLOSED AND
LATCHED
Engine Inlet............................................................. CONDITION
Check for Foreign Objects and leaks inside air inlet. Ensure that there
is no damage to the T12 Sensor and that the FADEC Cooling Inlet is
clear.
Fan Blades.............................................................. CHECKED
Check for damaged Fan Blades and ensure Fan is free to rotate.
Check for damages on spinner.
19. ENGINE 1 RH SIDE
RH Nacelle Strake.................................................. CONDITION
Oil Fill Access Door................................................ CLOSED
FADEC Cooling Vent.............................................. CLEAR
RH Fan Cowl Doors................................................ CONDITION AND
LATCHED
RH Thrust Reverser................................................ CONDITION AND
LATCHED
Core Pressure Relief Door..................................... CLOSED
20. LEFT CENTER WING
LH 2 and LH 1 Magnetic Level Indicators.............. PUSHED IN,
NO LEAKS
Landing, Taxi and Wing Inspection Light................ CONDITION
Clean and undamaged.
Left Ram Air Inlet.................................................... NO
OBSTRUCTION
No obstruction or damage.
Air Inlets and Outlets.............................................. NO
OBSTRUCTION
If not in use, visibly secured.
Air Conditioning Connection Access Door.............. CHECKED
CONTINUED...
3-07
Copyright © by Embraer. Refer to cover page for details.
Page 8
External Inspection
REVISION 23
AOM-1502-016
No obstruction or damage.
Collector Tank Water Drain Valve Door.................. SECURED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
AOM-1502-016
No obstruction or damage.
3-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
External Inspection
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-07
Copyright © by Embraer. Refer to cover page for details.
Page 10
External Inspection
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
BEFORE START
Airplane Manuals and Documents.......................... ON BOARD
Check all the required documents including:
– Technical Log.
– AOM.
– QRH.
!Airplanes with Electronic Checklist
– Verify if the ECL database version is compatible with the paper
QRH revision.
"
– Airworthiness Certificate.
– Weight and Balance.
– Radio Station Certificate.
– Navigation Kit.
Jump Seat Oxy Masks, Regulators and Audio
Panel..................................................................... CHECKED
AOM-1502-016
Verify the observer’s masks.
Carry out the test as follows:
– Set the regulator control knob to “100%“.
– Press and hold the “TEST/RESET“ button.
– Verify a short illumination or “blink“ of the flow indicator.
– Verify audible oxygen flow in the headset or loudspeakers.
– Once the mask fully pressurizes the indicator must go out, showing
that the system is leak free.
– Release the “TEST/RESET“ button.
ELECTRIC Panel.................................................... SET
– IDG 1 and IDG 2 Selectors knobs to AUTO.
– AC BUS TIES selector knob to AUTO.
– GPU button as required.
– APU GEN button to PUSHED IN.
– TRU 1 toggle switch to AUTO.
– TRU ESS toggle switch to AUTO.
– TRU 2 toggle switch to AUTO.
– DC BUS TIES toggle switch to AUTO.
– Battery 1 selector knob to ON.
– Battery 2 selector knob to AUTO.
COCKPIT LIGHTS Panel........................................ AS REQUIRED
– Adjust Main Panel, Overhead Panel and Pedestal lights.
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Before Start
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Push ANNUNCIATORS TEST button and verify all associated
lights.
– Set DOME light as required.
Engine 1 Fire Handle.............................................. STOWED
FUEL Panel............................................................. SET
– FUEL XFEED selector knob as required.
– DC PUMP selector knob to AUTO.
– AC PUMP 1 and AC PUMP 2 selectors knobs to AUTO.
PASSENGER SIGNS Panel................................... SET
– NO SMKG and FSTN BELTS switches to ON.
– STERILE light as required.
– Turn FSTN BELTS switch to ON after finishing refueling the
airplane.
FIRE EXTINGUISHER Panel (Overhead).............. CHECKED
– Cargo Smoke FWD/AFT buttons pushed out and not illuminated.
– APU Fire Extinguishing button pushed out and not illuminated.
APU CONTROL Panel............................................ AS REQUIRED
The APU FADEC is ready for use when APU rpm and EGT dashed
indications (--) are replaced by numbers.
EXTERNAL LIGHTS Panel..................................... AS REQUIRED
Engine 2 Fire Handle.............................................. STOWED
HYDRAULIC Panel................................................. CHECKED/SET
– Verify ENG PUMP SHUTOFF 1 and 2 buttons with no lights and
guarded.
– Verify PTU selector knob to AUTO.
– Verify the HYDRAULIC SYS 1 and SYS 2 ELEC PUMPs selector
knob to AUTO.
– Verify the HYDRAULIC SYS 3 ELEC PUMP A selector knob to
OFF.
– Verify the HYDRAULIC SYS 3 ELEC PUMP B selector knob to
AUTO.
PRESSURIZATION Panel...................................... SET
– CABIN ALT selector knob to STOP.
– MODE selector knob to AUTO.
– LFE selector knob to STOP.
– DUMP button, no lights and guarded.
WINDSHIELD HEATING Button............................. PUSHED IN
ICE PROTECTION Panel....................................... SET
– WINDSHIELD and ENGINE buttons pushed in.
– MODE selector knob to AUTO.
– WING button pushed in.
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
Page 2
Before Start
REVISION 23
AOM-1502-016
EMER STOP button pushed out and not illuminated.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
–
AIR
–
–
TEST selector knob to OFF.
COND/PNEUMATIC Panel.............................. SET
CKPT and PAX CABIN temperature control knobs as required.
RECIRC, PACK 1, PACK 2, XBLEED, APU BLEED, BLEED 1 and
BLEED 2 buttons pushed in.
PASSENGER OXYGEN Panel............................... SET
– MASK DEPLOY selector knob to AUTO.
– MASK DEPLOYED indicator no light.
Oxygen Masks and Regulators.............................. CHECKED/100%
Check masks for oxygen supply and for microphone functionality.
The MFD Status page must be checked and the available oxygen
supply and pressure must be adequate for use.
AOM-1502-016
Carry out the test as follows:
– Set the regulator controller to “100%”.
– Press and hold the “TEST/RESET” button.
– Verify a short illumination or “blink” of the flow indicator.
– Verify audible oxygen flow in the headset or loudspeakers.
– Once the mask fully pressurizes the indicator must go out, showing
that the system is leak free.
– Release the “TEST/RESET” button.
Glareshield Lights Control Panel............................ AS REQUIRED
DISPLAY CONTROLLER Panel............................. SET
– Set BARO SET knob to actual pressure.
– Push HSI button for Full Compass, ARC or MAP.
– Select the FMS as the primary NAV source (if raw data information
is intended, use preview mode or Bearing pointers).
– BRG circle (O) to OFF, VOR1, ADF1 or FMS1 as required.
– BRG diamond (◊) to OFF, VOR2, ADF2 or FMS2 as required.
Speed Selector Knob.............................................. MAN
REVERSIONARY Panel......................................... SET
– Displays selectors knob to AUTO.
– Sensors selectors (ADS/IRS) in normal configuration.
Flight Instruments................................................... SET/XCHECKED
Verify:
– AIRSPEED TAPES not showing speed.
– Set altimeter setting and cross check it with the field elevation.
– EADIs leveled and flag-free.
– Initial assigned altitude on the ALT SEL.
– Altitude tape indications cross-check.
– Both VSIs showing zero.
– EHSIs with the courses selected according to the intended
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Before Start
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
departure procedure and NAV source selected.
– EHSIs and magnetic compass flag free and showing the same
magnetic heading.
– HDG bug set according to the proposed departure procedure.
– Check IESS and adjust the altimeter setting.
– Weather set on PFD and/or MFDs MAP page as required.
– It is recommended that PM sets the Terrain on MFD up to MSA.
– Set the MFDs MAP page menu as required.
– TCAS should be always displayed on both MFDs.
STATUS Page......................................................... CHECKED
Verify on the status page ENG OIL LEVEL and BRAKES EMER ACCU
pressure.
– Left Seat Pilot should select FLIGHT CONTROL synoptic page.
– Right Seat Pilot should remain on STATUS synoptic page.
!Airplanes equipped with Autobrake OR POST-MOD SB 190-32-0006
Autobrake................................................................ RTO
"
GND PROX TERR INHIB Button........................... CHECKED
Verify button pushed out and no striped white bar illuminated.
EICAS..................................................................... CHECKED
Check EICAS messages to ensure agreement with airplane status.
Clock ...................................................................... SET
Select GPS on the GPS/INT/SET selector. If the clock displays dashes
(-- -- --), adjust the clock INT position.
GND PROX G/S INHIB Button............................... CHECKED
Verify no striped white bar illuminated.
LG WRN INHIB Button........................................... CHECKED
Verify no striped white bar illuminated.
FLIGHT CONTROLS MODE Panel ....................... CHECKED
Verify the SHAKER 1 CUTOUT and SHAKER 2 CUTOUT buttons
pushed out and no striped white bar illuminated.
IGNITION Selector Knobs...................................... AUTO
EICAS FULL........................................................... CHECKED
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
Page 4
Before Start
REVISION 23
AOM-1502-016
Verify ELEVATORS, RUDDER and SPOILER buttons guarded and
no striped white bar illuminated.
SHAKER 1 and 2 CUTOUT Buttons...................... CHECKED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Verify the EICAS Full button in the desired position.
Speedbrake Lever................................................... CLOSED
Thrust Levers.......................................................... IDLE
GND PROX FLAP OVRD....................................... CHECKED
Verify button pushed out, guarded and no striped white bar illuminated.
AUDIO CONTROL Panel........................................ AS REQUIRED
Select the microphone and audio reception buttons as required and
adjust the volume levels. To avoid background noise do not set the
SPKR volume higher than 55.
TRIM Panel............................................................. CHECKED
Verify that ROLL, YAW and PITCH (Captain, First Officer and Backup)
trims are operating properly both ways and check that Position
Indication on EICAS changes accordingly. Verify system’s 3 second
protection working properly. Adjust YAW and ROLL trims to the neutral
position and PITCH trim to the green band.
NOTE: The PITCH TRIM Backup Switch may be checked once a day
only, by flight crew or maintenance personnel, at the operator′s
discretion.
Flight Controls DISCONNECT Handles................. CHECKED
Alternate Gear Extension Compartment................. CHECKED
Verify the alternate gear extension lever is fully down and the electrical
override switch is in the “NORMAL” position.
AOM-1502-016
!Pre-mod MAU load 27.1
MCDU..................................................................... SET
– On PROGRESS page, activate the FMS AUTOTUNE by deleting
the NAV1 frequency for FMS1 and NAV2 frequency for FMS2
displayed on LSK 5L and 5R, respectively. In case of FMS
AUTOTUNE OFF takeoff is selected in order to hard-tune a specific
VOR, return to FMS AUTOTUNE ON as soon as the VOR
frequency is no longer necessary;
– Select NAV IDENT page and check its contents;
– Select POSITION INIT page and load the present position;
– It is recommended that PF sets the applicable FLIGHT ID and the
route in the FMS ROUTE page according to the flight plan and
both pilots check course, distance, time, altitude on each waypoint
and LFE in the EICAS according to the destination landing field
elevation;
– It is recommended that PF sets on PERF INIT page 1/1 the
CLIMB, CRUISE, DESCENT and DEP/APPROACH speed
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Before Start
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
schedule, select page 2/3 and check/set its contents, on page 3/3
set all fields with the available data;
!!Airplanes equipped with Autoland system
– If applicable select enable or disable on MENU - MISC MENU OPR CONFIG Page.
""
!!Airplanes Post-Mod Load 25.4 or airplanes Post-Mod Load 25.3
– FLIGHT ID information is not removed when the flight complete
logic becomes active. The Flight ID information will remain even
after a complete power reset is performed (power down – power
up).
""
"
..............................SHORTLY BEFORE STARTUP..............................
Fuel Quantity........................................................... CHECKED
!Airplanes equipped with Electronic Flight Bag (EFB)
Electronic Flight Bag............................................... SET
– Verify EFB with adequate battery level or properly connected to
power source;
– Check software and software database properly updated;
– If applicable set performance and weight and balance initialization
data;
– Check performance and weight and balance data;
– If applicable set navigation charts and navigation data.
"
MCDU..................................................................... SET
– Insert the intended SID or the departing runway on the FMS and
both pilots must check the accuracy of the procedure retrieved by
FMS database. Select LNAV if intended to takeoff with lateral
mode armed on ground.
– Set the Performance initialization data on PERF INIT page. If it is
already available enter the zero fuel weight and press CONFIRM
INIT prompt on page 3/3. If performance is confirmed and taking
off with vertical mode armed on ground is desired, select VNAV.
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
Page 6
Before Start
REVISION 23
AOM-1502-016
!Pre-mod MAU load 27.1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Select TAKEOFF DATASET MENU page on the MCDU and set
the data below:
–
Thrust Rate Mode (TO-1, TO-2 or, when applicable,TO-3).
–
TO TEMP (__ºC).
–
ATTCS (ON or OFF).
–
REF ECS (ON or OFF).
–
REF A/I (OFF, ENG or ALL).
–
FLEX T/O (ON or OFF).
–
FLEX TEMP (__ºC).
–
Press ENTER Prompt to confirm the settings.
– Select TAKEOFF page and set all data in accordance with the
runway analysis and airplane configuration for takeoff.
– Select RADIO page 1/2 and insert assigned transponder code and
for LVTO using HGS set the ILS frequency for the departing
runway on both NAV windows.
"
VSPEED READOUTS AND BUGS
Four speeds are displayed prior to takeoff:
4O
1OO
12O
13O
14O
V 2 ..........2..........WHITE
V FS .......FS.......GREEN
EM170AOM980001B.DGN
V1 ..........1..........MAGENTA
V R..........R..........CYAN
1
R
2
FS
VSpeed Readouts and Bugs
NOTE: Green Dot speed can be used for immediate return when the
scenario does not allow pilots to calculate landing performance.
!Pre-mod MAU load 27.1
AOM-1502-016
SPEED Selector Knob............................................ SET
At pilot’s discretion set the SPEED Selector knob to FMS or MANUAL.
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Before Start
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
If MANUAL, set Vfs on the speed window.
In case of Noise Abatement procedure set V2 + 10.
If FMS, set the departure speed on the DEP/APP speeds page on the
FMS.
"
!Pre-mod MAU load 27.1
TOGA Button........................................................... PRESSED
"
!Pre-mod MAU load 27.1
TRIM Panel............................................................. SET/ZERO/ZERO
Set the PITCH trim according to load sheet and verify YAW and ROLL
trims to the neutral position.
"
Doors and Windows................................................ CLOSED
Verify that the cockpit windows are closed and check all airplane
doors closed indications on MFD status page. It is recommended to
assure that escape slides are armed.
Check the cockpit door securely closed.
Takeoff Briefing....................................................... COMPLETED
The takeoff briefing shall be performed prior to engines start in order
to not interfere with takeoff preparation. The briefing shall cover all
actions for both normal, such as flaps and autobrake settings, and
non-normal takeoff procedures expected to be used during the takeoff
phase. Additional briefing items may be required when different
elements exist, such as adverse weather, runway in use, runway
conditions, noise abatement requirements, dispatch using the MEL,
terrain clearance, special engine failure departure procedure or any
other situation or special consideration that differ from routine.
Red beacon............................................................. ON
Electric Hydraulic Pump 3A.................................... ON
Ground Equipment.................................................. AS REQUIRED
CONTINUED...
3-09
Copyright © by Embraer. Refer to cover page for details.
Page 8
Before Start
REVISION 23
AOM-1502-016
The takeoff briefing should be performed by the PF and the left seat
pilot must state the Reject Takeoff procedures.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
If performing a push back assure that the ground equipment not used
for this procedure is removed.
Emergency/Parking Brake...................................... AS REQUIRED
Verify if the Emergency/Parking Brake is set in accordance with the
engine start procedures.
Steering Disengage Switch..................................... PRESSED
AOM-1502-016
Verify the STEER OFF message displayed on the EICAS.
3-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Before Start
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-09
Copyright © by Embraer. Refer to cover page for details.
Page 10
Before Start
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ENGINE START
BASIC STATEMENT
NOTE: – Engine start can be done simultaneously with push back,
requiring the parking brake released and disengagement of
the steering (verify EICAS message STEER OFF). In case of
a static engine start be sure that the parking brake is set.
– Check if the jet way and stairs are removed and the doors
are closed.
– Obtain ATC and ground clearance.
– Confirm nose gear green towing light prior to start pushback
with the ground personnel.
ENGINE WARMUP
In order to allow thermal stabilization of the engines, operate them at or
near IDLE for at least 2 minutes before selecting high trust settings. Taxi
time at or near IDLE can be included in the warm up period.
NO BREAK POWER TRANSFER (NBPT)
To avoid power interruptions it is recommended to wait 30 s after the
%N2 stabilizes before shutting the APU down or GPU disconnection, or
to use the Electrical Synoptic Page to follow the power transfer.
ENGINE VIBRATION
During the first minute after engine start, the vibration level amber band
will start at 5.0 instead of 4.0 units, as long as the thrust levers are kept
at IDLE.
ENGINE START PROCEDURE
Associated START/STOP Selector......................... START, then RUN
AOM-1502-016
Hold the selector knob at START position for at least 2 s.
NOTE: During ground starts only, the transition of the cockpit
START/STOP switch from STOP to START must be less than
30 s or the FADEC will prevent an engine start until the switch is
cycled through STOP.
CONTINUED...
3-11
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Engine Start
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Engine Parameters................................................. MONITOR
Repeat the sequence for the other engine.
!Airplanes with MAU Load 25.4 or airplanes Pre-Mod MAU Load 25.3
PACKS LOGIC DURING ENGINE START
When REF ECS is selected ON in the MCDU T/O DATASET MENU
page, the caution EICAS message ENG REF ECS DISAG may be
temporarily displayed after both engines have started and are stabilized
at idle. Refer to AOM 14-02-15 for details.
"
ABNORMAL ENGINE START INDICATIONS
Although FADEC provides automatic over-temperature protection and
will automatically abort the start in the event of a hot start, hot restart or
hung start, the engine start must be manually aborted when:
– No positive oil pressure indication within 10 s after N2 speed starts
to increase.
– During engine start with tailwind, if a positive increase of N1 is not
indicated before starter cutout (50% N2). In this case the airplane
should be repositioned prior to engine start to minimize tailwind
effects.
– No ITT indication within 1 minute after the fuel is applied (15 s after
fuel is reapplied).
– ITT exceeds start limit (hot start).
– If oil pressure stabilizes below the engine limits.
– N1 and/or N2 failing to accelerate to stable idle speed (hung start).
– An intermittent electrical pneumatic or starter malfunction occurs
before the starter disengagement.
CONTINUED...
3-11
Copyright © by Embraer. Refer to cover page for details.
Page 2
Engine Start
TEMP.
REVISION
23.3
AOM-1502-016
NOTE: – In case an automatic abort occurs or engine start is manually
aborted due to abnormal engine indications, its cause must
be investigated and corrected before further attempts to start
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
the engines.
!190/195 models equipped with ENGINE FADEC 5.50 and on, or airplanes
POST-MOD SB 190-73-0016
– The FADEC commands an automatic abort when ITT is 10°C
lower than the engine hot start limit. This will prevent ENG
EXCEEDANCE EICAS message to be displayed. In this
case, two additional engine starts are allowed without any
cause investigation.
"
– If both the following conditions occur, one additional engine
start is allowed:
Engine– start is manually aborted due to no ITT indication 15 s after
fuel is reapplied, and
AOM-1502-016
″ENG –1(2) NO DISPATCH″ or ″ENG 1(2) SHORT DISPATCH″
EICAS messages are not displayed.
3-11
Copyright © by Embraer. Refer to cover page for details.
TEMP.
23.3
REVISION
Engine Start
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-11
Copyright © by Embraer. Refer to cover page for details.
Page 4
Engine Start
TEMP.
REVISION
23.3
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ENGINE START
BASIC STATEMENT
NOTE: – Engine start can be done simultaneously with push back,
requiring the parking brake released and disengagement of
the steering (verify EICAS message STEER OFF). In case of
a static engine start be sure that the parking brake is set.
– Check if the jet way and stairs are removed and the doors
are closed.
– Obtain ATC and ground clearance.
– Confirm nose gear green towing light prior to start pushback
with the ground personnel.
ENGINE WARMUP
In order to allow thermal stabilization of the engines, operate them at or
near IDLE for at least 2 minutes before selecting high trust settings. Taxi
time at or near IDLE can be included in the warm up period.
NO BREAK POWER TRANSFER (NBPT)
To avoid power interruptions it is recommended to wait 30 s after the
%N2 stabilizes before shutting the APU down or GPU disconnection, or
to use the Electrical Synoptic Page to follow the power transfer.
ENGINE VIBRATION
During the first minute after engine start, the vibration level amber band
will start at 5.0 instead of 4.0 units, as long as the thrust levers are kept
at IDLE.
ENGINE START PROCEDURE
Associated START/STOP Selector......................... START, then RUN
AOM-1502-016
Hold the selector knob at START position for at least 2 s.
NOTE: During ground starts only, the transition of the cockpit
START/STOP switch from STOP to START must be less than
30 s or the FADEC will prevent an engine start until the switch is
cycled through STOP.
CONTINUED...
3-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Engine Start
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Engine Parameters................................................. MONITOR
Repeat the sequence for the other engine.
!Airplanes with MAU Load 25.4 or airplanes Pre-Mod MAU Load 25.3
PACKS LOGIC DURING ENGINE START
When REF ECS is selected ON in the MCDU T/O DATASET MENU
page, the caution EICAS message ENG REF ECS DISAG may be
temporarily displayed after both engines have started and are stabilized
at idle. Refer to AOM 14-02-15 for details.
"
ABNORMAL ENGINE START INDICATIONS
Although FADEC provides automatic over-temperature protection and
will automatically abort the start in the event of a hot start, hot restart or
hung start, the engine start must be manually aborted when:
– No positive oil pressure indication within 10 s after N2 speed
starts to increase.
– During engine start with tailwind, if a positive increase of N1 is
not indicated before starter cutout (50% N2). In this case the
airplane should be repositioned prior to engine start to minimize
tailwind effects.
– No ITT indication within 1 minute after the fuel is applied (15 s
after both igniters on and fuel is reapplied).
– ITT exceeds start limit (hot start).
– If oil pressure stabilizes below the engine limits.
– N1 and/or N2 failing to accelerate to stable idle speed (hung
start).
– An intermittent electrical pneumatic or starter malfunction occurs
before the starter disengagement.
CONTINUED...
3-11
Copyright © by Embraer. Refer to cover page for details.
Page 2
Engine Start
REVISION 20
AOM-1502-016
NOTE: – In case an automatic abort occurs or engine start is manually
aborted due to abnormal engine indications, its cause must
be investigated and corrected before further attempts to start
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
the engines.
!190/195 models equipped with ENGINE FADEC 5.50 and on, or airplanes
POST-MOD SB 190-73-0016
– The FADEC commands an automatic abort when ITT is 10°C
lower than the engine hot start limit. This will prevent ENG
EXCEEDANCE EICAS message to be displayed. In this
case, two additional engine starts are allowed without any
cause investigation.
AOM-1502-016
"
3-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Engine Start
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-11
Copyright © by Embraer. Refer to cover page for details.
Page 4
Engine Start
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
AFTER START
Ground Equipment.................................................. REMOVED
Be sure that the emergency/parking brake is set and nose gear/RAT
pins and ground equipment have been removed.
N1 Target................................................................ CHECKED
The N1 target indication on the EICAS must be equivalent to the N1
target indication available via performance calculation.
The difference between N1 given by FADEC (indicated on EICAS)
and the computed value is zero or this difference is positive and lower
than or equal to 0.5%.
Transponder............................................................ AS REQUIRED
Select the transponder to TA/RA or in accordance with local
requirements.
SLAT/FLAP............................................................. SET__
Adjust SLAT/FLAP to a setting consistent with the intended takeoff
configuration and performance.
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
If the SLAT/FLAP lever setting is different from the input made on the
FMS TAKEOFF page the aural message “NO TAKEOFF FLAP” will
sound during the takeoff configuration check.
"
APU......................................................................... AS REQUIRED
Set APU ON or OFF according to the electrical and pressurization
systems. The APU usage shall be defined for a specific operation in
order to minimize the overall costs.
APU shutting down can only be performed after confirmation of the
power transfer through the Electrical Synoptic page or wait 30 s after
%N2 stabilizes.
Flight Controls......................................................... CHECKED
Press the STEERING DISENGAGE SWITCH, check the control
column and rudder pedals.
AOM-1502-016
Flight controls should be checked for freedom of movement in a
smooth and continuous manner.
A full green box indication on the synoptic page is not a requirement
for a successful check.
– The flight controls check must be performed with the flight controls
synoptic page displayed;
CONTINUED...
3-13
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
After Start
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
–
–
–
–
Elevator - full up, neutral, full down and neutral;
Aileron - full left, neutral, full right and neutral;
Rudder - full left, neutral, full right and neutral;
Press the steering handle to engage the STEERING and select
MAP on the MFD prior to start the taxi.
NOTE: – The Hydraulic PBIT starts when all the three hydraulic
systems are pressurized and takes about one minute to
complete. Performing the flight controls check while the
Hydraulic PBIT is running may interrupt the PBIT.
!MAU load 21.2 and on OR POST-MOD SB 190-31-0015
– FLT CTRL TEST IN PROG Status message is displayed
while hydraulic PBIT is in progress.
3-13
Copyright © by Embraer. Refer to cover page for details.
Page 2
After Start
REVISION 21
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
BEFORE TAKEOFF
The Before Takeoff Procedures and checklist must be performed when
cleared to line up on the runway. Use all available information such as
heading and FMS course indication (PFD), lateral profile (MFD) and
departure runway (MCDU) to ensure the airplane is at the assigned
runway for takeoff.
Cabin Crew............................................................. ADVISED
After receiving “Cabin OK” from the Purser, inform the cabin crew
through PA: “Cabin Crew prepare for takeoff”.
Taxi Ligths............................................................... OFF
Turn off the taxi lights. Taxi (side) may be used to assist takeoff from
takeoff to 10000 ft AFE at pilots discretion.
Landing Lights......................................................... ON
Strobe Lights........................................................... ON
Brake Temperature................................................. CHECK
Brake temperature indication must be in the green range for takeoff.
Select MAP on MFD.
EICAS..................................................................... CHECKED
Check:
– No EICAS messages displayed or only EICAS advisory and status
messages related to a given airplane configuration resulted by
crew action should be displayed.
– Thrust Rate Mode: TO-1, TO-2 or, when applicable, TO-3.
– ATTCS ON or OFF.
– FLEX TEMP (__°C).
Transponder............................................................ TA/RA
Takeoff Configuration.............................................. CHECKED
Press the T/O button and “TAKEOFF OK” synthetic message shall be
heard.
AOM-1502-016
NOTE: Arm the AT when the airplane is lined up and ready for takeoff.
3-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Before Takeoff
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-15
Copyright © by Embraer. Refer to cover page for details.
Page 2
Before Takeoff
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
TAKEOFF
Thrust Levers.......................................................... TO/GA
Adjust thrust to 40% N1. When engines stabilize at 40% N1, advance
thrust levers to TO/GA detent.
Engine Parameters................................................. MONITOR
NOTE: During takeoff roll, after checking thrust levers to TO/GA, check
N1 equal to N1 target and green ATTCS indication presented on
EICAS if ATTCS ON is selected in MCDU.
At VR rotate the airplane according to the Flight Director pitch angle.
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
In case of Flight Director inoperative, rotate the airplane according to the
takeoff pitch angle displayed on TAKEOFF page on the MCDU.
"
With Positive Rate:
Landing Gear........................................................ UP
AOM-1502-016
Minimum Airspeed................................................ V 2 + 10
3-16
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Takeoff
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-16
Copyright © by Embraer. Refer to cover page for details.
Page 2
Takeoff
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
AFTER TAKEOFF
This checklist should be initiated as soon as possible after FLAPS are
retracted.
Landing Gear.......................................................... UP
Confirm the three white UP indications on the EICAS.
SLAT/FLAP............................................................. 0
AOM-1502-016
Select SLAT/FLAP to zero following F-Bug reference. In case F-Bug
disappears before total accomplishment of Slat/Flap retraction, retract
Slat/Flap following Greed Dot + 10 kt.
3-17
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
After Takeoff
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-17
Copyright © by Embraer. Refer to cover page for details.
Page 2
After Takeoff
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
CLIMB
This procedure can be initiated as soon as the After Takeoff Checklist is
completed.
APU......................................................................... AS REQUIRED
Set the APU ON or OFF according to the electrical and pressurization
systems. The APU usage shall be defined for a specific operation in
order to minimize the overall costs.
Air Conditioning and Pressurization....................... CHECKED
Check for the proper air conditioning and pressurization settings and
parameters.
.......................................At Transition Altitude.......................................
!Pre-mod MAU load 27.1
Altimeters................................................................ SET/X-CHECKED
Set the altimeters to standard (as required by local regulations). The
IESS altimeter must be set also.
"
.......................................Above 10000 ft AFE.......................................
FSTN BELTS.......................................................... AS REQUIRED
NO SMKG............................................................... AS REQUIRED
Verify in accordance with local regulations.
External lights......................................................... OFF
AOM-1502-016
Upon passing 10000 ft AFE switch off the external lights according to
the operating policies.
3-18
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Climb
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-18
Copyright © by Embraer. Refer to cover page for details.
Page 2
Climb
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
DESCENT
Approach Briefing................................................... COMPLETED
– It is recommended to perform the approach briefing before starting
descent.
– The items to be covered are: inoperative airplane components,
weather at destination/alternate airports, fuel status/delays, runway
conditions, low visibility procedures, terrain/MSA, descent profile
and missed approach procedures.
– Set performance data on EFB and check the information. Assess
the landing distance for current conditions and compare with the
runway length available. If conditions affecting airplane
performance change during the approach, reassess the evaluation.
Note that the EFB must be kept secured and viewable below
10000 ft.
– If the destination airport runway is reported to be slippery or
contaminated, it is necessary to discuss the outcome on the
landing distance during the approach briefing. The same
discussion is applicable if the crew has planned to use additional
speed for the approach due to wind/gust conditions.
– If any failure that affects the required landing distance occurs in
the final approach, consider a missed approach in order to better
evaluate the situation and an appropriate runway length. Failures
that affect the landing distance are commonly associated to brakes,
ground spoilers and/or thrust reversers.
– On EFB, if applicable, prepare the approach charts. A thorough
understanding by the PF and PM of all the applicable approach
charts and Notam is essential, including taxi-in procedures.
– Both pilots should set RA/BARO minimums, pre-select radios and
courses for the approach.
– With VNAV engaged, select the ALT SEL only to altitudes cleared
by ATC.
!Airplanes equipped with Autobrake OR POST-MOD SB 190-32-0006
AUTOBRAKE.......................................................... SET
Set the AUTOBRAKE OFF, LOW, MED or HI in accordance with the
runway analysis calculations for landing.
AOM-1502-016
"
Landing Data........................................................... SET
– Verify on the LANDING page the expected landing weight. Insert
all data according to the type of approach and runway conditions
CONTINUED...
3-19
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Descent
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
to set VREF, VAP, VAC and VFS.
14O
16O
15O
14O
13O
1 25
12O
11O
1OO
9O
19O M
GSPD
13O KT
AC
AP
RF
3-19
Copyright © by Embraer. Refer to cover page for details.
Page 2
Descent
REVISION 21
AOM-1502-016
VAC ..........AC..........MAGENTA
V FS ..........FS..........GREEN
FS
EM170AOM980002A.DGN
VREF ..........RF..........WHITE
VAP ..........AP..........CYAN
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
APPROACH
PASSENGER SIGNS Panel................................... SET
!Pre-mod MAU load 27.1
SPEED Selector Knob............................................ AS REQUIRED
– The use of FMS SPEEDS after the Final Approach Fix (FAF) is not
allowed, as per AFM. Select the speed selector knob to manual
when passing the FAF.
– If FMS speeds is intended to be used during approach, insert
manually in the DEP/APP Speeds page 2/3, or APPROACH
Speeds page 2/3 on MCDU the speeds according to the table that
follows.
SPEED
(KIAS)
210
176 [1]
150
140
140
130
FLAP
UP
2
3
4
5
FULL
1. FLAP 2 speed resulting in 180 KIAS FLAP 1 speed.
"
!Pre-mod MAU load 27.1
Altimeters................................................................ SET/X-CHECKED
If flight is being conducted in ICAO airspace, set the altimeters to
QNH when passing the Transition Level. Otherwise, set as required
by local regulations.
"
AOM-1502-016
Approach Aids......................................................... SET/X-CHECKED
Verify that the frequencies and courses that were selected and
pre-selected are correct for the intended approach.
CONTINUED...
3-21
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Approach
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
If using preview mode to set the courses for final approach, assure
that the course selected is the one desired (on-side or cross-side).
Pressing the preview button once displays the on-side VOR/LOC
preview on PFD; pressing twice shows the cross-side VOR/LOC
preview and a third time deactivates the preview mode.
Ensure that both PFDs are displaying appropriate information.
3-21
Copyright © by Embraer. Refer to cover page for details.
Page 2
Approach
REVISION 21
AOM-1502-016
Also verify that the approach minimums and the FMS are properly
selected for the type of approach in use.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
BEFORE LANDING
Landing Lights......................................................... AS REQUIRED
AOM-1502-016
Taxi (side) lights may be used to assist landing from 10000 ft AFE at
pilots discretion.
Landing Gear.......................................................... DOWN
Slat/Flap.................................................................. SET--
3-23
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Before Landing
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-23
Copyright © by Embraer. Refer to cover page for details.
Page 2
Before Landing
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
GO-AROUND
!Pre-mod MAU load 27.1
TOGA button........................................................... PRESSED
"
Thrust Levers.......................................................... TO/GA
SLAT/FLAP............................................................. GA FLAPS SET
Rotate or verify that autopilot rotates the airplane following the flight
director guidance.
NOTE: In case of flight director is inoperative, rotate the airplane to 8°
nose up.
Landing SLAT/FLAP
FULL
5
Go Around SLAT/FLAP
4
2
With positive climb:
Landing Gear........................................................ UP
Minimum Airspeed................................................ V REF + 20
AOM-1502-016
At the acceleration altitude proceed as in a normal takeoff.
3-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Go Around
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-25
Copyright © by Embraer. Refer to cover page for details.
Page 2
Go Around
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
AFTER LANDING
NOTE: Upon landing, thrust reversers should be set to MIN REV at
60 KIAS and be closed at 30 KIAS. During RTO the thrust
reversers can be used until the airplane comes to a complete
stop.
APU......................................................................... AS REQUIRED
Turn the APU On when it is required.
The APU FADEC is ready for use when APU RPM and EGT dashed
indications (--) are replaced by numbers.
External Lights........................................................ AS REQUIRED
Turn off the unnecessary lights.
Transponder............................................................ AS REQUIRED
Select the transponder to STBY or in accordance with local
requirements.
SLAT/FLAP............................................................. 0
Select the SLAT/FLAP control lever to zero.
PITCH Trim............................................................. SET
AOM-1502-016
Set Pitch Trim to 2 UP.
3-27
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
After Landing
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-27
Copyright © by Embraer. Refer to cover page for details.
Page 2
After Landing
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
SHUTDOWN
Thrust Levers.......................................................... IDLE
It is recommended to keep the engine running at idle during 2 min to
permit engine thermal stabilization prior to shutdown the engine. Time
of operation at or near idle, such as taxiing, is included in this 2 min
minutes period.
Emergency/Parking Brake...................................... SET
– Pull the Emergency/Parking Brake to the set position after airplane
has stopped. Make sure that the airplane is static before doing so.
– Verify brake temperature. If close to the cautionary range, verify
that chocks are on and release the Emergency/Parking Brake to
reduce the brake cooling time.
Electrical.................................................................. ON GPU/APU
– If APU GEN is not available, an AC GPU should be plugged in.
– Check the AVAIL light illuminated before pushing in the GPU
button.
NOTE: To prevent electrical power interruptions, it is recommended to
wait 10 s after GPU button is pushed in or after APU is stabilized
before shutting down one of the engines.
If one of the engines is shut down prior to using the APU, wait
10 s until the electrical system has stabilized on the remaining
IDG before starting the APU.
START/STOP Selectors.......................................... STOP
– The engines will not shut down with START/STOP Selectors unless
Thrust Levers are first moved to IDLE. If STOP is selected before
Thrust Lever is retarded to IDLE, momentarily cycle START/STOP
Selector do RUN and back to STOP.
!MAU load up to 19.4
– Do not press any rudder pedal up to 15 s after all hydraulic power
is shut down.
"
Electric Hydraulic Pump System 3A....................... OFF
Red Beacon............................................................ OFF
FSTN Belts.............................................................. OFF
AOM-1502-016
Make sure that the scape slides are disarmed before turning OFF the
fasten belts signs.
Turn FSTN BELTS switch to OFF after complete engine stop.
3-29
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Shutdown
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-29
Copyright © by Embraer. Refer to cover page for details.
Page 2
Shutdown
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
LEAVING THE AIRPLANE
NOTE: This procedure applies when a power down is required.
PASSENGER SIGNS Panel................................... OFF
Set all switches to OFF.
!Airplanes equipped with Electronic Flight Bag (EFB)
Electronic Flight Bag............................................... OFF
"
Turn off electrical power:
APU (if available).................................................. OFF
Wait until the APU label OFF is displayed. Wait additional 80 s until
APU FUEL SOV CLOSED is momentarily displayed.
GPU (if available)................................................. PUSH OUT
AOM-1502-016
Batteries 1 and 2.................................................. OFF
3-31
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Leaving the Airplane
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-31
Copyright © by Embraer. Refer to cover page for details.
Page 2
Leaving the Airplane
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
REQUIRED
EQUIPMENT
OPERATIONS
NORMAL PROCEDURES
FOR
SPECIAL
This section is intended to be used as guidance about the minimum
equipment required when operating under the following special
operations requirements:
• RVSM Airspace;
•
•
•
•
BARO RNAV Operations;
Low Visibility Operations (LVTO, ILS CAT II, AUTOLAND and HUD
A3);
Required Navigation Performance Operations (RNP);
P-RNAV and B-RNAV.
Additional restrictions on inoperative items may apply based on
operator’s practices or local authorities’ requests and/or requirements.
AOM-1502-016
In case of any discrepancies, the AFM/MMEL/Local Operational
requirements must prevail over this guidance.
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
REDUCED VERTICAL SEPARATION MINIMUM (RVSM)
Equipment Required
Radar Altimeter
System
Traffic Alert and
Collision Avoidance
System II (TCAS II)
ATC Transponder and
Automatic Altitude
Reporting System
RVSM Compliant Air
Data Systems
Number Required
1
1
Not Disconected/No
EICAS message.
Remarks
—
—
Required for autopilot
engagement.
1
Required for TCAS
operation (if TCAS is
required).
-
As required by local
regulations.
1
—
2
The ADS 1, ADS 2
and ADS 3 are
compliant with RVSM
operation.
The ADS 3 is not
considered RVSM
compliant in case of
loss of sideslip
compensation, i.e.,
with the EICAS
message ADS 3
SLIPCOMP FAIL
displayed.
TAT sensor failure
does not affect ADS
compliance with
RVSM.
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 2
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
Autopilot Channels
Autopilot (AP) Button
ROLL CONTROL
DISC and PITCH
CONTROL DISC
Advisory EICAS
Message
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
VERTICAL NAVIGATION - BARO VNAV
Equipment Required
Item
Number Required
FMS Source Selector
Buttons
1
AOM-1502-016
Flight Management
System (FMS)
Approach (APP)
mode button
Remarks
Not required if FMS is
already selected as
navigation source.
1
—
1
—
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
LOW VISIBILITY OPERATIONS - ILS CAT II
Equipment Required
Number Required
Flight Director
Channels
2
Autopilot (AP) Button
1
Approach (APP)
1
Mode Button
Autopilot/Trim
Disengage (AP/TRIM
2
DISC) Buttons
ROLL CONTROL
DISC and PITCH
Not Disconnected/No
CONTROL DISC
EICAS message.
Advisory EICAS
Message
Windshield Wiper
2
System
RA/BARO Selector
2
Knobs
Decision
Height/Minimum
Descent Altitude
2
(MINIMUMS) Selector
Knobs
VOR/Localizer (V/L)
Source Selector
Buttons
Radar Altimeter
System
VOR/ILS Systems
1
Remarks
For CAT II operation
with one engine
inoperative, manual
FD approaches are
prohibited.
If Autopilot is
required.
—
If Autopilot is
required.
—
—
2 knobs set to RA
required.
—
1 required only if
PREV button is
inoperative on the
same side.
1
—
2
—
CONTINUED...
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 4
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Item
Marker Beacon
Systems
Ground Proximity
Warning System
(GPWS)
VHF/COMM System
Air Data Systems
(ADS)
Primary Flight
Displays (PFD)
Inertial Reference
Systems
Rudder
AOM-1502-016
SPOILER FAULT
Caution EICAS
Message
Number Required
1
Remarks
Unless otherwise
authorized.
1
—
1
—
2
—
2
—
2
—
—
Rudder in Normal
Mode
No EICAS Message.
—
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
!Airplanes equipped with Autoland system
AUTOLAND
Equipment Required
Autopilot (AP) Button
Number Required
1
Remarks
—
2
—
1
Approach (APP)
1
Mode Button
Autopilot/Trim
Disengage (AP/TRIM
2
DISC) Buttons
ROLL CONTROL
DISC and PITCH
Not Disconnected/No
CONTROL DISC
EICAS message.
Advisory EICAS
Message
Windshield Wiper
2
System
RA/BARO Selector
2
Knobs
Decision
Height/Minimum
Descent Altitude
2
(MINIMUMS) Selector
Knobs
VOR/Localizer (V/L)
Source Selector
Buttons
Radar Altimeter
System
VOR/ILS Systems
1
Due to Autopilot
inoperative.
—
Due to Autopilot
inoperative.
—
—
—
—
1 is required only if
PREV button is
inoperative on the
same side.
2
—
2
—
CONTINUED...
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 6
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
Autopilot Channels
Flight Director
Channels
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Item
Marker Beacon
Systems
Inertial Reference
Systems
Primary Flight
Displays (PFD)
VHF/COMM System
Ground Proximity
Warning System
(GPWS)
Air Data Systems
(ADS)
Number Required
1
Remarks
Unless otherwise
authorized.
2
—
2
—
1
—
1
—
2
—
AOM-1502-016
"
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
REQUIRED NAVIGATION PERFORMANCE - RNP 0.3
(PRE-MOD MAU LOAD 27.1)
Item
Number Required
FMS Source Selector
Buttons
1
VOR System
Distance Measuring
Equipment (DME)
Systems
Global Positioning
System (GPS)
Flight Management
System (FMS)
Inertial Reference
System
MCDU
Display Units
RVSM Compliant Air
Data Systems
1
Remarks
Not required if FMS is
already selected as
navigation source.
—
1
—
1
—
1
—
1
—
1
4
—
—
The ADS 1, ADS 2
and ADS 3 are
compliant with RVSM
operation. The ADS 3
is not considered
RVSM compliant in
case of loss of
sideslip
compensation, i.e.,
with the EICAS
message ADS 3
SLIPCOMP FAIL
displayed. TAT sensor
failure does not affect
ADS compliance with
RVSM.
2
CONTINUED...
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 8
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Equipment Required
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
AOM-1502-016
Item
Flight Director
Channels
Number Required
Remarks
1
—
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
REQUIRED NAVIGATION PERFORMANCE - RNP 1
(PRE-MOD MAU LOAD 27.1)
Equipment Required
FMS Source Selector
Buttons
Number Required
Remarks
1
—
1
1
VOR System
0
Distance Measuring
Equipment (DME)
Systems
1
0
1
Global Positioning
System (GPS)
0
Flight Management
System (FMS)
Not required if FMS is
already selected as
navigation source.
Required when GPS
is not available.
Not required when
GPS operates
normally.
Required when GPS
is not available.
Not required when
GPS operates
normally.
Required when VOR
and DME are not
available.
Not required when
VOR and DME
operate normally.
1
—
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 10
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
Flight Director
Channels
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
REQUIRED NAVIGATION PERFORMANCE - RNP 2
(PRE-MOD MAU LOAD 27.1)
Equipment Required
Item
FMS Source Selector
Buttons
Number Required
Remarks
1
—
VOR System
0
1 Required if GPS is
not available.
Distance Measuring
Equipment (DME)
Systems
0
1 Required if GPS is
not available.
1
Global Positioning
System (GPS)
0
AOM-1502-016
Flight Management
System (FMS)
1 Required if VOR
and DME are not
available.
May be inoperative
provided VOR and
DME operate
normally
1
—
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 11
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
REQUIRED NAVIGATION PERFORMANCE - RNP 10
(PRE-MOD MAU LOAD 27.1)
Equipment Required
Number Required
FMS Source Selector
Buttons
1
Global Positioning
System (GPS)
Flight Management
System (FMS)
Inertial Reference
System (IRS)
Remarks
Not required if FMS is
already selected as
navigation source.
2
—
2
—
2
—
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 12
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
PERFORMANCE BASED NAVIGATION - P-RNAV /
B-RNAV / RNAV 5 (PRE-MOD MAU LOAD 27.1)
Equipment Required
Item
Flight Director
Channels
FMS Source Selector
Buttons
Flight Management
System (FMS)
Number Required
Remarks
1
—
1
—
1
—
1
VOR Systems
0
Distance Measuring
Equipment (DME)
System
1
0
1
Global Positioning
System (GPS)
0
Required if GPS and
DME/DME are not
available.
May be inoperative
provided GPS or
DME/DME operates
normally.
Required if GPS is
not available.
May be inoperative
provided GPS
operates normally.
Required if DME/DME
and VOR/DME are
not available.
May be inoperative
provided DME/DME
or VOR/DME
operates normally.
PERFORMANCE BASED NAVIGATION - RNAV 1 /
RNAV 2 (PRE-MOD MAU LOAD 27.1)
AOM-1502-016
Equipment Required
Item
Flight Director
Channels
Number Required
Remarks
1
—
CONTINUED...
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 13
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Item
FMS Source Selector
Buttons
Number Required
Remarks
1
—
1
Inertial Reference
System (IRS)
0
1
Distance Measuring
Equipment (DME)
Systems
0
1
Global Positioning
System (GPS)
0
Flight Management
System (FMS)
Required if GPS is
not available.
May be inoperative
provided GPS
operates normally.
Required if GPS is
not available.
May be inoperative
provided GPS
operates normally.
Required if DME or
IRS are not available.
May be inoperative
provided DME and
IRS operate normally.
1
—
REQUIRED NAVIGATION PERFORMANCE - RNP
APCH (PRE-MOD MAU LOAD 27.1)
Equipment Required
Number Required
FMS Source Selector
Buttons
1
Global Positioning
System (GPS)
Flight Management
System (FMS)
MCDU
Display Units
Remarks
Not required if FMS is
already selected as
navigation source.
1
—
1
—
1
4
—
—
CONTINUED...
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 14
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Item
Number Required
RVSM Compliant Air
Data Systems
2
Flight Director
Channels
1
Remarks
The ADS 1, ADS 2
and ADS 3 are
compliant with RVSM
operation. The ADS 3
is not considered
RVSM compliant in
case of loss of
sideslip
compensation, i.e.,
with the EICAS
message ADS 3
SLIPCOMP FAIL
displayed. TAT sensor
failure does not affect
ADS compliance with
RVSM.
—
AOM-1502-016
NOTE: VGP mode and APP button must be available for RNP APCH
with BARO – VNAV.
3-60
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Required Equipment for Special
Operations
Page 15
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
RNP AR 0.3 WITH MISSED APPROACH 1.0 (PRE-MOD
MAU LOAD 27.1)
Equipment Required
VGP
Number Required
Remarks
1
—
1
—
1
Radar Altimeter
System
Enhanced Ground
Proximity Warning
System (EGPWS)
Global Positioning
System (GPS)
Flight Management
System (FMS)
Inertial Reference
System
MCDU
Display Units
TAT
RVSM Compliant Air
Data Systems
Flight Director
1
1
VGP UNAVAILABLE
scratchpad message
not presented on the
MCDU.
Due to EGPWS
inoperative.
All modes are
required.
1
—
1
—
1
—
1
4
1
—
—
—
2
—
1
—
3-60
Copyright © by Embraer. Refer to cover page for details.
Page 16
Required Equipment for Special
Operations
REVISION 23
AOM-1502-016
Item
FMS Source Selector
Buttons
Approach (APP)
mode button
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
MANUAL PRESSURIZATION OPERATION
Pressurization Mode Selector................................. MAN
Cabin Altitude Controller......................................... AS REQUIRED
The airplane/cabin altitude conversion table must be consulted to
determine the cabin altitude according to airplane altitude. Refer to
the Quick Reference Handbook.
Check on the EICAS the proper cabin altitude, cabin rate and
differential pressure values.
Selection to UP momentarily position causes an increase of cabin
rate.
Selection to DOWN momentarily position causes a decrease in cabin
rate.
At the traffic pattern altitude, slowly position the knob to full UP. The
maximum differential pressure at takeoff and landing is 0.2 psi.
During descent the thrust levers should be moved as slowly as possible
to prevent bumps.
ECS OFF TAKEOFF
The Engines or the APU can supply bleed air for the air conditioning
packs during takeoff. To have an additional engine thrust during takeoff,
the FADEC may send an ECS OFF signal to the AMS controller
requesting that no air is extracted from the Engines and the bleed air for
packs operation can be provided by the APU.
On the MCDU Takeoff Data Set Menu the ECS ON or OFF option is
displayed. Selecting ECS ON commands the ENG BLEED to remain ON
and selecting ECS OFF commands the ENG BLEED to OFF until the
first 500 ft AGL.
It is possible to maintain the airplane pressurized during the initial 500 ft,
if all the following conditions occur:
– ECS is selected to OFF,
– APU is available, and
AOM-1502-016
– APU BLEED is PUSHED IN.
By accomplishing the recommended procedure, the ENG BLEED valves
will remain closed and the APU BLEED valve will supply bleed air for
CONTINUED...
3-68
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Suppl Procedures - Air
Management System
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
PACKS operation during takeoff until 500 ft AGL.
If APU BLEED is unavailable the PACKS will remain OFF until 500 ft
AGL.
ECS OFF TAKEOFF PROCEDURE
NOTE: – APU BLEED valve will supply bleed air for both PACKS
operation during takeoff until 500 ft. If APU BLEED is
unavailable, the PACKS will remain OFF until 500 ft AGL.
– The APU bleed cannot be used for the anti-ice system
operation. If the REF A/I is set to ENG or ALL for takeoff or
ice is detected during takeoff with APU BLEED, the APU
BLEED VALVE will close and the PACKS will switch OFF.
BEFORE START
REF ECS.............................................................. OFF
Select REF ECS OFF on the MCDU Takeoff Data Set.
AFTER START
APU (if available).................................................. ON
3-68
Copyright © by Embraer. Refer to cover page for details.
Page 2
Suppl Procedures - Air
Management System
REVISION 22
AOM-1502-016
AFTER TAKEOFF
APU....................................................................... OFF
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
UNPRESSURIZED FLIGHT
BASIC STATEMENT
Limit flight level to 10000 ft if carrying passengers. For flights without
passengers, flight level may be greater than 10000 ft provided crew
uses oxygen (Refer to appropriate regulations).
For flights with Air Conditioning Packs inoperative (MMEL Item 21-51-00)
or not running (MMEL Item 36-11-03), the following recommendations
apply:
– Prior to flight, if a Ground Air Conditioning System is available,
precondition the cabin in order to avoid high peak temperatures,
– Consideration should be given to passenger comfort and TAT
expected to be encountered in flight. When carrying passengers
or TAT is hotter than 20°C, close passenger window shades and
turn off unnecessary lights in order to minimize cabin heat.
Operating at TAT hotter than 32°C is not recommended due to
the resulting high temperatures in the cabin and cockpit,
– Using the Recirculation Fans to ON cools down the cabin
temperature,
– Flight crews can use Total Air Temperature to predict cabin and
cockpit temperatures during Ram Air operation, especially at
longer duration flights.
BEFORE START
Pressurization Mode Selector Knob....................... MAN
Outflow Valve on MFD ECS Synoptic Page........... Check fully OPEN
If the Outflow Valve is not fully open:
CABIN ALT Selector Knob...................................... UP
AOM-1502-016
Hold the cabin altitude selector knob UP until the Outflow Valve is
verified fully OPEN on MFD ECS Synoptic Page. If Outflow Valve
Indication is inoperative, hold the Cabin Altitude Selector Knob UP for at
least 60 s.
Except for ditching, the outflow valve should be kept OPEN during the
flight in order to avoid pressurizing the cabin. If Outflow Valve may not
be moved or is inoperative, it should be secured OPEN and extended
overwater operations are prohibited.
CONTINUED...
3-68
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Suppl Procedures - Air
Management System
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
On the MCDU Takeoff Data set:
REF ECS................................................................ OFF
CLIMB AND DESCENT
If possible, maintain climb and descent rates to a maximum of 500 ft/min
in order to improve comfort.
!Airplanes equipped with IFE (In-flight Entertainment System)
NOTE: In-Flight Entertainment system must be deactivated.
3-68
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Page 4
Suppl Procedures - Air
Management System
REVISION 22
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
Airplanes equipped with Autoland system
AUTOLAND
BEFORE TAKEOFF
Verify/Select Autoland enable on MCDU.
DESCENT
Set the RA/BARO Minimums on both Display Controls Panels.
APPROACH
NOTE: – The pilot should maintain hand and feet on controls during
entire approach and go-around in order to respond to an AP
disengagement.
– In case of autopilot disconnection, during an Autoland
operation below 800 ft, a pitch up tendency is expected due
to the automatic pre-trim.
– In case of Autoland capability degradation (degrade to APPR
2 or APPR 1) the approach must only be accomplished in
VMC, otherwise a go-around is required.
– The pilot should be vigilant for ILS disturbances on any ILS
quality beam in CAT I or better weather conditions when the
critical area protection is not assured by ATC. The pilot
should be warned that fluctuations of the LOC or G/S may
occur and be prepared to immediately disconnect the AP and
take appropriate actions in case unsatisfactory performance
occur.
APPROACH
Set the speed selector knob to manual.
Select the same ILS frequency on MCDU.
NOTE: – A minimum distance of 4 NM to the Outer Marker is
recommended for interception and stabilization along the
approach course.
– The Landing Reference Speed (VREF5) for Autoland
operations is the appropriate speed obtained from the CAFM.
AOM-1502-016
BEFORE LANDING
– Set airspeed bug to the approach speed (AP).
CONTINUED...
3-69
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Supp Procedures - Autoland
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– The approach speed must be bled off in such a way that over the
threshold the target speed will be at reference speed.
CONTINUED...
3-69
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Page 2
Supp Procedures - Autoland
REVISION 21
AOM-1502-016
– If visual contact is not made upon reaching the decision height,
or if visual contact is made but the airplane is not in position for
landing, or in case of any malfunction during approach, a missed
approach must be immediately initiated, unless the
meteorological conditions permit landing with the available
systems.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
MISSED APPROACH
GO-AROUND Procedure........................................ PERFORM
NOTE: A safe go around can be performed at any height.
!Airplanes equipped with Autoland System, ANAC or FAA certification
LANDING
Five seconds after touchdown, autopilot disengages and pilot is
responsible for speed and directional control.
"
!EMBRAER 190 models equipped with Autoland system, ANAC or FAA certification
DEMONSTRATED WIND COMPONENTS
For Autoland mode operations the following wind components have
been demonstrated:
Headwind................................................................ 37 kt
Tailwind................................................................... 17 kt
Crosswind............................................................... 21 kt
These values are provided for information only.
"
AUTOLAND OPERATION UNDER VMC
Although the autoland system was primarily designed to allow low
visibility approaches, an operator may adopt as company philosophy, to
perform automatic landings whenever is possible, to reduce errors and
pilot workload. Also there are many other reasons that may lead the
crew to perform an autoland under visual conditions, like crew
qualification, operational demonstrations or system verification.
This section provides some tips that should be observed when operating
an automatic landing on a CAT I beam or in a CAT II/III beam under
VMC.
There are basically two conditions that do not require an autoland, but
its execution may be accomplished:
AOM-1502-016
•
•
Category I only airports.
Category II or III airports, when operating under VMC.
CONTINUED...
3-69
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Supp Procedures - Autoland
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Below are some precautions that should be taken into account when
operating under one of the conditions above.
CATEGORY I ONLY AIRPORTS
CAT I airports must be qualified by the local authority for automatic
landings; because the quality of the signal may not support automatic
coupling since it is not a requirement for CAT I beams. But even on
beams qualified for autolands, the quality of the beam is a reason for
concern. The main factor affecting its accuracy is that the ILS sensitive
area is not protected, thus airplanes or other vehicles can cause
disturbance.
Also sudden and unexpected flight control movements may occur at a
very low altitude or during the landing and rollout when the autopilot
attempts to follow the beam bends.
It is also important to notice that CAT I beams are not qualified under
50 ft (100 ft in some airports) so anomalies below this altitude are more
common.
Other conditions that should be observed are:
•
The pre-threshold terrain may contain irregularities which may
cause abnormal autopilot behaviour.
•
The switch over time of the ground aids (time necessary for the
secondary power supply to actuate in case of a failure of the
primary source), are not in accordance with ICAO annex 14.
CATEGORY II OR III AIRPORTS OPERATING UNDER
VMC
Having observed the conditions and possibilities above the crew should
follow the procedures below to ensure the safety of an autoland on
those conditions:
CONTINUED...
3-69
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Page 4
Supp Procedures - Autoland
REVISION 21
AOM-1502-016
When an airport is operating under low visibility procedures, many
precautions and procedures are applied to ensure that the ILS critical
areas are protected. If operating under VMC, many of those procedures
are not in force, thus it is possible to encounter vehicles or other
airplanes inside the critical areas, causing ILS bends not usually found
in a beam qualified for CAT II or III. It is important that the pilot keeps this
in mind when operating in such conditions.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
AOM-1502-016
...CONTINUED
•
Always use fully the autoland operational procedures, regardless
of the weather conditions.
•
Flight crew should be alert to the possibility of abnormal autopilot
behavior and guard the flight controls (control wheel, rudder
pedals, and thrust levers) throughout all automatic approaches
and landings. They should be prepared to disconnect the autopilot
and manually land or go-around. Attempts to override the autopilot
instead of a disconnection are not recommended due to the
forces required to overpower the autopilot servos.
•
The ATC should be informed about the intention to conduct an
autoland. Such information should not be taken as a request for
or expectation of the protection of the ILS but is merely given to
enhance the possibility for ATC to inform the flight crew of any
known or anticipated disturbance.
3-69
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Supp Procedures - Autoland
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-69
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Page 6
Supp Procedures - Autoland
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ENGINE CROSSBLEED START
ENGINE CROSSBLEED START PROCEDURE
BEFORE START
Operating Engine Thrust Lever............................ ADVANCE
The minimum recommended bleed duct pressure prior to start is 40
minus 0.5 psi for every 1000 ft above sea level.
Smoothly advance operating engine thrust lever to obtain the
recommended duct pressure required.
Bleed Pressure on Status or ECS Synoptic
Page.................................................................... CHECK
Engine Start.......................................................... ACCOMPLISH
A bleed pressure drop is expected, but no thrust levers adjustment is
necessary.
AFTER START
Thrust Levers........................................................ AS REQUIRED
ENGINE TRANSFER HOSE START
This procedure gives the necessary instructions to start one engine of
the affected airplane with pneumatic pressure from a source airplane
APU or CF34 series engine.
BEFORE START
AOM-1502-016
For both airplanes, affected and source, set or keep these switches and
controls as follows:
Engine Thrust Levers........................................... IDLE
ELECTRIC Panel.................................................. SET
– IDG 1 Selector AUTO
– IDG 2 Selector AUTO
– AC BUS TIES Selector AUTO
– GPU Button AS REQUIRED
– APU GEN Button PUSHED IN
– TRU 1 AUTO
– TRU ESS AUTO
– TRU 2 AUTO
– DC BUS TIES AUTO
– Battery 1 Selector ON
CONTINUED...
3-70
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Engine
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Battery 2 Selector AUTO
IGNITION Selector Knobs.................................... AUTO
START/STOP Selector......................................... STOP
FUEL Panel........................................................... SET
– DC PUMP 1 Selector AUTO
– AC PUMP 1 and AC PUMP 2 selectors AUTO
AIR COND/PNEUMATIC Panel............................ SET
– PACK 1 Button PUSHED OUT
– PACK 2 Button PUSHED OUT
– XBLEED Button PUSHED IN
– BLEED 1 Button PUSHED OUT
– BLEED 2 Button PUSHED OUT
ICE PROTECTION Panel..................................... SET
– ENGINE 1 Button PUSHED OUT
– ENGINE 2 Button PUSHED OUT
– WING Button PUSHED OUT
ENGINE START WITH SOURCE AIRPLANE APU BLEED
This procedure gives the necessary instructions to start one engine of
the affected airplane with pneumatic pressure being supplied by the
source airplane APU.
Source Airplane
APU....................................................................... START
APU BLEED Button.............................................. PUSH IN
Affected Airplane
Bleed Pressure on ECS Synoptic Page............... CHECK
The recommended bleed duct pressure for engine start varies with
altitude and ambient temperature (OAT) according to the table below.
Check on the ECS synoptic page on MFD the bleed pressure before
starting the engines.
Pressure (psig)
40
39
38
CONTINUED...
3-70
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Page 2
Suppl Procedures - Engine
REVISION 23
AOM-1502-016
SEA LEVEL
OAT (°C)
-40
-20
-10
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
SEA LEVEL
OAT (°C)
0
10
20
40
54
Altitude (ft)
Pressure (psig)
37
36
35
34
33
CORRECTION
Pressure (psig) minus 0.5 psig
per 1000 ft ASL.
For instance, at an airport where the field elevation is 2000 ft and the
OAT is 10°C, the recommended bleed duct pressure for engine start
using a ground pneumatic cart is 35 psig.
Engine Start.......................................................... ACCOMPLISH
AFTER START
Transfer Hose and Ground Equipment................ DISCONNECT
Thrust Levers........................................................ AS REQUIRED
After engine start reconfigure the airplane as required.
ENGINE START WITH SOURCE AIRPLANE ENGINE
BLEED
This procedure gives the necessary instructions to start one engine of
the affected airplane with pneumatic pressure being supplied by the
source airplane engine.
Source Airplane
ENGINE 2............................................................. START
APU BLEED Button.............................................. PUSH OUT
BLEED 2 Button................................................... PUSH IN
Engine 2 Thrust Lever.......................................... ADVANCE
AOM-1502-016
Smoothly advance engine 2 thrust lever on the source airplane until
the recommended duct pressure required is achieved on the affected
airplane. The minimum recommended bleed duct pressure prior to
start is 40 minus 0.5 psi for every 1000 ft above sea level.
Affected Airplane
CONTINUED...
3-70
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Engine
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Bleed Pressure on ECS Synoptic Page............... CHECK
The minimum recommended bleed duct pressure prior to start is 40
minus 0.5 psi for every 1000 ft above sea level.
Engine Start.......................................................... ACCOMPLISH
A bleed pressure drop is expected, but no thrust levers adjustment on
the source airplane is necessary.
AFTER START
Transfer Hose and Ground Equipment................ DISCONNECT
Thrust Levers........................................................ AS REQUIRED
After engine start reconfigure the airplane as required.
ENGINE GROUND PNEUMATIC START
Engine starts using pneumatic carts usually presents higher ITT values.
It is recommended to use pneumatic carts to start the RH engine.
At operator’s discretion pneumatic carts can be used to start the LH
engine. However, due to airplane’s pneumatic system ducts geometry
the pneumatic cart may provide less pneumatic pressure when used to
start the LH engine.
All safety measures for ground personnel must be observed and the
crew must guarantee that the recommended bleed duct pressure for
engine start is achieved before attempting an engine start.
Perform an engine crossbleed start on the second engine.
AIR CONDITIONING PACKS
Before connecting the ground pneumatic cart, the packs must be pushed
out in order to avoid any cabin air contamination.
BEFORE START
APU Bleed Button (if applicable).......................... PUSH OUT
Close APU Bleed valve if APU is in use.
PACKS.................................................................. PUSH OUT
Ground Cart.......................................................... CONNECT
CONTINUED...
3-70
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Page 4
Suppl Procedures - Engine
REVISION 23
AOM-1502-016
Bleed Pressure on ECS Synoptic Page............... CHECK
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
The recommended bleed duct pressure for engine start varies with
altitude and ambient temperature (OAT) according to the table below.
Check on the ECS synoptic page on MFD the bleed pressure before
starting the engines.
SEA LEVEL
OAT (°C)
-40
-20
-10
0
10
20
40
54
Altitude (ft)
Pressure (psig)
40
39
38
37
36
35
34
33
CORRECTION
Pressure (psig) minus 0.5 psig
per 1000 ft ASL.
For instance, at an airport where the field elevation is 2000 ft and
the OAT is 10°C, the recommended bleed duct pressure for engine
start using a ground pneumatic cart is 35 psig.
Engine Start.......................................................... ACCOMPLISH
Engine start using pneumatic cart usually presents higher ITT values.
Consider performing a crossbleed start on the second engine.
AFTER START
Ground Cart.......................................................... DISCONNECT
PACKS.................................................................. PUSH IN
APU Bleed Button (if applicable).......................... PUSH IN
Open APU Bleed Valve if it was closed before engine start.
ENGINE BATTERY START
AOM-1502-016
This procedure allows engine starts with batteries as the only electrical
power and a pneumatic source (i.e. HPU or APU bleed air).
Engine starts using pneumatic carts usually presents higher ITT values.
It is recommended to use pneumatic carts to start the RH engine.
CONTINUED...
3-70
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Engine
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
At operator’s discretion pneumatic carts can be used to start the LH
engine. However, due to airplane’s pneumatic system ducts geometry
the pneumatic cart may provide less pneumatic pressure when used to
start the LH engine.
All safety measures for ground personnel must be observed and the
crew must guarantee that the recommended bleed duct pressure for
engine start is achieved before attempting an engine start.
Perform an engine crossbleed start on the second engine.
Considerations about the logistic regarding passengers boarding and
ground personal clearance must be taken into account prior to the
engine start, according to local authority allowances.
EICAS MESSAGES
Expect EICAS messages related to hydraulic system not being
pressurized and PACKs being shutoff. Wait until the procedure is
complete before acknowledging any EICAS message not related to an
abnormal engine start.
ENGINE BATTERY START PROCEDURE
BEFORE START
Perform the cabin inspection normally.
Internal Safety Inspection..................................... PERFORM
Battery 1............................................................... ON
Battery 2............................................................... AUTO
Batteries Voltage................................................... CHECK
FIRE EXTINGUISHER Panel............................... CHECK
Hydraulic ENG PUMP SHUTOFF 1 and 2........... PUSH IN
Electric Hydraulic Pumps 1, 2, 3A AND 3B.......... OFF
Before connecting the ground pneumatic cart, the packs must be
pushed out in order to avoid any cabin air contamination.
CONTINUED...
3-70
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Page 6
Suppl Procedures - Engine
REVISION 23
AOM-1502-016
No hydraulic pump may be turned on for at least 3 min after AC power
is established or, for airplanes Post-Mod. SB 190-31-0007 (Primus
Epic Load 4.5) or an equivalent modification factory incorporated, the
FLT CTRL TEST IN PROG Status message is no longer presented.
Otherwise the electrical PBIT will not run.
PACKS.................................................................. PUSH OUT
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Pneumatic Source................................................ CHECK AVAILABLE
Minimum Duct Pressure on STATUS Synoptic
Page.................................................................... CHECK
The minimum recommended bleed duct pressure is 40 minus 0.5 psi
for every 1000 ft above sea level.
Ignition Selector Knob.......................................... AUTO
Red Beacon.......................................................... ON
Engine Start.......................................................... ACCOMPLISH
Ground Cart (if applicable)................................... DISCONNECT
AFTER START
................................................Wait 2 min................................................
PACKS.................................................................. PUSH IN
After electrical PBIT is completed:
Hydraulic ENG PUMP SHUTOFF 1 and 2...... PUSH OUT
Electric Hydraulic Pumps 1, 2 and 3B............. AUTO
Electric Hydraulic Pump 3A............................. ON
SECOND ENGINE START
ENGINE CROSSBLEED START Procedure........ PERFORM
MANUAL STARTER VALVE OPERATION
ENGINE START
Accomplish the engine start through the following steps:
– Establish good coordination with the ground personnel about the
opening of the Starter Control Valve (SCV). Make sure that the
safety hazards are assessed, that the ground personnel is
protected from heat and air blast from the starters. A safe distance
must be kept from the engine air intake and exhaust areas during
the start operation.
– Use the ramp interphone to communicate with the ground
personnel during the start operation.
AOM-1502-016
– Turn the START/STOP selector to START and hold it in this
position.
CONTINUED...
3-70
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Engine
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Immediately after turning the START/STOP selector to START,
ask the ground personnel to open the Starter Control Valve
(SCV).
– Release the START/STOP selector to the RUN position.
– When N2 reaches 50%, ask the ground personnel to close the
SCV.
SINGLE ENGINE TAXI
To improve fuel savings a single engine taxi can be used, delaying the
start of the second engine prior to takeoff and/or shutting one engine just
after landing when taxiing in.
Single engine taxi may be performed when operating under icing
conditions provided that the Engine Run-Up procedure is used before
takeoff. However, single engine taxi should be avoided when operating
on slippery or contaminated taxiways.
Engine 1 or 2 can be used for single engine taxi operation.
BASIC STATEMENT
When performing a single engine taxi with engine 2 running, the Electric
Hydraulic Pump 1 Selector knob must be set to ON to ensure that the
hydraulic system 1 is pressurized.
!Airplanes equipped with SPDA previous than Block 12.1 OR PRE MOD SB190-240025
LOAD SHED EICAS message may be displayed on ground if airplane is
powered by only one AC power source and indicated airspeed is at or
above 50 kt.
"
Additional considerations should be taken into account to evaluate the
viability of this procedure.
TAXI OUT
When taxiing out, check if the following statements permit the single
engine taxi.
– Ramp gradient: positive ramp gradients demand more power.
– Taxi time to active runway.
CONTINUED...
3-70
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Page 8
Suppl Procedures - Engine
REVISION 23
AOM-1502-016
– Ramp weight: heavier airplanes demand more power.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
– Engines warm up.
If performing the Flight Controls check during Single Engine Taxi, check
one surface at a time (aileron, rudder or elevator) to avoid spurious FLT
CTRL NO DISPATCH message display.
SECOND ENGINE START
The engine start should be preferably performed with the airplane static
to avoid heads down condition during taxi.
Prior to takeoff, the second engine warm up cycle must be performed:
– Keep the engine running at or near IDLE for at least 2 minutes
before selecting high trust settings.
TAXI IN
When taxiing in, engines cool down cycle must be performed:
– Keep engines running for at least 2 minutes after IDLE thrust has
been set before engine shutdown to allow engine thermal
stabilization.
ENGINE 2 SHUTDOWN
The APU start cycle must be performed as follows:
– The APU start must be accomplished with the engine 2 running
or after the engine 2 shutdown cycle has been completed.
This procedure is necessary to ensure that battery 2 is available to the
airplane’s electrical network as a back-up and not isolated for APU start
only.
ENGINE 1 SHUTDOWN
In order to maintain hydraulic pressure on both brake systems the
Electric Hydraulic Pump 1 must be kept ON throughout the taxi.
SINGLE ENGINE TAXI PROCEDURE
TAXI OUT
AOM-1502-016
After one engine start up:
If using engine 2 for taxiing out:
Electric Hydraulic Pump 1 Selector knob............. ON
CONTINUED...
3-70
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Engine
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Start the second engine within an available time from takeoff, to allow
2 min of thermal stabilization. Taxi time at or near IDLE can be included
in the engine warm up period.
Second engine start.............................................. ACCOMPLISH
Electric Hydraulic Pump 1 Selector knob............. AUTO
After start procedure............................................. ACCOMPLISH
TAXI IN
APU......................................................................... AS REQUIRED
If using engine 2 for taxiing in, before shutting down engine 1:
Electric Hydraulic Pump 1 Selector knob............. ON
3-70
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Page 10
Suppl Procedures - Engine
REVISION 23
AOM-1502-016
After engines shutdown:
Electric Hydraulic Pump 1 Selector knob............. AUTO
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
BOUNCED LANDING RECOVERY
The key factor for a successful landing is a stabilized approach and
proper thrust/flare coordination. Do not extend the flare at idle thrust as
it will significantly increase landing distance. Reducing to idle before the
flare will also require an increase in pitch. Flaring high and quickly
reducing thrust to idle can cause the plane to settle abruptly. Do not
apply stabilizer trim during the flare.
AOM-1502-016
When a light bounce occurs, maintain or re-establish a normal landing
attitude. Increasing pitch can lead to a tail strike. Beware of the increased
landing distance and use power as required to soften the second
touchdown. When a more severe bounce occurs, initiate a go around –
do not attempt to land. Press the go-around button and advance thrust
levers to TOGA. Hold the flare attitude until the engines spool up and
reset stabilizer trim, then follow normal go-around procedures.
3-72
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Suppl Procedures - Bounced
Landing
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-72
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Page 2
Suppl Procedures - Bounced
Landing
REVISION 9
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
HOT WEATHER OPERATION
The following procedures will improve cockpit and cabin cooling during
ground operations:
NOTE: When engine is shutdown, apply cool air from the air
conditioning cart whenever possible.
AIR COND RECIRC Button.................................... PUSH IN
CKPT/PAX CABIN Temperature Controllers.......... MAX COLD
Doors and Windows................................................ KEEP CLOSED
Passenger Cabin Gasper and Cockpit Outlets...... OPEN
Window Shades on the Sun-exposed Side of the
Cabin..................................................................... CLOSE
ICING CONDITIONS, COLD WEATHER AND COLD
SOAK OPERATIONS
This Section contains the procedures and techniques to operate in icing,
cold weather and cold soak conditions and supplements those
procedures published in the AFM. In case of differences, the AFM shall
govern. Strict reference to AFM procedures throughout the flight is
necessary.
The procedure begins with information on several systems and then
continues with the procedures and checklists to perform before, during
and after flight.
BASIC STATEMENTS
FREEZING RAIN AND FREEZING DRIZZLE
Atmospheric conditions involving freezing rain or freezing drizzle
associated to supercooled large droplets (SLD), may present a condition
that is beyond those for which the airplane was certified.
AOM-1502-016
Both freezing rain and freezing drizzle can exist down to ground level
and cause ice to form quite rapidly on all surfaces even during short
exposures and on areas not normally known to be subjected to ice
accretion. This means that the airplane is not designed to fly under
freezing rain/drizzle (SLD) conditions.
If the crew notices abnormal ice formation on areas not usually affected
by this phenomenon, or ice formation on the previously treated upper
surface of the wings, they must consider to be flying under severe icing
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
conditions. In this case, the anti-ice system is failing to reduce or control
ice formation. The crew must then exit freezing rain/drizzle conditions as
soon as possible since continuous flight under such conditions is, indeed,
quite hazardous.
BATTERIES
Certain temperatures require batteries removal to prevent cold soaking.
Verify that batteries have been reinstalled.
AMBIENT TEMPERATURE
VERSUS
EXPOSURE TIME
12
REMOVE BATTERIES
8
6
4
NO ACTION
0
−30
−25
−20
−15
−10
AMBIENT TEMPERATURE (°C)
EM170AOM030002A.DGN
EXPOSURE TIME − PARKING (HOURS)
16 OR
MORE
NOTE: – The time count starts when the airplane is powered down.
– The temperature used to enter the graphic must be the
lowest one that the airplane has been exposed during the
parking time.
– If the airplane is heated (external pneumatic heat source)
during the parking, there is no need to remove the batteries,
regardless of time and temperature.
CONTINUED...
3-75
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Page 2
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
APU
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Check the APU air inlet, cooling air inlet and APU outlet to ensure that it
is clear of ice or snow.
If APU cannot be started, apply heat from a ground cart directly into the
APU compartment.
CAUTION: DO NOT ALLOW THE HOT AIR FROM THE GROUND
CART TO EXCEED 100°C (212°F), IN ORDER TO
PREVENT ANY DAMAGE TO THE COMPONENTS INSIDE
THE COMPARTMENT.
EXTERNAL INSPECTION
Operating regulations clearly state that no takeoff is allowed when snow,
ice or frost is adhering to the airplane.
The captain has the final responsibility for ensuring that the airplane is
clear of ice, frost or snow. The primary method for the flight crew to
ensure a clean airplane is through close visual and physical inspection
of the critical surfaces prior to takeoff.
Even at intermediate stops, an external walk around is necessary due to
the possibility of ice forming after landing from either cold soaking frost,
conventional frost or precipitation freezing on the airplane.
Make sure wheel chocks are in place.
Remove covers from engine air inlet/outlet, APU air outlet, APU oil
cooler air inlet, smart probes, TAT probes and wheels. If required, leave
engine covers installed until engine start.
Visually check the wing, control surfaces, engines and fuselage prior to
takeoff. In addition, as no frozen contamination is allowed on the wing
upper surface, if ice accretion is suspected, perform a physical
(hands-on) inspection to ensure that there is no ice accumulation.
Do not touch the surfaces with bare hands, as the skin may stick to a
freezing surface.
AOM-1502-016
Check that the fuselage, wing upper and lower surfaces, tail and control
surfaces are free of frost, ice or snow. Inspect control surfaces, gaps
and hinges for signs of residual fluid or gel.
A 3 mm (1/8 in) frost layer is permitted on the underwing surfaces. Frost
is not permitted on the lower or upper surface of the horizontal stabilizer
or the upper surface of the wing. Cold-soaked fuel frost may form on the
ground on the wing upper surface after long flights at low temperatures.
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Expect this kind of frost when fuel remaining in each tank exceeds
3420 kg (7540 lb).
A thin layer of hoarfrost is permitted on the fuselage provided the layer is
thin enough to distinguish surface features underneath, such as painting
and markings.
No contamination is permitted on the lower/upper surface of the
horizontal stabilizer or the upper surface of the wing. If any degree of
contamination is found, de-icing and/or anti-icing has to be requested by
the pilot in command. All snow and ice must also be cleared from nose
radome and fuselage nose forward of windshield, as it is likely to blow
back into windshields during taxi or takeoff.
The fan must be able to rotate freely. Heavy accumulation of ice or snow
in the inlet, on the spinner, on the fan blades or on the booster area must
be removed prior to start. Light ice (similar to hoar frost) or light snow in
the inlet, on the spinner, on the fan blades or on the booster area may
be removed by performing the engine run-up procedure. A small area of
thin ice formed at the basis of the inlet near the drain in front of the fan
blades is allowed as long as the fan is free to rotate prior to engine start.
During the pre-flight walk-around check that the Air Data Smart Probes
(ADSPs) are free from residual deicing and anti-icing fluid and that there
is no residual hardened residue on any part of the ADSPs, especially if
Type II or IV fluid were used recently. If any contamination is found on
Smart Probes, call maintenance.
CONTINUED...
3-75
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Page 4
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
Check TAT probes, pressurization static port, all inlets, outlets and vents
are clear of ice and unobstructed.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
ANTI−ICING FLUID RESIDUE
EM170AOM030010A.DGN
ANTI−ICING FLUID RESIDUE
AOM-1502-016
SAMPLE OF SMART PROBE ANTI-ICE FLUID CONTAMINATION
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
EM170AOM130034A.DGN
...CONTINUED
LEGEND:
A THIN LAYER HOAR FROST WHERE YOU CAN SEE THE
AIRCRAFT MARKINGS ON THE FUSELAGE IS PERMITTED.
OTHERWISE, DEICING FLUID MUST BE APPLIED.
DEICING FLUID APPLICATION AREAS.
DEICING FLUID NON−APPLICATION AREAS.
CONTINUED...
3-75
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Page 6
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
DEICING FLUID APPLICATION
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
EM170AOM130035A.DGN
...CONTINUED
LEGEND:
ANTI−ICING FLUID APPLICATIONS AREAS.
ANTI−ICING FLUID NON−APPLICATION AREAS.
TYPE II/III/IV ANTI-ICING FLUID APPLICATION
AOM-1502-016
If the airplane has become cold soaked as a result of flight at very cold
temperatures, fuel might be at a subfreezing temperature. This can
cause ice accumulation if the airplane is subjected to high humidity, fog,
drizzle or rain even when the outside air temperature is substantially
above freezing.
At the completion of the walk-around, if ice, snow or frost is discovered,
de-icing, and possibly anti-icing will be required. The check for ice
accumulation should be done in a well-lit area.
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Recommended practice is to use holdover times in conjunction with a
pre-takeoff check to ascertain that frozen deposits have not started to
accumulate on treated surfaces. This is a check normally conducted
from inside the cockpit.
Although only the wing tips and leading edges can be seen from the
cockpit, the entire wing is visible from a cabin window. If checking the
wing tips is not enough to make sure the holdover times is still
appropriate, look at the entire upper surface and not just the leading
edge or wing tip.
A pre-takeoff contamination check is normally accomplished when the
airplane cannot be effectively inspected by a pre-takeoff check or when
the holdover times has been exceeded. It must be completed within
5 min prior to beginning takeoff and from the outside the airplane, unless
the operator’s program specifies otherwise. The assistance of ground
personnel trained and qualified to inspect the wing, empennage and
fuselage may be required.
The upper surface of the horizontal stabilizer/elevator is not visible either
from the ground or the cockpit.
A comparative analysis may be used to validate the condition of these
surfaces. The upper surface of the wing should be used as the
comparative surface. If the inspection of the upper wing surface dictates
that there is a requirement to de-ice/anti-ice then the horizontal
stabilizer/elevator upper surface must also be de-iced/anti-iced.
Conversely, if the inspection of the upper wing surface dictates that
there is no requirement to de-ice/anti-ice then the horizontal
stabilizer/elevator upper surface need not be de-iced/anti-iced.
When contamination is in evidence, the de-icing/anti-icing operation
must be repeated. It is the pilot’s responsibility to decide whether or not
to accept the airplane for flight. If contamination is suspected, the
airplane should return for additional deicing or anti-icing.
DOORS
CONTINUED...
3-75
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Page 8
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
Holdover time should not be considered an exact figure. It is just an
average time, which can be reduced by many factors affecting the fluid
effectiveness. In the case of ice build up after deicing/anti-icing fluid
application, do not assume that ice will be blown off during takeoff roll.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
All doors and windows must be closed to prevent snow and humidity
from entering into the airplane.
Whenever possible, to maintain cabin warmth, keep the passenger,
cargo and service doors closed at intermediate stops.
Check that doors, gear locks and mechanisms are unobstructed and
clear of ice and snow and ensure no leaks exist.
NOTE: In case the cargo door vent panel is stuck due to cold soak,
heat should be applied for at least 5 min to the door latch
mechanism at the bottom edge of the door, around the
inspection windows. Use a heat gun or heater equipment with
maximum hot air temperature of 80°C.
ENGINE START
Do not start the engine until heavy accumulation of ice or snow in the
inlet, on the spinner, on the fan blades or on the booster area is
removed.
Fuel temperature limits for engine start are the same as those prescribed
for APU start.
Perform normal engine start. If the engine does not start, maintenance
procedures may be required or ground heating may be necessary to
warm the nacelle, Air Turbine Starter (ATS) and Starting Control Valve
(SCV).
During start with low oil temperatures, the oil pressure may drop below
the minimum oil pressure levels temporarily after start. If the oil pressure
remains below minimum levels for more than 2 min, the engine must be
shut down and the oil heated. During the subsequent start after heating
the oil, if the oil pressure does not recover, the engine must be shut
down and the cause investigated.
NOTE: – In order to improve the chances of a successful engine start,
the oil temperature should be raised to at least -20°C.
– In ambient temperatures lower than -2°C, dual ignition and
increased starting fuel flow schedule take place to provide
greater torque during engine on ground starts.
CAUTION:
•
AOM-1502-016
•
TO PREVENT DAMAGE TO NACELLE COMPONENTS,
DO NOT ALLOW THE HOT AIR FROM THE GROUND
CART TO EXCEED 100°C (212°F).
DURING COLD WEATHER OPERATIONS, OIL
PRESSURE PEAKS TO FULL SCALE MAY OCCUR
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
DUE TO HIGH OIL VISCOSITY. OIL PRESSURE
SHOULD DECREASE AS THE OIL TEMPERATURE
INCREASES. IF THE OIL PRESSURE REMAINS
ABOVE NORMAL OPERATING RANGE, THE ENGINE
SHOULD BE SHUTDOWN AND THE CAUSE
INVESTIGATED.
TAXI
Use minimum thrust for breakaway and taxiing, to avoid blowing snow or
slush on personnel or airplanes nearby. Maintain ground speed as low
as practical when taxiing in snow covered or icy runways. Lower speeds
will also avoid throwing slush on the wheel and brake assembly.
Use firm brake pressure on taxi stops whenever pavement conditions
permit in order to warm up the brakes and dry moisture buildup within
the disk stack. Anti-skid protection is not provided below 10 kt, so apply
brakes accordingly.
During taxi, “cold set” (the condition where the tire retains the flat shape
it had while parked) may induce vibration in the airplane. Vibration
should disappear as the tires recover their elasticity during taxi. Do not
initiate your takeoff run before the “cold set” disappears.
Turns should be performed at the largest turning radius, preferably at a
speed which do not required braking during the turn.
Maintain a greater than normal distance behind other airplanes while
taxiing in snow or slush-covered runways, to avoid contamination by
snow blown by jet blasts.
ENGINE RUN-UP
The engine run-up procedure must be used in the following conditions:
– In icing conditions for ground operations of more than 30 min.
– In case of increased fan vibration due to fan ice accumulation.
– to remove light ice (similar to hoar frost) or light snow in the inlet,
on the spinner, on the fan blades or on the booster area as
observed during the external inspection. Perform at the earliest
convenient moment, not to exceed 30 min after engine start.
CONTINUED...
3-75
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Page 10
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
The engine run-up procedure is as follows:
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
The engine thrust level must be increased at maximum 30 min intervals
to a minimum of 54% N1 and held at that thrust level for 30 s or until fan
vibration level returns to normal.
Do not apply reverse thrust during taxi, unless absolutely necessary.
TAKEOFF
It is recommended that the ice shedding engine run-up procedure be
completed just before, or in conjunction with the takeoff procedure.
Particular attention should be given to engine parameters prior to final
advance to takeoff thrust.
NOTE: Engine vibration may indicate maximum display value before
shedding ice, however, it has no adverse effect on the engine.
GENERAL REMARKS WHEN FLYING IN ICING CONDITIONS
– Continuously monitor engine parameters, airplane pitch attitude
and airspeed.
!MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II
– The green dot does not account for ice accretion. Therefore,
when flying in icing conditions (EICAS message STALL PROT
ICE SPEED displayed) it is recommended to add 10 kt to the
green dot.
"
!MAU Load 25.5.0.1 and on
– The green dot accounts for ice accretion.
"
– Be careful for any mistrimmed condition that may be masked by
the autopilot - keep the airplane trimmed at all the times. Consider
turning autopilot off if you suspect you are flying in severe icing
conditions.
AOM-1502-016
– Monitor anti-ice systems for proper operation. Apply the
associated AFM abnormal procedure in case of system failure. If
the failure persists, exit and avoid icing conditions. Make the air
traffic controller know you are requesting a change due to icing
conditions and keep him informed about it.
– Strictly follow AFM Operation In Icing Condition normal
procedures.
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 11
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Avoid landing in an airport where icing conditions exist or are
anticipated if anti-ice system, brakes, thrust reverser, ground
spoilers, nosewheel steering or flight controls have failed.
– Do not hesitate to leave icing conditions when icing cannot be
handled, even with anti-ice system operating properly.
– Typically as ice is shed asymmetrically from the fan, a fan
unbalance will occur resulting in higher than normal vibration
indications. When the ice shedding is complete the vibration
levels will typically return to normal indication levels for the
particular engine. This reduction in vibration indication is a sign to
the flight crew that the ice shed was successful and it may take
several minutes or more for this to occur. Likewise, an increase
in vibration level would be a sign that fan ice was possibly
accumulating.
NOTE: Engine and Wing Ice Protection Systems operation is automatic
and based on the primary ice detection system. However the
crew remains responsible for monitoring icing conditions and for
manual activation of the ice protection system if icing conditions
are present and the ice detection system is not activating the ice
protection system.
CLIMB/CRUISE
Operation in moderate to severe icing conditions may allow ice to build
up on the fan spinner and/or blades.
If allowed to accumulate, asymmetrical ice shedding may result in high
fan vibration.
For operations in moderate to severe icing conditions, reduce one thrust
lever at a time towards idle, then advance to a minimum of 70% N1 for
10 - 30 s, then return thrust lever to position required for flight conditions.
Accomplish the periodic engine run up every 15 min if fan ice build up is
suspected (high indicated or perceived vibration).
Operation of the ignition system is not required for this procedure
provided the FADEC automatic relight system is operating normally.
NOTE: Engine vibration indication may peek to the maximum value
prior to ice shedding, however, this will not affect the engine.
If engine vibration increases reduce the thrust to idle, advance thrust
levers to obtain 70% N1 and then return to the desired setting.
CONTINUED...
3-75
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Page 12
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
DESCENT
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
When using the autopilot, monitor pitch attitude and speed continuously.
CAUTION: EVEN SMALL ACCUMULATIONS OF ICE ON THE WING
LEADING
EDGE
MAY
CHANGE
THE
STALL
CHARACTERISTICS OR THE STALL PROTECTION
SYSTEM WARNING MARGIN.
LANDING ON WET OR SLIPPERY RUNWAYS
Conduct a positive landing to ensure initial wheel spin-up and initiate
firm ground contact upon touchdown, achieving wheel load as quickly as
possible. Such technique avoids hydroplaning on wet runways and
reduces the strength of any ice bond that might have been eventually
formed on brake and wheel assemblies during flight.
The factors that influence the occurrence of hydroplaning are high
speed, standing water and poor runway macrotexture. When
hydroplaning occurs, it causes a substantial loss of tire friction and
wheel spin-up may not occur.
Icy runways can be very slippery at all speeds depending on
temperature.
Stopping the airplane with the least landing run must be emphasized
when landing on wet or slippery runways.
– Anticipate the approach procedures and speeds: a well-planned
and executed approach, flare and touchdown minimize the
landing distance;
– Immediately after touchdown, check the ground spoiler automatic
deployment when thrust levers are reduced to IDLE;
– Lower nose wheel immediately to the runway. It will decrease lift
and will increase main gear loading;
– Apply thrust reversers cautiously and observe how the airplane
responds before full reverse is used. Normal procedure is to
move the thrust levers out of reverse when ground speed is
reduced to 60 kt. In a emergency, reverse thrust may be used to
bring the airplane to a full stop;
AOM-1502-016
– Do not use asymmetric reverse thrust on slippery and icy
runways;
– Apply brakes with moderate-to-firm pressure, smoothly and
symmetrically, and let the anti-skid do its job;
CONTINUED...
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REVISION 23
Suppl Procedures Environmental
Page 13
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– If no braking action is felt, hydroplaning is probably occurring. Do
not apply Emergency/Parking Brake, as it will remove anti-skid
protection. Maintain runway centerline and keep braking until
airplane is decelerated.
LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN
EXTENDED PERIOD
Anti-icing fluid can be applied to the airplane surfaces at the time of
arrival, on short turn arounds during freezing precipitation, and on
overnight stops. This will minimize ice accumulation before departure
and usually makes subsequent deicing easier.
The procedure ″LEAVING THE AIRPLANE - SECURING FOR COLD
SOAK OR AN EXTENDED PERIOD″ should be performed in the event
of extended airplane exposure to low temperatures. At non-maintenance
stations, the crew should ensure that the actions have been
accomplished.
For an icy ramp, leave Emergency/Parking Brakes applied. Otherwise,
Emergency/Parking Brakes must not be applied to avoid brakes freezing.
Wheel and tires may melt snow or ice by the heat retained in the brakes.
Parking main tires on a layer of sand or on a mat may prevent tires from
freezing on pavement surfaces.
Install protective covers at engines and APU inlets/outlets, APU oil
cooler air inlet, smart probes, TAT probes, and wheels.
Drain water and waste from all water tanks if cold soak temperature is
expected to be lower than 0°C (32°F).
3-75
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
If the airplane is heated (external pneumatic heat source) during the
parking, there is no need to remove the batteries, regardless of time and
temperature.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ICING CONDITIONS, COLD WEATHER AND COLD
SOAK PROCEDURE
POWER UP
Batteries.................................................................. CHECK
INSTALLED/
CONDITIONS
Minimum Battery Temperature................................ -20°C (-4°F)
Minimum Battery 2 Voltage..................................... 22.0 V
External Power (if available)................................... CHECK
Minimum temperature (to start the APU) using
external electrical power....................................... -54°C (-65°F)
Accomplish a normal power up.
Wait for PBIT completeness and the message FLT CTRL TEST IN
PROG disappearance.
Hydraulic System Warm Up................................... ACCOMPLISH
Warm up must be accomplished before starting the engines in case of
reservoir temperatures below -18°C (-0.4°F).
Electric Hydraulic Pump Sys 1 and 3A.................. ON
PTU......................................................................... ON
...............................................WAIT 30 s...............................................
PTU......................................................................... AUTO
Electric Hydraulic Pump Sys 2............................... ON
SLAT/FLAP............................................................. CHECK
Leave the flaps and slats up if application of anti-icing/deicing fluids is
expected. Ensure they are free from ice or snow. Extend and retract
them.
Fuel Temperature.................................................... CHECK
Minimum Fuel Temperature for APU Start:
For Jet A Fuel......................................................... -37°C (-34°F)
For Jet A1 Fuel....................................................... -44°C (-47°F)
NOTE: For minimum temperature limits applicable to other fuel types,
refer to the AFM.
AOM-1502-016
NOTE: If temperature is below -10°C before engine start, Embraer
recommends the use of fuel ice inhibitor additive.
EXTERNAL SAFETY INSPECTION
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 15
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Wheel Chocks......................................................... IN PLACE
Smart Probes/TAT................................................... CHECK
Free of ice and residual deicing and anti-icing fluids.
Air Conditioning Inlets/Outlets................................ CLEAR OF ICE
Ice Protective Covers.............................................. CHECK REMOVED
If required, leave engine covers installed until engine start.
Engine..................................................................... CLEAR OF ICE OR
SNOW
NOTE: For exceptions, refer to Basic Statements - External Inspection.
Landing Gear.......................................................... CLEAR OF ICE,
UNOBSTRUCTED
Fuselage, Wing, Tail and Control Surfaces............ FREE OF FROST,
ICE OR SNOW
If ice accretion is suspected, perform a physical (hands on) inspection
to ensure that there is no ice accumulation.
APU Area................................................................ CLEAR OF ICE OR
SNOW
CABIN WARM UP
Doors....................................................................... CLOSE
Air Conditioning Pneumatic Panel.......................... SET
Keep all pushbuttons pushed in, while bleeding air from the APU, or
use a ground cart to warm up the interior of the airplane. Set Cockpit
and Cabin rotating knobs to full hot for rapid cabin warm up in low
ambient temperature. The warm-up should be accomplished with all
doors closed and the toilets doors open, if possible.
BEFORE START
TO DATASET MENU.............................................. SET
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
Ensure that the TO DATASET MENU page on the MCDU and Ice
Protection Mode Selector are set according to the table OAT/visible
moisture table.
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
ON GROUND
Outside Air
Temperature
Visible
Moisture
Higher than 10°C
Equal to or higher than
5°C and equal to or
lower than10°C
Lower than 5°C
Any
YES
MCDU
(TAKEOFF
DATASET
MENU)
OFF
YES
ENG
YES
NO
ALL
OFF
Ice
Protection
Mode
Selector
AUTO
If moisture presence is in question, visible moisture should be
assumed.
ADS Probe Heaters................................................ AS REQUIRED
If probes are contaminated, push in and verify light illuminates.
NOTE: Do not turn on the heaters while the airplane is energized by
batteries, to avoid battery discharge.
ENGINE START
Minimum Oil Temperature....................................... CHECK
Minimum Oil Temperature is -40°C (-40°F).
Accomplish normal engine start procedure.
AFTER START
Engine Instruments................................................. MONITOR
Continue to monitor engine instruments, mainly oil pressure and
temperature. Apply associated abnormal procedure if any failure
arises.
Main Panel.............................................................. CHECK
Check proper operation of all instruments and systems. Confirm
engine anti-ice system is operating normally.
Steering................................................................... ENGAGE
AOM-1502-016
NOTE: If steering had been disengaged for push-back, reengage it and
keep it engaged while the electric hydraulic pumps are running.
ADS Probe Heaters................................................ PUSH OUT
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 17
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
After reservoir temperatures are higher than 0°C (32°F) for systems
1, 2 and 3:
Electric Hydraulic Pumps Sys 1 and 2................. AUTO
NOTE: – When attempting a single engine taxi with engine 2, select
the Electric Hydraulic Pump 1 knob to ON.
– After starting engine 1, select Electric Hydraulic Pump 1
knob to AUTO.
AIRPLANE ANTI-ICING/DEICING
ENGINES/APU RUNNING
FLUID
APPLICATION
WITH
CAUTION: APU OPERATION IS NOT RECOMMENDED DURING THE
AIRPLANE DEICING/ANTI-ICING PROCEDURE. IF APU
OPERATION IS ABSOLUTELY NECESSARY, MAKE SURE
THAT DEICING/ANTI-ICING FLUID IS NOT APPLIED
DIRECTLY TO OR NEAR THE APU AIR INLET, THE APU
BLEED AIR VALVE IS CLOSED, AND THE PACKS ARE
SET TO OFF.
Parking Brake......................................................... ON
Doors....................................................................... CLOSE
Thrust Levers.......................................................... IDLE
SLAT/FLAP............................................................. CHECK UP
Pitch Trim................................................................ FULL NOSE DOWN
Engine Bleed Buttons............................................. PUSH OUT
APU Bleed Button................................................... PUSH OUT
Packs Buttons......................................................... PUSH OUT
Packs should be off to avoid contamination of cabin air with fumes
generated from ingestion of fluids in engine/APU.
After Deicing/Anti-icing Procedure is complete:
..........................................Wait at least 1 min..........................................
APU Bleed Button................................................. PUSH IN
Engine Bleed Buttons........................................... PUSH IN
Wait at least three minutes to push in the air conditioning packs
pushbuttons, thereby avoiding contaminating the airframe air
conditioning system with deicing/anti-icing fluid gases.
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
..........................................Wait at least 3 min..........................................
Packs Buttons....................................................... PUSH IN
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
TAXI
Ground Speed Taxi................................................. AS LOW AS
PRACTICAL
Engine Run-Up....................................................... AS REQUIRED
SLAT/FLAP............................................................. AS REQUIRED
When taxiing through slush or standing water, slat/flap should be
retracted to avoid snow and slush contamination from the main gear
wheels.
WARNING: IF FLAPS/SLATS WERE LEFT UP DURING TAXI,
COMPLETE AFTER START CHECKLIST BEFORE
TAKING OFF.
CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS
TO AVOID SKIDDING THE AIRPLANE. REDUCE SPEED
FOR ALL TURNS AND USE CAUTION WHEN TAXING
WITH HIGH CROSSWINDS.
BEFORE TAKEOFF
Takeoff Briefing....................................................... COMPLETE
Flight Controls......................................................... CHECK
Check freedom of movement and full travel of all flight controls
(including trims).
A full green box indication on the synoptic page or a full trim travel
indication on the EICAS are not a requirement for a successful check.
Pitch Trim................................................................ SET
Set the PITCH trim according to load sheet and verify YAW and ROLL
trims to the neutral position.
SLAT/FLAP............................................................. SET
Set SLAT/FLAP to takeoff setting (if flaps were left up after starting
the engines).
Takeoff Configuration.............................................. CHECK
Ice Accumulation..................................................... CHECK
Engine Run-Up....................................................... AS REQUIRED
TAKEOFF
AOM-1502-016
Accomplish takeoff procedure normally.
IN FLIGHT
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 19
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Engine Parameters................................................. MONITOR
Pitch Attitude and Airspeed..................................... MONITOR
!MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium II
– The green dot does not account for ice accretion. Therefore,
when flying in icing conditions (EICAS message STALL PROT
ICE SPEED displayed) it is recommended to add 10 kt to the
green dot.
"
!MAU Load 25.5.0.1 and on
– The green dot accounts for ice accretion.
"
HOLDING
Landing Gear.......................................................... UP
SLAT/FLAP............................................................. UP
Minimum Airspeed.................................................. 210 KIAS
CAUTION: EVEN SMALL ACCUMULATIONS OF ICE ON THE WING
LEADING
EDGE
MAY
CHANGE
THE
STALL
CHARACTERISTICS OR THE STALL PROTECTION
SYSTEM WARNING MARGIN.
DESCENT
Assess the operational landing distance according to the reported
landing runway conditions.
APPROACH AND LANDING
Observe normal approach and landing procedures.
TAXI-IN AND PARKING
Engine and Wing Ice Protection............................. AS REQUIRED
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
After landing, set the Engine and Wing Ice Protection systems using
the overhead panel Ice Protection Mode Switches according to
weather conditions.
SLAT/FLAP............................................................. AS REQUIRED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
CAUTION: TAXI AT REDUCED SPEED IN ICE-COVERED RUNWAYS
TO AVOID SKIDDING THE AIRPLANE AND THROWING
SLUSH ON WHEEL AND BRAKE ASSEMBLIES.
NOTE: – Make sure the slat/flap are free from snow, ice or slush
before retracting them.
– If any difference is felt while taxiing, verify if tires present any
flat spot which may indicate that the brake was blocked at
touchdown.
THROUGH-FLIGHTS
Doors and Windows................................................ CLOSE
Whenever possible, to maintain cabin warmth, keep the passenger,
cargo and service doors closed at intermediate stops.
APU......................................................................... ON
APU should be on to provide bleed air to the air conditioning packs in
order to maintain cabin heat.
Walk around the airplane and check the following items:
Wing, Tail and Control Surfaces........................... FREE OF FROST,
ICE OR SNOW
Air Data Smart and TAT Probes........................... CLEAR OF ICE
Engine/APU Air Inlet............................................. CLEAR OF ICE OR
SNOW
NOTE: For exceptions, refer to Basic Statements - External Inspection.
Landing Gear ....................................................... CLEAR OF ICE,
UNOBSTRUCTED
Air Conditioning Inlets and Outlets....................... CLEAR OF ICE
Fuel Tank Vents.................................................... CLEAR OF ICE OR
SNOW
Pressurization Static Port..................................... CLEAR OF ICE
In case of deice/anti-ice fluid application is necessary, perform
″AIRPLANE ANTI-ICING/DEICING FLUID APPLICATION WITH
ENGINES/APU RUNNING″.
AOM-1502-016
LEAVING THE AIRPLANE - SECURING FOR COLD SOAK OR AN
EXTENDED PERIOD
SLAT/FLAP............................................................. UP
CONTINUED...
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REVISION 23
Suppl Procedures Environmental
Page 21
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
3-75
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Page 22
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
Pitch Trim................................................................ FULL DOWN
Wheel Chocks......................................................... CHECK IN PLACE
Emergency/Parking Brakes.................................... AS REQUIRED
Protective Covers.................................................... CHECK
INSTALLED
Water and Waste System....................................... CHECK DRAINED
Batteries.................................................................. CHECK REMOVED
Doors....................................................................... CHECK CLOSED
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
LIGHTNING STRIKE
Even though the airplane is adequately protected against lightning strike
effects, operating procedures should be established in an attempt to
avoid such phenomenon.
In-flight lightning avoidance is closely associated with thunderstorm
avoidance. Therefore, avoid penetration of thunderstorms. Maintain
visual contact with thunderstorms during the daytime and lightning at
night. Check the radar for precipitation, review all available types of
weather information, examine other pilot reports and follow ATC
instructions. Even with a good weather report received and understood,
pay close attention to storms that develop rapidly along the route in a
given area which cannot be predicted. While enroute, continuously
update weather briefings through the use of radio contact and airborne
equipment for actual storm avoidance.
Remember that radar detects only liquid droplets, not the cloud itself.
Only rain suspended in the cloud will produce a radar echo, which may
lead to occasional encounters with hail and lightning.
If possible, circumnavigate the detected thundercloud or area by 25
miles or more when traffic conditions permit.
Be aware that lightning can strike an airplane miles away from the
extreme side of a developed thunderstorm. Reports of airplane receiving
strikes in clear air at 25 NM or more from the nearest storm are
common.
AOM-1502-016
The following paragraphs summarize the conditions in which strikes are
most common:
Meteorological conditions: incident reports show that an airplane must
be within or beneath a cloud to receive a strike, or in or near regions of
precipitation. Incident reports show that in over 80% of the strikes, the
airplane was within a cloud and experiencing some precipitation and
turbulence. But other strikes may occur in a cloud where there is no
precipitation nearby, in clear air reasonably distant from a thundercloud,
during snowstorms and in clouds over erupting volcanoes. Flight through
or in the vicinity of a cold front, warm front, stationary front, unstable air
or squall lines increases the probability of lightning strikes. Incident
reports also show that lightning strikes occur most commonly under light
or heavy turbulence conditions.
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 23
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Flight regime: Takeoff, climb, level flight, descent or approach.
– Altitude: strikes are more common between 5000 ft and 20000 ft,
but may occur at virtually all flight altitudes. Lightning strike
incidents at lower altitudes are far more frequent since at higher
altitudes airplanes can divert around thunderclouds with greater
ease.
– Outside air temperature: most strike incidents have occurred
when the airplane is flying in temperatures near or at freezing
level. Strikes may also occur at temperatures as high as 25°C, or
as low as - 45°C.
Metal airplanes produce a phenomenon called Faraday Cage effect,
which distributes electrical charges along the airframe in such a manner
that occupants and internal components will not receive the high current
that causes injury and damage. Internal components and systems have
also special protections against side effects of the lightning strike.
Direct effects which result from a lightning strike may be:
– Pit marks often seen along the fuselage or holes in the trailing
edge of wing and tail tips.
– Melting of rivets.
– Puncturing of nonmetallic structures.
– Puncturing and de-lamination of composites.
– Slight deformation of metal skins and structure.
– Welding or roughening of moveable hinges and bearings.
– Damage to other parts that may conduct lightning current other
than the airframe, such as bonding or diverted straps and pitot
tubes.
Effects caused by the flash-induced electromagnetic field and the
increase of the voltage due to the current at the airplane structure are
defined as indirect effects and may be:
– Interruption of instruments and navigation equipment.
– Damage to electronic and electrical equipment.
– Popping of circuit breakers.
– Engine flame-out.
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
– Loss of electrical power.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Report the lightning strike to maintenance personnel, by filling out the
LIGHTNING STRIKE INCIDENT REPORT form.
AOM-1502-016
Make sure that maintenance proceed is in accordance with AMM MPP
05-50-01/ 601 before flying the airplane again.
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 25
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
EMB −190 LIGHTN I N G STRIKE INCIDENT REPORT
Part I (to be com pleted by flight crew)
Conditions at tim e of strike:
·
·
·
·
Operator:
Date of incident:
ACFT S/N:
Flight no.:
Route: From
To:
·
Flight phase:
·
Other:
W eather: Cloud type % Cover Ceiling (ft) Top at (ft) OAT (°C)
Altitude:
ft
Approach
Rain
·
·
Sleet
Airspeed:
Clim b
Hail
kt
Level Flight
Snow
W as St. Elm o’s fire visible before strike?
None
Yes
No
Any effects on:
Electrical power system :
Flight controls:
Engine:
Avionics:
Other (describe):
Any effects on personnel, such as: Flash blindness:
Electrical shock:
Part I com pleted by:
EM170AOM030012A.DGN
·
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
EMB-190 LIGHTNING STRIKE INCIDENT REPORT
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
LIGHTNING STRIKE PROCEDURE
IN-FLIGHT OPERATIONS
IF A LIGHTNING STRIKE IS LIKELY TO OCCUR
Indication of imminent lightning strike event:
– Buildup of static discharge which causes interference on ADF
indicators or noise in communication receivers.
– Elmo’s Fire, which is visible at night as small electrical discharges
running across the windshields and sparking on the wings.
Penetration in the Thunderstorm............................ AVOID
Visual Contact with Thunderstorm and Lightning... MAINTAIN
Weather Radar........................................................ CHECK FOR
PRECIPITATION
NOTE: Remember that radar detects only liquid droplets, not the
cloud itself.
Thundercloud Detected........................................... CIRCUMNAVIGATE
Circumnavigate the detected thundercloud or area at 25 miles or
more when traffic conditions permit.
All Cockpit Lights.................................................... ON/FULL
BRIGHTNESS
Sunglasses.............................................................. CONSIDER WEAR
Consider wearing sunglasses to protect your eyes from the flash or
have one pilot keep eyes downward.
IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING
Apply the associated emergency/abnormal procedure if any failure arises
after a lightning strike. If the situation is under control after a lightning
strike, apply the following procedure to ascertain whether the flight may
proceed safely.
Altitude.................................................................. MAINTAIN
If not required by performance, obstacle clearance or operational
contingencies, stop climbing during airplane check.
Circuit Breakers.................................................... CHECK
AOM-1502-016
Navigation Systems.............................................. CHECK
CONTINUED...
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REVISION 23
Suppl Procedures Environmental
Page 27
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Check magnetic compass and heading system for normal indications.
Report on the LIGHTNING STRIKE INCIDENT REPORT the
difference between the magnetic compass and the heading indication
on PFDs.
Engine Indication.................................................. CHECK
Check engine for normal indications. In case of engine shutdown, the
flight crew must analyze the circumstances of the event and consider
an engine airstart.
Pressurization....................................................... CHECK
Check for no evidences of pressurization leaks.
Flight Controls....................................................... CHECK
Check all flight controls for freedom of movement. Verify that
slats/flaps and speed brakes are working properly.
Fuel System.......................................................... CHECK
Check fuel system for normal operation. Monitor fuel remaining and
fuel consumption to ascertain that no fuel leak exists.
All Other Airplane Systems................................... CHECK
Check for EICAS messages and airplane instruments following a
panel scan sequence to ascertain that safety of flight prevails.
Communication Systems...................................... CHECK
NOTE: Consider discontinuing the flight and land at the nearest
suitable airport if any unsafe condition is revealed after
checking systems operation.
AFTER LANDING
Lightning Strike Event............................................. REPORT TO
MAINTENANCE
Report any effects on the airplane systems. Report the lightning strike
to the maintenance personnel by filling out the LIGHTNING STRIKE
INCIDENT REPORT form.
ON GROUND OPERATIONS
ON THE GROUND
IF THE AIRPLANE HAS BEEN HIT BY LIGHTNING
Holes, Punctures, Discoloration and Delamination
throughout the Whole Airframe............................. CHECK
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
External safety inspection
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Loose, Melted or Missing Rivets............................ VERIFY
Verify that there are no loose, melted or missing rivets.
Static Dischargers................................................... NUMBER AND
CONDITION
Verify 3 static dischargers on each aileron and 6 static dischargers on
each winglet.
E170/175: Verify 4 Static Dischargers on the rudder, 4 on each
elevator and 1 on vertical stabilizer.
E190/195: Verify 4 Static Dischargers on the rudder, 3 on each
elevator, 3 on each horizontal stabilizer and 1 on vertical stabilizer.
Refer to CDL for dispatch with missing items.
Landing and Taxi Lights.......................................... CONDITION
Clean and undamaged.
Wing Inspection, Landing and Taxi Lights.............. CONDITION
Clean and undamaged.
Navigation, Strobe and Red Beacon Lights........... CONDITION
Clean and undamaged.
Smart Probes/TAT Sensor/Ice Detectors................ CHECK
Verify condition with no obstructions, covers or damage.
Radome................................................................... CHECK
Antennas................................................................. CONDITION
Maintenance procedure is in accordance with AMM
MPP 05-50-01/601 before the airplane next flight.. CONFIRM
TURBULENT AIR PENETRATION
If possible, flight through severe turbulence must be avoided. If not
possible, the following procedure is recommended for turbulent air
penetration.
AOM-1502-016
The recommended turbulent air penetration target speeds are:
Airspeed.................................................................. ADJUST
Below 10000 ft........................................................ MAX 250 KIAS
At or above 10000 ft............................................... MAX
270 KIAS/0.76 M
WHICHEVER IS
LOWER
CONTINUED...
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REVISION 23
Suppl Procedures Environmental
Page 29
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Severe turbulence causes large and often rapid variations in indicated
airspeed. Do not chase the airspeed.
NOTE: – Do not extend flaps except for approach and landing.
– Large altitude variations are possible in severe turbulence,
do not chase altitude. Let both altitude and airspeed vary
and maintain attitude.
– If severe turbulence cannot be avoided disconnect
Autothrottle and make an initial thrust setting for the target
airspeed. Change thrust setting only in case of unacceptable
airspeed variation.
– Maintain wings level and pitch attitude. Use attitude indicator
as the primary instrument. Do not use sudden large control
inputs.
– Maintain control of the airplane with the elevators. After
establishing the trim setting for penetration speed, do not
change pitch trim.
VOLCANIC ASH
Flight in areas of known volcanic activity must be avoided. This is
particularly crucial while flying at night or in daytime with instrument
meteorological conditions when volcanic dust may not be visible. When
a flight is planned into an area with a known potential for volcanic
activity, it is recommended that all NOTAMs and air traffic control
directives be reviewed for current status of volcanic activity. If volcanic
activity is reported, the planned flight should remain well clear of the
area and, if possible, stay on the upwind side of the volcanic dust.
The airplane’s weather radar is not capable of detecting volcanic
ash/dust clouds and is therefore not reliable under these circumstances.
The presence of volcanic ash/dust may be indicated by:
– Smoke of dust appearing inside the airplane;
– Odor similar to electrical smoke;
– Engine malfunctions such as power loss, engine stalls, increasing
ITT, fluctuating engine rpm, etc;
– At night, Saint Elmo’s fire/static discharges may be observed
around the windshield or windows;
CONTINUED...
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Suppl Procedures Environmental
REVISION 23
AOM-1502-016
– Orange glow from engine inlets.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
Flight into volcanic ash/dust clouds can result in the degradation of
airplane and engine performance. The adverse effects cause by volcanic
ash/dust encounters may be:
– Rapid erosion and damage to the internal engine components;
– Ash/dust build-up and blockage of the guide vanes and cooling
holes, which may cause surge, loss of thrust and/or high ITT;
– Ash/dust blockage of the pitot system, resulting in unreliable
airspeed indications;
– The abrasive properties of volcanic material may cause serious
damage to the engines, wing and tail leading edge surfaces,
windshields, landing lights, etc;
AOM-1502-016
– Windshield and windows may become opaque, reducing visibility.
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 31
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
ON GROUND OPERATIONS
The following recommendations apply to starting and operating engines
on airports where volcanic ash has fallen and ground contamination is
present:
– When the airplane is parked install engine covers or reposition
the aircraft to limit blowing ash accumulation from wind and jet
blasts from other airplane;
– During preflight, check that the engine inlet and exhaust areas
have been cleared of volcanic ash;
– Check that all volcanic ash has been cleaned away from the area
within 14 ft of the engine inlets;
– Use APU for engine starting only, not for air conditioning.
– Prior to starting, dry motor the engine for 90 s in order to blow out
any ash that may have entered the engine bypass duct area;
– Use minimum required thrust for breakaway and taxi; therefore
single engine taxi must be avoided.
– Keep bleed valves closed during taxi. Limit exposure to
contaminated surfaces by selecting alternate cleaner taxi routes
if available;
– Avoid static engine operation above idle;
– Be aware of loose ash being blown by the exhaust wake of other
aircraft. Maintain adequate ground separation and allow for dust
to set on the runway before starting the takeoff roll;
– Use a rolling takeoff technique. Avoid setting high thrust at low
airspeeds;
CONTINUED...
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Page 32
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
– After landing at an airport contaminated with volcanic ash,
minimize the use of reverse thrust to prevent any recirculation
ingestion.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
IN FLIGHT OPERATIONS
Flight operations in volcanic ash are extremely hazardous and must be
avoided. However, volcanic ash/dust clouds may sometimes extend for
hundreds of miles, reaching altitudes above 60000 ft and an encounter
may be unavoidable.
In case of an inadvertent encounter, proceed as follows:
Volcanic Ash Area................................................... EXIT/AVOID
Consider performing a 180° turn. Due to the dimensions of the ash
clouds, a 180° turn could be the fastest way to exit an ash cloud.
Crew Oxygen Masks (if necessary)........................ DON, 100%
If a significant amount of volcanic ash fills the cockpit or if there is a
strong smell of sulphur, don an oxygen mask and select 100%.
Ignition Selectors.................................................... OVRD
Autothrottle.............................................................. DISENGAGE
The autothrottle must be kept disconnected to prevent thrust increase
due to smart probes contamination.
Ice Protection Mode Selector................................. ON
This action will increase bleed air extraction from the engines and
further improve the engine stall margin.
Thrust Levers (If altitude permits)........................... IDLE
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE
FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Recirculation Button................................................ PUSH OUT
Airspeed.................................................................. MONITOR
Monitor airspeed for any abnormal indication. If necessary perform the
Unreliable Airspeed procedure.
ITT........................................................................... MONITOR
NOTE: If the ITT is still increasing even with the thrust levers in idle:
AOM-1502-016
Affected Engine.................................................... Shutdown
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 33
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
If engine is shutdown or flames-out, restart the engine (refer to Quick
Reference Handbook) once it has cooled down. If engine fails to start,
repeated attempts should be made immediately.
NOTE: A successful start may not be possible until the airplane is
clear of the volcanic ash/dust, and the airspeed and altitude
is within the airstart envelope. The engines may accelerate
slowly to idle at high altitudes and this could be interpreted as
a failure to start or as an engine malfunction.
3-75
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Page 34
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
After exiting the area of volcanic ash/dust cloud and with the engine(s)
restarted, restore systems to normal operation. Inform ATC of the
encounter.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
SANDSTORM OPERATION
A Sandstorm Operation is characterized when the airplane:
– Flies through a sandstorm.
– Lands or takes off during a sandstorm.
– Operates on ground (towing, taxiing, parking) during a sandstorm.
– Operates the APU or the Packs in during a sandstorm.
In many deserts, the prevailing wind blows steadily from one cardinal
direction for most of the year, and eventually switches to another
direction for the remaining months. The equinoctial gales raise huge
sandstorms that rise to several thousand feet and may last for several
days. Gales and sandstorms in the winter months may be very cold.
Desert winds can be very destructive to large and relatively light items
attached to the airplane, such as antennas and cover caps.
Especially in the deserts, dust and sand represent serious danger to
equipment, since it is almost impossible to avoid particles settling on
moving parts.
Sand mixed with oil forms an abrasive and corrosive paste. Therefore,
fuselage areas must be routinely checked and cleaned to prevent an
undesirable OEW increase and payload reduction.
Landing gear and flaps/slats are critical items for sand accumulation.
Static electricity is also relevant and poses a danger in the desert. Poor
grounding conditions may cause fire and damage circuit boards and
other electronic equipment.
Sandstorms are difficult to forecast and are likely to occur and stop
suddenly.
AOM-1502-016
During a severe sandstorm, sand permeates everything and
compromises visibility, which may become as low as 30 ft in the worst
cases. Besides, blowing sand damages the wings leading edges and
other airplane moving parts, especially the engine intakes. Rubber
components such as gaskets and seals may become fragile and oil
leaks may be more frequent. The effects of a sandstorm are very similar
to those identified for Volcanic Ash.
CONTINUED...
3-75
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REVISION 23
Suppl Procedures Environmental
Page 35
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
If a sandstorm occurs when the airplane is on ground, with the applicable
protective covers installed, and if there is no dust or sand behind the
covers, it is not necessary to inspect the respective components or
systems, as described in the Airplane Maintenance Manual.
The critical items to be considered after the airplane has been exposed
to a sandstorm are:
– Airplane external cleaning
– Airplane structure
– External lights and sensors
– Flight control system (actuators, tracks, rollers and cables)
– Forward and middle avionics compartments
– Forward and after cargo compartments
– Airplane interior
– Fuel system
– APU
– Air management system
– Hydraulic system
– Engines
CRITICAL AIRPLANE SYSTEMS
AVIONICS
It is recommended to protect computers from exposure to sand or dust
by using plastic bags. Compressed air can be used to clean keyboards
and other computer systems components.
Keep the Air Data Smart Probes (ADSP) protected whenever possible to
avoid contamination. During airplane inspection give special attention to
the probes and contact the maintenance team if necessary.
ENGINE
The fan by itself separates a significant amount of sand and dust away
CONTINUED...
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Page 36
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
In the event of a sandstorm occurs, it is not recommended to increase
thrust. Sand or dust entering the engines with high airspeed will cause
damage to internal components and affect the engines performance.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
from the compressor via the bypass duct, but high abrasive particles will
strike the spinner, fan blades, vanes and splitter, leading to erosion of
these items.
Solid particles that are not separated through the fan will enter the
compressor chamber, strike the compressor blades or vanes, leading to
erosion of these items.
Sand or dust under entering the engines will be under high temperatures,
with potential to melt and choke the airflow, causing a backpressure
increase and consequently decreasing the engines performance.
Besides, if damaged or choked, the fuel injectors might lead to an
engine shutoff.
Exposure to sandstorms may lead the airfoils to change shape over time
and therefore their aerodynamic efficiency will drop. Fan blade
deterioration will also reduce thrust, since about 3/5 of an engine’s total
thrust is generated through the FAN.
Thus, when regularly operating in sandstorm condition, is recommended
to wash the engines frequently to prevent a buildup of sand and dust.
This will help minimize the possibility of inlet air and lubricating oil
contamination and permit normal engine cooling.
Active monitoring of the engines performance trends is also very
important.
POWER PLANT
Considering operations of high bypass turbofan engines in desert
environments, high concentrations of dust and sand in the airflow are
the most impacting factors. Both sand and dust are considered erosive
FOD that can significantly reduce the lifetime of all of the engines’
moving parts.
AIR MANAGEMENT SYSTEM
AOM-1502-016
Bleed air comes from the engines and APU, passes through valves,
ducts, filters, heat exchangers, turbines and electronic components, to
supply air to the Air Conditioning, Pressurization and Anti-Ice systems. If
the air ingested by the engines is humid and/or contaminated with dust
and/or sand, it may damage AMS components and demand more
frequent maintenance actions to prevent failures.
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 37
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
SERVICING PROCEDURES
If the airport has records of sandstorm occurrences, the airplane and
fuel vehicles have to be well secured on ground at all the times to avoid
damage. Securing of vehicles and equipment should be accomplished
in accordance with appropriate procedures specified in the respective
maintenance manuals.
When cleaning any surface of the airplane contaminated with dust or
sand, do not rub the surface. Dust and sand are very abrasive.
In order to prevent accumulation of dust and sand, covers and shields
must be properly installed to ensure a good fit.
In addition to the normal servicing requirements and procedures referred
in the AMM give special attention to the following:
– When practical, position the airplane heading into the wind.
– Maintain full engine oil tank to provide maximum heat absorption
capability and help prevent excessive oil temperatures.
– Prior to servicing ensure that filler openings and caps are clean
before opening and closing servicing caps. Clean up fluid spills
as they occur during servicing.
– Verify that all engine inlet air ducts are free of sand. Use a
lint-free cloth to remove any accumulation.
OPERATIONAL PROCEDURES
PRE-FLIGHT INSPECTION
Verify that no accumulation of sand exists in the engines inlet. Use a
lint-free cloth to remove any accumulated sand.
POWER UP
– If available, prefer using a GPU for the airplane power up.
– Minimize thrust for crossbleed starts.
– Apply thrust just high enough for adequate manifold pressure.
CONTINUED...
3-75
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Page 38
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
– Consider location for minimum FOD ingestion prior to crossbleed
start.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
TAXI
– Avoid engine overhanging unpaved surfaces.
– If possible, leave engines at idle.
– Minimize thrust assist from outboard engine in 180° turn,
particularly if outboard engine overhangs unpaved surfaces.
– Minimize breakaway thrust.
– If possible, apply less than 40% N1.
– Minimize taxi thrust.
– Avoid allowing airplane to come to complete stop.
– Avoid taxing closely behind other airplane where FOD may be
blown.
TAKEOFF
– If possible, accomplish rolling takeoffs. Initial 30 KIAS taxi speed
before applying thrust eliminates vortices formed at typical takeoff
thrust settings.
– Whenever possible, take off with FLAP 4 in order to reduce the
airplane ground run and the engines sand/dust ingestion.
– If allowed, extend the flaps shortly before initiating the takeoff
procedure. This will reduce sand/dust accumulation on the
flap/slats mechanisms.
– Minimize breakaway thrust.
– Use derated thrust settings whenever practical. This will help
reduce the engines degradation.
IN-FLIGHT
– Avoid airborne sand whenever possible.
– Consider reducing thrust to maintain ITT as low as possible.
LANDING AND TAXING
AOM-1502-016
– Avoid using reverse thrust on dry runways.
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 39
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
ENGINE SHUTDOWN
If ground power is supplied to the airplane after engine shutdown, turn
off all electrical equipment which is not required. This practice will
reduce the heat generated unnecessarily and will substantially prolong
the service life of the equipment.
AFTER SHUTDOWN
– Install covers and shields.
– Inspect for evidence of fluid leaks that might accumulate sand.
– Clean the area appropriately and try to eliminate source of fluid
leak.
EXTERNAL PNEUMATIC POWER SOURCE AND AIR
CONDITIONING GROUND CART UTILIZATION
The contaminated air ingested by the engines can result in malfunctions
and operational problems due to degradation or malfunction of AMS
components.
Therefore, when an external pneumatic power source or an air
conditioning ground cart is available, it is recommended to use these
alternative sources to power up the engines or to condition the cabin
temperature following the Ground Servicing section of this manual.
The external pneumatic power source provides pressurized air that is
used to power up the engines, eliminating the need to keep APU or
engines running during servicing and reducing the demand for bleed air.
The air conditioning ground cart provides clean, pressurized and cool air
that is used to maintain the cabin air temperature at the desired level
without using the PACKs. It also reduces the use of the APU and bleed
air demand during servicing.
BIRD OR HAIL STRIKE
The inspection must be conducted by a flight crew member who has
been properly trained to perform the procedure on behalf of the
maintenance personnel.
CONTINUED...
3-75
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Page 40
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
This procedure contains the information to perform an external inspection
of the airplane structure after a suspected bird or hail strike.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
The information contained herein do not constitute an operational
approval. If Local Regulatory Authority approval is required, it should be
obtained by the Operator.
BIRD OR HAIL STRIKE INSPECTION PROCEDURE
NO-GO FINDINGS
During the inspection, the occurrence of the following items requires
maintenance intervention:
– Stains of blood and other bird remains that can not be cleaned
from the airplane surfaces,
– Evidence of the ingress of bird remains into the engine, openings
or intakes regardless if they can be cleaned,
– Any obvious damages such as:
– Buckling, wrinkles, cracks, dents, nicks, and damaged paint
finish,
– Bent, twisted or loosened parts,
– Loose or pulled fasteners,
– Missing or pulled apart structures,
– Hydraulic line leakage, and
– General misalignment of the structure and assemblies.
– Any technical malfunction that could be related to a Bird or Hail
strike occurrence.
NOTE: If bad smell through the bleeding system or abnormal engine
parameters are noticed anytime after the suspected bird or
hail strike, maintenance intervention is required.
PREPARING FOR THE INSPECTION
External Lights...................................................... AS REQUIRED
Emergency/Parking Brake.................................... ON
Visual/Access Blockers......................................... REMOVE
AOM-1502-016
Remove any objects that may block access to the airplane and its
parts such as ground support equipment and ice and snow
accumulation.
SLAT/FLAP........................................................... FULL
Flashlight............................................................... AS REQUIRED
CONTINUED...
3-75
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures Environmental
Page 41
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
BIRD OR HAIL STRIKE INSPECTION
WARNING: WHILE CONDUCTING THE INSPECTION, BE AWARE
OF MOVING VEHICLES IN THE AIRPLANE
SURROUNDINGS.
During the inspection, wipe any detected bird remains from the airplane
surfaces with detergent.
WARNING: TO AVOID BIOLOGICAL HAZARDS, LOCAL
REGULATIONS MUST BE FOLLOWED IN DEALING
AND DISCARDING ANIMAL REMAINS.
Perform the inspection as follows:
Nose Section/Fwd Fuselage................................. CHECK
Verify radome, windshields, direct vision window, fuselage skin,
probes, sensors, and detectors.
Antennas............................................................... CHECK
Verify upper and lower fuselage.
Landing Gear (NLG and MLG)............................. CHECK
Verify doors, components, assembly, and compartments.
Wings.................................................................... CHECK
Verify wing leading edges, slats, flap surfaces, flap track fairings,
winglet/wingtip, spoilers, ailerons, wing-to-fuselage fairing, and wing
lower skin.
Horizontal/Vertical Stabilizers............................... CHECK
Verify leading edges, surface and attachments, including rudder and
elevators.
Engines................................................................. CHECK
Verify pylon fairings, engine nacelle, reverser doors, and exhaust
nozzle, air inlet module (inlet cowl, lipskin, inner and outer barrels),
spinner, fan module (leading and trailing edges), OGVs and booster
inlets.
If any item listed as a NO-GO FINDING is detected during the inspection,
no operation is allowed and maintenance intervention is required.
Otherwise, if no item is detected, the airplane can return to service.
3-75
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Page 42
Suppl Procedures Environmental
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
COMMUNICATION MANAGEMENT FUNCTION
OPERATION
Specific operational procedures are required for the ACARS function
use in accordance with CFR 14, Part 25, Subpart G - Operating
Limitations and Information, § 25.1529,§ 25.1581, § 25.1583 and §
25.1585.
AOM-1502-016
DO-296 - Safety Requirements for Aeronautical Operational Control
(AOC) Datalink Messages provides a guideline for hazard identification
and risk reduction strategies related to ACARS operation.
3-76
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Suppl Procedures Communication
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
3-76
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Page 2
Suppl Procedures Communication
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
ALTIMETERS MISCOMPARE TOLERANCES
The Air Data System (ADS) relies on total of four Air Data Smart Probes
(ADSPs) and two Total Air Temperature probes (TATs) to determine air
total pressure, static pressure and total temperature. Three Air Data
Applications (ADAs) compute these informations to provide air data to
PFDs and other airplane systems. IESS (Integrated Electronic Standby
System) performs both the functions of computing air information and
presenting air data to flight crew.
There are four ADS, which interact with flight crew. In normal operation,
ADS 1 provides information to captain’s PFD, ADS 2 provides information
to co-pilot’s PFD and ADS 3 is the backup source for both PFDs
whereas ADS 4 is the IESS.
Differences between pilot and co-pilot altitude readings may occur due
to a number of reasons. Altitude, airspeed, airplane configuration and
the ADSPs locations influence the altitude reading miscompare. As long
as the miscompare is within a certain tolerance, it is acceptable.
To verify if altimeter difference is within tolerance, the flight crew should
proceed as follows:
Altitude.................................................................... STABILIZE
Maintain variation within ± 50 ft.
Air Speed................................................................ STABILIZE
Maintain variation within ± 5 kt.
AOM-1502-016
Wait a minimum of 15 s in straight and leveled flight, preferably with
Autopilot engaged, to compare the difference between altitudes using
the following table:
CONTINUED...
3-80
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Flight
Instruments
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MAXIMUM DIFFERENCE
BETWEEN ALTITUDES [1]
ADS 1 to ADS 2
ADS 1 to ADS 3/IESS [2]
ADS 2 to ADS 3/IESS [3]
50 ft
120 ft
180 ft
AIRPLANE ALTITUDE
-2000 ft up to 10000 ft
10000 ft up to 20000 ft
20000 ft up to 41000 ft
1. These are comparative, not absolute values.
2. Message ADS 3 (4) SLIPCOMP FAIL must not be displayed.
3. ADS 3 and IESS use the same pressure sensors. Comparison
between them is not applicable.
If a difference above the tolerance is noticed, report to the maintenance
personnel.
PERFORMANCE BASED NAVIGATION
INTRODUCTION
!Pre-mod MAU load 27.1
The material contain herein is a guidance to perform PBN operation. It
does not consider AC-90-101 or AMC-20-26 which deal with RNP AR
operation. For RNP AR operation, refer to GP-3801 – RNP AR Operation.
"
In addition to the guidance of this section, the operator must continue to
ensure they comply with the general operating requirements; checking
Notices to Airmen (NOTAMS), availability of Navigational Aids (NAVAID),
airworthiness of airplane systems, and flight crew qualification.
NAVIGATION DATA VALIDATION
NOTE: If the AIRAC cycle will change during the flight, the locations
of the waypoints used to define routes and procedures must
be verified with current navigational charts.
CONTINUED...
3-80
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Page 2
Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
The navigation database must be obtained by a supplier complying with
AC 20-153 or equivalent and is expected to be current for the duration of
the flight.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
GENERAL GUIDANCE
While operating on RNP segments, pilots are encouraged to use flight
director and/or autopilot in lateral navigation mode and vertical navigation
mode.
RNP approach procedures require flight crew monitoring of lateral and
vertical track deviations on the PFD to ensure the airplane remains
within the bounds defined by the procedure. Since the lateral scale and
CDI are automatically changed by the RNP value set on FMS, pilots
must ensure the RNP set is suitable for each of the various segments of
the procedure.
All pilots are expected to maintain centerlines, as depicted by onboard
lateral deviation indicators and/or flight guidance during all RNP
operations, unless authorized to deviate by ATC or under emergency
conditions. For normal operations, cross-track error/deviation should be
limited to half the navigation accuracy associated with the procedure
(i.e., 0.5 NM for RNP 1). Brief deviations from this standard (e.g.,
overshoots or undershoots) during and immediately after turns, up to a
maximum of one times the navigation accuracy (i.e., 1.0 NM for RNP 1),
are allowable.
PRIOR TO FLIGHT
Airplane minimum configuration........................... CHECK
Check the airplane configuration complies with the applicable list
below:
!Pre-mod MAU load 27.1
– 1 FMS.
– 1 GPS.
– 1 IRU.
– 1 MCDU.
– 4 Display units.
– 2 RVSM Compliant Air Data Systems.
– 1 Flight Director.
– 1 VOR.
AOM-1502-016
"
CONTINUED...
3-80
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Suppl Procedures - Flight
Instruments
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!Pre-mod MAU load 27.1
FMS Position........................................................ INITIALIZE
"
Flight Plan............................................................. ACTIVATE
Procedure ............................................................ CONFIRM
Crew must confirm that the correct procedure has been selected by
comparing the FMS waypoints with the approach chart, and ensure
the reasonableness of track angles and distances, and other
parameters that can be altered, such as altitude and speed
constraints.
NOTE: – The procedure may subsequently be modified through the
insertion or deletion of specific waypoints in response to
ATC clearances. The manual entry or creation of new
waypoints, by manual entry of latitude and longitude or
rho/theta values is not permitted. Additionally, pilots must
not change any database waypoint type from a fly-by to a
fly-over or vice versa.
– Differences of 3° or less between navigation information
on the charts and the PFDs heading are acceptable.
After an RTO, the performance init must be checked.
RNP predictive performance capability................ CONFIRM
AVAILABLE
The performance capability may be checked from an offline station, or
with the airplane own capability. If using the airplane capability, insert
the appropriate GPS NOTAMS to allow for an accurate predictive
RAIM.
NOTAM NAVAIDS................................................. INSERT
Insert the appropriate NAVAIDS in accordance with NOTAMs.
NOTE: For RNP 1 with approval based on DME/DME, critical DME
facilities (listed on the approach chart) must be operative.
NAV Database...................................................... VERIFY
CURRENCY
PFD NAV Source.................................................. SELECT FMS
CONTINUED...
3-80
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Page 4
Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
Verify that the Navigation Data Base (NDB) is current for the duration
of the flight.
Takeoff Page......................................................... SET/CONFIRM
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Speed Selector Knob............................................ AS REQUIRED
LNAV..................................................................... AS REQUIRED
VNAV.................................................................... AS REQUIRED
DEPARTURE, ROUTE AND ARRIVAL
Navigation Sensor (Progress Page on MCDU).... CHECK
If DME-DME or IRS is the current navigation sensor, a manual runway
position update needs to be performed by the crew. Ensure the
runway for departure is selected on the FMS and use the LSK 2R on
the POS INIT page to update FMS position when aligned for
departure.
Track deviation...................................................... MONITOR
The deviation can be monitored through the lateral deviation scale on
CDI and PFD or cross track error on MFD MAP page. Lateral deviation
should not exceed half of the RNP value. Slight deviations up to
1xRNP during or immediately after turns are allowable.
MFD
FMS1
36 O
ZUN
55.6 NM
23 MIN
5
PUMPS
N
33
3O
GUP44
15 SAT ^C
25 TAT ^C
3OO TAS KTS
DME1
LAX
65.3 NM
2O MIN
3
6
GUP
AOM-1502-016
5 A
WX/R/T S
STAB TGT
LX
1OO
1OO
1
EM170AOM980132B.DGN
WEATHER
E
W
ZUN
O.O5 L
PROGRESS
NEXT
DEST
WPT
ZUN
GUP
DIST ETE FUEL
55.6 O1+32 11.4
95 O2+52 1O.4
CONTINUED...
3-80
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 5
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
1 - Cross Track Error.
NOTE: If ATC issues a heading assignment taking the airplane off a
procedure, the crew should not modify the primary flight plan,
until a clearance is received to rejoin the route or the
controller confirms a new route clearance. The specified
accuracy requirement does not apply when the airplane is
not on the published RNP 1 procedure.
APPROACH
Track deviation...................................................... MONITOR
CONTINUED...
3-80
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Page 6
Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
The deviation can be monitored through the vertical and lateral scales
and CDI on PFD. Vertical deviation must not exceed 100 ft high or 50
ft low during the approach segment. Lateral deviation must not exceed
the half RNP value at any time during the approach. If the deviation
exceeds the limits perform a missed approach.
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MAIN PANEL
SPD T
LNAV ALT
AP
AT
21O
O6OOO
731O
24O
2O
2O
1O
1O
VTA
1
2 1O
9
776O
1
2
75OO
FS
17O
1O
1O
2O
2O
4
RA
1O13 HPA
2OO
HDG
DTK
21O
3O2
21O
FMS2
YOCUL
S
21
2
DME2
29.7 NM
MIN
RNP 1.OO
TERM
3O
12
W
3
E
33
N
3
VHF1
118 5O
119 25
O
O
24
15
2.O NM
O MIN
1
8O
18O
GSPD
235 KT
2
1
8OOO
EM170AOM980131B.DGN
19O
4
NAV2
116.2O
114.8O
6
1 - Vertical deviation scale.
2 - Lateral deviation scale.
3 - CDI Lateral deviation scale.
AOM-1502-016
In the horizontal deviation scale, full-scale deflection (two dots)
corresponds to 1xRNP lateral (both on the CDI and PFD).
CONTINUED...
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 7
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
The vertical deviation scale is 250 ft/Dot on terminal. Upon reaching 2
NM from the FAF, the scale changes to 75 ft/Dot during approach.
At the IAF:
Altimeters.............................................................. SET
Obtain and set a current, local altimeter setting. If a current, local
altimeter setting is not available, do not start the approach.
NOTE: The use of a remote altimeter setting is not authorized.
Altimeters.............................................................. COMPARE
When crossing a known waypoint on the approach procedure,
crosscheck the primary barometric altimeters against one another.
The difference between the altimeter indications must not exceed 100
ft. If the difference exceeds 100 ft, abandon the approach and begin a
missed approach.
2 NM before the FAF:
APPR Annunciation.............................................. CHECK
The annunciation indicates that the EPU value is inside the RNP
value and the GPS is functional.
PFD
HDG
DTK
FMS2
JEXOT
S
21
DME2
29.7 NM
MIN
RNP O.3O
APPR
3O
12
W
1
E
33
N
3
6
VHF1
118 5O
119 25
O
O
24
15
2.O NM
O MIN
3O2
21O
NAV2
116.2O
114.8O
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
21O
EM170AOM980133B.DGN
GSPD
235 KT
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
1 - APPR Annunciation.
MISSED APPROACH
TO/GA................................................................... PRESS
NOTE: The missed approach prompt is automatically activated and
displayed on the MCDU MISSED APPROACH page after
passing the initial approach fix (IAF) without pressing TO/GA
button.
The missed approach prompt only activates the lateral part of
the procedure, so the pilot is still responsible for selecting the
vertical navigation mode.
!Airplanes not equipped with Auto LNAV, Pre-mod MAU load 27.1
LNAV..................................................................... SELECT
The pilot flying must immediately re-select LNAV after the TO/GA and
follow the flight director’s guidance to ensure airplane compliance
with the procedure’s track.
"
!190/195 models, Pre-Mod MAU load 25.1.0.1
NOTE: When a go around is initiated (TO/GA button is pressed) far
away and GA mode on FMA is not active prior to 2 NM from
the FAF, the missed approach procedure will not be
automatically activated. To activate the missed approach in
the flight plan, the TO/GA button must be pressed again when
within 2 NM of the FAF. After pressing TO/GA a second time,
the NAV button must also be pressed again to re-engage
LNAV, guaranteeing the missed approach path will be correctly
followed.
"
ADVANCED FEATURES - VGP
The information below applies to the use of VGP during approach
operations.
AOM-1502-016
TEMPERATURE COMPENSATION
Due to the effect of nonstandard temperature on VGP operations,
temperature limits may apply to some procedures (temperature limits
presented in the notes section of the chart). By using the temperature
compensation function it is possible to disregard those limits, provided
the function is activated prior to commencing the approach.
Temperature compensation (if applicable)........... ACTIVATE
CONTINUED...
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 9
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
The temperature value used should be the current, local temperature
for the airport and runway of intended landing.
NOTE: Prior to applying temperature compensation, the flight crew
must coordinate its use with ATC. Failure to do so could
result in a loss of vertical separation with other traffic.
LOSS OF VGP
Should any system failure affect the VGP functionality, if a VNAV MDA
(DA) is in use, the crew must immediately revert to LNAV only MDA (DA)
or perform a go around.
ADVANCED FEATURES - RF LEGS
Radius to Fix Legs (RF Legs) are turn segments with constant radius
between to fixes. RF legs may appear on RNAV/RNP procedures during
the initial, intermediate and missed approach segments of instrument
approaches, RNP departure procedures and RNP STARS. RF legs are
not used in the final approach segment.
Additional requirements for RF legs are indicated in the charts, in the
notes section, or at the applicable initial approach fix for instrument
approaches. Common additional requirements are airspeed restrictions
during the legs that must be complied with.
ABNORMAL PROCEDURES
In case of loss of RNP capability, alternate airports or alternate non-RNP
procedures at the destination airport must be available.
LOSS OF SIGNAL IN SPACE
If at any time GNSS signal is lost, it will be annunciated to the crew as a
dual GPS failure (MCDU scratchpad messages), and the DGRAD PFD
annunciation will be displayed.
DEGRADED NAVIGATION
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
The navigation will be degraded whenever the EPU value is greater than
RNP or if the navigation sensors required for the approach are not
available on final approach (2 NM before the FAF).
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
PFD
GSPD
3OO KT
HDG
33O
MAG1
36 O
1O
PUMPS
N
FMS1
33
GUP44
CHR
O7:12
3
ZUN
55.6 NM
RNP 1.1O
GUP
DGRAD
ZUN
1
1OO
VHF1
118 5O
119 25
O.4 R
NAV1
119 1O
119 15
EM170AOM980135C.DGN
23 MIN
1 - DGRAD Annunciation.
The UNABLE RNP, GPS RAIM ABOVE LIMIT and GPS RAIM
UNAVAILABLE scratchpad message will also be displayed.
If the DGRAD annunciation is displayed:
AOM-1502-016
Select the non-affected FMS.
CONTINUED...
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 11
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
For single FMS installations or in case of both FMS are affected, use the
procedures from the following table:
Operation
Non-RNP Terminal or En-route
(including B-RNAV)
P-RNAV
RNP Terminal, En-route, Remote
Non-RNP (excluding GPS
required) Approach
RNP APCH, RNP 0.3 and GPS
required Approach
Non-RNP Remote
Required Action
Crosscheck FMS data with raw
data from VOR, DME, and NDB.
De-select sensor causing error, if
detectable.
Contact ATC, advise inability to
continue P-RNAV.
Contact ATC and advise inability
to continue RNP operations.
Use alternate source (VOR, NDB
or visual references) if available.
If not, declare Missed Approach.
If not visual, declare Missed
Approach.
Crosscheck FMS data with raw
data from GPS, IRS. De-select
error causing sensor, if
detectable.
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
NOTE: P-RNAV can also be read as RNAV 1.
B-RNAV can also be read as RNAV 5.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
FMS 1 (2) FAILURE
Select the cross-side FMS.
In case both FMS are unavailable, use the procedures from the following
table:
Operation
Non-RNP Terminal or En-route
B-RNAV, P-RNAV, or RNP
operations
Non-RNP (excluding GPS
required) Approach
RNP APCH, RNP 0.3 or GPS
required approach
Remote Operations
Required Action
Use alternate source (VOR, NDB,
DME).
Contact ATC and declare inability
to continue B-RNAV, P-RNAV, or
RNP operations.
Use alternate source, if available
(VOR, NDB or visual references).
If not available, declare missed
approach.
If not visual, declare Missed
Approach.
Contact ATC and declare loss of
long range navigation capability.
NOTE: P-RNAV can also be read as RNAV 1.
B-RNAV can also be read as RNAV 5.
AOM-1502-016
END
3-80
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 13
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
!Pre-mod MAU load 27.1
PRNAV OPERATIONS
The material contained herein is a guidance material prepared based on
TGL-10.
NOTE: To fly into an airspace designated as RNAV 1, is necessary to
comply with the deltas from TGL No. 10 to the criteria of the
RNAV 1 navigation specification.
The P-RNAV operations satisfies a required track keeping accuracy of
±1 NM for at least 95% of the flight time, and the automatic selection,
verification and, where appropriate, de-selection of navaids.
P-RNAV operations determine airplane position on the horizontal plane
using inputs from the following types of positioning sensors:
– Distance Measurement Equipment (DME) giving measurements
from two or more ground station (DME/DME).
– VHF Omni-directional Range (VOR) with a co-located DME
(VOR/DME), where it is identified as meeting the requirements of
the procedures.
– Global Navigation Satellite System (GNSS) GPS or GALILEO.
– Inertial Reference System (IRS), with automatic updating from
suitable radio based navigation equipment.
P-RNAV is used for departures, arrivals and approaches down to
(FAWP). The final APPR segment down to the RWY threshold and the
associated missed approach are not covered by P-RNAV procedures.
NOTE: The FMS VNAV and the FMS SPEED are not required for
P-RNAV.
LIMITATIONS
MINIMUM EQUIPMENT LIST
– 1 FMS.
FMS 1 (2) FAIL displayed on the EICAS.
– 1 FD.
– 1 DME.
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
FD FAULT displayed on the EICAS.
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– 1 VOR.
– 1 GPS.
NOTE: For procedures specified in the Aeronautical Information
Publication (AIP) as requiring dual P-RNAV, both FMS must be
operative at dispatch. If an FMS in-flight failure occurs, the
procedure must be discontinued.
The sensors status can be checked in FMS MAINTENANCE PAGE.
FMS 1 MAINTENANCE
2/3
FAILED SENSORS
IRS 1
IRS 2
DME 1
DME 2
1R
2L
2R
3L
3R
4L
4R
5L
5R
6L
SETUP
SENSOR HISTORY
EM170AOM030029A.DGN
1L
6R
FMS MAINTENANCE PAGE 2/3
GENERAL LIMITATIONS
– If GPS RAIM is annunciated as not available during any phase of
flight, the pilot must monitor FMS guidance data and crosscheck
with raw data from an alternate source (i.e. VOR, DME, or IRS).
AOM-1502-016
– Although the magnetic heading and track angle provided by the
IRS are available up to 73° latitude north and 60° latitude south,
the FMS uses the IRS as sensor in the range 72° 30.0’ latitude
north and 59° 30.0’ latitude south. The P-RNAV operation is
prohibited outside of the IRS FMS usable range.
CONTINUED...
3-80
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 15
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– The RNP-RNAV airworthiness approval has not accounted for
database accuracy or compatibility as defined per FAA AC
20-153.
– P-RNAV requires the use of the Flight Director.
– Prior to flight using FMS for IFR navigation any appropriate
ground facilities that are utilized by the procedures to be flown
must be verified as operational using an approved method.
– The Approved FMS Pilot’s Operating Manual or other approved
manual must be available to the flight crew. The Pilot’s Manual
must match the FMS software version installed in the airplane.
– The creation of new waypoints by manual entry into the RNAV
system by the flight crew is not permitted as it would invalidate
the affected P-RNAV procedure. Route modifications in the
terminal area may take the form of radar headings or ‘direct to’
clearances and the flight crew must be capable of reacting in a
timely fashion. This may include the insertion in the flight plan of
waypoints loaded from the database.
– The FMS software version NZ7.01 or later approved version
must be installed.
– P-RNAV operations with FMS software v7.0, v7.01 or v7.02 are
prohibited.
– When a GPS Only Approach is planned (GPS only in title or GPS
required by operational rules), prior to dispatch, the crew is
required to verify that the predictive RAIM at the destination ETA
is within the approach criteria. This information (RAIM
AVAILABLE), is displayed on the PREDICTIVE RAIM page on
the MCDU.
– The FMS Disable selection on MCDU Radio Tune NAV page is
prohibited.
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
– The pilot must ensure that the displayed guidance data from
non-usable stations is not used for navigation purposes by the
flight crew. The NOTAM function in the FMS does not always
inhibit tuning of a NOTAM selected station by the FMS when in
AUTO tune mode. Note that the FMS will not use NOTAM
selected station data for FMS position determination.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
NORMAL PROCEDURES
PRIOR TO FLIGHT
Verify NOTAM for the availability of the intended P-RNAV procedure.
Verify also if any navaid identified in the AIP as critical for the intended
P-RNAV procedure is unavailable.
FMS Identification................................................. VERIFY NAV DB
FMS Position........................................................ INITIALIZE
Flight Plan............................................................. ACTIVATE
At system initialization, the flight crew must confirm that the navigation
database is current and verify that the aircraft position has been
entered correctly. The active flight plan should be checked by
comparing the charts, SID or other applicable documents, with the
MFD MAP display and the MCDU. This includes confirmation of the
waypoint sequence, reasonableness of track angles and distances,
any altitude or speed constraints, and, where possible, which
waypoints are fly-by and which are fly-over. If required by a procedure,
a check will need to be made to confirm that updating will use a
specific navigation aid(s), or to confirm exclusion of a specific
navigation aid. A procedure shall not be used if doubt exists as to the
validity of the procedure in the navigation database.
FMS AUTOTUNE MODE...................................... ON
PFD NAVSource on PF Side................................ SELECT FMS
Contigency Procedure.......................................... REVIEW
AFTER TAKEOFF
LNAV..................................................................... SELECT
The LNAV mode can command bank angles up to 30°, which is
above the maximum allowable bank angle for OEI conditions below
the level OFF. Do not engage the LNAV mode until the airplane is
above the level off if the departure procedure may cause the airplane
to bank over the 15° limit.
AOM-1502-016
ARRIVAL
Verify NOTAM for the availability of the intended P-RNAV procedure.
Verify also if any navaid identified in the AIP as critical for the intended
P-RNAV procedure is unavailable.
Flight Plan............................................................. LOAD
At the desired flight plan loading, the flight crew must confirm that the
navigation database is current and verify that the aircraft position has
been entered correctly. The loaded procedure must be checked by
CONTINUED...
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 17
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
comparing the charts or other applicable documents with the MFD
MAP display and the MCDU. This includes confirmation of the
waypoint sequence, reasonableness of track angles and distances,
any altitude or speed constraints, and, where possible, which
waypoints are fly-by and which are fly-over. If required by a procedure,
a check will need to be made to confirm that updating will use a
specific navigation aid(s), or to confirm exclusion of a specific
navigation aid. A procedure shall not be used if doubt exists as to the
validity of the procedure in the navigation database.
PFD NAV Source on PF Side.............................. SELECT FMS
Contigency Procedure.......................................... REVIEW
NOTE: During the procedure and where feasible, flight progress
should be monitored for navigational reasonableness, by
cross-checks, with conventional navigation aids using the
primary displays in conjunction with the MCDU.
EMERGENCY AND ABNORMAL PROCEDURES
NAVIGATION DEGRADATION
The navigation degradation is annunciated by:
– The DGRAD annunciator on the PFD.
– The DEAD REACKONING scratchpad message.
– The UNABLE RNP scratchpad message.
Non Affected FMS................................................ SELECT
In case the procedure requires dual P-RNAV capability, single FMS
installations failures or dual FMS failures in dual FMS configuration,
accomplish the contingency procedure.
FMS 1 (2) FAIL
Non Affected FMS................................................ SELECT
In case the procedure requires dual P-RNAV capability, single FMS
installations failures or dual FMS failures in dual FMS configuration,
accomplish the contingency procedure.
CONTINUED...
3-80
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Page 18
Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
FD FAULT
Non Affected Side................................................. SELECT AS
NAVIGATION
SOURCE
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
In case of FD FAIL occurs, apply the P-RNAV contingency procedure.
NOTE: A single channel FD loss is annunciated through the FD FAULT
EICAS message. In the affected side, the FD cue comes out
of view.
"
FMS USAGE IN AREAS NOT COVERED BY WGS-84
OR NAD-83 DATUM
BASIC STATEMENTS
This procedure is to be used in cases when operating in areas not
covered by coordinates method WGS – 84 or NAD-83 datum and the
use of the FMS is desired.
When applying this procedure by deselecting the GPS 1 and 2 on both
MCDUs the FMS may be used normally as long as no DEGRADED
message appears, meaning that the EPU (estimate position uncertainty)
is meeting the required navigation performance for the flight phase.
When the GPS is deselected an inscription DESEL is displayed
confirming that the GPS is disabled.
POSITION INITIALIZATION
The inertial component requires system initialization (entry of latitude
and longitude). Initialization may take place either from a FMS from
input that the crew manually enters via the MCDU, or automatically from
the GPS. A pilot-entered position has priority over a position from a
GPS.
FLIGHTS ORIGINATING ON AREAS NOT COVERED
AFTER AIRPLANE POWER UP
POS INIT page (from the NAV INDEX).................. SELECT
AOM-1502-016
If the airplane is at the same position it was on the last power down.
LAST POS.............................................................. LOAD
For other cases, set the proper position coordinate using the airport or
the gate position.
REF WPT................................................................ SET and LOAD
POS SENSORS page............................................. SELECT
CONTINUED...
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 19
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
On MCDU 1:
GPS 1 (LSK 4L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 2
On MCDU 2:
GPS 1 (LSK 4L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 2
DURING THRU FLIGHTS
POS SENSORS page............................................. SELECT
On MCDU 1:
GPS 1 (LSK 4L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 2
On MCDU 2:
GPS 1 (LSK 4L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
AFTER TAKEOFF
CONTINUED...
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
– LINE SELECT on GPS 2
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
...CONTINUED
AFTER TRANSITION ALTITUDE
POS SENSORS page............................................. SELECT
On MCDU 1:
GPS 1 (LSK 4L)...................................................... ENABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... ENABLE
– Press DELETE key
– LINE SELECT on GPS 2
On MCDU 2:
GPS 1 (LSK 4L)...................................................... ENABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... ENABLE
– Press DELETE key
– LINE SELECT on GPS 2
FLIGHTS APPROACHING TO AREAS NOT COVERED
DESCENT PHASE
AFTER TRANSITION LEVEL
POS SENSORS page............................................. SELECT
On MCDU 1:
GPS 1 (LSK 4L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 1
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 2
On MCDU 2:
GPS 1 (LSK 4L)...................................................... DISABLE
AOM-1502-016
– Press DELETE key
– LINE SELECT on GPS 1
CONTINUED...
3-80
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REVISION 23
Suppl Procedures - Flight
Instruments
Page 21
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
GPS 2 (LSK 5L)...................................................... DISABLE
– Press DELETE key
– LINE SELECT on GPS 2
QFE OPERATION
This procedure is accomplished when ATC altitude assignments are
referenced to QFE altimeter settings.
NOTE: Do not use VNAV below transition altitude/level. Altitudes in
the navigation database are not referenced to QFE. Do not
use FMS LNAV information in procedures that contain
conditional waypoints. Use only raw data for navigation.
Altimeters................................................................ SET
Set altimeters to QFE when below transition altitude/level.
Prior to descent:
Pressurization Mode Selector................................. LFE CTRL
LFE Selector........................................................... SET ZERO
Perform a normal descent approach and landing procedures.
After engines shutdown:
3-80
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Suppl Procedures - Flight
Instruments
REVISION 23
AOM-1502-016
Pressurization Mode Selector................................. AUTO
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
RVSM OPERATION
The RVSM operation reduces the airplane minimum vertical separation
from 2000 ft to 1000 ft between FL 290 and FL 410.
Airworthiness approval alone, does not authorize the flight into the
airspace for which a RVSM operational approval is required by an ICAO
Regional Navigation Agreement.
NORMAL PROCEDURES
EXTERNAL SAFETY INSPECTION
NOSE SECTION
Air Data Smart Probes......................................... NO DAMAGE OR
OBSTRUCTION
Particular attention should be paid to the condition of the pressure ports
and to the marked area on the fuselage skin near each Air Data Smart
Probe.
BEFORE TAKEOFF
Altimeters.............................................................. SET TO THE
AIRFIELD QNH
Altitude Indications................................................ CHECK
NOTE: – An alternative procedure using QFE may also be used;
– The maximum difference between altimeters indication,
and also, the maximum difference between field elevation
and altimeters, should not exceed 23 m (75 ft).
CRUISE
Be sure that all required equipment are in proper operating condition.
AOM-1502-016
Ensure that the airplane is flown at the cleared flight level and that ATC
clearances are fully understood and followed. Do not depart from cleared
flight level without a positive clearance from ATC except for a
contingency or emergency situation.
While changing flight levels, do not overshoot or undershoot the cleared
flight level by more than 45 m (150 ft).
CONTINUED...
3-94
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
RVSM OPERATION
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
The autopilot should be operative and engaged during level cruise,
except for circumstances such as the need to re-trim the airplane or
when it must be disengaged due to turbulence.
When altitude difference between PFD 1 and PFD 2 exceeds 180 ft,
select ADS 3 on the PFD that does not agree with IESS.
To verify if altimeter difference is within tolerance, the flight crew should
proceed as follows:
Altitude.................................................................... STABILIZE
Maintain variation within ± 50 ft.
Air Speed................................................................ STABILIZE
Maintain variation within ± 5 kt.
Wait a minimum of 15 s in straight and leveled flight, preferably with
Autopilot engaged, to compare the difference between altitudes.
AFTER LANDING
In case of failure or malfunction, the following information should be
recorded when appropriate:
– ADS 1, ADS 2, ADS 3 altimeter readings;
– Altitude selector setting;
– Baro Set value and Baro Set unit (INHG/HPA);
– Flight Director used with the Autopilot to control the airplane and
any differences when the other Flight Director was coupled;
– Use of air data system reversion for fault diagnosis procedure;
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Page 2
RVSM OPERATION
REVISION 23
AOM-1502-016
– The transponder selected to provide altitude information to ATC
and any difference noted when an alternative transponder was
selected.
AOM-1502-016
REVISION 21
Flight Patterns
80 Knots
EM170AOM980007E.DGN
THRUST
SET
ROTATE
V1
· GEAR UP
· V2 +10 Knots
POSITIVE RATE
· CLIMB SEQUENCE
· VNAV
· RETRACT FLAPS ON SCHEDULE
ACCELERATION ALTITUDE
TAKEOFF − ALL ENGINES OPERATING
FLAP 0
· CLIMB SPEED
· AFTER TAKEOFF CHECKLIST
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
FLIGHT PATTERNS
TAKEOFF
Copyright © by Embraer. Refer to cover page for details.
3-95
Page 1
Copyright © by Embraer. Refer to cover page for details.
3-95
Page 2
Flight Patterns
REVISION 21
AOM-1502-016
THRUST
SET
80 kt
· GEAR UP
· V2 + 10 kt
POSITIVE RATE
ROTATE
V1
AT 800 ft (NADP 1) OR 1500 ft (ICAO A) AFE
· SELECT VNAV
· MAINTAIN V2 + 10 to 20 kt
UNTIL 3000 ft AFE
· SET SPEED TARGET AS REQUIRED
· RETRACT FLAPS ON SCHEDULE
AT 3000 AFE
NOISE ABATEMENT TAKEOFF NADP 1 / ICAO A
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NOISE ABATEMENT TAKEOFF A
EM170AOM980013E.DGN
AOM-1502-016
THRUST
SET
80 kt
REVISION 21
Flight Patterns
· GEAR UP
· V2 + 10 kt
POSITIVE RATE
ROTATE
V1
AT 800 ft (NADP 2) OR 1000 ft (ICAO B) AFE
· RETRACT FLAPS ON SCHEDULE
· SET VNAV
· MAINTAIN VFS + 10 to 20 kt
UNTIL 3000 ft AFE
AT 3000 AFE
· SET SPEED TARGET AS REQUIRED
NOISE ABATEMENT TAKEOFF NADP 2 / ICAO B
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
NOISE ABATEMENT TAKEOFF B
Copyright © by Embraer. Refer to cover page for details.
3-95
Page 3
EM170AOM980020E.DGN
Page 4
Copyright © by Embraer. Refer to cover page for details.
3-95
Flight Patterns
REVISION 21
AOM-1502-016
· GEAR DOWN
· FLAPS 3
TURNING BASE
700 − 500 FT
· LANDING FLAPS
· BEFORE LANDING CHECKLIST
BASE
30 SEC
· FLAPS 2
ABEAM THRESHOLD
1500 FT
2 nm
VISUAL APPROACH
· PUSH TO/GA SWITCH
· GO AROUND THRUST
· GO AROUND ATTITUDE
· SET GO AROUND FLAPS
· POSITIVE RATE / GEAR UP
· COMPLETE GO AROUND PROCEDURE
· AFTER TAKEOFF CHECKLIST
MISSED APPROACH
· FLAPS 1
ENTERING DOWNWIND
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
VISUAL APPROACH
EM170AOM980009B.DGN
APPROACHING INTERCEPT HEADING
REVISION 21
Flight Patterns
· GEAR DOWN
· FLAPS 3
ONE DOT
· PRESELECT
GO AROUND HEADING
LOCALIZER CAPTURE
· ARM APP MODE
· INTERCEPT WITH FLAPS 2
FIX
· SET LANDING FLAPS
· SET GO AROUND ALTITUDE
· BEFORE LANDING CHECKLIST
GLIDE SLOPE INTERCEPT
· COMPLETE APPROACH CHECKLIST
APPROACHING FIELD
· APPROPRIATE VERTICAL AND LATERAL MODES
· PUSH TO/GA SWITCH
· GO AROUND THRUST
· GO AROUND ATTITUDE
· SET GO AROUND FLAPS
· POSITIVE RATE / GEAR UP
· COMPLETE GO AROUND PROCEDURE
· AFTER TAKEOFF CHECKLIST
MISSED APPROACH
PRECISION APPROACH (ILS)
EM170AOM980011C.DGN
AOM-1502-016
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
PRECISION APPROACH (ILS)
Copyright © by Embraer. Refer to cover page for details.
3-95
Page 5
Page 6
Flight Patterns
Copyright © by Embraer. Refer to cover page for details.
3-95
REVISION 21
AOM-1502-016
APPROACHING FAF
· SET LANDING FLAPS
· SET MDA (DA) OR GO AROUND ALTITUDE (VGP)
ON ALTITUDE PRE SELECTOR
· BEFORE LANDING CHECKLIST
· FOR GPS APPROACH CHECK APPR ANNUNCIATION
RUNWAY INSIGHT
· INTERCEPT LANDING
PROFILE
· SET GO AROUND ALTITUDE
(NON − VGP)
· PERFORM A PRECISION − LIKE
APPROACH
DESCENDING TO MDA
· COMPLETE APPROACH CHECKLIST
· GEAR DOWN
· FLAPS 3
FAF
INBOUND
· INTERCEPT WITH FLAPS 2
APPROACHING INTERCEPT HEADING
· PUSH TO/GA SWITCH
· GO AROUND THRUST
· GO AROUND ATTITUDE
· SET GO AROUND FLAPS
· POSITIVE RATE / GEAR UP
· COMPLETE GO AROUND PROCEDURE
· AFTER TAKEOFF CHECKLIST
MISSED APPROACH
· APPROPRIATE VERTICAL AND LATERAL MODES
APPROACHING FIELD
NON−PRECISION/GPS/RNAV APPROACH
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON−PRECISION APPROACH
EM170AOM980010E.DGN
AOM-1502-016
REVISION 21
INITIAL APPROACH CONFIGURATION
· GEAR DOWN
· FLAPS 3
· SET CIRCLING MINIMUMS
Flight Patterns
· START CHRONOMETER
· MAINTAIN VISUAL REFERENCES
ABEAM THRESHOLD
· LEVEL OFF AT CIRCLING ALTITUDE
· PROCEED TO DOWNWIND LEG
RUNWAY INSIGHT
· LANDING FLAPS
· BEFORE LANDING CHECKLIST
· SET GO AROUND ALTITUDE
TURNING BASE
· INTERCEPT VISUAL PATH
· AUTO PILOT DISCONNECTED
FINAL
· PUSH TO/GA SWITCH
· GO AROUND THRUST
· GO AROUND ATTITUDE
· SET GO AROUND FLAPS
· POSITIVE RATE / GEAR UP
· COMPLETE GO AROUND PROCEDURE
· AFTER TAKEOFF CHECKLIST
MISSED APPROACH
CIRCLING APPROACH
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
CIRCLING APPROACH
Copyright © by Embraer. Refer to cover page for details.
3-95
Page 7
EM170AOM980012D.DGN
Page 8
Flight Patterns
Copyright © by Embraer. Refer to cover page for details.
3-95
REVISION 21
AOM-1502-016
EM170AOM030023A.DGN
· GEAR UP
· FLAPS 2
· SET CIRCLING MINIMUMS
INITIAL APPROACH CONFIGURATION
· START CHRONOMETER
· MAINTAIN VISUAL REFERENCES
ABEAM THRESHOLD
· LEVEL OFF AT CIRCLING ALTITUDE
· PROCEED TO DOWNWIND LEG
RUNWAY INSIGHT
· GEAR DOWN
· FLAPS 3
TURNING BASE
· FLAPS 5
· INTERCEPT VISUAL PATH
· AUTOPILOT DISCONNECTED
· SET RUDDER TRIM TO NEUTRAL
· BEFORE LANDING CHECKLIST
FINAL
· PUSH TO/GA SWITCH
· GO AROUND THRUST
· GO AROUND ATTITUDE
· SET GO AROUND FLAPS
· POSITIVE RATE / GEAR UP
· COMPLETE GO AROUND PROCEDURE
· AFTER TAKEOFF CHECKLIST
MISSED APPROACH
ONE ENGINE INOPERATIVE − CIRCLING APPROACH
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ONE ENGINE INOPERATIVE - CIRCLING APPROACH
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
CAT II ENGAGEMENT LOGIC
The Primus Epic integrated Avionics has a CAT II logic which is
automatically activated whenever the RA/BARO minimums selector knob
is set to RA position. A green APPR 2 annunciator indicates the correct
setting and a white or amber APPR 1 ONLY annunciator indicates an
incorrect setting. The green APPR 2 annunciator is displayed in the
Autopilot Approach Status Annunciator above each FMA.
NOTE: Although the radio altitude setting may be adjusted down to
80 ft, if requested by an ILS CAT II Approved Chart, the Decision
Height (DH) is limited to 100 ft above ground level.
CAT II CONDITIONS OF OPERATION
CAT II operation is allowed only with the green APPR 2 annunciator
enabled.
To obtain a green APPR 2 annunciator the following conditions must be
met:
– Radio altitude below 1500 ft.
– SLAT/FLAP 5.
– NAV 1 on pilot’s side and NAV 2 on copilot’s side, both NAVs
tuned to the same LOC frequency.
– An active approach GS/LOC mode selected. Both courses set to
same value.
– Both Flight Directors operational.
– Attitude and Heading valid on both PFDs.
– Glide slope and Localizer deviation valid on both PFDs.
– No reversions (IRS and ADC) modes selected on both PFDs.
– Valid Airspeed and Baro Altitude on both PFDs.
– No comparison monitors are tripped (FPA, Attitude, Heading,
Airspeed, Baro Altitude, Localizer, Glide slope and Radio altitude)
on both PFDs.
– No back course selected.
AOM-1502-016
– The EICAS message APPR 2 NOT AVAIL not presented.
– RA/BARO Minimums Selector knob set to RA.
CONTINUED...
3-97
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Suppl Procedures - Category II
Page 1
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– Both Display Control Panels set to the same CAT II Decision
Height.
– No TCS Button pressed.
NOTE: – If the CAT II Instrument Approach Landing chart does not
authorize the use of RA, set the RA to OFF (setting
minimums knob to 0 ft). In this case there is no EGPWS call
outs “APPROACHING MINIMUMS” and “MINIMUMS,
MINIMUMS”.
– When the green APPR 2 annunciator is enabled, the
localizer lateral deviation scale is expanded with the
external limits representing the excessive deviation points.
If one of these conditions is not met, the green APPR 2 annunciator will
not appear.
If the green APPR 2 annunciation is displayed and one of the following
conditions is achieved, the amber APPR 1 ONLY annunciation will flash
active characters inverse video for 5 s then steady in conjunction with
the RA Minimum Selected Digital Readout:
– No valid Radio Altitude displayed.
– Airplane no longer APPR 2 capable.
– Crew selects flaps position other than 5 below 800 ft.
– EICAS message SLAT/FLAP LEVER DISAG displayed.
– Either Minimums Selected Readouts change from RA to BARO.
3-97
Copyright © by Embraer. Refer to cover page for details.
Page 2
Suppl Procedures - Category II
REVISION 21
AOM-1502-016
– LOC frequency or inbound course mismatch.
AIRPLANE
OPERATIONS
MANUAL
NORMAL PROCEDURES
NORMAL PROCEDURES
CAT II APPROACH
BEFORE INTERCEPTING LOCALIZER COURSE
– Set the RA/BARO Minimums Selector knob to RA.
– Perform the Descent/Approach/Before Landing checklists, as
appropriate.
– Set the CAT II Decision Height on both Display Control Panels.
– Test Radio Altimeter if only one is available.
– Select the same ILS frequency on MCDU.
NOTE: – If Radio Altimeter is checked not functioning properly the
CAT ll approach must be discontinued.
– A minimum distance of 4 NM to the Outer Marker is
recommended for interception and stabilization along the
approach course.
BEFORE INTERCEPTING THE GLIDE SLOPE
– Monitor radio altimeter information.
– Lower landing gear (one dot below GS interception) and set flaps
to 5.
– Set the Landing Reference Speed (VREF 5) on AP bug (cyan
bug).
– Stabilize and maintain the Landing Reference Speed (VREF 5).
– Set approach climb speed on FS reference speed bug (green
bug).
AOM-1502-016
– Be sure that Marker Beacon audio is on.
CONTINUED...
3-97
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Suppl Procedures - Category II
Page 3
NORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
AFTER PASSING FAF
– The pilot flying should maintain the Landing Reference Speed
(VREF 5).
– At 80 ft above the decision height setting the EGPWS will call out
″APPROACHING MINIMUMS″.
!MAU load 21.2 and on OR POST-MOD SB 190-31-0015
NOTE: If CAT II Instrument Approach Landing chart does not authorize
the use of RA, set the RA to OFF (setting minimums knob to
0 ft). In this case there is no EGPWS call outs ″APPROACHING
MINIMUMS″ and “MINIMUMS”.
"
– If visual contact is not made upon reaching the decision height or
if any malfunction could not be promptly identified during
approach, a missed approach must be immediately initiated.
MISSED APPROACH
GO-AROUND Procedure........................................ APPLY
LANDING
Reaching the Decision Height with runway in sight:
Autopilot................................................................ DISENGAGE
3-97
Copyright © by Embraer. Refer to cover page for details.
Page 4
Suppl Procedures - Category II
REVISION 21
AOM-1502-016
Landing................................................................. PERFORM
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SECTION 4
EMERGENCY AND ABNORMAL PROCEDURES
TABLE OF CONTENTS
AOM-1502-016
Block
Page
Introduction.......................................................... 4-INTRO ....
1
Smoke.................................................................... 4-01-01 ......
1
Non Annunciated.................................................. 4-02-01 ......
1
Airplane General (Cargo
Compartment/Doors/Lighting)...................... 4-03-01 ......
1
Pneumatic/Air Conditioning/Pressurization...... 4-03-02 ......
1
Autoflight.............................................................. 4-03-03 ......
1
Auxiliary Power Unit............................................ 4-03-04 ......
1
Electrical............................................................... 4-03-05 ......
1
Engine................................................................... 4-03-06 ......
1
Fire Protection...................................................... 4-03-07 ......
1
Flight Controls...................................................... 4-03-08 ......
1
FMS/NAV/COMM/Flight Instruments.................. 4-03-09 ......
1
Fuel........................................................................ 4-03-10 ......
1
Hydraulics............................................................. 4-03-11 ......
1
Ice and Rain Protection....................................... 4-03-12 ......
1
Landing Gear and Brakes................................... 4-03-13 ......
1
Oxygen.................................................................. 4-03-14 ......
1
AUTOLAND........................................................... 4-04-52 ......
1
Category II Operation.......................................... 4-04-54 ......
1
Electronic Flight Bag (EFB)................................ 4-04-56 ......
1
4-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
Block
Page
RVSM OPERATION............................................... 4-04-57 ...... 1
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
INTRODUCTION
This section provides the emergency and abnormal procedures to be
performed in case of a system malfunction or failure, in order to protect
passengers and/or crew from serious harm and to maintain the
airworthiness of the airplane.
In case any discrepancy between a procedure contained in this section
and the approved Airplane Flight Manual (AFM) occurs, the AFM
procedures must be followed. In the event that any of the procedures
are missing or unusable, operations may be continued provided the
approved AFM is available for use.
The Emergency/Abnormal Procedures contained herein are based on
system conditions annunciated on EICAS and non-annunciated
conditions. System information displayed on synoptic pages is
informative only and flight crew should always rely on EICAS messages
for system status. Any failure of safety-critical parameter represented on
the MFD synoptic page would also generate an EICAS message.
The Emergency/Abnormal Procedures, in this section, are ordered in
alphabetical sequence and divided into four blocks:
– Smoke Procedures: contain all annunciated and non-annunciated
smoke related procedures.
– Non Annunciated Procedures: procedures, which are not related to
an EICAS message but rather to a condition presented in the airplane.
– Annunciated Procedures: procedures related to an EICAS message.
These procedures are grouped by system and titled with the
correspondent EICAS message wording.
– Supplementary Procedures: procedures related to a special
operation, like CAT II or HGS or Steep Approach which have specific
procedures. These procedures are divided in Non-annunciated and
Annunciated procedures, both in alphabetical order.
Flight crew should use the Ground Resets procedures to clear nuisance
EICAS messages and miscellaneous nuisance faults, detected during
power on and other ground operations.
CHECKLIST OPERATION
AOM-1502-016
The emergency/abnormal procedures have priority over the normal
checklist, except when the crew judges that this is not the safest course
of action.
Flying the airplane is always the priority in any emergency/abnormal
situation. Checklists should only be called by the PF after the flight path
4-INTRO
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
is under control, critical phases of flight (takeoff and landing) have ended
and all memory items have been accomplished.
Some EICAS messages do not have an associated QRH procedure. In
those cases, “Crew Awareness” identifies the EICAS message as noted
in the Index Table. If a Crew Awareness message is displayed on the
EICAS, takeoff is prohibited, unless at least one of the following
conditions is met:
– The message is an expected result of an intentional operation;
– Flight crew action is taken to clear the message;
– Maintenance personnel take action to clear the message;
– The airplane is dispatched in accordance with all approved company
MEL provisions.
The procedures contained herein assume that:
– Airplane systems were operating normally prior to the failure.
– All emergency/abnormal actions are performed in the order they are
presented in the procedure.
– Normal procedures have been properly accomplished.
– System controls were in normal condition prior to initiation of the
associated procedure.
– Aural warnings are silenced as applicable. Master Warning/Caution
lights are reset as soon as the failure is recognized.
– In case of depressurization and presence of smoke, full-face oxygen
masks have been donned and communication has been established.
– A tripped circuit breaker is usually a result of an abnormality in the
electrical load or in associated wiring. Circuit breakers must not be
reset in-flight, unless it is imperative to reset the circuit breaker for
the safe completion of the flight. Should the circuit breaker trip again,
no further attempt should be made to reset that circuit breaker. The
reset of a circuit breaker is also permitted where the checklist
specifically directs to do so.
All tasks foreseen in the procedures have the indication END stating that
the specific task for that condition is over. No task is over until END has
been reached.
In the event of multiple failures (excluding cascade failures) with different
4-INTRO
Copyright © by Embraer. Refer to cover page for details.
Page 2
REVISION 23
AOM-1502-016
Upon completion of the procedure the pilot reading it should state:
“___________ Checklist Complete”.
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
landing configurations and/or landing distance correction factors, the
crew should use good judgment to determine the safest course of
action.
CHECKLIST STRUCTURE
Some procedures bring a characterization below the title in case any
relevant emergency/abnormal condition is present, such as aural
warnings, lights, EICAS indications, flight instrument flags and the
airplane condition itself.
The actions contained in the bold square boxes are memory items. They
must be performed expeditiously, from memory.
Some procedures require landing at the nearest suitable airport. This
statement may be presented below the associated emergency/abnormal
characterization or at the beginning of a task that requires so. When the
crew determines that significant threat to safety is present, they should
always accomplish the earliest possible descent and landing regardless
of having this statement present in the procedure.
Some procedures contain “Lists of Relevant Inoperative Items” for that
particular condition. Those lists presents only the most relevant items
and for the full list, the AOM should be consulted. As SMOKE events are
very time critical, on those procedures the lists contain only items that
significantly affect airplane performance and/or controllability. For the
entire list of relevant inoperative items on those conditions, the pilot can
refer to the procedures associated with the electrical busses off.
Procedures for failures affecting the landing distance presents an
″abnormal landing correction factor″. This factor must be multiplied by
the applicable unfactored landing distance. The factor presented in the
procedure is applicable to dry runways. Additional factors for other
conditions are presented in the performance section of this manual.
Throughout this manual, a text followed by () means that either condition
apply. A text followed by “-” means that both conditions apply
simultaneously.
Whenever a question is necessary in the checklist it will be in a Yes/No
format and presented inside a box, with arrows pointing where the
checklist will continue depending on the answer, being that the “Yes” will
always be directly below the question box. In some cases the arrows
may be presented as a dashed line, to avoid confusion when there are
two arrows close to each other.
AOM-1502-016
NOTE: Circuit Breakers reset may be performed when following the
limitations and procedures specified in the GROUND RESETS.
4-INTRO
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-INTRO
Copyright © by Embraer. Refer to cover page for details.
Page 4
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
SMOKE
TABLE OF CONTENTS
Block
Page
WARNING
CRG FWD (AFT) SMOKE ...................................... 4-01-01......
1
LAV SMOKE.......................................................... 4-01-01......
2
SMOKE EVACUATION........................................... 4-01-01......
2
SMOKE / FIRE / FUMES ....................................... 4-01-01......
3
CAUTION
Airplanes equipped with IFE (In-flight Entertainment System)
AOM-1502-016
IFE RACK SMOKE ................................................ 4-01-01......
RECIRC SMOKE ................................................... 4-01-01......
11
11
4-01-01-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-01-01-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 22
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
CRG FWD (AFT) SMOKE
Light:
Associated Cargo Fire-Extinguishing Button
illuminates.
Associated Cargo Fire Extinguishing Button........ PUSH
LAND AT THE NEAREST SUITABLE AIRPORT.
ON GROUND?
No
Yes
After CRG AFT (FWD) FIREX LO ARM message is displayed and
the associated Cargo Fire Extinguishing Button is illuminated:
Associated Cargo Fire Extinguishing Button........ AS REQUIRED
NOTE: – Advise Ground Crew of possible Halon vapors after
discharging the extinguishing bottle.
– After the bottle discharge and with the airplane on
ground, the message CRG FWD (AFT) FIRE SYS FAIL
will appear.
END
AOM-1502-016
END
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
LAV SMOKE
Establish contact with the cabin crew.
If necessary:
Diversion............................................................... CONSIDER
SMOKE EVACUATION Procedure....................... ACCOMPLISH
END
SMOKE EVACUATION
Crew Oxygen Masks............................................ DON, 100%
Crew Communication........................................... ESTABLISH
Pressurization Dump Button................................. PUSH IN
LAND AT THE NEAREST SUITABLE AIRPORT.
Cockpit Door........................................................... CLOSE
Cabin Rate.............................................................. VERIFY
CABIN RATE IS LESS THAN 1000 FT/MIN?
No
Yes
Pressurization Mode Selector................................. MAN
Pack 1 Button.......................................................... PUSH OUT
Pack 2 Button.......................................................... PUSH OUT
Fstn Belts Signs...................................................... ON
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
Thrust Lever............................................................ IDLE
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
Smoke
REVISION 23
AOM-1502-016
Recirc Fan Button................................................... PUSH OUT
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
...CONTINUED
Speedbrake............................................................. FULL OPEN
Airspeed.................................................................. MAX/
APPROPRIATE
Transponder............................................................ 7700
ATC......................................................................... NOTIFY
END
SMOKE / FIRE / FUMES
CONDITION:
Smoke fire or fumes have been spotted by the
crew without an EICAS warning.
Crew Oxygen Masks............................................ DON, 100%
Crew Communication........................................... ESTABLISH
LAND AT THE NEAREST SUITABLE AIRPORT.
Recirc Fan Button................................................... PUSH OUT
NOTE: Any time the smoke becomes dense, perform the SMOKE
EVACUATION Procedure.
SMOKE ORIGIN IS OBVIOUS AND CAN BE REMOVED?
No
Yes
Affected source....................................................... REMOVE
SMOKE STOPS OR DECREASES?
No
Yes
SMOKE EVACUATION Procedure.......................... AS REQUIRED
AOM-1502-016
END
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Fstn Belts Signs...................................................... ON
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
Thrust Levers.......................................................... IDLE
Speedbrake............................................................. FULL OPEN
Airspeed.................................................................. MAX/
APPROPRIATE
Transponder............................................................ 7700
ATC......................................................................... NOTIFY
Pressurization DUMP Button.................................. PUSH IN
NOTE: Smoke will initially decrease due to pressurization dumping,
even if the correct source has not yet been removed.
Bleed 1 Button........................................................ PUSH OUT
Bleed 2 Button........................................................ PUSH OUT
Emergency Lights................................................... OFF
RAT Manual Deploy Lever...................................... PULL
Airspeed.................................................................. MIN 130 KIAS
IDG 1 Selector........................................................ OFF
IDG 2 Selector........................................................ OFF
APU Gen Button..................................................... PUSH OUT
NOTE: Do not accomplish THE ELEC EMERGENCY Procedure.
BATT DISCHARGING MESSAGE PRESENTED?
No
Yes
IDG 1 or 2 Selector................................................. AUTO
Yes
No
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
Smoke
REVISION 23
AOM-1502-016
SMOKE STOPS OR DECREASES?
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
...CONTINUED
Relevant Inoperative Items
All Engine Reversers
All Ground Spoilers
All Multi Function Spoilers
Display Unit 1
Display Unit 4
Display Unit 5
Nosewheel Steering
Service Interphone System
(Normal Mode)
Icing Conditions...................................................... EXIT/AVOID
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap................................................................ 3
Set Vref = Vref
FULL
+ 20 KIAS or 130 KIAS (whichever is higher).
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.21.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ Vref FULL+ 20 or
130 KIAS
WHICHEVER
IS HIGHER
NOTE: On ground, steer the airplane using differential braking and
rudder.
END
SUITABLE AIRPORT IS DISTANT?
No
AOM-1502-016
Yes
IDG 1 Selector........................................................ AUTO
IDG 2 Selector........................................................ AUTO
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
DC BUS TIES Switch............................................. OFF
TRU 1 Switch.......................................................... OFF
Battery 1.................................................................. OFF
DC ESS BUS 1 AND DC BUS 1 ARE DEENERGIZED.
SMOKE STOPS OR DECREASES?
Yes
No
Relevant Inoperative Items
Engine 1 Reverser
Multi function spoilers L5 and
R5
Outboard Brakes
Icing Conditions...................................................... EXIT/AVOID
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap ............................................................... 3
Set Vref = Vref
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.37.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ Vref FULL+ 20
until the
acceleration
altitude is
reached.
CAUTION:
•
•
APPLY THE EMERGENCY/PARKING BRAKE
MONITORING
THE
EMERGENCY/PARKING
BRAKE LIGHT.
WHEN THE EMERGENCY/PARKING BRAKE
LIGHT IS ON, MAINTAIN STEADY PRESSURE
SINCE THE ANTI-SKID PROTECTION IS NOT
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 6
Smoke
REVISION 23
AOM-1502-016
If necessary, on Ground:
Emergency/Parking Brake.................................... PULL
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
...CONTINUED
AVAILABLE.
END
Battery 1.................................................................. ON
TRU 1 Switch.......................................................... AUTO
TRU 2 Switch.......................................................... OFF
Battery 2.................................................................. OFF
DC ESS BUS 2 AND DC BUS 2 ARE DEENERGIZED.
SMOKE STOPS OR DECREASES?
Yes
No
Relevant Inoperative Items
All Engine Reversers
Inboard Brakes
Multi Function Spoilers L3, R3,
L4 and R4
Nosewheel Steering
Speedbrakes
Icing Conditions...................................................... EXIT/AVOID
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap ............................................................... 3
Set Vref = Vref
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.55.
UNFACTORED
AOM-1502-016
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ Vref FULL+ 20
until the
acceleration
altitude is
reached.
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
If necessary, on Ground:
Emergency/Parking Brake.................................... PULL
CAUTION:
•
•
APPLY THE EMERGENCY/PARKING BRAKE
MONITORING
THE
EMERGENCY/PARKING
BRAKE LIGHT.
WHEN THE EMERGENCY/PARKING BRAKE
LIGHT IS ON, MAINTAIN STEADY PRESSURE
SINCE THE ANTI-SKID PROTECTION IS NOT
AVAILABLE.
NOTE: On ground, steer the airplane using differential braking and
rudder.
END
Battery 2.................................................................. AUTO
TRU 2 Switch.......................................................... AUTO
TRU ESS Switch..................................................... OFF
DC ESS BUS 3 ARE DEENERGIZED.
SMOKE STOPS OR DECREASES?
No
Yes
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap ............................................................... 3
Set Vref = Vref
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.35.
UNFACTORED
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 8
Smoke
REVISION 23
AOM-1502-016
If a go around is required:
Slat/Flap................................................................ 3
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
...CONTINUED
Airspeed................................................................ Vref FULL+ 20
until the
acceleration
altitude is
reached.
END
WARNING: CONSIDER AN IMMEDIATE LANDING.
TRU ESS Switch..................................................... AUTO
DC BUS TIES Switch............................................. AUTO
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap ............................................................... 3
Set Vref = Vref
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.35.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ Vref FULL+ 20
until the
acceleration
altitude is
reached.
AOM-1502-016
END
CONTINUED...
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Relevant Inoperative Items
All Engine Reversers
All Ground Spoilers
All Multi Function Spoilers
Display Unit 1
Display Unit 4
Display Unit 5
Nosewheel Steering
Service Interphone System
(Normal Mode)
Icing Conditions...................................................... EXIT / AVOID
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap................................................................ 3
Set Vref = Vref
FULL
+ 20 KIAS or 130 KIAS (whichever is higher).
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.21.
UNFACTORED
NOTE: On ground, steer the airplane using differential braking and
rudder.
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ Vref FULL+ 20 or
130 KIAS
WHICHEVER
IS HIGHER
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 10
Smoke
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
!Airplanes equipped with IFE (In-flight Entertainment System)
IFE RACK SMOKE
LAND AT THE NEAREST SUITABLE AIRPORT.
IFE Button............................................................... PUSH OUT
If necessary:
SMOKE EVACUATION Procedure....................... ACCOMPLISH
END
"
RECIRC SMOKE
LAND AT THE NEAREST SUITABLE AIRPORT.
Recirc Fan Button................................................... PUSH OUT
AOM-1502-016
END
4-01-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Smoke
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
SMOKE PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-01-01
Copyright © by Embraer. Refer to cover page for details.
Page 12
Smoke
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
NON ANNUNCIATED
TABLE OF CONTENTS
Block
Page
EMERGENCY
CARGO COMPARTMENT FIRE ............................. 4-02-01......
1
DITCHING............................................................. 4-02-01......
2
DUAL ENGINE FAILURE ....................................... 4-02-01......
3
EMERGENCY DESCENT ...................................... 4-02-01......
6
EMERGENCY EVACUATION ................................. 4-02-01......
7
ENGINE ABNORMAL START ................................. 4-02-01......
7
ENGINE FIRE, SEVERE DAMAGE OR
SEPARATION .................................................. 4-02-01......
8
FORCED LANDING ............................................... 4-02-01......
11
FUEL LEAK ........................................................... 4-02-01......
12
JAMMED CONTROL COLUMN (PITCH)................. 4-02-01......
13
JAMMED CONTROL WHEEL (ROLL)..................... 4-02-01......
14
JAMMED RUDDER PEDALS ................................. 4-02-01......
15
PITCH TRIM RUNAWAY ........................................ 4-02-01......
16
REJECTED TAKEOFF ........................................... 4-02-01......
17
ROLL (YAW) TRIM RUNAWAY ............................... 4-02-01......
18
STEERING RUNAWAY .......................................... 4-02-01......
19
TAKEOFF WITH ENGINE FAILURE AT OR ABOVE
V1 ................................................................... 4-02-01......
19
ABNORMAL
ABNORMAL LANDING GEAR EXTENSION ........... 4-02-01......
APU EGT AMBER INDICATION ............................. 4-02-01......
20
21
AOM-1502-016
O.B Nº 170-006/05 - AP quick disconnect button malfunctions
"AUTOPILOT" AURAL CAN NOT BE CANCELED... 4-02-01......
BLANK DISPLAY UNIT WITHOUT AUTOMATIC
REVERSION.................................................... 4-02-01......
21
22
4-02-01-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
Block
ABNORMAL
EICAS MESSAGE MISCOMPARISON....................
ENGINE ABNORMAL VIBRATION..........................
ENGINE AIRSTART ...............................................
ENGINE AIRSTART ENVELOPE ............................
ENGINE ITT OVERTEMPERATURE.......................
ENGINE OIL OVERTEMPERATURE ......................
ENGINE OIL PRESSURE ABNORMAL
INDICATION ....................................................
ENGINE SHUTDOWN ...........................................
ENGINE TAILPIPE FIRE ........................................
GEAR LEVER CAN NOT BE MOVED UP...............
Page
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
23
23
25
28
29
29
4-02-01......
4-02-01......
4-02-01......
4-02-01......
30
31
32
32
IESS ATTITUDE OSCILLATION WITH RAT
DEPLOYED ..................................................... 4-02-01......
IMPAIRED OR CRACKED WINDSHIELD................ 4-02-01......
33
34
O.B Nº 170-011/08 - IESS operation with RAT deployed
O.B Nº 170-003/11 - Continuous in flight LANDING GEAR aural
warning due to radar altimeter misbehavior
"LANDING GEAR" AURAL CAN NOT BE
CANCELED .....................................................
LOSS OF APU INDICATIONS ................................
LOSS OF COMMUNICATIONS ..............................
LOSS OF HYDRAULIC SYSTEM 1 ........................
LOSS OF HYDRAULIC SYSTEM 2 ........................
LOSS OF HYDRAULIC SYSTEM 3 ........................
LOSS OF HYDRAULIC SYSTEM 1 AND 2 .............
LOSS OF HYDRAULIC SYSTEM 1 AND 3 .............
LOSS OF HYDRAULIC SYSTEM 2 AND 3 .............
LOSS OF PRESSURIZATION INDICATION ............
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
4-02-01......
35
37
37
38
38
39
40
41
42
43
O.B Nº 170-006/05 - AP quick disconnect button malfunctions
45
46
47
4-02-01-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
NON ANNUNCIATED LOSS OF ALL TRIMS AND
AUTOPILOT .................................................... 4-02-01......
ONE ENGINE INOPERATIVE APPROACH AND
LANDING ........................................................ 4-02-01......
OXYGEN LEAKAGE .............................................. 4-02-01......
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
Block
AOM-1502-016
ABNORMAL
PARTIAL OR GEAR UP LANDING .........................
STRUCTURAL DAMAGE .......................................
UNRELIABLE AIRSPEED ......................................
VOLCANIC ASH ....................................................
Page
4-02-01......
4-02-01......
4-02-01......
4-02-01......
47
48
49
53
4-02-01-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-02-01-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 4
Table of Contents
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
CARGO COMPARTMENT FIRE
Associated Cargo Fire Extinguishing Button........ PUSH
LAND AT THE NEAREST SUITABLE AIRPORT.
After CRG AFT (FWD) FIREX HI ARM message is displayed and
the associated Cargo Fire Extinguishing Button is illuminated:
Associated Cargo Fire Extinguishing Button........ PUSH AGAIN
ON GROUND?
No
Yes
After CRG AFT (FWD) FIREX LO ARM message is displayed and
the associated Cargo Fire Extinguishing Button is illuminated:
Associated Cargo Fire Extinguishing Button........ AS REQUIRED
NOTE: – Advise Ground Crew of possible Halon vapors after
discharging the extinguishing bottle.
– After the bottle discharge and with the airplane on
ground, the message CRG FWD (AFT) FIRE SYS FAIL
will appear.
END
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
DITCHING
Descent:
Cabin Crew........................................................... NOTIFY
ATC....................................................................... NOTIFY
Transponder.......................................................... 7700
Aural Warning CBs (C7; C31).............................. PULL
No Smkg/Fstn Belts Signs.................................... ON
ELT........................................................................ ON
Landing Data........................................................ SET
At 10000 ft AGL:
Pressurization Dump Button................................. PUSH IN
When differential pressure reaches 0.2 psid or below:
Airspeed................................................................ MAX 160 KIAS
If necessary extend Flap/Slat as required to maintain airspeed
below 160 KIAS.
Direct Vision Window............................................ OPEN
Approach:
Altimeters.............................................................. SET
At 5000 ft AGL:
Pressurization Mode Selector............................... MAN
Cabin Alt Controller............................................... HOLD DOWN
FOR 50 s
Ditching Configuration:
Terrain Inhibit Button............................................. IN
Landing Gear........................................................ UP
Slat/Flap................................................................ MAXIMUM
AVAILABLE
NOTE: If engines are not running maintain minimum speed of
130 KIAS.
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
Non Annunciated
REVISION 23
AOM-1502-016
APU Emergency Stop Button............................... PUSH IN
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Just Before Water Contact:
Cabin..................................................................... ANNOUNCE
IMPACT
After Ditching:
Thrust Levers........................................................ IDLE
Start/Stop Selectors.............................................. STOP
Fire Extinguishing Handles................................... PULL AND
ROTATE
Emergency Evacuation......................................... ANNOUNCE
Batteries................................................................ OFF
END
DUAL ENGINE FAILURE
EICAS Indication: FAIL icon inside both N1 indicators.
EICAS Indication: Both oil pressure indications in red.
Airspeed................................................................ 265 KIAS MIN
RAT Manual Deploy Lever.................................... PULL
LAND AT THE NEAREST SUITABLE AIRPORT.
APU......................................................................... START
Emergency Lights................................................... OFF
Thrust Levers.......................................................... IDLE
BOTH ENGINES SUCCESSFUL AUTORELIGHT?
No
Yes
Flight Controls Mode Buttons (Spoilers, Elevators,
Rudder)................................................................... PUSH IN, then
OUT
AOM-1502-016
Descent:
Landing Data........................................................ SET
Approach Aids....................................................... SET
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Altimeters.............................................................. SET/CHECK
Landing Configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap................................................................ 3
Set VREF = VREF
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.35.
UNFACTORED
NOTE: – During engine auto relight, if N2 is steady accelerating
while ITT remains within start limit, the start is
progressing normally.
– During inflight starts, FADEC has no protection for hot
starts, hung starts or failure to light off.
– Crew must take appropriate action in case of abnormal
engine indications.
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ VREF FULL +
20 KIAS
END
ENGINE AIRSTART ENVELOPE........................... CHECK
Fuel Xfeed Selector................................................ LOW 1
Inoperative Engine(s):
Start/Stop Selector(s)........................................... STOP
Ignition(s).............................................................. OVRD
Start/Stop Selector(s)........................................... START, then
RUN
Yes
No
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
Non Annunciated
REVISION 23
AOM-1502-016
DUAL ENGINE FAILURE CONDITION PERSISTS?
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Landing Configuration:
Emergency Lights................................................. ARMED
Slat/Flap................................................................ 3
Set VREF = VREF FULL + 20 KIAS or VREF = 130 KIAS (whichever is
higher).
FORCED LANDING or DITCHING Procedure....... ACCOMPLISH
END
Flight Controls Mode Buttons (Spoilers, Elevators,
Rudder)................................................................. PUSH IN, then
OUT
After engine(s) stabilized at idle:
Ignition(s).............................................................. AUTO
Fuel....................................................................... BALANCE
ONE ENGINE INOPERATIVE?
No
Yes
Inoperative Engine START/STOP Selector............. STOP
Transponder............................................................ TA ONLY
Descent:
Landing Data........................................................ SET
Approach Aids....................................................... SET
Altimeters.............................................................. SET/CHECK
Landing Configuration:
Emergency Lights................................................. ARMED
AOM-1502-016
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Landing Gear........................................................ DOWN
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Slat/Flap................................................................ 3
Set VREF = VREF
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.30.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ VREF FULL +
20 KIAS
END
EMERGENCY DESCENT
Fstn Belts Signs.................................................... ON
Altitude.................................................................. 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
Thrust Levers........................................................ IDLE
Speedbrake........................................................... FULL OPEN
Airspeed................................................................ MAX/
APPROPRIATE
Transponder.......................................................... 7700
ATC....................................................................... NOTIFY
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 6
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
EMERGENCY EVACUATION
Emergency/Parking Brake.................................... ON
Slat/Flap Lever...................................................... 5
Thrust Levers........................................................ IDLE
Start/Stop Selectors.............................................. STOP
Fire Extinguishing Handles................................... PULL AND
ROTATE (1-L
and 2-R)
APU Emergency Stop Button............................... PUSH IN
APU Fire Extinguishing Button............................. PUSH
Pressurization Dump Button................................. PUSH IN
ATC....................................................................... NOTIFY
Emergency Evacuation......................................... ANNOUNCE
Batteries................................................................ OFF
END
ENGINE ABNORMAL START
Affected engine:
Start/Stop Selector............................................. STOP
ENGINE AIRSTART ENVELOPE........................... CHECK
ENGINE DRY MOTORING CONSIDERED?
No
Yes
Affected engine:
Ignition.................................................................. OFF
Start/Stop Selector................................................ START, then
RUN
AOM-1502-016
ITT, N1, N2, Fuel Flow and Oil Pressure............. MONITOR
...................After appropriate parameters are attained...................
Start/Stop Selector................................................ STOP
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Ignition.................................................................. AUTO
If applicable:
Transponder.......................................................... TA ONLY
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
END
ENGINE FIRE, SEVERE DAMAGE OR
SEPARATION
Autothrottle............................................................ DISENGAGE
Affected engine:
Thrust Lever....................................................... IDLE
Start/Stop Selector............................................. STOP
Fire Extinguishing Handle.................................. PULL
LAND AT THE NEAREST SUITABLE AIRPORT.
Fire Extinguishing Handle....................................... ROTATE
(L or R)
........................................Wait 30 seconds........................................
FIRE PERSISTS?
No
Yes
Fire Extinguishing Handle (remaining bottle).......... ROTATE
No
Yes
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 8
Non Annunciated
REVISION 23
AOM-1502-016
ON GROUND?
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
EMERGENCY EVACUATION Procedure................ AS REQUIRED
END
HIGH VIBRATION?
No
Yes
Airspeed.................................................................. REDUCE
Airspeeds below VA are recommended to reduce vibration.
Icing Conditions...................................................... EXIT/AVOID
Transponder............................................................ TA ONLY
EICAS ASSOCIATED FUEL INDICATION LOST?
No
Yes
NOTE: Assume that fuel is leaking from tank associated to engine
failed side.
Fuel Xfeed Selector................................................ OFF
LEAK ON THE RH TANK?
No
Yes
APU......................................................................... OFF
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
AOM-1502-016
END
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!O.B Nº 170-001/09 - ENGINE STALL DUE TO BACKPRESSURE FROM APU
BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
END
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Fuel......................................................................... BALANCE
Autothrottle.............................................................. AS REQUIRED
When appropriate:
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 10
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
FORCED LANDING
Descent:
Cabin Crew........................................................... NOTIFY
ATC....................................................................... NOTIFY
Transponder.......................................................... 7700
Aural Warning CBs (C7; C31).............................. PULL
No Smkg/Fstn Belts Signs.................................... ON
ELT........................................................................ ON
Landing Data........................................................ SET
At 10000 ft:
Pressurization Dump Button................................. PUSH IN
Approach:
Altimeters.............................................................. SET
Landing Configuration:
Terrain Inhibit Button............................................. IN
Landing Gear........................................................ DOWN
Slat/Flap................................................................ MAXIMUM
AVAILABLE
APU Emergency Stop Button............................... PUSH IN
NOTE: If engines are not running maintain minimum speed of
130 KIAS and alternate gear extension may be required.
Just Before Touchdown:
Cabin..................................................................... ANNOUNCE
IMPACT
After Landing:
Thrust Levers........................................................ IDLE
Start/Stop Selectors.............................................. STOP
AOM-1502-016
Fire Extinguishing Handles................................... PULL AND
ROTATE
Emergency Evacuation......................................... ANNOUNCE
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Batteries................................................................ OFF
END
FUEL LEAK
LAND AT THE NEAREST SUITABLE AIRPORT.
A fuel leak may be detected by either:
•
•
•
•
•
•
A fuel imbalance develops; or
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings; or
With both engines operative, an unexpected difference
between the total fuel quantity indicated on EICAS and the
total fuel quantity indicated on the FMS Fuel Management
page or PERF INIT page 3/3.
Fuel Xfeed Selector................................................ OFF
Affected Fuel Tank.................................................. IDENTIFY
Identify the affected fuel tank using the fuel flow, fuel quantity or
visually.
Asymmetric Thrust.................................................. AS REQUIRED
Use asymmetric thrust to improve or maintain wing fuel balance
to counteract the effect of the suspected wing fuel leak.
LEAK ON THE RH TANK?
No
Yes
APU......................................................................... OFF
Right tank supplies fuel to the APU.
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 12
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
!O.B Nº 170-001/09 - ENGINE STALL DUE TO BACKPRESSURE FROM APU
BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
END
JAMMED CONTROL COLUMN (PITCH)
Elev Disc Handle.................................................. PULL
Unrestricted Control Column.................................. IDENTIFY
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
NOTE: Expect lower pitch rates and authority.
Relevant Inoperative Items:
AOA Limit
Autopilot
Avoid sidesliping the airplane.
NOTE: The stick shaker remains operative.
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF
FULL
+ 15 KIAS.
AOM-1502-016
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.29.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 4
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Airspeed................................................................ VREF FULL +
15 KIAS
(limited to
175 KIAS)
END
JAMMED CONTROL WHEEL (ROLL)
Aileron Disc Handle.............................................. PULL
Unrestricted Control Wheel..................................... IDENTIFY
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
NOTE: –
–
–
–
–
Expect lower roll rates.
Avoid abrupt and large aileron inputs.
Maintain bank angle below 25°.
Rudder may be used to help controlling the airplane.
Do not accomplish the Spoiler Fault procedure.
Relevant Inoperative Items:
Multi Function Spoiler L3 and
R3
Another Multi Function Spoiler
pair depending on the affected
side
Affected side aileron
Autopilot
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF
•
•
+ 15 KIAS.
DURING LANDING, A CROSSWIND COMPONENT
GREATER THAN 10 KT MUST BE AVOIDED.
MULTIPLY THE FULL FLAPS UNFACTORED
LANDING DISTANCE BY 1.29.
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 14
Non Annunciated
REVISION 23
AOM-1502-016
CAUTION:
FULL
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
If a go around is required:
Slat/Flap................................................................ 4
Airspeed................................................................ VREF FULL +
15 KIAS
(limited to
175 KIAS)
END
JAMMED RUDDER PEDALS
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
Relevant Inoperative Items:
Yaw trim
NOTE: Use asymmetric thrust for directional control.
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF FULL.
CAUTION: DURING LANDING, A CROSSWIND COMPONENT
GREATER THAN 10 KT MUST BE AVOIDED.
Before Landing:
Steer Disc Switch (Pilot non flying)...................... PRESS and
HOLD
Asymmetric Thrust................................................ MAINTAIN
UNTIL
NOSEWHEEL
TOUCHDOWN
AOM-1502-016
After nosewheel touchdown:
Nosewheel Steering Handle................................. PRESS and
HOLD
Steer Disc Switch................................................. RELEASE
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 15
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Thrust Levers........................................................ IDLE
Asymmetric Braking.............................................. AS REQUIRED
CAUTION: DO NOT RELEASE THE NOSEWHEEL STEERING
HANDLE UNTIL THE AIRPLANE IS COMPLETELY
STOPPED.
If a go around is required, proceed as a normal go around limiting
the airspeed to 175 KIAS.
NOTE: As asymmetric thrust may be required to help controlling
the airplane, maximum thrust on both engines may not be
possible.
END
PITCH TRIM RUNAWAY
A/P Disc Button.................................................... PRESS AND
HOLD
Pitch Trim Systems 1 and 2 Cutout Button.......... PUSH IN
A/P Disc Button....................................................... RELEASE
WARNING: DO NOT OPEN THE SPEEDBRAKE.
NOTE: Continuous turns helps to alleviate excessive pitch up
tendencies.
Prepare to overcome unwanted pitch change:
Pitch Trim System 1 Cutout Button...................... PUSH OUT
Pitch Trim Switch.................................................. ACTUATE
PITCH TRIM NORMAL?
No
Yes
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 16
Non Annunciated
REVISION 23
AOM-1502-016
NOTE: Manual trim command through Pitch Trim Switches is
available with at least one functional HS-ACE channel.
With one HS-ACE channel available expect the following
differences on the pitch trim indication on EICAS:
• Pitch trim readout display showing amber dashes.
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
•
Pitch trim scale without the solid green pointer.
END
Pitch Trim System 1 Cutout Button........................ PUSH IN
Pitch Trim System 2 Cutout Button........................ PUSH OUT
NOTE: Manual trim command through Pitch Trim Switches is
available with at least one functional HS-ACE channel.
With one HS-ACE channel available expect the following
differences on the pitch trim indication on EICAS:
• Pitch trim readout display showing amber dashes.
• Pitch trim scale without the solid green pointer.
END
REJECTED TAKEOFF
Thrust Levers.......................................................... IDLE
Reverse Thrust....................................................... AS REQUIRED
Brake Pedals (If Autobrake is not armed).............. MAXIMUM
APPLY
NOTE: During RTO the thrust reversers can be used until the
airplane comes to a complete stop.
When airplane has stopped:
Emerg/Parking Brake............................................ ON
If applicable:
EMERGENCY EVACUATION Procedure............. ACCOMPLISH
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 17
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
ROLL (YAW) TRIM RUNAWAY
A/P Disc Button.................................................... PRESS AND
HOLD
Do not engage the autopilot.
Prepare to overcome unexpected roll (yaw):
A/P Disc Button.................................................... RELEASE
ROLL (YAW) TRIM NORMAL?
No
Yes
END
A/P Disc Button....................................................... PRESS AND
HOLD
Roll (Yaw) Trim Electronic CB................................ OUT
Select on the MCDU: CB → CB MENU → CB BY SYSTEM →
NEXT → FLT CTRL → ROLL TRIM PWR or YAW TRIM PWR.
A/P Disc Button....................................................... RELEASE
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 18
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
STEERING RUNAWAY
Steer Disc Switch................................................. PRESS
Use differential braking and rudder to steer the airplane.
END
TAKEOFF WITH ENGINE FAILURE AT OR
ABOVE V1
At VR rotate the airplane following the flight director guidance.
In case of flight director is inoperative, rotate the airplane
according to the following schedule:
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
Rotate the airplane according to the takeoff pitch angle displayed
on TAKEOFF page 3/3 on the MCDU.
"
With positive climb:
Landing Gear..................................................... UP
Airspeed............................................................. MIN V2
Maintain V2 minimum up to the acceleration altitude. At the
acceleration altitude, select flaps up according to the flap retraction
speed reference indication.
Accelerate the airplane to the final segment speed (VFS) and set the
engine thrust rate to continuous.
NOTE: If the airplane is at low weight and the selected altitude is
low, TO/GA vertical mode may be reverted to ASEL.
After retracting flaps, accomplish the ENG 1 (2) FAIL Procedure.
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 19
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
ABNORMAL LANDING GEAR EXTENSION
Landing Gear Lever................................................ DOWN
Electrical Override Switch....................................... GEAR DOWN
LG INDICATIONS DOWN?
No
Yes
END
Alternate Gear Extension Lever............................. PULL
NOTE: Ensure the Alternate Gear Extension Lever is completely
actuated and locked.
Landing Gear Indications........................................ CHECK
LG INDICATIONS DOWN?
Yes
No
Relevant Inoperative Items
Nosewheel Steering
END
PARTIAL OR GEAR UP LANDING Procedure...... ACCOMPLISH
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 20
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
APU EGT AMBER INDICATION
APU ESSENTIAL FOR FLIGHT?
No
Yes
END
APU......................................................................... OFF
END
!O.B Nº 170-006/05 - AP quick disconnect button malfunctions
"AUTOPILOT" AURAL CAN NOT BE CANCELED
Autopilot.................................................................. ENGAGE
Autopilot Quick Disconnect Button......................... PRESS TWO
TIMES
AURAL IS CANCELED?
No
Yes
END
AOM-1502-016
NOTE: The aural warning can only be canceled by powering down
the airplane.
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 21
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Relevant Inoperative Items:
Autopilot
Pitch trim indication
Roll trim
Yaw trim
Pitch Trim System 1 Cutout Button........................ PUSH IN
PITCH TRIM NORMAL?
No
Yes
END
Pitch Trim System 1 Cutout Button........................ PUSH OUT
Pitch Trim System 2 Cutout Button........................ PUSH IN
END
"
BLANK DISPLAY UNIT WITHOUT AUTOMATIC
REVERSION
Select the affected side reversionary panel display selector to PFD
or EICAS, as required.
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 22
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
EICAS MESSAGE MISCOMPARISON
INDICATION:
CAS MSG flag on PFD.
CAS SOURCE SELECTION................................... ALTERNATE
BETWEEN
CAS 1 AND
CAS 2 AND
COMPARE
Select on the MCDU: MENU→MISC (LSK 1L)→SETUP (LSK
2L)→CAS SOURCE SELECTION (LSK 2R)→CAS 1→CAS 2.
Compare the messages of the two CAS sources displayed on the
EICAS to check which is the discrepant message. Analyze the
situation to check whether the discrepant message is spurious or
not, and take the appropriate corrective action.
END
ENGINE ABNORMAL VIBRATION
EICAS Indication: Engine vibration indication displayed in amber.
Autothrottle.............................................................. DISENGAGE
ENG VIBRATION DUE TO ICE ACCUMULATION?
No
Yes
NOTE: If both engines are affected, perform the following steps for
one engine at a time.
Associated Thrust Lever......................................... IDLE, THEN
MINIMUM 70%
N1
........................................Wait 30 seconds........................................
Associated Thrust Lever......................................... AS REQUIRED
AOM-1502-016
END
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 23
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Associated Thrust Lever......................................... REDUCE
Reduce thrust to achieve green range vibration.
Associated Thrust Lever......................................... AS REQUIRED
ENG ABNORMAL VIBRATION REMAINS?
No
Yes
Associated Thrust Lever......................................... REDUCE
Reduce thrust to keep vibration within limits.
Transponder............................................................ TA ONLY
If unable to keep vibration within limits and other parameters of
the affected engine become abnormal or exceed operating
limits:
ENGINE SHUTDOWN Procedure........................ CONSIDER
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 24
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
ENGINE AIRSTART
NOTE: – After an engine airstart, if flight conditions permit
operate the engine at idle for 2 minutes prior to apply
engine thrust.
– Engine Starts at altitudes between 20000 and 21000 ft
are more reliable with ITT above 50°C.
Autothrottle.............................................................. DISENGAGE
Airstart Envelope..................................................... CHECK
ENGINE AIRSTART ASSISTED?
No
Yes
N2 (Operative Engine)............................................ MIN 80%
Inoperative engine:
Ignition.................................................................. OVRD
Start/Stop Selector................................................ START, THEN
RUN
ENGINE NORMAL START?
No
Yes
After engine stabilizes at idle:
Ignition.................................................................. AUTO
Autothrottle............................................................ AS REQUIRED
Transponder.......................................................... TA/RA
END
Start/Stop Selector.................................................. STOP
Ignition..................................................................... AUTO
AOM-1502-016
Fuel......................................................................... BALANCE
Transponder............................................................ TA ONLY
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 25
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
...CONTINUED
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
END
Perform a windmilling start:
Xbleed Button....................................................... PUSH OUT
APU Bleed Button (if engine 1 affected).............. PUSH OUT
Inoperative engine:
N2..................................................................... MIN 7.2%
Ignition.............................................................. OVRD
Start/Stop Selector........................................... START, THEN
RUN
NOTE: – During engine auto relight, if N2 is steady accelerating
while ITT remains within start limit, the start is
progressing normally.
– During inflight starts, FADEC has no protection for hot
starts, hung starts or failure to light off.
– Crew must take appropriate action in case of abnormal
engine indications.
ENGINE NORMAL START?
No
Yes
After engine stabilizes at idle:
Xbleed Button....................................................... PUSH IN
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO
BACKPRESSURE FROM APU BLEED
NOTE: If the APU is ON, maintain the APU Bleed Button pushed
OUT.
"
APU Bleed Button................................................. PUSH IN
Autothrottle............................................................ AS REQUIRED
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 26
Non Annunciated
REVISION 23
AOM-1502-016
Ignition.................................................................. AUTO
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Transponder.......................................................... TA/RA
END
Xbleed Button......................................................... PUSH IN
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO
BACKPRESSURE FROM APU BLEED
NOTE: If the APU is ON, maintain the APU Bleed Button pushed
OUT.
"
APU Bleed Button................................................... PUSH IN
Start/Stop Selector.................................................. STOP
Ignition..................................................................... AUTO
Fuel......................................................................... BALANCE
Transponder............................................................ TA ONLY
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................. ACCOMPLISH
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 27
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENGINE AIRSTART ENVELOPE
30000
REGION 1 − REQUIRED MAXIMUM ITT FOR START IS 90°C.
REGION 2 − REQUIRED MINIMUM ITT FOR START IS 50°C.
25000
2
265 KIAS
320 KIAS
21000 ft
ALTITUDE − ft
20000
125 KIAS
17500 ft
15000
195 KIAS
1
ASSISTED OR
WINDMILLING
START
10000
ASSISTED
START ONLY
8000 ft
50
100
150
200
250
300
INDICATED AIRSPEED − KIAS
350
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 28
Non Annunciated
REVISION 23
AOM-1502-016
0
EM170AOM040003D.DGN
5000
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
ENGINE ITT OVERTEMPERATURE
CONDITION:
ITT pointer in white, dial and readout in red
inverse video.
Autothrottle.............................................................. DISENGAGE
Associated Thrust Lever......................................... REDUCE
Reduce thrust to keep ITT within limits.
Transponder............................................................ TA ONLY
ITT WITHIN LIMITS?
No
Yes
END
ENGINE SHUTDOWN Procedure........................ ACCOMPLISH
END
ENGINE OIL OVERTEMPERATURE
Autothrottle.............................................................. DISENGAGE
Associated Thrust Lever......................................... ADJUST TO
KEEP
TEMPERATURE
WITHIN LIMITS
AOM-1502-016
NOTE: If oil temperature rise follows thrust reduction, advancing
the thrust lever may reduce oil temperature.
Transponder............................................................ TA ONLY
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 29
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
OVERTEMPERATURE REMAINS?
No
Yes
If other parameters of affected engine become abnormal or
exceed operating limits:
ENGINE SHUTDOWN Procedure........................ ACCOMPLISH
END
END
ENGINE OIL PRESSURE ABNORMAL INDICATION
INDICATION:
Oil pressure indication on EICAS is displayed in
amber dashes or displays zero PSI.
ENG 1 (2) OIL LO PRESS MESSAGE PRESENTED?
No
Yes
ENGINE SHUTDOWN Procedure........................... ACCOMPLISH
END
Engine Parameters................................................. MONITOR
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 30
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
ENGINE SHUTDOWN
LAND AT THE NEAREST SUITABLE AIRPORT.
Autothrottle.............................................................. DISENGAGE
Affected Engine:
Thrust Lever.......................................................... IDLE
Start/Stop Selector................................................ STOP
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Associated Fuel Pump............................................ AUTO
Fuel......................................................................... BALANCE
Transponder............................................................ TA ONLY
When appropriate:
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 31
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENGINE TAILPIPE FIRE
CONDITION:
Tailpipe fire was detected visually by crew or
ground personnel. No EICAS message
displayed.
Affected Engine:
Thrust Lever.......................................................... IDLE
Start/Stop Selector................................................ STOP
Ignition.................................................................. OFF
Start/Stop Selector................................................ START, then
RUN
ITT........................................................................... MONITOR
ATC......................................................................... NOTIFY
........................................Wait 90 Seconds........................................
Associated Start/Stop Selector............................... STOP
NOTE: If fire is not extinguished while the engine is motored, it
must be extinguished using ground equipment, and
maintenance procedures applied.
END
GEAR LEVER CAN NOT BE MOVED UP
LG WOW SYS FAIL MESSAGE DISPLAYED?
No
Yes
Landing Gear Lever................................................ DOWN
NOTE: The DN LOCK REL button may be pressed to move the
landing gear lever up if climb performance is required to
clear obstacles.
LG WOW SYS FAIL Procedure.............................. ACCOMPLISH
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 32
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
DN LOCK REL Button............................................ PRESS and
HOLD
Landing Gear Lever................................................ UP
DN LOCK REL Button............................................ RELEASE
END
!O.B Nº 170-011/08 - IESS operation with RAT deployed
IESS ATTITUDE OSCILLATION WITH RAT
DEPLOYED
Maintain leveled flight:
Airspeed................................................................ MAINTAIN
CURRENT
SPEED
CAGE Button........................................................ PRESS AND
HOLD FOR 2
SECONDS
........................................Wait 10 seconds........................................
IESS ATTITUDE INDICATION OSCILLATION PERSISTS?
No
Yes
Maintain leveled flight:
Airspeed................................................................ REDUCE OR
INCREASE BY
15 KIAS
CAGE Button........................................................ PRESS AND
HOLD FOR 2
SECONDS
........................................Wait 10 seconds........................................
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 33
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
END
"
IMPAIRED OR CRACKED WINDSHIELD
Affected Windshield Heating Button....................... PUSH OUT
Cockpit Door .......................................................... CLOSE
NOTE: There is a windshield heating wire between the middle and
outer layers that can be used as a reference to determine
which layer is cracked. If the wire can be seen without a gap
the crack is in the outer layer, and if there is a wire
discontinuity, the crack may be located in the middle and/or
inner layers.
ONLY OUTER LAYER CRACKED?
No
Yes
END
CAUTION: ACCOMPLISH THE DESCENT IN A MAXIMUM OF 15
MINUTES.
Airspeed.................................................................. MAX 220 KIAS
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
During Descent:
Pressurization Mode Selector............................... MAN
Cabin Altitude........................................................ INCREASE
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 34
Non Annunciated
REVISION 23
AOM-1502-016
NOTE: Maintain cabin altitude at 10000 ft while descending the
airplane.
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
At or below 10000 ft:
Pack 1 Button....................................................... PUSH OUT
Pack 2 Button....................................................... PUSH OUT
No
ONLY ONE SIDE IMPAIRED
Yes
Pilot flying must be on the non-impaired side.
END
Airspeed.................................................................. MAX 140 KIAS
Direct Vision Window.............................................. OPEN
END
!O.B Nº 170-003/11 - Continuous in flight LANDING GEAR aural warning due to
radar altimeter misbehavior
"LANDING GEAR" AURAL CAN NOT BE
CANCELED
CONDITION:
Continuous LANDING GEAR aural warning with
no RALT 1 (2) FAIL EICAS message.
Crosscheck both LH and RH PFD RALT digital readouts for any
non-reliable readings.
FLYING ABOVE 2500 ft AGL?
No
Yes
AOM-1502-016
LH PFD RALT NON-RELIABLE READINGS?
No
Yes
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 35
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Radar Altimeter 1 Electronic CB............................. OUT
NOTE: Select on the MCDU: CB → CB MENU → CB BY SYSTEM
→ NAV → RALT 1.
RALT 1 (2) FAIL Procedure..................................... ACCOMPLISH
END
Radar Altimeter 2 Electronic CB............................. OUT
NOTE: Select on the MCDU: CB → CB MENU → CB BY SYSTEM
→ NAV → RALT 2.
RALT 1 (2) FAIL Procedure..................................... ACCOMPLISH
END
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 36
Non Annunciated
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
LOSS OF APU INDICATIONS
CONDITION:
APU RPM or APU EGT indication on EICAS is
displayed in amber dashes.
APU ESSENTIAL FOR THE FLIGHT?
No
Yes
Monitor the APU for the remainder of the flight. If any APU fault
message is displayed on EICAS:
APU Emergency Stop Button................................. PUSH IN
APU Master Selector.............................................. OFF
Do not restart the APU.
END
LOSS OF COMMUNICATIONS
ACP 1 BKUP Button............................................... PUSH OUT
AND ADJUST
VOLUME
NOTE: Only VHF1 is available for the Captain.
ACP 2 BKUP Button............................................... PUSH OUT
AND ADJUST
VOLUME
!Airplanes without Dual HF installation
NOTE: Only VHF2 is available for the First Officer.
"
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 37
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
LOSS OF HYDRAULIC SYSTEM 1
Autopilot.................................................................. DISENGAGE
NOTE: – Expect lower roll rates and lower speedbrake efficiency.
– Do not accomplish the SPOILER FAULT procedure.
– Do not command the engine 1 reverser.
Relevant Inoperative Items:
Autopilot
Engine 1 Reverser
Ground Spoiler L2 and R2
Multi Function Spoilers L3, R3,
L4 and R4
Outboard Brakes
Plan a long final approach.
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.76.
UNFACTORED
END
LOSS OF HYDRAULIC SYSTEM 2
NOTE: – Expect lower roll rates and lower speedbrake efficiency.
– Do not accomplish the SPOILER FAULT procedure.
– Do not command the engine 2 reverser.
Relevant Inoperative Items:
Ground Spoilers L1 and R1
Inboard Brakes
Landing Gear Retraction and
Normal Extension
(Fluid quantity loss only)
Multi Function Spoilers L5 and
R5
Nosewheel Steering
Plan a long final approach.
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 38
Non Annunciated
REVISION 23
AOM-1502-016
Engine 2 Reverser
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Landing configuration:
Landing Gear Lever.............................................. DOWN
LANDING GEAR FAILED TO EXTEND AND LOCK DOWN?
No
Yes
Alternate Gear Extension Lever........................... PULL
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.66.
UNFACTORED
If a go around is required:
Landing Gear........................................................ DOWN
NOTE: If hydraulic system 2 still has hydraulic fluid, the PTU may
be available to retract the landing gear in the event of a
go-around.
END
LOSS OF HYDRAULIC SYSTEM 3
Relevant Inoperative Items:
Outboard Aileron Actuators.
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 39
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
LOSS OF HYDRAULIC SYSTEM 1 AND 2
LAND AT THE NEAREST SUITABLE AIRPORT.
NOTE: – Expect lower roll and pitch rates.
– Do not accomplish the ELEVATOR FAULT and the
SPOILER FAULT procedures.
– Apply the Emergency/Parking Brake to stop the airplane
monitoring the Emergency/Parking Brake light.
– Braking action starts after Emergency/Parking Brake light
illumination. Apply the brake carefully since the Anti-Skid
protection is not available.
Relevant Inoperative Items:
Multi Function Spoilers L3, R3,
L4, R4, L5 and R5
Autopilot
Engine 1 and Engine 2
Nosewheel Steering
Reversers
Ground Spoilers L1, R1, L2 and
Outboard and Inboard Brakes
R2
Landing Gear Retraction and
Speedbrake
Normal Extension
L.H. Elevator
Plan a long final approach.
Landing configuration:
Landing Gear Lever.............................................. DOWN
Alternate Gear Extension Lever........................... PULL
Slat/Flap................................................................ 5
Set VREF = VREF
•
•
+ 10 KIAS.
AVOID
LANDING
WITH
CROSSWIND
COMPONENTS ABOVE 10 KT.
MULTIPLY THE FULL FLAPS UNFACTORED
LANDING DISTANCE BY 2.46.
If a go around is required:
Landing Gear Lever.............................................. DOWN
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 40
Non Annunciated
REVISION 23
AOM-1502-016
CAUTION:
FULL
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Slat/Flap................................................................ 4
Airspeed................................................................ VREF FULL +
10 KIAS
Maintain go-around configuration until the acceleration altitude is
reached.
END
LOSS OF HYDRAULIC SYSTEM 1 AND 3
LAND AT THE NEAREST SUITABLE AIRPORT.
Autopilot.................................................................. DISENGAGE
NOTE: – Expect lower roll rates and lower speedbrake efficiency.
– Do not accomplish the SPOILER FAULT procedure.
– Do not command the engine 1 reverser.
Relevant Inoperative Items:
Autopilot
Engine 1 Reverser
Ground Spoilers L2 and R2
Multi Function Spoilers L3, R3,
L4 and R4
Outboard aileron actuators.
Outboard Brakes
Rudder
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF
CAUTION:
•
•
FULL
+ 10 KIAS.
AVOID
LANDING
WITH
CROSSWIND
COMPONENTS ABOVE 10 KT.
MULTIPLY THE FULL FLAPS UNFACTORED
LANDING DISTANCE BY 2.11.
AOM-1502-016
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 41
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
LOSS OF HYDRAULIC SYSTEM 2 AND 3
LAND AT THE NEAREST SUITABLE AIRPORT.
NOTE: – Expect lower roll and pitch rates and lower speedbrake
efficiency.
– Do not accomplish the ELEVATOR FAULT and the
SPOILER FAULT procedures.
– Do not command the engine 2 reverser.
Relevant Inoperative Items:
Ailerons
Autopilot
Engine 2 Reverser
Ground Spoilers L1 and R1
Inboard Brakes
Landing Gear Retraction and
Normal Extension
(Sys 2 fluid quantity loss only)
Multi Function Spoilers L5 and
R5
NoseWheel Steering
R.H. Elevator
Plan a long final approach.
Landing configuration:
Landing Gear Lever.............................................. DOWN
LANDING GEAR FAILED TO EXTEND AND LOCK DOWN?
No
Yes
Alternate Gear Extension Lever........................... PULL
Slat/Flap................................................................ 5
CAUTION:
•
FULL
+ 10 KIAS.
AVOID
LANDING
WITH
COMPONENTS ABOVE 10 KT.
CROSSWIND
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 42
Non Annunciated
REVISION 23
AOM-1502-016
Set VREF = VREF
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
...CONTINUED
•
MULTIPLY THE FULL FLAPS UNFACTORED
LANDING DISTANCE BY 1.96.
If a go around is required:
Landing Gear Lever.............................................. DOWN
Slat/Flap................................................................ 4
Airspeed................................................................ VREF FULL +
10 KIAS
NOTE: If hydraulic system 2 still has hydraulic fluid, the PTU may
be available to retract the landing gear in the event of a
go-around.
END
LOSS OF PRESSURIZATION INDICATION
CONDITION:
Cabin altitude or cabin ∆P is not being
presented, or during use of the pressurization
manual control.
NOTE: This table must be used to control the cabin altitude/∆P,
when operating in manual mode only.
AIRPLANE/CABIN ALTITUDE CONVERSION TABLE
AOM-1502-016
AIRPLANE ALTITUDE (ft)
10000
11000
12000
13000
14000
15000
16000
17000
18000
19000
20000
CABIN ALTITUDE
(ft)
900
1000
1200
1300
1500
1700
1900
2100
2300
2600
2800
DIFFERENTIAL
PRESSURE (psid)
4.2
4.5
4.8
5.1
5.3
5.6
5.8
6.0
6.2
6.4
6.6
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 43
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
AIRPLANE ALTITUDE (ft)
21000
22000
23000
24000
25000
26000
27000
28000
29000
30000
31000
32000
33000
34000
35000
36000
37000
38000
39000
40000
41000
CABIN ALTITUDE
(ft)
3000
3300
3600
3900
4200
4500
4800
5100
5400
5700
6000
6300
6700
7000
7300
7600
8000
8000
8000
8000
8000
DIFFERENTIAL
PRESSURE (psid)
6.7
6.9
7.0
7.1
7.2
7.3
7.4
7.5
7.5
7.6
7.7
7.7
7.7
7.8
7.8
7.8
7.8
8.0
8.1
8.3
8.4
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 44
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
!O.B Nº 170-006/05 - AP quick disconnect button malfunctions
NON ANNUNCIATED LOSS OF ALL TRIMS AND
AUTOPILOT
Pitch Trim System 1 Cutout Button........................ PUSH IN
PITCH TRIM NORMAL?
Yes
No
Relevant Inoperative Items:
Autopilot
Pitch trim indication
Roll trim
Yaw trim
END
Pitch Trim System 1 Cutout Button........................ PUSH OUT
Pitch Trim System 2 Cutout Button........................ PUSH IN
Relevant Inoperative Items:
Autopilot
Pitch trim indication
Roll trim
Yaw trim
END
AOM-1502-016
"
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 45
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ONE ENGINE INOPERATIVE APPROACH AND
LANDING
Descent:
Landing Data ....................................................... SET
Approach Aids....................................................... SET
Altimeters ............................................................. SET/CHECK
Landing Configuration:
Landing Gear........................................................ DOWN
Slat/Flap................................................................ 5
Set VREF = VREF
FULL
+ 20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.37.
UNFACTORED
If a go around is required:
TOGA Button........................................................ PRESS
Thrust Levers........................................................ TO/GA
Rotate the airplane following the flight director guidance.
NOTE: In case of flight director guidance is inoperative, rotate the
airplane to 8° nose up.
Slat/Flap................................................................ 2
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 46
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
OXYGEN LEAKAGE
CONDITION:
Evidence of oxygen leakage through the crew
masks, mask hose, flow indicator (blinker), or
oxygen lines.
No Smoking............................................................ ON
Oxygen Test/Reset Button...................................... ACTUATE
Altitude.................................................................... AS REQUIRED
END
PARTIAL OR GEAR UP LANDING
NOTE: – Plan to land on available gear.
– Burn off fuel to reduce touchdown speed.
Prior to approach:
Cabin Crew........................................................... NOTIFY
Aural Warning CBs (C7; C31).............................. PULL
APU....................................................................... OFF
Pressurization Dump Button ................................ PUSH IN
Landing Configuration:
Landing Gear Lever.............................................. DOWN
Slat/Flap................................................................ FULL
Just Before Touchdown:
Cabin..................................................................... ANNOUNCE
IMPACT
After Landing:
Thrust Levers........................................................ IDLE
Start/Stop Selectors.............................................. STOP
Fire Extinguishing Handles................................... PULL and
ROTATE
AOM-1502-016
Emergency Evacuation......................................... ANNOUNCE
Batteries................................................................ OFF
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 47
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
...CONTINUED
If a go around is required:
Landing Gear Lever.............................................. DOWN
END
STRUCTURAL DAMAGE
LAND AT THE NEAREST SUITABLE AIRPORT.
Airspeed.................................................................. MAX VA
Maneuvering speed (VA) table:
VA - EMBRAER 190
ALTITUDE (ft)
ABOVE 32500
32500
30000
25000
20000
15000
10000
5000
0
SPEED (KIAS)
MMO = 0.82
295
292
285
278
272
264
257
250
Avoid high maneuvering loads.
FUSELAGE IS DAMAGED?
No
Yes
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 48
Non Annunciated
REVISION 23
AOM-1502-016
When reaching 10000 ft:
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
...CONTINUED
Pressurization Dump Button................................. PUSH IN
Establish landing configuration early.
END
UNRELIABLE AIRSPEED
Autothrottle.............................................................. DISENGAGE
Avoid quick Thrust Lever movements.
Autopilot.................................................................. DISENGAGE
Flight Director.......................................................... OFF
Yaw Damper........................................................... OFF
CAUTION: AVOID USING THE SPEEDBRAKE.
Attitude/Thrust......................................................... ADJUST
Maintain airplane control. Refer to Unreliable Airspeed tables.
Altitude and/or Vertical Speed indications may also be unreliable.
Ground speed indication is available on the PFD for reference.
GPS altitude may also be used as a reference if PFD indication is
unreliable.
UNRELIABLE AIRSPEED TABLES
CLIMB, Flaps UP, CLB-1 Thrust Rating Mode
PRESSURE
ALTITUDE (FT)
Pitch ATT
0
(250
V/S
KIAS) (ft/min)
10000
Pitch ATT
AOM-1502-016
(250
V/S
KIAS) (ft/min)
70000
80000
WEIGHT (LB)
90000
100000
110000
120000
14
12
12
11
11
10
5900
5100
4400
3900
3400
3000
7
6
6
6
6
7
3100
2700
2300
1900
1700
1500
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 49
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
PRESSURE
ALTITUDE (FT)
20000 Pitch ATT
(290
V/S
KIAS) (ft/min)
30000
Pitch ATT
(0.75
V/S
Mach) (ft/min)
40000
Pitch ATT
(0.75
V/S
Mach) (ft/min)
70000
80000
WEIGHT (LB)
90000
100000
110000
120000
4
4
4
4
4
4
3300
2700
2300
2000
1700
1500
3
3
3
3
3
3
2400
2000
1600
1300
1000
700
-
-
-
-
3
4
1000
600
CRUISE, Flaps UP, %N1 for Level Flight
(250
KIAS)
15000
(270
KIAS)
20000
(270
KIAS)
25000
(270
KIAS)
30000
(0.70
Mach)
35000
(0.70
Mach)
40000
(0.70
Mach)
%N1
70000
80000
WEIGHT (LB)
90000
100000
110000
120000
1
1
2
2
3
4
63.6
64.6
65.7
67.0
68.4
69.8
Pitch ATT
0
1
1
2
2
3
%N1
70.1
70.9
71.8
72.6
74.0
75.3
Pitch ATT
0
1
1
2
2
3
%N1
73.6
74.5
75.5
76.6
77.7
78.7
Pitch ATT
0
1
1
2
2
3
%N1
77.3
78.3
79.1
80.2
81.5
82.9
Pitch ATT
1
1
2
2
3
3
%N1
80.0
81.0
82.2
83.5
84.7
86.1
Pitch ATT
2
2
3
4
4
%N1
80.4
81.9
83.1
86.1
88.6
-
-
-
Pitch ATT
3
4
%N1
83.3
86.2
-
-
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 50
Non Annunciated
REVISION 23
AOM-1502-016
PRESSURE
ALTITUDE (FT)
10000
Pitch ATT
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NON ANNUNCIATED
PROCEDURES
...CONTINUED
DESCENT, Flaps UP, IDLE Thrust
PRESSURE
70000
ALTITUDE (FT)
Pitch ATT
0
-3
(250
V/S
-1700
KIAS) (ft/min)
10000
Pitch ATT
-2
(250
V/S
-1300
KIAS) (ft/min)
20000
Pitch ATT
-5
(290
V/S
-3000
KIAS) (ft/min)
30000
Pitch ATT
-4
(0.75
V/S
-3000
Mach) (ft/min)
40000
Pitch ATT
-1
(0.75
V/S
-2800
Mach) (ft/min)
80000
WEIGHT (LB)
90000
100000
110000
120000
-3
-2
-1
0
0
-1600
-1500
-1600
-1400
-1400
-1
0
0
1
2
-1200
-1100
-1100
-1100
-1100
-4
-3
-3
-2
-1
-2900
-2600
-2600
-2400
-2300
-3
-3
-2
-2
-1
-3000
-3000
-3000
-3000
-3000
-1
0
1
2
3
-2700
-2600
-2600
-2600
-2700
110000
6
120000
5
63.0
210
64.6
220
HOLDING, %N1 for Level Flight
PRESSURE
ALTITUDE (FT)
Pitch ATT
5000
10000
%N1
KIAS
70000
2
80000
3
WEIGHT (LB)
90000
100000
4
5
54.0
210
56.2
210
58.7
210
61.6
210
Pitch ATT
2
3
4
5
6
6
%N1
KIAS
57.6
210
59.9
210
62.5
210
65.3
210
66.7
210
68.2
220
TERMINAL AREA (5000FT Pressure Altitude), Gear UP, %N1 for
Level Flight
SLAT/FLAP POSITION
(VREF FULL +
INCREMENT)
SLAT/FLAP 0
(VREF FULL
+ 60)
SLAT/FLAP 1
AOM-1502-016
(VREF FULL
+ 35)
WEIGHT (LB)
70000
80000
90000
100000
Pitch ATT
6
6
7
7
%N1
50.9
53.9
56.8
59.5
Pitch ATT
6
7
7
8
%N1
53.8
57.2
60.4
63.1
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 51
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
SLAT/FLAP POSITION
(VREF FULL +
INCREMENT)
SLAT/FLAP 2
(VREF FULL
+ 25
SLAT/FLAP 3
(VREF FULL
+ 20)
SLAT/FLAP 4
(VREF FULL
+ 10)
WEIGHT (LB)
70000
80000
90000
100000
Pitch ATT
7
8
8
8
%N1
54.3
57.9
61.2
64.0
Pitch ATT
5
6
6
6
%N1
56.7
60.3
63.5
66.3
Pitch ATT
8
8
8
9
%N1
57.7
61.4
64.7
67.5
FINAL APPROACH (1500FT Pressure Altitude), Gear Down, %N1
for 3° GLIDESLOPE
SLAT/FLAP POSITION
(VREF FULL +
INCREMENT)
SLAT/FLAP 5
(VREF FULL
+ 10)
WEIGHT (LB)
70000
80000
90000
100000
Pitch ATT
5
6
6
6
%N1
47.0
49.9
52.4
54.9
SLAT/FLAP
FULL
Pitch ATT
1
2
2
2
(VREF FULL
+ 10)
%N1
51.6
54.6
57.4
60.1
NOTE: With the airplane stabilized under correct pitch attitude
and power setting, the crew should crosscheck the
instruments in order to identify any possible reliable
instrument. In case a reliable source is identified, ADS
reversion may be attempted.
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 52
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
VOLCANIC ASH
LAND AT THE NEAREST SUITABLE AIRPORT.
Volcanic Ash Area................................................... EXIT/AVOID
Consider performing a 180° turn.
Crew Oxygen Masks (if necessary)........................ DON, 100%
If a significant amount of volcanic ash fills the cockpit, or if there
is a strong smell of sulphur, don an oxygen mask and select
100%.
Ignition Selectors.................................................... OVRD
Autothrottle.............................................................. DISENGAGE
Ice Protection Mode Selector................................. ON
If altitude permits:
Thrust Lever.......................................................... IDLE
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Recirculation Button................................................ PUSH OUT
ITT........................................................................... MONITOR
ITT INCREASING EVEN WITH AFFECTED ENGINE IN IDLE?
No
Yes
ENGINE SHUTDOWN Procedure........................... ACCOMPLISH
ANY ENGINE FLAMEOUT?
No
AOM-1502-016
Yes
Ice Protection Mode Selector.................................. AUTO
CONTINUED...
4-02-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Non Annunciated
Page 53
EMERGENCY AND
ABNORMAL PROCEDURES
NON ANNUNCIATED
PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
ENG 1 (2) FAIL or DUAL ENGINE FAILURE
Procedure................................................................ ACCOMPLISH
ABNORMAL AIRSPEED INDICATIONS?
No
Yes
UNRELIABLE AIRSPEED Procedure..................... ACCOMPLISH
END
4-02-01
Copyright © by Embraer. Refer to cover page for details.
Page 54
Non Annunciated
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE GENERAL (CARGO
COMPARTMENT/DOORS/LIGHTING)
TABLE OF CONTENTS
Block
Page
WARNING
DOOR CRG FWD (AFT) OPEN.............................. 4-03-01......
1
DOOR EMER LH (RH) OPEN ................................ 4-03-01......
2
DOOR PAX (SERV) FWD (AFT) OPEN .................. 4-03-01......
3
CAUTION
DOOR CENTER (FWD) EBAY OPEN .....................
DOOR HYD OPEN ................................................
EMER LT NOT ARMED..........................................
EMER LT ON ........................................................
4
4
4
4
4-03-01......
4-03-01......
4-03-01......
4-03-01......
AOM-1502-016
ADVISORY
DOOR FUELING OPEN ........................................ Crew Awareness
EMER LT BATT FAULT ......................................... Crew Awareness
4-03-01-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 11
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-01-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 11
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
DOOR CRG FWD (AFT) OPEN
NORMAL PRESSURIZATION?
No
Yes
END
LAND AT THE NEAREST SUITABLE AIRPORT.
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
At 10000 ft :
Pressurization Dump Button................................. PUSH IN
AOM-1502-016
END
4-03-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 11
Airplane General (Cargo
Compartment/Doors/Lighting)
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
DOOR EMER LH (RH) OPEN
Fstn Belts Signs...................................................... ON
NORMAL PRESSURIZATION?
No
Yes
Check the affected door lock indicators.
MINIMUM OF 1 INDICATOR IN GREEN?
No
Yes
END
LAND AT THE NEAREST SUITABLE AIRPORT.
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
At 10000 ft:
Pressurization Dump Button................................. PUSH IN
4-03-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
Airplane General (Cargo
Compartment/Doors/Lighting)
REVISION 11
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
DOOR PAX (SERV) FWD (AFT) OPEN
Fstn Belts Signs...................................................... ON
NORMAL PRESSURIZATION?
No
Yes
Check the affected door lock and latch indicators.
MINIMUM OF 2 INDICATORS IN GREEN?
No
Yes
END
LAND AT THE NEAREST SUITABLE AIRPORT.
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
At 10000 ft:
Pressurization Dump Button................................. PUSH IN
AOM-1502-016
END
4-03-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 11
Airplane General (Cargo
Compartment/Doors/Lighting)
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
DOOR CENTER (FWD) EBAY OPEN
NORMAL PRESSURIZATION?
No
Yes
END
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
END
DOOR HYD OPEN
Airspeed.................................................................. MAX 250 KIAS
END
EMER LT NOT ARMED
Emergency Lights................................................... ARMED
END
EMER LT ON
4-03-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
Airplane General (Cargo
Compartment/Doors/Lighting)
REVISION 11
AOM-1502-016
Emergency Lights................................................... OFF, then
ARMED
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AOM-1502-016
END
4-03-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 11
Airplane General (Cargo
Compartment/Doors/Lighting)
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
DOOR FUELING OPEN
Crew Awareness.
END
EMER LT BATT FAULT
Crew Awareness.
4-03-01
Copyright © by Embraer. Refer to cover page for details.
Page 6
Airplane General (Cargo
Compartment/Doors/Lighting)
REVISION 11
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AMS - PNEUMATIC/AIR
CONDITIONING/PRESSURIZATION
TABLE OF CONTENTS
Block
Page
WARNING
AOM-1502-016
CABIN ALTITUDE HI ............................................. 4-03-02......
1
CAUTION
AMS CTRL FAIL ....................................................
BLEED 1 (2) FAIL ..................................................
BLEED 1 (2) LEAK ................................................
BLEED 1 (2) OVERPRESS ....................................
BLEED APU LEAK.................................................
CABIN DIFF PRESS FAIL......................................
CENTER EBAY FANS FAIL....................................
CRG FWD VENT FAIL ...........................................
FWD EBAY FANS FAIL ..........................................
PACK 1 (2) FAIL ....................................................
PACK 2 LEAK .......................................................
PRESN AUTO FAIL ...............................................
PRESN MAN FAIL .................................................
PRESSURIZATION CONVERSION TABLE .............
RECIRC SMK DET FAIL ........................................
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
4-03-02......
ADVISORY
AMS CTRL FAULT ................................................
BLEED 1 (2) OFF .................................................
PACK 1 (2) OFF ...................................................
PRESN AUTO FAULT ...........................................
RAM AIR FAULT ...................................................
XBLEED FAIL .......................................................
XBLEED SW OFF.................................................
Crew Awareness
4-03-02...... 13
4-03-02...... 13
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
2
2
3
4
5
7
8
8
8
9
9
10
11
11
13
4-03-02-TOC
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REVISION 18
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-02-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 18
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
CABIN ALTITUDE HI
EICAS Indication: Cabin Altitude indication in red.
Aural Warning:
CABIN
Crew Oxygen Masks............................................ DON, 100%
Crew Communication........................................... ESTABLISH
Altitude.................................................................. 10000 ft or
MEA,
WHICHEVER
IS HIGHER
Thrust Levers........................................................ IDLE
Speed Brake......................................................... FULL OPEN
Airspeed................................................................ MAX/
APPROPRIATE
Transponder.......................................................... 7700
ATC....................................................................... NOTIFY
Cabin Altitude.......................................................... MONITOR
CABIN ALTITUDE REACHES 14500 ft?
No
Yes
Passenger Oxygen Selector................................... OVRD
At 10000 ft:
Pressurization DUMP Button................................ PUSH IN
AOM-1502-016
END
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AMS CTRL FAIL
CONDITION:
Cabin Pressurization and temperature control is
lost.
Icing Conditions...................................................... EXIT/AVOID
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
NOTE: Monitor Cabin Altitude and increase rate of descent
accordingly. An emergency descent may be required.
At 10000 ft:
Pressurization Dump Button................................. PUSH IN
NOTE: – Assisted crossbleed start is not available.
– Pneumatic assisted engine start with APU is not
available.
END
BLEED 1 (2) FAIL
Affected Bleed Button............................................. PUSH OUT
..........................................Wait 1 minute..........................................
BLEED 1 (2) FAIL MESSAGE EXTINGUISHES?
No
Yes
Affected Bleed Button............................................. PUSH IN
BLEED 1(2) FAIL MESSAGE REMAINS EXTINGUISHED?
No
Yes
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 2
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Affected Bleed Button............................................. PUSH OUT
BOTH BLEEDS AFFECTED?
No
Yes
Icing Conditions....................................................... EXIT/AVOID
APU......................................................................... START
Altitude.................................................................... MAX 15000 ft
END
Altitude.................................................................... MAX 31000 ft
END
BLEED 1 (2) LEAK
Light:
Amber striped bar illuminates inside the affected
bleed button.
Affected Bleed Button............................................. PUSH OUT
XBleed Button......................................................... PUSH OUT
BLEED 1 LEAK?
No
Yes
APU Bleed Button................................................... PUSH OUT
AOM-1502-016
Icing Conditions...................................................... EXIT/AVOID
Altitude.................................................................... MAX 31000 ft
.........................................Wait 3 minutes.........................................
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
BLEED 1 (2) LEAK MESSAGE EXTINGUISHES?
No
Yes
END
NOTE: Consider the possibility of leaking occurring in the opposite
side.
Opposite Side Bleed Button................................... PUSH OUT
APU Bleed Button................................................... PUSH OUT
Altitude.................................................................... 10000 FT OR
MEA
WHICHEVER
IS HIGHER
At 10000 ft:
Pressurization Dump Button................................... PUSH IN
END
BLEED 1 (2) OVERPRESS
Affected Bleed Button............................................. PUSH OUT
then IN
BLEED 1 (2) OVERPRESS MESSAGE EXTINGUISHES?
No
Yes
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 4
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Affected Bleed Button............................................. PUSH OUT
APU Bleed Button (if applicable)............................ PUSH OUT
XBleed Button......................................................... PUSH OUT
Icing Conditions...................................................... EXIT/AVOID
Altitude.................................................................... MAX 31000 ft
BLEED 1 (2) OVERPRESS MESSAGE EXTINGUISHES?
No
Yes
END
Associated Thrust Lever......................................... IDLE
Transponder............................................................ TA ONLY
When applicable:
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
END
BLEED APU LEAK
APU Bleed Button................................................... PUSH OUT
.........................................Wait 3 minutes.........................................
BLEED APU LEAK MESSAGE EXTINGUISHES?
No
Yes
AOM-1502-016
END
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
APU Emergency Stop Button................................. PUSH IN
APU......................................................................... OFF
BLEED APU LEAK MESSAGE EXTINGUISHES?
No
Yes
END
Bleed 1 Button........................................................ PUSH OUT
XBleed Button......................................................... PUSH OUT
Verify BLEED 1 OFF and XBLEED SW OFF messages displayed
on EICAS.
Icing Conditions...................................................... EXIT/AVOID
Altitude.................................................................... MAX 31000 ft
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 6
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
CABIN DIFF PRESS FAIL
EICAS Indication: Abnormal cabin altitude indication may be
presented.
If Cabin Differential Pressure red limit is reached:
CABIN DIFFERENTIAL PRESSURE POSITIVE?
No
Yes
Pack 1 Button.......................................................... PUSH OUT
Pack 2 Button.......................................................... PUSH OUT
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
END
Airplane Descent Rate............................................ REDUCE
AOM-1502-016
END
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
CENTER EBAY FANS FAIL
LAND AT THE NEAREST SUITABLE AIRPORT.
END
CRG FWD VENT FAIL
LAND AT THE NEAREST SUITABLE AIRPORT.
END
FWD EBAY FANS FAIL
TRU 1 (2) FAIL MESSAGE DISPLAYED?
No
Yes
LAND AT THE NEAREST SUITABLE AIRPORT.
END
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 8
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
PACK 1 (2) FAIL
Associated Temperature Controller........................ 12 O’CLOCK
Affected Pack Button.............................................. PUSH OUT
.........................................Wait 1 minute.........................................
Affected Pack Button.............................................. PUSH IN
PACK 1 (2) FAIL MESSAGE EXTINGUISHES?
No
Yes
After 1 minute:
Associated Temperature Controller...................... OPERATE
NORMALLY
END
Affected Pack Button.............................................. PUSH OUT
Altitude.................................................................... MAX 31000 ft
END
PACK 2 LEAK
Pack 2 Button......................................................... PUSH OUT
Altitude.................................................................... MAX 31000 ft
.........................................Wait 3 minutes.........................................
PACK 2 LEAK MESSAGE EXTINGUISHES?
No
Yes
AOM-1502-016
END
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Icing Conditions...................................................... EXIT/AVOID
Bleed 2 Button........................................................ PUSH OUT
XBleed Button......................................................... PUSH OUT
END
PRESN AUTO FAIL
EICAS Indication: Landing Field Elevation indications showing
amber dashes.
Pressurization Mode Selector................................. MAN, THEN
AUTO
PRESN AUTO FAIL MESSAGE EXTINGUISHES?
No
Yes
END
Pressurization Mode Selector................................. MAN
Cabin Alt Controller................................................. AS REQUIRED
Operate the cabin altitude control knob to set pressurization
according to the PRESSURIZATION CONVERSION TABLE.
When appropriate:
Cabin Alt Controller............................................... HOLD UP FOR
50 s
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 10
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
PRESN MAN FAIL
Altitude ................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
At 25000 ft:
Pack 1 Button....................................................... PUSH OUT
At 10000 ft:
Pack 2 Button....................................................... PUSH OUT
END
PRESSURIZATION CONVERSION TABLE
NOTE: This table must be used to control the cabin altitude/ ∆P
when operating in manual mode only.
AIRPLANE/CABIN ALTITUDE CONVERSION TABLE
AOM-1502-016
AIRPLANE ALTITUDE (ft)
10000
11000
12000
13000
14000
15000
16000
17000
18000
19000
20000
21000
22000
23000
CABIN ALTITUDE
(ft)
900
1000
1200
1300
1500
1700
1900
2100
2300
2600
2800
3000
3300
3600
DIFFERENTIAL
PRESSURE (psid)
4.2
4.5
4.8
5.1
5.3
5.6
5.8
6.0
6.2
6.4
6.6
6.7
6.9
7.0
CONTINUED...
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
AIRPLANE ALTITUDE (ft)
24000
25000
26000
27000
28000
29000
30000
31000
32000
33000
34000
35000
36000
37000
38000
39000
40000
41000
CABIN ALTITUDE
(ft)
3900
4200
4500
4800
5100
5400
5700
6000
6300
6700
7000
7300
7600
8000
8000
8000
8000
8000
DIFFERENTIAL
PRESSURE (psid)
7.1
7.2
7.3
7.4
7.5
7.5
7.6
7.7
7.7
7.7
7.8
7.8
7.8
7.8
8.0
8.1
8.3
8.4
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 12
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
RECIRC SMK DET FAIL
Recirc Fan Button................................................... PUSH OUT
END
AMS CTRL FAULT
Crew Awareness.
END
BLEED 1 (2) OFF
Altitude.................................................................... MAX 31000 ft
END
PACK 1 (2) OFF
Altitude.................................................................... MAX 31000 ft
AOM-1502-016
END
4-03-02
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
AMS - Pneumatic/Air
Conditioning/Pressurization
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
PRESN AUTO FAULT
Crew Awareness.
END
RAM AIR FAULT
Crew Awareness.
END
XBLEED FAIL
Crew Awareness.
END
XBLEED SW OFF
Crew Awareness.
4-03-02
Copyright © by Embraer. Refer to cover page for details.
Page 14
AMS - Pneumatic/Air
Conditioning/Pressurization
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AUTOFLIGHT
TABLE OF CONTENTS
Block
Page
CAUTION
AP FAIL.................................................................
AP PITCH MISTRIM ..............................................
AP PITCH TRIM FAIL ............................................
AP ROLL MISTRIM................................................
AT FAIL .................................................................
AT NOT IN HOLD ..................................................
FD LATERAL MODE OFF ......................................
FD VERT MODE OFF............................................
SHAKER ANTICIPATED.........................................
STALL PROT FAIL.................................................
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
4-03-03......
ADVISORY
AFCS FAULT ........................................................
AFCS PANEL FAIL................................................
AFCS PANEL FAULT ............................................
AP FAULT.............................................................
AP PITCH TRIM FAULT ........................................
AP RUDDER NOT AVAIL.......................................
APPR 2 NOT AVAIL ..............................................
AT FAULT .............................................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
1
1
1
2
2
2
2
3
3
4
Airplanes equipped with Autoland 1 system
AOM-1502-016
AUTOLAND 1 NOT AVAIL .....................................
FD FAIL................................................................
FD FAULT.............................................................
SHAKER 1 (2) FAIL ..............................................
STALL PROT FAULT .............................................
YD FAIL................................................................
YD FAULT ............................................................
YD OFF ................................................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-03-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-03-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AP FAIL
Fly the airplane manually.
RVSM capability is lost.
NOTE: The AP may be available for re-engagement 10 seconds
after disengagement.
END
AP PITCH MISTRIM
Control Wheel......................................................... HOLD FIRMLY
A/P Disc Button ..................................................... PRESS
Pitch Trim................................................................ AS REQUIRED
Autopilot.................................................................. AS REQUIRED
END
AP PITCH TRIM FAIL
Control Wheel......................................................... HOLD FIRMLY
A/P Disc Button....................................................... PRESS
Pitch Trim................................................................ AS REQUIRED
Autopilot.................................................................. AS REQUIRED
AOM-1502-016
END
4-03-03
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoflight
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AP ROLL MISTRIM
Roll Trim.................................................................. AS REQUIRED
END
AT FAIL
Operate thrust levers manually.
NOTE: The AT may be available for re-engagement 10 seconds
after disengagement.
END
AT NOT IN HOLD
Disengage the autothrottle.
END
FD LATERAL MODE OFF
Select a flight director lateral mode.
4-03-03
Copyright © by Embraer. Refer to cover page for details.
Page 2
Autoflight
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FD VERT MODE OFF
Select a flight director vertical mode.
END
SHAKER ANTICIPATED
Avoid side slipping the airplane.
AIRSPEED ABOVE 0.5 M?
No
Yes
Airspeed.................................................................. MIN 250 KIAS
NOTE: Above 0.5 M, stick shaker and LSA are not Available.
FLAP FAIL MESSAGE PRESENTED?
No
Yes
FLAP FAIL Procedure............................................. ACCOMPLISH
END
SLAT FAIL MESSAGE PRESENTED?
No
Yes
SLAT FAIL Procedure.............................................. ACCOMPLISH
AOM-1502-016
END
CONTINUED...
4-03-03
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoflight
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
NOTE: Limit bank angle to 20° maximum.
END
STALL PROT FAIL
Condition:
Stick Shaker and AOA Limiting are inoperative.
Avoid side slipping the airplane.
Landing Configuration:
For flaps 5, set VREF = VREF
FULL
+ 15 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS UNFACTORED
LANDING DISTANCE BY 1.29.
For flaps FULL, set VREF = VREF FULL + 10 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.15.
UNFACTORED
4-03-03
Copyright © by Embraer. Refer to cover page for details.
Page 4
Autoflight
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AFCS FAULT
Crew Awareness
END
AFCS PANEL FAIL
Crew Awareness.
END
AFCS PANEL FAULT
Crew Awareness.
END
AP FAULT
Crew Awareness.
END
AP PITCH TRIM FAULT
Crew Awareness.
AOM-1502-016
END
4-03-03
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoflight
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AP RUDDER NOT AVAIL
Crew Awareness.
END
APPR 2 NOT AVAIL
Crew Awareness.
END
AT FAULT
Crew Awareness.
END
!Airplanes equipped with Autoland 1 system
AUTOLAND 1 NOT AVAIL
Crew Awareness.
END
4-03-03
Copyright © by Embraer. Refer to cover page for details.
Page 6
Autoflight
REVISION 21
AOM-1502-016
"
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ANNUNCIATED PROCEDURES
FD FAIL
Crew Awareness.
END
FD FAULT
Crew Awareness.
END
SHAKER 1 (2) FAIL
INADVERTENT SHAKER ACTUATION?
No
Yes
NOTE: – Autopilot may disengage.
Affected Shaker Cutout Button............................... PUSH IN
END
AOM-1502-016
END
4-03-03
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Autoflight
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
STALL PROT FAULT
Crew Awareness.
END
YD FAIL
Crew Awareness.
END
YD FAULT
Crew Awareness.
END
YD OFF
Crew Awareness.
4-03-03
Copyright © by Embraer. Refer to cover page for details.
Page 8
Autoflight
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AUXILIARY POWER UNIT
TABLE OF CONTENTS
Block
Page
CAUTION
MAU load 21.2 and on OR POST-MOD SB 190-31-0015
AOM-1502-016
APU ALTITUDE EXCEED ......................................
APU FAIL ..............................................................
APU FAULT...........................................................
APU OIL HI TEMP .................................................
APU OIL LO PRESS..............................................
4-03-04......
4-03-04......
4-03-04......
4-03-04......
4-03-04......
1
1
2
3
3
4-03-04-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-04-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
!MAU load 21.2 and on OR POST-MOD SB 190-31-0015
APU ALTITUDE EXCEED
APU IS ESSENTIAL FOR FLIGHT?
No
Yes
Descend until the message is no longer displayed.
END
APU......................................................................... OFF
END
"
APU FAIL
APU FAILED DURING START?
No
Yes
APU can be restarted according to the APU starter limitations.
END
APU......................................................................... OFF
Do not restart the APU.
AOM-1502-016
END
4-03-04
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Auxiliary Power Unit
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ANNUNCIATED PROCEDURES
APU FAULT
EICAS Indication: Abnormal APU
presented.
ABNORMAL INDICATION?
EGT
indication
may
be
No
Yes
APU Bleed Button................................................... PUSH OUT
..........................................Wait 1 minute..........................................
ABNORMAL INDICATION REMAINS?
No
Yes
APU Emergency Stop Button................................. PUSH IN
APU......................................................................... OFF
END
NOTE: If the APU is not essential for the flight, turn off the APU.
4-03-04
Copyright © by Embraer. Refer to cover page for details.
Page 2
Auxiliary Power Unit
REVISION 20
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
APU OIL HI TEMP
APU FAULT Procedure........................................... ACCOMPLISH
END
APU OIL LO PRESS
APU FAULT Procedure........................................... ACCOMPLISH
AOM-1502-016
END
4-03-04
Copyright © by Embraer. Refer to cover page for details.
REVISION 20
Auxiliary Power Unit
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-04
Copyright © by Embraer. Refer to cover page for details.
Page 4
Auxiliary Power Unit
REVISION 20
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ELECTRICAL
TABLE OF CONTENTS
Block
Page
WARNING
BATT 1 (2) OVERTEMP......................................... 4-03-05......
1
BATT 1-2 OFF ....................................................... 4-03-05......
1
BATT DISCHARGING ............................................ 4-03-05......
1
ELEC EMERGENCY.............................................. 4-03-05......
1
AOM-1502-016
CAUTION
AC BUS 1 OFF......................................................
AC BUS 2 OFF......................................................
AC ESS BUS OFF.................................................
AC STBY BUS OFF...............................................
APU GEN OFF BUS ..............................................
BATT 1 (2) DISCHARGING ....................................
BATT 1 (2) TEMP SENS FAULT .............................
BATT 1 OFF ..........................................................
BATT 2 OFF ..........................................................
DC BUS 1 OFF .....................................................
DC BUS 2 OFF .....................................................
DC ESS BUS 1 OFF..............................................
DC ESS BUS 2 OFF..............................................
DC ESS BUS 3 OFF..............................................
GPU CONNECTED ...............................................
IDG 1 (2) OFF BUS ...............................................
IDG 1 (2) OIL ........................................................
INVERTER FAIL ....................................................
RAT FAIL...............................................................
TRU 1 (2) FAIL ......................................................
TRU ESS FAIL ......................................................
4-03-05......
5
4-03-05......
5
4-03-05......
6
4-03-05......
6
4-03-05......
7
4-03-05......
7
Crew Awareness
4-03-05......
8
4-03-05......
8
4-03-05......
8
4-03-05......
9
4-03-05...... 10
4-03-05...... 11
4-03-05...... 13
4-03-05...... 14
4-03-05...... 14
4-03-05...... 15
Crew Awareness
Crew Awareness
4-03-05...... 16
4-03-05...... 16
ADVISORY
LOAD SHED......................................................... Crew Awareness
4-03-05-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
Block
Page
4-03-05-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
ADVISORY
REMOTE CB TRIP................................................ Crew Awareness
SPDA FAIL ........................................................... 4-03-05...... 17
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
BATT 1 (2) OVERTEMP
Associated Battery................................................ OFF
NOTE: Do not start the APU.
END
BATT 1-2 OFF
LAND AT THE NEAREST SUITABLE AIRPORT.
NOTE: APU start is not available.
END
BATT DISCHARGING
LAND AT THE NEAREST SUITABLE AIRPORT.
END
ELEC EMERGENCY
LAND AT THE NEAREST SUITABLE AIRPORT.
Airspeed.................................................................. MIN 150 KIAS
!O.B Nº 170-011/08 - IESS operation with RAT deployed
NOTE: When flying below 200 KIAS the IESS attitude indication
may oscillate. At any time this oscillation occurs perform the
IESS ATTITUDE OSCILLATION WITH RAT DEPLOYED
procedure.
AOM-1502-016
"
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
IDG 1 Selector........................................................ OFF, THEN
AUTO
IDG 2 Selector........................................................ OFF, THEN
AUTO
Emergency Lights................................................... OFF
CAUTION: ONLY TWO APU START ATTEMPTS ARE ALLOWED.
ELEC EMERGENCY MESSAGE PERSISTS?
No
Yes
BATT DISCHARGING MESSAGE PRESENTED?
No
Yes
RAT Manual Deploy Lever...................................... PULL
TRU 1 Switch ......................................................... OFF
TRU 2 Switch ......................................................... OFF
Icing Conditions....................................................... EXIT/AVOID
Altitude.................................................................... 10000 ft OR
MEA,
WHICHEVER
IS HIGHER
Relevant Inoperative Items:
IRS 2
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 2
Electrical
REVISION 23
AOM-1502-016
ADS 1 and 2
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Anti-Ice System
MCDU 1
Multi Function Spoilers L3, R3,
L4, R4, L5 and R5
NAVCOM 2
Nosewheel Steering
Pack 1 and 2
Pax Masks Auto Deploy
AOA Limit
Autopilot
Autothrottle
CCD 2
Display Unit 1, 4 and 5
Engine 1 and Engine 2
Reversers
Radio Altimeters 1 and 2
FMS 1
Flight Director 1 and 2
Fuel AC Pump 1
GPS 1
Ground Spoilers L1, R1, L2 and
R2
Hyd Sys 1 Elec Pump
Hyd Sys 2 Elec Pump
Hyd Sys 3 Elec Pump B
Ice Detectors 1 and 2
Electromechanical Door Latch
Service Interphone System
(Normal Mode)
Speedbrake
TAT 1 and 2
TCAS
Yaw Damper
Weather Radar
Windshear Detection
Windshield Heater 1 and 2
Windshield Wiper 1 and 2
NOTE: – Avoid side slipping the airplane.
– On ground, use differential braking and rudder to steer
the airplane.
– The slats and flaps will operate at low rate.
– The reinforced cockpit door can only be opened
manually.
Landing configuration:
Emergency Lights................................................. ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
LG WRN INHIB Button......................................... PUSH IN
Slat/Flap................................................................ 3
AOM-1502-016
Set VREF = VREF FULL + 20 KIAS or 130 KIAS (whichever is higher).
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 2.21.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ VREF FULL +
20 KIAS or
130 KIAS
(whichever is
higher)
END
Flight Controls Mode Buttons (Spoilers, Elevators
and Rudder).......................................................... PUSH IN,
THEN OUT
Landing configuration:
Emergency Lights ................................................ ARMED
Gnd Prox Flap Ovrd Button.................................. PUSH IN
Slat/Flap................................................................ 3
Set VREF = VREF
FULL
+20 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.35.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 3
Airspeed................................................................ VREF FULL +
20 KIAS
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 4
Electrical
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AC BUS 1 OFF
Relevant Inoperative Items:
Fuel AC Pump 1
Hyd Sys 2 Elec Pump
Ice Detector 1
Pitch Trim Indication
Windshield Wiper 2
Windshield Heater 2
NOTE: – The slats will operate at low rate mode.
– Fuel Crossfeed Low 2 is not available.
When flying in icing conditions:
Ice Protection Mode Selector............................... ON
Two minutes after exiting icing conditions:
Ice Protection Mode Selector........................... AUTO
END
AC BUS 2 OFF
Relevant Inoperative Items:
Hyd Sys 1 Elec Pump
Hyd Sys 3 Elec Pump B
Ice Detector 2
Windshield Wiper 1
Windshield Heater 1
NOTE: The flaps will operate at low rate.
When flying in icing conditions:
Ice Protection Mode Selector............................... ON
Two minutes after exiting icing conditions:
Ice Protection Mode Selector........................... AUTO
AOM-1502-016
END
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AC ESS BUS OFF
TRU ESS Switch..................................................... OFF
Relevant Inoperative Items:
AC Fuel Pump 2
Hyd Sys 3 Elec Pump A
Pitch Trim Indication
NOTE: – The flaps and slats will extend at low rate mode.
– Fuel Crossfeed Low 1 is not available.
END
AC STBY BUS OFF
Monitor the electrical system.
Relevant Inoperative Items:
Ignition 1A
Ignition 2A
NOTE: Engine Start, with batteries only, is not available.
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 6
Electrical
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
APU GEN OFF BUS
APU Gen Button..................................................... PUSH OUT,
THEN IN
APU GEN OFF BUS MESSAGE EXTINGUISHES?
No
Yes
END
APU Gen Button..................................................... PUSH OUT
END
BATT 1 (2) DISCHARGING
Associated TRU Switch.......................................... OFF, THEN
AUTO
BATT 1 (2) DISCHARGING MESSAGE EXTINGUISHES?
No
Yes
END
Associated TRU Switch.......................................... OFF
AOM-1502-016
END
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
BATT 1 (2) TEMP SENS FAULT
Crew Awareness.
END
BATT 1 OFF
Battery 1.................................................................. VERIFY ON
NOTE: If battery 1 selector is off, APU start is not available.
END
BATT 2 OFF
Battery 2.................................................................. VERIFY AUTO
END
DC BUS 1 OFF
Autothrottle.............................................................. DISENGAGE
Emergency Lights................................................... OFF
Altitude.................................................................... MAX 31000 ft
ADS 1
Nosewheel Steering
Autopilot
Pax Oxy Masks Auto Deploy
Autothrottle 1
Pack 1
CCD 2
Pitch Trim Indication
Display Unit 1
PTU
Display Unit 4
Radio Altimeter 1
Engine 1 Reverser
Weather Radar
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 8
Electrical
REVISION 23
AOM-1502-016
Relevant Inoperative Items:
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Hyd Sys 2 Elec Pump
Windshield Heater 2
MCDU 1
Windshield Wiper 2
Multi Function Spoiler L5 and R5
NOTE: The slats will operate at low rate.
Landing Configuration:
Emergency Lights................................................. ARMED
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.07.
UNFACTORED
On ground:
Use differential braking and rudder to steer the airplane.
END
DC BUS 2 OFF
Autothrottle.............................................................. DISENGAGE
Altitude.................................................................... MAX 31000 ft
Relevant Inoperative Items:
AOM-1502-016
ADS 2
Autobrakes
Autothrottle 2
Display Unit 5
Engine 2 Reverser
Engines Vibration Indications
Electromechanical Door Latch
FMS 1
HF Transceiver
Hyd Sys 1 Elec Pump
Hyd Sys 3 Elec Pump B
Nosewheel Steering
Pack 2
Pax Oxy Masks Auto Deploy
Pedal Adjustment Switch
Pitch Trim indication
Radio Altimeter 2
Roll Trim
TCAS
Transponder 2
Windshield Heater 1
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Multi Function Spoilers L3, R3,
L4 and R4
NAVCOM 2
Windshield Wiper 1
NOTE: The reinforced cockpit door can only be opened manually.
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.10.
UNFACTORED
On ground:
Use differential braking and rudder to steer the airplane.
END
DC ESS BUS 1 OFF
LAND AT THE NEAREST SUITABLE AIRPORT.
Icing Conditions...................................................... EXIT/AVOID
Battery 1.................................................................. OFF
ADS 1
Ignition 1A
APU
Master Warning/Caution 1
Autopilot
MCDU 1 (except circuit breakers
page)
Digital Audio Panel 1
Multi Function Spoilers L5 and R5
Display Unit 3
NAVCOM 1
Engine 1 Start Valve
Engine 1 oil pressure indication
Fuel Quantity 1 Indication
Outboard Brakes
Fwd LAV Smoke Detection
RAT Automatic Deployment
Hyd Sys 2 Depressurization Valve
Transponder 1
Hyd Sys 3 Elec Pump A
Weather Radar
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 10
Electrical
REVISION 23
AOM-1502-016
Relevant Inoperative Items:
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
NOTE: –
–
–
–
–
Compass internal light will be lost.
FADEC will set flight idle on ground.
The flaps will operate at low rate.
Engine 2 windmill start is not available.
Thrust Reversers, Wing Anti-Ice and Ground Idle may
not be available.
– Expect lower roll rates and lower speedbrake efficiency.
– Do not accomplish the SPOILER FAULT procedure.
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.58.
UNFACTORED
On Ground:
Brakes................................................................... APPLY
NORMALLY
END
DC ESS BUS 2 OFF
LAND AT THE NEAREST SUITABLE AIRPORT.
Icing Conditions ..................................................... EXIT/AVOID
Battery 2.................................................................. OFF
Relevant Inoperative Items:
AC Fuel Pump 1.
ADS 3
Aft Lavatory Smoke Detection
APU Fire Extinguishing
APU Fuel Shutoff Valve
AOM-1502-016
Aural Warning 2
Engine 1 and Engine 2
Reversers
Engine 2 Oil pressure indication
Fuel Quantity 2 Indication
Fuel x-feed LOW 2 Operation
Hydraulic System 1
Depressurization Valve
Ignition 2A
CONTINUED...
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Autopilot
CCD 1
DC Fuel Pump
Digital Audio Panel 2
Inboard Brakes
Master Warning/Caution 2
MCDU 2
Multi Function Spoilers L3, R3,
L4 and R4
Display Unit 2
NOTE: –
–
–
–
The slats will operate at low rate.
FADEC will set flight idle on ground.
Engine 1 windmill start is not available.
Thrust Reversers, Wing Anti-Ice and Ground Idle may
not be available.
– Expect lower roll rates and lower speedbrake efficiency.
– Do not accomplish the SPOILER FAULT procedure.
APU......................................................................... OFF
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.66.
UNFACTORED
On Ground:
Brakes................................................................... APPLY
NORMALLY
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 12
Electrical
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
DC ESS BUS 3 OFF
TRU ESS Switch..................................................... OFF
DC ESS BUS 3 OFF MESSAGE EXTINGUISHES?
No
Yes
END
Relevant Inoperative Items:
ADS 2
Landing Gear Override Switch
AFT LAV Smoke Detector
Landing Gear Control Lever
Locking Solenoid
Fire Extinguisher Button Lights
PAX Address (Cabin Interphone
and PA Handset)
Fuel Crossfeed Valve
Pitch Trim Indication
Internal Light of all Switches
Rudder Trim
NOTE:
•
•
•
The flaps will operate at low rate.
IESS Speed and Altitude tape are not available.
The PA button on the Audio Control Panel lights green
when selected, but Cabin Interphone and PA Handset
are not available.
AOM-1502-016
END
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
GPU CONNECTED
Before Taxi:
GPU...................................................................... DISCONNECT
END
IDG 1 (2) OFF BUS
Affected IDG Selector............................................. OFF, THEN
AUTO
IDG 1 (2) OFF BUS MESSAGE EXTINGUISHES?
No
Yes
END
Affected IDG Selector ............................................ OFF
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO
BACKPRESSURE FROM APU BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 14
Electrical
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
IDG 1 (2) OIL
Light:
Affected IDG light becomes amber.
Affected IDG Selector............................................. DISC
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO
BACKPRESSURE FROM APU BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
END
INVERTER FAIL
Crew Awareness.
END
RAT FAIL
Crew Awareness.
AOM-1502-016
END
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 15
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
TRU 1 (2) FAIL
Affected TRU Switch............................................... OFF, THEN
AUTO
TRU 1 (2) FAIL MESSAGE EXTINGUISHES?
No
Yes
END
Affected TRU Switch............................................... OFF
END
TRU ESS FAIL
TRU ESS Switch..................................................... OFF
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 16
Electrical
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
LOAD SHED
Crew Awareness.
END
REMOTE CB TRIP
Crew Awareness.
END
SPDA FAIL
Both thrust reversers may be inoperative.
AOM-1502-016
END
4-03-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electrical
Page 17
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-05
Copyright © by Embraer. Refer to cover page for details.
Page 18
Electrical
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENGINE
TABLE OF CONTENTS
Block
Page
AOM-1502-016
WARNING
ENG 1 (2) OIL LO PRESS ..................................... 4-03-06......
1
ENG 1 (2) REV DEPLOYED .................................. 4-03-06......
1
CAUTION
ENG 1 (2) CONTROL FAULT .................................
ENG 1 (2) FADEC OVERTEMP..............................
ENG 1 (2) FAIL......................................................
ENG 1 (2) FUEL IMP BYPASS ...............................
ENG 1 (2) FUEL LO PRESS ..................................
ENG 1 (2) NO DISPATCH ......................................
ENG 1 (2) OIL LO LEVEL ......................................
ENG 1 (2) REV FAIL..............................................
ENG 1 (2) REV PROT FAULT ................................
ENG 1 (2) REV TLA FAIL.......................................
ENG 1 (2) START VLV OPEN ................................
ENG 1 (2) TLA FAIL...............................................
ENG EXCEEDANCE..............................................
ENG NO TAKEOFF DATA ......................................
ENG REF A-I DISAG .............................................
ENG REF ECS DISAG ..........................................
ENG THR RATING DISAG .....................................
ENG TLA NOT TOGA ............................................
4-03-06......
2
4-03-06......
3
4-03-06......
4
4-03-06......
7
4-03-06......
7
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-06...... 10
4-03-06...... 10
4-03-06...... 11
Crew Awareness
4-03-06...... 12
4-03-06...... 12
4-03-06...... 13
Crew Awareness
4-03-06...... 13
ADVISORY
ENG 1 (2) FADEC FAULT .....................................
ENG 1 (2) FUEL SW FAIL .....................................
ENG 1 (2) OIL IMP BYPASS .................................
ENG 1 (2) OIL SW FAIL ........................................
ENG 1 (2) SHORT DISPATCH...............................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-06-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-06-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENG 1 (2) OIL LO PRESS
EICAS Indication: Oil pressure indication in red or amber may be
presented.
OIL PRESSURE INDICATION ABNORMAL?
No
Yes
ENGINE SHUTDOWN Procedure........................... ACCOMPLISH
END
ENG 1 (2) REV DEPLOYED
EICAS Indication: REV icon above the associated ITT indication.
LAND AT THE NEAREST SUITABLE AIRPORT.
Autothrottle.............................................................. DISENGAGE
Associated Thrust Lever......................................... IDLE
ANY BUFFETING NOTICED?
No
Yes
Start/Stop Selector (affected engine)...................... STOP
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU ........................................................................ START
AOM-1502-016
Fuel ........................................................................ BALANCE
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Autothrottle.............................................................. AS REQUIRED
Transponder............................................................ TA ONLY
When appropriate:
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
END
ENG 1 (2) CONTROL FAULT
Autothrottle.............................................................. DISENGAGE
CAUTION: AVOID QUICK THRUST LEVER MOVEMENT, HIGH
ENGINE THRUST AND THRUST REVERSER
OPERATION ON THE AFFECTED ENGINE.
ABLE TO CONTROL AFFECTED ENGINE THRUST?
No
Yes
END
AFFECTED ENGINE THRUST STABLE AT IDLE?
No
Yes
Associated Thrust Lever......................................... IDLE
Transponder............................................................ TA ONLY
When appropriate:
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 2
Engine
REVISION 23
AOM-1502-016
Continue the flight monitoring engine parameters.
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure.......................................... ACCOMPLISH
END
ENGINE SHUTDOWN Procedure.......................... ACCOMPLISH
END
ENG 1 (2) FADEC OVERTEMP
ENGINE PARAMETERS ABNORMAL?
No
Yes
ENGINE SHUTDOWN Procedure........................... ACCOMPLISH
CAUTION: IF THE ENGINE DOES NOT SHUTDOWN, PULL (DO
NOT
ROTATE)
THE
ASSOCIATED
FIRE-EXTINGUISHING HANDLE.
NOTE: Exit and avoid icing conditions if the associated Fire
Extinguishing Handle has been pulled.
AOM-1502-016
END
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENG 1 (2) FAIL
EICAS Indication: FAIL icon on N1 indication.
EICAS Indication: Oil press indication in red.
LAND AT THE NEAREST SUITABLE AIRPORT.
Associated Thrust Lever......................................... IDLE
ENGINE AUTO RELIGHTS?
No
Yes
The EICAS message may be caused by a fuel leak. Fuel leak
may be detected by either:
•
•
•
•
•
A fuel imbalance develops; or
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings.
NOTE: – If flight conditions permit, operate the engine at idle for
2 min prior to apply engine thrust.
– During engine auto relight, if N2 is steady accelerating
while ITT remains within start limit, the start is
progressing normally.
– During inflight starts, FADEC has no protection for hot
starts, hung starts or failure to light off.
– Crew must take appropriate action in case of abnormal
engine indications.
END
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 4
Engine
REVISION 23
AOM-1502-016
Associated Start/Stop Selector............................... STOP
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Transponder............................................................ TA ONLY
The EICAS message may be caused by a fuel leak. Fuel leak
may be detected by either:
•
•
•
•
•
A fuel imbalance develops; or
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings.
FUEL LEAK SUSPECTED?
No
Yes
NOTE: Assume that fuel is leaking from tank associated to engine
failed side.
Fuel Xfeed Selector................................................ OFF
LEAK ON THE RH TANK?
No
Yes
APU......................................................................... OFF
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
AOM-1502-016
END
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
!O.B Nº 170-001/09 - ENGINE STALL DUE TO BACKPRESSURE FROM APU
BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
END
RESTART CONSIDERED?
No
Yes
ENGINE AIRSTART Procedure.............................. ACCOMPLISH
END
NOTE: Engine failure may cause scavenge pump to stop fuel
transfer to the Collector Box. The loss of fuel transfer system
to the Collector Box may trigger the EICAS WARNING
message FUEL 1 (2) LO LEVEL. The EICAS message may
display even though fuel quantity indication on the EICAS or
MFD FUEL System Synoptic Page is up to 6170 lb in that
tank.
Fuel......................................................................... BALANCE
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................. ACCOMPLISH
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 6
Engine
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENG 1 (2) FUEL IMP BYPASS
CAUTION: IF BOTH ENGINES ARE AFFECTED, LAND AT THE
NEAREST SUITABLE AIRPORT.
END
ENG 1 (2) FUEL LO PRESS
Fuel Xfeed Selector................................................ OFF
Autothrottle.............................................................. DISENGAGE
Engine Parameters................................................. MONITOR
The EICAS message may be caused by a fuel leak. Fuel leak
may be detected by either:
•
•
•
•
•
•
A fuel imbalance develops; or
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings; or
With both engines operative, an unexpected difference
between the total fuel quantity indicated on EICAS and the
total fuel quantity indicated on the FMS Fuel Management
page or PERF INIT page 3/3.
FUEL LEAK SUSPECTED?
No
Yes
FUEL LEAK Procedure........................................... ACCOMPLISH
AOM-1502-016
END
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
DESIRED THRUST MAINTAINED?
No
Yes
ENGINE PARAMETERS FLUCTUATE?
No
Yes
Altitude.................................................................... DESCEND AS
REQUIRED
END
END
Altitude.................................................................... DESCEND AS
REQUIRED
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 8
Engine
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENG 1 (2) NO DISPATCH
Crew Awareness.
END
ENG 1 (2) OIL LO LEVEL
Crew Awareness.
END
ENG 1 (2) REV FAIL
Crew Awareness.
END
ENG 1 (2) REV PROT FAULT
Crew Awareness.
AOM-1502-016
END
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENG 1 (2) REV TLA FAIL
Inflight, do not move the thrust levers below idle.
On ground, the associated thrust reverser is not available.
END
ENG 1 (2) START VLV OPEN
XBleed Button......................................................... PUSH OUT
Associated Bleed Button......................................... PUSH OUT
ON GROUND?
No
Yes
ENGINE 1 AFFECTED?
No
Yes
APU Bleed Button................................................... PUSH OUT
Engine 1:
Thrust Lever.......................................................... IDLE
Start/Stop Selector................................................ STOP
END
Engine 2:
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 10
Engine
REVISION 23
AOM-1502-016
Engine Start Ground Cart....................................... REMOVE
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Thrust Lever.......................................................... IDLE
Start/Stop Selector................................................ STOP
END
APU Bleed Button................................................... PUSH OUT
Icing Conditions ..................................................... EXIT/AVOID
Altitude.................................................................... MAX 31000 ft
CAUTION: IN FLIGHT ASSISTED STARTS ARE NOT POSSIBLE
FOR THE AFFECTED ENGINE.
END
ENG 1 (2) TLA FAIL
CONDITION:
Associated engine thrust control may be lost.
ABLE TO CONTROL AFFECTED ENGINE THRUST?
No
Yes
END
NOTE: The engine thrust will be set to idle automatically.
Associated Thrust Lever......................................... IDLE
Transponder............................................................ TA ONLY
AOM-1502-016
When appropriate:
ONE ENGINE INOPERATIVE APPROACH AND
CONTINUED...
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
LANDING Procedure.......................................... ACCOMPLISH
END
ENG EXCEEDANCE
Crew Awareness.
END
ENG NO TAKEOFF DATA
Engine Takeoff Data............................................... ENTER
END
ENG REF A-I DISAG
Configure the airplane according to takeoff data or re-enter the
takeoff data according to the airplane configuration.
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 12
Engine
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENG REF ECS DISAG
Configure the airplane according to takeoff data or re-enter the
takeoff data according to the airplane configuration.
END
ENG THR RATING DISAG
Crew Awareness.
END
ENG TLA NOT TOGA
Move the thrust levers to TOGA position.
END
ENG 1 (2) FADEC FAULT
Crew Awareness.
AOM-1502-016
END
4-03-06
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Engine
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ENG 1 (2) FUEL SW FAIL
Crew Awareness.
END
ENG 1 (2) OIL IMP BYPASS
Crew Awareness.
END
ENG 1 (2) OIL SW FAIL
Crew Awareness.
END
ENG 1 (2) SHORT DISPATCH
Crew Awareness.
4-03-06
Copyright © by Embraer. Refer to cover page for details.
Page 14
Engine
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FIRE PROTECTION
TABLE OF CONTENTS
Block
Page
AOM-1502-016
WARNING
APU FIRE ............................................................. 4-03-07......
1
ENG 1 (2) FIRE ..................................................... 4-03-07......
1
CAUTION
APU FIRE DET FAIL..............................................
APU FIREX FAIL ...................................................
CRG AFT (FWD) FIRE SYS FAIL ...........................
ENG 1 (2) FIRE DET FAIL .....................................
LAV SMOKE DET FAIL ..........................................
4-03-07......
4
4-03-07......
4
4-03-07......
4
4-03-07......
5
Crew Awareness
ADVISORY
APU FIREXBTL DISCH .........................................
CRG AFT FIREX HI (LO) ARM ..............................
CRG FIRE PROT FAULT.......................................
CRG FWD FIREX HI (LO) ARM.............................
ENG 1 (2) FIREXBTL A (B) FAIL ...........................
ENG FIREXBTL A (B) DISCH ................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-07-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-07-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ANNUNCIATED PROCEDURES
APU FIRE
Light:
APU Emergency Stop Button upper half
illuminates in red.
APU Emergency Stop Button............................... PUSH IN
APU......................................................................... OFF
APU FIRE MESSAGE EXTINGUISHES?
No
Yes
END
APU Fire Extinguishing Button............................... PUSH
END
ENG 1 (2) FIRE
EICAS Indication: FIRE icon on the associated ITT indicator.
Light:
Associated fire handle illuminates.
Autothrottle............................................................ DISENGAGE
Affected engine:
Thrust Lever....................................................... IDLE
Start/Stop Selector............................................. STOP
Fire Extinguishing Handle.................................. PULL
AOM-1502-016
LAND AT THE NEAREST SUITABLE AIRPORT.
Fire Extinguishing Handle....................................... ROTATE
(L or R)
CONTINUED...
4-03-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fire Protection
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
........................................Wait 30 seconds........................................
FIRE PERSISTS?
No
Yes
Fire Extinguishing Handle (remaining bottle).......... ROTATE
ON GROUND?
No
Yes
EMERGENCY EVACUATION Procedure................ AS REQUIRED
END
HIGH VIBRATION?
No
Yes
Airspeed.................................................................. REDUCE
Airspeeds below VA are recommended to reduce vibration.
Icing Conditions...................................................... EXIT/AVOID
Transponder............................................................ TA ONLY
EICAS ASSOCIATED FUEL INDICATION LOST?
No
Yes
Fuel Xfeed Selector................................................ OFF
CONTINUED...
4-03-07
Copyright © by Embraer. Refer to cover page for details.
Page 2
Fire Protection
REVISION 23
AOM-1502-016
NOTE: Assume that fuel is leaking from tank associated to engine
failed side.
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
LEAK ON THE RH TANK?
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
No
Yes
APU......................................................................... OFF
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
END
!O.B Nº 170-001/09 - ENGINE STALL DUE TO BACKPRESSURE FROM APU
BLEED
NOTE: If APU use is intended, push OUT the APU Bleed button
prior to APU start.
"
APU......................................................................... AS REQUIRED
ONE ENGINE INOPERATIVE APPROACH AND
LANDING Procedure............................................... ACCOMPLISH
END
!Airplanes with O.B. N° 170-001/09 - ENGINE 2 STALL DUE TO BACKPRESSURE FROM APU BLEED
APU Bleed Button................................................... PUSH OUT
"
APU......................................................................... START
Fuel......................................................................... BALANCE
Autothrottle.............................................................. AS REQUIRED
AOM-1502-016
When appropriate:
ONE ENGINE INOPERATIVE APPROACH AND
CONTINUED...
4-03-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fire Protection
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
LANDING Procedure.......................................... ACCOMPLISH
END
APU FIRE DET FAIL
APU......................................................................... OFF
END
APU FIREX FAIL
APU......................................................................... OFF
END
CRG AFT (FWD) FIRE SYS FAIL
AFFECTED CARGO COMPARTMENT IS EMPTY?
No
Yes
END
LAND AT THE NEAREST SUITABLE AIRPORT.
4-03-07
Copyright © by Embraer. Refer to cover page for details.
Page 4
Fire Protection
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ENG 1 (2) FIRE DET FAIL
If fire is suspected in the affected engine:
ENGINE FIRE, SEVERE DAMAGE OR
SEPARATION Procedure.................................... ACCOMPLISH
END
LAV SMOKE DET FAIL
Crew Awareness.
END
APU FIREXBTL DISCH
Crew Awareness.
END
CRG AFT FIREX HI (LO) ARM
Crew Awareness.
AOM-1502-016
END
4-03-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fire Protection
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
CRG FIRE PROT FAULT
Crew Awareness.
END
CRG FWD FIREX HI (LO) ARM
Crew Awareness.
END
ENG 1 (2) FIREXBTL A (B) FAIL
Crew Awareness.
END
ENG FIREXBTL A (B) DISCH
Crew Awareness.
4-03-07
Copyright © by Embraer. Refer to cover page for details.
Page 6
Fire Protection
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FLIGHT CONTROLS
TABLE OF CONTENTS
Block
Page
AOM-1502-016
WARNING
ELEV NML MODE FAIL ......................................... 4-03-08......
1
GROUND SPOILERS FAIL .................................... 4-03-08......
1
RUDDER NML MODE FAIL.................................... 4-03-08......
2
SPOILER NML MODE FAIL ................................... 4-03-08......
2
CAUTION
AOA LIMIT FAIL.....................................................
ELEV THR COMP FAIL .........................................
ELEVATOR FAULT ................................................
ELEVATOR LH (RH) FAIL ......................................
FLAP FAIL.............................................................
FLT CTRL BIT EXPIRED........................................
FLT CTRL NO DISPATCH ......................................
FLT CTRL TEST FAILED .......................................
PITCH TRIM FAIL..................................................
RUDDER FAIL.......................................................
RUDDER FAULT ...................................................
RUDDER LIMITER FAIL ........................................
SLAT FAIL .............................................................
SLAT-FLAP LEVER DISAG ....................................
SPOILER FAULT ...................................................
STAB LOCK FAULT ...............................................
4-03-08......
3
4-03-08......
3
4-03-08......
3
4-03-08......
4
4-03-08......
5
Crew Awareness
Crew Awareness
Crew Awareness
4-03-08......
8
4-03-08......
9
4-03-08...... 10
4-03-08...... 11
4-03-08...... 11
4-03-08...... 15
4-03-08...... 15
4-03-08...... 17
ADVISORY
AILERON LH (RH) FAIL ........................................
AUTO CONFIG TRIM FAIL....................................
FLAP (SLAT) LO RATE .........................................
FLT CTRL FAULT..................................................
PITCH CONTROL DISC ........................................
PITCH TRIM BKUP FAIL .......................................
4-03-08...... 17
Crew Awareness
4-03-08...... 18
Crew Awareness
Crew Awareness
Crew Awareness
4-03-08-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
Block
ADVISORY
PITCH TRIM LO RATE..........................................
PITCH TRIM SW 1 (2) FAIL ..................................
ROLL CONTROL DISC .........................................
SPDBRK LEVER DISAG .......................................
STALL PROT ICE SPEED .....................................
TAILSTRIKE AVOID FAIL ......................................
TAILSTRIKE PROT FAIL .......................................
Page
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-08...... 20
4-03-08...... 21
4-03-08...... 21
4-03-08-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ELEV NML MODE FAIL
Flight Controls Mode Elevators Button................... PUSH IN
NOTE: Do not accomplish the ELEVATOR FAULT Procedure.
Relevant Inoperative Items:
AOA Limit
Auto Configuration Trim
Autopilot
Elevator Thrust Compensation
Avoid side slipping the airplane.
END
GROUND SPOILERS FAIL
CONDITION:
One or more ground spoiler panels have
extended inadvertently, have failed to extend
when commanded or are unavailable to extend.
In flight:
Speedbrake........................................................... CLOSE
Landing configuration:
Slat/Flap........................................................... FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.10.
UNFACTORED
AOM-1502-016
END
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
RUDDER NML MODE FAIL
Flight Controls Mode Rudder Button...................... PUSH IN
NOTE: Do not accomplish the RUDDER FAULT Procedure.
Relevant Inoperative Items:
Turn Coordination
Yaw Damper
END
SPOILER NML MODE FAIL
Speedbrake............................................................. CLOSE
Flight Controls Mode Spoilers Button..................... PUSH IN
NOTE: Do not accomplish the SPOILER FAULT Procedure.
Relevant Inoperative Items:
Ground Spoilers
SpeedBrake
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.30.
UNFACTORED
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 2
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AOA LIMIT FAIL
Avoid side slipping the airplane.
NOTE: The stick shaker remains operative.
END
ELEV THR COMP FAIL
Compensate manually any pitch tendency following thrust variations.
END
ELEVATOR FAULT
NOTE: If the SPOILER FAULT message is also displayed,
accomplish the Spoiler Fault procedure prior to this
procedure.
Flight Controls Mode Elevators Button................... PUSH IN,
THEN OUT
ELEVATOR FAULT MESSAGE EXTINGUISHES?
No
Yes
END
Relevant Inoperative Items:
AOM-1502-016
AOA Limit
Auto Configuration Trim
Autopilot
Elevator Thrust Compensation
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Avoid side slipping the airplane.
END
ELEVATOR LH (RH) FAIL
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
NOTE: Expect less elevator control authority and slower response,
especially during landing flare.
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF FULL + 15 KIAS.
Apply brakes only after nose landing gear touches down.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.29.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 4
Airspeed................................................................ VREF FULL +
15 KIAS
(limited to
175 KIAS)
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 4
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FLAP FAIL
SLAT/FLAP LEVER ACTUATED?
No
Yes
Altitude.................................................................... MAX 20000 ft
Slat/Flap Lever........................................................ RETURN TO
THE
PREVIOUS
POSITION
........................................Wait 10 seconds........................................
Slat/Flap Lever........................................................ RESELECT
DESIRED
POSITION
MESSAGE EXTINGUISHES?
No
Yes
END
Slat/Flap Lever........................................................ RETURN TO
THE
PREVIOUS
POSITION
AOM-1502-016
........................................Wait 10 seconds........................................
Slat/Flap Lever........................................................ RESELECT
DESIRED
POSITION
MESSAGE EXTINGUISHES?
Yes
No
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
END
NOTE: For landing, the Slat/Flap lever can be moved to select the
desired Slat position.
Landing Configuration:
Select the desired slat position and use the landing data according
to the FLAP/SLAT FAIL LANDING CONFIGURATION TABLE, or
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE.
The Actual Landing Distance is equal to the Unfactored Landing
Distance for flaps FULL multiplied by the listed LDG Coef provided
on the table below.
NOTE: – If amber dashes are displayed on the EICAS, use the
most conservative position to enter the table (e.g. for a
failure between 1 and 2, consider 1).
– Flaps external marks can be used to determine flap
position.
Autothrottle............................................................ DISENGAGE
Bank Angle............................................................ 20° MAXIMUM
Gnd Prox Flap Ovrd Button.................................. PUSH IN
If a go-around is required:
Slat/Flap................................................................ MAINTAIN
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 6
Flight Controls
REVISION 21
AOM-1502-016
Maintain the Vref presented in the respective Landing Configuration
Table.
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE
FLAP
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
SLAT
0
1 (2) (3)
4 (5 ) (FULL)
VREF FULL+60 VREF FULL+50 VREF FULL+50
0
1.90
1.77
1.81
VREF FULL+35 VREF FULL+35 VREF FULL+35
1
1.52
1.56
1.58
VREF FULL+30 VREF FULL+25 VREF FULL+25
2
1.44
3 (4) (5)
FULL
1.39
1.41
VREF FULL+20 VREF FULL+10
NOT
USABLE
1.35
1.22
VREF FULL+5
VREF FULL
1.08
1.00
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE
SLAT
FLAP
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
0
1 (2) (3)
4 (5 )
(FULL)
VREF FULL+60 VREF FULL+60 VREF FULL+60
0
1.90
1.95
1.99
VREF FULL+40 VREF FULL+40 VREF FULL+40
1
1.60
1.63
1.66
VREF FULL+30 VREF FULL+30 VREF FULL+30
2
1.44
3 (4) (5)
FULL
1.47
1.49
VREF FULL+20 VREF FULL+15
NOT
USABLE
1.35
1.29
VREF FULL+5
VREF FULL
1.08
1.00
AOM-1502-016
END
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
FLT CTRL BIT EXPIRED
Crew Awareness.
END
FLT CTRL NO DISPATCH
Crew Awareness.
END
FLT CTRL TEST FAILED
Crew Awareness.
END
PITCH TRIM FAIL
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
Pitch Trim System 1 and 2 Cutout Buttons............ PUSH IN,
THEN OUT
Pitch Trim Switches................................................ ACTUATE
PITCH TRIM NORMAL?
No
Yes
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 8
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Pitch Trim System 1 and 2 Cutout Buttons............ PUSH IN
NOTE: – No more pitch trim is available.
– Continuous turns helps to alleviate excessive pitch up
tendencies.
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF FULL + 15 KIAS.
Establish landing configuration early.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.29.
UNFACTORED
If a go around is required:
Slat/Flap................................................................ 4
Airspeed................................................................ VREF FULL +
15 KIAS
(limited to
175 KIAS)
END
RUDDER FAIL
LAND AT THE NEAREST SUITABLE AIRPORT.
Maximum Airspeed................................................. CURRENT OR
175 KIAS,
WHICHEVER
IS HIGHER
Relevant Inoperative Items:
Turn Coordination
Yaw Damper
Yaw Trim
Landing configuration:
Slat/Flap................................................................ FULL
AOM-1502-016
Set VREF FULL.
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
CAUTION: AVOID LANDING WITH CROSSWIND COMPONENTS
ABOVE 10 KT.
If a go around is required, proceed as a normal go around limiting
the airspeed to 175 KIAS.
NOTE: As assymetric thrust may be required to help controlling the
airplane, maximum thrust on both engines may not be
possible.
END
RUDDER FAULT
NOTE: If the SPOILER FAULT message is also displayed,
accomplish the SPOILER FAULT procedure prior to this
procedure.
Flight Controls Mode Rudder Button...................... PUSH IN,
THEN OUT
No
RUDDER FAULT MESSAGE EXTINGUISHES?
Yes
END
RUDDER LIMITER FAIL MESSAGE DISPLAYED?
No
Yes
Flight Controls Mode Rudder Button...................... PUSH IN,
THEN OUT
RUDDER FAULT MESSAGE EXTINGUISHES?
No
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 10
Flight Controls
REVISION 21
AOM-1502-016
Yes
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
END
Relevant Inoperative Items:
Yaw Damper
Turn Coordination
END
RUDDER LIMITER FAIL
CONDITION:
WARNING:
•
•
Rudder position limiter is inoperative and rudder
authority in flight is 30°.
DO NOT APPLY ABRUPT PEDAL COMMANDS.
DO NOT APPLY FULL RUDDER DEFLECTION.
END
SLAT FAIL
SLAT/FLAP LEVER ACTUATED?
No
Yes
Altitude.................................................................... MAX 20000 ft
Slat/Flap Lever........................................................ RETURN TO
THE
PREVIOUS
POSITION
AOM-1502-016
........................................Wait 10 seconds........................................
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Slat/Flap Lever........................................................ RESELECT
DESIRED
POSITION
MESSAGE EXTINGUISHES?
No
Yes
END
Slat/Flap Lever........................................................ RETURN TO
THE
PREVIOUS
POSITION
........................................Wait 10 seconds........................................
Slat/Flap Lever........................................................ RESELECT
DESIRED
POSITION
MESSAGE EXTINGUISHES?
No
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 12
Flight Controls
REVISION 21
AOM-1502-016
Yes
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
END
NOTE: For landing, the Slat/Flap lever can be moved to select the
desired Flap position.
Landing Configuration:
Select the desired flap position and use the landing data according
to the FLAP/SLAT FAIL LANDING CONFIGURATION TABLE, or
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE.
The Actual Landing Distance is equal to the Unfactored Landing
Distance for flaps FULL multiplied by the listed LDG Coef provided
on the table below.
NOTE: – If amber dashes are displayed on the EICAS, use the
most conservative position to enter the table (e.g. for a
failure between 1 and 2, consider 1).
– Slats external marks can be used to determine slat
position.
Autothrottle............................................................ DISENGAGE
Bank Angle............................................................ 20° MAXIMUM
Gnd Prox Flap Ovrd Button.................................. PUSH IN
If a go-around is required:
Slat/Flap................................................................ MAINTAIN
AOM-1502-016
Maintain the Vref presented in the respective Landing Configuration
Table.
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE
FLAP
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
SLAT
0
1 (2) (3)
4 (5 ) (FULL)
VREF FULL+60 VREF FULL+50 VREF FULL+50
0
1.90
1.77
1.81
VREF FULL+35 VREF FULL+35 VREF FULL+35
1
1.52
1.56
1.58
VREF FULL+30 VREF FULL+25 VREF FULL+25
2
1.44
3 (4) (5)
FULL
1.39
1.41
VREF FULL+20 VREF FULL+10
NOT
USABLE
1.35
1.22
VREF FULL+5
VREF FULL
1.08
1.00
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE
SLAT
FLAP
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
VREF (KIAS)
LDG Coef
0
1 (2) (3)
4 (5 )
(FULL)
VREF FULL+60 VREF FULL+60 VREF FULL+60
0
1.90
1.95
1.99
VREF FULL+40 VREF FULL+40 VREF FULL+40
1
1.60
1.63
1.66
VREF FULL+30 VREF FULL+30 VREF FULL+30
2
1.44
3 (4) (5)
FULL
1.47
1.49
VREF FULL+20 VREF FULL+15
NOT
USABLE
1.35
1.29
VREF FULL+5
VREF FULL
1.08
1.00
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 14
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
SLAT-FLAP LEVER DISAG
Return the slat/flap lever to previous position and then use it as
required.
END
SPOILER FAULT
CONDITION:
One or more Multifunction Spoilers Panels have
reverted to Direct Mode, have extended
inadvertently or have failed to extend.
Autopilot.................................................................. DISENGAGE
Speedbrake............................................................. CLOSE
Flight Controls Mode Spoilers Button..................... PUSH IN,
THEN OUT
SPOILER FAULT MESSAGE EXTINGUISHES?
No
Yes
Speedbrake............................................................. AS REQUIRED
END
Relevant Inoperative Items:
Ground Spoilers (partially or fully lost)
SpeedBrake (partially or fully lost)
NOTE: In case of Speedbrake partially lost, the remaining panels
may be used. In this case the advisory message SPDBRK
LEVER DISAG may be displayed.
AOM-1502-016
ALL SPOILER PANELS POSITION DETERMINED?
No
Yes
CONTINUED...
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 15
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
ALL SPOILER PANELS FAILED CLOSED?
No
Yes
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.30.
UNFACTORED
END
Landing configuration:
Slat/Flap................................................................ 5
Set VREF = VREF
FULL
+ 15 KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.63.
UNFACTORED
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 16
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
STAB LOCK FAULT
CONDITION:
The Horizontal Stabilizer may have a drift rate
up to 0.5 deg/min nose up or nose down.
LAND AT THE NEAREST SUITABLE AIRPORT.
Pitch Trim................................................................ AS REQUIRED
CAUTION: DO NOT PRESS ANY PITCH TRIM SYSTEM CUTOUT
BUTTON.
END
AILERON LH (RH) FAIL
On ground, do not takeoff.
In flight:
Avoid abrupt and large aileron inputs and limit bank angle to 25°.
Establish landing configuration early.
Landing configuration:
Slat/Flap........................................................... 5
Set VREF
FULL+10
KIAS.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.21.
UNFACTORED
AOM-1502-016
END
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 17
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AUTO CONFIG TRIM FAIL
Crew Awareness.
END
FLAP (SLAT) LO RATE
During approach:
Slat/Flap Actuation................................................ ANTICIPATE
END
FLT CTRL FAULT
Crew Awareness.
END
PITCH CONTROL DISC
Crew Awareness.
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 18
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
PITCH TRIM BKUP FAIL
Crew Awareness.
END
PITCH TRIM LO RATE
Crew awareness.
END
PITCH TRIM SW 1 (2) FAIL
Crew Awareness.
END
ROLL CONTROL DISC
Crew Awareness.
END
SPDBRK LEVER DISAG
Crew Awareness.
AOM-1502-016
END
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 19
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
STALL PROT ICE SPEED
Set landing reference speeds for ice accretion.
LANDING IN ICING CONDITIONS OR
ACCRETION?
WITH
ICE No
Yes
Use landing performance data for ice accretion.
END
Landing Configuration:
For flap 5:
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.35.
UNFACTORED
For flap FULL:
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.10.
UNFACTORED
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 20
Flight Controls
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
TAILSTRIKE AVOID FAIL
During landing:
Pitch Angle............................................................ MAX 10°
END
TAILSTRIKE PROT FAIL
During landing:
Pitch Angle............................................................ MAX 10°
AOM-1502-016
END
4-03-08
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Flight Controls
Page 21
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-08
Copyright © by Embraer. Refer to cover page for details.
Page 22
Flight Controls
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FMS/NAV/COMM/FLIGHT INSTRUMENTS
TABLE OF CONTENTS
Block
Page
WARNING
AOM-1502-016
NO TAKEOFF CONFIG.......................................... 4-03-09......
CAUTION
ADS 1 (2) FAIL ......................................................
ADS 3 FAIL ...........................................................
ADS 1 (2) (3) HTR FAIL.........................................
ADS 4 HTR FAIL ...................................................
APM FAIL..............................................................
APM MISCOMP.....................................................
AURAL WRN SYS FAIL .........................................
AVNX ASCB FAULT ...............................................
AVNX MAU 1A FAIL...............................................
AVNX MAU 1B FAIL ..............................................
AVNX MAU 2A FAIL...............................................
AVNX MAU 2B FAIL ..............................................
AVNX MAU 3A FAIL...............................................
AVNX MAU 3B FAIL ..............................................
AVNX MAU 1A (1B) OVHT.....................................
AVNX MAU 2A (2B) OVHT.....................................
AVNX MAU 3A (3B) OVHT.....................................
AVNX MAU 1 (2) (3) FAN FAIL...............................
CMS FAIL..............................................................
CREW WRN SYS FAULT.......................................
DISPLAY CTRL FAIL .............................................
DISPLAY CTRL FAULT ..........................................
EICAS FAULT........................................................
EICAS OVHT.........................................................
FMS POS DISAG ..................................................
FMS1 (2) - GPS POS DISAG .................................
GND PROX FAIL ...................................................
1
4-03-09......
1
4-03-09......
1
4-03-09......
1
4-03-09......
2
Crew Awareness
Crew Awareness
4-03-09......
2
Crew Awareness
4-03-09......
3
4-03-09......
4
4-03-09......
4
4-03-09......
5
4-03-09......
5
4-03-09......
6
4-03-09......
6
4-03-09......
7
4-03-09......
7
Crew Awareness
Crew Awareness
Crew Awareness
4-03-09......
8
Crew Awareness
4-03-09......
9
4-03-09......
9
4-03-09......
9
4-03-09...... 10
4-03-09...... 10
4-03-09-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
Block
Page
CAUTION
IRS EXCESSIVE MOTION .....................................
IRS 1 (2) FAIL .......................................................
MFD 1 (2) FAULT ..................................................
MFD 1 (2) OVHT ...................................................
NAVCOM 1 (2) FAIL ..............................................
NAVCOM 1 (2) OVHT ............................................
PFD 1 (2) FAULT ...................................................
PFD 1 (2) OVHT....................................................
SYS CONFIG FAIL ................................................
TERRAIN FAIL ......................................................
VALIDATE CONFIG ...............................................
VHF 1 (2) (3) OVHT...............................................
VHF 3 FAIL ...........................................................
WINDSHEAR FAIL.................................................
XPDR 1 (2) IN STBY .............................................
4-03-09...... 10
4-03-09...... 11
4-03-09...... 11
4-03-09...... 11
4-03-09...... 12
4-03-09...... 12
4-03-09...... 12
4-03-09...... 13
Crew Awareness
4-03-09...... 13
Crew Awareness
4-03-09...... 14
4-03-09...... 14
4-03-09...... 14
4-03-09...... 15
ADVISORY
ADS PROBE 1 (2) (3) (4) FAIL ..............................
ADS 1 (2) HTR FAULT ..........................................
ADS 3 SLIPCOMP FAIL ........................................
ADS 4 SLIPCOMP FAIL ........................................
APM FAULT..........................................................
ATC 1 (2) DATALINK FAIL.....................................
AURAL WRN SYS FAULT .....................................
AVNX DB MODULE FAIL ......................................
AVNX MAU 1A (1B) FAULT ...................................
AVNX MAU 2A (2B) FAULT ...................................
AVNX MAU 3A (3B) FAULT ...................................
AVNX MAU 1 (2) (3) FAN FAULT...........................
CCD 1 (2) FAULT..................................................
CMC FAIL.............................................................
CMF 1 (2) FAIL .....................................................
CMS FAULT..........................................................
CVR AFT (FWD) FAIL ...........................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-09...... 17
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-09-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
Block
AOM-1502-016
ADVISORY
DATALINK 1 (2) FAIL ............................................
FDR AFT (FWD) FAIL ...........................................
FLT CTRL ADS FAIL .............................................
FMS 1 (2) FAIL .....................................................
IRS 1 (2) NAV MODE FAIL....................................
IRS ALIGNING ......................................................
IRS PRES POS INVALID.......................................
RALT 1 (2) FAIL ....................................................
TAT 1 (2) FAIL ......................................................
TCAS FAIL ...........................................................
TERRAIN NOT AVAILABLE ...................................
XPDR 1 (2) FAIL ...................................................
Page
Crew Awareness
Crew Awareness
Crew Awareness
4-03-09...... 19
4-03-09...... 20
Crew Awareness
4-03-09...... 20
4-03-09...... 20
4-03-09...... 21
Crew Awareness
Crew Awareness
4-03-09...... 22
4-03-09-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-09-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 4
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
NO TAKEOFF CONFIG
Configure the airplane for takeoff.
END
ADS 1 (2) FAIL
Confirm the affected ADS automatic reversion.
If necessary:
Associated Reversionary Panel ADS Button........ PUSH
END
ADS 3 FAIL
Reversion................................................................ AS REQUIRED
END
ADS 1 (2) (3) HTR FAIL
Revert the affected ADS.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ADS 4 HTR FAIL
Disregard IESS altitude and airspeed indication.
END
APM FAIL
Crew Awareness.
END
APM MISCOMP
Crew Awareness.
END
AURAL WRN SYS FAIL
Monitor visual indications.
NOTE: Aural warnings, including EGPWS callouts, are lost. TCAS
aural will be operative.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 2
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AVNX ASCB FAULT
Crew Awareness.
END
AVNX MAU 1A FAIL
Icing Conditions...................................................... EXIT/AVOID
Relevant Inoperative Items:
ACARS
ADS 1
Autopilot 1
FMS 1
Left Aileron Indication
MCDU1 (except circuit breakers
page)
Multi Function Spoilers L5 and
R5
Nosewheel Steering
Outboard Brakes
Pitch Trim Indication
Weather Radar
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.58.
UNFACTORED
On ground:
Brakes................................................................... APPLY
NORMALLY
Steer the airplane using differential braking and rudder.
The nosewheel steering operates normally if the EICAS
message AVNX MAU 1A FAIL is displayed after the engagement
of nosewheel steering.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AVNX MAU 1B FAIL
Relevant Inoperative Items:
GPS 1
Multi Function Spoilers L5 and
R5
Pitch Trim Indication
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.07.
UNFACTORED
END
AVNX MAU 2A FAIL
Relevant Inoperative Items:
Autobrake
FMS 1.
Nosewheel Steering.
On ground:
Steer the airplane using rudder and differential braking.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 4
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AVNX MAU 2B FAIL
Relevant Inoperative Items:
ADS 2
Autopilot 2
Inboard Brakes
Mach Trim
MCDU 2 (except circuit
EGPWS
breakers page)
IESS Localizer and Glide Slope Right Side Weather Radar
Indication
Control
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.51.
UNFACTORED
On ground:
Brakes................................................................... APPLY
NORMALLY
END
AVNX MAU 3A FAIL
Icing Conditions...................................................... EXIT/AVOID
Relevant Inoperative Items:
ADS 3
APU
Autothrottle
Autopilot 2
FMS 2
GPS 2
Multi Function Spoiler L3, R3,
L4 and R4
Right Aileron Indication
Speedbrake
AOM-1502-016
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CONTINUED...
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.30.
UNFACTORED
END
AVNX MAU 3B FAIL
Relevant Inoperative Items:
Engine Vibration Indication
Multi Function Spoilers L3, R3,
L4 and R4
Pitch Trim Indication
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.10.
UNFACTORED
END
AVNX MAU 1A (1B) OVHT
Associated CB........................................................ PULL
NOTE: – For MAU 1A OVHT, pull the B6 and B7 CB.
– For MAU 1B OVHT, pull the B15 CB.
Associated AVNX MAU 1A FAIL or AVNX MAU 1B
FAIL Procedure..................................................... ACCOMPLISH
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 6
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AVNX MAU 2A (2B) OVHT
Associated CB........................................................ PULL
NOTE: – For MAU 2A OVHT, pull the B25 CB.
– For MAU 2B OVHT, pull the B26 and B35 CB.
Associated AVNX MAU 2A FAIL or AVNX MAU 2B
FAIL Procedure..................................................... ACCOMPLISH
END
AVNX MAU 3A (3B) OVHT
Associated CB........................................................ PULL
NOTE: – For MAU 3A OVHT, pull the B34 CB.
– For MAU 3B OVHT, pull the B27 CB.
Associated AVNX MAU 3A FAIL or AVNX MAU 3B
FAIL Procedure..................................................... ACCOMPLISH
END
AVNX MAU 1 (2) (3) FAN FAIL
Crew Awareness.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
CMS FAIL
Crew Awareness.
END
CREW WRN SYS FAULT
Crew Awareness.
END
DISPLAY CTRL FAIL
NOTE: – PFD selections of VOR, FMS, RA/BARO, Minimums and
Baro setting will be locked at the last setting position
prior to the failure.
– Disregard altitude callouts from aural system.
– Use IESS for barometric setting and ILS approach.
Relevant Inoperative Items:
Bearing “<>” Pushbutton
Bearing “O” Pushbutton
FMS Pushbutton
FPR Pushbutton
HSI Pushbutton
IN/Hpa baro setting knob
PREV Pushbutton
RAD/BARO Minimums Knob
STD Pushbutton
V/L Pushbutton
WX Pushbutton
NOTE: The items above are inoperative on both pilot and copilot
display controllers.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 8
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
DISPLAY CTRL FAULT
Crew Awareness.
END
EICAS FAULT
Crosscheck EICAS information and revert if necessary.
END
EICAS OVHT
B11 CB.................................................................... PULL
Reversionary Panel Selector.................................. EICAS
END
FMS POS DISAG
Do not use FMS as navigation source.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 9
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
FMS1 (2) - GPS POS DISAG
DUAL FMS INSTALLED?
No
Yes
Select another FMS source.
END
Select another navigation source.
END
GND PROX FAIL
Increase awareness in relation to ground proximity.
END
IRS EXCESSIVE MOTION
Airplane................................................................... STOP
The IRS will restart the alignment after the motion is stopped.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 10
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
IRS 1 (2) FAIL
Reversionary Panel IRS Button.............................. PUSH
END
MFD 1 (2) FAULT
Crosscheck the affected MFD display information (System
Synoptics, MAP, TAS, TAT, SAT, TCAS info, WX radar and Terrain
Data) with the opposite side MFD display information and revert if
necessary. Disregard any non reliable information from the affected
MFD.
END
MFD 1 (2) OVHT
Associated CB........................................................ PULL
Reversion................................................................ AS REQUIRED
NOTE: – For MFD 1 OVHT, pull the B29 CB.
– For MFD 2 OVHT, pull the B20 CB.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 11
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
NAVCOM 1 (2) FAIL
Select and use the remaining NAVCOM (VHF, VOR, DME and
Transponder).
END
NAVCOM 1 (2) OVHT
Associated MRC CB............................................... PULL
NOTE: – For NAVCOM 1 OVHT, pull the C10 CB.
– For NAVCOM 2 OVHT, pull the MRC 2 Electronic CB.
Select on the MCDU: CB → CB MENU → CB BY SYSTEM
→ NEXT → NEXT→NAV → MRC 2.
NAVCOM 1 (2) FAIL Procedure.............................. ACCOMPLISH
END
PFD 1 (2) FAULT
Crosscheck the affected PFD display information (Attitude, Airspeed,
Altitude, FMA, FPA, Minimums, Baro setting, NAVCOM radio
frequencies, HDG and CRS) with the opposite side PFD display
information and revert if necessary. Disregard any non-reliable
information from the affected PFD.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 12
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
PFD 1 (2) OVHT
Associated CB........................................................ PULL
Reversionary Panel Selector.................................. AS REQUIRED
NOTE: – For PFD 1 OVHT, pull the B19 CB
– For PFD 2 OVHT, pull the B21 CB.
END
SYS CONFIG FAIL
Crew Awareness.
END
TERRAIN FAIL
Increase awareness in relation to terrain proximity.
END
VALIDATE CONFIG
Crew Awareness.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 13
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ANNUNCIATED PROCEDURES
VHF 1 (2) (3) OVHT
Associated CB........................................................ PULL
NOTE: – For VHF 1 OVHT, pull the C11 CB.
– For VHF 2 OVHT, pull the VHF 2 Electronic CB.
– For VHF 3 OVHT, pull the VHF 3 Electronic CB.
END
VHF 3 FAIL
Select another VHF source.
END
WINDSHEAR FAIL
Increase awareness in relation to weather, wind and speed
variations.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 14
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
XPDR 1 (2) IN STBY
Transponder............................................................ TA/RA OR AS
REQUIRED
END
ADS PROBE 1 (2) (3) (4) FAIL
Crew Awareness.
END
ADS 1 (2) HTR FAULT
Crew Awareness.
END
ADS 3 SLIPCOMP FAIL
Crew Awareness.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 15
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ADS 4 SLIPCOMP FAIL
Crew Awareness.
END
APM FAULT
Crew Awareness.
END
ATC 1 (2) DATALINK FAIL
Crew Awareness.
END
AURAL WRN SYS FAULT
Crew Awareness.
END
AVNX DB MODULE FAIL
Crew Awareness.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 16
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AVNX MAU 1A (1B) FAULT
Crew Awareness.
END
AVNX MAU 2A (2B) FAULT
Crew Awareness.
END
AVNX MAU 3A (3B) FAULT
Crew Awareness.
END
AVNX MAU 1 (2) (3) FAN FAULT
Crew Awareness.
END
CCD 1 (2) FAULT
Crew Awareness.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 17
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
CMC FAIL
Crew Awareness.
END
CMF 1 (2) FAIL
Crew Awareness.
END
CMS FAULT
Crew Awareness.
END
CVR AFT (FWD) FAIL
Crew Awareness.
END
DATALINK 1 (2) FAIL
Crew Awareness.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 18
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FDR AFT (FWD) FAIL
Crew Awareness.
END
FLT CTRL ADS FAIL
Crew Awareness.
END
FMS 1 (2) FAIL
ANOTHER FMS AVAILABLE?
No
Yes
Select another FMS source.
NOTE: Operative FMS is controlled only by same side MCDU.
END
Select another navigation source.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 19
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
IRS 1 (2) NAV MODE FAIL
Associated Reversionary Panel IRS Button........... PUSH
END
IRS ALIGNING
Crew Awareness.
END
IRS PRES POS INVALID
FMS Present Position............................................. ENTER OR
REENTER
END
RALT 1 (2) FAIL
ANOTHER RADIO ALTIMETER AVAILABLE?
No
Yes
During approach:
Increase awareness in relation to autothrottle operation.
CONTINUED...
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 20
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
During approach:
Autothrottle............................................................ DISENGAGE
END
TAT 1 (2) FAIL
TAT 1 FAILED?
No
Yes
TAS data from ADS 1 and 3 is not reliable anymore.
Do not couple AP and AT source to a PFD using ADS 1 or 3.
END
TAS data from ADS 2 is not reliable anymore.
Do not couple AP and AT source to a PFD using ADS 2.
AOM-1502-016
END
4-03-09
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
FMS/NAV/COMM/Flight
Instruments
Page 21
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
TCAS FAIL
Crew Awareness.
END
TERRAIN NOT AVAILABLE
Crew Awareness.
END
XPDR 1 (2) FAIL
Select and use the remaining Transponder.
4-03-09
Copyright © by Embraer. Refer to cover page for details.
Page 22
FMS/NAV/COMM/Flight
Instruments
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FUEL
TABLE OF CONTENTS
Block
Page
WARNING
FUEL 1 (2) LO LEVEL ........................................... 4-03-10......
1
CAUTION
APU FUEL SOV FAIL ............................................ 4-03-10......
ENG 1 (2) FUEL SOV FAIL .................................... 4-03-10......
FUEL IMBALANCE ................................................ 4-03-10......
2
2
2
MAU load 19.3 and on OR POST-MOD SB 190-31-0009
FUEL TANK LO TEMP ........................................... 4-03-10......
FUEL XFEED FAIL ................................................ 4-03-10......
4
5
ADVISORY
DEFUEL SOV OPEN............................................. Crew Awareness
MAU load 19.3 and on OR POST-MOD SB 190-31-0009
AOM-1502-016
FUEL AC PUMP 1 (2) FAIL....................................
FUEL DC PUMP FAIL ...........................................
FUEL EQUAL-XFEED OPEN.................................
FUEL FEED 1 (2) FAULT ......................................
FUEL KG-LB MISMATCH ......................................
4-03-10......
6
4-03-10......
6
Crew Awareness
4-03-10......
7
Crew Awareness
4-03-10-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-10-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FUEL 1 (2) LO LEVEL
EICAS Indication: Associated fuel quantity indication in red.
LAND AT THE NEAREST SUITABLE AIRPORT.
CAUTION: AVOID ATTITUDES IN EXCESS OF 15° NOSE UP OR
DOWN, UNCOORDINATED MANEUVERS AND
NEGATIVE G’S.
Associated Fuel AC Pump...................................... ON
The EICAS message may be caused by a fuel leak. Fuel leak
may be detected by either:
•
•
•
•
•
•
A fuel imbalance develops; or
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings; or
With both engines operative, an unexpected difference
between the total fuel quantity indicated on EICAS and the
total fuel quantity indicated on the FMS Fuel Management
page or PERF INIT page 3/3.
FUEL LEAK SUSPECTED?
No
Yes
FUEL LEAK Procedure........................................... ACCOMPLISH
END
Fuel Xfeed Selector................................................ AS REQUIRED
AOM-1502-016
END
4-03-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fuel
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
APU FUEL SOV FAIL
Do not restart the APU.
END
ENG 1 (2) FUEL SOV FAIL
AFTER PULLING FIRE HANDLE?
No
Yes
Associated Fuel AC Pump...................................... OFF
Fuel Xfeed Selector................................................ OFF
END
END
FUEL IMBALANCE
CONDITION:
Imbalance between wing tanks greater than the
limit.
The EICAS message may be caused by a fuel leak. Fuel leak
may be detected by either:
Excessive fuel flow in one of the engines; or
Fuel quantity from one tank decreases at abnormal rate; or
Fuel smell; or
Fuel spray from the wings; or
With both engines operative, an unexpected difference
between the total fuel quantity indicated on EICAS and the
total fuel quantity indicated on the FMS Fuel Management
page or PERF INIT page.
CONTINUED...
4-03-10
Copyright © by Embraer. Refer to cover page for details.
Page 2
Fuel
REVISION 23
AOM-1502-016
•
•
•
•
•
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
FUEL LEAK SUSPECTED?
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
No
Yes
FUEL LEAK Procedure........................................... ACCOMPLISH
END
Attitude.................................................................... WING LEVEL
•
Compare total fuel quantity indication on EICAS with fuel
remaining information indicated on FMS Fuel Management
page. If FMS fuel remaining quantity is lower than EICAS
total fuel indication, disregard FMS fuel remaining
information. Monitor fuel quantities using the EICAS
indications.
NOTE: – The guidance to compare the total fuel quantity
indication on EICAS with fuel remaining information
indicated on FMS Fuel Management page is not valid
when flying with one engine inoperative. In this case
only the fuel indications presented on EICAS must be
used.
RH WING LOWER LEVEL?
No
Yes
Fuel Xfeed Selector................................................ LOW 2
When the desired balance is achieved:
Fuel Xfeed Selector.............................................. OFF
Monitor total fuel indication in EICAS with FMS fuel remaining
information.
AOM-1502-016
END
Fuel Xfeed Selector................................................ LOW 1
CONTINUED...
4-03-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fuel
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
When the desired balance is achieved:
Fuel Xfeed Selector.............................................. OFF
Monitor total fuel indication in EICAS with FMS fuel remaining
information.
END
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
FUEL TANK LO TEMP
Airspeed.................................................................. ACCELERATE
AS MUCH AS
POSSIBLE UP
TO VMO/MMO
.........................................Wait 3 minutes.........................................
FUEL TANK LO TEMP MESSAGE PERSISTS?
No
Yes
Altitude ................................................................... DESCEND AS
REQUIRED
END
4-03-10
Copyright © by Embraer. Refer to cover page for details.
Page 4
Fuel
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FUEL XFEED FAIL
FUEL XFEED SELECTOR OFF?
No
Yes
END
FUEL IS BEING EQUALIZED?
No
Yes
When appropriate:
Fuel Xfeed Selector.............................................. OFF
END
Fuel Xfeed Selector................................................ OFF
Asymmetric Thrust.................................................. AS REQUIRED
AOM-1502-016
END
4-03-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fuel
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
DEFUEL SOV OPEN
Crew Awareness.
END
!MAU load 19.3 and on OR POST-MOD SB 190-31-0009
FUEL AC PUMP 1 (2) FAIL
Fuel Xfeed Selector................................................ OFF
END
"
FUEL DC PUMP FAIL
Fuel DC Pump Selector ......................................... OFF
END
FUEL EQUAL-XFEED OPEN
Crew Awareness.
4-03-10
Copyright © by Embraer. Refer to cover page for details.
Page 6
Fuel
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
FUEL FEED 1 (2) FAULT
IN FLIGHT?
No
Yes
Continue the flight monitoring the systems.
END
Emergency/Parking Brake.................................... SET
Associated FUEL AC PUMP................................. AUTO
Associated Thrust Lever....................................... ADVANCE to
65% N2
Associated FUEL AC PUMP................................. ON
.........................................Wait 5 seconds.........................................
Associated FUEL AC PUMP................................. AUTO
FUEL FEED 1 (2) FAULT MESSAGE PERSISTS?
No
Yes
Do not takeoff.
Associated Thrust Lever......................................... IDLE
AOM-1502-016
END
4-03-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Fuel
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
FUEL KG-LB MISMATCH
Crew Awareness.
4-03-10
Copyright © by Embraer. Refer to cover page for details.
Page 8
Fuel
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
HYDRAULICS
TABLE OF CONTENTS
Block
Page
AOM-1502-016
WARNING
HYD 1 (2) OVERHEAT........................................... 4-03-11 ......
1
HYD 3 OVERHEAT................................................ 4-03-11 ......
1
CAUTION
HYD PTU FAIL ......................................................
HYD 1 (2) EDP NOT D-PRESS..............................
HYD 1 (2) HI TEMP ...............................................
HYD 3 HI TEMP ....................................................
HYD 1 (2) LO PRESS............................................
HYD 3 LO PRESS .................................................
HYD 3 VLV FAIL....................................................
4-03-11 ......
4-03-11 ......
4-03-11 ......
4-03-11 ......
4-03-11 ......
4-03-11 ......
4-03-11 ......
2
2
3
3
3
4
4
ADVISORY
HYD PTU NOT AUTO ...........................................
HYD PUMP NOT AUTO ........................................
HYD TEMP SENS FAIL.........................................
HYD 1 (2) EDP FAIL .............................................
HYD 1 (2) ELEC PUMP FAIL.................................
HYD 3 ELEC PUMP A FAIL...................................
HYD 3 ELEC PUMP B FAIL ..................................
HYD 1 (2) (3) LO QTY ..........................................
HYD 1 (2) SOV FAIL .............................................
HYD 3 PUMP A NOT ON ......................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-11 ......
5
4-03-11 ......
6
4-03-11 ......
7
Crew Awareness
Crew Awareness
Crew Awareness
4-03-11-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 14
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-11-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 14
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
HYD 1 (2) OVERHEAT
Associated Electric Hydraulic Pump Selector ....... OFF
Associated Engine Pump Shutoff Button............... PUSH IN
HYD 1 (2) SOV FAIL MESSAGE PRESENTED?
No
Yes
LAND AT THE NEAREST SUITABLE AIRPORT.
ENGINE SHUTDOWN Procedure ......................... ACCOMPLISH
Appropriate LOSS OF HYDRAULIC SYSTEM 1 or
LOSS OF HYDRAULIC SYSTEM 2 Procedure.... ACCOMPLISH
END
HYD 3 OVERHEAT
Electric HYD SYS 3 Pump A Selector ................... OFF
Electric HYD SYS 3 Pump B Selector .................. OFF
Relevant Inoperative Items:
Outboard Aileron Actuators.
AOM-1502-016
END
4-03-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Hydraulics
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
HYD PTU FAIL
PTU Selector........................................................... ON
HYD PTU FAIL MESSAGE PERSISTS?
No
Yes
PTU Selector Knob................................................. OFF
END
NOTE: During cruise flight, the PTU Selector Knob may be turned
to AUTO.
END
HYD 1 (2) EDP NOT D-PRESS
An engine windmill restart will not be available.
4-03-11
Copyright © by Embraer. Refer to cover page for details.
Page 2
Hydraulics
REVISION 17
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
HYD 1 (2) HI TEMP
Associated Electric Hydraulic Pump Selector ....... OFF
END
HYD 3 HI TEMP
Electric Hydraulic Pump A Selector........................ OFF
END
HYD 1 (2) LO PRESS
Associated Electric Hydraulic Pump Selector ....... ON
HYD 1 (2) LO PRESS MESSAGE PERSISTS?
No
Yes
Associated Electric Hydraulic Pump Selector......... OFF
Appropriate LOSS OF HYDRAULIC SYSTEM 1 or
LOSS OF HYDRAULIC SYSTEM 2........................ ACCOMPLISH
END
AOM-1502-016
END
4-03-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Hydraulics
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
HYD 3 LO PRESS
Electric Hydraulic Pump B Selector ...................... ON
Electric Hydraulic Pump A Selector........................ OFF
HYD 3 LO PRESS MESSAGE PERSISTS?
No
Yes
Electric Hydraulic Pump B Selector........................ OFF
Relevant Inoperative Items:
Outboard Aileron Actuators.
END
END
HYD 3 VLV FAIL
Airspeed.................................................................. MIN 130 KIAS
4-03-11
Copyright © by Embraer. Refer to cover page for details.
Page 4
Hydraulics
REVISION 17
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
HYD PTU NOT AUTO
Crew Awareness.
END
HYD PUMP NOT AUTO
Crew Awareness.
END
HYD TEMP SENS FAIL
Crew Awareness.
END
HYD 1 (2) EDP FAIL
Crew Awareness.
END
HYD 1 (2) ELEC PUMP FAIL
BOTH PUMPS AFFECTED AND ASSOCIATED WITH ANY FLAP No
OR SLAT MALFUNCTION MESSAGE?
Yes
Both Electric Hydraulic Pump Selectors................. ON
HYD 1 ELEC PUMP FAIL AND HYD 2 ELEC PUMP FAIL No
MESSAGES DISAPPEAR?
AOM-1502-016
Yes
CONTINUED...
4-03-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Hydraulics
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Both Electric Hydraulic Pump Selectors................. AUTO
NOTE: – The messages will be posted again after the pumps are
turned back to AUTO. Consider the messages spurious.
– At any moment, if the Slat/Flap lever is moved out of
position 0, the messages will extinguish.
END
Associated Electric Hydraulic Pump Selector ....... OFF
END
HYD 3 ELEC PUMP A FAIL
Electric Hydraulic Pump A Selector........................ OFF
4-03-11
Copyright © by Embraer. Refer to cover page for details.
Page 6
Hydraulics
REVISION 17
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
HYD 3 ELEC PUMP B FAIL
Electric Hydraulic Pump B Selector........................ OFF
END
HYD 1 (2) (3) LO QTY
Crew Awareness.
END
HYD 1 (2) SOV FAIL
Crew Awareness.
END
HYD 3 PUMP A NOT ON
Crew Awareness.
AOM-1502-016
END
4-03-11
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Hydraulics
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-11
Copyright © by Embraer. Refer to cover page for details.
Page 8
Hydraulics
REVISION 17
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
ICE AND RAIN PROTECTION
TABLE OF CONTENTS
Block
Page
AOM-1502-016
WARNING
A-I WING 1 (2) LEAK............................................. 4-03-12......
1
CAUTION
A-I ENG 1 (2) FAIL ................................................
A-I LO CAPACITY..................................................
A-I WING FAIL.......................................................
A-I WING NO DISPATCH .......................................
ICE DETECTOR 1 (2) FAIL ....................................
WINDSHIELD 1 (2) HTR FAIL ................................
4-03-12......
4-03-12......
4-03-12......
4-03-12......
4-03-12......
4-03-12......
2
3
4
5
5
6
ADVISORY
A-I ENG 1 (2) FAULT ............................................
A-I MODE NOT AUTO...........................................
A-I SWITCH OFF ..................................................
ICE CONDITION ...................................................
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-12-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-12-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
A-I WING 1 (2) LEAK
Ice Protection Wing Button..................................... PUSH OUT
Icing Conditions ..................................................... EXIT/AVOID
A-I WING 1 (2) LEAK MESSAGE PERSISTS?
No
Yes
Affected Bleed Button............................................. PUSH OUT
XBleed Button......................................................... PUSH OUT
Altitude.................................................................... MAX 31000 ft
AFFECTED BLEED 1?
No
Yes
APU Bleed Button................................................... PUSH OUT
During Landing:
ICE CONDITIONS OR ICE ACCRETION?
No
Yes
Landing Configuration:
Slat/Flap................................................................ 5
AOM-1502-016
Set VREF FLAP 5 ICE.
CONTINUED...
4-03-12
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Ice and Rain Protection
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.25.
UNFACTORED
NOTE: Limit bank angle to 20°.
NOTE: Do not perform the A-I WING FAIL procedure.
END
A-I ENG 1 (2) FAIL
Affected Ice Protection Engine Button.................... PUSH OUT,
THEN IN
A-I ENG 1 (2) FAIL MESSAGE EXTINGUISHES?
No
Yes
END
Ice Protection Mode Selector................................. ON
A-I ENG 1 (2) FAIL MESSAGE PERSISTS?
No
Yes
Icing Conditions....................................................... EXIT/AVOID
HIGH ENGINE VIBRATION?
No
ENGINE ABNORMAL VIBRATION Procedure........ ACCOMPLISH
CONTINUED...
4-03-12
Copyright © by Embraer. Refer to cover page for details.
Page 2
Ice and Rain Protection
REVISION 23
AOM-1502-016
Yes
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
Two minutes after exiting icing conditions:
Ice Protection Mode Selector............................... AUTO
END
A-I LO CAPACITY
Thrust Levers.......................................................... ADVANCE
A-I LO CAPACITY MESSAGE PERSISTS?
No
Yes
Icing Conditions....................................................... EXIT/AVOID
END
AOM-1502-016
END
4-03-12
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Ice and Rain Protection
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
A-I WING FAIL
Ice Protection Wing Button..................................... PUSH OUT,
THEN IN
A-I WING FAIL MESSAGE EXTINGUISHES?
No
Yes
END
Ice Protection Mode Selector................................. ON
A-I WING FAIL MESSAGE PERSISTS?
No
Yes
Ice Protection Mode Selector.................................. AUTO
Ice Protection Wing Button..................................... PUSH OUT
Icing Conditions ..................................................... EXIT/AVOID
LANDING IN ICING CONDITION OR WITH ICE ACCRETION?
No
Yes
Landing Configuration:
Slat/Flap................................................................ 5
CONTINUED...
4-03-12
Copyright © by Embraer. Refer to cover page for details.
Page 4
Ice and Rain Protection
REVISION 23
AOM-1502-016
Set VREF FLAP 5 ICE .
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.25.
UNFACTORED
NOTE: Limit bank angle to 20°.
END
Two minutes after exiting icing conditions:
Ice Protection Mode Selector............................... AUTO
END
A-I WING NO DISPATCH
Do not perform an assisted engine start.
END
ICE DETECTOR 1 (2) FAIL
When flying in icing conditions:
Ice Protection Mode Selector............................... ON
Two minutes after exiting icing conditions:
Ice Protection Mode Selector........................... AUTO
AOM-1502-016
END
4-03-12
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Ice and Rain Protection
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
WINDSHIELD 1 (2) HTR FAIL
Affected Windshield Heating Button....................... PUSH OUT,
THEN IN
WINDSHIELD 1 (2) HTR FAIL MSG EXTINGUISHES?
No
Yes
END
Affected Windshield Heating Button....................... PUSH OUT
END
A-I ENG 1 (2) FAULT
Crew Awareness.
4-03-12
Copyright © by Embraer. Refer to cover page for details.
Page 6
Ice and Rain Protection
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
A-I MODE NOT AUTO
Crew Awareness.
END
A-I SWITCH OFF
Crew Awareness.
END
ICE CONDITION
Crew Awareness.
AOM-1502-016
END
4-03-12
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Ice and Rain Protection
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-12
Copyright © by Embraer. Refer to cover page for details.
Page 8
Ice and Rain Protection
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
LANDING GEAR AND BRAKES
TABLE OF CONTENTS
Block
Page
WARNING
AOM-1502-016
LG LEVER DISAG ................................................. 4-03-13......
1
CAUTION
AUTOBRAKE FAIL ................................................
BRK LH (RH) FAIL.................................................
BRK OVERHEAT ...................................................
EMER BRK FAIL ...................................................
LG NO DISPATCH .................................................
LG NOSE DOOR OPEN ........................................
LG WOW SYS FAIL...............................................
PRKG BRK NOT RELEASED.................................
STEER FAIL..........................................................
4-03-13......
2
4-03-13......
2
4-03-13......
2
4-03-13......
3
Crew Awareness
4-03-13......
3
4-03-13......
4
4-03-13......
4
4-03-13......
5
ADVISORY
BRK CONTROL FAULT .........................................
BRK LH (RH) FAULT.............................................
BRK PEDL LH (RH) SEAT FAIL.............................
EMER BRK FAULT ...............................................
LG TEMP EXCEEDANCE .....................................
STEER FAULT ......................................................
4-03-13......
6
4-03-13......
6
Crew Awareness
Crew Awareness
Crew Awareness
Crew Awareness
4-03-13-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-13-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
LG LEVER DISAG
EICAS Indication: One or more landing gear indications disagree
with the landing gear lever.
Landing Gear Lever................................................ CYCLE
LG LEVER DISAG MESSAGE PERSISTS?
No
Yes
DURING EXTENSION?
No
Yes
ABNORMAL LANDING GEAR EXTENSION
Procedure................................................................ ACCOMPLISH
END
Landing Gear Lever................................................ DOWN
Icing Conditions ..................................................... EXIT/AVOID
END
AOM-1502-016
END
4-03-13
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing Gear and Brakes
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
AUTOBRAKE FAIL
Apply brakes normally.
END
BRK LH (RH) FAIL
NOTE: Thrust reverser may also be used to stop the airplane.
During landing run gradually apply the normal brake, using rudder
pedals to steer the airplane.
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.51.
UNFACTORED
END
BRK OVERHEAT
ON GROUND?
No
Yes
Airplane................................................................... STOP
Chocks.................................................................... ON
Emergency/Parking Brake...................................... OFF
END
Landing Gear.......................................................... DOWN
Yes
No
CONTINUED...
4-03-13
Copyright © by Embraer. Refer to cover page for details.
Page 2
Landing Gear and Brakes
REVISION 23
AOM-1502-016
BRK OVERHEAT MESSAGE PERSISTS?
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
After the BRK OVERHEAT message disappears:
.........................................Wait 5 minutes.........................................
Landing Gear.......................................................... UP
END
EMER BRK FAIL
CONDITION:
Emergency/Parking Brake is inoperative.
When parking the airplane, use wheel chocks.
END
LG NO DISPATCH
Crew Awareness.
END
LG NOSE DOOR OPEN
Airspeed.................................................................. MAX 250 KIAS
GEAR LEVER DOWN?
No
Yes
CAUTION: DO NOT MOVE THE LANDING GEAR LEVER UP,
EXCEPT FOR CLIMB PERFORMANCE TO CLEAR
OBSTACLES.
AOM-1502-016
END
4-03-13
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing Gear and Brakes
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
END
LG WOW SYS FAIL
LAND AT THE NEAREST SUITABLE AIRPORT.
Icing Conditions ..................................................... EXIT/AVOID
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF
FULL.
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.30.
UNFACTORED
NOTE: – Thrust Reversers, Steering, Ground Spoilers, Wing
Anti-Ice and Ground Idle may not be available.
– If the Weather Radar is inoperative, the Forced Standby
option may be available to allow its use.
If a go-around is required, keep the landing gear lever DOWN in
case the gear lever can not be moved up.
END
PRKG BRK NOT RELEASED
Emergency/Parking Brake Lever............................ CYCLE
CONTINUED...
4-03-13
Copyright © by Embraer. Refer to cover page for details.
Page 4
Landing Gear and Brakes
REVISION 23
AOM-1502-016
Ensure that the lever is completely stowed.
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MESSAGE PERSISTS?
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
No
Yes
Parking Brake may or may not be locked.
Expect a potential tire burst during landing.
Landing Configuration:
Slat/Flap................................................................ FULL
Set VREF FULL.
After Landing:
If no unusual brake action is noticed, apply brakes normally.
END
END
STEER FAIL
Steer the airplane using differential braking and rudder.
NOTE: During taxi, smooth radius turns must be performed.
AOM-1502-016
END
4-03-13
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing Gear and Brakes
Page 5
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
BRK CONTROL FAULT
Brakes..................................................................... APPLY
NORMALLY
Landing configuration:
Slat/Flap................................................................ FULL
Set VREF FULL.
END
BRK LH (RH) FAULT
NOTE: During landing run, expect a slight directional tendency.
Landing Configuration:
Slat/Flap................................................................ FULL
Set Vref FULL.
Brakes..................................................................... APPLY
NORMALLY
!O.B Nº 170-002/07 - Simultaneous BRAKE LH (RH) FAULT messages
NOTE: Do not move the landing gear up except to improve climb
performance or airplane range.
"
BOTH SIDES AFFECTED?
No
Yes
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.51.
UNFACTORED
CONTINUED...
4-03-13
Copyright © by Embraer. Refer to cover page for details.
Page 6
Landing Gear and Brakes
REVISION 23
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
...CONTINUED
CAUTION: MULTIPLY THE FULL FLAPS
LANDING DISTANCE BY 1.19.
UNFACTORED
END
BRK PEDL LH (RH) SEAT FAIL
Crew Awareness.
END
EMER BRK FAULT
Crew Awareness.
END
LG TEMP EXCEEDANCE
Crew Awareness.
END
STEER FAULT
Crew Awareness.
AOM-1502-016
END
4-03-13
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing Gear and Brakes
Page 7
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-13
Copyright © by Embraer. Refer to cover page for details.
Page 8
Landing Gear and Brakes
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
OXYGEN
TABLE OF CONTENTS
Block
Page
CAUTION
CREW OXY LO PRESS......................................... 4-03-14......
PAX OXY NOT DEPLOYED ................................... 4-03-14......
1
1
AOM-1502-016
ADVISORY
OBSERVER OXY LO PRESS................................ 4-03-14......
1
PAX OXY SW NOT AUTO ..................................... Crew Awareness
4-03-14-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-03-14-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 17
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
CREW OXY LO PRESS
Altitude.................................................................... 10000 ft or
MEA,
WHICHEVER
IS HIGHER
END
PAX OXY NOT DEPLOYED
If required:
Passenger Oxygen Selector................................. OVRD
END
OBSERVER OXY LO PRESS
OBSERVER SEAT OCCUPIED?
No
Yes
Altitude ................................................................... 10000 ft or
MEA,
WHICHEVER
IS HIGHER
END
AOM-1502-016
END
4-03-14
Copyright © by Embraer. Refer to cover page for details.
REVISION 17
Oxygen
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
ANNUNCIATED PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
PAX OXY SW NOT AUTO
Crew Awareness.
4-03-14
Copyright © by Embraer. Refer to cover page for details.
Page 2
Oxygen
REVISION 17
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AUTOLAND
TABLE OF CONTENTS
Block
Page
ABNORMAL
Airplanes equipped with Autoland System, ANAC or FAA
certification
AOM-1502-016
ABNORMAL CALL-OUTS.......................................
AUTOPILOT MALFUNCTION .................................
HARDOVER ..........................................................
ONE ENGINE INOPERATIVE APPROACH .............
SLOWOVER..........................................................
4-04-52......
4-04-52......
4-04-52......
4-04-52......
4-04-52......
4
3
1
2
1
4-04-52-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-52-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
Airplanes equipped with Autoland system
HARDOVER
If any unusual acceleration or motion is noticed on the airplane flight
path the approach must be discontinued, and:
Autopilot.................................................................. DISENGAGE
MISSED APPROACH Procedure........................... PERFORM AS
REQUIRED
!Airplanes equipped with Autoland system, FAA and EASA Certification
NOTE: Consider the possibility of continuing and performing the
landing if the meteorological conditions and airplane attitude
permit an approach with the available systems.
"
END
SLOWOVER
The Slowover consists in a smooth and slow airplane attitude change
due to an autopilot system malfunction. It may be recognized if one
of the following symptoms occurs during approach:
– Unusual glide slope small deviation.
– Change in the rate of descent (small or large).
– Excessive glide slope deviation and the GS indications
becoming amber.
– Autopilot or Autoland 1 self disconnection.
If a Slowover tendency is confirmed:
Autopilot................................................................ DISENGAGE
MISSED APPROACH Procedure......................... PERFORM AS
REQUIRED
NOTE: Consider the possibility of continuing and performing the
landing if the meteorological conditions and airplane attitude
permit an approach with the available systems.
AOM-1502-016
END
4-04-52
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
AUTOLAND
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
ONE ENGINE INOPERATIVE APPROACH
ENGINE FAILURE BEFORE FINAL APPROACH
The Automatic Flight Control System has demonstrated adequate
performance for low visibility approach with an inoperative engine.
Before Autoland 1 engagement directional control should be
maintained through rudder pedals. Adjust the yaw trim to zero just
after Autoland 1 engagement.
NOTE: – The reference speed for one engine failure to be used is
VREF = VREF FULL + 20 KIAS.
ENGINE FAILURE ON FINAL APPROACH
Go-Around............................................................... PERFORM
!190/195 models equipped with Autoland system, ANAC or FAA certification
OBSTACLE CLEARENCE DURING GO AROUND
In order to determine a safe obstacle clearance, considering a
coupled go around during approach, the following information shall
be used:
– Height loss from go around point: 49 ft.
– Distance from go around point to the point where approach
climb speed is attained: 2.5 nm.
– Height gain from go around point to the point where approach
climb speed is attained: 63 ft.
After reaching the point where approach climb speed is attained,
use the approach climb gradient presented in the CAFM.
"
4-04-52
Copyright © by Embraer. Refer to cover page for details.
Page 2
AUTOLAND
REVISION 21
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AUTOPILOT MALFUNCTION
BEFORE REACHING FAF
If the Autopilot is disengaged manually or automatically, it may be
reengaged.
If the autopilot disengages again:
MISSED APPROACH Procedure........................... PERFORM AS
REQUIRED
!Airplanes equipped with Autoland system, FAA and EASA Certification
NOTE: – Consider the possibility of continuing and performing the
landing if the meteorological conditions and airplane
attitude permit an approach with the available systems.
– Consider the possibility of continuing to CAT I minima.
"
AFTER REACHING FAF
If the Autopilot is disengaged manually or automatically, it must not
be reengaged.
MISSED APPROACH Procedure........................... PERFORM AS
REQUIRED
!Airplanes equipped with Autoland system, FAA and EASA Certification
NOTE: – Consider the possibility of continuing and performing the
landing if the meteorological conditions and airplane
attitude permit an approach with the available systems.
– Consider the possibility of continuing to CAT I minima.
"
EXCESSIVE DEVIATION WARNING
– Above 200 ft: Monitor the ILS deviation to ensure that the
airplane returns to the center beam.
AOM-1502-016
– At or below 200 ft:
CONTINUED...
4-04-52
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
AUTOLAND
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MISSED APPROACH Procedure........................... PERFORM AS
REQUIRED
!Airplanes equipped with Autoland system, FAA and EASA Certification
NOTE: Consider the possibility of continuing and performing the
landing if the meteorological conditions permit an approach
with the available systems.
"
END
!Airplanes equipped with Autoland System, ANAC or FAA certification
ABNORMAL CALL-OUTS
In addition to the normal call-outs, the following abnormalities should
be called out during an Autoland 1 operation:
– Above 100 ft:
– Excessive LOC or GS deviations.
– Airspeed 10 kt higher or 5 kt lower than the target speed.
– Roll angle in excess of 25°.
– Pitch angle below - 5° or above 5°.
– Rate of descent in excess of 1200 ft/min.
– Below 100 ft:
– Excessive LOC or GS deviations.
– Airspeed 10 kt higher or 5 kt lower than the target speed.
– Roll angle in excess of 5°.
– Pitch angle below 0° or above 10°.
– Rate of descent in excess of 800 ft/min.
END
4-04-52
Copyright © by Embraer. Refer to cover page for details.
Page 4
AUTOLAND
REVISION 21
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
CATEGORY II OPERATION
TABLE OF CONTENTS
Block
AOM-1502-016
ABNORMAL
ABNORMALITIES ..................................................
ALTITUDE LOSS ...................................................
AUTOPILOT MALFUNCTION .................................
ENGINE FAILURE ON FINAL APPROACH OR
DURING GO-AROUND ....................................
HARDOVER ..........................................................
SLOWOVER..........................................................
Page
4-04-54......
4-04-54......
4-04-54......
4
1
3
4-04-54......
4-04-54......
4-04-54......
2
1
2
4-04-54-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-54-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 9
AOM-1502-016
INTENTIONALLY BLANK
EMERGENCY AND
ABNORMAL PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
SUPPLEMENTARY PROCEDURES
ALTITUDE LOSS
The demonstrated altitude loss due to a pitch down hardover during
flight test is presented in the graph below.
– Recovery initiated 1 second after failure recognition:
300
250
FAILURE OCCURS
AIRPLANE WHEEL
150
100
50
FAILURE
RECOGNIZED
RECOVERY
INITIATED
0
−800 −600 −400 −200
RUNWAY
THRESHOLD
SLOPE 1/29
0
200
400
600
800
EM170AOM050003C.DGN
ALTITUDE − ft
200
1000 1200 1400
HORIZONTAL DISTANCE − m
HARDOVER ALTITUDE LOSS
NOTE: The maximum demonstrated altitude loss due to autopilot
malfunction is 20 ft.
END
AOM-1502-016
HARDOVER
If any unusual acceleration or motion is noticed on the airplane
flight path the approach must be discontinued, and:
Autopilot................................................................ DISENGAGE
CONTINUED...
4-04-54
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Category II Operation
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
MISSED APPROACH Procedure......................... PERFORM AS
REQUIRED
Perform a normal MISSED APPROACH Procedure, unless the
approach is continued under visual conditions and the airplane
position and attitude assure a safe landing.
END
SLOWOVER
The Slowover consists in a smooth and slow airplane attitude change
due to an autopilot system malfunction. It may be recognized if one
of the following symptoms occurs during approach:
– Unusual glide slope small deviation.
– Change in the rate of descent (small or large).
– Excessive glide slope deviation and the GS indications
becoming amber.
– Autopilot self disconnection.
If a Slowover tendency is confirmed:
Autopilot................................................................ DISENGAGE
MISSED APPROACH Procedure......................... PERFORM AS
REQUIRED
NOTE: Consider the possibility of continuing and performing the
landing if under visual conditions and the airplane position
and attitude assure a safe landing.
END
ENGINE FAILURE ON FINAL APPROACH OR
DURING GO-AROUND
Go-Around............................................................... PERFORM
4-04-54
Copyright © by Embraer. Refer to cover page for details.
Page 2
Category II Operation
REVISION 9
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AUTOPILOT MALFUNCTION
BEFORE REACHING FAF
If the autopilot disengages or has to be disengaged, try to
reengage it.
If the autopilot disengages again:
MISSED APPROACH Procedure..................... PERFORM AS
REQUIRED
NOTE: Consider the possibility of continuing and performing the
landing if under visual conditions and the airplane position
and attitude assure a safe landing.
AFTER REACHING FAF
If the autopilot disengages or has to be disengaged, do not reengage
the autopilot.
MISSED APPROACH Procedure........................... PERFORM AS
REQUIRED
NOTE: Consider the possibility of continuing and performing the
landing if under visual conditions and the airplane position
and attitude assure a safe landing.
DISPLAY WARNINGS DURING FINAL APPROACH
Discontinue the approach if any of the following warnings occur:
– APPR 1 ONLY displayed on Autopilot Approach Status
Annunciator,
– EICAS message APPR 2 NOT AVAIL presented,
– RALT FAIL (cyan),
– RA (amber),
– GS (amber),
– LOC (amber),
– PIT (amber),
AOM-1502-016
– HDG (amber),
– CAS (amber),
CONTINUED...
4-04-54
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Category II Operation
Page 3
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
– FPA (amber).
Perform a normal MISSED APPROACH Procedure, unless the
approach is continued under visual conditions and the airplane
position and attitude assure a safe landing.
EXCESSIVE DEVIATION WARNING
If warning occurs above 200 ft Radio Altitude:
Monitor the ILS deviation to ensure that the airplane returns to the
center beam.
If not recovered up to 200 ft radio altitude:
Discontinue the approach.
If warning occurs below 200 ft Radio Altitude:
Discontinue the approach.
In both cases, perform a normal MISSED APPROACH Procedure,
unless the approach is continued under visual conditions and the
airplane position and attitude assure a safe landing.
END
ABNORMALITIES
The following abnormalities are deviation from CAT II ILS tracking
normal range and must be called out:
– Excessive LOC or GS deviations.
– Airspeed 10 kt higher or 5 kt lower than the Landing
Reference Speed (VREF 5).
– Roll angle in excess of 25°.
– Pitch angle below -5° or above 5°.
– Rate of descent in excess of 1200 ft/min.
4-04-54
Copyright © by Embraer. Refer to cover page for details.
Page 4
Category II Operation
REVISION 9
AOM-1502-016
END
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
ELECTRONIC FLIGHT BAG (EFB)
TABLE OF CONTENTS
Block
Page
AOM-1502-016
ABNORMAL
ELECTRONIC FLIGHT BAG (EFB)......................... 4-04-56......
1
4-04-56-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-56-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
Airplanes equipped with CMC Electronic Flight Bag (EFB)
ELECTRONIC FLIGHT BAG (EFB)
ABNORMAL OPERATION
Information about abnormal operation is presented in the table
below:
ACTION
Check that the power
connections are secure. Verify
POWER UP - The unit fails to
that the circuit breakers (Pilot
power up.
and Copilot) are closed. Check
that the EDU is connected
properly to the I/O connector.
To lighten or darken the display,
BRIGHTNESS - The display is
use the top right Brightness
too dark or too light.
buttons of the EDU.
HARDWARE - USB device not Unplug the USB device, wait 10
working.
seconds and then reconnect it.
WINDOWS - Shutdown not
Press the reset button at the
functioning.
top of the EDU.
Enable wireless functionality
and enter parameters via
WIRELESS COMMUNICATION
Windows Control Panel
- Inoperative.
(Start/Control Panel/Network
Connection).
Prior to exiting Setup, ensure to
MASTER MENU - Changed
select Save and Exit. The
Master Menu setting via the
PilotView™ EFB will need to be
Setup application and changes
restarted to make the changes
are not active.
active.
Password is case sensitive.
PASSWORD - Invalid when
Make sure that Caps Lock is
trying to exit Master Menu.
not activated.
AOM-1502-016
FAILURE
4-04-56
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Electronic Flight Bag (EFB)
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-56
Copyright © by Embraer. Refer to cover page for details.
Page 2
Electronic Flight Bag (EFB)
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
RVSM OPERATION
TABLE OF CONTENTS
Block
Page
AOM-1502-016
ABNORMAL
EMERGENCY AND ABNORMAL PROCEDURES ... 4-04-57......
1
4-04-57-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 10
Table of Contents
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-57-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 10
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
EMERGENCY AND ABNORMAL PROCEDURES
– In case of either emergency, abnormal situation or
contingencies (equipment failures, weather, etc.), which affect
the ability to maintain the cleared flight level, notify ATC and
co-ordinate an action plan that is appropriate to the airspace
concerned;
– Notify ATC when encountering greater than moderate
turbulence;
AOM-1502-016
– If unable to notify ATC and obtain an ATC clearance prior to
deviating from the cleared flight level, follow any established
contingency procedures and obtain ATC clearance as soon
as possible.
4-04-57
Copyright © by Embraer. Refer to cover page for details.
REVISION 10
RVSM OPERATION
Page 1
EMERGENCY AND
ABNORMAL PROCEDURES
SUPPLEMENTARY PROCEDURES
AIRPLANE
OPERATIONS
MANUAL
4-04-57
Copyright © by Embraer. Refer to cover page for details.
Page 2
RVSM OPERATION
REVISION 10
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
SECTION 5
PERFORMANCE
TABLE OF CONTENTS
AOM-1502-016
Block
Page
Configuration and Definitions............................ 5-01 ...........
AIRSPEED DEFINITIONS..................................... 5-01 ...........
METEOROLOGICAL DEFINITIONS...................... 5-01 ...........
CONTAMINATED RUNWAY.................................. 5-01 ...........
1
1
3
3
Data Conversion................................................... 5-10 ...........
DEMONSTRATED CROSSWIND.......................... 5-10 ...........
WIND AND ALTITUDE CONVERSION.................. 5-10 ...........
ALTIMETER SETTING TO STATION PRESSURE.. 5-10 ...........
GEOMETRIC HEIGHT TO PRESSURE HEIGHT.. 5-10 ...........
1
1
1
3
6
Thrust Setting....................................................... 5-15 ...........
THRUST SETTING TABLES................................. 5-15 ...........
1
1
Takeoff................................................................... 5-20 ...........
TAKEOFF ANALYSIS DESCRIPTION AND USE.. 5-20 ...........
ASSUMED TEMPERATURE REDUCED
THRUST........................................................... 5-20 ...........
FLEXIBLE TEMPERATURE DETERMINATION
TABLES............................................................ 5-20 ...........
SIMPLIFIED TAKEOFF ANALYSIS TABLES......... 5-20 ...........
TAKEOFF SPEEDS............................................... 5-20 ...........
FLAP RETRACTION SPEED SCHEDULE............ 5-20 ...........
FINAL SEGMENT SPEED..................................... 5-20 ...........
STAB TRIM SETTING FOR TAKEOFF................. 5-20 ...........
ALL ENGINES OPERATING.................................. 5-20 ...........
1
1
8
29
48
57
58
59
63
Supplementary Takeoff Information................... 5-25 ...........
SUPPLEMENTARY TAKEOFF INFORMATION.... 5-25 ...........
ACN........................................................................ 5-25 ...........
1
1
7
Approach............................................................... 5-30 ...........
APPROACH AND LANDING SPEEDS.................. 5-30 ...........
1
1
4
5-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Table of Contents
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
Block
Page
APPROACH CLIMB GRADIENT........................... 5-30 ........... 5
Landing................................................................. 5-35 ........... 1
UNFACTORED LANDING DISTANCE.................. 5-35 ........... 1
OPERATIONAL LANDING DISTANCE.................. 5-35 ........... 28
QUICK TURN AROUND WEIGHT......................... 5-35 ........... 42
1
1
2
5-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 23
AOM-1502-016
Supplementary Operations................................. 5-40 ...........
CAT II OPERATION............................................... 5-40 ...........
AUTOLAND............................................................ 5-40 ...........
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
AIRSPEED DEFINITIONS
INDICATED AIRSPEED – KIAS
It is the reading on the airspeed indicator (knots), as installed in the
airplane, uncorrected for static source position error. Zero instrument
error is assumed.
CALIBRATED AIRSPEED – KCAS
It is the indicated airspeed (knots), corrected for static source position
error.
TRUE AIRSPEED – TAS
It is the equivalent airspeed corrected for atmospheric density effects.
CRITICAL ENGINE FAILURE SPEED – VEF
It is the speed at which the critical engine fails. May not be less than
VMCG.
1-G STALL SPEED – VS1G
Is the minimum speed at which the lift provided by the wing is capable of
supporting the weight of the airplane.
REFERENCE STALL SPEED – VSR
It is stall speed used as the reference in determining the various airplane
speeds. VSR may not be less than VS1G.
TAKEOFF DECISION SPEED – V1
It is the speed at which, following a failure of one engine at VEF, the
decision to continue the takeoff results in:
•
A takeoff distance to a height of 35 ft at V2 speed, that will not exceed
the available takeoff distance;
•
A distance to bring the airplane to a full stop that will not exceed the
accelerate-stop distance available.
AOM-1502-016
V1 must not be greater than the rotation speed (VR).
5-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 18
Configuration and Definitions
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
ROTATION SPEED – VR
It is the speed at which rotation is initiated during the takeoff, to attain
the takeoff safety speed at or before a height of 35 ft above runway
surface.
TAKEOFF SAFETY SPEED – V2
The target speed to be attained at a height of 35 ft during a takeoff with
an engine failure.
AIR MINIMUM CONTROL SPEED – VMCA
The minimum flight speed at which the airplane is controllable with a
maximum 5° bank, when one engine suddenly becomes inoperative with
the remaining engine operating at takeoff power. The value presented
represents the most critical combination of power, weight, and center of
gravity.
GROUND MINIMUM CONTROL SPEED – VMCG
The minimum speed on the ground at which the takeoff can be
continued, utilizing aerodynamic controls alone, when one engine
suddenly becomes inoperative and the remaining engine is operating at
takeoff power. The value presented represents the most critical
combination of power, weight, and center of gravity.
LANDING REFERENCE SPEED – VREFXX
The speed at a height of 50 ft in a normal landing. This speed is equal to
1.23 VS1G in the landing configuration (gear down and specific landing
flaps XX).
MANEUVERING SPEED – VA
The maximum speed at which application of full available aileron or
rudder will not overstress the airplane.
Maneuver involving pitching control must not exceed the limit load factor
defined in Section 2 – Limitations.
VMCL is the minimum control speed during landing and approach with all
engines operating, when the critical engine is suddenly made inoperative.
5-01
Copyright © by Embraer. Refer to cover page for details.
Page 2
Configuration and Definitions
REVISION 18
AOM-1502-016
MINIMUM CONTROL SPEEDS DURING LANDING AND
APPROACH – VMCL
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
FINAL TAKEOFF SEGMENT SPEED – VFS
It is the speed to be achieved during final segment, with landing gear up
and flaps retracted.
METEOROLOGICAL DEFINITIONS
INTERNATIONAL STANDARD ATMOSPHERE – ISA
As accepted by the International Civil Aviation Organization.
STATIC AIR TEMPERATURE – SAT
Outside air temperature as indicated on the MFD.
TRUE OUTSIDE AIR TEMPERATURE
The free air static (ambient) temperature.
WIND VELOCITY
The actual wind velocity at a height of 10 m (32.8 ft), reported from the
tower and corrected by the wind component chart to a headwind or
tailwind component parallel to the flight path.
CONTAMINATED RUNWAY
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 the following:
– surface water more than 3 mm (0.125 in) deep, or by slush, or loose
snow, equivalent to more than 3 mm (0.125 in) of water;
– snow which has been compressed into a solid mass which resists
further compression and will hold together or break into lumps if
picked up (compacted snow); or
AOM-1502-016
– ice, including wet ice.
5-01
Copyright © by Embraer. Refer to cover page for details.
REVISION 18
Configuration and Definitions
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-01
Copyright © by Embraer. Refer to cover page for details.
Page 4
Configuration and Definitions
REVISION 18
AOM-1502-016
INTENTIONALLY BLANK
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
DEMONSTRATED CROSSWIND
The maximum demonstrated crosswind component for landing is 28 kt.
This maximum demonstrated value is not considered to be limiting.
WIND AND ALTITUDE CONVERSION
WIND COMPONENT
80
WIND DIRECTION RELATIVE
TO RUNWAY
(STRAIGHT LINES)
60
0°
50
10°
20°
30°
40°
40
50°
30
60°
20
70°
10
EFFECTIVE TAILWIND
COMPONENT − kt
0
80°
90°
0
10
20
30
40
50
100°
−10
CROSSWIND
COMPONENT − kt
110°
−20
120°
−30
130°
140°
−40
150°
−50
180°
170°
REPORTED WIND
SPEED
(CURVED LINES)
160°
EM170AOM050004A.DGN
EFFECTIVE HEADWIND
COMPONENT − kt
70
−60
−70
−80
AOM-1502-016
WIND COMPONENT
CONTINUED...
5-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Data Conversion
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
USE
Enter the chart with the reported wind velocity and the relative angle to
the runway, to read the wind component parallel to the runway and the
crosswind.
EXAMPLE
Given:
Wind velocity............................................................. 20 kt
Wind direction............................................................ 60°
5-10
Copyright © by Embraer. Refer to cover page for details.
Page 2
Data Conversion
REVISION 21
AOM-1502-016
Determine:
Wind component parallel to the runway................... 10 kt
Crosswind.................................................................. 17.5 kt
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
ALTIMETER SETTING TO STATION PRESSURE
QNH TO PRESSURE ALTITUDE
QNH
inHg
28.81
28.92
29.03
29.13
29.24
29.35
29.45
29.56
29.67
29.77
29.88
29.98
30.09
30.20
30.31
30.42
30.53
30.64
30.75
30.86
30.97
AOM-1502-016
Example:
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
to
28.91
29.02
29.12
29.23
29.34
29.44
29.55
29.66
29.76
29.87
29.97
30.08
30.19
30.30
30.41
30.52
30.63
30.74
30.85
30.96
31.07
hPa
976 to 979
980 to 983
984 to 986
987 to 990
991 to 994
995 to 997
998 to 1001
1002 to 1004
1005 to 1008
1009 to 1012
1013 to 1015
1016 to 1019
1020 to 1022
1023 to 1026
1027 to 1030
1031 to 1034
1035 to 1037
1038 to 1041
1042 to 1045
1046 to 1048
1049 to 1052
CORRECTION TO
ELEVATION FOR
PRES. ALT. (ft)
1000
900
800
700
600
500
400
300
200
100
0
-100
-200
-300
-400
-500
-600
-700
-800
-900
-1000
Elevation = 2000 ft
QNH = 29.60 in.Hg
Correction = 300 ft
Pressure Altitude = 2300 ft
CONTINUED...
5-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Data Conversion
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
QFE TO STATION PRESSURE
QFE
PRESSURE
PRESSURE
inHg
hPa
ALTITUDE (ft)
inHg
hPa
ALTITUDE (ft)
31.01
1050
-989
25.55
865
4313
30.86
1045
-856
25.40
860
4468
30.71
1040
-723
25.25
855
4625
30.57
1035
-589
25.10
850
4781
30.42
1030
-454
24.96
845
4939
30.27
1025
-319
24.81
840
5097
30.12
1020
-184
24.66
835
5257
29.98
1015
-48
24.51
830
5417
29.83
1010
89
24.36
825
5579
29.68
1005
227
24.21
820
5740
29.53
1000
364
24.07
815
5903
29.38
995
503
23.92
810
6065
29.23
990
641
23.77
805
6230
29.09
985
781
23.62
800
6394
6561
28.94
980
921
23.48
795
28.79
975
1062
23.33
790
6727
28.64
970
1202
23.18
785
6895
28.50
965
1344
23.03
780
7063
28.35
960
1486
22.89
775
7233
28.20
955
1630
22.74
770
7402
28.05
950
1773
22.59
765
7574
27.91
945
1918
22.44
760
7745
27.76
940
2062
22.30
755
7920
27.61
935
2208
22.15
750
8095
27.46
930
2353
22.00
745
8269
27.32
925
2500
21.85
740
8442
27.17
920
2647
21.71
735
8619
27.02
915
2796
21.56
730
8796
26.87
910
2944
21.41
725
8975
26.73
905
3094
21.26
720
9154
26.58
900
3243
21.12
715
9335
26.43
895
3394
20.97
710
9516
CONTINUED...
5-10
Copyright © by Embraer. Refer to cover page for details.
Page 4
Data Conversion
REVISION 21
AOM-1502-016
QFE
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
AOM-1502-016
QFE
QFE
PRESSURE
PRESSURE
inHg
hPa
ALTITUDE (ft)
26.28
890
3545
20.82
705
9699
26.14
885
3698
20.67
700
9882
25.99
880
3850
20.53
695
10068
25.84
875
4004
20.38
690
10253
25.69
870
4157
20.19
685
10439
inHg
hPa
ALTITUDE (ft)
5-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Data Conversion
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
GEOMETRIC HEIGHT TO PRESSURE HEIGHT
Pressure altimeters are calibrated to indicate true altitude under
International Standard Atmosphere (ISA) conditions. Any deviation from
ISA will therefore result in an erroneous reading on the altimeter. When
the temperature is higher than ISA, the true altitude will be higher than
the figure indicated by the altimeter. When the temperature is lower than
ISA, the true altitude will be lower than the figure indicated by the
altimeter. The altimeter error may be significant under conditions of
extremely cold temperature (ICAO PANS-OPS Vol I 3.1.4.5.2).
AERODROME
TEMP.
(°C)
0
-10
-20
-30
-40
-50
AERODROME
TEMP.
(°C)
0
-10
-20
-30
-40
-50
HEIGHT ABOVE THE ELEVATION OF THE
ALTIMETER SETTING SOURCE
(ft)
200
300 400
500
600 700 800
20
20
30
30
40
40
50
20
30
40
50
60
70
80
30
50
60
70
90
100 120
40
60
80
100
120 140 150
50
80
100
120
150 170 190
60
90
120
150
180 210 240
HEIGHT ABOVE THE ELEVATION OF THE
ALTIMETER SETTING SOURCE
(ft)
900 1000 1500 2000 3000 4000 5000
50
60
90
120
170
230
280
90
100
150
200
290
390
490
130
140
210
280
420
570
710
170
190
280
380
570
760
950
220
240
360
480
720
970 1210
270
300
450
590
890 1190 1500
The tables above are based on an aerodrome at sea level. However,
they can be used operationally at any aerodrome elevation.
Airport Elevation........................................................ 1500 ft
Airport Temperature................................................... -20°C
CONTINUED...
5-10
Copyright © by Embraer. Refer to cover page for details.
Page 6
Data Conversion
REVISION 21
AOM-1502-016
Example:
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
...CONTINUED
Obstacle Height above airport elevation................... 800 ft
Altimeter adjusted to airport QNH (on ground altimeter reads 1500 ft).
Refer to table at 800 ft and -20°C and read 120 ft.
Therefore, when the airplane reaches the obstacle geometric height, the
altimeter will read 1500 + 800 + 120 = 2420 ft.
EM170AOM050005C.DGN
ALTIMETERS READ
2420 ft
AOM-1502-016
ELEVATION=1500 ft
T=−20°C
ALTIMETERS READ 1500 ft
5-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Data Conversion
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-10
Copyright © by Embraer. Refer to cover page for details.
Page 8
Data Conversion
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
THRUST SETTING TABLES
Thrust settings tables are presented for various pressure altitudes and
static air temperatures, with engine bleed closed or open, and anti-ice
on or off.
AOM-1502-016
The following tables present Takeoff N1 regarding T/O-1 and T/O-2
mode and Go-around N1 for CF34-10E6 engines.
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-1
ECS ON — ANTI-ICE OFF
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-40
78.4
-35
79.2
-30
80.0
-25
80.8
-20
81.6
-15
82.3
-10
83.1
-5
83.9
0
84.6
5
85.4
0
1000
2000
3000
4000
5000
6000
7000
79.3
79.8
80.2
80.7
81.2
81.7
82.0
82.5
80.2
80.6
81.1
81.6
82.1
82.6
82.9
83.3
81.0
81.4
81.9
82.4
82.9
83.3
83.7
84.1
81.8
82.2
82.7
83.2
83.7
84.1
84.5
84.9
82.6
83.0
83.5
84.0
84.5
84.9
85.3
85.7
83.4
83.8
84.3
84.8
85.3
85.7
86.1
86.5
84.1
84.6
85.1
85.6
86.0
86.5
86.9
87.3
84.9
85.4
85.8
86.3
86.8
87.3
87.6
88.1
85.7
86.1
86.6
87.1
87.6
88.1
88.4
88.8
86.4
86.9
87.4
87.9
88.3
88.8
89.2
89.6
8000
9000
10000
82.9
83.3
83.8
83.7
84.2
84.7
84.6
85.0
85.5
85.3
85.8
86.3
86.1
86.5
87.0
86.9
87.3
87.8
87.7
88.1
88.6
88.5
88.9
89.4
89.3
89.7
90.2
90.0
90.5
91.0
Pressure
Altitude
(ft)
-1000
0
1000
2000
3000
10
86.1
87.2
87.6
88.1
88.6
15
86.8
87.9
88.4
88.9
89.4
20
87.6
88.7
89.1
89.6
90.1
25
88.3
89.4
89.9
90.4
90.9
30
89.0
90.1
90.6
91.1
91.3
35
89.8
90.9
90.7
90.7
90.7
40
89.5
90.0
90.0
90.1
90.1
45
88.8
89.4
89.4
89.5
89.4
50
88.2
88.8
88.7
88.6
88.6
4000
5000
6000
89.1
89.6
90.0
89.8
90.3
90.7
90.6
91.1
91.5
91.3
91.8
91.7
91.3
91.3
91.1
90.7
90.7
90.6
90.1
90.2
89.9
89.4
89.3
89.1
88.6
88.7
88.6
7000
8000
90.4
90.8
91.1
91.6
91.9
92.1
91.5
91.3
91.0
90.8
90.4
90.2
89.6
89.4
89.0
88.8
88.4
---
9000
10000
91.2
91.7
92.0
92.5
91.8
91.6
91.2
91.1
90.6
90.5
89.9
89.7
89.2
89.1
88.7
88.6
-----
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 2
Thrust Setting
REVISION 23
AOM-1502-016
Static Air Temperature — °C
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-1
ECS ON — WING AND ENGINE ANTI-ICE ON
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
AOM-1502-016
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-35
79.2
-30
80.0
-25
80.8
-20
81.6
-15
82.3
-10
83.1
-5
83.9
0
84.6
5
85.4
10
86.1
0
1000
2000
3000
4000
5000
6000
7000
80.2
80.6
81.1
81.6
82.0
82.6
82.9
83.3
81.0
81.4
81.9
82.4
82.9
83.3
83.7
84.1
81.8
82.3
82.7
83.2
83.7
84.1
84.5
84.9
82.6
83.0
83.5
84.0
84.5
84.9
85.3
85.7
83.4
83.8
84.3
84.8
85.2
85.7
86.1
86.5
84.1
84.6
85.1
85.5
86.0
86.5
86.9
87.3
84.9
85.4
85.8
86.3
86.8
87.3
87.6
88.1
85.7
86.1
86.6
87.1
87.6
88.1
88.4
88.8
86.4
86.9
87.4
87.8
88.3
88.8
89.2
89.6
87.2
87.7
88.1
88.6
89.1
89.6
90.0
90.4
8000
9000
10000
83.7
84.1
84.7
84.6
85.0
85.5
85.3
85.8
86.3
86.1
86.6
87.0
86.9
87.4
87.8
87.7
88.1
88.6
88.5
88.9
89.4
89.3
89.7
90.2
90.0
90.5
91.0
90.8
90.8
90.6
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-1
ECS OFF — ANTI-ICE OFF
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-40
79.0
-35
79.9
-30
80.7
-25
81.5
-20
82.3
-15
83.0
-10
83.8
-5
84.6
0
85.4
5
86.1
0
1000
2000
3000
4000
5000
6000
7000
80.0
80.5
81.0
81.5
82.0
82.5
83.0
83.4
80.9
81.4
81.8
82.3
82.9
83.4
83.8
84.3
81.7
82.2
82.7
83.2
83.7
84.2
84.6
85.1
82.5
83.0
83.5
84.0
84.5
85.0
85.4
85.9
83.3
83.8
84.3
84.8
85.3
85.8
86.2
86.7
84.1
84.6
85.1
85.6
86.1
86.6
87.1
87.5
84.9
85.4
85.9
86.4
86.9
87.4
87.9
88.4
85.7
86.2
86.7
87.2
87.7
88.3
88.7
89.1
86.5
86.9
87.5
88.0
88.5
89.0
89.4
89.9
87.2
87.7
88.2
88.7
89.3
89.8
90.2
90.7
8000
9000
10000
83.9
84.3
84.9
84.7
85.2
85.8
85.6
86.0
86.6
86.4
86.8
87.4
87.2
87.6
88.2
88.0
88.4
89.0
88.8
89.3
89.8
89.6
90.1
90.6
90.4
90.9
91.4
91.2
91.7
92.2
Pressure
Altitude
(ft)
-1000
0
1000
2000
3000
10
86.9
88.0
88.5
89.0
89.5
15
87.6
88.7
89.2
89.7
90.3
20
88.4
89.5
90.0
90.5
91.0
25
89.1
90.2
90.7
91.3
91.8
30
89.9
91.0
91.5
92.0
92.3
35
90.6
91.8
91.7
91.7
91.7
40
90.4
90.9
90.9
91.0
91.1
45
89.6
90.3
90.4
90.4
90.5
50
89.1
89.7
89.7
89.6
89.7
4000
5000
6000
90.0
90.6
91.0
90.8
91.3
91.8
91.6
92.1
92.5
92.3
92.8
92.8
92.3
92.3
92.2
91.7
91.8
91.7
91.2
91.2
91.0
90.4
90.4
90.3
89.7
89.8
89.7
7000
8000
91.5
92.0
92.3
92.7
93.0
93.3
92.7
92.5
92.1
92.0
91.6
91.4
90.8
90.6
90.2
90.1
89.6
---
9000
10000
92.4
93.0
93.2
93.8
93.1
92.9
92.4
92.3
91.9
91.8
91.2
91.0
90.5
90.5
90.0
89.9
-----
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 4
Thrust Setting
REVISION 23
AOM-1502-016
Static Air Temperature — °C
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-1
ECS OFF — WING AND ENGINE ANTI-ICE ON
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
AOM-1502-016
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-35
79.8
-30
80.7
-25
81.5
-20
82.3
-15
83.1
-10
83.8
-5
84.6
0
85.4
5
86.2
10
86.9
0
1000
2000
3000
4000
5000
6000
7000
80.9
81.4
81.8
82.3
82.8
83.4
83.8
84.3
81.7
82.2
82.7
83.2
83.7
84.2
84.6
85.1
82.5
83.0
83.5
84.0
84.5
85.0
85.4
85.9
83.3
83.8
84.3
84.8
85.3
85.8
86.2
86.7
84.1
84.6
85.1
85.6
86.1
86.6
87.1
87.5
84.9
85.4
85.9
86.4
86.9
87.4
87.9
88.4
85.7
86.2
86.7
87.2
87.7
88.3
88.7
89.1
86.5
86.9
87.5
88.0
88.5
89.0
89.5
89.9
87.2
87.7
88.2
88.8
89.3
89.8
90.2
90.7
88.0
88.5
89.0
89.5
90.0
90.6
91.0
91.5
8000
9000
10000
84.7
85.2
85.8
85.6
86.0
86.6
86.4
86.9
87.4
87.2
87.7
88.2
88.0
88.5
89.0
88.8
89.3
89.8
89.6
90.1
90.6
90.4
90.9
91.4
91.2
91.7
92.2
92.0
91.9
91.8
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-2
ECS ON — ANTI-ICE OFF
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-40
75.5
-35
76.3
-30
77.1
-25
77.8
-20
78.6
-15
79.3
-10
80.1
-5
80.8
0
81.5
5
82.2
0
1000
2000
3000
4000
5000
6000
7000
76.4
76.8
77.3
77.7
78.1
78.5
78.9
79.3
77.2
77.7
78.1
78.5
78.9
79.3
79.7
80.1
78.0
78.5
78.9
79.3
79.7
80.1
80.5
80.9
78.8
79.2
79.7
80.1
80.5
80.9
81.3
81.7
79.6
80.0
80.4
80.8
81.3
81.7
82.1
82.5
80.3
80.7
81.2
81.6
82.0
82.4
82.9
83.3
81.1
81.5
81.9
82.4
82.8
83.2
83.6
84.0
81.8
82.3
82.7
83.1
83.6
84.0
84.4
84.8
82.6
83.0
83.5
83.9
84.3
84.7
85.1
85.6
83.3
83.7
84.2
84.6
85.0
85.5
85.9
86.3
8000
9000
10000
79.7
80.1
80.5
80.5
80.9
81.3
81.3
81.7
82.1
82.1
82.5
82.9
82.9
83.2
83.6
83.6
84.0
84.4
84.4
84.8
85.2
85.2
85.6
86.0
86.0
86.4
86.8
86.7
87.1
87.5
Pressure
Altitude
(ft)
-1000
0
1000
2000
3000
10
82.9
84.0
84.5
84.9
85.3
15
83.6
84.7
85.2
85.6
86.1
20
84.3
85.4
85.9
86.3
86.8
25
85.1
86.1
86.6
87.1
87.2
30
85.8
86.8
86.8
86.7
86.6
35
85.6
86.2
86.1
86.0
86.0
40
84.9
85.5
85.5
85.4
85.3
45
84.3
84.8
84.8
84.7
84.6
50
83.7
84.3
84.1
83.9
83.8
4000
5000
6000
85.8
86.2
86.7
86.5
86.9
87.4
87.2
87.7
87.6
87.2
87.1
87.0
86.5
86.4
86.4
85.9
85.8
85.8
85.3
85.2
85.0
84.5
84.3
84.3
83.8
83.8
84.2
7000
8000
87.1
87.5
87.8
88.0
87.5
87.4
86.9
86.8
86.3
86.2
85.7
85.6
84.8
84.8
84.3
84.5
84.7
---
9000
10000
87.9
88.3
87.9
87.7
87.3
87.2
86.7
86.6
86.1
86.1
85.4
85.2
84.8
84.9
85.0
85.5
-----
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 6
Thrust Setting
REVISION 23
AOM-1502-016
Static Air Temperature — °C
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-2
ECS ON — WING AND ENGINE ANTI-ICE ON
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
AOM-1502-016
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-35
76.3
-30
77.0
-25
77.8
-20
78.6
-15
79.3
-10
80.0
-5
80.8
0
81.5
5
82.3
10
83.0
0
1000
2000
3000
4000
5000
6000
7000
77.3
77.7
78.1
78.5
78.9
79.3
79.7
80.1
78.0
78.5
78.9
79.3
79.7
80.1
80.5
80.9
78.8
79.2
79.7
80.1
80.5
80.9
81.3
81.7
79.6
80.0
80.4
80.9
81.3
81.7
82.1
82.5
80.3
80.7
81.2
81.6
82.0
82.4
82.9
83.3
81.1
81.5
81.9
82.4
82.8
83.2
83.6
84.0
81.8
82.3
82.7
83.1
83.5
84.0
84.4
84.8
82.6
83.0
83.5
83.8
84.3
84.7
85.1
85.6
83.3
83.7
84.2
84.6
85.0
85.5
85.9
86.3
84.0
84.5
84.9
85.3
85.8
86.2
86.6
86.5
8000
9000
10000
80.5
80.9
81.3
81.3
81.7
82.1
82.1
82.5
82.9
82.9
83.3
83.6
83.6
84.1
84.4
84.4
84.8
85.2
85.2
85.6
86.0
86.0
86.4
86.8
86.7
86.8
86.7
86.4
86.3
86.1
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-2
ECS OFF — ANTI-ICE OFF
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-40
76.1
-35
76.9
-30
77.7
-25
78.5
-20
79.2
-15
80.0
-10
80.8
-5
81.5
0
82.3
5
83.0
0
1000
2000
3000
4000
5000
6000
7000
77.1
77.5
78.0
78.4
78.9
79.3
79.8
80.2
77.9
78.4
78.8
79.3
79.7
80.2
80.6
81.0
78.7
79.2
79.6
80.1
80.5
81.0
81.4
81.8
79.5
80.0
80.4
80.9
81.3
81.7
82.2
82.6
80.3
80.7
81.2
81.6
82.1
82.5
83.0
83.4
81.0
81.5
82.0
82.4
82.9
83.3
83.8
84.2
81.8
82.3
82.7
83.2
83.7
84.1
84.6
85.0
82.6
83.0
83.5
84.0
84.5
84.9
85.4
85.8
83.3
83.8
84.3
84.8
85.2
85.7
86.1
86.6
84.0
84.6
85.0
85.5
86.0
86.4
86.9
87.3
8000
9000
10000
80.6
81.0
81.5
81.4
81.9
82.3
82.3
82.7
83.2
83.1
83.5
84.0
83.9
84.3
84.8
84.7
85.1
85.6
85.4
85.9
86.4
86.2
86.7
87.2
87.0
87.5
88.0
87.8
88.3
88.7
Pressure
Altitude
(ft)
-1000
0
1000
2000
3000
10
83.7
84.8
85.3
85.8
86.2
15
84.4
85.5
86.0
86.5
87.0
20
85.1
86.2
86.7
87.2
87.7
25
85.9
87.0
87.5
88.0
88.2
30
86.6
87.7
87.7
87.6
87.6
35
86.5
87.0
87.0
87.0
87.0
40
85.8
86.4
86.4
86.4
86.3
45
85.1
85.7
85.8
85.7
85.7
50
84.6
85.2
85.1
84.9
84.9
4000
5000
6000
86.7
87.2
87.6
87.4
87.9
88.4
88.2
88.7
88.6
88.1
88.1
88.1
87.5
87.5
87.5
86.9
86.9
86.9
86.3
86.3
86.2
85.6
85.4
85.4
84.9
84.9
84.9
7000
8000
88.1
88.6
88.9
89.1
88.6
88.5
88.0
88.0
87.4
87.4
86.9
86.8
86.0
86.0
85.4
85.4
84.9
---
9000
10000
89.0
89.5
89.1
89.0
88.5
88.5
88.0
87.9
87.4
87.4
86.7
86.5
86.0
86.0
85.5
85.5
-----
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 8
Thrust Setting
REVISION 23
AOM-1502-016
Static Air Temperature — °C
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR T/O-2
ECS OFF — WING AND ENGINE ANTI-ICE ON
AIRSPEED: 0 KCAS
CF34-10E6 ENGINE
AOM-1502-016
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-35
76.9
-30
77.7
-25
78.5
-20
79.3
-15
80.0
-10
80.8
-5
81.5
0
82.3
5
83.0
10
83.7
0
1000
2000
3000
4000
5000
6000
7000
77.9
78.4
78.8
79.3
79.7
80.2
80.6
81.0
78.7
79.2
79.6
80.1
80.5
81.0
81.4
81.8
79.5
80.0
80.4
80.9
81.3
81.7
82.2
82.6
80.3
80.7
81.2
81.6
82.1
82.5
83.0
83.4
81.0
81.5
82.0
82.4
82.9
83.3
83.8
84.2
81.8
82.3
82.7
83.2
83.6
84.1
84.6
85.0
82.6
83.0
83.5
84.0
84.4
84.9
85.4
85.8
83.3
83.8
84.3
84.8
85.2
85.7
86.1
86.6
84.1
84.6
85.0
85.5
85.9
86.4
86.9
87.4
84.8
85.3
85.8
86.2
86.7
87.2
87.5
87.5
8000
9000
10000
81.4
81.9
82.3
82.3
82.7
83.2
83.1
83.5
84.0
83.9
84.3
84.8
84.7
85.1
85.6
85.4
85.9
86.4
86.2
86.7
87.2
87.0
87.5
88.0
87.8
87.9
87.9
87.4
87.4
87.4
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 9
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR GO-AROUND
ECS OFF — ANTI-ICE OFF
CF34-10E6 ENGINE
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-40
81.3
-35
82.2
-30
83.0
-25
83.8
-20
84.6
-15
85.4
-10
86.2
-5
87.0
0
87.8
5
88.5
0
1000
2000
3000
4000
5000
6000
7000
82.3
82.9
83.5
84.1
84.7
85.4
85.9
86.3
83.1
83.7
84.3
85.0
85.6
86.3
86.7
87.2
83.9
84.6
85.2
85.8
86.4
87.1
87.5
88.0
84.8
85.4
86.0
86.6
87.3
87.9
88.4
88.8
85.6
86.2
86.8
87.4
88.1
88.7
89.2
89.6
86.4
87.0
87.6
88.3
88.9
89.5
90.0
90.4
87.2
87.8
88.4
89.1
89.7
90.3
90.8
91.2
88.0
88.6
89.2
89.9
90.5
91.2
91.6
92.0
88.8
89.4
90.0
90.7
91.3
91.9
92.4
92.8
89.5
90.2
90.8
91.4
92.1
92.7
93.2
93.6
8000
9000
10000
86.8
87.3
86.3
87.7
88.1
87.1
88.5
89.0
87.9
89.3
89.8
88.7
90.1
90.6
89.4
90.9
91.4
90.2
91.7
92.2
91.0
92.5
93.0
91.8
93.3
93.8
92.5
94.1
94.5
93.2
Pressure
Altitude
(ft)
-1000
0
1000
2000
3000
4000
10
89.3
90.3
90.9
91.6
92.2
92.8
15
90.1
91.1
91.7
92.3
93.0
93.6
20
90.8
91.8
92.5
93.1
93.7
94.4
25
91.6
92.6
93.2
93.9
94.5
95.2
30
92.3
93.4
94.0
94.6
95.0
95.1
35
93.1
94.1
94.3
94.4
94.4
94.4
40
93.2
93.8
93.8
93.8
93.8
93.8
45
92.7
93.2
93.3
93.2
-----
50
92.1
92.6
---------
5000
6000
7000
93.5
94.0
94.4
94.3
94.7
95.2
95.0
95.5
95.9
95.8
95.7
95.6
95.1
95.0
95.0
94.4
94.4
94.3
93.9
-----
-------
-------
8000
9000
94.9
95.3
95.6
96.1
96.2
96.1
95.6
95.5
94.9
94.8
-----
-----
-----
-----
10000
94.0
94.7
94.2
93.5
92.8
---
---
---
---
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 10
Thrust Setting
REVISION 23
AOM-1502-016
Static Air Temperature — °C
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 FOR GO-AROUND
ECS OFF — WING AND ENGINE ANTI-ICE ON
CF34-10E6 ENGINE
AOM-1502-016
Pressure
Altitude
Static Air Temperature — °C
(ft)
-1000
-35
85.3
-30
86.2
-25
87.0
-20
87.8
-15
88.6
-10
89.4
-5
90.2
0
91.0
5
91.8
10
92.5
0
1000
2000
3000
4000
5000
6000
7000
86.6
87.2
87.7
88.4
89.0
89.1
89.1
89.1
87.4
88.0
88.6
89.2
89.8
89.9
89.9
89.9
88.2
88.8
89.4
90.0
90.6
90.7
90.7
90.7
89.0
89.6
90.2
90.8
91.4
91.5
91.5
91.5
89.9
90.4
91.0
91.6
92.2
92.3
92.3
92.3
90.7
91.2
91.8
92.4
93.0
93.1
93.1
93.0
91.5
92.0
92.6
93.2
93.8
93.9
93.9
93.8
92.3
92.8
93.4
94.0
94.6
94.6
94.6
94.6
93.0
93.6
94.1
94.8
95.4
95.4
95.4
95.3
93.8
94.4
94.9
95.5
95.7
95.4
95.4
95.3
8000
9000
10000
89.0
89.0
87.1
89.9
89.8
87.9
90.7
90.6
88.7
91.5
91.4
89.4
92.3
92.2
90.2
93.0
93.0
91.0
93.8
93.8
91.8
94.6
94.6
92.5
95.4
95.3
92.5
95.1
95.1
91.9
5-15
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Thrust Setting
Page 11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-15
Copyright © by Embraer. Refer to cover page for details.
Page 12
Thrust Setting
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
TAKEOFF ANALYSIS DESCRIPTION AND USE
Using Embraer Runway Analysis Software, airlines can produce takeoff
analysis tables. Using these tables the crew is able to get the following
information for a certain ambient conditions and airplane configuration:
– Maximum takeoff weight and the performance limitation code;
– Takeoff speeds;
AOM-1502-016
– Takeoff N1.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
PART A
NOTE: FOR REFERENCE ONLY
EMBRAER XXX − TAKEOFF ANALYSIS
GTY/GOTA
GOTHAM CITY
30
CF34−YYY Engines
ZZZ Certification
Auto Brakes: On
Brakes: ABSC 90002340PR
ATTCS: On
Air Conditioning: Off
V2/Vs: Fixed 1.18
Reverse: No reverse thrust credit
Thrust: T/O−1
Elevation: 0 ft
Align Allow TODA: 0,0 m
Length: 2890 m
Clearway: 0 m
Stopway: 0 m
Slop: 0,00 %
Align Allow ASDA: 0 m
Flaps: 1
App Flaps: 2
Anti Ice: OFF
MTOW User Defined: 48000 kg
Rwy Condition: DRY
2°seg. obst. clearance preferred
Stop Margin: No Stop Margin
V1/Vr: Optimum V1
CG: Standard
Gross Level Off Altitude: 400ft
Gross Level Off Height: 400ft
Obstacle Data (measured from ETORA)
Obst.#:
1
Height(ft): 400
Dist.(ft):
4000
Remarks:
Output Description(Weights in kg, Speeds in KIAS):
MTOW−LIM
V1/Vr/V2
Wind (Kt)
Temp (°C)
N1
−10
0
10
20
0
82.6
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
6
83.4
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
12
84.3
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
18
85.1
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
24
86.0
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
30
86.8
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
42000−S
92/135/137
36
86.0
42000−S
93/136/137
#42000−S
#89/136/137
#42000−S
#89/136/137
#42000−S
#89/136/137
42
85.2
42000−S
112/136/137
42000−S
97/136/137
#42000−S
#90/136/137
#42000−S
#87/136/137
48
84.5
41294−W
119/136/136
41294−W
109/136/136
41294−W
104/136/136
41294−W
99/136/136
A54
83.6
38946−W
113/132/132
38946−W
102/132/132
38946−W
96/132/132
#38946−W
#89/132/132
A60
82.9
37239−W
109/129/129
37239−W
97/129/129
37239−W
91/129/129
#37239−W
#84/129/129
84.5
PART B
41294−W 99/136/136
Codes
Field Length AEO (RA)
Field Length OEI (RO)
Approach Climb OEI (A)
Climb Accel Segment (AS)
Climb 1° Seg. (FS)
Climb 2° Seg. (W)
Brake Energy (B)
MTOW Max str TOW [S]
Obstade # (1,2,3)
A − Temperatures for assumed temperature only
# − Minimum V1 check must be done
RW−000−A Version 0.0.0 Date: (day−month−year): 00−00−0000
SCAP Module Version: 000−00000−000
Tire Speed (P)
Climb Final Seg. (SF)
No operation *******
Database: 000−00000−000.DAT
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 2
Takeoff
REVISION 23
AOM-1502-016
48
EM170AOM050066A.DGN
Air conditioning off after engine failure.
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
DESCRIPTION OF THE OUTPUTS OF THE CHART
Part A: Head Lines with the following information:
– Airplane Configuration (engine, thrust, flap, brakes, etc);
– Runway Characteristics (elevation, length, obstacles, clearway,
stopway, slope, etc).
Part B: Performance Information:
– OAT: Outside Air Temperature (if a letter A follow the temperature it
means that the weight can be used only for assumed temperature
calculation);
– Takeoff N1;
– Maximum Takeoff Weight;
– V1: Takeoff decision speed;
– VR: Rotation speed;
– V2: Safety speed;
AOM-1502-016
– Limitation code.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
ASSUMED TEMPERATURE REDUCED THRUST
In many situations, the airplane takes off at weights lower than the
maximum permissible takeoff weight. In consequence, it is possible to
continue complying with performance limitations using a decreased
engine thrust adapted to the actual weight. This is called assumed
temperature reduced thrust method.
Certification authorities permit the use of up to 25% of takeoff thrust
reduction for operation with assumed temperature reduced thrust.
UTILIZATION OF ASSUMED TEMPERATURE REDUCED
THRUST
Assumed temperature reduced thrust method can only be used when
the actual weight is lower than the maximum permissible takeoff weight
for the actual temperature.
AIRWORTHINESS REQUIREMENTS
•
Maximum Assumed Temperature (MaxAT) (25% reduction). See
Maximum Assumed Temperature Table.
•
Assumed temperature reduced thrust is not allowed when runway is
contaminated with water, ice, slush or snow.
•
The operator shall at regular intervals check the maximum thrust in
order to detect any possible engine deterioration, unless the operators
has an adequate engine performance monitoring program.
RECOMMENDATION
Assumed temperature reduced thrust should be used whenever possible
in order to save engine life.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 4
Takeoff
REVISION 23
AOM-1502-016
Always use the flaps configuration, that provides the greatest maximum
takeoff weight in order to maximize thrust reduction.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLEXIBLE TEMPERATURE DETERMINATION
Verify if actual weight is lower than or equal to the maximum
takeoff weight in takeoff analysis for correspondent OAT
and wind.
E n t er w i th actu al w ei gh t an d act u al w i n d o n tak eo f f
an al y si s an d f i n d th e co r r esp o n d en t tem p er atu r e ( T ) .
Enter with pressure altitude and tem perature in Maximum
Assum ed Tem perature table and find Maxim um Assum ed
Tem perature (MaxAT).
Com pare T and MaxAT and choose the lower value as
Assum ed Tem perature value (AT).
If AT is higher than
MinAT: Take this
tem perature (AT) as
Assum ed
Tem perature.
AOM-1502-016
If AT is lower than
MinAT: No Flexible
takeoff is possible,
use m axim um thrust.
EM170AOM050009D.DGN
E n ter w i th p r essu r e al ti tu d e i n M i n i m u m A ssu m ed
Temp er a ture table and find Minimum Assumed Temp er a ture
(MinAT ) .
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1 % FOR FLEXIBLE TAKEOFF
Enter with AT and pressure altitude in N1 for T/O−X m ode
and find out N1 reference (N1ref).
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 6
Takeoff
REVISION 23
AOM-1502-016
Reduced N1% is:
N1red = N1ref − N1corr.
EM170AOM050010A.DGN
Enter with the difference between AT and OAT in N1
adjustm ent for tem perature difference table and find out
N1corr.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
TAKEOFF SPEEDS
Using Runway Analysis, enter with the Actual Takeoff
Weight in the reported wind column to find out V1, VR, V2.
(Step 1).
Using Minimum V1 and VR tables find out V1min
and VRmin.
If V1 and VR are
higher than V1min
and VRmin, use
takeoff speeds found
out in Step 1.
If V1 and VR are
lower than V1min and
VRmin.
AOM-1502-016
Determine again
N1% and use this
V1, VR and V2 of
previous step as a
takeoff speeds.
EM170AOM050011D.DGN
Use Runway analysis
and find out in what
Temperature V1 and
VR are equal or
higher than V1min
and VRmin.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 8
Takeoff
REVISION 23
AOM-1502-016
FLEXIBLE TEMPERATURE DETERMINATION
TABLES
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MAXIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-1
ECS ON — ANTI-ICE OFF
PRESSURE ALTITUDE (x 1000 ft)
OAT
(°C) -1
0
1
2
3
4
5
6
7
8
52
66 --- --- --- --- --- --- --- --- --50
66 64 --- --- --- --- --- --- --- --45
64 64 62 61 --- --- --- --- --- --40
59 59 59 59 59 57 55 --- --- --35
56 54 54 54 54 54 54 53 51 --30
54 54 52 50 49 49 49 49 49 48
25
51 50 50 49 48 47 45 45 45 44
20
51 49 48 46 45 45 44 44 42 41
15
51 49 47 46 44 42 40 39 39 38
10
51 49 47 45 44 42 40 38 35 33
5
50 49 47 45 44 42 40 37 35 32
0
and 50 49 47 45 43 42 40 37 35 32
below
RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED
TEMPERATURE
MINIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-1
AOM-1502-016
-1
MinAt 37
0
35
9
----------47
44
41
37
32
30
10
----------45
44
40
37
32
27
29
27
ANTI-ICE OFF
PRESSURE ALTITUDE (x 1000 ft)
1
2
3
4
5
6
7
8
33 31 29 27 25 23 21 19
9
17
10
15
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 9
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE
Engine: CF34-10E6 — T/O-1
ANTI-ICE OFF
AT
MINUS
OAT
(°C)
-40
-20
0
5
10
15
20
25
30
35
40
45
50
52
5
10
20
-------
-------
----3.2
--1.6
3.1
0.8
1.6
3.1
0.8
1.6
3.0
0.8
1.5
2.9
0.8
1.5
2.9
0.7
1.5
2.8
0.7
1.4
2.7
0.7
1.4
2.7
0.7
1.4
2.6
0.7
1.3
---
0.7
1.3
---
30
40
50
60
70
------10.0
11.2
--6.5
7.9
9.1
10.2
4.6
6.0
7.2
8.3
---
4.5
5.8
7.0
8.1
---
4.4
5.7
6.8
-----
4.3
5.5
6.7
-----
4.2
5.4
-------
4.1
5.3
-------
4.0
---------
3.9
---------
-----------
-----------
-----------
-----------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 10
Takeoff
REVISION 23
AOM-1502-016
OUTSIDE AIR TEMPERATURE (OAT) – (°C)
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
MAXIMUM ASSUMED TEMPERATURE
ECS ON
WING & ENG ANTI-ICE ON
Engine: CF34-10E6 — T/O-1
PRESSURE ALTITUDE (x 1000 ft)
OAT
(°C) -1
0
1
2
3
4
5
6
7
8
10
48 46 44 42 41 39 38 36 35 33
5
48 46 44 42 41 39 38 36 34 32
0
48 46 44 42 41 39 38 36 34 32
-5
48 45 44 42 41 39 37 36 34 32
-10 47 45 44 42 40 39 37 36 34 31
-15 47 45 43 42 40 39 37 36 34 31
-20
and 47 45 43 42 40 39 37 36 34 31
below
RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED
TEMPERATURE
9
31
30
29
29
29
29
10
29
27
27
27
27
26
29
26
MINIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-1
WING & ENG ANTI-ICE ON
AOM-1502-016
-1
MinAt 28
0
26
PRESSURE ALTITUDE (x 1000 ft)
1
2
3
4
5
6
7
8
24 22 20 18 16 14 12 10
9
8
10
6
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE
Engine: CF34-10E6 — T/O-1
WING & ENG ANTI-ICE ON
AT
MINUS
OAT (°C)
5
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
---
---
---
---
---
---
---
10
20
30
-------
-------
-------
-------
----4.9
----4.8
--3.3
4.7
---
---
0.8
0.8
--3.2
4.6
1.6
3.1
4.5
1.6
3.1
4.4
1.6
3.0
4.3
40
50
60
70
--8.4
9.8
11.0
--8.2
9.5
10.7
6.7
8.1
9.3
10.4
6.5
7.9
9.1
10.2
6.4
7.7
8.9
---
6.2
7.5
8.6
---
6.1
7.3
-----
5.9
7.1
-----
5.8
-------
5.7
-------
---------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 12
Takeoff
REVISION 23
AOM-1502-016
OUTSIDE AIR TEMPERATURE (OAT) – (°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MAXIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-2
ECS ON — ANTI-ICE OFF
PRESSURE ALTITUDE (x 1000 ft)
OAT
(°C) -1
0
1
2
3
4
5
6
7
8
52
61 --- --- --- --- --- --- --- --- --50
59 59 --- --- --- --- --- --- --- --45
54 54 53 53 --- --- --- --- --- --40
49 49 49 49 48 48 48 --- --- --35
44 44 44 44 44 44 43 43 43 --30
39 39 39 39 39 39 39 39 38 38
25
35 34 34 34 34 34 34 33 33 33
20
35 34 31 29 28 28 28 28 28 28
15
35 33 31 29 27 25 23 23 22 22
10
35 33 31 29 27 25 23 20 18 17
5
34 33 31 29 27 25 23 20 18 16
0
and 34 33 31 29 26 24 22 20 18 15
below
RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED
TEMPERATURE
MINIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-2
AOM-1502-016
-1
MinAt 32
0
30
9
----------38
33
28
22
16
13
10
----------38
33
27
22
16
11
13
10
ANTI-ICE OFF
PRESSURE ALTITUDE (x 1000 ft)
1
2
3
4
5
6
7
8
28 26 24 22 20 18 16 14
9
12
10
10
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 13
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE
Engine: CF34-10E6 — T/O-2
ANTI-ICE OFF
AT
MINUS
OAT
(°C)
-40
-20
0
5
10
15
20
25
30
35
40
45
50
52
5
10
20
-------
-------
----3.0
--1.5
3.0
0.8
1.5
2.9
0.8
1.5
2.8
0.7
1.4
2.8
0.7
1.4
2.7
0.7
1.4
2.7
0.7
1.4
2.6
0.7
1.3
2.6
0.7
1.3
---
0.6
1.3
---
0.6
-----
30
40
50
60
70
------9.5
10.7
--6.2
7.5
8.6
9.7
4.4
5.6
6.8
7.9
---
4.3
5.6
6.7
-----
4.2
5.4
6.5
-----
4.1
5.3
-------
4.0
5.2
-------
4.0
---------
3.9
---------
-----------
-----------
-----------
-----------
-----------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 14
Takeoff
REVISION 23
AOM-1502-016
OUTSIDE AIR TEMPERATURE (OAT) – (°C)
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
MAXIMUM ASSUMED TEMPERATURE
ECS ON
WING & ENG ANTI-ICE ON
Engine: CF34-10E6 — T/O-2
PRESSURE ALTITUDE (x 1000 ft)
OAT
(°C) -1
0
1
2
3
4
5
6
7
8
10
34 32 30 28 27 25 23 21 18 17
5
33 31 30 28 26 24 23 20 18 16
0
33 31 30 28 26 24 22 20 18 16
-5
33 31 29 28 26 24 22 20 18 15
-10 33 31 29 27 26 24 22 20 17 15
-15 33 31 29 27 25 24 22 20 17 15
-20
and 33 31 29 27 25 23 22 19 17 15
below
RMK: FOR ECS OFF ADD 2°C ON MAXIMUM ASSUMED
TEMPERATURE
9
17
14
13
13
13
13
10
17
11
11
11
11
11
13
10
MINIMUM ASSUMED TEMPERATURE
Engine: CF34-10E6 — T/O-2
WING & ENG ANTI-ICE ON
AOM-1502-016
-1
MinAt 23
0
21
PRESSURE ALTITUDE (x 1000 ft)
1
2
3
4
5
6
7
8
19 17 15 13 11
9
7
5
9
3
10
1
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 15
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
N1% ADJUSTMENT FOR TEMPERATURE DIFFERENCE
Engine: CF34-10E6 — T/O-2
WING & ENG ANTI-ICE ON
AT
MINUS
OAT (°C)
5
-40
-35
-30
-25
-20
-15
-10
-5
0
5
10
---
---
---
---
---
---
10
20
30
-------
-------
-------
----4.8
----4.7
--3.2
4.6
---
---
0.8
0.8
0.8
--3.1
4.5
1.6
3.0
4.4
1.5
3.0
4.3
1.5
2.9
---
1.5
2.8
---
40
50
60
70
--8.0
9.3
10.4
6.5
7.8
9.0
---
6.3
7.6
8.8
---
6.2
7.5
-----
6.1
7.3
-----
5.9
-------
5.8
-------
---------
---------
---------
---------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 16
Takeoff
REVISION 23
AOM-1502-016
OUTSIDE AIR TEMPERATURE (OAT) – (°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: Sea Level and Below
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
105
104
103
102
101
100
100
99
99
98
15
105
104
103
102
101
100
100
99
98
98
20
104
103
102
102
101
100
100
99
98
98
25
104
103
102
102
101
100
99
99
98
98
30
104
103
102
101
101
100
99
99
98
98
35
104
103
102
101
101
100
99
99
98
97
40
102
101
100
99
99
98
97
97
96
96
45
100
99
98
97
96
96
95
95
94
94
50
97
97
96
95
94
94
93
93
92
92
AOM-1502-016
Altitude: 2000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
102
101
100
100
99
98
97
97
96
96
15
102
101
100
99
99
98
97
97
96
96
20
102
101
100
99
99
98
97
97
96
96
25
102
101
100
99
99
98
97
97
96
95
30
102
101
100
99
98
98
97
97
96
95
35
100
99
98
98
97
96
96
95
94
94
40
98
97
96
96
95
94
94
93
93
92
45
96
95
94
93
93
92
92
91
91
90
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 17
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: 4000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
100
99
98
97
97
96
95
95
94
94
15
100
99
98
97
96
96
95
95
94
93
20
99
99
98
97
96
96
95
94
94
93
25
99
98
98
97
96
96
95
94
94
93
30
98
97
97
96
95
95
94
93
93
92
35
96
95
95
94
93
93
92
91
91
90
40
94
93
93
92
91
91
90
90
89
89
Altitude: 6000 ft
60
66
72
78
84
90
96
102
108
114
10
97
96
95
95
94
93
93
92
92
91
15
97
96
95
95
94
93
93
92
92
91
20
97
96
95
94
94
93
93
92
91
91
25
96
95
94
94
93
92
92
91
91
90
30
94
93
93
92
91
91
90
90
89
89
35
92
92
91
90
90
89
88
88
87
87
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 18
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: 8000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
94
93
92
92
91
91
90
89
89
88
15
94
93
92
92
91
90
90
89
89
88
20
94
93
92
91
91
90
90
89
89
88
25
92
91
91
90
89
89
88
88
87
87
30
90
89
89
88
88
87
87
86
86
85
AOM-1502-016
Altitude: 10000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
91
90
90
89
88
88
87
87
86
86
15
91
90
90
89
88
88
87
87
86
86
20
90
89
88
88
87
86
86
85
85
85
25
88
87
87
86
85
85
84
84
83
83
30
86
86
85
84
84
83
83
82
82
82
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 19
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: Sea Level and Below
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
99
99
98
97
96
96
95
94
94
93
15
99
98
98
97
96
95
95
94
94
93
20
99
98
97
97
96
95
95
94
94
93
25
99
98
97
97
96
95
95
94
93
93
30
99
98
97
96
96
95
94
94
93
93
35
97
96
95
94
94
93
92
92
91
91
40
95
94
93
92
92
91
90
90
89
89
45
92
92
91
90
90
89
88
88
87
87
50
90
89
89
88
87
87
86
86
85
85
Altitude: 2000 ft
60
66
72
78
84
90
96
102
108
114
10
97
96
95
95
94
93
93
92
92
91
15
97
96
95
95
94
93
93
92
92
91
20
97
96
95
94
94
93
93
92
91
91
25
97
96
95
94
94
93
92
92
91
91
30
95
94
93
93
92
91
91
90
90
89
35
93
92
91
91
90
89
89
88
88
87
40
91
90
89
89
88
88
87
86
86
85
45
89
88
87
87
86
86
85
85
84
84
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 20
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: 4000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
95
94
93
92
92
91
91
90
89
89
15
95
94
93
92
92
91
90
90
89
89
20
94
94
93
92
92
91
90
90
89
89
25
93
92
92
91
90
90
89
89
88
88
30
91
90
90
89
88
88
87
87
86
86
35
89
88
88
87
87
86
85
85
84
84
40
87
86
86
85
85
84
84
83
83
82
AOM-1502-016
Altitude: 6000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
92
91
91
90
90
89
88
88
87
87
15
92
91
91
90
89
89
88
88
87
87
20
91
91
90
89
89
88
88
87
87
86
25
89
89
88
87
87
86
86
85
85
84
30
87
87
86
85
85
84
84
83
83
82
35
86
85
84
84
83
83
82
82
81
81
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 21
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM V1
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: 8000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
90
89
88
88
87
87
86
86
85
85
15
89
89
88
87
87
86
86
85
85
84
20
88
87
86
86
85
85
84
84
83
83
25
86
85
84
84
83
83
82
82
81
81
30
84
83
83
82
81
81
81
80
80
79
Altitude: 10000 ft
60
66
72
78
84
90
96
102
108
114
10
87
87
86
85
85
84
84
83
83
82
15
86
85
84
84
83
83
82
82
81
81
20
84
83
83
82
82
81
81
80
80
79
25
82
81
81
80
80
79
79
78
78
78
30
80
80
79
79
78
78
77
77
76
76
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 22
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: Sea Level and Below
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
110
107
105
102
101
100
100
99
99
98
15
110
107
105
102
101
100
100
99
98
98
20
110
107
104
102
101
100
100
99
98
98
25
109
107
104
102
101
100
99
99
98
98
30
109
107
104
101
101
100
99
99
98
98
35
109
107
104
101
101
100
99
99
98
97
40
106
104
101
99
99
98
97
97
96
96
45
103
100
98
97
96
96
95
95
94
94
50
100
97
96
95
94
94
93
93
92
92
AOM-1502-016
Altitude: 2000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
106
104
101
100
99
98
97
97
96
96
15
106
104
101
99
99
98
97
97
96
96
20
106
104
101
99
99
98
97
97
96
96
25
106
103
101
99
99
98
97
97
96
95
30
106
103
101
99
98
98
97
97
96
95
35
104
101
98
98
97
96
96
95
94
94
40
101
98
96
96
95
94
94
93
93
92
45
97
95
94
93
93
92
92
91
91
90
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 23
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: 4000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
103
100
98
97
97
96
95
95
94
94
15
103
100
98
97
96
96
95
95
94
93
20
103
100
98
97
96
96
95
94
94
93
25
103
100
98
97
96
96
95
94
94
93
30
101
98
97
96
95
95
94
93
93
92
35
98
95
95
94
93
93
92
91
91
90
40
95
93
93
92
91
91
90
90
89
89
Altitude: 6000 ft
60
66
72
78
84
90
96
102
108
114
10
99
96
95
95
94
93
93
92
92
91
15
99
96
95
95
94
93
93
92
92
91
20
99
96
95
94
94
93
93
92
91
91
25
98
95
94
94
93
92
92
91
91
90
30
95
93
93
92
91
91
90
90
89
89
35
92
92
91
90
90
89
88
88
87
87
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 24
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-1
EMBRAER 190
Altitude: 8000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
95
93
92
92
91
91
90
89
89
88
15
95
93
92
92
91
90
90
89
89
88
20
94
93
92
91
91
90
90
89
89
88
25
92
91
91
90
89
89
88
88
87
87
30
90
89
89
88
88
87
87
86
86
85
AOM-1502-016
Altitude: 10000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
91
90
90
89
88
88
87
87
86
86
15
91
90
90
89
88
88
87
87
86
86
20
90
89
88
88
87
86
86
85
85
85
25
88
87
87
86
85
85
84
84
83
83
30
86
86
85
84
84
83
83
82
82
82
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 25
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: Sea Level and Below
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
102
100
98
97
96
96
95
94
94
93
15
102
99
98
97
96
95
95
94
94
93
20
102
99
97
97
96
95
95
94
94
93
25
102
99
97
97
96
95
95
94
93
93
30
102
99
97
96
96
95
94
94
93
93
35
99
96
95
94
94
93
92
92
91
91
40
95
94
93
92
92
91
90
90
89
89
45
92
92
91
90
90
89
88
88
87
87
50
90
89
89
88
87
87
86
86
85
85
Altitude: 2000 ft
60
66
72
78
84
90
96
102
108
114
10
99
96
95
95
94
93
93
92
92
91
15
99
96
95
95
94
93
93
92
92
91
20
99
96
95
94
94
93
93
92
91
91
25
99
96
95
94
94
93
92
92
91
91
30
96
94
93
93
92
91
91
90
90
89
35
93
92
91
91
90
89
89
88
88
87
40
91
90
89
89
88
88
87
86
86
85
45
89
88
87
87
86
86
85
85
84
84
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 26
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: 4000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
96
94
93
92
92
91
91
90
89
89
15
95
94
93
92
92
91
90
90
89
89
20
95
94
93
92
92
91
90
90
89
89
25
93
92
92
91
90
90
89
89
88
88
30
91
90
90
89
88
88
87
87
86
86
35
89
88
88
87
87
86
85
85
84
84
40
87
86
86
85
85
84
84
83
83
82
AOM-1502-016
Altitude: 6000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
92
91
91
90
90
89
88
88
87
87
15
92
91
91
90
89
89
88
88
87
87
20
91
91
90
89
89
88
88
87
87
86
25
89
89
88
87
87
86
86
85
85
84
30
87
87
86
85
85
84
84
83
83
82
35
86
85
84
84
83
83
82
82
81
81
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 27
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
MINIMUM VR
Engine: CF34-10E6 — T/O-2
EMBRAER 190
Altitude: 8000 ft
WEIGHT (X 1000 lb)
OAT
(°C)
60
66
72
78
84
90
96
102
108
114
10
90
89
88
88
87
87
86
86
85
85
15
89
89
88
87
87
86
86
85
85
84
20
88
87
86
86
85
85
84
84
83
83
25
86
85
84
84
83
83
82
82
81
81
30
84
83
83
82
81
81
81
80
80
79
Altitude: 10000 ft
60
66
72
78
84
90
96
102
108
114
10
87
87
86
85
85
84
84
83
83
82
15
86
85
84
84
83
83
82
82
81
81
20
84
83
83
82
82
81
81
80
80
79
25
82
81
81
80
80
79
79
78
78
78
30
80
80
79
79
78
78
77
77
76
76
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 28
Takeoff
REVISION 23
AOM-1502-016
WEIGHT (X 1000 lb)
OAT
(°C)
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
SIMPLIFIED TAKEOFF ANALYSIS TABLES
Simplified Takeoff Analysis tables are presented for a set of pressure
altitudes, temperatures and runway lengths for the conditions below:
– Dry runway;
– Zero wind;
– Zero slope;
– No clearway;
– No stopway;
– Obstacles are not considered;
– Maximum manual braking;
– ECS and ATTCS ON;
– Balanced V1;
– Landing flap 5.
Following limitation factors were considered in the calculation of these
tables:
– R – Runway Length;
– W – WAT (Climb);
– B – Brake Energy;
– S – Structural;
– A – Approach Climb;
– SF – Final Segment;
– P – Tire Speed;
– L– Maximum Lift-off Speed.
AOM-1502-016
NOTE: The Maximum Structural Takeoff Weight defined in the AFM
must be checked.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 29
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: Sea Level
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
-15
101642 R
106340 R
110929 R
114199 S
114199 S
114199 S
114199 S
137/139/143
141/143/146
145/147/150
148/149/152
148/149/152
148/149/152
148/149/152
100734 R
105358 R
109884 R
114199 S
114199 S
114199 S
114199 S
136/138/142
140/142/146
144/146/149
148/149/152
148/149/152
148/149/152
148/149/152
-10
99845 R
104409 R
108876 R
113194 R
114199 S
114199 S
114199 S
135/138/142
140/141/145
144/145/148
147/149/151
148/149/152
148/149/152
148/149/152
-5
98981 R
103495 R
107885 R
112164 R
114199 S
114199 S
114199 S
134/137/141
139/141/144
143/144/147
146/148/150
148/149/152
148/149/152
148/149/152
0
98083 R
102566 R
106880 R
111117 R
114199 S
114199 S
114199 S
133/136/141
138/140/144
142/144/147
145/147/150
148/149/152
148/149/152
148/149/152
5
97228 R
101665 R
105915 R
110095 R
114133 R
114199 S
114199 S
132/135/140
137/139/143
141/143/146
145/146/149
148/149/152
148/149/152
148/149/152
10
96354 R
100717 R
104941 R
109051 R
113045 R
114199 S
114199 S
131/135/139
136/138/142
140/142/145
144/145/148
147/149/151
148/149/152
148/149/152
15
95494 R
99820 R
103991 R
108043 R
112003 R
114199 S
114199 S
131/134/139
135/138/142
139/141/145
143/145/148
146/148/150
148/149/152
148/149/152
20
94654 R
98937 R
103045 R
107055 R
110968 R
114199 S
114199 S
130/133/138
134/137/141
138/141/144
142/144/147
145/147/150
148/149/152
148/149/152
25
93819 R
98073 R
102149 R
106090 R
109953 R
113668 R
114199 S
129/133/137
133/136/141
137/140/143
141/143/146
145/146/149
148/149/151
148/150/152
30
93024 R
97213 R
101269 R
105148 R
108983 R
112661 R
114199 S
128/132/137
133/136/140
137/139/143
140/142/146
144/145/148
147/148/151
148/150/152
35
92230 R
96360 R
100366 R
104194 R
107963 R
111597 R
114199 S
127/131/136
132/135/139
136/138/142
139/142/145
143/145/148
146/148/150
148/150/152
40
89188 R
93208 R
97061 R
100784 R
104371 R
107881 R
111243 R
126/129/134
130/133/137
134/136/140
137/139/143
141/142/145
144/145/147
147/148/150
45
86480 R
90373 R
94129 R
97737 R
101225 R
104583 R
107832 R
124/127/132
128/131/135
132/134/138
136/137/140
139/140/143
142/143/145
145/146/147
50
83878 R
87663 R
91335 R
94840 R
98239 R
101516 R
103304 W
123/126/130
127/129/133
131/132/136
134/136/138
137/139/141
140/141/143
142/143/144
For ANTI-ICE ON, decrease weight by 350 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 30
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 500 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
100204 R
104829 R
109321 R
113687 R
114199 S
114199 S
114199 S
136/138/142
140/142/145
144/146/148
148/149/151
148/149/152
148/149/152
148/149/152
99313 R
103864 R
108304 R
112617 R
114199 S
114199 S
114199 S
135/137/141
139/141/145
143/145/148
147/148/151
148/149/152
148/149/152
148/149/152
98436 R
102935 R
107300 R
111562 R
114199 S
114199 S
114199 S
134/137/141
138/140/144
142/144/147
146/147/150
148/149/152
148/149/152
148/149/152
97576 R
102027 R
106315 R
110538 R
114199 S
114199 S
114199 S
133/136/140
138/140/143
142/143/146
145/147/149
148/149/152
148/149/152
148/149/152
96690 R
101112 R
105347 R
109501 R
113518 R
114199 S
114199 S
132/135/140
137/139/143
141/142/146
144/146/149
148/149/151
148/150/152
148/150/152
95846 R
100192 R
104404 R
108484 R
112471 R
114199 S
114199 S
131/134/139
136/138/142
140/142/145
143/145/148
147/148/151
148/150/152
148/150/152
94982 R
99286 R
103448 R
107467 R
111402 R
114199 S
114199 S
130/134/138
135/137/141
139/141/144
143/144/147
146/147/150
148/150/152
148/150/152
94143 R
98407 R
102501 R
106480 R
110385 R
114105 R
114199 S
130/133/138
134/137/141
138/140/144
142/144/147
145/147/149
148/150/152
148/150/152
93304 R
97542 R
101590 R
105524 R
109357 R
113071 R
114199 S
129/132/137
133/136/140
137/139/143
141/143/146
144/146/149
147/149/151
148/150/152
92503 R
96696 R
100717 R
104588 R
108382 R
112059 R
114199 S
128/132/137
132/135/140
136/139/142
140/142/145
143/145/148
147/148/150
148/150/152
91726 R
95853 R
99849 R
103676 R
107424 R
111070 R
114199 S
127/131/136
131/135/139
135/138/142
139/141/145
143/144/147
146/147/150
148/150/152
90537 R
94594 R
98528 R
102303 R
105955 R
109552 R
112915 R
126/130/135
130/134/138
134/137/141
138/140/144
142/143/146
145/146/149
147/149/151
87601 R
91557 R
95342 R
99001 R
102525 R
105935 R
109264 R
124/128/133
129/132/136
133/135/139
136/138/141
139/141/144
143/144/146
145/147/148
84964 R
88791 R
92481 R
96026 R
99453 R
102739 R
105913 R
123/126/131
127/130/134
131/133/137
134/136/139
138/139/142
141/142/144
144/145/146
82293 R
86007 R
89607 R
93044 R
96377 R
99590 R
101297 W
122/124/129
126/128/132
129/131/134
133/134/137
136/137/139
139/140/142
140/141/143
For ANTI-ICE ON, decrease weight by 350 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 31
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 1000 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
98790 R
103333 R
107734 R
112036 R
114199 S
114199 S
114199 S
135/137/141
139/141/144
143/145/147
147/148/150
149/150/152
149/150/152
149/150/152
-15
97901 R
102383 R
106728 R
110967 R
114199 S
114199 S
114199 S
134/136/140
138/140/144
142/144/147
146/147/150
149/150/152
149/150/152
149/150/152
-10
97033 R
101468 R
105740 R
109936 R
113979 R
114199 S
114199 S
133/136/140
137/139/143
141/143/146
145/146/149
148/149/152
149/150/152
149/150/152
-5
96160 R
100567 R
104783 R
108917 R
112928 R
114199 S
114199 S
132/135/139
136/139/142
140/142/145
144/146/148
147/149/151
149/150/152
149/150/152
0
95300 R
99663 R
103838 R
107896 R
111862 R
114199 S
114199 S
131/134/139
136/138/142
140/141/145
143/145/148
147/148/150
149/150/152
149/150/152
5
94464 R
98748 R
102900 R
106891 R
110812 R
114199 S
114199 S
130/133/138
135/137/141
139/141/144
142/144/147
146/147/150
149/150/152
149/150/152
10
93622 R
97870 R
101965 R
105903 R
109788 R
113506 R
114199 S
129/133/137
134/136/140
138/140/143
141/143/146
145/146/149
148/149/151
149/150/152
15
92800 R
97000 R
101034 R
104951 R
108776 R
112468 R
114199 S
129/132/137
133/136/140
137/139/143
141/142/145
144/146/148
147/148/151
148/150/152
20
91980 R
96154 R
100155 R
104022 R
107768 R
111450 R
114199 S
128/131/136
132/135/139
136/138/142
140/142/145
143/145/147
146/148/150
148/150/152
25
91196 R
95309 R
99289 R
103095 R
106814 R
110455 R
113846 R
127/131/136
131/134/139
135/138/141
139/141/144
142/144/147
145/147/149
148/150/152
30
90436 R
94502 R
98441 R
102211 R
105878 R
109471 R
112846 R
126/130/135
130/134/138
134/137/141
138/140/144
141/143/146
145/146/149
147/149/151
35
88850 R
92835 R
96702 R
100407 R
103994 R
107486 R
110821 R
125/129/134
129/132/137
133/136/140
137/139/142
140/142/145
143/145/147
146/148/150
40
86022 R
89910 R
93634 R
97230 R
100691 R
104040 R
107287 R
123/127/132
128/130/135
131/134/137
135/137/140
138/140/142
141/143/145
144/145/147
45
83458 R
87218 R
90843 R
94325 R
97692 R
100919 R
104008 W
122/125/130
126/129/133
130/132/135
133/135/138
137/138/140
139/141/143
142/143/145
50 A
80716 R
84371 R
87891 R
91263 R
94528 R
97676 R
99285 W
120/123/128
124/127/130
128/130/133
132/133/136
135/136/138
138/139/140
139/140/141
For ANTI-ICE ON, decrease weight by 350 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 32
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 1500 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
97434 R
101901 R
106215 R
110448 R
114199 S
114199 S
114199 S
134/136/140
138/140/143
142/143/146
146/147/149
149/150/152
149/150/152
149/150/152
96557 R
100963 R
105229 R
109393 R
113417 R
114199 S
114199 S
133/135/140
137/139/143
141/143/146
145/146/149
148/149/151
149/150/152
149/150/152
95704 R
100069 R
104271 R
108379 R
112362 R
114199 S
114199 S
132/135/139
136/138/142
140/142/145
144/145/148
147/148/151
149/150/152
149/150/152
94828 R
99168 R
103314 R
107355 R
111314 R
114199 S
114199 S
131/134/138
135/138/141
139/141/144
143/144/147
146/148/150
149/150/152
149/150/152
93988 R
98263 R
102384 R
106363 R
110253 R
114005 R
114199 S
130/133/138
134/137/141
138/140/144
142/144/146
145/147/149
149/150/152
149/150/152
93154 R
97374 R
101460 R
105371 R
109234 R
112940 R
114199 S
129/132/137
134/136/140
138/140/143
141/143/146
145/146/148
148/149/151
149/150/152
92333 R
96516 R
100533 R
104428 R
108222 R
111888 R
114199 S
128/132/136
133/135/140
137/139/142
140/142/145
144/145/148
147/148/150
149/150/152
91510 R
95667 R
99637 R
103496 R
107210 R
110878 R
114199 S
127/131/136
132/135/139
136/138/142
139/141/144
143/144/147
146/147/150
149/150/152
90723 R
94835 R
98778 R
102586 R
106252 R
109874 R
113261 R
127/130/135
131/134/138
135/137/141
139/141/144
142/144/146
145/147/149
148/149/151
89959 R
94005 R
97926 R
101674 R
105324 R
108896 R
112256 R
126/130/135
130/133/138
134/137/141
138/140/143
141/143/146
144/146/148
147/149/151
89219 R
93221 R
97106 R
100829 R
104434 R
107943 R
111288 R
125/129/134
129/133/137
133/136/140
137/139/143
140/142/145
144/145/148
146/148/150
87237 R
91145 R
94942 R
98577 R
102095 R
105493 R
108781 R
124/128/133
128/131/136
132/135/138
136/138/141
139/141/144
142/144/146
145/146/148
84486 R
88307 R
91969 R
95503 R
98904 R
102192 R
105358 R
122/126/130
126/129/133
130/133/136
134/136/139
137/139/141
140/141/144
143/144/146
81906 R
85599 R
89143 R
92581 R
95889 R
99062 R
102096 W
121/124/128
125/127/131
129/131/134
132/134/137
135/137/139
138/139/141
141/142/144
79143 R
82717 R
86185 R
89509 R
92699 R
95784 R
97264 W
119/122/126
123/125/129
127/129/132
130/132/134
133/135/137
136/137/139
138/139/140
For ANTI-ICE ON, decrease weight by 350 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 33
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 2000 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
96087 R
100483 R
104730 R
108865 R
112860 R
114199 S
114199 S
133/135/139
137/139/142
141/142/145
145/146/148
148/149/151
149/150/152
149/150/152
-15
95224 R
99570 R
103755 R
107822 R
111797 R
114199 S
114199 S
132/134/139
136/138/142
140/142/145
144/145/148
147/148/150
149/150/152
149/150/152
-10
94383 R
98681 R
102813 R
106823 R
110757 R
114199 S
114199 S
131/134/138
135/137/141
139/141/144
143/144/147
146/147/150
149/150/152
149/150/152
-5
93509 R
97781 R
101872 R
105826 R
109694 R
113423 R
114199 S
130/133/137
134/137/140
138/140/143
142/143/146
145/146/149
148/149/151
149/150/152
0
92677 R
96871 R
100941 R
104833 R
108654 R
112361 R
114199 S
129/132/137
133/136/140
137/139/143
141/143/145
144/146/148
147/149/151
149/150/152
5
91855 R
96018 R
100030 R
103890 R
107654 R
111308 R
114199 S
128/131/136
132/135/139
136/139/142
140/142/145
143/145/147
147/148/150
149/150/152
10
91052 R
95173 R
99123 R
102963 R
106669 R
110283 R
113701 R
127/131/135
132/134/139
136/138/141
139/141/144
143/144/147
146/147/149
148/150/151
15
90248 R
94341 R
98263 R
102051 R
105684 R
109289 R
112672 R
126/130/135
131/134/138
135/137/141
138/140/143
142/143/146
145/146/149
148/149/151
20
89475 R
93506 R
97408 R
101149 R
104767 R
108306 R
111663 R
126/129/134
130/133/137
134/136/140
138/140/143
141/143/145
144/146/148
147/148/150
25
88726 R
92710 R
96573 R
100264 R
103860 R
107337 R
110678 R
125/129/134
129/132/137
133/136/140
137/139/142
140/142/145
143/145/147
146/147/149
30
88012 R
91964 R
95760 R
99448 R
102999 R
106425 R
109741 R
124/128/133
128/132/136
132/135/139
136/138/142
139/141/144
142/144/147
145/147/149
35
85633 R
89467 R
93191 R
96760 R
100210 R
103540 R
106755 R
123/126/131
127/130/134
131/133/137
134/136/140
138/139/142
141/142/145
144/145/147
40
82960 R
86711 R
90311 R
93785 R
97128 R
100358 R
103466 R
121/125/129
125/128/132
129/131/135
133/134/138
136/137/140
139/140/142
142/143/144
45
80363 R
83990 R
87467 R
90848 R
94096 R
97216 R
100215 W
120/123/127
124/126/130
127/129/133
131/133/135
134/135/138
137/138/140
140/141/142
50 A
77580 R
81085 R
84488 R
87749 R
90881 R
93903 R
95354 W
118/121/125
122/124/128
126/127/131
129/131/133
132/133/135
135/136/138
136/137/139
For ANTI-ICE ON, decrease weight by 350 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 34
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 2500 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
94789 R
99113 R
103298 R
107344 R
111292 R
114199 S
114199 S
132/134/138
136/138/141
140/141/144
143/145/147
147/148/150
149/150/152
149/150/152
93933 R
98216 R
102337 R
106326 R
110232 R
113966 R
114199 S
131/133/138
135/137/141
139/141/144
143/144/146
146/147/149
149/150/152
149/150/152
93075 R
97332 R
101402 R
105338 R
109207 R
112899 R
114199 S
130/133/137
134/136/140
138/140/143
142/143/146
145/146/148
148/149/151
149/150/152
92238 R
96440 R
100471 R
104366 R
108151 R
111831 R
114199 S
129/132/136
133/136/139
137/139/142
141/142/145
144/145/148
147/148/150
149/150/152
91408 R
95541 R
99551 R
103384 R
107131 R
110775 R
114192 R
128/131/136
132/135/139
136/138/142
140/142/144
143/145/147
146/148/150
149/150/152
90597 R
94699 R
98637 R
102457 R
106136 R
109738 R
113149 R
127/130/135
131/134/138
135/138/141
139/141/144
142/144/146
145/147/149
148/149/151
89788 R
93867 R
97760 R
101545 R
105161 R
108740 R
112122 R
126/130/135
131/133/138
134/137/140
138/140/143
141/143/146
145/146/148
147/149/150
89013 R
93046 R
96915 R
100650 R
104240 R
107752 R
111105 R
125/129/134
130/133/137
134/136/140
137/139/143
141/142/145
144/145/147
147/148/150
88258 R
92226 R
96073 R
99748 R
103326 R
106785 R
110112 R
125/128/133
129/132/136
133/135/139
136/139/142
140/142/144
143/144/147
146/147/149
87515 R
91451 R
95251 R
98902 R
102435 R
105836 R
109143 R
124/128/133
128/131/136
132/135/139
136/138/141
139/141/144
142/144/146
145/146/148
86624 R
90510 R
94245 R
97876 R
101348 R
104731 R
107989 R
123/127/132
127/131/135
131/134/138
135/137/141
138/140/143
141/143/145
144/146/148
84085 R
87851 R
91508 R
95012 R
98400 R
101670 R
104820 R
121/125/130
126/129/133
130/132/136
133/135/138
136/138/141
139/141/143
142/144/145
81456 R
85140 R
88673 R
92083 R
95364 R
98538 R
101592 R
120/123/128
124/127/131
128/130/134
131/133/136
135/136/139
138/139/141
140/141/143
78857 R
82417 R
85831 R
89149 R
92337 R
95400 R
98340 W
119/122/126
123/125/129
126/128/132
130/131/134
133/134/136
136/137/139
138/139/141
76142 R
79581 R
82922 R
86127 R
89200 R
92169 R
93492 W
117/120/124
121/123/127
125/126/129
128/129/132
131/132/134
134/135/136
135/136/137
For ANTI-ICE ON, decrease weight by 350 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 35
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 3000 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
93497 R
97766 R
101879 R
105844 R
109735 R
113445 R
114199 S
131/133/137
135/137/140
139/140/143
142/144/146
146/147/149
149/150/151
149/150/152
-15
92651 R
96872 R
100930 R
104853 R
108687 R
112370 R
114199 S
130/132/137
134/136/140
138/140/143
141/143/145
145/146/148
148/149/151
149/150/152
-10
91799 R
95995 R
100013 R
103894 R
107651 R
111313 R
114199 S
129/132/136
133/135/139
137/139/142
141/142/145
144/145/147
147/148/150
149/150/152
-5
90965 R
95085 R
99080 R
102898 R
106610 R
110250 R
113667 R
128/131/135
132/135/139
136/138/141
140/141/144
143/144/147
146/147/149
149/150/152
0
90147 R
94233 R
98174 R
101959 R
105620 R
109201 R
112592 R
127/130/135
131/134/138
135/137/141
139/141/143
142/144/146
145/146/148
148/149/151
5
89346 R
93391 R
97267 R
101035 R
104659 R
108180 R
111565 R
126/129/134
130/133/137
134/137/140
138/140/143
141/143/145
144/146/148
147/148/150
10
88550 R
92569 R
96418 R
100137 R
103701 R
107199 R
110554 R
125/129/134
130/132/137
133/136/139
137/139/142
140/142/145
144/145/147
146/148/149
15
87793 R
91742 R
95573 R
99245 R
102796 R
106228 R
109550 R
124/128/133
129/132/136
133/135/139
136/138/142
140/141/144
143/144/146
146/147/149
20
87044 R
90953 R
94747 R
98383 R
101898 R
105282 R
108573 R
124/127/132
128/131/135
132/134/138
135/138/141
139/141/143
142/143/146
145/146/148
25
86312 R
90191 R
93917 R
97538 R
101005 R
104373 R
107619 R
123/127/132
127/130/135
131/134/138
135/137/140
138/140/143
141/143/145
144/145/147
30
85245 R
89069 R
92741 R
96313 R
99739 R
103057 R
106249 R
122/126/131
126/130/134
130/133/137
134/136/139
137/139/142
140/142/144
143/144/146
35
82548 R
86245 R
89835 R
93276 R
96601 R
99812 R
102905 R
120/124/129
124/128/132
128/131/135
132/134/137
135/137/140
138/140/142
141/142/144
40
79960 R
83577 R
87046 R
90393 R
93613 R
96729 R
99730 R
119/122/127
123/126/130
127/129/132
130/132/135
133/135/137
136/138/140
139/140/142
45 A
77359 R
80854 R
84205 R
87460 R
90589 R
93596 R
96448 W
118/121/125
121/124/128
125/127/130
128/130/133
132/133/135
134/136/137
137/138/140
50 A
74713 R
78090 R
81367 R
84497 R
87531 R
90445 R
91769 W
116/119/123
120/122/125
123/125/128
127/128/131
130/131/133
133/134/135
134/135/136
For ANTI-ICE ON, decrease weight by 450 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 36
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 3500 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45 A
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
92179 R
96387 R
100435 R
104344 R
108143 R
111810 R
113106 W
129/132/136
134/136/139
138/139/142
141/143/145
145/146/148
148/149/150
149/150/151
91321 R
95503 R
99499 R
103362 R
107116 R
110748 R
112988 W
129/131/136
133/135/139
137/139/142
140/142/144
144/145/147
147/148/150
149/150/151
90513 R
94640 R
98599 R
102423 R
106094 R
109709 R
112869 W
128/131/135
132/134/138
136/138/141
139/141/144
143/144/146
146/147/149
148/149/151
89704 R
93763 R
97698 R
101461 R
105117 R
108677 R
112067 R
127/130/135
131/134/138
135/137/140
139/140/143
142/143/146
145/146/148
148/149/150
88900 R
92925 R
96792 R
100541 R
104149 R
107648 R
111013 R
126/129/134
130/133/137
134/136/140
138/139/142
141/143/145
144/145/147
147/148/150
88090 R
92090 R
95913 R
99627 R
103175 R
106645 R
109996 R
125/129/133
129/132/136
133/136/139
137/139/142
140/142/144
143/145/147
146/147/149
87316 R
91276 R
95071 R
98720 R
102260 R
105672 R
108985 R
124/128/133
128/131/136
132/135/139
136/138/141
139/141/144
142/144/146
145/147/148
86572 R
90462 R
94236 R
97843 R
101354 R
104732 R
107999 R
123/127/132
128/131/135
132/134/138
135/137/141
138/140/143
142/143/145
144/146/148
85832 R
89693 R
93403 R
97003 R
100468 R
103804 R
107036 R
123/127/132
127/130/135
131/133/137
134/137/140
138/140/142
141/142/145
144/145/147
85114 R
88934 R
92603 R
96171 R
99594 R
102908 R
106095 R
122/126/131
126/129/134
130/133/137
134/136/139
137/139/142
140/142/144
143/144/146
83680 R
87431 R
91036 R
94543 R
97906 R
101160 R
104306 R
121/125/130
125/128/133
129/132/136
132/135/138
136/138/141
139/140/143
142/143/145
81042 R
84674 R
88199 R
91578 R
94844 R
97989 R
101036 R
119/123/128
123/126/131
127/130/133
131/133/136
134/136/138
137/138/141
140/141/143
78470 R
82022 R
85426 R
88715 R
91876 R
94936 R
97885 R
118/121/126
122/125/129
126/128/131
129/131/134
132/134/136
135/136/138
138/139/141
75878 R
79308 R
82597 R
85792 R
88863 R
91815 R
94551 W
116/119/124
120/123/126
124/126/129
127/129/132
130/132/134
133/134/136
136/137/138
73347 R
76663 R
79878 R
82955 R
85935 R
88796 R
90102 W
115/118/122
119/121/124
122/124/127
126/127/129
129/130/132
131/132/134
133/133/135
For ANTI-ICE ON, decrease weight by 550 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 37
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17 – ANTI-ICE OFF
Airport Pressure Altitude: 4000 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
90870 R
95017 R
99003 R
102854 R
106572 R
110188 R
111681 W
128/131/135
133/135/138
137/138/141
140/142/144
144/145/147
147/148/149
148/149/150
-15
90024 R
94143 R
98087 R
101884 R
105548 R
109132 R
111562 W
127/130/135
132/134/138
136/138/141
139/141/143
143/144/146
146/147/148
148/149/150
-10
89227 R
93273 R
97195 R
100944 R
104576 R
108118 R
111442 W
127/130/134
131/133/137
135/137/140
138/140/143
142/143/145
145/146/148
148/149/150
-5
88446 R
92460 R
96328 R
100044 R
103637 R
107115 R
110479 R
126/129/134
130/133/137
134/136/139
138/139/142
141/142/145
144/145/147
147/148/149
0
87661 R
91628 R
95435 R
99134 R
102690 R
106106 R
109446 R
125/128/133
129/132/136
133/135/139
137/138/141
140/141/144
143/144/146
146/147/149
5
86858 R
90801 R
94579 R
98227 R
101724 R
105132 R
108438 R
124/128/132
128/131/135
132/135/138
136/138/141
139/141/143
142/144/146
145/146/148
10
86102 R
89976 R
93734 R
97335 R
100818 R
104180 R
107433 R
123/127/132
127/130/135
131/134/138
135/137/140
138/140/143
141/143/145
144/145/147
15
85359 R
89191 R
92908 R
96474 R
99922 R
103243 R
106459 R
122/126/131
127/130/134
131/133/137
134/136/140
137/139/142
140/142/144
143/145/147
20
84633 R
88432 R
92085 R
95634 R
99030 R
102338 R
105520 R
122/126/131
126/129/134
130/132/136
133/136/139
137/139/141
140/141/144
143/144/146
25
83908 R
87684 R
91301 R
94815 R
98187 R
101454 R
104611 R
121/125/130
125/128/133
129/132/136
132/135/138
136/138/141
139/141/143
142/143/145
30
82123 R
85805 R
89342 R
92783 R
96082 R
99275 R
102363 R
120/124/129
124/127/132
128/130/134
131/133/137
134/136/139
137/139/142
140/142/144
35
79547 R
83113 R
86572 R
89891 R
93099 R
96187 R
99178 R
118/122/127
122/125/129
126/129/132
129/132/135
133/134/137
136/137/139
138/140/142
40
76990 R
80476 R
83818 R
87046 R
90149 R
93155 R
96051 R
117/120/125
121/123/127
124/127/130
128/130/133
131/132/135
134/135/137
137/138/139
45 A
74404 R
77770 R
80998 R
84130 R
87146 R
90043 R
92688 W
115/118/122
119/122/125
123/125/128
126/128/130
129/130/133
132/133/135
134/135/137
50 A
71986 R
75243 R
78401 R
81423 R
84347 R
87157 R
88458 W
114/116/120
118/120/123
121/123/126
124/126/128
127/128/130
130/131/133
131/132/134
For ANTI-ICE ON, decrease weight by 550 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 38
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: Sea Level
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
109860 W 109860 W 109860 W 109860 W 109860 W 109860 W 109860 W
130/130/134
130/130/134
109466 R
109794 W 109794 W 109794 W 109794 W 109794 W 109794 W
129/129/134
129/129/134
108951 R
109727 W 109727 W 109727 W 109727 W 109727 W 109727 W
129/129/133
129/129/134
108449 R
109651 W 109651 W 109651 W 109651 W 109651 W 109651 W
129/129/133
129/129/134
107893 R
109505 W 109505 W 109505 W 109505 W 109505 W 109505 W
128/128/133
129/129/134
107236 R
109339 W 109339 W 109339 W 109339 W 109339 W 109339 W
127/128/132
129/129/133
106461 R
109088 W 109088 W 109088 W 109088 W 109088 W 109088 W
127/127/132
129/129/133
129/129/133
105722 R
108478 R
108825 W 108825 W 108825 W 108825 W 108825 W
126/127/131
129/129/133
129/129/133
105029 R
107850 R
108562 W 108562 W 108562 W 108562 W 108562 W
125/126/131
128/128/133
129/129/133
104358 R
107234 R
108298 W 108298 W 108298 W 108298 W 108298 W
124/126/130
128/128/132
129/129/133
103565 R
106628 R
108034 W 108034 W 108034 W 108034 W 108034 W
123/125/130
128/128/132
129/129/133
102625 R
106030 R
106946 W 106946 W 106946 W 106946 W 106946 W
122/124/129
127/127/131
128/128/132
99295 R
130/130/134
129/129/134
129/129/134
129/129/134
129/129/134
129/129/133
130/130/134
129/129/134
129/129/134
129/129/134
129/129/134
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
128/128/132
130/130/134
129/129/134
129/129/134
129/129/134
129/129/134
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
128/128/132
130/130/134
129/129/134
129/129/134
129/129/134
129/129/134
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
128/128/132
130/130/134
129/129/134
129/129/134
129/129/134
129/129/134
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
129/129/133
128/128/132
102020 W 102020 W 102020 W 102020 W 102020 W 102020 W
121/123/127
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
95992 R
97702 W
97702 W
97702 W
97702 W
97702 W
125/125/129
97702 W
119/121/125
122/122/126
122/122/126
122/122/126
122/122/126
122/122/126
122/122/126
92654 R
93773 W
93773 W
93773 W
93773 W
93773 W
93773 W
118/119/123
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
For ANTI-ICE ON, decrease weight by 650 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 39
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 500 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
108318 W 108318 W 108318 W 108318 W 108318 W 108318 W 108318 W
129/129/133
129/129/133
107953 R
108252 W 108252 W 108252 W 108252 W 108252 W 108252 W
128/128/133
129/129/133
107444 R
108185 W 108185 W 108185 W 108185 W 108185 W 108185 W
128/128/132
129/129/133
106931 R
108101 W 108101 W 108101 W 108101 W 108101 W 108101 W
128/128/132
128/128/133
106368 R
107955 W 107955 W 107955 W 107955 W 107955 W 107955 W
127/127/132
128/128/133
105704 R
107784 W 107784 W 107784 W 107784 W 107784 W 107784 W
126/127/131
128/128/132
105015 R
107531 W 107531 W 107531 W 107531 W 107531 W 107531 W
126/126/131
128/128/132
128/128/132
104330 R
106962 R
107275 W 107275 W 107275 W 107275 W 107275 W
125/126/130
128/128/132
128/128/132
103659 R
106354 R
107018 W 107018 W 107018 W 107018 W 107018 W
124/125/130
127/127/132
128/128/132
103001 R
105786 R
106761 W 106761 W 106761 W 106761 W 106761 W
123/125/129
127/127/131
128/128/132
102086 R
105263 R
106504 W 106504 W 106504 W 106504 W 106504 W
122/124/129
127/127/131
128/128/132
100732 R
104083 R
105088 W 105088 W 105088 W 105088 W 105088 W
121/123/128
126/126/130
127/127/131
40
97532 R
129/129/133
129/129/133
129/129/133
128/128/133
128/128/133
128/128/132
129/129/133
129/129/133
129/129/133
128/128/133
128/128/133
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/131
129/129/133
129/129/133
129/129/133
128/128/133
128/128/133
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/131
129/129/133
129/129/133
129/129/133
128/128/133
128/128/133
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/131
129/129/133
129/129/133
129/129/133
128/128/133
128/128/133
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/131
100177 W 100177 W 100177 W 100177 W 100177 W 100177 W
120/121/126
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
94317 R
95996 W
95996 W
95996 W
95996 W
95996 W
95996 W
118/120/124
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
45
50 A
124/124/128
90883 R
91951 W
91951 W
91951 W
91951 W
91951 W
91951 W
117/118/122
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
For ANTI-ICE ON, decrease weight by 650 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 40
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 1000 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
106905 W 106905 W 106905 W 106905 W 106905 W 106905 W 106905 W
128/128/132
128/128/132
106440 R
106835 W 106835 W 106835 W 106835 W 106835 W 106835 W
128/128/132
127/127/132
128/128/132
105948 R
106764 W 106764 W 106764 W 106764 W 106764 W 106764 W
127/127/131
128/128/132
105480 R
106656 W 106656 W 106656 W 106656 W 106656 W 106656 W
127/127/131
128/128/132
104929 R
106498 W 106498 W 106498 W 106498 W 106498 W 106498 W
126/126/131
128/128/132
104274 R
106320 W 106320 W 106320 W 106320 W 106320 W 106320 W
125/126/130
127/127/132
127/127/132
103607 R
106034 R
106090 W 106090 W 106090 W 106090 W 106090 W
124/125/130
127/127/131
127/127/131
102946 R
105509 R
105879 W 105879 W 105879 W 105879 W 105879 W
124/125/129
127/127/131
127/127/131
102296 R
104986 R
105675 W 105675 W 105675 W 105675 W 105675 W
123/125/129
127/127/131
127/127/131
101529 R
104472 R
105470 W 105470 W 105470 W 105470 W 105470 W
122/124/129
126/126/130
127/127/131
100627 R
103905 R
105266 W 105266 W 105266 W 105266 W 105266 W
121/123/128
126/126/130
127/127/131
98850 R
102136 R
103164 W 103164 W 103164 W 103164 W 103164 W
120/122/127
124/125/129
126/126/130
126/126/130
126/126/130
126/126/130
95779 R
98424 W
98424 W
98424 W
98424 W
98424 W
98424 W
118/120/125
122/122/127
122/122/127
122/122/127
122/122/127
122/122/127
122/122/127
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/132
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/132
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/132
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
128/128/132
128/128/132
128/128/132
128/128/132
128/128/132
127/127/132
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
126/126/130
92649 R
94284 W
94284 W
94284 W
94284 W
94284 W
94284 W
117/119/123
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
89118 R
90106 W
90106 W
90106 W
90106 W
90106 W
90106 W
116/116/120
117/117/121
117/117/121
117/117/121
117/117/121
117/117/121
117/117/121
For ANTI-ICE ON, decrease weight by 650 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 41
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 1500 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
105591 W 105591 W 105591 W 105591 W 105591 W 105591 W 105591 W
127/127/131
127/127/131
105205 R
105531 W 105531 W 105531 W 105531 W 105531 W 105531 W
127/127/131
127/127/131
104763 R
105470 W 105470 W 105470 W 105470 W 105470 W 105470 W
126/126/131
127/127/131
104285 R
105358 W 105358 W 105358 W 105358 W 105358 W 105358 W
126/126/130
127/127/131
103656 R
105211 W 105211 W 105211 W 105211 W 105211 W 105211 W
125/126/130
127/127/131
102996 R
105056 W 105056 W 105056 W 105056 W 105056 W 105056 W
124/125/130
127/127/131
127/127/131
102339 R
104829 R
104892 W 104892 W 104892 W 104892 W 104892 W
123/125/129
127/127/131
127/127/131
101693 R
104320 R
104712 W 104712 W 104712 W 104712 W 104712 W
123/124/129
126/126/130
126/126/131
101014 R
103806 R
104522 W 104522 W 104522 W 104522 W 104522 W
122/124/128
126/126/130
126/126/130
100107 R
103282 R
104331 W 104331 W 104331 W 104331 W 104331 W
121/123/128
125/125/130
126/126/130
99230 R
102668 R
104145 W 104145 W 104145 W 104145 W 104145 W
120/122/127
125/125/129
126/126/130
97048 R
100317 R
101175 W 101175 W 101175 W 101175 W 101175 W
119/121/126
123/124/128
124/124/128
124/124/128
124/124/128
124/124/128
94071 R
96701 W
96701 W
96701 W
96701 W
96701 W
96701 W
117/119/124
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
30
35
40
45
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
126/126/131
126/126/130
126/126/130
126/126/130
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
126/126/131
126/126/130
126/126/130
126/126/130
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
126/126/131
126/126/130
126/126/130
126/126/130
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
127/127/131
126/126/131
126/126/130
126/126/130
126/126/130
124/124/128
90873 R
92570 W
92570 W
92570 W
92570 W
92570 W
92570 W
116/117/122
119/119/123
119/119/123
119/119/123
119/119/123
119/119/123
119/119/123
50 A
87327 R
88254 W
88254 W
88254 W
88254 W
88254 W
88254 W
115/115/119
116/116/120
116/116/120
116/116/120
116/116/120
116/116/120
116/116/120
For ANTI-ICE ON, decrease weight by 600 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 42
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 2000 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
104466 R
104555 W 104555 W 104555 W 104555 W 104555 W 104555 W
126/126/130
126/126/131
104019 R
104487 W 104487 W 104487 W 104487 W 104487 W 104487 W
126/126/130
126/126/130
103581 R
104419 W 104419 W 104419 W 104419 W 104419 W 104419 W
126/126/130
126/126/130
103031 R
104283 W 104283 W 104283 W 104283 W 104283 W 104283 W
125/125/130
126/126/130
102375 R
104127 W 104127 W 104127 W 104127 W 104127 W 104127 W
124/125/129
126/126/130
101719 R
103969 W 103969 W 103969 W 103969 W 103969 W 103969 W
123/124/129
126/126/130
126/126/130
101076 R
103632 R
103810 W 103810 W 103810 W 103810 W 103810 W
122/124/128
126/126/130
126/126/130
100443 R
103133 R
103637 W 103637 W 103637 W 103637 W 103637 W
121/123/128
125/125/130
126/126/130
99592 R
102629 R
103455 W 103455 W 103455 W 103455 W 103455 W
121/123/127
125/125/129
126/126/130
98701 R
102026 R
103272 W 103272 W 103272 W 103272 W 103272 W
120/122/127
124/125/129
126/126/130
97851 R
101430 R
103032 W 103032 W 103032 W 103032 W 103032 W
119/121/126
124/124/129
125/125/130
125/125/130
125/125/130
125/125/130
95257 R
98513 R
99302 W
99302 W
99302 W
99302 W
99302 W
118/120/125
122/122/127
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
126/126/131
126/126/130
126/126/130
126/126/130
126/126/130
126/126/131
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/131
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/131
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/131
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
92377 R
94936 R
94996 W
94996 W
94996 W
94996 W
94996 W
116/118/123
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
89107 R
90860 W
90860 W
90860 W
90860 W
90860 W
90860 W
115/116/120
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
85540 R
86522 W
86522 W
86522 W
86522 W
86522 W
86522 W
114/114/118
115/115/119
115/115/119
115/115/119
115/115/119
115/115/119
115/115/119
For ANTI-ICE ON, decrease weight by 600 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 43
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 2500 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
-15
-10
-5
0
5
103268 R
103533 W 103533 W 103533 W 103533 W 103533 W 103533 W
126/126/130
126/126/130
102826 R
103460 W 103460 W 103460 W 103460 W 103460 W 103460 W
125/125/129
126/126/130
102386 R
103386 W 103386 W 103386 W 103386 W 103386 W 103386 W
125/125/129
126/126/130
101756 R
103231 W 103231 W 103231 W 103231 W 103231 W 103231 W
124/124/129
126/126/130
101098 R
103072 W 103072 W 103072 W 103072 W 103072 W 103072 W
123/124/128
125/125/130
100449 R
102914 W 102914 W 102914 W 102914 W 102914 W 102914 W
122/123/128
125/125/129
125/125/129
99817 R
102418 R
102755 W 102755 W 102755 W 102755 W 102755 W
121/123/128
125/125/129
125/125/129
99098 R
101927 R
102589 W 102589 W 102589 W 102589 W 102589 W
120/123/127
125/125/129
125/125/129
98200 R
101388 R
102414 W 102414 W 102414 W 102414 W 102414 W
120/122/126
124/124/129
125/125/129
97319 R
100757 R
102239 W 102239 W 102239 W 102239 W 102239 W
119/121/126
123/124/128
125/125/129
96289 R
99903 R
118/120/125
122/123/128
125/125/129
125/125/129
125/125/129
125/125/129
93535 R
96722 R
97467 W
97467 W
97467 W
97467 W
97467 W
117/119/123
121/121/126
122/122/126
122/122/126
122/122/126
122/122/126
122/122/126
10
15
20
25
30
35
40
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
126/126/130
126/126/130
126/126/130
126/126/130
125/125/130
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
101923 W 101923 W 101923 W 101923 W 101923 W
125/125/129
90704 R
93196 R
93295 W
93295 W
93295 W
93295 W
93295 W
115/117/122
119/119/123
119/119/123
119/119/123
119/119/123
119/119/123
119/119/123
45
87410 R
89149 W
89149 W
89149 W
89149 W
89149 W
89149 W
114/115/119
117/117/120
117/117/120
117/117/120
117/117/120
117/117/120
117/117/120
50 A
83938 R
84837 W
84837 W
84837 W
84837 W
84837 W
84837 W
113/113/117
114/114/118
114/114/118
114/114/118
114/114/118
114/114/118
114/114/118
For ANTI-ICE ON, decrease weight by 600 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 44
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 3000 ft
TEMP
(°C)
-20
-15
-10
-5
0
5
10
15
20
25
30
35
40
45 A
50 A
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
102073 R
102460 W 102460 W 102460 W 102460 W 102460 W 102460 W
125/125/129
125/125/129
101636 R
102383 W 102383 W 102383 W 102383 W 102383 W 102383 W
124/124/129
125/125/129
101132 R
102305 W 102305 W 102305 W 102305 W 102305 W 102305 W
124/124/128
125/125/129
100480 R
102179 W 102179 W 102179 W 102179 W 102179 W 102179 W
123/124/128
125/125/129
99826 R
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
125/125/129
102035 W 102035 W 102035 W 102035 W 102035 W 102035 W
122/123/128
125/125/129
125/125/129
99185 R
101699 R
101867 W 101867 W 101867 W 101867 W 101867 W
125/125/129
121/123/127
125/125/129
125/125/129
98561 R
101208 R
101700 W 101700 W 101700 W 101700 W 101700 W
120/122/127
124/124/128
125/125/129
97707 R
100725 R
101529 W 101529 W 101529 W 101529 W 101529 W
120/122/126
124/124/128
125/125/129
96823 R
100117 R
101353 W 101353 W 101353 W 101353 W 101353 W
119/121/126
123/124/128
124/124/129
95957 R
99490 R
118/120/125
122/123/127
94742 R
98382 R
117/119/124
121/122/127
124/124/128
124/124/128
124/124/128
124/124/128
91822 R
94951 R
95725 W
95725 W
95725 W
95725 W
95725 W
116/118/122
120/120/124
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
125/125/129
125/125/129
125/125/129
124/124/129
125/125/129
125/125/129
125/125/129
125/125/129
124/124/129
125/125/129
125/125/129
125/125/129
125/125/129
124/124/129
125/125/129
125/125/129
125/125/129
125/125/129
124/124/129
101177 W 101177 W 101177 W 101177 W 101177 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100231 W 100231 W 100231 W 100231 W 100231 W
124/124/128
89040 R
91456 R
91596 W
91596 W
91596 W
91596 W
91596 W
114/116/120
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
118/118/122
85717 R
87438 W
87438 W
87438 W
87438 W
87438 W
87438 W
113/114/118
116/116/119
116/116/119
116/116/119
116/116/119
116/116/119
116/116/119
82339 R
83273 W
83273 W
83273 W
83273 W
83273 W
83273 W
112/112/116
113/113/116
113/113/116
113/113/116
113/113/116
113/113/116
113/113/116
For ANTI-ICE ON, decrease weight by 600 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 45
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 3500 ft
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
TEMP
(°C)
-20
-15
100820 R
101381 W 101381 W 101381 W 101381 W 101381 W 101381 W
124/124/128
124/124/129
100389 R
101299 W 101299 W 101299 W 101299 W 101299 W 101299 W
124/124/128
124/124/128
-10
99832 R
123/123/128
-5
99205 R
124/124/129
124/124/128
124/124/129
124/124/128
124/124/129
124/124/128
124/124/129
124/124/128
124/124/129
124/124/128
101216 W 101216 W 101216 W 101216 W 101216 W 101216 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
101126 W 101126 W 101126 W 101126 W 101126 W 101126 W
122/123/127
124/124/128
124/124/128
98567 R
100990 R
100998 W 100998 W 100998 W 100998 W 100998 W
121/122/127
124/124/128
124/124/128
97935 R
100493 R
100821 W 100821 W 100821 W 100821 W 100821 W
120/122/126
124/124/128
124/124/128
97209 R
100005 R
100643 W 100643 W 100643 W 100643 W 100643 W
119/121/126
124/124/128
124/124/128
96319 R
99469 R
119/121/125
123/123/127
95442 R
98845 R
118/120/125
122/123/127
94599 R
98224 R
117/119/124
121/122/127
124/124/128
124/124/128
124/124/128
124/124/128
93000 R
96586 R
98341 W
98341 W
98341 W
98341 W
98341 W
116/118/123
120/121/125
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
0
5
10
15
20
25
30
35
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100465 W 100465 W 100465 W 100465 W 100465 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100285 W 100285 W 100285 W 100285 W 100285 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100105 W 100105 W 100105 W 100105 W 100105 W
124/124/128
90152 R
93212 R
94015 W
94015 W
94015 W
94015 W
94015 W
115/117/121
119/119/123
120/120/124
120/120/124
120/120/124
120/120/124
120/120/124
40
87358 R
89704 R
89897 W
89897 W
89897 W
89897 W
89897 W
113/115/119
117/117/121
117/117/121
117/117/121
117/117/121
117/117/121
117/117/121
45 A
84046 R
85728 W
85728 W
85728 W
85728 W
85728 W
85728 W
112/113/117
114/114/118
114/114/118
114/114/118
114/114/118
114/114/118
114/114/118
50 A
80830 R
81761 W
81761 W
81761 W
81761 W
81761 W
81761 W
111/111/115
112/112/115
112/112/115
112/112/115
112/112/115
112/112/115
112/112/115
For ANTI-ICE ON, decrease weight by 600 lb.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 46
Takeoff
REVISION 23
AOM-1502-016
The certified MTOW of the airplane has to be respected.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
SIMPLIFIED TAKEOFF ANALYSIS TABLES
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 4 – V2/VS = 1.19 – ANTI-ICE OFF
Airport Pressure Altitude: 4000 ft
TEMP
(°C)
-20
RUNWAY LENGTH (ft)
TAKEOFF WEIGHT(lb) – LIMITATION CODE V1/VR/V2 (KIAS)
5500
6000
6500
7000
7500
8000
8500
99573 R
123/123/127
-15
99121 R
123/123/127
-10
98531 R
122/122/127
-5
0
5
10
15
20
25
30
35
40
45 A
50 A
97935 R
100290 W 100290 W 100290 W 100290 W 100290 W 100290 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100206 W 100206 W 100206 W 100206 W 100206 W 100206 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100121 W 100121 W 100121 W 100121 W 100121 W 100121 W
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
100036 W 100036 W 100036 W 100036 W 100036 W 100036 W
121/122/126
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
97315 R
99784 R
99903 W
99903 W
99903 W
99903 W
124/124/128
99903 W
120/122/126
123/123/128
124/124/128
124/124/128
124/124/128
124/124/128
124/124/128
96687 R
99290 R
99731 W
99731 W
99731 W
99731 W
99731 W
119/121/126
123/123/127
123/123/128
123/123/128
123/123/128
123/123/128
123/123/128
95823 R
98804 R
99559 W
99559 W
99559 W
99559 W
99559 W
118/120/125
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
94943 R
98196 R
99385 W
99385 W
99385 W
99385 W
99385 W
118/120/124
122/122/127
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
94083 R
97575 R
99212 W
99212 W
99212 W
99212 W
99212 W
117/119/124
121/122/126
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
93252 R
96965 R
99041 W
99041 W
99041 W
99041 W
99041 W
116/118/123
120/121/126
123/123/127
123/123/127
123/123/127
123/123/127
123/123/127
91265 R
94795 R
96529 W
96529 W
96529 W
96529 W
96529 W
115/117/122
119/120/124
121/121/125
121/121/125
121/121/125
121/121/125
121/121/125
88491 R
91474 R
92314 W
92314 W
92314 W
92314 W
92314 W
114/116/120
118/118/122
119/119/123
119/119/123
119/119/123
119/119/123
119/119/123
85682 R
87960 R
88192 W
88192 W
88192 W
88192 W
88192 W
112/114/118
116/116/120
116/116/120
116/116/120
116/116/120
116/116/120
116/116/120
82382 R
84041 W
84041 W
84041 W
84041 W
84041 W
84041 W
111/112/116
113/113/117
113/113/117
113/113/117
113/113/117
113/113/117
113/113/117
79324 R
80269 W
80269 W
80269 W
80269 W
80269 W
80269 W
110/110/114
111/111/114
111/111/114
111/111/114
111/111/114
111/111/114
111/111/114
For ANTI-ICE ON, decrease weight by 650 lb.
AOM-1502-016
The certified MTOW of the airplane has to be respected.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 47
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
TAKEOFF SPEEDS
The following tables present V1, VR and V2 for balanced runway and
fixed V2/VS ratio.
The tables have been generated with the settings below:
– Dry runway;
– Zero wind;
– Zero slope;
– Balanced V1;
– Minimum V2/VS;
– Maximum manual braking;
– ATTCS ON;
– Anti-ice ON/OFF;
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 48
Takeoff
REVISION 23
AOM-1502-016
– ECS ON/OFF.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-1 – FLAP 1 – V2/VS = 1.18
PRESSURE
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
AOM-1502-016
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40
-40
-40
-40
to
to
to
to
40
37
33
31
41
38
34
32
-40
-40
to
to
to
to
to
to
47
44
40
35
30
27
48
45
41
36
31
28
-40
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
52
50
48
44
40
36
31
27
21
19
↓
↓
↓
V1 VR V2
V1 VR V2
V1 VR V2
102
102
102
102
104
107
110
112
115
117
119
122
124
126
128
130
132
134
136
138
141
143
145
147
149
150
152
108
110
110
113
115
117
119
121
123
125
126
128
130
132
134
135
137
139
141
142
144
146
147
149
150
152
153
117
117
119
121
122
124
126
128
129
131
132
134
136
137
139
140
142
143
145
146
148
149
151
152
153
155
156
100
100
102
103
106
108
111
114
116
118
120
123
125
127
129
131
133
136
138
140
142
144
146
148
149
151
152
108
109
111
113
115
117
119
121
123
125
127
129
131
132
134
136
138
139
141
143
144
146
148
149
151
152
153
115
117
119
121
122
124
126
128
129
131
132
134
136
137
139
140
142
143
145
146
148
149
151
152
153
155
156
99
101
103
106
109
111
113
116
118
120
123
125
127
129
132
134
136
138
140
142
144
145
147
148
-------
108
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
139
140
142
144
145
147
148
149
-------
115
117
119
121
122
124
126
128
129
131
133
134
136
137
139
140
142
143
145
146
148
149
151
152
-------
45
41
37
32
28
22
20
-40
-40
to
to
to
to
to
to
to
to
to
↓
46
44
42
40
37
33
28
23
17
V1 VR V2
100
103
106
109
111
114
116
118
121
123
125
127
130
132
134
136
138
140
141
143
---------------
109
111
113
115
117
119
121
123
125
127
129
131
132
134
136
138
139
141
142
144
---------------
115
117
119
121
123
124
126
128
129
131
133
134
136
137
139
140
142
144
145
146
---------------
38
34
29
24
18
to
to
to
to
to
↓
38
36
34
32
30
V1 VR V2
104
106
109
111
114
117
119
121
124
126
128
130
132
134
136
-------------------------
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
-------------------------
115
117
119
121
123
124
126
128
129
131
133
134
136
137
139
-------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 49
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-1 – FLAP 2 – V2/VS = 1.17
PRESSURE
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40 to
-40 to
-40 to
40 41
37 38
33 34
-40
to
to
to
to
44
41
37
32
45
42
38
33
-40
-40
-40
-40
-40
to
to
to
to
to
to
to
to
to
52
50
48
43
39
34
30
25
21
↓
↓
↓
V1 VR V2
V1 VR V2
V1 VR V2
99
99
99
99
102
104
107
109
112
114
116
119
121
123
126
128
130
132
134
136
138
140
142
144
145
147
149
107
106
106
108
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
139
140
142
144
145
147
148
150
119
117
116
117
119
121
123
124
126
127
129
131
132
134
135
137
138
140
141
142
144
145
147
148
149
151
152
98
98
98
100
103
105
108
110
113
115
118
120
122
125
127
129
131
133
135
137
139
141
143
144
146
148
149
105
104
106
108
111
113
115
117
119
121
123
125
127
128
130
132
134
136
137
139
141
143
144
146
147
149
150
116
115
116
117
119
121
123
124
126
127
129
131
132
134
135
137
138
140
141
142
144
145
147
148
149
151
152
96
98
100
102
105
108
110
113
115
118
120
122
124
127
129
131
133
135
137
139
140
142
143
145
146
-----
104
105
107
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
139
140
142
143
145
146
148
-----
113
114
116
118
119
121
123
124
126
128
129
131
132
134
135
137
138
140
141
143
144
145
147
148
149
-----
44
40
35
31
26
22
-40
-40
-40
to
to
to
to
to
to
to
to
to
↓
46
44
42
40
36
32
27
22
16
V1 VR V2
98
100
103
106
109
111
114
116
118
121
123
125
127
129
131
133
135
137
138
140
---------------
105
107
109
111
114
116
118
120
122
124
126
127
129
131
133
135
136
138
140
141
---------------
112
114
116
118
119
121
123
124
126
128
129
131
132
134
135
137
138
140
141
143
---------------
37
33
28
23
17
to
to
to
to
to
↓
38
36
34
32
30
V1 VR V2
101
104
107
109
112
115
117
119
121
124
125
127
129
131
133
134
-----------------------
106
109
111
113
115
117
119
121
123
125
127
129
131
132
134
135
-----------------------
112
114
116
118
119
121
123
124
126
128
129
131
132
134
135
137
-----------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 50
Takeoff
REVISION 23
AOM-1502-016
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-1 – FLAP 3 – V2/VS = 1.17
PRESSURE
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
AOM-1502-016
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40 to
-40 to
-40 to
41 42
39 40
34 35
-40
-40
-40
to
to
to
to
to
to
47
44
40
35
31
27
48
45
41
36
32
28
-40
to
to
to
to
to
to
to
52
50
46
41
37
32
27
↓
↓
↓
V1 VR V2
V1 VR V2
V1 VR V2
101
101
100
100
100
99
100
102
105
108
110
113
115
117
120
122
124
126
128
130
132
134
135
137
138
140
141
107
106
105
104
104
104
106
108
110
112
114
116
118
120
122
123
125
127
129
130
132
134
135
137
138
140
141
120
119
117
116
114
114
116
118
119
121
122
124
125
127
128
129
131
132
134
135
136
138
139
140
142
143
144
98
98
98
97
97
99
102
105
107
110
112
115
117
119
121
124
126
128
129
131
133
134
136
137
-------
103
102
101
102
103
105
107
109
111
113
115
117
119
121
123
124
126
128
129
131
133
134
136
137
-------
116
114
112
112
113
115
116
118
119
121
122
124
125
127
128
129
131
132
134
135
136
138
139
140
-------
96
96
96
96
99
102
104
107
109
112
114
116
119
121
123
125
127
129
130
132
133
-------------
100
99
100
102
104
106
108
110
112
114
116
118
120
122
123
125
127
129
130
132
133
-------------
111
110
110
111
113
115
116
118
119
121
122
124
125
127
128
129
131
132
134
135
136
-------------
47
42
38
33
28
-40
-40
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
↓
48
46
44
42
40
36
31
26
21
15
V1 VR V2
93
94
96
99
102
105
107
110
112
114
117
119
121
123
125
126
128
129
131
-----------------
97
99
101
104
106
108
110
112
114
116
118
119
121
123
125
126
128
129
131
-----------------
107
108
110
111
113
115
116
118
119
121
122
124
125
127
128
130
131
132
134
-----------------
37
32
27
22
16
to
to
to
to
to
↓
38
36
34
32
30
V1 VR V2
95
98
101
104
107
109
111
113
116
118
119
121
123
124
---------------------------
99
101
104
106
108
110
112
114
116
118
119
121
123
124
---------------------------
106
108
110
111
113
115
116
118
119
121
122
124
125
127
---------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 51
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-1 – FLAP 4 – V2/VS = 1.19
PRESSURE
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40
-40
-40
-40
to
to
to
to
41
39
34
31
42
40
35
32
-40
-40
to
to
to
to
to
to
47
44
40
35
31
27
48
45
41
36
32
28
-40
to
to
to
to
to
to
to
52
50
46
41
37
32
27
47
42
38
33
28
-40
-40
to
to
to
to
to
to
to
48
46
44
39
27
30
24
↓
↓
↓
↓
V1 VR V2
V1 VR V2
V1 VR V2
V1 VR V2
98
97
97
97
97
97
97
99
101
103
105
107
109
110
112
114
116
118
119
121
124
125
127
129
-------
106
106
105
104
103
102
103
104
106
107
109
110
112
114
115
117
118
120
122
123
125
126
128
129
-------
119
118
116
115
113
112
112
113
114
115
116
118
119
120
122
123
124
126
127
128
129
131
132
133
-------
95
95
95
95
95
96
98
100
102
104
106
108
110
112
113
115
117
119
121
123
125
127
-----------
103
102
101
100
100
101
103
104
106
108
109
111
113
114
116
118
119
121
122
124
125
127
-----------
115
114
112
110
110
110
111
112
114
115
116
117
119
120
122
123
124
126
127
128
129
131
-----------
93
93
93
93
95
97
99
101
103
105
107
109
111
113
115
117
119
121
123
-----------------
100
99
98
98
100
102
103
105
107
108
110
112
113
115
117
118
120
121
123
-----------------
111
109
108
107
108
109
111
112
113
115
116
117
119
120
122
123
124
126
127
-----------------
91
90
91
94
97
99
101
103
105
106
108
110
112
115
116
118
120
---------------------
96
95
96
98
100
102
104
106
107
109
111
113
114
116
118
119
120
---------------------
106
105
105
106
108
109
110
112
113
115
116
117
119
120
122
123
124
---------------------
40
28
31
25
-40
-40
-40
to
to
to
to
to
to
to
↓
42
27
38
36
34
32
30
V1 VR V2
90
92
94
97
99
101
104
106
107
109
111
112
114
116
118
-------------------------
94
95
98
100
102
104
105
107
109
110
112
114
115
117
118
-------------------------
102
103
104
106
107
109
110
112
113
115
116
118
119
120
122
-------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 52
Takeoff
REVISION 23
AOM-1502-016
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-2 – FLAP 1 – V2/VS = 1.18
PRESSURE
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
AOM-1502-016
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40
-40
-40
-40
-40
to
to
to
to
to
38
36
32
27
24
39
37
33
28
25
-40
-40
-40
to
to
to
to
to
to
to
to
47
44
40
36
31
27
22
18
↓
↓
V1 VR V2
V1 VR V2
99
101
104
106
109
112
114
116
119
121
123
125
128
130
132
134
137
139
141
143
145
146
148
150
151
-----
108
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
139
140
142
144
145
147
148
150
151
-----
115
117
119
121
122
124
126
128
129
131
132
134
136
137
139
140
142
143
145
146
148
149
151
152
153
-----
100
103
106
109
111
114
116
118
121
123
125
128
130
132
134
137
139
140
142
144
145
-------------
109
111
113
115
117
119
121
123
125
127
129
131
132
134
136
138
139
141
142
144
146
-------------
115
117
119
121
122
124
126
128
129
131
133
134
136
137
139
140
142
143
145
146
148
-------------
48
45
41
37
32
28
23
19
-40
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
to
to
↓
52
50
48
46
41
37
32
28
23
19
14
10
V1 VR V2
103
106
109
111
114
116
119
121
123
126
128
130
132
134
136
138
140
---------------------
110
112
114
116
118
120
122
124
126
128
130
132
133
135
137
138
140
---------------------
115
117
119
121
122
124
126
128
129
131
133
134
136
137
139
140
142
---------------------
42
38
33
29
24
20
15
11
to
to
to
to
to
to
to
to
↓
44
42
40
38
35
30
25
20
V1 VR V2
106
108
111
114
116
119
121
124
126
128
130
132
134
-----------------------------
111
113
115
117
119
121
123
125
127
129
130
132
134
-----------------------------
115
117
119
121
123
124
126
128
129
131
133
134
136
-----------------------------
36
31
26
21
to
to
to
to
↓
36
34
32
30
V1 VR V2
108
111
114
117
119
122
124
126
127
-------------------------------------
112
114
116
118
120
122
124
126
128
-------------------------------------
115
117
119
121
123
124
126
128
129
-------------------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 53
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-2 – FLAP 2 – V2/VS = 1.17
PRESSURE
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40
-40
-40
-40
-40
-40
to
to
to
to
to
to
38
36
32
27
24
22
39
37
33
28
25
23
-40
-40
-40
to
to
to
to
to
to
to
to
to
46
44
40
36
31
27
22
18
16
↓
↓
V1 VR V2
V1 VR V2
97
99
102
105
108
110
112
115
117
120
122
124
126
128
130
132
134
136
138
140
141
143
145
146
-------
104
106
108
111
113
115
117
119
121
123
125
127
128
130
132
134
136
137
139
141
142
144
145
147
-------
112
114
116
118
119
121
123
124
126
127
129
131
132
134
135
137
138
140
141
142
144
145
147
148
-------
99
101
104
107
109
112
115
117
119
122
124
126
128
130
132
134
136
137
139
140
142
-------------
105
107
109
112
114
116
118
120
122
124
126
128
129
131
133
135
136
138
140
141
143
-------------
112
114
116
118
119
121
123
124
126
128
129
131
132
134
135
137
138
140
141
142
144
-------------
47
45
41
37
32
28
23
19
17
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
to
to
↓
52
50
48
46
42
37
33
28
24
19
14
10
V1 VR V2
101
104
106
109
112
114
117
119
121
123
126
128
130
131
133
135
136
---------------------
106
108
110
113
115
117
119
121
123
125
127
129
130
132
134
135
137
---------------------
112
114
116
118
119
121
123
124
126
128
129
131
132
134
135
137
138
---------------------
43
38
34
29
25
20
15
11
to
to
to
to
to
to
to
to
↓
44
42
40
38
36
33 34
28 29
23 24
V1 VR V2
104
107
110
112
115
117
119
122
123
125
127
129
131
-----------------------------
108
110
112
114
117
119
121
123
124
126
128
130
131
-----------------------------
112
114
116
118
119
121
123
124
126
128
129
131
132
-----------------------------
to
to
to
↓
34
32
30
V1 VR V2
107
110
112
115
117
119
121
123
---------------------------------------
109
111
113
116
118
120
122
123
---------------------------------------
112
114
116
118
119
121
123
124
---------------------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 54
Takeoff
REVISION 23
AOM-1502-016
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-2 – FLAP 3 – V2/VS = 1.17
PRESSURE
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
AOM-1502-016
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40 to
-40 to
-40 to
35 36
33 34
28 29
-40
-40
-40
-40
to
to
to
to
to
to
to
44
41
37
33
28
23
20
45
42
38
34
29
24
21
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
52
50
46
42
37
33
28
24
19
14
↓
↓
↓
V1 VR V2
V1 VR V2
V1 VR V2
96
96
95
96
100
103
105
108
110
113
115
117
120
122
124
125
127
129
130
132
134
-------------
99
99
100
102
105
107
109
111
113
114
116
118
120
122
124
125
127
129
130
132
134
-------------
110
109
110
111
113
114
116
118
119
121
122
124
125
127
128
129
131
132
134
135
136
-------------
94
95
96
99
102
105
107
110
112
115
117
119
121
123
125
126
128
129
131
-----------------
98
99
101
103
106
108
110
112
114
116
117
119
121
123
125
126
128
129
131
-----------------
107
108
110
111
113
115
116
118
119
121
122
124
125
127
128
129
131
132
134
-----------------
93
96
99
102
105
108
110
112
115
117
119
120
122
124
125
127
-----------------------
98
100
103
105
107
109
111
113
115
117
119
120
122
124
125
127
-----------------------
106
108
110
111
113
115
116
118
119
121
122
124
125
127
128
129
-----------------------
47
43
38
34
29
25
20
15
-40
-40
to
to
to
to
to
to
to
to
to
to
↓
48
46
44
42
40
37
33
28
23
18
V1 VR V2
98
100
103
106
108
111
113
115
116
118
120
121
-------------------------------
100
102
104
107
109
111
113
115
116
118
120
121
-------------------------------
106
108
110
111
113
115
116
118
119
121
122
124
-------------------------------
38
34
29
24
19
to
to
to
to
to
↓
38
36
34
32
30
V1 VR V2
101
104
106
108
110
112
114
-----------------------------------------
102
104
106
108
110
112
114
-----------------------------------------
106
108
110
111
113
115
116
-----------------------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 55
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
V1/VR/V2 SPEEDS
EMBRAER 190 – CF34-10E6 – T/O-2 – FLAP 4 – V2/VS = 1.19
PRESSURE
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
STATIC AIR TEMPERATURE (°C)
-40 to
-40 to
-40 to
36 37
34 35
29 30
-40
-40
to
to
to
to
to
41
39
34
30
25
↓
↓
V1 VR V2
V1 VR V2
93
93
93
93
96
98
100
102
104
106
108
110
112
113
115
118
120
122
123
-----------------
99
98
97
97
100
102
103
105
107
108
110
112
114
115
117
119
120
122
123
-----------------
110
108
107
106
108
109
111
112
113
115
116
117
119
120
122
123
124
125
127
-----------------
91
91
92
94
97
99
101
103
105
107
109
111
113
115
117
119
121
---------------------
96
95
96
98
100
102
104
106
107
109
111
113
114
116
118
119
121
---------------------
106
104
104
106
108
109
110
112
113
115
116
117
119
120
122
123
124
---------------------
42
40
35
31
26
-40
-40
-40
-40
-40
-40
-40
to
to
to
to
to
to
to
to
to
to
to
to
↓
52
50
48
45
41
36
32
27
22
17
12
10
V1 VR V2
90
92
94
97
99
101
104
106
108
109
111
113
114
116
118
-------------------------
94
95
97
100
102
104
105
107
109
110
112
113
115
116
118
-------------------------
102
103
104
106
107
109
110
112
113
115
116
117
119
120
122
-------------------------
46
42
37
33
28
23
18
13
11
to
to
to
to
to
to
to
to
to
↓
46
44
42
40
38
36
34
28 29
23 24
V1 VR V2
93
95
97
100
102
104
106
108
110
-------------------------------------
95
97
99
101
103
105
107
108
110
-------------------------------------
101
103
104
106
107
109
110
112
113
-------------------------------------
to
to
↓
32
30
V1 VR V2
95
97
100
103
-----------------------------------------------
97
99
101
103
-----------------------------------------------
101
103
104
106
-----------------------------------------------
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 56
Takeoff
REVISION 23
AOM-1502-016
ALTITUDE (ft)
-1000 →
SL →
1000 →
2000 →
3000 →
4000 →
5000 →
6000 →
7000 →
8000 →
9000 →
10000 →
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
FLAP RETRACTION SPEED SCHEDULE
During flap retraction, the next flap setting should be selected when the
F-Bug is reached.
AOM-1502-016
The F-Bug calculation algorithm is designed so as to meet minimum
safe margins to VFE and Shaker speed. A minimum margin of 20%
above the stall speed is set for the next flap.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 57
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FINAL SEGMENT SPEED
EMBRAER 190
VFS
(KIAS)
156
159
161
164
166
168
171
173
175
178
180
182
184
186
189
191
193
195
197
199
201
203
205
207
209
211
212
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 58
Takeoff
REVISION 23
AOM-1502-016
WEIGHT
(lb)
62000
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
STAB TRIM SETTING FOR TAKEOFF
EMBRAER 190
FLAPS 1
CG POSITION (% MAC)
TOW
(lb)
115000
110000
105000
100000
95000
90000
85000
80000
75000
70000
AOM-1502-016
65000
5
7
9
11
13
15
17
19
21
23
25
27
29
4
4
4
3.8
3.5
3.1
2.8
2.4
2.2
1.8
1.5
1.2
0.8
UP UP UP UP UP UP UP UP UP UP UP UP UP
4
4
3.9
3.6
3.3
2.9
2.6
2.2
2
1.6
1.3
1
0.6
UP UP UP UP UP UP UP UP UP UP UP UP UP
4
4
3.8
3.4
3.1
2.8
2.5
2.1
1.8
1.5
1.2
0.8
0.5
UP UP UP UP UP UP UP UP UP UP UP UP UP
4
3.9
3.5
3.2
2.9
2.6
2.2
1.9
1.6
1.3
0.9
0.7
0.4
UP UP UP UP UP UP UP UP UP UP UP UP UP
3.9
3.7
3.3
3
2.7
2.4
2
1.7
1.4
1.1
0.8
0.5
0.2
UP UP UP UP UP UP UP UP UP UP UP UP UP
3.8
3.5
3.2
2.8
2.5
2.2
1.9
1.6
1.3
1
0.6
0.3
0.1
UP UP UP UP UP UP UP UP UP UP UP UP UP
3.6
3.2
2.9
2.5
2.3
2
1.6
1.4
1.1
0.8
0.5
0.1
UP UP UP UP UP UP UP UP UP UP UP UP
3.3
2.9
2.5
2.2
2
1.7
1.3
1.1
0.8
0.5
0.2
0
0
0
0
0
0
0
0
0
0
UP UP UP UP UP UP UP UP UP UP UP
3
2.7
2.3
2
1.8
1.5
1.1
0.9
0.6
0.3
0.1
UP UP UP UP UP UP UP UP UP UP UP
2.7
2.4
2.1
1.8
1.5
1.2
0.8
0.6
0.3
0.1
UP UP UP UP UP UP UP UP UP UP
2.4
2.1
1.8
1.5
1.2
0.9
0.7
0.4
0.1
UP UP UP UP UP UP UP UP UP
0
0
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 59
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190
FLAPS 2
CG POSITION (% MAC)
TOW
115000
110000
105000
100000
95000
90000
85000
80000
75000
70000
65000
5
7
9
11
13
15
17
19
21
23
25
27
29
3.5
3.5
3.5
3.4
3
2.7
2.4
2.1
1.7
1.4
1
0.6
0.2
UP UP UP UP UP UP UP UP UP UP UP UP UP
3.5
3.5
3.5
3.2
2.8
2.5
2.2
1.9
1.5
1.2
0.8
0.4
UP UP UP UP UP UP UP UP UP UP UP UP
3.5
3.5
3.5
3.1
2.7
2.4
2.1
1.7
1.4
1
0.7
0.3
0
0.1
UP UP UP UP UP UP UP UP UP UP UP UP DN
3.5
3.5
3.2
2.9
2.5
2.2
1.8
1.5
1.2
0.8
0.5
0.1
0.3
UP UP UP UP UP UP UP UP UP UP UP UP DN
3.5
3.4
3
2.7
2.3
2
1.7
1.3
1
0.6
0.3
0.1
0.4
UP UP UP UP UP UP UP UP UP UP UP DN DN
3.3
3.1
2.8
2.5
2.1
1.8
1.5
1.2
0.9
0.5
0.1
0.3
0.5
UP UP UP UP UP UP UP UP UP UP UP DN DN
3.2
2.9
2.5
2.2
1.8
1.6
1.3
1
0.6
0.3
0.1
0.4
0.5
UP UP UP UP UP UP UP UP UP UP DN DN DN
2.9
2.6
2.2
1.9
1.5
1.3
1
0.7
0.3
UP UP UP UP UP UP UP UP UP
2.7
2.3
2
1.6
1.3
1.1
0.8
0.5
0.1
0
0.2
0.4
0.5
0.5
DN DN DN
0.4
0.5
0.5
UP UP UP UP UP UP UP UP UP DN DN DN DN
2.5
2
1.7
1.3
1.1
0.8
0.5
0.2
0.1
0.5
0.5
0.5
0.5
UP UP UP UP UP UP UP UP DN DN DN DN DN
2.1
1.7
1.4
1.1
0.7
0.5
0.3
UP UP UP UP UP UP UP
0
0.3
0.5
0.5
0.5
0.5
DN DN DN DN DN
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 60
Takeoff
REVISION 23
AOM-1502-016
(lb)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190
FLAPS 3
CG POSITION (% MAC)
TOW
(lb)
115000
110000
105000
100000
95000
90000
85000
80000
75000
70000
AOM-1502-016
65000
5
7
9
11
13
15
17
19
21
23
3
3
3
2.7
2.3
1.9
1.5
1.2
0.8
0.4
UP UP UP UP UP UP UP UP UP UP
3
3
2.9
2.5
2.1
1.7
1.4
1
0.6
0.2
25
0
0.2
27
29
0.4
0.8
DN DN
0.6
1
UP UP UP UP UP UP UP UP UP UP DN DN DN
3
3
2.8
2.4
2
1.6
1.3
0.9
0.5
0.1
0.3
0.7
1.1
UP UP UP UP UP UP UP UP UP UP DN DN DN
3
2.9
2.5
2.1
1.8
1.4
1
0.6
0.3
0.1
0.5
0.9
1.2
UP UP UP UP UP UP UP UP UP DN DN DN DN
2.9
2.7
2.3
1.9
1.6
1.2
0.8
0.4
0.1
0.3
0.7
1.1
1.3
UP UP UP UP UP UP UP UP UP DN DN DN DN
2.7
2.5
2.1
1.8
1.4
1
0.6
0.3
0.1
0.5
0.8
1.2
1.5
UP UP UP UP UP UP UP UP DN DN DN DN DN
2.5
2.2
1.8
1.5
1.1
0.7
0.4
UP UP UP UP UP UP UP
2.2
1.8
1.5
1.1
0.8
0.4
0.1
0
0.3
0.4
0.7
1
1.4
1.5
DN DN DN DN DN
0.7
1
1.3
1.5
1.5
UP UP UP UP UP UP UP DN DN DN DN DN DN
2
1.6
1.2
0.8
0.5
0.1
0.2
0.6
0.9
1.2
1.4
1.5
1.5
UP UP UP UP UP UP DN DN DN DN DN DN DN
1.7
1.3
0.9
0.5
0.2
0.2
0.6
0.9
1.2
1.5
1.5
1.5
1.5
UP UP UP UP UP DN DN DN DN DN DN DN DN
1.4
0.9
0.6
0.3
0.1
0.5
0.8
1.1
1.5
1.5
1.5
1.5
1.5
UP UP UP UP DN DN DN DN DN DN DN DN DN
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 61
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190
FLAPS 4
CG POSITION (% MAC)
TOW
115000
110000
105000
100000
95000
90000
85000
80000
75000
70000
65000
5
7
9
11
13
15
17
19
21
23
25
4
4
3.9
3.5
3
2.6
2.2
1.8
1.3
0.9
0.5
UP UP UP UP UP UP UP UP UP UP UP
4
4
3.7
3.3
2.8
2.4
2
1.6
1.1
0.7
0.3
27
0
0.2
29
0.5
DN
0.6
UP UP UP UP UP UP UP UP UP UP UP DN DN
4
4
3.6
3.1
2.7
2.3
1.9
1.4
1
0.6
0.1
0.3
0.7
UP UP UP UP UP UP UP UP UP UP UP DN DN
4
3.7
3.3
2.9
2.4
2.1
1.6
1.1
0.7
0.3
0.1
0.5
0.9
UP UP UP UP UP UP UP UP UP UP DN DN DN
3.9
3.5
3.1
2.7
2.2
1.9
1.4
0.9
0.5
0.1
0.3
0.7
1
UP UP UP UP UP UP UP UP UP UP DN DN DN
3.7
3.2
2.8
2.4
2
1.6
1.2
0.8
0.3
0.1
0.5
0.9
1
UP UP UP UP UP UP UP UP UP DN DN DN DN
3.3
2.9
2.5
2.1
1.7
1.3
0.9
0.4
UP UP UP UP UP UP UP UP
3
2.5
2.1
1.7
1.3
0.9
0.5
0.1
0
0.3
0.4
0.7
1
1
DN DN DN DN
0.7
1
1
1
UP UP UP UP UP UP UP UP DN DN DN DN DN
2.6
2.2
1.8
1.4
1
0.6
0.2
0.3
0.6
0.8
1
1
1
UP UP UP UP UP UP UP DN DN DN DN DN DN
2.2
1.8
1.4
1
0.6
0.2
0.2
0.6
1
1
1
1
1
UP UP UP UP UP UP DN DN DN DN DN DN DN
1.8
1.5
1.1
0.7
0.3
0.2
0.5
0.9
1
1
1
1
1
UP UP UP UP UP DN DN DN DN DN DN DN DN
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 62
Takeoff
REVISION 23
AOM-1502-016
(lb)
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
CLIMB GRADIENT - ALL ENGINES OPERATING
The climb gradient tables show the climb gradients in percentage and in
ft/NM for several weights, temperatures and pressure altitudes. These
tables are published in the following configurations:
GRADIENTS FOR TAKEOFF THRUST
The gradients were obtained for:
– A speed equal to V2 + 10 KIAS;
– FLAP 2;
– V2/VS ratio equal to the minimum of the range;
– Anti-Ice OFF;
– ECS ON;
– Landing Gear Up;
– Wings Leveled;
– Temperatures in Celsius Degrees.
AOM-1502-016
Corrections in the climb gradient for Anti-Ice ON and Flaps 4 are also
provided in the footer of each table.
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 63
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
GRADIENTS FOR CLIMB THRUST
The gradients were obtained for:
– A speed equal to VFS KIAS and 250 KIAS;
– FLAP UP;
– CLB-1 Thrust Rating;
– Anti-Ice OFF;
– ECS ON;
– Landing Gear Up;
– Wings Leveled;
– Temperatures in ISA Deviation.
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 64
Takeoff
REVISION 23
AOM-1502-016
Corrections in the climb gradient for Anti-Ice ON and CLB-2 thrust rating
are also provided in the footer of each table.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: Sea Level
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
30 and
41.2
35.4
30.7
27.0
23.9
21.3
19.1
17.2
15.5
114000
14.2
below
(2503)
(2152)
(1862)
(1639)
(1453)
(1296)
(1161)
(1044)
(944)
(860)
40.9
35.1
30.4
26.7
23.7
21.1
19.0
17.0
15.4
14.0
(2483)
(2133)
(1844)
(1623)
(1439)
(1284)
(1151)
(1035)
(936)
(853)
35
37.7
32.4
28.0
24.6
21.8
19.4
17.4
15.6
14.1
12.8
(2293)
(1970)
(1702)
(1496)
(1326)
(1181)
(1057)
(949)
(856)
(779)
35.3
30.4
26.2
23.0
20.3
18.1
16.2
14.5
13.0
11.8
(2146)
(1844)
(1591)
(1397)
(1236)
(1099)
(981)
(879)
(791)
(718)
33.2
28.6
24.6
21.6
19.0
16.9
15.0
13.4
12.0
10.8
(2018)
(1734)
(1495)
(1310)
(1155)
(1024)
(911)
(812)
(728)
(657)
40
45
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 71. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 65
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: 2000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
25 and
38.5
33.1
28.6
25.2
22.3
19.9
17.8
16.0
14.4
114000
13.1
below
(2338)
(2009)
(1736)
(1528)
(1354)
(1207)
(1080)
(970)
(876)
(797)
38.4
33.0
28.5
25.1
22.2
19.8
17.7
15.9
14.4
13.1
(2332)
(2004)
(1732)
(1524)
(1350)
(1203)
(1077)
(968)
(874)
(795)
30
36.2
31.1
26.8
23.6
20.9
18.6
16.6
14.9
13.4
12.2
(2197)
(1888)
(1630)
(1433)
(1268)
(1128)
(1008)
(903)
(814)
(739)
33.8
29.0
25.0
22.0
19.4
17.2
15.3
13.7
12.3
11.1
(2052)
(1763)
(1520)
(1334)
(1178)
(1046)
(932)
(833)
(748)
(677)
31.5
27.1
23.3
20.4
18.0
15.9
14.1
12.6
11.3
10.2
(1916)
(1645)
(1415)
(1239)
(1092)
(967)
(859)
(765)
(684)
(617)
35
40
45
29.2
25.1
21.5
18.8
16.5
14.5
12.9
11.4
10.2
9.1
(1775)
(1522)
(1306)
(1140)
(1001)
(883)
(781)
(692)
(616)
(553)
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 66
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 71. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: 4000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
20 and
36.1
31.1
26.8
23.6
20.9
18.6
16.6
14.9
13.4
114000
12.2
below
(2195)
(1887)
(1629)
(1432)
(1267)
(1127)
(1007)
(903)
(814)
(739)
36.0
31.0
26.7
23.5
20.8
18.5
16.5
14.8
13.4
12.1
(2188)
(1881)
(1624)
(1427)
(1263)
(1124)
(1004)
(900)
(811)
(736)
25
34.6
29.7
25.6
22.5
19.9
17.7
15.8
14.1
12.7
11.5
(2100)
(1805)
(1557)
(1367)
(1208)
(1074)
(958)
(857)
(771)
(698)
32.3
27.7
23.9
20.9
18.5
16.4
14.6
13.0
11.6
10.5
(1960)
(1684)
(1450)
(1271)
(1121)
(994)
(884)
(789)
(707)
(638)
30.1
25.8
22.2
19.4
17.1
15.1
13.4
11.9
10.6
9.6
(1827)
(1568)
(1347)
(1179)
(1037)
(917)
(813)
(723)
(645)
(581)
30
35
40
27.9
23.9
20.5
17.9
15.7
13.8
12.2
10.8
9.6
8.6
(1695)
(1452)
(1244)
(1085)
(951)
(838)
(740)
(654)
(581)
(520)
45
26.0
22.2
18.9
16.5
14.4
12.6
11.1
9.7
8.6
7.7
(1577)
(1348)
(1151)
(1000)
(874)
(766)
(673)
(592)
(522)
(465)
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 2. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 72. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 67
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: 6000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
15 and
33.7
29.0
25.0
21.9
19.4
17.2
15.4
13.7
12.3
114000
11.2
below
(2049)
(1761)
(1518)
(1333)
(1177)
(1046)
(932)
(834)
(750)
(679)
33.6
28.9
24.9
21.9
19.3
17.2
15.3
13.7
12.3
11.1
(2043)
(1756)
(1514)
(1329)
(1174)
(1042)
(929)
(831)
(747)
(676)
20
32.7
28.1
24.2
21.2
18.7
16.6
14.8
13.2
11.9
10.7
(1987)
(1707)
(1470)
(1289)
(1138)
(1010)
(899)
(803)
(720)
(651)
30.5
26.2
22.5
19.7
17.3
15.3
13.6
12.1
10.8
9.7
(1852)
(1590)
(1367)
(1197)
(1054)
(932)
(826)
(735)
(657)
(592)
28.5
24.4
21.0
18.3
16.1
14.2
12.5
11.1
9.9
8.9
(1730)
(1484)
(1273)
(1111)
(976)
(860)
(760)
(674)
(599)
(538)
25
30
35
26.4
22.6
19.3
16.8
14.7
13.0
11.4
10.1
8.9
8.0
(1605)
(1374)
(1175)
(1023)
(896)
(787)
(693)
(612)
(542)
(484)
40
24.4
20.9
17.8
15.4
13.5
11.8
10.3
9.1
8.0
7.1
(1484)
(1268)
(1080)
(938)
(818)
(716)
(627)
(550)
(484)
(430)
22.8
19.5
16.5
14.3
12.4
10.8
9.4
8.2
7.2
6.4
(1388)
(1183)
(1004)
(869)
(755)
(658)
(573)
(500)
(437)
(386)
45
50
A-ICE CORRECTION SUBTRACT: 0.1 % OR 8. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 68
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 76. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: 8000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
10 and
31.2
26.8
23.1
20.2
17.8
15.8
14.1
12.5
11.2
114000
10.1
below
(1896)
(1628)
(1401)
(1228)
(1083)
(960)
(853)
(761)
(682)
(616)
31.1
26.7
23.0
20.2
17.8
15.8
14.0
12.5
11.2
10.1
(1891)
(1624)
(1397)
(1225)
(1080)
(957)
(850)
(758)
(679)
(613)
15
30.7
26.3
22.7
19.8
17.5
15.5
13.8
12.3
11.0
9.9
(1864)
(1600)
(1376)
(1205)
(1062)
(940)
(835)
(744)
(666)
(601)
28.5
24.4
21.0
18.3
16.1
14.2
12.5
11.1
9.9
8.9
(1731)
(1484)
(1273)
(1112)
(976)
(861)
(762)
(675)
(601)
(540)
26.6
22.8
19.5
16.9
14.8
13.0
11.5
10.1
9.0
8.0
(1614)
(1382)
(1182)
(1029)
(901)
(792)
(697)
(615)
(545)
(487)
20
25
30
24.7
21.1
18.0
15.6
13.6
11.9
10.5
9.2
8.1
7.2
(1502)
(1284)
(1094)
(950)
(829)
(725)
(636)
(558)
(491)
(437)
35
22.8
19.4
16.5
14.3
12.4
10.8
9.4
8.2
7.2
6.4
(1384)
(1179)
(1001)
(867)
(753)
(656)
(572)
(499)
(437)
(385)
21.2
18.1
15.3
13.2
11.4
9.9
8.6
7.4
6.5
5.7
(1290)
(1097)
(928)
(800)
(692)
(600)
(520)
(451)
(392)
(343)
40
45
A-ICE CORRECTION SUBTRACT: 0.2 % OR 13. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 77. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 69
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-1
FLAP 2 – V2/VS = 1.17
Altitude: 10000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
10 and
28.7
24.6
21.2
18.5
16.3
14.4
12.7
11.3
10.1
114000
9.1
below
(1745)
(1497)
(1285)
(1124)
(988)
(873)
(774)
(687)
(613)
(551)
28.7
24.6
21.1
18.5
16.2
14.3
12.7
11.3
10.1
9.0
(1740)
(1493)
(1282)
(1121)
(986)
(870)
(771)
(685)
(611)
(549)
15
26.7
22.8
19.5
17.0
14.9
13.1
11.6
10.2
9.1
8.1
(1620)
(1387)
(1187)
(1035)
(907)
(798)
(704)
(622)
(552)
(494)
24.8
21.2
18.1
15.7
13.7
12.0
10.5
9.3
8.2
7.3
(1508)
(1288)
(1098)
(954)
(833)
(729)
(640)
(562)
(495)
(441)
23.1
19.7
16.8
14.5
12.6
11.0
9.6
8.4
7.3
6.5
(1405)
(1198)
(1017)
(881)
(765)
(667)
(582)
(508)
(445)
(393)
20
25
30
21.2
18.1
15.3
13.2
11.4
9.9
8.6
7.4
6.4
5.6
(1290)
(1096)
(927)
(799)
(691)
(599)
(519)
(450)
(391)
(343)
35
19.8
16.8
14.1
12.1
10.4
9.0
7.8
6.7
5.7
5.0
(1202)
(1019)
(857)
(736)
(634)
(546)
(470)
(405)
(348)
(303)
18.4
15.5
13.0
11.1
9.5
8.1
7.0
5.9
5.1
4.3
(1115)
(942)
(789)
(674)
(577)
(494)
(422)
(360)
(307)
(263)
40
45
A-ICE CORRECTION SUBTRACT: 1.4 % OR 86. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 70
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 79. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: Sea Level
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
30 and
34.9
30.0
25.9
22.7
20.1
17.9
16.0
14.3
12.8
114000
11.6
below
(2123)
(1824)
(1574)
(1382)
(1221)
(1086)
(969)
(867)
(780)
(707)
32.6
28.0
24.1
21.2
18.7
16.6
14.7
13.2
11.8
10.7
(1982)
(1702)
(1466)
(1285)
(1134)
(1006)
(895)
(799)
(716)
(647)
35
30.5
26.1
22.5
19.7
17.3
15.3
13.6
12.1
10.8
9.7
(1850)
(1588)
(1365)
(1195)
(1052)
(930)
(825)
(735)
(656)
(591)
28.4
24.4
20.9
18.2
16.0
14.1
12.5
11.1
9.9
8.8
(1726)
(1480)
(1269)
(1108)
(973)
(858)
(758)
(672)
(598)
(537)
26.4
22.6
19.3
16.8
14.7
12.9
11.4
10.0
8.9
7.9
(1604)
(1372)
(1173)
(1022)
(894)
(786)
(692)
(610)
(540)
(482)
40
45
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.2 % OR 75. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 71
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: 2000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
25 and
32.7
28.1
24.2
21.2
18.7
16.6
14.8
13.2
11.8
114000
10.7
below
(1985)
(1705)
(1469)
(1288)
(1137)
(1008)
(898)
(801)
(719)
(650)
31.0
26.6
22.9
20.0
17.6
15.6
13.9
12.4
11.0
10.0
(1882)
(1615)
(1389)
(1216)
(1072)
(948)
(842)
(750)
(671)
(605)
30
28.9
24.8
21.3
18.6
16.3
14.4
12.7
11.3
10.1
9.0
(1755)
(1505)
(1291)
(1128)
(991)
(875)
(774)
(686)
(611)
(549)
27.0
23.1
19.8
17.2
15.1
13.3
11.7
10.3
9.2
8.2
(1639)
(1403)
(1201)
(1046)
(917)
(806)
(711)
(628)
(557)
(498)
25.1
21.5
18.3
15.9
13.9
12.2
10.7
9.4
8.3
7.4
(1527)
(1305)
(1113)
(967)
(844)
(740)
(649)
(571)
(503)
(448)
35
40
45
23.2
19.8
16.8
14.5
12.6
11.0
9.6
8.4
7.4
6.5
(1408)
(1200)
(1020)
(883)
(767)
(669)
(584)
(510)
(446)
(394)
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 0. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 72
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 77. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: 4000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
20 and
30.5
26.2
22.5
19.7
17.3
15.3
13.6
12.1
10.8
114000
9.8
below
(1851)
(1589)
(1366)
(1196)
(1053)
(932)
(827)
(736)
(658)
(592)
29.3
25.1
21.6
18.9
16.6
14.6
13.0
11.5
10.3
9.2
(1779)
(1526)
(1310)
(1146)
(1007)
(889)
(788)
(699)
(624)
(561)
25
27.4
23.4
20.1
17.5
15.3
13.5
11.9
10.5
9.3
8.4
(1662)
(1424)
(1219)
(1063)
(932)
(820)
(724)
(640)
(568)
(508)
25.5
21.8
18.6
16.2
14.2
12.4
10.9
9.6
8.5
7.6
(1550)
(1326)
(1131)
(984)
(860)
(754)
(663)
(584)
(515)
(459)
23.8
20.3
17.3
15.0
13.0
11.4
10.0
8.7
7.7
6.8
(1446)
(1234)
(1049)
(910)
(792)
(692)
(606)
(530)
(466)
(412)
30
35
40
22.0
18.7
15.9
13.7
11.9
10.3
9.0
7.8
6.8
6.0
(1336)
(1137)
(963)
(831)
(721)
(626)
(544)
(473)
(412)
(362)
45
20.3
17.2
14.5
12.5
10.8
9.3
8.0
6.9
6.0
5.2
(1234)
(1047)
(882)
(758)
(654)
(565)
(487)
(420)
(363)
(316)
50
A-ICE CORRECTION SUBTRACT: 0.0 % OR 2. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 78. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 73
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: 6000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
15 and
28.4
24.3
20.9
18.2
16.0
14.1
12.5
11.1
9.8
114000
8.8
below
(1723)
(1478)
(1268)
(1107)
(972)
(857)
(758)
(672)
(598)
(536)
27.6
23.7
20.3
17.7
15.5
13.7
12.1
10.7
9.5
8.5
(1679)
(1439)
(1233)
(1076)
(944)
(831)
(734)
(649)
(577)
(517)
20
25.8
22.1
18.9
16.4
14.4
12.6
11.1
9.8
8.7
7.7
(1570)
(1343)
(1147)
(998)
(873)
(766)
(674)
(594)
(525)
(468)
24.1
20.6
17.5
15.2
13.2
11.6
10.1
8.9
7.8
6.9
(1463)
(1249)
(1063)
(922)
(804)
(703)
(615)
(539)
(474)
(420)
22.4
19.1
16.2
14.0
12.2
10.6
9.2
8.0
7.0
6.2
(1363)
(1161)
(984)
(851)
(738)
(642)
(559)
(487)
(425)
(374)
25
30
35
20.8
17.7
14.9
12.8
11.1
9.6
8.3
7.2
6.2
5.4
(1263)
(1072)
(905)
(779)
(673)
(582)
(504)
(435)
(377)
(329)
40
19.2
16.2
13.6
11.7
10.0
8.6
7.4
6.3
5.4
4.7
(1164)
(985)
(827)
(708)
(608)
(523)
(449)
(384)
(329)
(284)
18.3
15.4
12.9
11.0
9.4
8.1
6.9
5.9
5.0
4.3
(1110)
(937)
(784)
(670)
(573)
(490)
(419)
(356)
(303)
(260)
45
50
A-ICE CORRECTION SUBTRACT: 0.1 % OR 8. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 74
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 80. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: 8000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
10 and
26.4
22.6
19.3
16.8
14.7
12.9
11.4
10.0
8.9
114000
7.9
below
(1601)
(1370)
(1172)
(1020)
(893)
(785)
(691)
(609)
(540)
(482)
26.0
22.3
19.0
16.6
14.5
12.7
11.2
9.9
8.7
7.8
(1579)
(1352)
(1155)
(1005)
(879)
(772)
(679)
(598)
(529)
(473)
15
24.3
20.8
17.7
15.3
13.4
11.7
10.2
9.0
7.9
7.0
(1476)
(1260)
(1073)
(931)
(812)
(710)
(622)
(545)
(480)
(426)
22.7
19.3
16.4
14.2
12.3
10.7
9.3
8.1
7.1
6.3
(1377)
(1173)
(995)
(861)
(748)
(651)
(568)
(495)
(432)
(381)
21.1
17.9
15.2
13.1
11.3
9.8
8.5
7.3
6.4
5.6
(1284)
(1090)
(921)
(793)
(686)
(594)
(514)
(445)
(386)
(337)
20
25
30
19.6
16.6
14.0
12.0
10.3
8.9
7.6
6.5
5.6
4.9
(1190)
(1008)
(848)
(727)
(625)
(538)
(463)
(397)
(341)
(296)
35
18.0
15.2
12.7
10.8
9.3
7.9
6.7
5.7
4.9
4.2
(1094)
(923)
(771)
(658)
(562)
(480)
(409)
(348)
(295)
(252)
17.0
14.3
11.9
10.1
8.6
7.3
6.2
5.2
4.4
3.7
(1031)
(867)
(721)
(613)
(521)
(442)
(374)
(315)
(265)
(224)
40
45
A-ICE CORRECTION SUBTRACT: 1.5 % OR 88. ft/NM
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 80. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 75
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
TAKEOFF THRUST
EMBRAER 190 – CF34-10E6 – T/O-2
FLAP 2 – V2/VS = 1.17
Altitude: 10000 ft
Grad %
WEIGHT (lb)
(ft/NM)
SAT (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
10 and
24.3
20.8
17.7
15.3
13.4
11.7
10.3
9.0
7.9
114000
7.0
below
(1476)
(1261)
(1074)
(932)
(813)
(711)
(623)
(546)
(481)
(427)
22.8
19.4
16.5
14.2
12.4
10.8
9.4
8.2
7.2
6.3
(1383)
(1178)
(1000)
(865)
(751)
(654)
(570)
(497)
(434)
(384)
15
21.2
18.0
15.3
13.2
11.4
9.9
8.6
7.4
6.4
5.6
(1289)
(1096)
(927)
(799)
(691)
(599)
(519)
(450)
(390)
(343)
19.8
16.8
14.1
12.1
10.4
9.0
7.7
6.7
5.7
5.0
(1204)
(1020)
(858)
(737)
(634)
(546)
(470)
(404)
(348)
(302)
18.4
15.6
13.0
11.1
9.5
8.1
6.9
5.9
5.0
4.3
(1119)
(945)
(790)
(675)
(577)
(494)
(422)
(359)
(305)
(262)
20
25
30
16.8
14.2
11.8
10.0
8.5
7.2
6.1
5.1
4.3
3.6
(1022)
(860)
(714)
(606)
(515)
(437)
(369)
(310)
(260)
(220)
35
15.8
13.2
10.9
9.2
7.8
6.6
5.5
4.6
3.8
3.1
(957)
(802)
(663)
(560)
(472)
(398)
(333)
(277)
(229)
(191)
15.6
13.1
10.8
9.1
7.7
6.4
5.4
4.5
3.7
3.1
(947)
(792)
(654)
(552)
(465)
(391)
(327)
(271)
(224)
(186)
40
45
A-ICE CORRECTION SUBTRACT: 2.6 % OR 155. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 76
Takeoff
REVISION 23
AOM-1502-016
FLAP 4 CORRECTION SUBTRACT: 1.3 % OR 81. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: Sea Level
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
38.7
33.6
29.5
26.0
23.2
20.9
18.8
17.1
15.6
114000
14.3
(2353)
(2040)
(1789)
(1579)
(1407)
(1267)
(1143)
(1038)
(948)
(868)
-30
38.7
33.5
29.4
25.9
23.1
20.8
18.8
17.1
15.6
14.3
(2348)
(2036)
(1785)
(1575)
(1404)
(1265)
(1141)
(1036)
(946)
(866)
-20
38.5
33.4
29.3
25.8
23.0
20.7
18.7
17.0
15.5
14.2
(2340)
(2029)
(1779)
(1570)
(1399)
(1260)
(1137)
(1032)
(942)
(863)
38.3
33.2
29.1
25.7
22.9
20.6
18.6
16.9
15.4
14.1
(2327)
(2017)
(1769)
(1561)
(1391)
(1253)
(1130)
(1025)
(936)
(857)
38.1
33.0
28.9
25.5
22.8
20.5
18.5
16.8
15.3
14.0
(2313)
(2006)
(1758)
(1551)
(1383)
(1245)
(1123)
(1019)
(930)
(851)
-10
0
10
33.2
28.8
25.2
22.2
19.8
17.8
16.0
14.4
13.1
12.0
(2018)
(1752)
(1534)
(1351)
(1202)
(1080)
(970)
(876)
(797)
(726)
20
28.9
25.1
22.0
19.3
17.2
15.4
13.7
12.4
11.2
10.1
(1754)
(1525)
(1334)
(1173)
(1042)
(934)
(835)
(751)
(679)
(614)
30
A-ICE CORRECTION SUBTRACT: 3.1 % OR 186. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 6.8 % OR 413. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 77
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: 2000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
36.4
31.5
27.5
24.3
21.7
19.5
17.6
16.0
14.6
114000
13.3
(2208)
(1916)
(1673)
(1478)
(1320)
(1183)
(1068)
(971)
(884)
(807)
-30
36.3
31.5
27.5
24.3
21.7
19.4
17.6
16.0
14.5
13.3
(2204)
(1912)
(1670)
(1475)
(1317)
(1180)
(1066)
(969)
(882)
(805)
-20
36.2
31.4
27.4
24.2
21.6
19.4
17.5
15.9
14.5
13.2
(2197)
(1906)
(1665)
(1471)
(1313)
(1177)
(1063)
(966)
(880)
(803)
36.0
31.2
27.3
24.1
21.5
19.3
17.4
15.8
14.4
13.1
(2186)
(1896)
(1656)
(1463)
(1306)
(1170)
(1057)
(960)
(874)
(798)
35.8
31.0
27.1
24.0
21.4
19.2
17.3
15.7
14.3
13.1
(2174)
(1886)
(1647)
(1455)
(1298)
(1163)
(1051)
(955)
(869)
(793)
-10
0
10
31.3
27.1
23.7
20.9
18.6
16.6
14.9
13.5
12.3
11.1
(1899)
(1647)
(1438)
(1269)
(1130)
(1009)
(908)
(822)
(744)
(675)
20
27.2
23.6
20.6
18.1
16.1
14.3
12.8
11.6
10.4
9.4
(1653)
(1433)
(1250)
(1101)
(979)
(870)
(779)
(702)
(631)
(569)
30
A-ICE CORRECTION SUBTRACT: 3.0 % OR 181. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 78
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 6.3 % OR 385. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: 4000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
34.1
29.5
25.8
22.9
20.3
18.2
16.5
14.9
13.5
114000
12.4
(2074)
(1791)
(1568)
(1388)
(1233)
(1107)
(1001)
(905)
(823)
(751)
-30
34.1
29.4
25.8
22.8
20.3
18.2
16.5
14.9
13.5
12.3
(2070)
(1788)
(1565)
(1385)
(1231)
(1105)
(999)
(904)
(821)
(749)
-20
34.0
29.3
25.7
22.7
20.2
18.1
16.4
14.8
13.5
12.3
(2065)
(1783)
(1561)
(1382)
(1227)
(1102)
(996)
(901)
(819)
(747)
33.8
29.2
25.6
22.6
20.1
18.1
16.3
14.8
13.4
12.2
(2055)
(1774)
(1553)
(1375)
(1221)
(1096)
(991)
(897)
(815)
(743)
33.7
29.1
25.4
22.5
20.0
18.0
16.2
14.7
13.3
12.2
(2045)
(1766)
(1546)
(1368)
(1215)
(1091)
(986)
(892)
(810)
(739)
-10
0
10
29.4
25.4
22.2
19.6
17.4
15.5
14.0
12.6
11.4
10.4
(1784)
(1540)
(1347)
(1191)
(1054)
(943)
(850)
(765)
(692)
(629)
20
25.6
22.0
19.2
17.0
15.0
13.3
12.0
10.7
9.6
8.7
(1552)
(1339)
(1168)
(1031)
(909)
(810)
(726)
(650)
(584)
(527)
30
A-ICE CORRECTION SUBTRACT: 3.0 % OR 180. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 5.9 % OR 361. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 79
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: 6000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
31.8
27.5
24.2
21.3
19.0
17.0
15.3
13.9
12.6
114000
11.4
(1932)
(1673)
(1468)
(1295)
(1152)
(1035)
(931)
(841)
(765)
(694)
-30
31.7
27.5
24.1
21.3
18.9
17.0
15.3
13.8
12.6
11.4
(1928)
(1669)
(1465)
(1292)
(1150)
(1033)
(929)
(840)
(763)
(692)
-20
31.7
27.4
24.1
21.2
18.9
17.0
15.3
13.8
12.5
11.4
(1923)
(1665)
(1461)
(1289)
(1147)
(1030)
(926)
(838)
(761)
(691)
31.5
27.3
24.0
21.1
18.8
16.9
15.2
13.7
12.5
11.3
(1915)
(1658)
(1455)
(1283)
(1142)
(1026)
(922)
(834)
(758)
(687)
31.4
27.2
23.8
21.0
18.7
16.8
15.1
13.7
12.4
11.3
(1907)
(1651)
(1448)
(1277)
(1136)
(1021)
(918)
(830)
(754)
(684)
-10
0
10
27.4
23.7
20.7
18.2
16.2
14.5
13.0
11.7
10.6
9.6
(1663)
(1439)
(1260)
(1108)
(984)
(881)
(789)
(711)
(643)
(580)
20
23.8
20.6
18.0
15.8
13.9
12.4
11.1
9.9
8.9
8.0
(1448)
(1251)
(1093)
(957)
(845)
(754)
(671)
(601)
(540)
(483)
30
A-ICE CORRECTION SUBTRACT: 2.9 % OR 175. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 80
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 5.4 % OR 330. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: 8000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
29.8
25.9
22.7
20.0
17.8
15.9
14.3
12.9
11.7
114000
10.6
(1812)
(1573)
(1376)
(1214)
(1081)
(965)
(868)
(784)
(708)
(642)
-30
29.8
25.9
22.6
20.0
17.8
15.9
14.3
12.9
11.6
10.5
(1809)
(1570)
(1374)
(1212)
(1079)
(964)
(867)
(783)
(706)
(640)
-20
29.7
25.8
22.6
19.9
17.7
15.8
14.2
12.9
11.6
10.5
(1804)
(1567)
(1370)
(1209)
(1077)
(961)
(865)
(781)
(704)
(638)
29.6
25.7
22.5
19.8
17.7
15.8
14.2
12.8
11.6
10.5
(1798)
(1561)
(1365)
(1205)
(1073)
(958)
(861)
(777)
(702)
(635)
29.5
25.6
22.4
19.8
17.6
15.7
14.1
12.7
11.5
10.4
(1791)
(1555)
(1360)
(1200)
(1068)
(954)
(858)
(774)
(698)
(632)
-10
0
10
25.5
22.1
19.3
17.0
15.1
13.4
12.1
10.8
9.7
8.8
(1550)
(1343)
(1171)
(1032)
(917)
(816)
(732)
(658)
(591)
(533)
20
22.2
19.2
16.7
14.6
13.0
11.5
10.2
9.1
8.1
7.3
(1349)
(1167)
(1014)
(889)
(786)
(696)
(620)
(554)
(493)
(441)
30
A-ICE CORRECTION SUBTRACT: 2.9 % OR 177. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 5.2 % OR 313. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 81
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
VFS
Altitude: 10000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
27.7
24.0
21.0
18.6
16.5
14.7
13.2
11.9
10.7
114000
9.7
(1685)
(1460)
(1277)
(1128)
(999)
(893)
(801)
(721)
(651)
(589)
-30
27.7
24.0
21.0
18.5
16.4
14.7
13.2
11.8
10.7
9.7
(1681)
(1457)
(1275)
(1126)
(997)
(891)
(800)
(719)
(649)
(587)
-20
27.6
23.9
20.9
18.5
16.4
14.6
13.1
11.8
10.7
9.6
(1677)
(1453)
(1272)
(1124)
(995)
(889)
(798)
(717)
(647)
(585)
27.5
23.9
20.9
18.4
16.3
14.6
13.1
11.8
10.6
9.6
(1672)
(1449)
(1268)
(1120)
(991)
(886)
(794)
(714)
(644)
(583)
27.4
23.8
20.8
18.4
16.3
14.5
13.0
11.7
10.6
9.6
(1667)
(1444)
(1263)
(1116)
(988)
(883)
(791)
(712)
(642)
(580)
-10
0
10
23.8
20.6
18.0
15.8
14.0
12.4
11.1
10.0
8.9
8.0
(1446)
(1249)
(1091)
(961)
(849)
(756)
(675)
(604)
(541)
(486)
20
20.7
17.8
15.5
13.6
11.9
10.6
9.4
8.3
7.4
6.6
(1256)
(1082)
(941)
(826)
(725)
(643)
(570)
(506)
(449)
(399)
30
A-ICE CORRECTION SUBTRACT: 2.8 % OR 169. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 82
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 4.6 % OR 282. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: Sea Level
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
28.8
25.9
23.4
21.3
19.5
17.9
16.5
15.3
14.2
114000
13.2
(1752)
(1571)
(1420)
(1291)
(1182)
(1088)
(1002)
(927)
(861)
(800)
-30
28.8
25.8
23.3
21.2
19.4
17.9
16.5
15.2
14.1
13.1
(1747)
(1567)
(1416)
(1288)
(1179)
(1085)
(1000)
(925)
(858)
(798)
-20
28.7
25.7
23.2
21.1
19.3
17.8
16.4
15.2
14.1
13.1
(1741)
(1561)
(1411)
(1283)
(1174)
(1081)
(996)
(921)
(855)
(795)
28.5
25.5
23.1
21.0
19.2
17.7
16.3
15.1
14.0
13.0
(1729)
(1551)
(1401)
(1274)
(1166)
(1074)
(989)
(915)
(849)
(789)
28.3
25.4
22.9
20.8
19.1
17.6
16.2
15.0
13.9
12.9
(1717)
(1541)
(1392)
(1266)
(1159)
(1067)
(983)
(909)
(843)
(784)
-10
0
10
24.1
21.7
19.6
17.8
16.3
15.0
13.8
12.7
11.7
10.9
(1466)
(1316)
(1189)
(1080)
(988)
(909)
(835)
(771)
(713)
(661)
20
20.6
18.5
16.7
15.1
13.8
12.7
11.6
10.7
9.9
9.1
(1249)
(1122)
(1013)
(919)
(839)
(770)
(706)
(650)
(600)
(554)
30
A-ICE CORRECTION SUBTRACT: 2.4 % OR 146. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 5.4 % OR 329. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 83
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: 2000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
26.8
24.1
21.7
19.8
18.1
16.6
15.3
14.2
13.1
114000
12.2
(1630)
(1462)
(1320)
(1201)
(1101)
(1010)
(931)
(861)
(798)
(740)
-30
26.8
24.0
21.7
19.7
18.1
16.6
15.3
14.2
13.1
12.2
(1627)
(1459)
(1317)
(1199)
(1098)
(1008)
(929)
(860)
(796)
(738)
-20
26.7
23.9
21.6
19.7
18.0
16.5
15.2
14.1
13.1
12.1
(1621)
(1454)
(1313)
(1195)
(1095)
(1004)
(926)
(857)
(793)
(736)
26.5
23.8
21.5
19.6
17.9
16.4
15.1
14.0
13.0
12.0
(1611)
(1445)
(1305)
(1187)
(1088)
(998)
(920)
(851)
(788)
(731)
26.4
23.6
21.3
19.4
17.8
16.3
15.1
13.9
12.9
12.0
(1601)
(1436)
(1297)
(1180)
(1081)
(992)
(914)
(846)
(783)
(726)
-10
0
10
22.5
20.2
18.2
16.6
15.2
13.9
12.8
11.8
10.9
10.1
(1367)
(1226)
(1107)
(1007)
(921)
(844)
(776)
(716)
(661)
(611)
20
19.2
17.2
15.5
14.1
12.9
11.7
10.8
9.9
9.1
8.4
(1164)
(1043)
(941)
(855)
(781)
(713)
(654)
(602)
(554)
(509)
30
A-ICE CORRECTION SUBTRACT: 2.4 % OR 144. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 84
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 5.0 % OR 306. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: 4000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
25.0
22.3
20.2
18.4
16.8
15.4
14.2
13.1
12.2
114000
11.3
(1516)
(1357)
(1227)
(1118)
(1021)
(937)
(864)
(798)
(738)
(685)
-30
24.9
22.3
20.2
18.4
16.8
15.4
14.2
13.1
12.1
11.2
(1512)
(1354)
(1224)
(1115)
(1018)
(935)
(862)
(796)
(736)
(683)
-20
24.8
22.2
20.1
18.3
16.7
15.3
14.2
13.1
12.1
11.2
(1508)
(1350)
(1221)
(1112)
(1015)
(932)
(860)
(793)
(734)
(681)
24.7
22.1
20.0
18.2
16.6
15.3
14.1
13.0
12.0
11.1
(1500)
(1343)
(1214)
(1106)
(1010)
(927)
(855)
(789)
(730)
(677)
24.5
22.0
19.9
18.1
16.5
15.2
14.0
12.9
11.9
11.1
(1491)
(1335)
(1207)
(1100)
(1004)
(922)
(850)
(784)
(725)
(673)
-10
0
10
21.0
18.8
17.0
15.4
14.1
12.9
11.9
10.9
10.1
9.3
(1273)
(1140)
(1031)
(938)
(855)
(783)
(721)
(663)
(611)
(565)
20
17.8
15.9
14.4
13.1
11.9
10.8
10.0
9.1
8.4
7.7
(1080)
(966)
(872)
(793)
(721)
(659)
(605)
(554)
(508)
(468)
30
A-ICE CORRECTION SUBTRACT: 2.3 % OR 142. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 4.7 % OR 283. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 85
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: 6000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
23.2
20.8
18.8
17.1
15.6
14.3
13.2
12.2
11.3
114000
10.4
(1407)
(1262)
(1142)
(1037)
(948)
(871)
(800)
(738)
(683)
(632)
-30
23.1
20.7
18.8
17.1
15.6
14.3
13.2
12.1
11.2
10.4
(1405)
(1260)
(1140)
(1036)
(946)
(870)
(799)
(737)
(682)
(631)
-20
23.1
20.7
18.7
17.0
15.5
14.3
13.1
12.1
11.2
10.4
(1401)
(1256)
(1137)
(1033)
(944)
(867)
(797)
(735)
(680)
(629)
23.0
20.6
18.6
16.9
15.5
14.2
13.1
12.1
11.2
10.3
(1395)
(1251)
(1132)
(1028)
(939)
(863)
(793)
(732)
(677)
(626)
22.9
20.5
18.5
16.8
15.4
14.1
13.0
12.0
11.1
10.3
(1388)
(1245)
(1126)
(1023)
(935)
(859)
(789)
(728)
(673)
(622)
-10
0
10
19.5
17.5
15.8
14.3
13.1
12.0
11.0
10.1
9.3
8.6
(1184)
(1062)
(960)
(871)
(794)
(728)
(667)
(614)
(566)
(521)
20
16.5
14.8
13.3
12.1
11.0
10.0
9.2
8.4
7.7
7.0
(1000)
(896)
(809)
(732)
(666)
(609)
(556)
(509)
(467)
(427)
30
A-ICE CORRECTION SUBTRACT: 2.2 % OR 134. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 86
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 4.3 % OR 262. ft/NM
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: 8000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
21.5
19.3
17.4
15.8
14.5
13.3
12.2
11.2
10.4
114000
9.6
(1306)
(1173)
(1059)
(962)
(880)
(805)
(741)
(683)
(630)
(582)
-30
21.5
19.3
17.4
15.8
14.4
13.2
12.2
11.2
10.3
9.6
(1303)
(1170)
(1056)
(960)
(877)
(803)
(739)
(681)
(628)
(581)
-20
21.4
19.2
17.3
15.8
14.4
13.2
12.1
11.2
10.3
9.5
(1300)
(1167)
(1053)
(957)
(875)
(801)
(737)
(679)
(626)
(579)
21.3
19.1
17.3
15.7
14.3
13.1
12.1
11.1
10.3
9.5
(1294)
(1162)
(1049)
(953)
(871)
(798)
(733)
(676)
(623)
(576)
21.2
19.0
17.2
15.6
14.3
13.1
12.0
11.1
10.2
9.4
(1288)
(1156)
(1044)
(949)
(867)
(794)
(730)
(673)
(620)
(573)
-10
0
10
18.1
16.2
14.6
13.3
12.1
11.1
10.2
9.3
8.6
7.9
(1099)
(986)
(889)
(807)
(736)
(672)
(616)
(566)
(520)
(479)
20
15.2
13.7
12.3
11.1
10.1
9.2
8.4
7.7
7.0
6.4
(925)
(829)
(746)
(676)
(615)
(559)
(511)
(467)
(426)
(390)
30
A-ICE CORRECTION SUBTRACT: 2.1 % OR 127. ft/NM
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 4.0 % OR 242. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Takeoff
Page 87
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CLIMB GRADIENT – ALL ENGINES OPERATING
CLIMB THRUST
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1 – CLB-1
250 KIAS
Altitude: 10000 ft
Grad %
WEIGHT (lb)
(ft/NM)
ISA (°C)
60000
66000
72000
78000
84000
90000
96000
102000
108000
20.0
17.9
16.2
14.7
13.4
12.3
11.3
10.4
9.6
114000
8.8
(1215)
(1089)
(983)
(894)
(815)
(747)
(686)
(631)
(582)
(537)
-30
19.9
17.9
16.1
14.7
13.4
12.3
11.3
10.4
9.6
8.8
(1212)
(1086)
(981)
(892)
(813)
(745)
(684)
(629)
(580)
(535)
-20
19.9
17.8
16.1
14.6
13.3
12.2
11.2
10.3
9.5
8.8
(1208)
(1083)
(978)
(889)
(810)
(743)
(682)
(627)
(578)
(534)
19.8
17.8
16.0
14.6
13.3
12.2
11.2
10.3
9.5
8.7
(1203)
(1078)
(974)
(885)
(807)
(739)
(679)
(624)
(576)
(531)
19.7
17.7
16.0
14.5
13.2
12.1
11.1
10.2
9.4
8.7
(1198)
(1074)
(969)
(881)
(803)
(736)
(675)
(621)
(573)
(528)
-10
0
10
16.7
15.0
13.5
12.3
11.2
10.2
9.3
8.5
7.8
7.2
(1017)
(911)
(821)
(745)
(677)
(619)
(566)
(519)
(476)
(437)
20
14.1
12.6
11.3
10.2
9.3
8.4
7.7
7.0
6.4
5.8
(853)
(763)
(686)
(621)
(563)
(512)
(466)
(425)
(388)
(353)
30
A-ICE CORRECTION SUBTRACT: 2.1 % OR 128. ft/NM
5-20
Copyright © by Embraer. Refer to cover page for details.
Page 88
Takeoff
REVISION 23
AOM-1502-016
CLB-2 CORRECTION SUBTRACT: 3.8 % OR 229. ft/NM
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
SUPPLEMENTARY TAKEOFF INFORMATION
TURN ANALYSIS
The method below presents the criteria for transforming a takeoff flight
path with turns into an equivalent straight flight path. This allows the use
of runway analysis software to determine obstacle clearance.
The method to be used herein converts an actual flight path with turns
and wind effects into an equivalent straight flight path with still air.
This straight flight path will be determined in terms of increments on the
height of the existing obstacle, and is taken into account to ensure
obstacle clearance. The performance calculation must be made with the
equivalent straight flight path, as per the AFM.
OPERATIONAL LIMITATIONS
Maximum bank angle: Both Engines Operative: 25° at V2 + 10
One Engine Inoperative: 15° at V2
One Engine Inoperative: 20° at V2 + 5 (*)
One Engine Inoperative: 25° at V2 + 10 (*)
AOM-1502-016
(*) According to FAR 121.189(f), the maximum bank angle with one
engine inoperative is 15°.
According to JAR OPS 1.495 (c), for bank angles greater than
15°, the airplane’s net path must clear all obstacles after the
banked turn by 50 ft instead of 35 ft.
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
EQUIVALENT STRAIGHT FLIGHT PATH DETERMINATION
The equivalent straight flight path (zero wind) to be used in the
performance calculation should be determined as follows:
1 - OBSTACLE INCREMENT IN A STEADY TURN
During a steady turn, the climb gradient deteriorates. To compensate
for this, an increment of the actual obstacle height must be obtained
as a function of the gradient loss due to a steady turn and the
turning distance flown to the obstacle:
∆H = DT x GL + Aw
where:
∆H = obstacle height increment.
DT = distance flown along the turning flight to the obstacle.
GL = gradient loss (obtained from the Turn performance
calculation part in the ECAFM).
Aw = allowance to compensate the lower wing tip height due to
the bank angle.
and
Aw = [Wing span x sin (bank angle)]/2
The equivalent obstacle height to be used in an obstacle clearance
calculation is:
HE = HA + ∆H1 + ∆H2 + ......+ ∆Hn
where:
HE = equivalent obstacle height.
HA = actual obstacle height.
∆H1,2,n = height increments for each distance portion flown in
the turn to the obstacle.
2 - WIND EFFECT ON THE FLIGHT PATH
Considering the drift compensation, the straight portions of the
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 2
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
2.1 - STRAIGHT FLIGHT PORTIONS
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
flight path may be corrected to a still air equivalent distance as
follows:
GD x TAS
GS
SAD =
where:
SAD = still air equivalent distance.
GD = actual ground distance.
TAS = airplane true airspeed (obtained from the radius of turns
and speed conversion chart).
GS = airplane ground speed.
For straight flight:
GS = TAS + (Vw x cosα)
where:
Vw = wind speed.
α = angle between flight direction and wind direction.
Remarks:
Vw x cosα is negative for a head wind component.
Vw x cosα is positive for a tailwind component.
2.2 - TURNING FLIGHT PORTIONS
Two effects must be taken into account:
2.2.1 -
Distance Flown Compensation:
The wind takes the same effect as mentioned in item 2.1.
SAD =
GD x TAS
GS
AOM-1502-016
For turning flight:
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
GS =
Dm
∆t
where:
Dm = distance flown along the actual trajectory.
∆t = elapsed time in turning flight.
2.2.2 -
Trajectory Displacement:
The trajectory is displaced in the wind component direction
proportionally to time.
The displacement may be calculated by:
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 4
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
∆D = ∆t x VW.
∆D = trajectory displacement in the wind component
direction.
∆t = elapsed time in turning flight (obtained from the
Horizontal Distance and Time to Complete chart).
VW = wind speed.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
STILL AIR TRAJECTORY (WITHOUT WIND)
D3
ACTUAL TRAJECTORY (WITH WIND)
D2
D1
AOM-1502-016
Vw
EM170AOM050012A.DGN
t2
t3
t1
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE CHARTS PRESENTATION
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 6
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
All necessary information is provided in the ECAFM.
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
AIRCRAFT CLASSIFICATION NUMBER - ACN
The Pavement Classification Number (PCN) reported shall indicate that
an airplane with ACN equal to or less than the reported PCN can
operate on that pavement.
PCN - PAVEMENT CLASSIFICATION NUMBER
Example: PCN 50 / F / A / X / T
| | | |
1 2 3 4
1) Type of pavement:
R = Rigid (concrete);
F = Flexible (asphalt);
2) Pavement sub-grade strength category:
A = High,
B = Medium,
C = Low,
D = Ultra-low.
3) Maximum tire pressure authorized for the pavement:
W = High, no limit;
X = Medium (up to 217 psi);
Y = Low (up to 145 psi);
Z = Very low (up to 73 psi).
4) Pavement evaluation method:
T = Technical evaluation;
U = By experience of airplane actually using the pavement.
OVERLOAD OPERATIONS
AOM-1502-016
Individual airport authorities are free to decide on their own criteria for
permitting overload operations as long as pavements remain safe for
use by airplanes.
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
!EMBRAER 190 LR Model
35
34
EMBRAER 190 LR − ACN RIGID PAVEMENT
33
32
31
TIRE SIZE: H41 x 16−20 22PR
TIRE PRESSURE: 11.04 kgf/cm² (157 psi) (UNLOADED)
NOTES:
30
29
AIRCRAFT CLASSIFICATION NUMBER − ACN
28
D (K = 20 MN/m³)
27
C (K = 40 MN/m³)
B (K = 80 MN/m³)
26
A (K = 150 MN/m³)
25
24
23
22
21
20
19
18
17
16
15
14
13
12
10
28000 30000 32000
62000
67000
34000 36000 38000 40000 42000 44000 46000 48000 50000 52000
WEIGHT − kg
72000
77000
82000
87000 92000
WEIGHT − lb
97000
102000 107000 112000 117000
EM170AOM050034C.DGN
11
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 8
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
"
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
!EMBRAER 190 LR Model
35
34
EMBRAER 190 LR − ACN FLEXIBLE PAVEMENT
33
32
NOTES:
31
TIRE SIZE: H41 x 16−20 22PR
TIRE PRESSURE: 10.04 kgf/cm² (157 psi) (UNLOADED)
30
29
28
D (CBR = 3%)
27
C (CBR = 6%)
AIRCRAFT CLASSIFICATION NUMBER − ACN
B (CBR = 10%)
26
A (CBR = 15%)
25
24
23
22
21
20
19
18
17
16
15
14
13
11
10
28000 30000 32000 34000 36000 38000 40000 42000 44000 46000
WEIGHT − kg
62000
67000
72000
77000
82000
87000 92000
WEIGHT − lb
97000
48000 50000 52000
102000 107000 112000 117000
EM170AOM050032C.DGN
12
AOM-1502-016
"
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 9
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
!EMBRAER 190 AR Model
35
34
EMBRAER 190 AR − ACN RIGID PAVEMENT
33
32
31
30
NOTES:
29
TIRE SIZE: H41 x 16−20
TIRE PRESSURE: 10.7 kgf/cm² (151 psi)
28
27
AIRCRAFT CLASSIFICATION NUMBER−ACN
26
D (k=20 MN/m³)
25
C (k=40 MN/m³)
B (k=80 MN/m³)
24
A (k=150 MN/m³)
23
22
21
20
19
18
17
16
15
14
13
12
10
60000
30000
65000
32000
70000
34000
75000
36000
80000
38000 40000
WEIGHT (kg)
85000
90000
42000
44000
95000
100000 105000 110000 115000
WEIGHT (lb)
46000
48000
50000
"
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 10
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
28000
EM170AOM050035B.DGN
11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
!EMBRAER 190 AR Model
35
34
EMBRAER 190 AR − ACN FLEXIBLE PAVEMENT
33
32
NOTES:
31
TIRE SIZE: H41 x 16−20
TIRE PRESSURE: 10.7 kgf/cm² (151 psi)
30
29
28
D (CBR=3%)
C (CBR=6%)
27
AIRCRAFT CLASSIFICATION NUMBER−ACN
B (CBR=10%)
A (CBR=15%)
26
25
24
23
22
21
20
19
18
17
16
15
14
13
12
10
28000
30000
32000
34000
36000
38000
40000
42000
44000
46000
48000
50000
WEIGHT (kg)
60000
65000
70000
75000
80000
85000
90000
95000
100000 105000 110000 115000
WEIGHT (lb)
EM170AOM050036B.DGN
11
AOM-1502-016
"
5-25
Copyright © by Embraer. Refer to cover page for details.
REVISION 22
Supplementary Takeoff
Information
Page 11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-25
Copyright © by Embraer. Refer to cover page for details.
Page 12
Supplementary Takeoff
Information
REVISION 22
AOM-1502-016
INTENTIONALLY BLANK
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH AND LANDING SPEEDS
EMBRAER 190
CF34-10E5/10E5A1/10E6/10E6A1
AOM-1502-016
Without Ice Accretion
WEIGHT
VREF
FLAP 5
VAC
FLAP 2
(lb)
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
(KIAS)
108
109
111
113
114
116
118
119
121
122
124
125
126
128
129
131
132
134
135
136
138
139
140
142
143
144
(KIAS)
132
134
136
138
140
142
144
146
148
150
151
153
155
157
159
160
162
164
165
167
169
170
172
173
175
177
VREF
FLAP
FULL
(KIAS)
104
104
104
106
107
109
110
112
113
115
116
117
119
120
121
123
124
125
127
128
129
130
132
133
134
135
VAC
FLAP 4
VFS
(KIAS)
117
119
121
122
124
126
128
129
131
132
134
136
137
139
140
142
143
145
146
148
149
151
152
154
155
156
(KIAS)
159
161
164
166
168
171
173
175
178
180
182
184
186
189
191
193
195
197
199
201
203
205
207
209
211
212
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190
CF34-10E5/10E5A1/10E6/10E6A1
WEIGHT
VREF
FLAP 5
VAC
FLAP 2
(lb)
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
(KIAS)
116
118
120
121
123
125
127
128
130
131
133
135
136
138
139
141
142
144
145
147
148
150
151
152
154
155
(KIAS)
132
134
136
138
140
142
144
146
148
150
151
153
155
157
159
160
162
164
165
167
169
170
172
173
175
177
VREF
FLAP
FULL
(KIAS)
107
109
110
112
114
115
117
118
120
121
123
124
126
127
129
130
131
133
134
135
137
138
139
141
142
143
VAC
FLAP 4
VFS
(KIAS)
117
119
121
122
124
126
128
129
131
132
134
136
137
139
140
142
143
145
146
148
149
151
152
154
155
156
(KIAS)
159
161
164
166
168
171
173
175
178
180
182
184
186
189
191
193
195
197
199
201
203
205
207
209
211
212
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 2
Approach
REVISION 23
AOM-1502-016
With Ice Accretion
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
EMBRAER 190
CF34-10E5/10E5A1/10E6/10E6A1
CAT II OPERATION - With or Without Ice Accretion
WEIGHT
(lb)
64000
66000
68000
70000
72000
74000
76000
78000
80000
82000
84000
86000
88000
90000
92000
94000
96000
98000
100000
102000
104000
106000
108000
110000
112000
114000
VREF
FLAP 5
(KIAS)
116
118
120
121
123
125
127
128
130
131
133
135
136
138
139
141
142
144
145
147
148
150
151
152
154
155
VAC
FLAP 2
(KIAS)
132
134
136
138
140
142
144
146
148
150
151
153
155
157
159
160
162
164
165
167
169
170
172
173
175
177
VFS
(KIAS)
159
161
164
166
168
171
173
175
178
180
182
184
186
189
191
193
195
197
199
201
203
205
207
209
211
212
AOM-1502-016
NOTE: The approach climb, landing climb and reference speeds for
autoland operation are equal to the speeds presented for CAT II
operation.
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAPS MANEUVERING SPEEDS
SPEED
(KIAS)
210
180
160
150
140
140
130
FLAP
UP
1
2
3
4
5
FULL
NOTE: The Flap Maneuvering Speeds provide at least 1.3 g margin
over stick shaker speed, which is equivalent to a shaker-free
bank angle of 40°. These speeds ensure such margin for all
weights up to the Maximum Landing Weight, with or without ice
accretion.
The speeds above may be used as reference for flaps extension
and maneuvering. For flaps retraction refer to the Flap
Retraction Speed Schedule presented on section 5-20 (Takeoff).
The green dot on the PFD provides at least 1.3 g margin over
stick shaker speed adjusted for the current airplane weight, thus
it can also be used as the Flap Maneuvering Speed.
!190 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium
II
For airplanes equipped with Load version previous than Load 25.5.0.1,
the green dot does not account for ice accretion. Therefore when flying
in icing conditions (EICAS message STALL PROT ICE SPEED
displayed) it is recommended to add 10 kt to the green dot.
"
!190 models, MAU Load 25.5.0.1 and on
For airplanes equipped with Load version 25.5.0.1 and on, the green dot
accounts for ice accretion.
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 4
Approach
REVISION 23
AOM-1502-016
"
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
APPROACH CLIMB GRADIENT
The Approach Climb Gradient tables show the gradients as function of
temperature (°C) and weight (lb).
The associated conditions are:
– CAT I Operation;
– Approach Flaps: 2 or 4;
– Gear UP;
– Anti-Ice OFF without Ice Accretion or Wing and Engine Anti-ice ON
with Ice Accretion;
– ECS OFF;
AOM-1502-016
– One Engine Inoperative.
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: Sea Level
ANTI-ICE OFF
WEIGHT (lb)
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
48
50
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
15.25
15.23
15.22
15.20
15.17
15.15
15.12
15.10
15.08
15.05
15.03
15.00
14.98
14.96
14.93
14.91
14.84
14.78
14.48
13.96
13.44
13.02
12.61
12.23
11.86
11.50
13.53
13.52
13.50
13.48
13.46
13.44
13.42
13.39
13.37
13.35
13.33
13.31
13.28
13.26
13.24
13.22
13.16
13.09
12.82
12.34
11.86
11.47
11.09
10.73
10.39
10.05
12.09
12.07
12.06
12.04
12.02
12.00
11.98
11.96
11.94
11.92
11.90
11.88
11.86
11.84
11.82
11.80
11.74
11.68
11.43
10.98
10.53
10.17
9.82
9.48
9.15
8.83
10.85
10.84
10.83
10.81
10.79
10.77
10.75
10.73
10.71
10.69
10.67
10.65
10.63
10.61
10.59
10.57
10.52
10.47
10.24
9.82
9.40
9.06
8.73
8.41
8.10
7.79
9.75
9.74
9.73
9.71
9.69
9.67
9.65
9.63
9.61
9.59
9.58
9.56
9.54
9.52
9.50
9.48
9.44
9.40
9.18
8.78
8.39
8.08
7.76
7.45
7.16
6.87
8.76
8.75
8.74
8.73
8.71
8.69
8.67
8.65
8.63
8.61
8.60
8.58
8.56
8.54
8.52
8.50
8.47
8.43
8.22
7.86
7.49
7.19
6.89
6.60
6.32
6.04
7.87
7.86
7.85
7.84
7.82
7.80
7.78
7.77
7.75
7.73
7.71
7.70
7.68
7.66
7.64
7.63
7.60
7.56
7.37
7.02
6.67
6.39
6.11
5.83
5.56
5.29
7.06
7.05
7.04
7.03
7.01
7.00
6.98
6.96
6.95
6.93
6.91
6.90
6.88
6.86
6.85
6.83
6.80
6.77
6.59
6.26
5.94
5.67
5.40
5.14
4.88
4.61
6.33
6.32
6.31
6.30
6.28
6.27
6.25
6.24
6.22
6.20
6.19
6.17
6.16
6.14
6.12
6.11
6.08
6.05
5.88
5.57
5.27
5.01
4.76
4.50
4.25
4.00
5.66
5.65
5.64
5.63
5.62
5.60
5.59
5.57
5.56
5.54
5.53
5.51
5.50
5.48
5.47
5.45
5.43
5.40
5.24
4.94
4.65
4.41
4.17
3.92
3.68
3.44
104000
5.05
5.04
5.03
5.02
5.00
4.99
4.98
4.96
4.95
4.93
4.92
4.90
4.89
4.88
4.86
4.85
4.83
4.80
4.64
4.37
4.09
3.86
3.62
3.39
3.15
2.92
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 6
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: Sea Level
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.84
12.83
12.82
12.80
12.79
12.77
12.76
12.74
12.71
12.69
11.15
11.14
11.13
11.11
11.10
11.09
11.07
11.06
11.03
11.00
9.73
9.72
9.71
9.69
9.68
9.67
9.66
9.64
9.62
9.59
8.51
8.50
8.49
8.48
8.46
8.45
8.44
8.42
8.40
8.38
7.42
7.41
7.40
7.39
7.38
7.37
7.36
7.34
7.32
7.30
6.45
6.43
6.42
6.41
6.40
6.39
6.38
6.37
6.35
6.33
5.56
5.55
5.55
5.54
5.53
5.52
5.51
5.49
5.47
5.45
4.77
4.76
4.75
4.74
4.73
4.72
4.71
4.70
4.68
4.66
4.04
4.03
4.02
4.02
4.01
4.00
3.99
3.98
3.96
3.94
3.38
3.37
3.36
3.35
3.35
3.34
3.33
3.32
3.30
3.29
104000
2.77
2.77
2.76
2.75
2.74
2.73
2.73
2.71
2.70
2.68
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 1000 ft
ANTI-ICE OFF
WEIGHT (lb)
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
48
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
14.60
14.59
14.57
14.55
14.52
14.50
14.48
14.46
14.43
14.41
14.39
14.36
14.34
14.32
14.30
14.27
14.25
13.99
13.49
12.99
12.58
12.17
11.78
11.42
11.05
12.94
12.93
12.91
12.89
12.87
12.85
12.83
12.80
12.78
12.76
12.74
12.72
12.70
12.68
12.66
12.64
12.61
12.38
11.91
11.45
11.06
10.68
10.32
9.98
9.63
11.55
11.53
11.52
11.50
11.48
11.46
11.44
11.42
11.40
11.38
11.36
11.34
11.32
11.30
11.28
11.26
11.24
11.02
10.59
10.15
9.80
9.44
9.10
8.77
8.45
10.35
10.33
10.32
10.30
10.28
10.27
10.25
10.23
10.21
10.19
10.18
10.16
10.14
10.12
10.10
10.08
10.06
9.86
9.45
9.05
8.71
8.38
8.05
7.74
7.44
9.28
9.26
9.25
9.23
9.22
9.20
9.19
9.17
9.16
9.14
9.12
9.10
9.09
9.07
9.05
9.03
9.02
8.82
8.44
8.06
7.74
7.43
7.12
6.83
6.53
8.32
8.31
8.29
8.28
8.27
8.25
8.24
8.22
8.21
8.19
8.18
8.16
8.14
8.13
8.11
8.09
8.08
7.89
7.53
7.17
6.87
6.58
6.29
6.01
5.73
7.46
7.45
7.44
7.43
7.41
7.40
7.38
7.37
7.35
7.34
7.32
7.31
7.29
7.28
7.26
7.24
7.23
7.05
6.71
6.37
6.09
5.81
5.54
5.27
5.00
6.69
6.68
6.67
6.65
6.64
6.62
6.61
6.59
6.58
6.56
6.55
6.53
6.52
6.50
6.49
6.48
6.46
6.29
5.97
5.65
5.39
5.12
4.86
4.60
4.34
5.98
5.97
5.96
5.95
5.93
5.92
5.90
5.89
5.88
5.86
5.85
5.83
5.82
5.81
5.79
5.78
5.76
5.60
5.30
4.99
4.74
4.49
4.24
3.99
3.74
5.34
5.33
5.32
5.30
5.29
5.27
5.26
5.25
5.23
5.22
5.21
5.19
5.18
5.17
5.15
5.14
5.13
4.98
4.68
4.39
4.15
3.91
3.67
3.43
3.19
104000
4.74
4.73
4.72
4.71
4.70
4.68
4.67
4.66
4.65
4.63
4.62
4.61
4.59
4.58
4.57
4.56
4.54
4.40
4.12
3.84
3.61
3.38
3.15
2.92
2.69
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 8
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 1000 ft
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.21
12.20
12.18
12.17
12.16
12.14
12.13
12.10
12.08
12.05
10.57
10.56
10.55
10.54
10.52
10.51
10.49
10.47
10.45
10.43
9.20
9.19
9.17
9.16
9.15
9.14
9.12
9.10
9.08
9.06
8.02
8.01
7.99
7.98
7.97
7.96
7.95
7.93
7.91
7.89
6.96
6.95
6.94
6.93
6.92
6.91
6.90
6.88
6.86
6.84
6.02
6.01
6.00
5.99
5.98
5.97
5.96
5.94
5.92
5.90
5.17
5.16
5.15
5.15
5.14
5.13
5.11
5.09
5.08
5.06
4.41
4.40
4.39
4.38
4.37
4.36
4.34
4.33
4.31
4.30
3.71
3.70
3.69
3.68
3.67
3.66
3.65
3.63
3.62
3.60
3.07
3.06
3.05
3.04
3.03
3.02
3.01
3.00
2.98
2.97
104000
2.48
2.47
2.46
2.46
2.45
2.44
2.43
2.41
2.40
2.38
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 9
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 2000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
14.01
13.99
13.97
13.95
13.94
13.92
13.90
13.88
13.86
13.84
13.82
13.80
13.78
13.76
13.74
13.73
13.50
13.02
12.55
12.15
11.75
11.36
10.97
10.57
12.39
12.38
12.36
12.34
12.33
12.31
12.29
12.27
12.25
12.23
12.22
12.20
12.18
12.16
12.14
12.13
11.92
11.47
11.03
10.66
10.29
9.93
9.56
9.19
11.04
11.03
11.01
10.99
10.97
10.96
10.94
10.92
10.91
10.89
10.87
10.85
10.84
10.82
10.80
10.79
10.59
10.18
9.77
9.42
9.07
8.73
8.38
8.04
9.87
9.86
9.84
9.82
9.81
9.79
9.78
9.76
9.75
9.73
9.71
9.70
9.68
9.67
9.65
9.64
9.45
9.07
8.68
8.35
8.03
7.70
7.38
7.06
8.83
8.81
8.80
8.78
8.77
8.76
8.74
8.73
8.71
8.70
8.68
8.67
8.66
8.64
8.63
8.62
8.44
8.07
7.71
7.40
7.10
6.79
6.49
6.18
7.89
7.88
7.87
7.85
7.84
7.83
7.82
7.80
7.79
7.78
7.76
7.75
7.73
7.72
7.71
7.70
7.53
7.19
6.84
6.55
6.26
5.97
5.68
5.40
7.06
7.05
7.03
7.02
7.01
7.00
6.99
6.97
6.96
6.95
6.93
6.92
6.91
6.89
6.88
6.87
6.71
6.39
6.06
5.79
5.51
5.24
4.96
4.69
6.30
6.29
6.28
6.27
6.25
6.24
6.23
6.22
6.21
6.19
6.18
6.17
6.16
6.14
6.13
6.12
5.97
5.66
5.36
5.09
4.83
4.57
4.31
4.05
5.61
5.60
5.59
5.58
5.57
5.56
5.55
5.53
5.52
5.51
5.50
5.49
5.47
5.46
5.45
5.44
5.30
5.01
4.71
4.46
4.22
3.97
3.72
3.47
4.98
4.97
4.96
4.95
4.94
4.93
4.92
4.91
4.90
4.89
4.88
4.86
4.85
4.84
4.83
4.82
4.69
4.41
4.13
3.89
3.66
3.42
3.18
2.94
104000
4.41
4.40
4.39
4.38
4.37
4.36
4.35
4.34
4.33
4.31
4.30
4.29
4.28
4.27
4.26
4.25
4.12
3.86
3.59
3.36
3.14
2.91
2.68
2.45
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
(°C)
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.64
11.63
11.61
11.60
11.58
11.57
11.55
11.53
11.51
11.49
10.05
10.03
10.01
10.00
9.98
9.97
9.95
9.93
9.91
9.90
8.71
8.69
8.67
8.66
8.64
8.63
8.61
8.59
8.58
8.56
7.56
7.54
7.53
7.51
7.50
7.48
7.47
7.45
7.43
7.42
6.53
6.52
6.50
6.49
6.47
6.46
6.44
6.43
6.42
6.40
5.61
5.60
5.58
5.57
5.56
5.54
5.53
5.52
5.50
5.49
4.78
4.77
4.76
4.74
4.73
4.72
4.71
4.69
4.68
4.67
4.03
4.02
4.01
4.00
3.99
3.97
3.96
3.95
3.94
3.93
3.35
3.34
3.33
3.32
3.31
3.29
3.28
3.27
3.26
3.25
2.73
2.72
2.71
2.70
2.69
2.67
2.66
2.65
2.64
2.63
104000
2.16
2.15
2.14
2.13
2.12
2.11
2.10
2.09
2.08
2.06
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 10
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 3000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
13.49
13.47
13.45
13.43
13.42
13.40
13.38
13.36
13.35
13.33
13.31
13.29
13.27
13.25
13.24
13.02
12.57
12.13
11.73
11.33
10.94
10.55
10.16
11.90
11.89
11.87
11.86
11.84
11.83
11.81
11.79
11.77
11.76
11.74
11.72
11.70
11.69
11.67
11.47
11.06
10.64
10.27
9.90
9.54
9.17
8.81
10.58
10.56
10.55
10.53
10.52
10.50
10.49
10.47
10.46
10.44
10.42
10.41
10.39
10.37
10.36
10.18
9.79
9.40
9.05
8.71
8.37
8.02
7.68
9.45
9.43
9.42
9.40
9.39
9.37
9.36
9.35
9.33
9.31
9.30
9.28
9.27
9.25
9.24
9.07
8.70
8.34
8.01
7.69
7.37
7.05
6.73
8.43
8.42
8.41
8.39
8.38
8.37
8.35
8.34
8.33
8.31
8.30
8.28
8.27
8.25
8.24
8.08
7.73
7.39
7.08
6.78
6.48
6.17
5.87
7.53
7.52
7.50
7.49
7.48
7.47
7.45
7.44
7.43
7.41
7.40
7.39
7.37
7.36
7.35
7.19
6.86
6.54
6.25
5.96
5.68
5.39
5.11
6.71
6.70
6.69
6.68
6.66
6.65
6.64
6.63
6.61
6.60
6.59
6.58
6.57
6.55
6.54
6.39
6.08
5.77
5.50
5.23
4.96
4.69
4.42
5.97
5.96
5.95
5.94
5.93
5.91
5.90
5.89
5.88
5.87
5.86
5.85
5.83
5.82
5.81
5.67
5.37
5.08
4.82
4.56
4.31
4.05
3.79
5.30
5.29
5.28
5.27
5.26
5.25
5.24
5.22
5.21
5.20
5.19
5.18
5.17
5.16
5.15
5.01
4.73
4.45
4.20
3.96
3.71
3.47
3.22
4.69
4.68
4.67
4.66
4.65
4.64
4.63
4.62
4.61
4.59
4.58
4.57
4.56
4.55
4.54
4.41
4.14
3.87
3.64
3.41
3.17
2.94
2.71
104000
4.13
4.12
4.11
4.10
4.09
4.08
4.07
4.06
4.05
4.04
4.03
4.02
4.00
3.99
3.98
3.86
3.60
3.35
3.12
2.90
2.68
2.45
2.23
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.14
11.12
11.10
11.09
11.07
11.05
11.03
11.01
10.99
10.98
9.58
9.56
9.54
9.53
9.51
9.49
9.47
9.46
9.44
9.42
8.27
8.25
8.23
8.22
8.20
8.19
8.17
8.15
8.14
8.12
7.15
7.13
7.12
7.10
7.09
7.07
7.06
7.04
7.03
7.01
6.15
6.13
6.12
6.10
6.09
6.07
6.06
6.05
6.03
6.02
5.25
5.24
5.22
5.21
5.20
5.18
5.17
5.16
5.14
5.13
4.44
4.43
4.42
4.41
4.39
4.38
4.37
4.35
4.34
4.33
3.71
3.70
3.69
3.68
3.66
3.65
3.64
3.63
3.62
3.60
3.05
3.04
3.02
3.01
3.00
2.99
2.98
2.97
2.96
2.94
2.44
2.43
2.42
2.41
2.40
2.39
2.38
2.36
2.35
2.34
104000
1.89
1.88
1.86
1.85
1.84
1.83
1.82
1.81
1.80
1.79
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 4000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.98
12.96
12.94
12.92
12.90
12.88
12.86
12.85
12.83
12.81
12.79
12.77
12.75
12.74
12.54
12.12
11.70
11.30
10.91
10.53
10.14
9.75
11.43
11.42
11.40
11.38
11.36
11.34
11.33
11.31
11.29
11.27
11.26
11.24
11.22
11.21
11.02
10.63
10.24
9.88
9.51
9.15
8.79
8.43
10.14
10.12
10.11
10.09
10.07
10.06
10.04
10.02
10.01
9.99
9.97
9.96
9.94
9.93
9.75
9.39
9.02
8.68
8.34
8.01
7.67
7.33
9.03
9.02
9.00
8.99
8.97
8.96
8.94
8.92
8.91
8.89
8.88
8.86
8.85
8.83
8.67
8.33
7.99
7.67
7.35
7.03
6.71
6.40
8.05
8.03
8.02
8.00
7.99
7.97
7.96
7.95
7.93
7.92
7.90
7.89
7.87
7.86
7.70
7.38
7.06
6.76
6.46
6.16
5.86
5.56
7.16
7.15
7.14
7.12
7.11
7.10
7.08
7.07
7.05
7.04
7.03
7.01
7.00
6.99
6.84
6.53
6.23
5.95
5.66
5.38
5.10
4.82
6.37
6.36
6.34
6.33
6.32
6.30
6.29
6.28
6.27
6.25
6.24
6.23
6.21
6.20
6.06
5.77
5.48
5.21
4.95
4.68
4.41
4.15
5.65
5.64
5.63
5.61
5.60
5.59
5.58
5.56
5.55
5.54
5.53
5.51
5.50
5.49
5.36
5.08
4.80
4.55
4.30
4.04
3.79
3.54
5.00
4.98
4.97
4.96
4.95
4.94
4.92
4.91
4.90
4.89
4.88
4.87
4.85
4.84
4.71
4.45
4.19
3.95
3.70
3.46
3.22
2.98
4.40
4.39
4.38
4.36
4.35
4.34
4.33
4.32
4.31
4.30
4.29
4.27
4.26
4.25
4.13
3.88
3.63
3.39
3.16
2.93
2.71
2.48
104000
3.85
3.84
3.83
3.82
3.81
3.80
3.79
3.77
3.76
3.75
3.74
3.73
3.72
3.71
3.59
3.35
3.11
2.89
2.66
2.45
2.23
2.02
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
(°C)
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
10.62
10.60
10.59
10.57
10.55
10.53
10.52
10.50
10.48
10.46
9.10
9.08
9.06
9.05
9.03
9.01
9.00
8.98
8.97
8.95
7.82
7.80
7.79
7.77
7.76
7.74
7.73
7.71
7.69
7.68
6.73
6.71
6.70
6.68
6.67
6.66
6.64
6.63
6.61
6.60
5.76
5.74
5.73
5.71
5.70
5.69
5.67
5.66
5.65
5.63
4.88
4.87
4.86
4.84
4.83
4.82
4.81
4.79
4.78
4.77
4.10
4.09
4.07
4.06
4.05
4.04
4.02
4.01
4.00
3.99
3.39
3.37
3.36
3.35
3.34
3.33
3.32
3.30
3.29
3.28
2.74
2.73
2.72
2.71
2.69
2.68
2.67
2.66
2.65
2.64
2.15
2.14
2.13
2.12
2.11
2.09
2.08
2.07
2.06
2.05
104000
1.61
1.60
1.59
1.58
1.56
1.55
1.54
1.53
1.52
1.51
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 12
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP 5 – APPROACH FLAP 2
Altitude: 5000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.44
12.42
12.41
12.39
12.37
12.35
12.34
12.32
12.30
12.28
12.27
12.25
12.23
12.05
11.66
11.28
10.89
10.50
10.12
9.73
9.35
10.93
10.92
10.90
10.88
10.87
10.85
10.84
10.82
10.80
10.79
10.77
10.75
10.74
10.57
10.21
9.85
9.49
9.13
8.77
8.42
8.06
9.67
9.66
9.64
9.63
9.61
9.60
9.58
9.57
9.55
9.54
9.52
9.50
9.49
9.33
9.00
8.66
8.32
7.99
7.65
7.32
6.99
8.60
8.59
8.57
8.56
8.54
8.53
8.51
8.50
8.48
8.47
8.46
8.44
8.43
8.28
7.96
7.64
7.33
7.01
6.70
6.39
6.08
7.64
7.63
7.62
7.60
7.59
7.57
7.56
7.55
7.53
7.52
7.51
7.49
7.48
7.34
7.03
6.73
6.43
6.13
5.84
5.55
5.26
6.78
6.77
6.76
6.75
6.73
6.72
6.71
6.69
6.68
6.67
6.65
6.64
6.63
6.49
6.21
5.92
5.64
5.35
5.07
4.81
4.54
6.01
6.00
5.99
5.97
5.96
5.95
5.94
5.92
5.91
5.90
5.89
5.87
5.86
5.73
5.46
5.19
4.92
4.65
4.39
4.13
3.88
5.31
5.30
5.29
5.28
5.26
5.25
5.24
5.23
5.22
5.20
5.19
5.18
5.17
5.04
4.79
4.53
4.27
4.02
3.77
3.53
3.29
4.68
4.66
4.65
4.64
4.63
4.62
4.61
4.60
4.58
4.57
4.56
4.55
4.54
4.42
4.17
3.93
3.68
3.44
3.20
2.97
2.75
4.10
4.08
4.07
4.06
4.05
4.04
4.03
4.02
4.01
3.99
3.98
3.97
3.96
3.85
3.61
3.38
3.15
2.91
2.69
2.47
2.25
104000
3.56
3.55
3.54
3.53
3.52
3.51
3.50
3.49
3.48
3.47
3.46
3.44
3.43
3.33
3.10
2.88
2.65
2.43
2.21
2.01
1.80
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
10.10
10.08
10.06
10.05
10.03
10.02
10.00
9.98
9.97
9.95
8.61
8.59
8.58
8.56
8.55
8.53
8.52
8.50
8.49
8.47
7.37
7.35
7.34
7.32
7.31
7.29
7.28
7.27
7.25
7.24
6.31
6.29
6.28
6.26
6.25
6.24
6.22
6.21
6.20
6.18
5.36
5.35
5.33
5.32
5.31
5.29
5.28
5.27
5.26
5.24
4.51
4.50
4.49
4.47
4.46
4.45
4.44
4.42
4.41
4.40
3.75
3.74
3.72
3.71
3.70
3.69
3.68
3.66
3.65
3.64
3.06
3.04
3.03
3.02
3.01
3.00
2.99
2.98
2.96
2.95
2.43
2.42
2.41
2.40
2.38
2.37
2.36
2.35
2.34
2.33
1.86
1.85
1.84
1.83
1.82
1.80
1.79
1.78
1.77
1.76
104000
1.33
1.32
1.32
1.30
1.29
1.28
1.27
1.26
1.25
1.24
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 13
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: Sea Level
ANTI-ICE OFF
WEIGHT (lb)
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
48
50
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
14.23
14.21
14.19
14.17
14.15
14.12
14.10
14.07
14.04
14.02
13.99
13.97
13.94
13.92
13.89
13.86
13.82
13.76
13.47
12.94
12.41
11.99
11.57
11.17
10.80
10.43
12.47
12.46
12.44
12.42
12.40
12.37
12.35
12.33
12.30
12.28
12.26
12.23
12.21
12.18
12.16
12.14
12.09
12.04
11.76
11.27
10.78
10.39
10.00
9.63
9.28
8.94
11.01
10.99
10.98
10.96
10.94
10.92
10.90
10.88
10.85
10.83
10.81
10.79
10.77
10.75
10.72
10.70
10.66
10.60
10.34
9.88
9.42
9.06
8.69
8.35
8.03
7.71
9.76
9.75
9.73
9.72
9.70
9.68
9.66
9.64
9.62
9.60
9.58
9.56
9.54
9.52
9.50
9.48
9.43
9.37
9.13
8.70
8.27
7.92
7.58
7.26
6.96
6.66
8.65
8.63
8.62
8.61
8.59
8.57
8.55
8.53
8.52
8.50
8.48
8.46
8.44
8.42
8.40
8.39
8.33
8.28
8.05
7.64
7.24
6.92
6.59
6.29
6.01
5.73
7.65
7.63
7.62
7.61
7.59
7.57
7.56
7.54
7.52
7.50
7.49
7.47
7.45
7.43
7.42
7.40
7.35
7.30
7.09
6.70
6.32
6.01
5.71
5.42
5.15
4.88
6.74
6.73
6.72
6.71
6.69
6.67
6.66
6.64
6.62
6.61
6.59
6.57
6.56
6.54
6.53
6.51
6.46
6.42
6.21
5.85
5.49
5.20
4.91
4.64
4.38
4.12
5.92
5.91
5.90
5.89
5.87
5.86
5.84
5.83
5.81
5.80
5.78
5.76
5.75
5.73
5.72
5.70
5.66
5.62
5.42
5.08
4.73
4.46
4.18
3.92
3.67
3.43
5.18
5.17
5.16
5.14
5.13
5.11
5.10
5.08
5.07
5.05
5.04
5.02
5.01
4.99
4.98
4.96
4.92
4.89
4.70
4.37
4.05
3.79
3.52
3.27
3.03
2.80
4.49
4.48
4.48
4.46
4.45
4.43
4.42
4.40
4.39
4.37
4.36
4.34
4.33
4.31
4.30
4.28
4.25
4.22
4.04
3.73
3.42
3.17
2.92
2.68
2.45
2.22
104000
3.87
3.86
3.85
3.84
3.82
3.81
3.79
3.78
3.77
3.75
3.74
3.72
3.71
3.69
3.68
3.66
3.64
3.60
3.44
3.14
2.85
2.61
2.37
2.13
1.91
1.69
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 14
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: Sea Level
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.32
12.31
12.30
12.28
12.27
12.25
12.24
12.22
12.19
12.17
10.59
10.58
10.56
10.55
10.54
10.52
10.51
10.49
10.47
10.44
9.14
9.13
9.12
9.10
9.09
9.08
9.07
9.05
9.03
9.01
7.91
7.89
7.88
7.87
7.86
7.85
7.84
7.82
7.80
7.78
6.80
6.79
6.78
6.77
6.76
6.75
6.74
6.72
6.70
6.68
5.81
5.80
5.79
5.78
5.77
5.76
5.75
5.74
5.72
5.70
4.92
4.91
4.90
4.89
4.88
4.87
4.86
4.85
4.83
4.81
4.11
4.10
4.09
4.08
4.07
4.06
4.05
4.04
4.02
4.00
3.37
3.36
3.35
3.34
3.33
3.32
3.31
3.30
3.28
3.27
2.69
2.68
2.67
2.66
2.66
2.65
2.64
2.63
2.61
2.59
104000
2.07
2.06
2.05
2.04
2.03
2.03
2.02
2.01
1.99
1.98
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 15
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 1000 ft
ANTI-ICE OFF
WEIGHT (lb)
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
48
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
13.58
13.56
13.54
13.52
13.50
13.48
13.45
13.43
13.41
13.39
13.36
13.34
13.32
13.30
13.27
13.25
13.23
12.97
12.46
11.95
11.53
11.12
10.72
10.35
9.98
11.87
11.85
11.83
11.81
11.79
11.77
11.75
11.73
11.71
11.69
11.67
11.65
11.62
11.60
11.58
11.56
11.54
11.30
10.83
10.35
9.97
9.58
9.21
8.87
8.52
10.44
10.43
10.41
10.39
10.37
10.35
10.33
10.31
10.29
10.27
10.25
10.24
10.22
10.20
10.18
10.16
10.14
9.91
9.47
9.03
8.66
8.30
7.96
7.64
7.31
9.23
9.22
9.20
9.18
9.16
9.14
9.13
9.11
9.09
9.07
9.05
9.03
9.01
9.00
8.98
8.96
8.94
8.73
8.31
7.90
7.56
7.22
6.90
6.59
6.29
8.15
8.14
8.12
8.10
8.09
8.07
8.05
8.03
8.02
8.00
7.98
7.96
7.94
7.93
7.91
7.89
7.87
7.67
7.28
6.89
6.57
6.25
5.95
5.66
5.38
7.18
7.17
7.15
7.14
7.12
7.10
7.09
7.07
7.05
7.04
7.02
7.00
6.99
6.97
6.95
6.94
6.92
6.73
6.36
5.99
5.69
5.39
5.10
4.82
4.55
6.30
6.29
6.28
6.27
6.25
6.23
6.22
6.20
6.19
6.17
6.16
6.14
6.12
6.11
6.09
6.08
6.06
5.88
5.53
5.18
4.89
4.60
4.33
4.07
3.81
5.51
5.50
5.49
5.48
5.46
5.45
5.43
5.42
5.40
5.39
5.37
5.36
5.34
5.33
5.31
5.30
5.28
5.11
4.78
4.45
4.17
3.90
3.63
3.38
3.13
4.79
4.78
4.76
4.75
4.74
4.72
4.71
4.70
4.68
4.67
4.65
4.64
4.63
4.61
4.60
4.58
4.57
4.41
4.09
3.77
3.51
3.25
3.00
2.76
2.52
4.12
4.11
4.10
4.09
4.08
4.06
4.05
4.04
4.03
4.01
4.00
3.99
3.97
3.96
3.95
3.93
3.92
3.76
3.46
3.16
2.91
2.66
2.42
2.19
1.95
104000
3.51
3.50
3.49
3.48
3.47
3.46
3.45
3.44
3.43
3.41
3.40
3.39
3.37
3.36
3.35
3.33
3.32
3.17
2.88
2.60
2.36
2.12
1.89
1.66
1.44
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 16
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 1000 ft
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.68
11.67
11.66
11.64
11.63
11.62
11.60
11.58
11.55
11.53
9.99
9.98
9.97
9.96
9.94
9.93
9.91
9.89
9.87
9.85
8.58
8.57
8.56
8.55
8.54
8.53
8.51
8.49
8.47
8.45
7.38
7.37
7.36
7.35
7.34
7.33
7.31
7.29
7.27
7.25
6.31
6.30
6.29
6.28
6.27
6.26
6.24
6.23
6.21
6.19
5.35
5.34
5.33
5.32
5.31
5.30
5.29
5.27
5.25
5.23
4.48
4.48
4.47
4.46
4.45
4.44
4.43
4.41
4.39
4.38
3.70
3.69
3.68
3.67
3.66
3.66
3.64
3.63
3.61
3.60
2.98
2.97
2.97
2.96
2.95
2.94
2.93
2.91
2.90
2.88
2.33
2.32
2.31
2.30
2.30
2.29
2.28
2.26
2.25
2.23
104000
1.73
1.72
1.71
1.70
1.70
1.69
1.68
1.66
1.65
1.63
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 17
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 2000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
46
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.97
12.95
12.93
12.92
12.90
12.88
12.86
12.84
12.82
12.80
12.79
12.77
12.75
12.73
12.71
12.69
12.46
11.98
11.50
11.10
10.69
10.29
9.90
9.50
11.30
11.29
11.27
11.25
11.24
11.22
11.20
11.19
11.17
11.15
11.13
11.11
11.09
11.08
11.06
11.04
10.83
10.38
9.93
9.56
9.18
8.81
8.44
8.07
9.92
9.90
9.89
9.87
9.86
9.84
9.82
9.81
9.79
9.77
9.76
9.74
9.72
9.70
9.69
9.67
9.47
9.05
8.63
8.28
7.93
7.59
7.24
6.89
8.73
8.72
8.71
8.69
8.68
8.66
8.65
8.63
8.62
8.60
8.58
8.57
8.55
8.54
8.52
8.51
8.32
7.92
7.53
7.20
6.87
6.55
6.22
5.89
7.68
7.67
7.66
7.64
7.63
7.62
7.60
7.59
7.57
7.56
7.54
7.53
7.51
7.50
7.48
7.47
7.29
6.92
6.55
6.24
5.93
5.62
5.31
5.00
6.74
6.73
6.72
6.71
6.69
6.68
6.67
6.65
6.64
6.62
6.61
6.59
6.58
6.56
6.55
6.54
6.37
6.02
5.67
5.37
5.08
4.78
4.49
4.20
5.90
5.89
5.87
5.86
5.85
5.83
5.82
5.81
5.79
5.78
5.76
5.75
5.74
5.72
5.71
5.70
5.54
5.21
4.87
4.59
4.31
4.03
3.75
3.48
5.13
5.12
5.10
5.09
5.08
5.06
5.05
5.04
5.02
5.01
5.00
4.99
4.97
4.96
4.95
4.94
4.78
4.47
4.15
3.88
3.62
3.35
3.09
2.82
4.42
4.41
4.40
4.38
4.37
4.36
4.35
4.34
4.32
4.31
4.30
4.29
4.27
4.26
4.25
4.24
4.10
3.79
3.49
3.24
2.98
2.73
2.48
2.22
3.77
3.76
3.75
3.74
3.73
3.72
3.71
3.69
3.68
3.67
3.66
3.65
3.64
3.62
3.61
3.61
3.47
3.18
2.89
2.65
2.40
2.16
1.92
1.68
104000
3.18
3.17
3.16
3.15
3.14
3.13
3.12
3.10
3.09
3.08
3.07
3.06
3.05
3.04
3.03
3.02
2.89
2.61
2.34
2.10
1.87
1.64
1.41
1.17
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
(°C)
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.10
11.09
11.07
11.06
11.05
11.03
11.01
10.99
10.97
10.95
9.45
9.44
9.43
9.42
9.40
9.39
9.37
9.35
9.33
9.31
8.08
8.07
8.06
8.04
8.03
8.02
8.00
7.98
7.97
7.95
6.91
6.90
6.89
6.88
6.87
6.85
6.84
6.82
6.80
6.79
5.86
5.85
5.84
5.83
5.82
5.81
5.80
5.78
5.76
5.75
4.93
4.92
4.91
4.90
4.89
4.88
4.86
4.85
4.83
4.82
4.09
4.08
4.07
4.05
4.04
4.03
4.02
4.00
3.99
3.98
3.32
3.31
3.30
3.29
3.28
3.26
3.25
3.24
3.23
3.22
2.63
2.61
2.60
2.59
2.58
2.57
2.56
2.54
2.53
2.52
1.99
1.98
1.96
1.95
1.94
1.93
1.92
1.91
1.90
1.89
104000
1.40
1.39
1.38
1.37
1.36
1.35
1.33
1.32
1.31
1.30
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 18
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 3000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
44
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
12.44
12.43
12.41
12.39
12.38
12.36
12.34
12.32
12.30
12.28
12.26
12.25
12.23
12.21
12.19
11.97
11.52
11.07
10.67
10.27
9.87
9.47
9.07
10.82
10.80
10.78
10.77
10.75
10.74
10.72
10.70
10.68
10.67
10.65
10.63
10.61
10.59
10.58
10.38
9.95
9.53
9.16
8.79
8.42
8.04
7.67
9.46
9.45
9.43
9.42
9.40
9.39
9.37
9.36
9.34
9.32
9.31
9.29
9.27
9.26
9.24
9.05
8.66
8.26
7.91
7.56
7.22
6.87
6.52
8.31
8.30
8.28
8.27
8.25
8.24
8.23
8.21
8.19
8.18
8.16
8.15
8.13
8.12
8.10
7.93
7.55
7.18
6.85
6.53
6.20
5.87
5.55
7.28
7.27
7.26
7.24
7.23
7.22
7.20
7.19
7.17
7.16
7.15
7.13
7.12
7.10
7.09
6.92
6.57
6.22
5.91
5.60
5.29
4.98
4.67
6.36
6.35
6.34
6.32
6.31
6.30
6.29
6.27
6.26
6.25
6.23
6.22
6.20
6.19
6.18
6.02
5.69
5.36
5.06
4.77
4.48
4.18
3.89
5.53
5.52
5.51
5.49
5.48
5.47
5.46
5.45
5.43
5.42
5.41
5.39
5.38
5.37
5.36
5.21
4.89
4.58
4.30
4.02
3.74
3.46
3.19
4.78
4.77
4.75
4.74
4.73
4.72
4.71
4.70
4.68
4.67
4.66
4.65
4.63
4.62
4.61
4.47
4.17
3.87
3.61
3.34
3.08
2.81
2.55
4.09
4.08
4.07
4.06
4.05
4.04
4.03
4.01
4.00
3.99
3.98
3.97
3.95
3.94
3.93
3.80
3.51
3.23
2.97
2.72
2.47
2.22
1.96
3.46
3.45
3.44
3.43
3.42
3.41
3.40
3.39
3.38
3.37
3.36
3.34
3.33
3.32
3.31
3.18
2.91
2.64
2.39
2.15
1.91
1.67
1.43
104000
2.89
2.88
2.87
2.86
2.85
2.84
2.83
2.82
2.80
2.79
2.78
2.77
2.76
2.75
2.74
2.62
2.36
2.09
1.86
1.63
1.40
1.17
0.94
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
10.59
10.57
10.56
10.54
10.52
10.50
10.48
10.47
10.45
10.43
8.98
8.96
8.94
8.93
8.91
8.89
8.87
8.86
8.84
8.82
7.64
7.62
7.60
7.59
7.57
7.56
7.54
7.52
7.51
7.49
6.49
6.48
6.46
6.45
6.43
6.42
6.40
6.39
6.37
6.36
5.48
5.46
5.45
5.43
5.42
5.41
5.39
5.38
5.36
5.35
4.56
4.55
4.54
4.52
4.51
4.50
4.48
4.47
4.46
4.44
3.74
3.72
3.71
3.70
3.69
3.67
3.66
3.65
3.64
3.62
2.99
2.98
2.96
2.95
2.94
2.93
2.92
2.90
2.89
2.88
2.31
2.30
2.28
2.27
2.26
2.25
2.24
2.23
2.21
2.20
1.68
1.67
1.66
1.65
1.64
1.63
1.62
1.61
1.60
1.58
104000
1.11
1.10
1.09
1.08
1.07
1.06
1.05
1.04
1.03
1.02
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 19
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 4000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
42
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.93
11.91
11.89
11.87
11.85
11.83
11.81
11.79
11.77
11.75
11.74
11.72
11.70
11.68
11.48
11.06
10.63
10.23
9.84
9.44
9.05
8.66
10.34
10.32
10.30
10.28
10.26
10.25
10.23
10.21
10.19
10.18
10.16
10.14
10.12
10.11
9.92
9.53
9.13
8.76
8.39
8.02
7.65
7.29
9.01
9.00
8.98
8.96
8.95
8.93
8.91
8.90
8.88
8.86
8.85
8.83
8.81
8.80
8.63
8.26
7.88
7.54
7.19
6.85
6.50
6.16
7.89
7.87
7.86
7.84
7.83
7.81
7.80
7.78
7.77
7.75
7.73
7.72
7.70
7.69
7.53
7.18
6.83
6.50
6.18
5.85
5.53
5.21
6.89
6.87
6.86
6.84
6.83
6.81
6.80
6.79
6.77
6.76
6.74
6.73
6.71
6.70
6.55
6.22
5.89
5.58
5.27
4.97
4.66
4.36
5.99
5.98
5.96
5.95
5.93
5.92
5.91
5.89
5.88
5.86
5.85
5.84
5.82
5.81
5.66
5.35
5.04
4.75
4.46
4.17
3.88
3.59
5.18
5.16
5.15
5.14
5.13
5.11
5.10
5.09
5.07
5.06
5.05
5.03
5.02
5.01
4.87
4.57
4.28
4.00
3.73
3.45
3.18
2.90
4.44
4.43
4.42
4.40
4.39
4.38
4.37
4.35
4.34
4.33
4.32
4.31
4.29
4.28
4.15
3.87
3.59
3.32
3.06
2.80
2.54
2.28
3.77
3.76
3.75
3.74
3.72
3.71
3.70
3.69
3.68
3.66
3.65
3.64
3.63
3.62
3.49
3.22
2.96
2.71
2.46
2.21
1.96
1.71
3.16
3.15
3.14
3.12
3.11
3.10
3.09
3.08
3.07
3.06
3.05
3.03
3.02
3.01
2.89
2.63
2.38
2.14
1.90
1.67
1.43
1.19
104000
2.60
2.59
2.57
2.56
2.55
2.54
2.53
2.52
2.51
2.50
2.49
2.48
2.47
2.46
2.34
2.09
1.85
1.62
1.39
1.17
0.94
0.71
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
(°C)
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
10.07
10.05
10.04
10.02
10.00
9.98
9.96
9.95
9.93
9.91
8.49
8.47
8.46
8.44
8.42
8.41
8.39
8.38
8.36
8.34
7.18
7.16
7.15
7.13
7.12
7.10
7.09
7.07
7.06
7.04
6.07
6.05
6.04
6.02
6.01
5.99
5.98
5.97
5.95
5.94
5.07
5.06
5.05
5.03
5.02
5.00
4.99
4.98
4.96
4.95
4.18
4.17
4.16
4.14
4.13
4.12
4.10
4.09
4.08
4.06
3.38
3.36
3.35
3.34
3.33
3.32
3.30
3.29
3.28
3.27
2.65
2.64
2.62
2.61
2.60
2.59
2.58
2.56
2.55
2.54
1.98
1.97
1.96
1.95
1.94
1.93
1.92
1.90
1.89
1.88
1.38
1.37
1.36
1.34
1.33
1.32
1.31
1.30
1.29
1.28
104000
0.82
0.81
0.80
0.79
0.78
0.77
0.76
0.75
0.74
0.73
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 20
Approach
REVISION 23
AOM-1502-016
SAT
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
APPROACH CLIMB GRADIENT (%)
EMBRAER 190 – CF34-10E6/10E6A1
LANDING FLAP FULL – APPROACH FLAP 4
Altitude: 5000 ft
ANTI-ICE OFF
WEIGHT (lb)
SAT
(°C)
0
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
32
34
36
38
40
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
11.38
11.36
11.34
11.33
11.31
11.29
11.27
11.26
11.24
11.22
11.20
11.19
11.17
10.99
10.59
10.20
9.80
9.41
9.02
8.63
8.24
9.83
9.81
9.79
9.78
9.76
9.74
9.73
9.71
9.70
9.68
9.66
9.65
9.64
9.47
9.10
8.73
8.36
7.99
7.62
7.26
6.89
8.54
8.52
8.51
8.49
8.48
8.46
8.45
8.43
8.42
8.40
8.39
8.37
8.36
8.20
7.86
7.51
7.17
6.82
6.48
6.14
5.80
7.45
7.43
7.42
7.40
7.39
7.37
7.36
7.35
7.33
7.32
7.30
7.29
7.28
7.13
6.80
6.48
6.16
5.84
5.51
5.19
4.87
6.47
6.46
6.44
6.43
6.42
6.40
6.39
6.38
6.36
6.35
6.34
6.32
6.31
6.17
5.86
5.56
5.26
4.95
4.65
4.35
4.04
5.59
5.58
5.57
5.56
5.54
5.53
5.52
5.51
5.49
5.48
5.47
5.45
5.44
5.31
5.02
4.73
4.45
4.16
3.87
3.59
3.30
4.80
4.79
4.78
4.77
4.76
4.74
4.73
4.72
4.71
4.69
4.68
4.67
4.66
4.53
4.26
3.99
3.71
3.44
3.17
2.90
2.63
4.09
4.08
4.06
4.05
4.04
4.03
4.02
4.01
3.99
3.98
3.97
3.96
3.95
3.83
3.57
3.31
3.05
2.79
2.53
2.27
2.02
3.44
3.43
3.41
3.40
3.39
3.38
3.37
3.36
3.35
3.34
3.33
3.31
3.30
3.19
2.94
2.69
2.44
2.19
1.95
1.71
1.46
2.84
2.83
2.82
2.81
2.80
2.79
2.78
2.77
2.76
2.75
2.73
2.72
2.71
2.60
2.36
2.12
1.89
1.65
1.41
1.18
0.95
104000
2.29
2.28
2.27
2.26
2.25
2.24
2.23
2.22
2.21
2.20
2.19
2.18
2.17
2.06
1.83
1.61
1.38
1.15
0.92
0.71
0.49
WING AND ENGINE ANTI-ICE ON
WEIGHT (lb)
SAT
(°C)
AOM-1502-016
-8
-6
-4
-2
0
2
4
6
8
10
64000 68000 72000 76000 80000 84000 88000 92000 96000 100000
9.53
9.51
9.49
9.48
9.46
9.45
9.43
9.41
9.40
9.38
7.99
7.98
7.96
7.94
7.93
7.91
7.90
7.88
7.87
7.85
6.71
6.70
6.69
6.67
6.66
6.64
6.63
6.62
6.60
6.59
5.63
5.62
5.60
5.59
5.58
5.56
5.55
5.54
5.52
5.51
4.66
4.65
4.64
4.62
4.61
4.60
4.59
4.57
4.56
4.55
3.79
3.78
3.77
3.76
3.75
3.73
3.72
3.71
3.70
3.69
3.01
3.00
2.99
2.98
2.97
2.95
2.94
2.93
2.92
2.91
2.30
2.29
2.28
2.27
2.26
2.25
2.24
2.22
2.21
2.20
1.66
1.64
1.63
1.62
1.61
1.60
1.59
1.58
1.57
1.56
1.06
1.05
1.04
1.03
1.02
1.01
1.00
0.99
0.98
0.97
104000
0.52
0.51
0.50
0.49
0.48
0.47
0.46
0.45
0.44
0.43
5-30
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Approach
Page 21
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
5-30
Copyright © by Embraer. Refer to cover page for details.
Page 22
Approach
REVISION 23
AOM-1502-016
INTENTIONALLY BLANK
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
UNFACTORED LANDING DISTANCE
Unfactored landing distance is the actual distance to land the airplane
on a zero slope, ISA temperature, dry runway, from a point 50 ft above
runway threshold at Vref, using only the brakes and spoilers as
deceleration devices (i.e., no engine reverse thrust is used).
The unfactored landing distances provided are valid for anti-ice ON and
OFF.
NORMAL OPERATION
The required landing distance for dispatch is the unfactored landing
distance increased by 66.7% for dry runway, or 91.7% for wet runway.
For obtaining the DRY runway factored distance, multiply unfactored
landing distance by 1.667.
For obtaining the WET runway factored distance, multiply unfactored
landing distance by 1.917.
The unfactored landing distance corrections are valid for overspeeds up
to Vref + 20 and no failure.
EMERGENCY/ABNORMAL OPERATION
LANDING DISTANCE CORRECTION FACTOR - DRY RUNWAYS
The Actual Landing Distance is equal to the Unfactored Landing Distance
for flaps FULL multiplied by the associated landing distance factor for
DRY runways.
AOM-1502-016
The DRY + OVSP corresponds to the factor associated to a 10 kt
overspeed (above the non-normal VREF) on a dry runway.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
LANDING DISTANCE CORRECTION FACTOR - WET RUNWAYS
The WET + OVSP corresponds to the factor associated to a 10 kt
overspeed (above the non-normal VREF) on a wet runway.
To calculate the actual landing distance on a WET runway, the pilot must
do the steps below:
1. Recognize the system malfunction;
2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick
Reference Handbook (QRH), considering the airplane type, altitude,
landing weight and ice accretion condition;
3.
Find the multiplier factor value (K) on the table with Landing Distance
Correction Factors and multiply the obtained values of (ULD) and
(K).
4. In the same line of table with Landing Distance Correction Factors,
find the value (B).
5.
Subtract (B) from the result of step (3). This is the actual landing
distance (ALD) to safely land the airplane on wet runways condition.
ALD = (ULD x K) – B
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 2
Landing
REVISION 23
AOM-1502-016
NOTE: The calculated value is the actual distance to safely land the
airplane, but no distance margins are included. The distance
margin available is the difference between the runway length
and the calculated value.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
0
WEIGHT
(lb)
1000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2496
2085
1956
1830
2543
2129
1998
1871
72000
2638
2217
2084
1955
2688
2264
2130
2000
78000
2778
2347
2211
2079
2831
2397
2260
2127
84000
2914
2475
2336
2201
2971
2528
2388
2251
90000
3050
2602
2460
2322
3111
2659
2515
2376
96000
3186
2730
2585
2443
3250
2789
2643
2500
102000
3321
2855
2707
2563
3388
2918
2769
2623
108000
3454
2981
2830
2683
3525
3046
2894
2746
114000
3584
3103
2949
2800
3662
3171
3017
2866
Per 5 kt above Vref (and no failure) add 208 ft.
PRESSURE ALTITUDE (ft)
2000
WEIGHT
(lb)
3000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2592
2174
2042
1914
2643
2222
2089
1959
72000
2740
2312
2177
2046
2795
2363
2227
2094
78000
2887
2449
2311
2176
2945
2503
2364
2228
84000
3030
2583
2441
2304
3092
2641
2498
2358
90000
3173
2717
2572
2431
3238
2778
2632
2489
96000
3316
2851
2703
2559
3385
2915
2766
2620
102000
3457
2983
2832
2685
3529
3050
2898
2749
108000
3597
3114
2961
2811
3673
3185
3030
2879
114000
3749
3243
3086
2934
3840
3317
3159
3004
AOM-1502-016
Per 5 kt above Vref (and no failure) add 222 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 3
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
4000
WEIGHT
(lb)
5000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2696
2271
2136
2006
2751
2321
2185
2053
72000
2852
2416
2278
2144
2910
2470
2331
2195
78000
3005
2559
2418
2281
3067
2617
2475
2336
84000
3156
2700
2556
2415
3222
2762
2616
2473
90000
3306
2841
2693
2549
3375
2906
2757
2611
96000
3456
2981
2831
2683
3529
3050
2898
2749
102000
3603
3120
2966
2816
3681
3192
3037
2885
108000
3751
3259
3102
2949
3839
3334
3176
3021
114000
3935
3393
3234
3078
4033
3473
3311
3154
Per 5 kt above Vref (and no failure) add 238 ft.
PRESSURE ALTITUDE (ft)
6000
WEIGHT
(lb)
7000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2807
2373
2236
2103
2865
2427
2289
2154
72000
2970
2526
2385
2249
3032
2584
2442
2304
78000
3132
2677
2533
2393
3198
2739
2593
2452
84000
3290
2825
2678
2534
3360
2891
2742
2597
90000
3447
2973
2822
2675
3522
3043
2890
2742
2887
96000
3605
3121
2967
2817
3683
3194
3039
102000
3760
3267
3110
2956
3843
3344
3186
3030
108000
3934
3413
3253
3096
4034
3494
3332
3174
114000
4136
3555
3392
3232
4244
3647
3475
3314
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 4
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 256 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
8000
WEIGHT
(lb)
9000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2925
2483
2344
2208
2987
2541
2400
2262
72000
3097
2644
2501
2361
3163
2706
2561
2419
78000
3267
2803
2656
2513
3337
2869
2720
2575
84000
3433
2959
2808
2661
3507
3029
2876
2728
90000
3598
3114
2960
2810
3677
3188
3033
2881
96000
3764
3270
3113
2959
3847
3348
3189
3034
102000
3927
3424
3263
3107
4023
3506
3344
3185
108000
4137
3578
3414
3254
4245
3664
3498
3336
114000
4356
3747
3560
3397
4472
3851
3660
3484
Per 5 kt above Vref (and no failure) add 276 ft.
PRESSURE ALTITUDE (ft)
10000
WEIGHT
(lb)
WIND (kt)
-10
0
10
20
66000
3051
2600
2457
2318
72000
3231
2769
2623
2480
78000
3410
2937
2786
2640
84000
3584
3101
2947
2797
90000
3759
3265
3107
2954
96000
3933
3429
3268
3111
102000
4126
3591
3427
3267
108000
4357
3755
3586
3422
114000
4594
3960
3764
3576
AOM-1502-016
Per 5 kt above Vref (and no failure) add 287 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 5
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
0
WEIGHT
(lb)
1000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2347
1946
1820
1697
2384
1981
1854
1731
72000
2430
2024
1896
1772
2470
2062
1933
1808
78000
2541
2128
1998
1872
2584
2169
2037
1910
84000
2651
2231
2099
1970
2696
2274
2140
2011
90000
2759
2333
2198
2067
2807
2378
2242
2110
96000
2867
2434
2297
2163
2918
2482
2344
2209
102000
2973
2534
2395
2259
3027
2584
2444
2307
108000
3082
2636
2495
2357
3139
2689
2547
2408
114000
3196
2742
2599
2458
3265
2807
2661
2520
Per 5 kt above Vref (and no failure) add 188 ft.
PRESSURE ALTITUDE (ft)
2000
WEIGHT
(lb)
3000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2423
2018
1890
1766
2465
2057
1928
1803
72000
2512
2100
1971
1845
2556
2142
2011
1884
78000
2628
2210
2078
1949
2675
2254
2121
1991
84000
2743
2318
2183
2053
2793
2365
2229
2097
90000
2857
2425
2288
2155
2910
2474
2336
2202
96000
2971
2531
2392
2257
3027
2583
2443
2306
102000
3083
2637
2495
2357
3142
2692
2549
2410
108000
3207
2753
2609
2468
3278
2819
2673
2531
114000
3336
2873
2726
2583
3410
2943
2794
2649
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 6
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 205 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
4000
WEIGHT
(lb)
5000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2508
2097
1967
1841
2552
2138
2007
1880
72000
2601
2184
2052
1924
2647
2227
2094
1965
78000
2724
2299
2165
2034
2773
2345
2210
2078
84000
2845
2412
2276
2143
2898
2462
2324
2190
90000
2965
2525
2386
2250
3021
2578
2437
2301
96000
3084
2637
2496
2358
3143
2693
2550
2411
102000
3211
2756
2612
2472
3284
2824
2678
2536
108000
3351
2887
2740
2596
3427
2958
2809
2664
114000
3487
3015
2864
2718
3567
3089
2937
2789
Per 5 kt above Vref (and no failure) add 225 ft.
PRESSURE ALTITUDE (ft)
6000
WEIGHT
(lb)
7000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2598
2180
2049
1921
2645
2224
2092
1963
72000
2696
2272
2138
2008
2746
2319
2184
2053
78000
2825
2393
2257
2124
2878
2443
2306
2172
84000
2953
2513
2374
2239
3009
2566
2426
2290
90000
3079
2632
2490
2353
3139
2689
2546
2406
96000
3214
2758
2614
2473
3287
2827
2681
2538
102000
3358
2893
2746
2602
3436
2966
2817
2671
108000
3506
3032
2881
2734
3587
3108
2956
2807
114000
3657
3166
3012
2862
3753
3246
3091
2939
AOM-1502-016
Per 5 kt above Vref (and no failure) add 242 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 7
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITHOUT ICE ACCRETION
PRESSURE ALTITUDE (ft)
8000
WEIGHT
(lb)
9000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2694
2270
2136
2006
2745
2318
2182
2051
72000
2797
2367
2231
2099
2851
2417
2280
2146
78000
2934
2495
2356
2221
2991
2548
2408
2272
84000
3068
2622
2480
2342
3129
2678
2535
2396
90000
3210
2754
2609
2469
3284
2823
2677
2534
96000
3363
2898
2750
2606
3442
2971
2821
2676
102000
3516
3040
2889
2742
3598
3118
2965
2816
108000
3671
3187
3032
2882
3759
3268
3112
2959
114000
3854
3329
3171
3018
3959
3414
3255
3099
Per 5 kt above Vref (and no failure) add 261 ft.
PRESSURE ALTITUDE (ft)
10000
WEIGHT
(lb)
WIND (kt)
-10
0
10
20
66000
2797
2366
2230
2097
72000
2906
2468
2330
2195
78000
3049
2603
2462
2324
84000
3197
2742
2597
2457
90000
3360
2895
2747
2602
96000
3522
3047
2895
2748
102000
3683
3197
3043
2892
108000
3860
3352
3194
3040
114000
4069
3502
3341
3184
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 8
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 271 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
0
WEIGHT
(lb)
1000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2734
2307
2172
2040
2787
2356
2219
2087
72000
2892
2454
2315
2181
2948
2506
2367
2230
78000
3048
2600
2458
2320
3108
2656
2513
2374
84000
3204
2746
2601
2459
3267
2805
2659
2516
90000
3357
2889
2741
2596
3424
2952
2803
2656
96000
3507
3030
2878
2730
3578
3097
2944
2794
102000
3658
3172
3017
2867
3733
3243
3086
2934
108000
3813
3311
3154
3000
3903
3385
3226
3071
114000
4010
3452
3292
3135
4107
3530
3368
3209
Per 5 kt above Vref (and no failure) add 223 ft.
PRESSURE ALTITUDE (ft)
2000
WEIGHT
(lb)
3000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2841
2406
2268
2135
2898
2459
2320
2185
72000
3006
2560
2419
2282
3067
2617
2475
2336
78000
3170
2714
2570
2429
3235
2775
2629
2487
84000
3333
2867
2719
2575
3402
2932
2782
2636
90000
3494
3018
2866
2719
3567
3086
2933
2784
96000
3651
3166
3011
2860
3728
3238
3082
2929
102000
3810
3315
3157
3003
3891
3391
3232
3076
108000
3996
3462
3301
3144
4095
3541
3379
3220
114000
4208
3617
3446
3286
4314
3712
3528
3366
AOM-1502-016
Per 5 kt above Vref (and no failure) add 239 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 9
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
4000
WEIGHT
(lb)
5000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2957
2514
2374
2237
3018
2570
2429
2291
72000
3130
2676
2532
2392
3195
2737
2591
2450
78000
3302
2838
2690
2546
3372
2902
2753
2608
84000
3474
2998
2847
2700
3547
3067
2915
2766
90000
3642
3157
3002
2851
3720
3230
3074
2921
96000
3808
3312
3155
3000
3890
3389
3230
3074
102000
3981
3470
3309
3151
4080
3551
3388
3229
108000
4197
3624
3460
3299
4304
3709
3543
3381
114000
4425
3811
3622
3448
4541
3915
3721
3535
Per 5 kt above Vref (and no failure) add 257 ft.
PRESSURE ALTITUDE (ft)
6000
WEIGHT
(lb)
7000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
3080
2629
2486
2347
3145
2690
2545
2404
72000
3262
2800
2653
2510
3332
2865
2716
2572
78000
3443
2970
2819
2672
3518
3039
2887
2738
84000
3623
3139
2984
2834
3702
3213
3057
2905
90000
3801
3305
3148
2993
3884
3384
3224
3068
96000
3975
3469
3308
3150
4063
3552
3389
3229
102000
4183
3635
3470
3309
4290
3722
3555
3393
108000
4415
3809
3629
3465
4532
3913
3721
3552
114000
4662
4023
3825
3635
4789
4136
3934
3740
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 10
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 278 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP 5 – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
8000
WEIGHT
(lb)
9000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
3213
2752
2606
2464
3281
2816
2669
2525
72000
3404
2932
2782
2636
3478
3001
2849
2701
78000
3594
3111
2957
2807
3673
3184
3029
2877
84000
3783
3289
3131
2977
3867
3367
3208
3052
90000
3970
3464
3303
3145
4058
3547
3384
3225
96000
4157
3637
3472
3311
4263
3724
3558
3395
102000
4401
3811
3643
3478
4517
3906
3733
3567
108000
4653
4021
3826
3642
4779
4134
3935
3743
114000
4921
4253
4047
3849
5059
4376
4165
3962
Per 5 kt above Vref (and no failure) add 300 ft.
PRESSURE ALTITUDE (ft)
10000
WEIGHT
(lb)
WIND (kt)
-10
0
10
20
66000
3352
2883
2734
2589
72000
3554
3072
2919
2769
78000
3754
3260
3103
2950
84000
3953
3448
3287
3130
90000
4150
3633
3468
3307
96000
4374
3815
3647
3482
102000
4638
4015
3827
3658
108000
4911
4252
4048
3852
114000
5204
4504
4289
4081
AOM-1502-016
Per 5 kt above Vref (and no failure) add 313 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 11
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
0
WEIGHT
(lb)
1000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2458
2050
1922
1797
2499
2088
1959
1834
72000
2581
2166
2035
1908
2625
2207
2075
1947
78000
2701
2278
2145
2015
2747
2322
2188
2057
84000
2820
2390
2254
2122
2869
2437
2300
2166
90000
2939
2502
2364
2229
2992
2552
2412
2277
96000
3059
2615
2474
2337
3115
2667
2525
2387
102000
3183
2731
2588
2448
3251
2795
2650
2509
108000
3318
2857
2711
2568
3389
2924
2776
2632
114000
3455
2985
2836
2691
3530
3056
2905
2758
Per 5 kt above Vref (and no failure) add 206 ft.
PRESSURE ALTITUDE (ft)
2000
WEIGHT
(lb)
3000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2540
2128
1997
1871
2585
2169
2038
1911
72000
2670
2249
2116
1987
2718
2294
2160
2030
78000
2796
2367
2232
2100
2847
2415
2278
2146
84000
2921
2485
2347
2212
2975
2535
2396
2261
90000
3047
2603
2462
2326
3104
2657
2515
2377
96000
3180
2728
2585
2445
3250
2794
2649
2507
102000
3322
2861
2714
2572
3396
2930
2782
2637
108000
3464
2993
2844
2698
3541
3066
2915
2768
114000
3614
3129
2977
2828
3706
3205
3051
2901
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 12
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 222 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
4000
WEIGHT
(lb)
5000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2631
2212
2080
1951
2678
2256
2123
1993
72000
2767
2340
2205
2073
2818
2387
2251
2119
78000
2899
2464
2326
2192
2954
2515
2376
2241
84000
3031
2588
2447
2311
3089
2642
2500
2363
90000
3169
2717
2574
2435
3240
2783
2639
2497
96000
3323
2861
2715
2572
3398
2931
2783
2639
102000
3472
3001
2852
2706
3551
3075
2924
2776
108000
3622
3141
2988
2839
3705
3219
3064
2914
114000
3802
3284
3128
2976
3902
3366
3208
3054
Per 5 kt above Vref (and no failure) add 238 ft.
PRESSURE ALTITUDE (ft)
6000
WEIGHT
(lb)
7000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2727
2302
2167
2037
2778
2349
2214
2082
72000
2870
2436
2299
2165
2925
2487
2349
2214
78000
3010
2568
2427
2291
3068
2622
2481
2343
84000
3151
2700
2557
2418
3223
2767
2623
2482
90000
3313
2852
2705
2563
3389
2923
2775
2630
96000
3476
3004
2854
2708
3556
3079
2928
2780
102000
3633
3152
2999
2849
3718
3231
3076
2925
108000
3799
3300
3143
2991
3900
3383
3225
3070
114000
4007
3451
3291
3135
4116
3539
3377
3219
AOM-1502-016
Per 5 kt above Vref (and no failure) add 256 ft.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 13
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
UNFACTORED LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MAXIMUM MANUAL BRAKING
FLAP FULL – WITH ICE ACCRETION
PRESSURE ALTITUDE (ft)
8000
WEIGHT
(lb)
9000
WIND (kt)
-10
0
10
20
-10
0
10
20
66000
2830
2398
2262
2129
2884
2449
2311
2177
72000
2981
2540
2400
2264
3039
2594
2453
2316
78000
3129
2679
2536
2397
3199
2744
2600
2459
84000
3297
2836
2690
2547
3373
2907
2759
2615
90000
3468
2996
2847
2700
3549
3072
2920
2773
96000
3639
3157
3004
2854
3725
3237
3082
2931
102000
3805
3313
3156
3003
3896
3398
3239
3084
108000
4005
3469
3309
3153
4115
3559
3397
3238
114000
4230
3641
3466
3306
4349
3747
3562
3396
Per 5 kt above Vref (and no failure) add 277 ft.
PRESSURE ALTITUDE (ft)
10000
WEIGHT
(lb)
WIND (kt)
-10
0
10
20
66000
2940
2501
2362
2226
72000
3099
2650
2508
2370
78000
3273
2813
2667
2525
84000
3452
2981
2831
2686
90000
3633
3151
2997
2847
96000
3814
3320
3163
3010
102000
4001
3486
3325
3168
108000
4229
3651
3487
3327
114000
4473
3859
3669
3489
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 14
Landing
REVISION 23
AOM-1502-016
Per 5 kt above Vref (and no failure) add 288 ft.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
LANDING DISTANCE CORRECTION FACTOR EMBRAER 190 - DRY RUNWAYS
Factor
Emerg/Abnormal
Procedure
Flaps – Speed
DUAL ENGINE FAILURE
Slat/Flap 3 – VREF
or 130 KIAS
JAMMED CONTROL
COLUMN (PITCH)
DRY +
OVSP
1.35
1.51
FULL
+ 20
Slat/Flap 5 – VREF
FULL
+ 15
1.29
1.45
JAMMED CONTROL
WHEEL (ROLL)
Slat/Flap 5 – VREF
FULL
+ 15
1.29
1.45
LOSS OF HYDRAULIC
SYSTEM 1
Slat/Flap Full – VREF
FULL
1.76
2.01
LOSS OF HYDRAULIC
SYSTEM 2
Slat/Flap Full – VREF
FULL
1.66
1.87
LOSS OF HYDRAULIC
SYSTEM 1 AND 2
Slat/Flap 5 – VREF
FULL
+ 10
2.46
2.97
LOSS OF HYDRAULIC
SYSTEM 1 AND 3
Slat/Flap 5 – VREF
FULL
+ 10
2.11
2.43
LOSS OF HYDRAULIC
SYSTEM 2 AND 3
Slat/Flap 5 – VREF
FULL
+ 10
1.96
2.20
ONE ENGINE
INOPERATIVE
APPROACH AND
LANDING
Slat/Flap 5 – VREF
FULL
+ 20
1.37
1.53
Slat/Flap 5 – VREF
FULL
+ 15
1.29
1.45
1.15
1.28
2.21
2.21
STALL PROT FAIL
Slat/Flap Full – VREF
10
FULL
+
ELEC EMERGENCY
Slat/Flap 3 – VREF
or 130 KIAS
DC BUS 1 OFF
Slat/Flap Full – VREF
FULL
1.07
1.20
DC BUS 2 OFF
Slat/Flap Full – VREF
FULL
1.10
1.25
DC ESS BUS 1 OFF
Slat/Flap Full – VREF
FULL
1.58
1.77
DC ESS BUS 2 OFF
Slat/Flap Full – VREF
FULL
1.66
1.87
GROUND SPOILERS FAIL
Slat/Flap Full – VREF
FULL
1.10
1.26
FULL
1.30
1.58
1.29
1.45
FULL
SPOILER NML MODE FAIL Slat/Flap Full – VREF
AOM-1502-016
DRY
ELEVATOR LH (RH) FAIL
Slat/Flap 5 – VREF
FULL
+ 20
+ 15
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 15
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
Flaps – Speed
PITCH TRIM FAIL
SPOILER FAULT
DRY
DRY +
OVSP
Slat/Flap 5 – VREF
FULL
+ 15
1.29
1.45
Slat/Flap 5 – VREF
FULL
+ 15
1.63
1.96
1.30
1.58
Slat/Flap Full – VREF
AILERON LH (RH) FAIL
Slat/Flap 5 – VREF
AVNX MAU 1A FAIL
Slat/Flap Full – VREF
AVNX MAU 1B FAIL
FULL
1.21
1.37
FULL
1.58
1.77
Slat/Flap Full – VREF
FULL
1.07
1.20
AVNX MAU 2B FAIL
Slat/Flap Full – VREF
FULL
1.51
1.68
AVNX MAU 3A FAIL
Slat/Flap Full – VREF
FULL
1.30
1.58
AVNX MAU 3B FAIL
Slat/Flap Full – VREF
FULL
FULL
+ 10
1.10
1.26
A-I WING FAIL or A-I WING
Slat/Flap 5 – VREF FLAP 5 ICE
1 (2) LEAK
1.25
1.40
BRK LH (RH) FAIL
Slat/Flap Full – VREF
FULL
1.51
1.68
LG WOW SYS FAIL
BRK LH
(RH)
FAULT
SMOKE/
FIRE/
FUMES
Slat/Flap Full – VREF
FULL
1.30
1.58
One side
affected
Slat/Flap Full – VREF
FULL
1.19
1.34
Both sides
affected
Slat/Flap Full – VREF
FULL
1.51
1.68
DC BUS 1
OFF and DC
Essential BUS
1 OFF
Slat/Flap 3 – VREF
DC Essential
BUS 2 and DC Slat/Flap 3 – VREF
BUS 2 OFF
FULL
+ 20
2.37
2.37
FULL
+ 20
2.55
2.55
DC Essential
BUS 3 OFF
Slat/Flap 3 – VREF
FULL
+ 20
1.35
1.51
TRU ESS and
TRU BUS
AUTO
Slat/Flap 3 – VREF
FULL
+ 20
1.35
1.51
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 16
Landing
REVISION 23
AOM-1502-016
Factor
Emerg/Abnormal
Procedure
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
LANDING DISTANCE CORRECTION FACTOR EMBRAER 190 - WET RUNWAYS - DISTANCE IN FEET
Emerg/Abnormal
Procedure
DUAL ENGINE
FAILURE
Flaps – Speed
B
K
B
2.81
2218
3.11
2372
Slat/Flap 5 – VREF
+ 15
2.63
2073
2.92
2211
Slat/Flap 5 – VREF
+ 15
2.63
2073
2.92
2211
2.84
2329
3.18
2575
2.64
2047
2.97
2313
Slat/Flap 5 – VREF
+ 10
4.91
4308
5.56
4442
Slat/Flap 5 – VREF
+ 10
3.56
3169
3.98
3458
Slat/Flap 5 – VREF
+ 10
3.33
2864
3.71
3146
Slat/Flap 5 – VREF
+ 20
2.55
1913
2.81
2067
Slat/Flap 5 – VREF
+ 15
2.63
2073
2.92
2211
Slat/Flap Full – VREF
+ 10
2.18
1450
2.43
1581
JAMMED CONTROL
WHEEL (ROLL)
FULL
LOSS OF
HYDRAULIC
SYSTEM 1 AND 2
LOSS OF
HYDRAULIC
SYSTEM 1 AND 3
LOSS OF
HYDRAULIC
SYSTEM 2 AND 3
ONE ENGINE
INOPERATIVE
APPROACH AND
LANDING
STALL PROT FAIL
WET + OVSP
K
FULL
LOSS OF
HYDRAULIC
SYSTEM 2
WET
Slat/Flap 3 – VREF
FULL + 20 or 130
KIAS
JAMMED CONTROL
COLUMN (PITCH)
LOSS OF
HYDRAULIC
SYSTEM 1
Factor
ALD = (ULD x K) – B
Slat/Flap Full – VREF
FULL
Slat/Flap Full – VREF
FULL
FULL
FULL
FULL
FULL
FULL
AOM-1502-016
FULL
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 17
PERFORMANCE
Emerg/Abnormal
Procedure
AIRPLANE
OPERATIONS
MANUAL
Flaps – Speed
Factor
ALD = (ULD x K) – B
WET
WET + OVSP
K
B
K
B
3.87
2175
5.01
3691
2.38
1804
2.67
2014
2.54
2011
2.86
2274
2.82
2100
3.12
2231
3.03
2349
3.37
2497
GROUND SPOILERS Slat/Flap Full – VREF
FAIL
FULL
2.21
1716
2.52
1913
SPOILER NML
MODE FAIL
2.92
2612
3.67
3343
FULL
ELEVATOR LH (RH)
FAIL
Slat/Flap 5 – VREF
+ 15
2.63
2073
2.92
2211
FULL
Slat/Flap 5 – VREF
+ 15
2.63
2073
2.92
2211
Slat/Flap 5 – VREF
+ 15
3.74
3271
4.27
3471
2.92
2612
3.43
2927
2.49
2001
2.77
2142
3.44
2828
3.76
2976
2.06
1522
2.33
1693
3.21
2549
3.50
2677
2.92
2612
3.43
2927
ELEC EMERGENCY
DC BUS 1 OFF
Slat/Flap 3 – VREF
FULL + 20 or
130 KIAS
Slat/Flap Full – VREF
FULL
DC BUS 2 OFF
Slat/Flap Full – VREF
FULL
DC ESS BUS 1 OFF
Slat/Flap Full – VREF
FULL
DC ESS BUS 2 OFF
Slat/Flap Full – VREF
FULL
PITCH TRIM FAIL
Slat/Flap Full – VREF
FULL
SPOILER FAULT
FULL
Slat/Flap Full – VREF
FULL
AILERON LH (RH)
FAIL
AVNX MAU 1A FAIL
Slat/Flap 5 – VREF
+ 10
FULL
Slat/Flap Full – VREF
FULL
AVNX MAU 1B FAIL
Slat/Flap Full – VREF
FULL
AVNX MAU 2B FAIL
Slat/Flap Full – VREF
FULL
AVNX MAU 3A FAIL
Slat/Flap Full – VREF
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 18
Landing
REVISION 23
AOM-1502-016
FULL
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
Emerg/Abnormal
Procedure
Flaps – Speed
Factor
ALD = (ULD x K) – B
WET
WET + OVSP
K
B
K
B
2.21
1716
2.52
1913
3.00
2854
3.30
3009
3.21
2549
3.50
2677
2.94
2513
3.44
2749
2.81
2234
3.09
2382
3.21
2549
3.50
2677
3.78
2388
4.41
3258
Slat/Flap 3 – VREF
FULL + 20
4.07
2589
4.80
3586
DC
Slat/Flap 3 – VREF
Essential
FULL + 20
BUS 3 OFF
2.81
2218
3.11
2372
TRU ESS
and TRU
BUS AUTO
2.81
2218
3.11
2372
AVNX MAU 3B FAIL
Slat/Flap Full – VREF
FULL
A-I WING FAIL or A-I
WING 1 (2) LEAK
BRK LH (RH) FAIL
Slat/Flap 5 – VREF
FLAP 5 ICE
Slat/Flap Full – VREF
FULL
LG WOW SYS FAIL
Slat/Flap Full – VREF
FULL
One side
BRK LH
affected
(RH)
Both sides
FAULT
affected
Slat/Flap Full – VREF
FULL
Slat/Flap Full – VREF
FULL
DC BUS 1
OFF and
Slat/Flap 3 – VREF
DC
FULL + 20
Essential
BUS 1 OFF
AOM-1502-016
DC
Essential
SMOKE/
BUS 2 and
FIRE/
DC BUS 2
FUMES
OFF
Slat/Flap 3 – VREF
FULL + 20
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 19
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP (SLAT) FAIL - EMBRAER 190 - DRY RUNWAYS
The Actual Landing Distance is equal to the Unfactored Landing Distance
for flaps FULL multiplied by the associated landing distance factor for
DRY runways.
Refer to the following tables for reference speed and factor to be applied
to the unfactored landing distance, for a flap/slat fail or a flap/slat fail
with shaker anticipated:
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - DRY RUNWAY
VREF (KIAS)
0
Factor
VREF (KIAS)
1
Factor
VREF (KIAS)
2
Factor
VREF (KIAS) 3 (4)
(5)
Factor
VREF (KIAS)
FULL
Factor
0
VREF FULL+60
1.90
VREF FULL+35
1.52
VREF FULL+30
1.44
NOT
SELECTABLE
SLAT
1 (2) (3)
VREF FULL+50
1.77
VREF FULL+35
1.56
VREF FULL+25
1.39
VREF FULL+20
1.35
VREF FULL+5
1.08
4 (5 ) (FULL)
VREF FULL+50
1.81
VREF FULL+35
1.58
VREF FULL+25
1.41
VREF FULL+10
1.22
VREF FULL
1.00
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 20
Landing
REVISION 23
AOM-1502-016
FLAP
AIRPLANE
OPERATIONS
MANUAL
FLAP/SLAT
PERFORMANCE
FAIL WITH SHAKER ANTICIPATED
CONFIGURATION TABLE - DRY RUNWAY
FLAP
VREF (KIAS)
0
Factor
VREF (KIAS)
1
Factor
VREF (KIAS)
2
Factor
VREF (KIAS) 3 (4)
(5)
Factor
VREF (KIAS)
FULL
Factor
0
VREF FULL+60
1.90
VREF FULL+40
1.60
VREF FULL+30
1.44
NOT
SELECTABLE
SLAT
1 (2) (3)
VREF FULL+60
1.95
VREF FULL+40
1.63
VREF FULL+30
1.47
VREF FULL+20
1.35
VREF FULL+5
1.08
LANDING
4 (5 ) (FULL)
VREF FULL+60
1.99
VREF FULL+40
1.66
VREF FULL+30
1.49
VREF FULL+15
1.29
VREF FULL
1.00
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED
FLAP
AOM-1502-016
VREF (KIAS)
0
Factor
VREF (KIAS)
1
Factor
VREF (KIAS)
2
Factor
VREF (KIAS) 3 (4)
(5)
Factor
VREF (KIAS)
FULL
Factor
0
VREF FULL+60
2.08
VREF FULL+35
1.67
VREF FULL+30
1.58
NOT
SELECTABLE
SLAT
1 (2) (3)
VREF FULL+50
1.95
VREF FULL+35
1.71
VREF FULL+25
1.54
VREF FULL+20
1.51
VREF FULL+5
1.20
4 (5 ) (FULL)
VREF FULL+50
1.99
VREF FULL+35
1.74
VREF FULL+25
1.57
VREF FULL+10
1.37
VREF FULL
1.11
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 21
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - DRY RUNWAY + 10 kt OVERSPEED
VREF (KIAS)
0
Factor
VREF (KIAS)
1
Factor
VREF (KIAS)
2
Factor
VREF (KIAS) 3 (4)
(5)
Factor
VREF (KIAS)
FULL
Factor
0
VREF FULL+60
2.08
VREF FULL+40
1.74
VREF FULL+30
1.58
NOT
SELECTABLE
SLAT
1 (2) (3)
VREF FULL+60
2.14
VREF FULL+40
1.79
VREF FULL+30
1.62
VREF FULL+20
1.51
VREF FULL+5
1.20
4 (5 ) (FULL)
VREF FULL+60
2.18
VREF FULL+40
1.82
VREF FULL+30
1.64
VREF FULL+15
1.45
VREF FULL
1.11
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 22
Landing
REVISION 23
AOM-1502-016
FLAP
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
FLAP (SLAT) FAIL - LANDING CONFIGURATION TABLE
- WET RUNWAYS
The WET + OVSP corresponds to the factor associated to a 10 kt
overspeed (above the non-normal VREF) on a wet runway.
To calculate the actual landing distance on a WET runway, the pilot must
do the steps below:
1. Recognize the FLAP/SLAT position;
2. Find the Unfactored Landing Distance (ULD) for Flaps Full in Quick
Reference Handbook (QRH), considering the airplane type, altitude,
landing weight and ice accretion condition;
3.
Find the multiplier factor value (K) on the table with FLAP/SLAT Fail
- Landing Configuration and multiply the obtained values of (ULD)
and (K).
4. In the same line of table with FLAP/SLAT Fail - Landing
Configuration, find the value (B).
5.
Subtract (B) from the result of step (3). This is the actual landing
distance (ALD) to safely land the airplane on wet runways condition.
ALD = (ULD x K) – B
AOM-1502-016
NOTE: The calculated value is the actual distance to safely land the
airplane, but no distance margins are included. The distance
margin available is the difference between the runway length
and the calculated value.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 23
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP (SLAT) FAIL - EMBRAER 190 - WET RUNWAYS
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - WET RUNWAY
ALD = (ULD x K) – B
0
Factor
VREF
(KIAS)
0
1 (2) (3)
4 (5) (FULL)
VREF FULL+60
VREF FULL+50
VREF FULL+50
K
4.31
K
3.95
K
3.95
B
3337
B
3064
B
3009
VREF FULL+35
VREF FULL+35
VREF FULL+35
Factor
K
3.37
K
3.38
K
3.38
VREF
(KIAS)
VREF FULL+30
VREF FULL+25
VREF FULL+25
K
3.13
K
2.98
K
2.99
1
2
Factor
VREF
(KIAS)
B
2707
B
2513
3
Factor
VREF
(KIAS)
4 (5)
Factor
VREF
(KIAS)
NOT
USABLE
B
2664
B
2388
VREF FULL+10
K
2.81
K
2.53
B
2218
B
2051
VREF FULL+20
VREF FULL+10
K
2.77
K
2.49
K
2.05
Factor
B
2372
VREF FULL+20
B
2159
VREF FULL+5
FULL
B
2631
B
1434
B
2001
VREF FULL
K
1.94
B
1280
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 24
Landing
REVISION 23
AOM-1502-016
Distance
in feet
VREF
(KIAS)
SLAT →
FLAP ↓
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP/SLAT
FAIL WITH SHAKER ANTICIPATED
CONFIGURATION TABLE - WET RUNWAY
LANDING
ALD = (ULD x K) – B
Distance
in feet
VREF
(KIAS)
SLAT →
FLAP ↓
1 (2) (3)
VREF FULL+60
0
Factor
VREF
(KIAS)
0
K
4.31
B
3337
VREF FULL+40
1
Factor
K
3.54
VREF
(KIAS)
VREF FULL+30
2
Factor
VREF
(KIAS)
K
3.13
B
2808
B
2513
3
4 (5)
Factor
VREF
(KIAS)
K
4.29
B
3245
K
4.28
B
3176
VREF FULL+40 VREF FULL+40
K
3.54
B
2756
K
3.54
B
2717
VREF FULL+30 VREF FULL+30
K
3.14
K
2.81
NOT
USABLE
B
2480
B
2218
K
3.14
B
2454
K
2.67
B
2126
VREF FULL+20 VREF FULL+15
K
2.77
B
2159
VREF FULL+5
FULL
K
2.05
Factor
AOM-1502-016
VREF FULL+60 VREF FULL+60
VREF FULL+20 VREF FULL+15
Factor
VREF
(KIAS)
4 (5) (FULL)
B
1434
K
2.63
B
2073
VREF FULL
K
1.94
B
1280
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 25
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP/SLAT FAIL WITHOUT SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED
ALD = (ULD x K) – B
SLAT →
FLAP ↓
0
Factor
VREF
(KIAS)
0
1 (2) (3)
4 (5) (FULL)
VREF FULL+60
VREF FULL+50 VREF FULL+50
K
4.65
K
4.29
B
3520
B
3245
K
4.28
B
3176
VREF FULL+35
VREF FULL+35 VREF FULL+35
Factor
K
3.71
K
3.70
VREF
(KIAS)
VREF FULL+30
VREF FULL+25 VREF FULL+25
K
3.45
K
3.30
1
2
Factor
VREF
(KIAS)
B
2904
B
2700
3
4 (5)
Factor
VREF
(KIAS)
B
2569
K
3.70
K
3.30
B
2799
B
2536
VREF FULL+20 VREF FULL+10
K
3.11
Factor
VREF
(KIAS)
B
2844
NOT
USABLE
B
2372
K
3.05
K
2.29
Factor
B
2201
VREF FULL+20 VREF FULL+10
B
2300
VREF FULL+5
FULL
K
2.82
B
1585
K
2.77
B
2142
VREF FULL
K
2.18
B
1410
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 26
Landing
REVISION 23
AOM-1502-016
Distance
in feet
VREF
(KIAS)
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
FLAP/SLAT FAIL WITH SHAKER ANTICIPATED LANDING
CONFIGURATION TABLE - WET RUNWAY + 10 kt OVERSPEED
ALD = (ULD x K) – B
Distance
in feet
VREF
(KIAS)
SLAT →
FLAP ↓
0
Factor
VREF
(KIAS)
0
1 (2) (3)
4 (5) (FULL)
VREF FULL+60
VREF FULL+60
VREF FULL+60
K
4.65
K
4.63
K
4.62
B
3520
B
3330
VREF FULL+40
VREF FULL+40
VREF FULL+40
Factor
K
3.87
K
3.87
K
3.86
VREF
(KIAS)
VREF FULL+30
VREF FULL+30
VREF FULL+30
K
3.45
K
3.45
K
3.45
1
2
Factor
VREF
(KIAS)
B
2999
B
2700
3
Factor
VREF
(KIAS)
4 (5)
Factor
VREF
(KIAS)
NOT
USABLE
B
2930
B
2654
B
2877
B
2615
VREF FULL+20
VREF FULL+15
K
3.11
K
2.96
B
2372
B
2274
VREF FULL+20
VREF FULL+15
K
3.05
K
2.92
B
2300
VREF FULL+5
FULL
K
2.29
Factor
AOM-1502-016
B
3412
B
1585
B
2211
VREF FULL
K
2.18
B
1410
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 27
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE
NOTE: The operational landing tables are intended for in-flight
assessment, not for dispatch.
The operational landing distance tables contained herein are based on
FAA AC 25.32. The data do not include any multiplication factor or
additional safety margin.
The distances are obtained from 50 ft above threshold until full airplane
stop and consider credit for all thrust reversers.
NOTE: Local operational regulations may require an additional factor to
these distances. Emergency/abnormal multiplication factors
were not analyzed for contaminated runways. For
Emergency/Abnormal Operation refer to the Unfactored Landing
Distance chapter.
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 28
Landing
REVISION 23
AOM-1502-016
In order to make the in-flight assessment if the runway condition is
reported, the Runway Condition Assessment Matrix (RCAM) is used. It
offers a correlation between runway condition and the pilot report
(PIREP). The maximum recommended crosswinds are also presented
in relation to each PIREP. Gust effects are not included and do not affect
the recommended crosswind values.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
RUNWAY CONDITION ASSESSMENT MATRIX
Assessment Criteria
AOM-1502-016
ICAO
Runway Condition Description
Code
6 – Dry
– Frost
– Wet (Includes Damp and
1/8” (3 mm) or less depth of
Water)
5
1/8’’ (3 mm) or less depth of:
– Slush
– Dry snow
– Wet snow
-15ºC and colder outside air
4 temperature:
– Compacted snow
– Wet (“Slippery when wet”
runway)
– Dry snow or wet snow (any
depth) over compacted
snow
Greater than 1/8’’ (3 mm)
3
depth of:
– Dry snow
– Wet snow
Warmer than -15ºC outside air
temperature:
– Compacted Snow
Greater than 1/8’’ (3 mm)
depth of:
2
– Water
– Slush
1 Ice
Downgrade
Assessment
Criteria
PIREP
Max.
Recomm.
Crosswind
(kt)
-
38
Good
31
Good to
Medium
20
Medium
15
Medium to
Poor
12
Poor
08
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 29
PERFORMANCE
0
AIRPLANE
OPERATIONS
MANUAL
– Wet ice
– Water on top of compacted
snow
– Dry snow or wet snow over
ice
Nil
Not applicable
(No
operations in
Nil condition)
The operational landing tables must be entered with runway braking
action, landing flaps, ice condition, autobrakes configuration, current
landing weight, landing field pressure altitude, temperature, wind, slope,
airplane overspeed above VREF and thrust reversers.
As an example, assume the following condition for the EMBRAER 190:
– Reported braking action: Good to Medium
– No ice conditions
– Flaps: 5
– Autobrakes: OFF (Max Manual)
– Landing weight: 85000 lb
– Airport Pressure Altitude: 3000 ft
– ISA -25°C
– Wind: 10 kt headwind
– Slope: 0%
– VREF + 5 kt at threshold
– All thrust reversers use
In the Good to Medium braking action, find the corresponding table for
flaps 5 and no ice accretion. In the MAX MANUAL braking line, find the
reference weight and distance in the first column. These values are:
– REF DIST = 4918 ft
Next correction regards the airplane actual landing weight. Take the
difference from the reference weight to the actual weight. In this case,
the actual landing weight is 9000 lb below the reference. The correction
is -41 ft for each 1000 lb below the reference correction:
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 30
Landing
REVISION 23
AOM-1502-016
– Reference weight = 94000 lb
AIRPLANE
OPERATIONS
MANUAL
PERFORMANCE
– Weight correction = 4918 - (41 x 9) = 4549 ft
Next correction is pressure altitude. The value is 144 ft for each 1000 ft
above Sea Level. Apply the correction for 3000 ft:
– Altitude correction = 4549 + (144 x 3) = 4981 ft
Next correction is temperature. The value is -31 ft for each 5ºC below
ISA, apply the correction for ISA -25°C:
– Temperature correction = 4981 - [(25 ÷ 5) x 31] = 4826 ft
Next correction is wind. The value is -110 ft for each 5 kt headwind,
apply the correction for 10 kt headwind:
– Wind correction = 4826 - [(10 ÷ 5) x 110] = 4606 ft
Next correction would be the slope. Since the slope is 0%, there is no
correction. We go directly to the VREF correction. Considering an
overspeed correction of 474 ft for each 5 kt above VREF:
– Overspeed correction = 4606 + 474 = 5080 ft
The last correction regards the thrust reverser. Since both reversers are
used, no correction is necessary.
The required landing distance is then 5080 ft.
AOM-1502-016
NOTE: In case the airplane lands above the Maximum Landing Weight
(MLW), the overweight correction in the footer is necessary.
Proceed as follows: Take the reference landing distance in the
first column; skip the weight correction and do all other
corrections. At last, apply the footer overweight correction
considering the actual weight above the AFM MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 31
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
DRY (6)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
3444
-26
25
87
-31
60
-78
323
-26
464
365
85
HI
4062
-31
29
96
-34
67
-88
351
-12
412
377
32
MED
4999
-41
40
130
-46
91
-114
478
-12
396
490
7
LOW
7284
-65
64
212
-72
150
-177
795
-30
423
811
6
-80
365
-28
503
385
111
For overweight landing add 127 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
3801
-29
29
97
-34
67
HI
4499
-34
33
107
-38
75
-91
370
-12
442
397
49
MED
5586
-46
45
147
-52
103
-119
502
-12
423
510
8
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
For overweight landing add 134 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
3091
-23
22
170
0
116
-16
360
0
288
270
131
HI
3724
-27
26
209
0
142
-12
426
0
297
343
151
MED
4551
-36
34
275
0
187
-14
554
0
319
450
200
LOW
6565
-58
55
437
0
297
-18
874
0
394
711
318
310
-22
435
336
67
For overweight landing add 48 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
3326
-25
24
83
-30
57
-76
HI
4022
-30
29
95
-33
66
-87
349
-8
389
370
11
MED
4949
-40
39
128
-45
90
-113
476
-10
376
486
9
LOW
7204
-64
63
209
-71
149
-176
790
-27
403
807
8
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 32
Landing
REVISION 23
AOM-1502-016
For overweight landing add 126 ft per 1000 lb above MLW.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
GOOD REPORTED BRAKING ACTION (5)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
hill
VREF
REV
per
rev
inop
ISA
ISA
wind
wind
MAX MAN
4315
-41
41
153
-39
110
-107
630
-39
695
528
560
HI
4627
-41
41
151
-39
107
-111
629
-40
686
529
585
MED
4999
-41
40
134
-46
102
-114
623
-12
665
529
585
LOW
7284
-65
64
212
-72
150
-177
795
-30
423
811
6
662
-44
752
522
661
For overweight landing add 151 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
4831
-46
47
175
-44
124
-113
HI
5149
-46
46
173
-44
121
-117
662
-45
743
526
691
MED
5586
-46
45
149
-52
116
-119
656
-12
723
526
690
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
For overweight landing add 170 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
3745
-34
33
204
0
137
-35
469
0
379
354
327
HI
4120
-34
34
217
0
145
-36
494
0
359
346
302
MED
4551
-36
34
275
0
187
-14
554
0
319
450
200
LOW
6565
-58
55
437
0
297
-18
874
0
394
711
318
For overweight landing add 115 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
4072
-38
37
139
-35
100
-102
583
-31
619
460
383
HI
4458
-39
38
140
-36
99
-107
590
-33
618
472
422
MED
4949
-40
39
128
-45
90
-113
539
-10
596
473
418
LOW
7204
-64
63
209
-71
149
-176
790
-27
403
807
8
AOM-1502-016
For overweight landing add 127 ft per 1000 lb above MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 33
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
GOOD TO MEDIUM REPORTED BRAKING ACTION (4)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
4918
-41
39
144
-31
98
-110
554
-70
703
474
569
HI
5250
-42
40
147
-33
99
-117
569
-72
701
441
579
MED
5343
-43
41
145
-40
100
-124
573
-55
655
490
525
LOW
7284
-65
64
212
-72
150
-177
795
-30
423
811
6
574
-73
746
518
667
For overweight landing add 151 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
5396
-45
43
160
-34
109
-113
HI
5746
-47
44
163
-36
109
-119
589
-75
743
479
694
MED
5930
-48
47
162
-46
113
-129
597
-55
670
516
627
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
For overweight landing add 170 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
4341
-34
33
187
0
125
-64
493
0
432
303
179
HI
4718
-36
34
206
0
137
-64
529
0
411
331
186
MED
4843
-37
36
253
0
172
-44
584
0
369
423
178
LOW
6565
-58
55
437
0
297
-18
874
0
394
711
318
-107
532
-58
645
388
350
For overweight landing add 106 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
4651
-38
36
133
-29
91
HI
5047
-40
38
138
-32
93
-114
552
-62
646
404
324
MED
5241
-42
40
140
-40
98
-123
563
-46
581
492
147
LOW
7204
-64
63
209
-71
149
-176
790
-27
403
807
8
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 34
Landing
REVISION 23
AOM-1502-016
For overweight landing add 126 ft per 1000 lb above MLW.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MEDIUM REPORTED BRAKING ACTION (3)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
hill
VREF
REV
per
rev
inop
ISA
ISA
wind
wind
MAX MAN
5438
-45
43
165
-35
112
-127
646
-111
856
466
479
HI
5731
-46
44
167
-37
111
-133
660
-112
854
476
508
MED
5736
-46
44
166
-38
111
-135
660
-105
854
477
506
LOW
7301
-65
64
211
-72
150
-175
795
-46
568
815
15
For overweight landing add 122 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
5944
-50
48
183
-39
123
-130
669
-115
905
460
550
HI
6257
-51
49
185
-41
122
-136
682
-116
900
470
584
MED
6301
-51
49
182
-45
123
-141
683
-98
888
500
525
LOW
8251
-74
74
241
-82
172
-186
842
-48
597
854
17
For overweight landing add 136 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
4781
-37
36
199
0
133
-79
555
-5
541
349
303
HI
5129
-39
37
218
0
145
-79
589
0
520
345
286
MED
5155
-39
38
241
0
163
-68
616
0
468
402
221
LOW
6574
-57
55
428
0
291
-23
871
0
436
704
311
For overweight landing add 97 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
5110
-42
40
151
-33
103
-124
620
-94
780
415
347
HI
5477
-44
41
156
-35
105
-130
637
-96
780
432
383
MED
5548
-44
42
154
-40
106
-135
640
-81
748
486
294
LOW
7212
-64
63
209
-70
149
-177
792
-39
521
809
17
AOM-1502-016
For overweight landing add 122 ft per 1000 lb above MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 35
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
MEDIUM TO POOR REPORTED BRAKING ACTION (2)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
6138
-61
60
248
-54
170
-165
1065
-139
1454
618
1668
HI
6263
-59
60
244
-60
166
-157
1069
-143
1431
638
1656
MED
6263
-59
60
244
-60
166
-157
1069
-143
1431
638
1656
LOW
7301
-65
64
215
-72
159
-175
994
-46
1251
800
1597
For overweight landing add 197 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
6760
-66
66
274
-64
185
-177
1093
-163
1526
590
1522
HI
6913
-66
66
271
-64
181
-174
1097
-156
1507
609
1517
MED
6913
-66
66
271
-64
181
-174
1097
-156
1507
609
1517
LOW
8251
-74
74
245
-82
181
-186
1036
-48
1281
833
1185
For overweight landing add 208 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
5238
-50
49
286
0
191
-62
736
0
871
516
1202
HI
5466
-49
49
292
0
196
-57
736
0
843
539
1220
MED
5466
-49
49
293
0
197
-54
736
0
837
539
1218
LOW
6574
-57
55
428
0
291
-23
871
0
436
704
311
For overweight landing add 214 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
5646
-55
54
215
-49
149
-151
967
-114
1205
528
1242
HI
5895
-54
54
216
-56
149
-151
977
-125
1197
552
1277
MED
5895
-54
54
216
-55
149
-149
977
-112
1197
552
1277
LOW
7212
-64
63
209
-70
149
-177
885
-39
982
815
847
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 36
Landing
REVISION 23
AOM-1502-016
For overweight landing add 213 ft per 1000 lb above MLW.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
POOR REPORTED BRAKING ACTION (1)
Flap 5 - No Ice Accretion
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
7588
-57
56
248
-53
165
-207
1083
-402
2170
483
873
HI
7772
-58
56
247
-53
163
-211
1090
-398
2155
496
888
MED
7772
-58
56
247
-53
163
-211
1090
-398
2155
496
888
LOW
8480
-66
65
250
-68
178
-229
1131
-327
1858
781
549
For overweight landing add 155 ft per each 1000 lb above MLW.
Flap 5 - Ice Accretion
MAX MAN
8172
-63
62
271
-58
179
-212
1110
-411
2139
468
878
HI
8379
-63
62
270
-58
176
-215
1117
-408
2127
483
900
MED
8379
-63
62
270
-58
176
-215
1117
-408
2127
483
900
LOW
9431
-75
74
280
-78
199
-240
1178
-328
1780
786
393
For overweight landing add 164 ft per 1000 lb above MLW.
Flap FULL - No Ice Accretion
MAX MAN
6591
-48
48
232
-13
157
-165
915
-254
1835
503
688
HI
6857
-49
49
250
-7
168
-163
890
-240
1764
522
718
MED
6857
-49
49
250
-7
168
-163
890
-240
1764
522
718
LOW
7570
-58
56
386
0
268
-116
1056
-74
1159
651
258
For overweight landing add 133 ft per 1000 lb above MLW.
Flap FULL - Ice Accretion
MAX MAN
6969
-54
52
222
-49
150
-204
1029
-332
1912
489
713
HI
7256
-55
53
224
-50
150
-209
1043
-332
1908
510
697
MED
7256
-55
53
224
-50
150
-209
1043
-332
1908
510
697
LOW
8208
-66
64
240
-63
172
-228
1106
-276
1689
777
369
AOM-1502-016
For overweight landing add 131 ft per 1000 lb above MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 37
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
CAT II
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
FLAP 5 - WITH / WITHOUT ICE ACCRETION
DRY (6)
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
hill
VREF
REV
per
rev
inop
ISA
ISA
wind
wind
MAX MAN
3801
-29
29
97
-34
67
-80
365
-28
503
385
111
HI
4499
-34
33
107
-38
75
-91
370
-12
442
397
49
MED
5586
-46
45
147
-52
103
-119
502
-12
423
510
8
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
752
522
661
For overweight landing add 134 ft per each 1000 lb above MLW.
GOOD REPORTED BRAKING ACTION (5)
MAX MAN
4831
-46
47
175
-44
124
-113
662
-44
HI
5149
-46
46
173
-44
121
-117
662
-45
743
526
691
MED
5586
-46
45
149
-52
116
-119
656
-12
723
526
690
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
For overweight landing add 170 ft per each 1000 lb above MLW.
GOOD TO MEDIUM REPORTED BRAKING ACTION (4)
MAX MAN
5396
-45
43
160
-34
109
-113
574
-73
746
518
HI
5746
-47
44
163
-36
109
-119
589
-75
743
479
667
694
MED
5930
-48
47
162
-46
113
-129
597
-55
670
516
627
LOW
8235
-74
74
241
-82
172
-187
842
-31
451
851
7
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 38
Landing
REVISION 23
AOM-1502-016
For overweight landing add 170 ft per each 1000 lb above MLW.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
CAT II
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
FLAP 5 - WITH / WITHOUT ICE ACCRETION
MEDIUM REPORTED BRAKING ACTION (3)
REF
WEIGHT
ALT
94000
per 1000 lb
per
TEMP
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
per 5ºC
above
weight
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
5944
-50
48
183
-39
123
-130
669
-115
905
460
550
HI
6257
-51
49
185
-41
122
-136
682
-116
900
470
584
MED
6301
-51
49
182
-45
123
-141
683
-98
888
500
525
LOW
8251
-74
74
241
-82
172
-186
842
-48
597
854
17
For overweight landing add 136 ft per each 1000 lb above MLW.
MEDIUM TO POOR REPORTED BRAKING ACTION (2)
MAX MAN
6760
-66
66
274
-64
185
-177
1093
-163
1526
590
1522
HI
6913
-66
66
271
-64
181
-174
1097
-156
1507
609
1517
MED
6913
-66
66
271
-64
181
-174
1097
-156
1507
609
1517
LOW
8251
-74
74
245
-82
181
-186
1036
-48
1281
833
1185
For overweight landing add 208 ft per each 1000 lb above MLW.
POOR REPORTED BRAKING ACTION (1)
MAX MAN
8172
-63
62
271
-58
179
-212
1110
-411
2139
468
878
HI
8379
-63
62
270
-58
176
-215
1117
-408
2127
483
900
MED
8379
-63
62
270
-58
176
-215
1117
-408
2127
483
900
LOW
9431
-75
74
280
-78
199
-240
1178
-328
1780
786
393
AOM-1502-016
For overweight landing add 164 ft per each 1000 lb above MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 39
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
Autoland/HUD A3
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
FLAP 5 - WITH / WITHOUT ICE ACCRETION
DRY (6)
REF
WEIGHT
ALT
94000
per 1000 lb
per
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
weight
TEMP
per 5ºC
above
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
hill
VREF
REV
per
rev
inop
ISA
ISA
wind
wind
MAX MAN
3951
-31
30
99
-36
70
-83
377
-30
532
414
3
HI
4585
-35
34
109
-39
76
-93
375
-11
482
418
9
MED
5672
-47
46
148
-52
104
-120
507
-12
444
515
9
LOW
8321
-75
75
243
-82
173
-189
846
-31
472
856
8
773
527
661
For overweight landing add 132 ft per 1000 lb above MLW.
GOOD REPORTED BRAKING ACTION (5)
MAX MAN
4918
-47
47
176
-44
125
-115
666
-44
HI
5235
-47
47
174
-45
122
-118
667
-45
763
531
691
MED
5672
-47
46
151
-52
117
-120
660
-12
744
531
690
LOW
8321
-75
75
243
-82
173
-189
846
-31
472
856
8
For overweight landing add 171 ft per 1000 lb above MLW.
GOOD TO MEDIUM REPORTED BRAKING ACTION (4)
MAX MAN
5482
-46
44
162
-35
110
-114
578
-73
767
523
667
HI
5833
-47
45
165
-37
110
-121
593
-75
764
484
694
MED
6016
-49
47
163
-46
114
-130
602
-55
691
521
627
LOW
8321
-75
75
243
-82
173
-189
846
-31
472
856
8
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 40
Landing
REVISION 23
AOM-1502-016
For overweight landing add 171 ft per 1000 lb above MLW.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
OPERATIONAL LANDING DISTANCE (ft)
Autoland/HUD A3
EMBRAER 190 – CF34-10E5/10E5A1/10E6/10E6A1
FLAP 5 - WITH / WITHOUT ICE ACCRETION
MEDIUM REPORTED BRAKING ACTION (3)
REF
WEIGHT
ALT
94000
per 1000 lb
per
TEMP
BRK
lb
blw/abv 94000 lb
1000 ft
CONF
landing
per 5ºC
above
weight
below
above
SL
WIND
per 5 kt
SLOPE
per 1 %
VREF
per 5
kt
below above
head
tail
uphill
down
above
REV
per
rev
inop
ISA
ISA
wind
wind
hill
VREF
MAX MAN
6031
-50
48
184
-39
124
-131
673
-115
926
466
550
HI
6343
-51
49
186
-41
123
-137
686
-116
921
475
584
MED
6387
-52
50
183
-46
124
-142
687
-97
909
505
525
LOW
8338
-75
74
242
-82
173
-187
846
-48
617
859
17
For overweight landing add 137 ft per 1000 lb above MLW.
MEDIUM TO POOR REPORTED BRAKING ACTION (2)
MAX MAN
6847
-67
67
275
-65
186
-179
1097
-162
1547
595
1522
HI
6999
-66
66
272
-64
182
-176
1101
-156
1528
614
1517
MED
6999
-66
66
272
-64
182
-176
1101
-156
1528
614
1517
LOW
8338
-75
74
246
-82
182
-187
1041
-48
1302
837
1185
For overweight landing add 209 ft per 1000 lb above MLW.
POOR REPORTED BRAKING ACTION (1)
MAX MAN
8258
-64
63
272
-59
180
-213
1115
-411
2160
472
878
HI
8466
-64
63
271
-59
177
-217
1122
-408
2148
487
900
MED
8466
-64
63
271
-59
177
-217
1122
-408
2148
487
900
LOW
9517
-75
75
281
-79
200
-241
1182
-328
1711
789
481
AOM-1502-016
For overweight landing add 165 ft per 1000 lb above MLW.
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 41
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT
For normal operation, the brake temperature can be monitored through
the brake temperature indication in the MFD.
The Quick Turn Around Weight Table must be used only when the brake
temperature indication is not working properly (according to the MMEL).
In this case, if the landing weight exceeds the Quick Turn Around
Weight, a subsequent takeoff must not be performed before 22 minutes
after chocks on. At the end of this time interval, check that the wheel
thermal plugs have not melted.
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 42
Landing
REVISION 23
AOM-1502-016
NOTE: If the tires are not flat after 22 minutes, this is a positive
indication that the wheel thermal plugs have not melted.
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITHOUT ICE ACCRETION
ALTITUDE
0 ft
Temp
1000 ft
(°C)
WIND
AOM-1502-016
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114199 114199 114199 114199
-10
114199 114199 114199 114199 113583 114199 114199 114199
-5
114199 114199 114199 114199 112570 114199 114199 114199
0
113493 114199 114199 114199 111567 114199 114199 114199
5
112503 114199 114199 114199 110589 114199 114199 114199
10
111536 114199 114199 114199 109633 114199 114199 114199
15
110590 114199 114199 114199 108700 114199 114199 114199
20
109667 114199 114199 114199 107803 114199 114199 114199
25
108766 114199 114199 114199 106963 114199 114199 114199
30
107891 114199 114199 114199 106096 114199 114199 114199
35
107079 114199 114199 114199 105244 114199 114199 114199
40
106244 114199 114199 114199 104412 114199 114199 114199
45
105419 114199 114199 114199 103600 113372 114199 114199
50
104614 114199 114199 114199 102849 112480 114199 114199
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 43
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITHOUT ICE ACCRETION
ALTITUDE
2000 ft
Temp
(°C)
3000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
113710 114199 114199 114199 111773 114199 114199 114199
-15
112673 114199 114199 114199 110728 114199 114199 114199
-10
111653 114199 114199 114199 109708 114199 114199 114199
-5
110643 114199 114199 114199 108706 114199 114199 114199
0
109655 114199 114199 114199 107744 114199 114199 114199
5
108688 114199 114199 114199 106839 114199 114199 114199
10
107761 114199 114199 114199 105906 114199 114199 114199
15
106889 114199 114199 114199 104997 114199 114199 114199
20
105991 114199 114199 114199 104108 113942 114199 114199
25
105113 114199 114199 114199 103261 112970 114199 114199
30
104253 114104 114199 114199 102458 112019 114199 114199
35
103425 113161 114199 114199 101629 111090 114199 114199
40
102649 112241 114199 114199 100850 110181 113480 114199
45
101854 111341 114199 114199
---
---
---
---
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 44
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITHOUT ICE ACCRETION
ALTITUDE
4000 ft
Temp
(°C)
-10 kt
AOM-1502-016
5000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
109818 114199 114199 114199 107871 114199 114199 114199
-15
108780 114199 114199 114199 106902 114199 114199 114199
-10
107779 114199 114199 114199 105898 114199 114199 114199
-5
106840 114199 114199 114199 104921 114199 114199 114199
0
105873 114199 114199 114199 103967 113788 114199 114199
5
104932 114199 114199 114199 103069 112744 114199 114199
10
104014 113836 114199 114199 102194 111725 114199 114199
15
103143 112828 114199 114199 101314 110733 114055 114199
20
102303 111845 114199 114199 100496 109764 113048 114199
25
101446 110885 114199 114199 99662 108817 112068 114199
30
100653 109948 113239 114199 98857 107902 111108 114199
35
99854 109032 112289 114199 98093 107051 110172 113416
40
99062 108136 111359 114199 97303 106175 109255 112466
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 45
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITHOUT ICE ACCRETION
ALTITUDE
0 ft
Temp
1000 ft
(°C)
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114199 114199 114199 114199
-10
114199 114199 114199 114199 114199 114199 114199 114199
-5
114199 114199 114199 114199 114199 114199 114199 114199
0
114199 114199 114199 114199 114199 114199 114199 114199
5
114199 114199 114199 114199 114199 114199 114199 114199
10
114199 114199 114199 114199 114199 114199 114199 114199
15
114199 114199 114199 114199 114199 114199 114199 114199
20
114199 114199 114199 114199 114199 114199 114199 114199
25
114199 114199 114199 114199 114199 114199 114199 114199
30
114199 114199 114199 114199 114199 114199 114199 114199
35
114199 114199 114199 114199 113574 114199 114199 114199
40
114199 114199 114199 114199 112701 114199 114199 114199
45
113762 114199 114199 114199 111809 114199 114199 114199
50
112918 114199 114199 114199 110946 114199 114199 114199
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 46
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITHOUT ICE ACCRETION
ALTITUDE
2000 ft
Temp
(°C)
-10 kt
AOM-1502-016
3000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114199 114199 114199 114199
-10
114199 114199 114199 114199 114199 114199 114199 114199
-5
114199 114199 114199 114199 114199 114199 114199 114199
0
114199 114199 114199 114199 114199 114199 114199 114199
5
114199 114199 114199 114199 114199 114199 114199 114199
10
114199 114199 114199 114199 114199 114199 114199 114199
15
114199 114199 114199 114199 113308 114199 114199 114199
20
114199 114199 114199 114199 112372 114199 114199 114199
25
113431 114199 114199 114199 111402 114199 114199 114199
30
112531 114199 114199 114199 110509 114199 114199 114199
35
111600 114199 114199 114199 109640 114199 114199 114199
40
110721 114199 114199 114199 108767 114199 114199 114199
45
109878 114199 114199 114199
---
---
---
---
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 47
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITHOUT ICE ACCRETION
ALTITUDE
4000 ft
Temp
(°C)
5000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114199 114199 114199 114199
-10
114199 114199 114199 114199 114199 114199 114199 114199
-5
114199 114199 114199 114199 113228 114199 114199 114199
0
114199 114199 114199 114199 112212 114199 114199 114199
5
113240 114199 114199 114199 111184 114199 114199 114199
10
112264 114199 114199 114199 110232 114199 114199 114199
15
111265 114199 114199 114199 109303 114199 114199 114199
20
110345 114199 114199 114199 108347 114199 114199 114199
25
109447 114199 114199 114199 107440 114199 114199 114199
30
108532 114199 114199 114199 106574 114199 114199 114199
35
107644 114199 114199 114199 105727 114199 114199 114199
40
106804 114199 114199 114199 104899 114199 114199 114199
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 48
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITH ICE ACCRETION
ALTITUDE
0 ft
Temp
1000 ft
(°C)
WIND
AOM-1502-016
-10 kt
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
110634 114199 114199 114199 108812 114199 114199 114199
-15
109675 114199 114199 114199 107849 114199 114199 114199
-10
108703 114199 114199 114199 106839 114199 114199 114199
-5
107740 114199 114199 114199 105895 114199 114199 114199
0
106752 114199 114199 114199 104959 114199 114199 114199
5
105830 114199 114199 114199 104048 113789 114199 114199
10
104928 114199 114199 114199 103158 112779 114199 114199
15
104047 113792 114199 114199 102289 111806 114199 114199
20
103188 112815 114199 114199 101441 110829 114114 114199
25
102347 111875 114199 114199 100613 109870 113120 114199
30
101527 110935 114199 114199 99802 108963 112181 114199
35
100723 109997 113257 114199 99010 108077 111258 114199
40
99939 109120 112345 114199 98235 107164 110308 113516
45
99171 108261 111455 114199 97476 106304 109426 112608
50
98420 107388 110543 113760 96750 105476 108569 111720
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 49
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITH ICE ACCRETION
ALTITUDE
2000 ft
Temp
(°C)
3000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
106960 114199 114199 114199 105155 114199 114199 114199
-15
105994 114199 114199 114199 104180 113947 114199 114199
-10
105043 114199 114199 114199 103230 112857 114199 114199
-5
104101 113848 114199 114199 102297 111810 114199 114199
0
103180 112798 114199 114199 101386 110760 114041 114199
5
102279 111791 114199 114199 100497 109736 112983 114199
10
101401 110777 114059 114199 99629 108767 111976 114199
15
100543 109788 113035 114199 98782 107806 110975 114199
20
99706 108851 112065 114199 97954 106835 109976 113177
25
98888 107932 111104 114199 97147 105932 109040 112208
30
98088 106986 110128 113335 96389 105051 108127 111258
35
97306 106110 109224 112397 95641 104190 107187 110277
40
96564 105257 108339 111481 94887 103347 106300 109371
45
95851 104421 107440 110540
---
---
---
---
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 50
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP 5 – WITH ICE ACCRETION
ALTITUDE
4000 ft
Temp
(°C)
-10 kt
AOM-1502-016
5000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
103334 112977 114199 114199 101511 110911 114199 114199
-15
102366 111891 114199 114199 100558 109806 113056 114199
-10
101421 110803 114087 114199 99623 108762 111973 114199
-5
100500 109740 112985 114199 98712 107728 110894 114124
0
99599 108734 111943 114199 97826 106692 109827 113025
5
98723 107737 110902 114132 96962 105725 108825 111987
10
97865 106736 109873 113071 96157 104781 107838 110953
15
97030 105802 108906 112069 95345 103860 106834 109924
20
96252 104891 107958 111077 94540 102963 105903 108959
25
95471 104001 106982 110074 93753 102086 104993 108019
30
94692 103132 106077 109141 93018 101227 104106 107045
35
93931 102283 105198 108229 92286 100390 103237 106140
40
93210 101452 104336 107298 91551
99571 102389 105261
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 51
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITH ICE ACCRETION
ALTITUDE
0 ft
Temp
1000 ft
(°C)
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114199 114199 114199 114199
-10
114199 114199 114199 114199 114199 114199 114199 114199
-5
114199 114199 114199 114199 114199 114199 114199 114199
0
114199 114199 114199 114199 114199 114199 114199 114199
5
114199 114199 114199 114199 113904 114199 114199 114199
10
114199 114199 114199 114199 112913 114199 114199 114199
15
113907 114199 114199 114199 111946 114199 114199 114199
20
112950 114199 114199 114199 111001 114199 114199 114199
25
112015 114199 114199 114199 110078 114199 114199 114199
30
111102 114199 114199 114199 109177 114199 114199 114199
35
110208 114199 114199 114199 108341 114199 114199 114199
40
109333 114199 114199 114199 107497 114199 114199 114199
45
108514 114199 114199 114199 106652 114199 114199 114199
50
107708 114199 114199 114199 105828 114199 114199 114199
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 52
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITH ICE ACCRETION
ALTITUDE
2000 ft
Temp
(°C)
-10 kt
AOM-1502-016
3000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
114199 114199 114199 114199 114199 114199 114199 114199
-15
114199 114199 114199 114199 114043 114199 114199 114199
-10
114199 114199 114199 114199 112986 114199 114199 114199
-5
113957 114199 114199 114199 111946 114199 114199 114199
0
112931 114199 114199 114199 110933 114199 114199 114199
5
111929 114199 114199 114199 109943 114199 114199 114199
10
110951 114199 114199 114199 108986 114199 114199 114199
15
109997 114199 114199 114199 108095 114199 114199 114199
20
109068 114199 114199 114199 107178 114199 114199 114199
25
108208 114199 114199 114199 106278 114199 114199 114199
30
107330 114199 114199 114199 105399 114199 114199 114199
35
106459 114199 114199 114199 104540 114159 114199 114199
40
105608 114199 114199 114199 103700 113218 114199 114199
45
104775 114199 114199 114199
---
---
---
---
5-35
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Landing
Page 53
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
QUICK TURN AROUND WEIGHT (lb)
EMBRAER 190 – CF34-10 ENGINES
FLAP FULL – WITH ICE ACCRETION
ALTITUDE
4000 ft
Temp
(°C)
5000 ft
WIND
0 kt
10 kt
20 kt
-10 kt
0 kt
10 kt
20 kt
-20
113100 114199 114199 114199 111072 114199 114199 114199
-15
112023 114199 114199 114199 110009 114199 114199 114199
-10
110970 114199 114199 114199 108977 114199 114199 114199
-5
109944 114199 114199 114199 108021 114199 114199 114199
0
108953 114199 114199 114199 107031 114199 114199 114199
5
108031 114199 114199 114199 106068 114199 114199 114199
10
107077 114199 114199 114199 105126 114199 114199 114199
15
106147 114199 114199 114199 104208 113790 114199 114199
20
105239 114199 114199 114199 103328 112785 114199 114199
25
104351 113948 114199 114199 102499 111805 114199 114199
30
103490 112978 114199 114199 101644 110848 114081 114199
35
102690 112027 114199 114199 100806 109911 113109 114199
40
101869 111098 114199 114199 100006 109004 112160 114199
5-35
Copyright © by Embraer. Refer to cover page for details.
Page 54
Landing
REVISION 23
AOM-1502-016
-10 kt
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
CAT II OPERATION
The performance data required for Category II operations are presented
by basic CAFM output tables and must be calculated previously.
APPROACH
CLIMB
LANDING
CLIMB
LANDING
ENGINES
TLA
FLAPS GEAR
AIRSPEED
APPROACH
CLMB
SPEED
1
TO/GA
2
UP
2
TO/GA
5
DOWN
VREF5
[1]
2
IDLE
5
DOWN
VREF5
[1]
AOM-1502-016
1. The Landing Reference Speed (VREF5) for Category II operations is
the appropriate speed obtained from the CAFM.
5-40
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Supplementary Operations
Page 1
PERFORMANCE
AIRPLANE
OPERATIONS
MANUAL
!Airplanes equipped with Autoland system
AUTOLAND
!!190 models, Airplanes with Autoland System, ANAC/TCCA/FAA Certification
The performance data required for Autoland operations are presented
by basic CAFM output tables, through the CAT III/Autoland option, and
must be calculated previously.
""
!!Airplanes equipped with Autoland System, ANAC or FAA certification
ENGINES
TLA
FLAPS
GEAR
AIRSPEED
APPROACH
CLIMB
SPEED
APPROACH
CLIMB
1
TO/GA
2
UP
LANDING
CLIMB
2
TO/GA
5
DOWN
VREF5
[1]
LANDING
2
IDLE
5
DOWN
VREF5
[1]
1. The Landing Reference Speed (VREF5) for Autoland operations is
the appropriate speed obtained from the CAFM.
5-40
Copyright © by Embraer. Refer to cover page for details.
Page 2
Supplementary Operations
REVISION 21
AOM-1502-016
""
"
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
SECTION 6
FLIGHT PLANNING
TABLE OF CONTENTS
Block
Page
Simplified Flight Planning................................... 6-05 ........... 1
SIMPLIFIED FLIGHT PLANNING.......................... 6-05 ........... 1
FLIGHT LEVEL TABLE.......................................... 6-05 ........... 6
ALTITUDE CAPABILITY TABLE............................ 6-05 ........... 9
WIND ALTITUDE TRADE...................................... 6-05 ........... 12
FUEL TANKERING................................................ 6-05 ........... 15
Engine and APU Fuel Consumption.................. 6-07 ...........
ENGINE FUEL CONSUMPTION........................... 6-07 ...........
APU FUEL CONSUMPTION.................................. 6-07 ...........
1
1
2
Climb..................................................................... 6-10 ...........
CLIMB SPEEDS..................................................... 6-10 ...........
CLIMB TABLES...................................................... 6-10 ...........
1
1
2
AOM-1502-016
Cruise.................................................................... 6-15 ........... 1
BUFFET ONSET.................................................... 6-15 ........... 1
LONG RANGE CRUISE........................................ 6-15 ........... 5
FIXED SPEED CRUISE......................................... 6-15 ........... 26
COST INDEX AND ECONOMIC CRUISE SPEED.. 6-15 ........... 37
Descent................................................................. 6-20 ...........
DESCENT.............................................................. 6-20 ...........
CONSTANT FLIGHT PATH ANGLE....................... 6-20 ...........
1
1
6
Holding.................................................................. 6-25 ...........
HOLDING............................................................... 6-25 ...........
1
1
One Engine Inoperative Performance................ 6-30 ........... 1
LONG RANGE CRUISE........................................ 6-30 ........... 1
DRIFTDOWN......................................................... 6-30 ........... 12
ALTITUDE CAPABILITY......................................... 6-30 ........... 15
HOLDING............................................................... 6-30 ........... 17
6-TOC
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Table of Contents
Page 1
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
Block
Page
MAXIMUM DISTANCE FROM AN ADEQUATE
AERODROME.................................................. 6-30 ........... 30
INFLIGHT DIVERSION.......................................... 6-30 ........... 32
1
1
4
6-TOC
Copyright © by Embraer. Refer to cover page for details.
Page 2
Table of Contents
REVISION 21
AOM-1502-016
Inflight Diversion.................................................. 6-35 ...........
INFLIGHT DIVERSION.......................................... 6-35 ...........
FLIGHT OVER MOUNTAINOUS AREA................. 6-35 ...........
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
SIMPLIFIED FLIGHT PLANNING
Simplified flight planning charts allow quick determination of estimated
trip fuel and time from brake release to landing. The following phases
are included: takeoff, climb, cruise, descent, approach and landing.
Charts are provided for Long Range Cruise (LRC) and Mach 0.78.
Alternate fuel, holding, reserve fuel and other allowances (APU usage
and taxi) should be added to the trip fuel in order to obtain the total fuel
required.
To determine trip fuel enter trip ground distance, correct for wind
condition and estimated landing weight, move as far as the line indicating
cruise pressure altitude, and read the trip fuel.
To determine trip time, enter trip ground distance, correct for wind
condition, move as far as the referring cruise pressure altitude, and read
the trip time.
For winds greater than those shown, enter in the chart, directly, corrected
ground distance, ignore wind correction reference line, to obtain the
corrected ground distance, apply the following equation.
CGD
=
GD
x
( TAS )
( TAS + WIND )
Where:
CGD: Corrected ground distance;
GD: Ground distance;
Head wind is negative;
Tail wind is positive.
The alternate fuel is determined by entering the LRC Simplified Flight
Planning chart with the alternate distance and wind.
AOM-1502-016
The holding fuel is determined from the holding table in this section.
Depending upon national regulations, the holding fuel is normally
calculated so that the aircraft can hold for 30 min, at 1500 ft above the
alternate airport.
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 1
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190 SIMPLIFIED FLIGHT PLANNING
TRIP FUEL
ALL ENGINE TYPES
LONG RANGE CRUISE
0
0
FL
30
0
FL
25
0
20
15
FL
FL
BASED ON:
250 / 290 / M 0.75 CLIMB
M 0.77 / 290 / 250 DESCENT
FL350 AND
ABOVE
97000
93000
89000
85000
81000
77000
REF.
LINE
60
30
0
60
0
200
400 600
800 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800
TRIP DISTANCE − NM
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 2
Simplified Flight Planning
REVISION 21
AOM-1502-016
REF. LINE
30
EM170AOM060032C.DGN
WIND − kt
HEAD
TAIL
LANDING WEIGHT − lb
FUEL REQUIRED − lb
ISA CONDITION
27000
26000
25000
24000
23000
22000
21000
20000
19000
18000
17000
16000
15000
14000
13000
12000
11000
10000
9000
8000
7000
6000
5000
4000
3000
2000
1000
0
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190 SIMPLIFIED FLIGHT PLANNING
TRIP TIME
ALL ENGINE TYPES
LONG RANGE CRUISE
ISA CONDITION
LANDING WEIGHT − lb
FLIGHT TIME − min
400
390
380
370
360
350
340
330
320
310
300
290
280
270
260
250
240
230
220
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
FL
15
0
BASED ON:
250 / 290 / M 0.75 CLIMB
M 0.77 / 290 / 250 DESCENT
FL
2
00
FL
25
0
FL
30
0
FL350 AND
ABOVE
97000
REF.
LINE
93000
89000
85000
81000
77000
30
0
REF.
LINE
30
60
AOM-1502-016
0
200
400
600
800
1000 1200 1400 1600 1800 2000 2200 2400 2600 2800
TRIP DISTANCE − NM
EM170AOM060033C.DGN
WIND − kt
TAIL
HEAD
60
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 3
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
EMBRAER 190 SIMPLIFIED FLIGHT PLANNING
TRIP FUEL
ALL ENGINE TYPES
MACH 0.78 CRUISE
0
30
FL
BASED ON:
250 / 290 / M 0.75 CLIMB
M 0.77 / 290 / 250 DESCENT
FL
35
0
FL350 AND
ABOVE
97000
93000
89000
85000
81000
77000
REF.
LINE
60
30
0
60
0
200
400 600
800 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800
TRIP DISTANCE − NM
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 4
Simplified Flight Planning
REVISION 21
AOM-1502-016
REF.
LINE
30
EM170AOM060034C.DGN
WIND − kt
HEAD
TAIL
LANDING WEIGHT − lb
FUEL REQUIRED − lb
ISA CONDITION
27000
26000
25000
24000
23000
22000
21000
20000
19000
18000
17000
16000
15000
14000
13000
12000
11000
10000
9000
8000
7000
6000
5000
4000
3000
2000
1000
0
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
EMBRAER 190 SIMPLIFIED FLIGHT PLANNING
TRIP TIME
ALL ENGINES TYPES
MACH 0.78 CRUISE
FLIGHT TIME − MIN
ISA CONDITION
340
330
320
310
300
290
280
270
260
250
240
230
220
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
BASED ON:
250 / 290 / M 0.75 CLIMB
M 0.77 / 290 / 250 DESCENT
FL350 AND ABOVE
FL
30
0
60
REF.
LINE
0
30
60
0
200
400
600
800
1000 1200 1400 1600 1800 2000 2200 2400 2600
AOM-1502-016
TRIP DISTANCE − NM
EM170AOM060035C.DGN
WIND − kt
HEAD
TAIL
30
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 5
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CRUISE - FLIGHT LEVEL TABLE
The following tables permit quick determination of the cruise flight level
for minimum fuel consumption, based on the trip distance and takeoff
weight.
The flight level was calculated based on a combination of minimum fuel
consumption and at least 5 minutes in cruise.
CLIMB
UP
DESCENT
AT LEAST 5 MINUTES
OF CRUISE
EM170AOM060008B.DGN
CRUISE
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 6
Simplified Flight Planning
REVISION 21
AOM-1502-016
The table data are presented for ISA condition, all engines operating,
Long Range Cruise and Mach 0.78 schedules. A minimum remaining
rate of climb equal to 300 ft/min is considered.
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
FLIGHT LEVEL - ALL ENGINES OPERATING
CF34-10E5/10E5A1/10E6/10E6A1
LONG RANGE CRUISE AND ISA CONDITIONS
TRIP DISTANCE (NM)
1500
TOW
(lb)
200
300
400
500
600
700
800
900
1000 1100 1200
and
above
114000
[1]
110000
[1]
106000
[1]
102000
[1]
98000
94000
90000
86000
82000
[2]
78000
[2]
74000
[2]
-
-
-
-
-
-
-
-
-
-
-
350
-
-
-
-
-
-
-
-
-
-
360
360
-
-
-
-
-
-
-
360
360
360
360
360
-
-
-
340
370
370
370
370
370
370
370
370
260
350
350
350
380
380
380
380
380
380
380
380
270
360
360
360
390
390
390
390
390
390
390
390
270
360
370
370
390
390
390
390
390
390
390
390
280
370
380
380
400
400
400
400
400
400
400
400
300
380
390
390
400
400
400
400
400
400
400
-
310
390
400
400
400
400
400
400
-
-
-
-
320
400
410
410
-
-
-
-
-
-
-
-
AOM-1502-016
1. The Blank spaces means that the landing weight is beyond the
Maximum Landing Weight.
2. The Blank spaces means that the TOW does not allow enough fuel
quantity to accomplish the specified trip distance.
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 7
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
FLIGHT LEVEL - ALL ENGINES OPERATING
CF34-10E5/10E5A1/10E6/10E6A1
MACH 0.78 CRUISE AND ISA CONDITIONS
TRIP DISTANCE (NM)
1500
TOW
(lb)
200
300
400
500
600
700
800
900
1000 1100
1200
and
above
114000
[1]
110000
[1]
106000
[1]
102000
[1]
98000
94000
90000
86000
82000
[2]
78000
[2]
74000
[2]
-
-
-
-
-
-
-
-
-
-
-
340
-
-
-
-
-
-
-
-
-
-
360
360
-
-
-
-
-
-
360
360
360
360
360
360
-
-
370
370
370
370
370
370
370
370
370
370
310
380
380
380
380
380
380
380
380
380
380
380
320
390
390
390
390
390
390
390
390
390
390
390
330
400
400
400
400
400
400
400
400
400
400
400
340
410
410
410
410
410
410
410
410
410
410
410
350
410
410
410
410
410
410
410
410
410
410
-
360
410
410
410
410
410
410
410
-
-
-
-
370
410
410
410
-
-
-
-
-
-
-
-
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 8
Simplified Flight Planning
REVISION 21
AOM-1502-016
1. The Blank spaces means that the landing weight is beyond the
Maximum Landing Weight.
2. The Blank spaces means that the TOW does not allow enough fuel
quantity to accomplish the specified trip distance.
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
CRUISE - ALTITUDE CAPABILITY TABLE
The tables below permit quick determination of the altitude capability,
based on the initial cruise weight. Tables are presented for various ISA
conditions and all engines operating.
The established associated conditions are:
AOM-1502-016
Flaps.......................................................................... UP
Gears......................................................................... UP
Bleeds........................................................................ OPEN
Center of gravity........................................................ 22%
Minimum Remaining Rate of Climb.......................... 300 ft/min
Minimum Buffet Margin............................................. 1.3 g
Thrust Setting............................................................ MAX CRUISE
THRUST
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 9
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING
LONG RANGE CRUISE
CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
-10
-5
0
5
10
15
20
25
30
35
115000
340
340
340
340
340
330
320
310
290
270
113000
340
340
340
340
340
330
320
310
300
270
111000
340
350
350
350
350
340
330
320
300
280
109000
340
350
350
350
350
340
330
320
310
290
107000
340
360
360
360
360
340
330
330
320
290
105000
340
360
360
360
360
350
340
330
320
300
103000
340
360
360
360
360
350
340
340
330
310
101000
340
370
370
370
370
360
350
340
330
310
99000
340
370
370
370
370
360
350
340
340
320
97000
340
370
370
370
370
360
350
350
340
330
95000
340
380
380
380
380
370
360
350
350
340
93000
340
380
380
380
380
370
370
350
350
350
91000
340
390
390
390
390
380
370
360
360
350
89000
340
390
390
390
390
380
370
370
360
360
87000
340
390
390
390
390
380
380
370
370
360
85000
340
400
400
400
400
390
380
380
370
370
83000
340
400
400
400
400
390
390
380
380
370
81000
340
410
410
410
410
400
390
390
380
370
79000
340
410
410
410
410
400
390
390
390
380
77000
340
410
410
410
410
400
400
400
390
380
75000
340
410
410
410
410
410
400
400
400
390
73000
340
410
410
410
410
410
410
410
400
390
71000
340
410
410
410
410
410
410
410
410
390
69000
340
410
410
410
410
410
410
410
410
400
67000
340
410
410
410
410
410
410
410
410
400
65000
340
410
410
410
410
410
410
410
410
410
63000
340
410
410
410
410
410
410
410
410
410
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 10
Simplified Flight Planning
REVISION 21
AOM-1502-016
ISA + ºC
Weight
(lb)
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
AOM-1502-016
CRUISE ALTITUDE CAPABILITY - ALL ENGINES OPERATING
MACH 0.78
CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
ISA + ºC
Weight
(lb)
-10
-5
0
5
10
15
20
25
30
35
115000
340
340
340
340
340
310
-
-
-
-
113000
340
340
340
340
340
320
-
-
-
-
111000
340
350
350
350
350
330
-
-
-
-
109000
340
350
350
350
350
340
-
-
-
-
107000
340
360
360
360
360
350
-
-
-
-
105000
340
360
360
360
360
350
-
-
-
-
103000
340
360
360
360
360
360
330
-
-
-
101000
340
370
370
370
370
360
340
-
-
-
99000
340
370
370
370
370
360
350
-
-
-
97000
340
380
380
380
380
370
350
-
-
-
95000
340
380
380
380
380
370
360
-
-
-
93000
340
380
380
380
380
380
360
-
-
-
91000
340
390
390
390
390
380
370
-
-
-
89000
340
390
390
390
390
380
370
360
-
-
87000
340
400
400
400
400
390
370
360
-
-
85000
340
400
400
400
400
390
380
360
-
-
83000
340
410
410
410
410
390
380
370
-
-
81000
340
410
410
410
410
400
390
370
-
-
79000
340
410
410
410
410
400
390
370
-
-
77000
340
410
410
410
410
410
390
380
-
-
75000
340
410
410
410
410
410
400
380
360
-
73000
340
410
410
410
410
410
400
390
360
-
71000
340
410
410
410
410
410
410
390
370
-
69000
340
410
410
410
410
410
410
390
370
-
67000
340
410
410
410
410
410
410
400
370
-
65000
340
410
410
410
410
410
410
400
380
-
63000
340
410
410
410
410
410
410
400
380
360
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 11
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CRUISE - WIND ALTITUDE TRADE
The following tables allow the determination of the break-even wind in
order to maintain the same ground specific range at another altitude
than the one planned initially. Long Range Cruise or Mach 0.78 tables
are provided.
These tables are based on the comparison between ground specific
range at the new and actual altitudes. They do not consider
climb/descent time, fuel and distances. The tables may be used in-flight,
where the wind information is available and more accurate.
Evaluation Method
1 - Check the wind factors for actual and new altitudes.
2 - Calculate the difference between new and actual wind factors. This
number may be negative or positive.
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 12
Simplified Flight Planning
REVISION 21
AOM-1502-016
3 - The BREAK-EVEN WIND at the new altitude is the wind component
at actual altitude plus the difference calculated on step (2).
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CRUISE – WIND ALTITUDE TRADE TABLES
LONG RANGE CRUISE
CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
Weight (lb)
Pressure
Altitude
(ft)
41000
40000
39000
38000
37000
36000
35000
34000
33000
32000
31000
30000
29000
28000
27000
78000 82000 86000 90000 94000 98000 102000 106000 110000
4
5
0
6
12
17
22
26
30
35
40
45
54
62
71
2
5
0
5
10
16
21
26
29
35
39
44
53
62
0
8
9
4
8
15
21
26
30
34
39
44
48
58
0
7
9
3
9
15
22
27
31
34
40
45
49
0
7
7
2
9
16
22
27
31
35
40
46
0
6
6
3
10
16
22
27
31
35
41
0
5
13
11
9
15
22
28
33
37
40
0
7
13
10
10
17
23
30
34
38
114000
0
7
13
8
11
17
24
29
34
0
8
11
5
11
18
24
30
Example: 90000 lb of actual cruise weight, LRC:
Actual Flight Level:
FL 280, -10 kt (headwind)
New Flight Level:
FL 350, -20 kt (headwind)
1 - Wind factor FL280 = 45, Wind factor FL350 = 9
2 - Difference = 9 (new FL) - 45 (actual FL) = -36
3 - Break Even Wind = -10 (wind actual FL) + (-36) (difference) =
-46 kt
AOM-1502-016
Wind on FL350 (20 kt headwind) is more favorable than Break-Even
Wind (46 kt headwind). Therefore, climb to FL350.
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 13
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
MACH 0.78
CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
Weight (lb)
Pressure
Altitude
(ft)
41000
40000
39000
38000
37000
36000
35000
34000
33000
32000
31000
30000
29000
28000
27000
78000 82000 86000 90000 94000 98000 102000 106000 110000
0
5
9
20
33
47
63
80
96
112
131
150
172
196
219
0
7
13
17
29
41
57
74
89
106
124
143
163
185
207
0
8
14
18
29
44
59
75
91
109
126
145
165
186
0
8
14
17
31
45
60
75
92
110
128
147
166
0
8
13
19
32
46
61
77
94
112
130
148
0
8
14
20
33
47
63
79
96
114
131
0
6
15
20
27
41
56
72
87
105
123
0
7
15
20
29
44
59
74
91
107
0
8
16
21
33
46
61
77
93
114000
0
10
16
21
34
48
63
78
Example: 94000 lb of actual cruise weight, Mach 0.78.
Actual Flight Level:
FL 360, -10 kt (headwind)
New Flight Level:
FL 310, 15 kt (tailwind)
1 - Wind factor FL360 = 13, Wind factor FL310 = 77
2 - Difference = 77 (new FL) - 13 (actual FL) = 64
3 - Break Even Wind = -10 (wind actual FL) + 64 (difference) = 54 kt
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 14
Simplified Flight Planning
REVISION 21
AOM-1502-016
Wind on FL310 (15 kt tailwind) is less favorable than Break-Even Wind
(54 kt tailwind). Therefore, maintain FL360.
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
FLIGHT PLANNING - FUEL TANKERING
Fuel price variations at different airports may require carrying more fuel
than the minimum required on a flight leg. The procedure of loading this
extra amount of fuel (or surplus fuel) in order to minimize fuel costs is
known as Fuel Tankering.
Since the surplus fuel tankered results in additional fuel burnoff (due to
the weight increase) it is important to analyze the costs of the extra fuel
transportation operation.
The following tables are designed to determine the break-even fuel price
on departure airport and it may be used whenever there is difference on
fuel price comparing to destination. Tables are provided for LRC and M
0.78 cruise schedule.
Enter the trip distance on the table and read the fuel surplus ratio
according to cruise altitude. The break-even fuel price is the price at
departure multiplied by the fuel surplus ratio. If break-even fuel price is
lower than destination price, it is economically feasible to execute fuel
tankering.
The additional maintenance costs involved with increased weight
operations (additional brakes and tires wearing) are not considered. It is
important to remind that whenever fuel tankering is considered, the
estimated landing weight at destination should be lower than the
Maximum Landing Weight.
Example
Analyze the possibility to proceed with fuel tankering between two
airports distant 600 NM from each other, using LRC speed schedule
cruising on FL350. Consider the following fuel prices:
Departure Airport: 1.80 US$/Gal.
AOM-1502-016
Destination Airport: 2.00 US$/Gal.
•
Enter the LONG RANGE CRUISE table for 600 NM trip distance and
FL350, the FUEL SURPLUS RATIO is 1.05.
•
The BREAK-EVEN PRICE is 1.80 (price at departure) multiplied by
1.05 = 1.89 US$/Gal.
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 15
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
Since fuel price on destination airport (2.00 US$/Gal) is greater than
break-even fuel price (1.89 US$/Gal), it is economically feasible the fuel
tankering operation between these two airports.
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 16
Simplified Flight Planning
REVISION 21
AOM-1502-016
FUEL TANKERING
EMBRAER 190 / CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
LONG RANGE CRUISE
FUEL SURPLUS RATIO
TRIP DISTANCE
31000 ft and
32000 ft
(NM)
below
above
200
1.01
1.02
400
1.03
1.03
600
1.04
1.05
800
1.05
1.06
1000
1.07
1.08
1200
1.08
1.10
1400
1.10
1.12
1600
1.11
1.13
1800
1.13
1.15
2000
1.14
1.18
2200
1.16
1.20
2400
1.17
1.21
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
AOM-1502-016
FUEL TANKERING
EMBRAER 190 / CF34-10E5/10E5A1/10E6/10E6A1 ENGINES
MACH 0.78
FUEL SURPLUS RATIO
TRIP DISTANCE
31000 ft and
32000 ft
(NM)
below
above
200
1.01
1.01
400
1.02
1.02
600
1.02
1.03
800
1.03
1.04
1000
1.04
1.05
1200
1.05
1.06
1400
1.06
1.07
1600
1.06
1.08
1800
1.07
1.09
2000
1.08
1.10
2200
1.09
1.11
2400
1.10
1.12
6-05
Copyright © by Embraer. Refer to cover page for details.
REVISION 21
Simplified Flight Planning
Page 17
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
6-05
Copyright © by Embraer. Refer to cover page for details.
Page 18
Simplified Flight Planning
REVISION 21
AOM-1502-016
INTENTIONALLY BLANK
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
ENGINE FUEL CONSUMPTION
The following values established for taxi, take-off, approach and go
around fuel consumption should be considered when calculating detailed
flight plans.
FUEL CONSUMPTION
ENGINE
PHASE OF FLIGHT
TAXI
ALL
TAKE-OFF
ENGINE
APPROACH AND LANDING
TYPES
GO AROUND
FUEL CONSUMPTION
lb/min
20
209
58
196
A typical average value to be used during the flight planning calculation
should be considered:
TAKE-OFF =314 lb (1.5 minutes used);
APPROACH AND LANDING = 174 lb (3 minutes used);
AOM-1502-016
GO AROUND = 157 lb (0.8 minutes used).
6-07
Copyright © by Embraer. Refer to cover page for details.
REVISION 9
Engine and APU Fuel
Consumption
Page 1
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
APU FUEL CONSUMPTION
The table below shows the APU fuel consumption on the ground and
during level flight at 5000 ft, 15000 ft, and 33000 ft altitudes. The data is
calculated for different airspeeds, APU air bleeds and electrical loads.
AIRSPEED
(KIAS)
0
0
APU AIR
BLEED
0
Max.
0
170
Max.
5000
0
300
Max.
0
170
Max.
15000
0
320
Max.
170
0
300
0
33000
APU GEN.
LOAD
(kVA)
0
40
0
40
0
40
0
40
0
40
0
40
0
40
0
40
0
40
0
40
0
40
0
40
APU FUEL
FLOW
(lb/min)
3.3
3.8
4.7
5.2
2.8
3.3
4.0
4.5
2.8
3.2
3.9
4.5
2.2
2.6
3.1
3.7
2.1
2.6
3.1
3.7
1.5
2.1
1.4
2.0
6-07
Copyright © by Embraer. Refer to cover page for details.
Page 2
Engine and APU Fuel
Consumption
REVISION 9
AOM-1502-016
ALTITUDE
(ft)
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB SPEEDS
MAXIMUM ANGLE OF CLIMB SPEED
This speed is recommended to reach an altitude on minimum ground
distance (i.e. for obstacle clearance). With flaps up, the recommended
maximum angle of climb speed for all operational gross weights and
altitudes is the Green Dot, or approximately VFS.
MAXIMUM RATE OF CLIMB SPEED
This speed is recommended when maximum rate of climb is desired in
order to reach an altitude on minimum climb time. The recommended
maximum rate of climb speed is related to flaps up, all engines operating
and is function of gross weights and altitudes as shown in the tables
below:
Weight (lb)
Altitude
(ft)
85000
90000
95000
100000 105000
110000
115000
5000
255
257
261
264
265
267
269
10000
249
250
250
252
254
255
257
15000
239
242
244
245
247
249
252
20000
229
233
237
242
244
247
249
25000
225
227
233
236
241
245
249
Maintain the speeds above until intercepting Mach 0.60 or green dot
speed, whichever is higher, following this until level off.
!190 models, MAU Load 21.2 up to Load 25.4 - Pentium M or Load 25.3 - Pentium
II
The green dot does not account for ice accretion. Therefore when flying
in icing conditions (EICAS message STALL PROT ICE SPEED
displayed) it is recommended to add 10 kt to the green dot.
"
!190 models, MAU Load 25.5.0.1 and on
The green dot accounts for ice accretion.
AOM-1502-016
"
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 1
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB TABLES
The climb planning tables show fuel consumption, distance, and time
elapsed from the Sea Level to the top of climb. Data are shown for
various weights, ISA deviations and cruise altitudes.
The takeoff fuel consumption is not considered in the following tables.
Tables present the scheduled climb speed according to the autopilot
climb mode, i.e.:
– 250 KIAS for altitudes up to 10000 ft, increasing linearly to 290 KIAS
at 12000 ft, maintaining 290 KIAS up to 28900 ft and 0.75 Mach
above 28900 ft.
The associated conditions are:
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 2
Climb
REVISION 23
AOM-1502-016
Thrust Mode.............................................................. CLB1
Flaps.......................................................................... UP
Gear........................................................................... UP
Bleeds........................................................................ OPEN
Anti-Ice...................................................................... OFF
CG............................................................................. 22%
Minimum Remaining Rate of Climb.......................... 300 ft/min
AIRPLANE
OPERATIONS
MANUAL
FLIGHT PLANNING
EXAMPLE:
Given:
Departure Airport Elevation....................................... 3500 ft
Takeoff weight............................................................ 96000 lb
ISA Condition Cruise Altitude.................................... 33000 ft
RESULTS:
Data for 5000 ft (3500 ft + 1500 ft above departure airport) obtained from
the climb table:
Fuel: 249 lb
Distance: 6 NM
Time: 1 min
Data provided from the Sea Level to 33000 ft (Top of Climb) table:
Fuel: 2132 lb
Distance: 98 NM
Time: 16 min
The fuel, distance and time spent during the climb phase (from 5000 ft to
33000 ft) are:
Fuel: 2132 – 249 = 1883 lb
Distance: 98 – 6 = 92 NM
Time: 16 – 1 = 15 min
AOM-1502-016
The fuel consumption related to the takeoff phase is provided on the
Section 1-06-07.
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 3
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
5000 FT
ISA + °C
–10
0
10
20
–20
6000 FT
ISA + °C
–10
0
10
20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
285
6
2
278
6
2
272
6
1
265
6
1
258
6
1
252
6
1
246
6
1
240
5
1
233
5
1
298
7
2
291
7
2
284
6
2
277
6
1
270
6
1
264
6
1
257
6
1
251
6
1
244
5
1
312
7
2
305
7
2
297
7
2
290
6
2
283
6
1
276
6
1
269
6
1
262
6
1
256
6
1
327
7
2
319
7
2
311
7
2
303
7
2
296
7
2
289
6
1
281
6
1
274
6
1
267
6
1
364
9
2
355
9
2
346
8
2
337
8
2
328
8
2
320
8
2
311
8
2
303
7
2
295
7
2
343
8
2
334
8
2
326
7
2
318
7
2
310
7
2
302
7
2
295
7
2
288
7
2
280
6
2
358
8
2
350
8
2
341
8
2
333
8
2
325
7
2
316
7
2
309
7
2
301
7
2
293
7
2
375
9
2
366
8
2
357
8
2
348
8
2
340
8
2
331
8
2
323
7
2
315
7
2
307
7
2
392
9
2
383
9
2
373
8
2
364
8
2
355
8
2
346
8
2
338
8
2
329
7
2
321
7
2
438
11
2
426
11
2
415
10
2
405
10
2
394
10
2
384
10
2
374
9
2
364
9
2
355
9
2
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
10
10
6
11
11
3
6
6
0
0
0
0
0
0
6
11
10
6
11
11
4
7
7
0
0
0
0
0
0
114000
112000
110000
108000
106000
104000
102000
100000
98000
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 4
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
AOM-1502-016
Fuel
96000
Distance
Time
Fuel
94000
Distance
Time
Fuel
92000
Distance
Time
Fuel
90000
Distance
Time
Fuel
88000
Distance
Time
Fuel
86000
Distance
Time
Fuel
84000
Distance
Time
Fuel
82000
Distance
Time
Fuel
80000
Distance
Time
Anti-ice ON increase
For Anti- Fuel
ice ON, Distance
increase Time
–20
5000 FT
ISA + °C
–10
0
10
20
–20
6000 FT
ISA + °C
–10
0
10
20
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
228
5
1
222
5
1
216
5
1
210
5
1
205
5
1
199
4
1
193
4
1
188
4
1
183
4
1
238
5
1
232
5
1
226
5
1
220
5
1
214
5
1
208
5
1
202
4
1
197
4
1
191
4
1
249
6
1
243
5
1
236
5
1
230
5
1
224
5
1
218
5
1
212
5
1
206
5
1
200
4
1
260
6
1
254
6
1
247
5
1
241
5
1
234
5
1
228
5
1
221
5
1
215
5
1
209
5
1
287
7
2
280
7
2
272
7
1
265
6
1
257
6
1
250
6
1
243
6
1
236
6
1
229
6
1
273
6
2
266
6
1
259
6
1
252
6
1
245
6
1
239
5
1
232
5
1
226
5
1
219
5
1
286
6
2
278
6
1
271
6
1
264
6
1
257
6
1
250
6
1
243
5
1
236
5
1
229
5
1
299
7
2
291
7
2
283
6
1
276
6
1
268
6
1
261
6
1
254
6
1
247
6
1
240
5
1
313
7
2
304
7
2
296
7
2
289
6
1
281
6
1
273
6
1
266
6
1
258
6
1
251
6
1
345
9
2
336
8
2
327
8
2
318
8
2
309
8
2
300
7
2
292
7
2
283
7
2
275
7
2
(%)
(%)
(%)
6
10
10
6
10
10
3
6
5
0
0
0
0
0
0
6
10
10
6
10
10
4
7
6
0
0
0
0
0
0
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 5
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 5000 AND 6000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
For Antiice ON,
increase
–20
5000 FT
ISA + °C
–10
0
10
20
–20
6000 FT
ISA + °C
–10
0
10
20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
178
4
1
172
4
1
167
4
1
162
4
1
157
3
1
152
3
1
147
3
1
186
4
1
180
4
1
175
4
1
170
4
1
164
4
1
159
3
1
154
3
1
194
4
1
189
4
1
183
4
1
177
4
1
172
4
1
166
4
1
161
4
1
203
4
1
197
4
1
191
4
1
186
4
1
180
4
1
174
4
1
169
4
1
223
5
1
216
5
1
210
5
1
203
5
1
197
5
1
190
5
1
184
4
1
213
5
1
207
5
1
201
5
1
194
4
1
188
4
1
182
4
1
177
4
1
223
5
1
216
5
1
210
5
1
203
5
1
197
4
1
191
4
1
185
4
1
233
5
1
226
5
1
219
5
1
213
5
1
206
5
1
200
4
1
193
4
1
244
5
1
237
5
1
229
5
1
223
5
1
216
5
1
209
5
1
202
4
1
267
7
1
259
6
1
251
6
1
244
6
1
236
6
1
228
6
1
221
5
1
Fuel
Distance
Time
(%)
(%)
(%)
5
10
9
5
10
9
3
5
5
0
0
0
0
0
0
5
10
9
5
10
10
3
6
6
0
0
0
0
0
0
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 6
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
–20
7000 FT
ISA + °C
–10
0
10
20
–20
8000 FT
ISA + °C
–10
0
10
20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
400
9
2
390
9
2
381
9
2
371
9
2
362
8
2
353
8
2
344
8
2
336
8
2
327
8
2
419
10
2
408
9
2
398
9
2
388
9
2
379
9
2
369
9
2
360
8
2
351
8
2
342
8
2
438
10
2
427
10
2
417
10
2
406
9
2
396
9
2
386
9
2
377
9
2
367
8
2
358
8
2
458
11
2
447
10
2
436
10
2
425
10
2
415
10
2
404
9
2
394
9
2
384
9
2
374
9
2
512
13
3
498
13
3
485
12
3
473
12
3
461
12
3
449
11
3
437
11
2
425
11
2
414
10
2
458
11
3
447
11
3
435
10
2
425
10
2
414
10
2
404
10
2
394
9
2
384
9
2
374
9
2
479
11
3
467
11
3
456
11
3
444
11
2
433
10
2
422
10
2
412
10
2
401
9
2
391
9
2
501
12
3
489
12
3
477
11
3
465
11
2
453
11
2
442
10
2
431
10
2
420
10
2
409
10
2
525
12
3
512
12
3
499
12
3
487
11
3
474
11
2
462
11
2
451
11
2
439
10
2
428
10
2
586
15
3
571
15
3
556
14
3
541
14
3
527
14
3
513
13
3
500
13
3
487
13
3
474
12
3
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
11
11
7
11
11
5
8
8
0
0
0
0
0
0
6
11
11
7
11
11
5
8
8
0
1
1
0
0
0
114000
112000
110000
108000
106000
104000
102000
100000
AOM-1502-016
98000
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 7
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
7000 FT
ISA + °C
–10
0
10
20
–20
8000 FT
ISA + °C
–10
0
10
20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
319
7
2
310
7
2
302
7
2
294
7
2
286
7
2
278
6
2
271
6
2
263
6
1
256
6
1
333
8
2
325
8
2
316
7
2
308
7
2
299
7
2
291
7
2
283
7
2
275
6
1
267
6
1
349
8
2
340
8
2
331
8
2
322
7
2
313
7
2
305
7
2
296
7
2
288
7
2
280
6
1
365
8
2
355
8
2
346
8
2
337
8
2
327
8
2
319
7
2
310
7
2
301
7
2
293
7
2
403
10
2
392
10
2
381
10
2
371
9
2
361
9
2
350
9
2
341
9
2
331
8
2
321
8
2
364
9
2
355
8
2
345
8
2
336
8
2
327
8
2
318
8
2
309
7
2
301
7
2
292
7
2
381
9
2
371
9
2
361
9
2
352
8
2
342
8
2
333
8
2
323
8
2
314
7
2
306
7
2
399
9
2
388
9
2
378
9
2
368
9
2
358
8
2
348
8
2
338
8
2
329
8
2
320
7
2
417
10
2
406
9
2
395
9
2
385
9
2
374
9
2
364
8
2
354
8
2
344
8
2
334
8
2
461
12
3
448
12
3
436
11
2
424
11
2
412
11
2
401
10
2
389
10
2
378
10
2
367
9
2
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
10
10
6
10
10
4
7
7
0
0
0
0
0
0
6
10
10
6
10
10
4
8
8
0
1
1
0
0
0
96000
94000
92000
90000
88000
86000
84000
82000
80000
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 8
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 7000 AND 8000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
AOM-1502-016
For Antiice ON,
increase
–20
7000 FT
ISA + °C
–10
0
10
20
–20
8000 FT
ISA + °C
–10
0
10
20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
248
6
1
241
6
1
234
5
1
227
5
1
220
5
1
213
5
1
206
5
1
260
6
1
252
6
1
245
6
1
237
5
1
230
5
1
222
5
1
215
5
1
272
6
1
264
6
1
256
6
1
248
6
1
240
5
1
233
5
1
225
5
1
284
6
1
276
6
1
268
6
1
259
6
1
251
6
1
243
6
1
235
5
1
312
8
2
302
8
2
293
7
2
284
7
2
275
7
2
266
7
1
257
6
1
284
7
2
275
6
2
267
6
1
259
6
1
251
6
1
243
6
1
235
5
1
297
7
2
288
7
2
279
7
2
271
6
1
262
6
1
254
6
1
246
6
1
310
7
2
301
7
2
292
7
2
283
7
2
274
6
1
266
6
1
257
6
1
325
8
2
315
7
2
306
7
2
296
7
2
287
7
2
278
6
1
269
6
1
356
9
2
345
9
2
335
9
2
324
8
2
314
8
2
304
8
2
294
8
2
Fuel
Distance
Time
(%)
(%)
(%)
5
10
9
5
10
10
4
7
7
0
0
0
0
0
0
5
10
9
5
10
10
4
8
7
0
1
1
0
0
0
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 9
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
9000 FT
ISA + °C
–10
0
10
20
–20
10000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
516
13
3
503
12
3
490
12
3
478
12
3
466
11
3
455
11
3
443
11
3
432
10
2
421
10
2
540
13
3
526
13
3
513
12
3
501
12
3
488
12
3
476
11
3
464
11
3
452
11
3
440
11
2
565
14
3
551
13
3
537
13
3
524
13
3
511
12
3
498
12
3
485
12
3
473
11
3
461
11
3
591
14
3
576
14
3
562
13
3
548
13
3
534
13
3
521
12
3
508
12
3
495
12
3
482
11
3
661
17
4
644
17
4
627
17
4
610
16
4
594
16
3
579
15
3
563
15
3
548
14
3
534
14
3
574
14
3
560
14
3
546
13
3
532
13
3
519
13
3
506
12
3
493
12
3
480
12
3
468
12
3
601
15
3
586
14
3
571
14
3
557
14
3
543
13
3
529
13
3
516
13
3
502
12
3
489
12
3
629
15
3
613
15
3
598
15
3
583
14
3
568
14
3
554
14
3
540
13
3
526
13
3
512
13
3
658
16
4
641
16
3
625
15
3
610
15
3
594
14
3
579
14
3
565
14
3
550
13
3
536
13
3
736
20
4
717
19
4
698
19
4
680
18
4
662
18
4
644
17
4
627
17
4
610
16
4
594
16
3
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
11
11
7
11
11
5
9
9
1
2
2
0
0
0
7
11
11
7
11
11
5
9
9
2
4
4
0
0
0
114000
112000
110000
108000
106000
104000
102000
100000
98000
20
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 10
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
–20
9000 FT
ISA + °C
–10
0
10
20
–20
10000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
410
10
2
399
10
2
388
9
2
378
9
2
368
9
2
358
9
2
348
8
2
338
8
2
328
8
2
429
10
2
418
10
2
406
10
2
396
9
2
385
9
2
374
9
2
364
9
2
354
8
2
344
8
2
449
11
2
437
10
2
425
10
2
414
10
2
403
10
2
392
9
2
381
9
2
370
9
2
360
9
2
469
11
2
457
11
2
445
11
2
433
10
2
421
10
2
410
10
2
398
9
2
387
9
2
376
9
2
519
14
3
505
13
3
491
13
3
478
13
3
464
12
3
451
12
3
438
12
3
425
11
2
413
11
2
455
11
3
444
11
3
432
11
2
420
10
2
409
10
2
397
10
2
386
9
2
375
9
2
365
9
2
477
12
3
464
11
3
452
11
3
440
11
2
428
10
2
416
10
2
404
10
2
393
10
2
382
9
2
499
12
3
486
12
3
473
12
3
460
11
3
448
11
2
435
11
2
423
10
2
411
10
2
399
10
2
522
13
3
508
12
3
495
12
3
481
12
3
468
11
3
455
11
2
443
11
2
430
10
2
418
10
2
578
16
3
562
15
3
546
15
3
531
14
3
516
14
3
502
13
3
487
13
3
473
13
3
459
12
3
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
10
10
6
11
10
5
8
8
1
2
2
0
0
0
6
10
10
6
11
10
5
9
9
2
3
3
0
0
0
96000
94000
92000
90000
88000
86000
84000
82000
AOM-1502-016
80000
20
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 11
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 9000 AND 10000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
For Antiice ON,
increase
–20
9000 FT
ISA + °C
–10
0
10
20
–20
10000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
319
8
2
309
7
2
300
7
2
291
7
2
282
7
2
273
7
2
264
6
2
334
8
2
324
8
2
314
7
2
305
7
2
295
7
2
286
7
2
276
7
2
349
8
2
339
8
2
329
8
2
319
8
2
309
7
2
299
7
2
289
7
2
365
9
2
354
8
2
344
8
2
333
8
2
323
8
2
312
7
2
302
7
2
401
11
2
389
10
2
377
10
2
365
10
2
353
9
2
342
9
2
331
9
2
354
9
2
344
8
2
333
8
2
323
8
2
313
8
2
303
7
2
293
7
2
371
9
2
360
9
2
349
8
2
338
8
2
328
8
2
317
8
2
307
7
2
388
9
2
376
9
2
365
9
2
354
9
2
343
8
2
332
8
2
321
8
2
406
10
2
394
9
2
382
9
2
370
9
2
359
9
2
347
8
2
336
8
2
446
12
3
432
12
3
419
11
2
406
11
2
393
10
2
380
10
2
368
10
2
Fuel
Distance
Time
(%)
(%)
(%)
5
10
10
5
10
10
4
8
8
1
2
2
0
0
0
5
10
10
6
10
10
4
8
8
2
3
3
0
0
0
20
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 12
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
–20
11000 FT
ISA + °C
–10
0
10
20
–20
12000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
665
17
4
648
17
4
632
16
4
616
16
4
601
15
4
585
15
3
570
15
3
556
14
3
541
14
3
696
18
4
679
17
4
662
17
4
645
16
4
629
16
4
613
16
3
597
15
3
582
15
3
567
14
3
729
18
4
711
18
4
693
18
4
675
17
4
658
17
4
642
16
4
625
16
3
609
15
3
593
15
3
762
19
4
743
19
4
725
18
4
706
18
4
689
17
4
671
17
4
654
16
4
637
16
3
621
16
3
855
24
5
833
23
5
811
23
5
789
22
5
768
21
5
748
21
4
728
20
4
708
20
4
689
19
4
762
20
5
743
20
4
725
19
4
706
19
4
688
18
4
671
18
4
654
17
4
637
17
4
620
17
4
798
21
5
778
21
5
759
20
4
739
20
4
721
19
4
702
19
4
684
18
4
667
18
4
649
17
4
836
22
5
815
22
5
794
21
4
774
20
4
755
20
4
735
19
4
717
19
4
698
18
4
680
18
4
874
23
5
853
22
5
831
22
5
810
21
4
790
21
4
769
20
4
750
20
4
730
19
4
711
19
4
986
29
6
960
28
6
934
27
6
909
26
5
885
26
5
861
25
5
838
24
5
815
24
5
793
23
5
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
7
11
11
7
12
12
6
10
10
3
6
5
0
0
0
7
12
12
7
12
12
6
11
11
4
7
7
0
0
0
114000
112000
110000
108000
106000
104000
102000
100000
AOM-1502-016
98000
20
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 13
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
11000 FT
ISA + °C
–10
0
10
20
–20
12000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
527
13
3
513
13
3
500
13
3
486
12
3
473
12
3
460
12
3
447
11
3
434
11
3
422
11
2
552
14
3
537
14
3
523
13
3
509
13
3
495
13
3
481
12
3
468
12
3
455
11
3
442
11
3
578
15
3
562
14
3
547
14
3
533
13
3
518
13
3
504
13
3
490
12
3
476
12
3
462
12
3
604
15
3
588
15
3
573
14
3
557
14
3
542
14
3
527
13
3
512
13
3
498
12
3
483
12
3
670
19
4
652
18
4
634
18
4
616
17
4
599
17
4
582
16
3
565
16
3
549
15
3
532
15
3
604
16
4
588
16
3
572
15
3
557
15
3
542
14
3
527
14
3
512
14
3
498
13
3
483
13
3
632
17
4
616
16
4
599
16
3
583
15
3
567
15
3
551
15
3
536
14
3
521
14
3
506
13
3
662
17
4
645
17
4
627
17
4
610
16
3
594
16
3
577
15
3
561
15
3
545
14
3
530
14
3
693
18
4
674
18
4
656
17
4
639
17
4
621
16
3
604
16
3
587
15
3
570
15
3
554
14
3
772
22
5
750
22
4
730
21
4
709
21
4
689
20
4
670
19
4
650
19
4
631
18
4
613
18
4
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
6
11
10
6
11
11
5
10
9
3
5
5
0
0
0
6
11
11
7
12
11
6
10
10
4
7
6
0
0
0
96000
94000
92000
90000
88000
86000
84000
82000
80000
20
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 14
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 11000 AND 12000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
AOM-1502-016
For Antiice ON,
increase
–20
11000 FT
ISA + °C
–10
0
10
20
–20
12000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
410
10
2
398
10
2
386
10
2
374
9
2
362
9
2
350
9
2
339
9
2
429
11
2
416
10
2
404
10
2
391
10
2
379
10
2
367
9
2
355
9
2
449
11
3
435
11
2
422
11
2
409
10
2
397
10
2
384
10
2
371
9
2
469
12
3
455
11
2
442
11
2
428
11
2
415
10
2
401
10
2
388
10
2
517
14
3
501
14
3
485
13
3
470
13
3
455
13
3
440
12
3
426
12
3
469
12
3
455
12
3
442
12
3
428
11
3
415
11
2
402
11
2
389
10
2
491
13
3
477
13
3
462
12
3
448
12
3
434
11
3
420
11
2
407
11
2
514
14
3
499
13
3
484
13
3
469
12
3
455
12
3
440
12
2
426
11
2
538
14
3
522
14
3
506
13
3
491
13
3
475
12
3
460
12
3
445
12
2
594
17
4
576
17
3
559
16
3
541
16
3
524
15
3
507
15
3
490
14
3
Fuel
Distance
Time
(%)
(%)
(%)
6
10
10
6
11
10
5
9
9
2
5
4
0
0
0
6
11
10
6
11
11
5
10
9
3
6
6
0
0
0
20
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 15
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
13000 FT
ISA + °C
–10
0
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
825
23
5
805
22
5
785
22
5
765
21
5
745
20
4
726
20
4
708
19
4
689
19
4
671
18
4
864
24
5
843
23
5
822
22
5
801
22
5
781
21
5
761
21
4
741
20
4
722
20
4
703
19
4
905
25
5
883
24
5
861
23
5
839
23
5
818
22
5
797
22
5
776
21
4
756
21
4
736
20
4
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
7
12
12
8
13
12
7
12
11
114000
112000
110000
108000
106000
104000
102000
100000
98000
20
–20
14000 FT
ISA + °C
–10
0
10
948 1072
26
32
5
6
924 1044
25
31
5
6
901 1016
24
30
5
6
878 989
24
30
5
6
856 962
23
29
5
6
834 936
23
28
5
6
812 911
22
27
5
6
791 886
21
27
4
5
770 862
21
26
4
5
890
25
5
867
24
5
845
24
5
824
23
5
803
23
5
783
22
5
762
21
5
743
21
4
723
20
4
932
26
5
908
26
5
886
25
5
863
24
5
841
24
5
820
23
5
799
22
5
778
22
5
757
21
4
8
13
13
8
13
13
10
5
8
8
1
1
1
20
976 1022 1161
27
28
36
6
6
7
952 996 1130
27
28
35
5
6
7
928 971 1100
26
27
34
5
5
7
904 947 1070
25
26
33
5
5
7
881 922 1041
25
26
32
5
5
6
859 899 1013
24
25
31
5
5
6
837 875
986
23
24
30
5
5
6
815 853
959
23
24
30
5
5
6
793 830
933
22
23
29
5
5
6
7
12
12
5
9
9
2
3
3
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 16
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
–20
13000 FT
ISA + °C
–10
0
10
20
–20
14000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
654
18
4
637
17
4
620
17
4
603
16
4
586
16
4
570
16
3
554
15
3
539
15
3
523
14
3
685
19
4
667
18
4
649
18
4
631
17
4
614
17
4
597
16
3
580
16
3
564
15
3
548
15
3
717
19
4
698
19
4
679
18
4
661
18
4
643
17
4
625
17
4
608
16
3
591
16
3
574
16
3
750
20
4
730
20
4
711
19
4
692
19
4
673
18
4
654
18
4
636
17
4
618
17
3
600
16
3
839
25
5
816
24
5
793
24
5
771
23
5
749
22
5
728
22
4
707
21
4
686
20
4
666
20
4
704
20
4
685
19
4
667
19
4
649
18
4
631
18
4
614
17
4
597
17
4
580
16
3
563
16
3
738
21
4
718
20
4
699
20
4
680
19
4
661
18
4
643
18
4
625
17
4
607
17
4
590
16
3
773
22
4
752
21
4
732
20
4
712
20
4
693
19
4
674
19
4
655
18
4
636
18
4
618
17
4
809
22
5
787
22
4
766
21
4
745
21
4
725
20
4
705
20
4
685
19
4
666
18
4
647
18
4
907
28
6
882
27
5
857
26
5
833
26
5
810
25
5
786
24
5
764
23
5
742
23
5
720
22
4
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
7
12
11
7
12
12
6
11
10
4
8
7
1
1
1
7
12
12
7
12
12
7
12
11
5
9
8
2
3
3
96000
94000
92000
90000
88000
86000
84000
82000
AOM-1502-016
80000
20
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 17
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 13000 AND 14000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
For Antiice ON,
increase
–20
13000 FT
ISA + °C
–10
0
10
20
–20
14000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
508
14
3
493
13
3
478
13
3
463
13
3
449
12
3
435
12
3
421
11
3
532
14
3
516
14
3
501
14
3
485
13
3
470
13
3
455
12
3
440
12
3
557
15
3
540
15
3
524
14
3
508
14
3
492
13
3
477
13
3
461
12
3
583
16
3
565
15
3
548
15
3
532
14
3
515
14
3
498
13
3
482
13
3
646
19
4
626
19
4
607
18
4
588
17
4
569
17
3
551
16
3
533
16
3
547
15
3
531
15
3
515
14
3
499
14
3
483
13
3
468
13
3
453
13
3
573
16
3
556
15
3
539
15
3
523
15
3
506
14
3
490
14
3
474
13
3
600
17
3
582
16
3
565
16
3
547
15
3
530
15
3
513
14
3
497
14
3
628
17
4
609
17
3
591
16
3
573
16
3
555
15
3
537
15
3
520
14
3
698
21
4
677
21
4
656
20
4
635
19
4
615
19
4
595
18
4
576
18
4
Fuel
Distance
Time
(%)
(%)
(%)
6
11
11
6
11
11
6
10
10
4
7
7
1
1
1
6
12
11
7
12
11
6
11
10
4
8
7
1
3
2
20
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 18
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
–20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
955
28
6
931
27
6
907
26
6
884
26
5
862
25
5
840
24
5
818
24
5
797
23
5
776
22
5
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
8
14
13
114000
112000
110000
108000
106000
104000
102000
100000
AOM-1502-016
98000
15000 FT
ISA + °C
–10
0
10
20
1001 1049 1098 1252
29
30
31
40
6
6
6
8
975 1022 1070 1219
28
29
31
39
6
6
6
8
951
996 1043 1186
27
29
30
38
6
6
6
7
927
971 1016 1154
27
28
29
37
6
6
6
7
903
946
990 1122
26
27
28
36
5
5
6
7
880
922
965 1092
25
26
28
35
5
5
5
7
857
898
940 1062
25
26
27
34
5
5
5
7
835
874
915 1033
24
25
26
33
5
5
5
6
813
852
891 1005
23
24
25
32
5
5
5
6
8
14
13
8
13
12
6
11
10
3
6
5
–20
16000 FT
ISA + °C
–10
0
10
20
1022 1071 1123 1176 1347
30
32
33
35
44
6
6
7
7
8
996 1044 1094 1146 1310
30
31
32
34
43
6
6
6
7
8
971 1017 1066 1116 1275
29
30
31
33
42
6
6
6
6
8
946
991 1039 1088 1240
28
29
31
32
40
6
6
6
6
8
921
966 1012 1060 1206
27
29
30
31
39
6
6
6
6
8
898
941 986 1032 1173
27
28
29
30
38
6
6
6
6
7
874
916 960 1005 1141
26
27
28
29
37
5
6
6
6
7
851
892 935 979 1109
25
26
28
29
36
5
5
5
6
7
829
869 910 953 1078
25
26
27
28
35
5
5
5
5
7
9
14
14
9
15
14
8
14
13
7
12
11
4
8
6
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 19
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
15000 FT
ISA + °C
–10
0
10
20
–20
16000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
755
22
5
735
21
4
715
21
4
696
20
4
677
20
4
658
19
4
640
18
4
622
18
4
604
17
4
791
23
5
770
22
5
749
22
4
729
21
4
709
20
4
690
20
4
670
19
4
651
19
4
633
18
4
829
24
5
807
23
5
785
22
5
764
22
4
743
21
4
722
21
4
702
20
4
682
19
4
663
19
4
868
25
5
845
24
5
822
23
5
799
23
5
778
22
4
756
22
4
735
21
4
714
20
4
694
20
4
977
31
6
949
30
6
923
29
6
897
28
6
871
27
5
846
27
5
822
26
5
798
25
5
774
24
5
807
24
5
785
23
5
764
23
5
743
22
5
723
21
4
703
21
4
683
20
4
664
20
4
645
19
4
846
25
5
823
24
5
801
24
5
779
23
5
757
22
5
736
22
4
716
21
4
696
20
4
676
20
4
886
26
5
862
25
5
839
25
5
816
24
5
794
23
5
772
23
5
750
22
4
729
21
4
708
21
4
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
7
13
12
8
13
13
7
12
12
5
10
9
3
5
4
8
13
13
8
14
13
7
13
12
96000
94000
92000
90000
88000
86000
84000
82000
80000
20
928 1048
27
34
5
7
903 1019
26
33
5
6
878
990
26
32
5
6
854
962
25
31
5
6
831
934
24
30
5
6
808
907
24
29
5
6
785
881
23
29
5
5
763
855
22
28
4
5
741
830
22
27
4
5
6
11
10
4
7
6
6-10
Copyright © by Embraer. Refer to cover page for details.
Page 20
Climb
REVISION 23
AOM-1502-016
BLEED: OPEN
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 15000 AND 16000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
BLEED: OPEN
ALL ENGINE TYPES
WEIGHT
(lb)
78000
76000
74000
72000
70000
68000
66000
AOM-1502-016
For Antiice ON,
increase
–20
15000 FT
ISA + °C
–10
0
10
20
–20
16000 FT
ISA + °C
–10
0
10
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
586
17
4
569
16
3
552
16
3
535
15
3
518
15
3
502
14
3
485
14
3
614
18
4
596
17
4
578
17
3
560
16
3
543
15
3
525
15
3
508
14
3
643
18
4
624
18
4
605
17
4
587
17
3
569
16
3
550
16
3
533
15
3
673
19
4
653
19
4
634
18
4
614
17
3
595
17
3
576
16
3
557
16
3
751
24
5
728
23
4
706
22
4
684
21
4
662
21
4
640
20
4
619
19
4
626
18
4
607
18
4
589
17
4
571
17
4
553
16
3
535
16
3
518
15
3
656
19
4
636
19
4
617
18
4
598
18
4
580
17
3
561
16
3
543
16
3
687
20
4
667
19
4
647
19
4
627
18
4
607
18
4
588
17
3
569
17
3
719
21
4
698
20
4
677
20
4
656
19
4
636
18
4
615
18
4
595
17
3
805
26
5
781
25
5
756
24
5
733
24
5
709
23
4
686
22
4
664
21
4
Fuel
Distance
Time
(%)
(%)
(%)
7
12
12
7
12
12
6
12
11
5
9
8
2
5
4
7
13
12
7
13
12
7
12
11
5
10
9
3
6
5
20
6-10
Copyright © by Embraer. Refer to cover page for details.
REVISION 23
Climb
Page 21
FLIGHT PLANNING
AIRPLANE
OPERATIONS
MANUAL
CLIMB PLANNING - ALL ENGINES OPERATING
ALTITUDE: SEA LEVEL TO 17000 AND 18000 FT
SPEED SCHEDULE
250 KIAS UP TO 10000 FT, INCREASING LINEARLY TO 290 KIAS AT
12000 FT, MAINTAINING 290 KIAS UP TO 28900 FT AND MACH 0.75
ABOVE 28900 FT.
CRUISE CONFIGURATION
ALL ENGINE TYPES
WEIGHT
(lb)
–20
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
Fuel
Distance
Time
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
lb
NM
min
1091
33
7
1063
32
7
1035
32
6
1009
31
6
983
30
6
957
29
6
932
28
6
908
28
6
884
27
5
For Anti- Fuel
ice ON, Distance
increase Time
(%)
(%)
(%)
9
15
14
114000
112000
110000
108000
106000
104000
102000
100000
98000
17000 FT
ISA + °C
–10
0
20
–20
1143 1199 1255 1445