AOM-145-1114-71-SEC-1-00

AIRPLANEOPERATIONS

MANUAL

GENERAL

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SECTION 1-00

GENERAL INFORMATIONAND DEFINITION OF TERMS

TABLE OF CONTENTSPage Block

General Information ................................................................... 1-00-00Definition of Terms..................................................................... 1-00-10Units Conversion........................................................................ 1-00-20EICAS Versions ......................................................................... 1-00-30Service Bulletin Table ................................................................ 1-00-35

GENERAL AIRPLANEOPERATIONS

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GENERAL INFORMATIONThis Airplane Operations Manual provides useful information tocomplement the Airplane Flight Manual, Weight and Balance Manualand the Master Minimum Equipment List. It must be used inconjunction with those publications to safe and efficiently operate allthe EMB-135 and EMB-145 models.

Any difference found between the data in the Airplane OperationsManual and the approved Manuals is due to airplane modifications andscheduling of amendments to publications. In the event of such adifference, the data in the approved manuals must prevail.

The Airplane Operations Manual philosophy and structure aredescribed on the next pages.

In the EMBRAER Operational Manuals, the Brazilian Civil Aviationauthority is identified as both ANAC and CTA. Therefore, wheneveryou find either, it corresponds to Brazilian certification. This is becausesince March 26, 2006, the Brazilian Civil Aviation authority wasreplaced by Civil Aviation National Agency (ANAC) instead of CTA.

Similarly, the European Aviation Safety Agency (EASA) co-exists withJAA. So, from now on, you may find JAA/EASA or just JAA, with bothcorresponding to European certification.

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OPERATIONAL REQUIREMENTS AND THE AIRPLANEOPERATIONS MANUAL

The existence of fleets composed of airplanes or other kind of aircraftmade by different manufacturers, led the Airworthiness Authorities torequire operators' certification, in addition to the airplane's certification.The idea is to standardize manuals, training and operation, so as tomake it easier for a pilot to change equipment. For instance, if a pilotused to fly an EMB-120 is scheduled to fly an EMB-145, the trainingsyllabus from the EMB-145 has to be very similar to the ones for theEMB-120; the operator normal, abnormal and emergency proceduresmust be quite similar when different from AFM, as well as the manualsfor both airplanes. By doing so, the operator will assure that humanfactors/ errors are minimized.Some operational requirements just define the main subjects that mustbe presented in an Airplane Operations Manual matter. However, evendetailing the Airplane Operations Manual at that level, all therequirements let the operators free to use different Airplane OperationsManual structures, depending on the manuals. that have been alreadyissued. Therefore, EMBRAER has developed this Airplane OperationsManual trying to cover, in the best possible way, the most currentlyused requirements. By doing so, it is possible for an operator to usethe EMBRAER Airplane Operations Manual, by just adding somemissing information that is specific to that operator.Following is a suggested Airplane Operations Manual structure tocomply with most of the Operation Requirements:

PART A

Presents operator’s administrative information, such as who are thepresident , vice-president, the managers, who is the chief pilot for theEMB-145, who is the responsible for revising manuals, where theoffices and bases are located, etc...

PART B

Presents airplane related information, like procedures, performance,dispatch procedures, Weight and Balance, bulletins and systemsdescription.


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PART C

Presents the operator’s airport and route information (performance andnavigation).

PART D

Presents training information.

EMBRAER AIRPLANE OPERATIONS MANUAL

This EMBRAER Airplane Operations Manual covers only Part B. PartsA and D should be generated by the operator only. Part C can begenerated by the operator with the help of EMBRAER operationssoftware (runway analysis, driftdown , and route analysis).

AIRPLANE OPERATIONS MANUAL STRUCTURE

The EMBRAER Airplane Operations Manual is organized in twovolumes, with the following contents:

− Volume 1:

− 1-00 General Information and Definition of Terms

− 1-01 Limitations

− 1-02 Normal Procedures

− 1-03 Emergency and Abnormal Procedures

− 1-04 Performance

− 1-05 Flight Planning

− 1-06 Weight and Balance

− 1-07 Loading

− 1-08 Configuration Deviation List

− 1-09 Dispatch Deviations Procedures Manual

− 1-10 Emergency Information

− 1-11 Emergency Evacuation

− 1-12 Ground Servicing

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− Volume 2:

− 2-1 Airplane Description

− 2-2 Equipment and Furnishings

− 2-3 Emergency Equipment

− 2-4 Crew Awareness

− 2-5 Electrical

− 2-6 Lighting

− 2-7 Fire Protection

− 2-8 Fuel

− 2-9 Auxiliary Power Unit

− 2-10 Powerplant

− 2-11 Hydraulic

− 2-12 Landing Gear and Brakes

− 2-13 Flight Controls

− 2-14 Pneumatics, Air Conditioning and Pressurization

− 2-15 Ice and Rain Protection

− 2-16 Oxygen

− 2-17 Flight Instruments

− 2-18 Navigation and Communication

− 2-19 AutopilotEach of the above sections may be divided into smaller parts, calledblocks. Such blocks are identified by the number of the sectionfollowed by a two-digit number.For example:

Section 1-04 can be divided as follows:− 1-04-00 Introduction

− 1-04-05 Wind and altitude

− 1-04-10 Thrust Setting

− 1-04-15 Takeoff

− 1-04-20 Supplementary Takeoff

− 1-04-25 Approach

− 1-04-30 Landing


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The page numbering of each part is independent from the remainingparts. Each page number is presented just to the right of the blocknumber.

As a complement, a code number is provided, to help identifying towhich configuration each block is applicable. Some codes may beapplicable to more than one configuration, whilst more than one codemay be specific to one configuration.As an example, there could be:

Block Codes Number of pages Numbering

1-04-00 01 2 1 to 2

1-04-05 01 6 1 to 6

01 20 1 to 20

1-04-10 02 20 1 to 20

03 20 1 to 20

01 6 1 to 6

1-04-15 02 6 1 to 6

03 10 1 to 10

04 4 1 to 4

01 24 1 to 24

1-04-20 02 24 1 to 24

05 20 1 to 20

01 4 1 to 4

1-04-25 03 4 1 to 4

04 4 1 to 4

07 4 1 to 4

01 6 1 to 6

1-04-30 02 4 1 to 4

03 6 1 to 6

04 4 1 to 4

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REVISIONS

EMBRAER may revise this manual periodically as required to updateinformation or to provide information not available at the time ofprinting the original issue. Revised data may result from EMBRAERapproved airplane modifications or from improved techniques gainedthrough operational experience. They are either replacements oradditional pages. A vertical line in the outside margin indicateschanges to the text.A vertical line adjacent to the page number indicates relocated orrearranged text or illustrations.The basic issuance date of this Manual is presented in the title page.The revisions affecting this Manual to be issued from the basicissuance date onwards, will be numbered sequentially (Rev. 1, 2, 3etc.), even for such pages bearing those earlier revision-denotingsymbols.

LIST OF EFFECTIVE PAGES

A list of Effective Pages for all Sections is located at the beginning ofthis Manual. This list presents the issuance date of each page and it isrevised together with the Manual. Its purpose is to check if all therevised pages of a revision have been correctly sent to the purchaser.


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DEFINITION OF TERMSThe following definitions apply to the terms below:

WARNING: OPERATING PROCEDURES, TECHNIQUES ANDOTHER RELATED INFORMATION WHICH MAYRESULT IN PERSONAL INJURY OR LOSS OF LIFE,IF NOT CAREFULLY FOLLOWED.

CAUTION: OPERATING PROCEDURES, TECHNIQUES ANDOTHER RELATED INFORMATION WHICH MAYRESULT IN DAMAGE OR DESTRUCTION OFEQUIPMENT, IF NOT CAREFULLY FOLLOWED.

NOTE: Operating procedures, techniques and other relatedinformation which are considered essential to emphasize.


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ABBREVIATIONS AND ACRONYMS

ABBREVIATIONSOR ACRONYMS

MEANING

ºC Degree Celsius

ºF Degree Fahrenheit

ft Feet

g Gravity Acceleration

h Hour

Hz Hertz

in.Hg Inches of Mercury

kg Kilogram

km Kilometer

kph Kilograms per Hour

kt Knot

lb Pounds

m Meter

mb Milibar

min Minute

mm Millimeter

mph Miles per Hour

nm Nautical Mile

psi Pound per Square Inch

sec Second

A

A Ampere

A/C Aircraft

AC Alternating Current

ACM Air Cycle Machine

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MEANING

ACOC Air Cooled Oil Cooler

ACT Actuation, Active

ADC Air Data Computer

ADF Automatic Direction Finder

ADJ Adjustment

ADV Advance

AFM Airplane Flight Manual

AFS Autoflight System

AGL Above Ground Level

AHC Attitude and Heading Computer

AHRS Attitude and Heading Reference System

AIL Aileron

ALC APU Line Contactor

ALT Altitude

ALTN Alternate

AM Amplitude Modulation

ANAC Agência Nacional de Aviação Civil (BrazilianCivil Aviation Authority)

ANR Automatic Navigation Realignment

ANT Antenna

AOA Angle of Attack

AP Autopilot

API Antenna Position Indicator

APR Automatic Power Reserve

APU Auxiliary Power Unit

ASC APU Starting Contactor

ATC Air Traffic Control

ATDT, ATTD Attendant


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MEANING

ATS Air Turbine Starter

ATT Attitude

ATTCS Automatic Takeoff Thrust Control System

AUTO Automatic

AUX Auxiliary

AVAIL Available

AWU Aural Warning Unit

B

B/C Back Course

BACV Bleed Air Check Valve

BAGG Baggage

BATT Battery

BBC Backup Battery Contactor

BC Battery Contactor

BCU Brake Control Unit

BCV Brake Control Valve

BFO Beat Frequency Oscillator

BIT Built In Test

BKUP INPH Back-Up Interphone

BLD Bleed

BTC Bus Tie Contactor

BTL Bottle

C

CAB EMERG Cabin Emergency

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MEANING

CAS Calibrated Airspeed, Crew Alerting System

CBV Cross Bleed Valve

CCDL Cross-Channel Data Link

CDH Clearance Delivery Head

CDL Configuration Deviation List

CCW Counterclockwise

CG Center of Gravity

CIS Cabin Interphone System

CL Climb

CLB Climb

CLR Clear

CLSD Closed

CMC Central Maintenance Computer

COMM, COM Communication

CON Continuous

CPAM Cabin Pressure Acquisition Module

CPCS Cabin Pressure Control System

CR Cruise

CRZ Cruise

CVG Compressor Variable Geometry

CVR Cockpit Voice Recorder

CW Clockwise

D

DAP Digital Audio Panel


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MEANING

DAU Data Acquisition Unit

DC Direct Current, Digital Controller

DEC Decrease

DET Detector

DFDR Digital Flight Data Recorder

DG Directional Gyro

DH Decision Height

DISC Disconnect

DME Distance Measurement Equipment

DMU Data Management Unit

DN Down

E

EADI Electronic Attitude Director Indicator

EBC Essential Bus Contactor

EBV Engine Bleed Valve

ECM Electronic Control Module

ECS Environmental Control System

ECU Environmental Control Unit

EDL Electrical Distribution Logic

EDS Electrical Distribution System

EFIS Electronic Flight Instrument System

EGPWS Enhanced Ground Position Warning System

EGT Exhaust Gas Temperature

EHSI Electronic Horizontal Situation Indicator

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MEANING

EIC Essential Interconnection Contactor

EICAS Engine Indication and Crew Alerting System

ELEC Electrical

ELEV Elevator

ELT Emergency Locator Transmitter

EMG, EMERG Emergency

EMER PILOT Emergency Pilot

ENG Engine

ERR Error

ESU Electronic Sequence Unit

ET Elapsed Time

EXT External

EXTG Extinguish

F

FADEC Full Authority Digital Electronic Control

FCOC Fuel Cooled Oil Cooler

FDAU Flight Data Acquisition Unit

FDRS Flight Data Recorder System

FECU Flap Electronic Control Unit

FLC Flight Level Change Mode

FLX Flexible

FMS Flight Management System

FPDU Flap Power and Drive Unit

FPLN Flight Plan

FPMU Fuel Pump and Metering Unit

FQIS Fuel Quantity Indicating System


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MEANING

FR Fuel Remaining

FSBY Forced Standby

FTB Flap Transmission Brake

FU Fuel Used

FVS Flap Velocity Sensor

FWD Forward

G

G/S, GS Glide Slope

GCU Generator Control Unit

GI Ground Idle

GLC Generator Line Contactor

GMAP Ground Mapping

GMT Greenwich Mean Time

GND Ground

GPC Ground Power Contactor

GPS Global Positioning System

GPU Ground Power Unit

GPWS Ground Proximity Warning System

H

HDG Heading

HF High Frequency

HP High Pressure

hPa HectoPascal

HSCU Horizontal Stabilizer Control Unit

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MEANING

HSI Horizontal Situation Indicator

HSV High Stage Valve

HYDR Hydraulic

I

IAC Integrated Avionics Computer

IAS Indicated Airspeed

IC Integrated Computer

ICAO International Civil Aviation Organization

ICU Integrated Communication UnitInterphone Control Unit

IFR Instrument Flight Rules

IFOG Interferometer Fiber Optic Gyros

ILS Instrument Landing System

IM Integrated Computer Configuration Module

INBD Inboard

INC Increase

INOP Inoperative

INTPH Interphone

INU Integrated Navigation Unit

IPS Inches Per Second

IRS Inertial Reference System

IRU Inertial Reference Unit

ISA International Standard Atmosphere

ISIS Integrated Standby Instrument System

ITT Interturbine Temperature

K

KCAS Calibrated Airspeed in Knots

KEAS Equivalent Airspeed in Knots

kHz Kilohertz


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MEANING

K

KIAS Indicated Airspeed in Knots

L

LAV Lavatory

LEI Local Engine Inoperative

LGEU Landing Gear Electronic Unit

LH Left-hand

LOC Localizer

LOGO Logotype

LP Low Pressure

LRN Long Range

LSB Lower Sideband

LSS Lightning Sensor System

LX Lightning Detection

M

M Mach

MAC Mean Aerodynamic Chord

MAN Manual

MAX Maximum

MB Marker Beacon

MEA Minimum Enroute Altitude

MFD Multifunction Display

MFDU Magnetic Flux Detector Unit

MHz Megahertz

MIN Minimum

MKR Marker

MLS Microwave Landing System

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MEANING

MLW Maximum Design Landing Weight

MMEL Master Minimum Equipment List

MMO Maximum Operating Mach

MOW Maximum Design Operating Weight

MRW Maximum Design Ramp Weight

MSU Mode Select Unit

MTOW Maximum Design Takeoff Weight

MZFW Maximum Design Zero Fuel Weight

N

N1 Fan Speed

N2 High-Pressure-Rotor Shaft Speed

NAV Navigation

NB Narrow Bandwidth

NDB Non-directional Beacon

O

OM Operations Manual

OUTBD Outboard

OVHT Overheating

OVLD Overload

OVPRESS Overpressure

OXY Oxygen

P

PAA Passenger Address Amplifier

PAS Passenger Address System

PAST Pilot Activated Self Test

PAX Passenger

PBE Protective Breathing Equipment


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MEANING

PCU Power Control Unit

PDSV Pressure Drop Spill Valve

PFD Primary Flight Display

PMA Permanent Magnet Alternator

POST Power On Self Test

PRCS Process

PRESS Pressure

PRV Pressurizing Valve

PSU Passenger Service Unit

PTT Press To Transmit

Q

QFE Question Field Elevation - Field ElevationPressure (Q-code)

QNE Question Normal Elevation - StandardPressure (1013 hPa/29.92 in.Hg) (Q-code)

QNH Question Normal Height - Sea LevelPressure (Q-code)

QTY Quantity

R

RA Radio Altimeter

RTA Receiver/Transmitter/Antenna

REACT Rain Echo Attenuation CompensationTechnique

REF Reference

REI Remote Engine Inoperative

RH Right-hand

RMI Radio Magnetic Indicator

RMS Radio Management System

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MEANING

RMU Radio Management Unit

RNG Range

RPM Revolution Per Minute

RSB Radio System Bus

S

SAT Static Air Temperature

SBC Shed Bus Contactor

SCV Starting Control Valve

SELCAL Selective Call

SL Sea Level

SLVD Slaved

SOV Shutoff Valve

SPC Stall Protection Computer

SPS Stall Protection System

SQ Squelch

STAB Stabilizer

STBY Stand By

SRN Short Range

SSB Single Sideband

T

TA Traffic Advisory

TAS True Airspeed

TAT Total Air Temperature

TCAS Traffic and Collision Avoidance System

TDR Transponder

TACAN Tactical Air Navigation Aid

TEMP Temperature


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MEANING

TGT Target

TKNB Turn Knob

TLA Thrust Lever Angle

TO Takeoff

TRB Turbulence

TST Test

TWA Time Weighted Average

V

V Volt

V1 Decision Speed

V2 Takeoff Safety Speed

VA Volt-Ampere

VAPP VOR Approach Mode

VA Design Maneuvering Speed

VEF Critical Engine Failure Speed

VFE Maximum Flaps Extended Speed

VFR Visual Flight Rules

VHF Very High Frequency

VLE Maximum Landing Gear Extended Speed

VLF Very Low Frequency

VLO Maximum Landing Gear Operating Speed

VLOF Lift Off Speed

VLV Valve

VMC Visual Minimum Condition

VMCA Air Minimum Control Speed

VMCG Ground Minimum Control Speed

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ABBREVIATIONSOR ACCRONYMS

MEANING

VMO Maximum Operating Speed

VOR VHF Omnidirectional Range

VR Rotation Speed

VREF Landing Reference Speed

VREFXX Landing Reference Speed associated to theflap setting XX

VS Stall Speed

VS Vertical Speed

W

W/S Windshield

WB Weight and Balance

WB Wide Bandwidth

WG Wing

WX Weather Detection

X

X Cross

XFR Transfer


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SYMBOLS AND NOTATIONS

SYMBOL MEANING

ORSHUTOFF VALVE, PRIORITY VALVE

CHECK VALVE

RESTRICTOR

RELIEF VALVE

OPTIONAL EQUIPMENT

SYSTEM MODULE

COMMUNICATION LINE

ELECTRIC PUMP

MECHANIC PUMP

ACCUMULATOR

ELECTRIC CONTACTOR (OPENPOSITION)


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SYMBOL MEANING

SWITCH

NACA AIR INLET

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UNITS CONVERSION

TO CONVERT INTO MULTIPLY BY AND ADD

Degree Celsius(ºC)

Degree Fahrenheit(ºF)

1.8000 +32

Degree Fahrenheit(ºF)

Degree Celsius(ºC)

0.5556 -17.7778

Feet (ft) Meter (m) 0.3048 -

Inches (In) Millimeter (mm) 25.4000 -

Inches of Mercury(in.Hg)

Millibar (mb) 33.8636 -

Kilogram (kg) Pounds (lb) 2.2046 -

Kilogram force perSquare meter(kgf/m2)

Pound per SquareInch (psi)

0.0014 -

Kilometer (km) Nautical Mile (nm) 0.5396 -

Kilometer per hour(km/h)

Knot (kt) 0.5396 -

Knot (kt) Kilometer per hour(km/h)

1.8532 -

Pounds (lb) Kilogram (kg) 0.4536 -

Meter (m) Feet (ft) 3.2808 -

Millibar (mb) Inches of Mercury(in.Hg)

0.0295 -

Millimeter (mm) Inches (In) 0.0394 -

Nautical Mile (nm) Kilometer (km) 1.8532 -

Pound per SquareInch (psi)

Kilogram force perSquare meter(kgf/m2)

703.0740 -


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EICAS VERSIONS

VERSIONS 14A AND 15A

− Fix the Pitch Trim Runaway Monitoring logic (airplanes equippedwith EICAS 14 or 15 are not allowed to use the Autopilot below1500 ft).

VERSION 14

− CAT II capability.

VERSION 15

− Oil pressure green indication increased to 95 psi and red above it(on EICAS 14 it was green up to 90 psi and amber above it).

− Higher brake temperature limits for LR brakes.− ICE/SPS ADVANCED renamed SPS/ICE SPEEDS.− Flaps 18 capability.− Autopilot “wing rocking” improvements.

VERSION 15B

− Fixes the nuisance “Check PFD” message.

VERSION 16

− ENG1 (2) REV DISAGREE message logic improved in order toavoid spurious alarms.

− RUD HDOV PROT FAIL message logic improved in order to avoidspurious alarms.

− Enhanced engine Time Limited Dispatch (TLD) incorporated:− E1 (2) CTL A (B) DEGRAD removed;− E1 (2) CTL A (B) FAIL revised (indicates loss of CVG/MMV

control);− E1 (2) NO DISP incorporated;− E1 (2) SHORT DISP incorporated.


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− Improvements in other engine messages not TLD related:− E1 (2) LOW N1 revised (available only for takeoff below V1-15);− ENG1 (2) OUT incorporated;− ENG 1-2 OUT incorporated;− ENG1 (2) TLA FAIL revised;− FADEC ID NO DISP incorporated;− CHECK xxx PERF incorporated;− E1 (2) ADC DATA FAIL removed.

− New FD control laws with different gain programming for FD modesin order to improve the Flight Director capture speed.

− Incorporation of the VERTICAL and LATERAL MODE OFFmessages.

− IC CONFIG FAIL cyan message (dispatchable) created to indicatea IM-600 failure and use by the IC-600 of the lastest IM-600 validdata.

− CONFIG MISMATCH cyan message (no takeoff) created toindicate that there is a discrepancy in the configuration module (IM-600) of each IC-600. The configuration module stores severalaircraft configuration parameters.

VERSION 16.5

− Anti-Icing system improvements (new messages and logic):− A/I LOW CAPACITY incorporated;− WG1 (2) A/ICE FAIL and WG ASYMETRY removed;− WG A/ICE FAIL incorporated;− ENG A/ICE OVERPRES incorporated;− E1 (2) A/ICE FAIL renamed ENG1 (2) A/ICE FAIL.

− TAT 1-2 HEAT INOP logic changed to improve TAT and SATindications and to increase the probes life.

− Brake messages logic changed to avoid failure messages due topower drop during APU start on ground.

− A1P and A1/3 thrust labels renamed from ALT T/O and T/O, to T/Oand T/O RSV respectivelly.

− ATTCS NO MRGN improvements for the A3 engine.− Support to the 8.33 kHz tune function in the FMZ 2000 FMS.− APU FUEL LO PRESS logic changed to avoid spurious messages

during APU pressure transients .− Support to Inertial System (IRS) as an AHRS replacement.− Improvement in the Cabin Pressure Control System (CPCS)

indication in order to avoid unnecessary amber indication on theEICAS.

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− Correction of autopilot disconnection logic discrepancy when awindshear condition is detected (removes the AFM limitationregarding use of autopilot coupled to FD#2 below 1500 ft).

− Flight Director Altitude Pre-selection Mode Capture logic improved.− LNAV Flight Director logic changed when PFD FMS NAV source is

changed from FMS 1 to 2 or vice-versa, in order to drop the LNAVFD mode. This change makes the FMS lateral navigation modesconsistent with the VOR & LOC FD modes.

− Correction of nuisance LATERAL/VERTICAL MODE OFFmessages when both FD are deselected by the pilots.

− Correction of nuisance LATERAL MODE OFF message when thepilot actuates the Turn Knob with a lateral mode (HDG, NAV, APR)active.

− CHK IC CONFIG amber message (no takeoff) created to replacethe CONFIG MISMATCH message in case of discrepancy betweenthe following information stored in the IM-600: 135 or 145, EngineType, Long Range Fuel Tank or English/Metric Units. CONFIGMISMATCH is still active in case of discrepancy of the otherparameters that do not trigger the CHK IC CONFIG message.

− Oil pressure green indication increased to 115 psi in takeoff mode.

VERSION 17

− Provides interface with the Head-Up Guidance System to allowCAT IIIa operation.

− Inclusion of FDR additional parameters according to FAR 121.344.− Autopilot improvement in the FD VOR mode capture and tracking

for VOR stations without an associated DME.− Provides crosscheck of the CAT 2 annunciators in both PFD,

avoiding a green CAT 2 indication on one side and an amber CAT 2indication on the opposite side.

− Automatic Radio Altimeter reversion in the case of one RA inop onaircraft equipped with two RA’s.

− Adjustments to the Fuel Quantity indication on the MFD, adjustingscale according to the airplane version.

− Inclusion of several messages related to IRS system.− ATTCS NO MRGN message logic improvements.− Electrical system display improvements : valid GPU 0V voltage and

valid Generator 0A amperage.− Oil Pressure limits presented in both amber and red bands above

the green one.


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OIL PRESSURE INDICATION

(1) For any takeoff thrust mode selected and TLA higher than 65º orwith thrust levers set to firewall (go-around), the upper limit ofthe green band is 115 psi. In all other thrust ratings it is 95 psi.

(2) For EICAS version 17 with FADEC B 5.1.1 the amber bandupper limit is 155 psi.

(3) For N2 < 88% the amber band between 34 psi and 50 psi doesnot exist, and the green band lower limit is 34 psi.

(4) For EICAS 14, a placard is installed in the cockpit allowing theoperation in the amber band, between 91 and 115 psi, duringthe takeoff and go-around phases, time limited to 5 minutes.

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VERSION 18 AND 18.5

− Pitch Trim System:− New caution messages PTRIM CPT SW FAIL, PTRIM F/O SW

FAIL and PTRIM BKP SW FAIL;− PTRIM 1(2) INOP renamed to PTRIM MAIN INOP and PTRIM

BACKUP INOP.− Autopilot system improvements:

− Improved localizer capture performance using AP/FD, especiallywhen under crosswind conditions;

− Roll Command inbound during LOC capture;− New Roll Rate limit (7.5 degrees/sec) and Bank Angle limit (30.0

degrees) for ILS Approach mode and LNAV mode in Terminaland Approach phases;

− Cancellation of APR light on Flight Guidance Controller (GC550)when glide slope mode is cancelled;

− Inhibition of VERTICAL MODE OFF message if the FD mode iscancelled by changing the preselected altitude;

− Inhibition of VERTICAL MODE OFF and/or LATERAL MODEOFF messages if a lateral and/or a vertical FD mode iscancelled by transferring the FD control to the cross-side;

− Improvements in the Autopilot system to prevent the AP fromdisconnecting when the speed brake is deployed while operatingin Touch Control Steering (TCS) mode;

− Inhibition of LATERAL MODE OFF message when thenavigation source is changed from one FMS to the cross-sideFMS when LNAV mode is armed.

− HGS:− Modification on the expanded localizer scale/display on the PFD

to help pilot in Cat IIIa operations;− Information to HGS that TOGA button was pressed;− Change of HGS FAIL from ADVISORY to AMBER (caution) to

comply with AC 120-28D requirements.

− AHRS:− New advisory messages AHRS 1-2 NO PPOS, AHRS 1-2 NO

MAG HDG.


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VERSION 19

The EICAS 19 features implemented in the software are describedbelow: Air conditioning system− The Bleed Temperature Pointers were modified to remain amber at

all the times that the messages BLD 1(2) LOW TEMP aredisplayed.

Brake System− New digital brake temperature indication on MFD (if IM-600 Digital

BRK TEMP parameter is enabled).

EICAS Internal Logic− New message DAU AC ID MISCMP.

Electrical System− GPU Voltage Indication modified in order to avoid dashes when the

indication should be 0 V.

Flap System− Flap 22 indication in red on EICAS display and NO TAKEOFF

CONFIG message when the aircraft is not certified to take off withflaps 22º.

Fuel System− New Message FUEL EQ XFEED OPN to inform that the imbalance

was correct and the crossfeed valve is still open.− Fuel Test Page units label modified in order to show the correct

English/Metric configuration.

General Changes− Synchronization of the Speed Target Bug with the previous selected

Speed Target instead of synchronizing with the current aircraft’sspeed shown on the Speed Tape when VS Vertical Flight DirectorMode is de-selected.

− Windshear indication on PFD always in red when RA test button ispressed.

− Due to mandatory installation of IM-600 on this EICAS version andon, the CAT II Operation is available and indicated.

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Anti Ice System− PITOT 1-2-3 INOP messages modified in order to avoid spurious

occurrences during APU starting.

Powerplant System− ENG NO TO DATA message modified in order to avoid an unlikely

scenario of a takeoff performed with only one engine running.− New messages :

− CHECK A1E PERF (only applicable to EMB-145 XR model),− E1-2 FPMU NO DISP (only applicable to EMB-145 XR

model),− E1-2 EXCEEDANCE.

− A1E thrust rating modes included on EICAS/RMU/MFD.− New upper range limit for fuel flow indication due to A1E engine.− ITT and N2 Dynamic Redlines.− Oil Pressure Indication modified in order to avoid spurious

indication of low oil pressure values.− ENG 1-2 REV DISAGREE message change in order to avoid a

failure without indication on EICAS.

Pressurization System− Changes to Cabin Altitude Rate.− New function HIGH ALT on MFD Bezel (only applicable to

EMB-145 XR model).− New message HI ALT LDG-T/O (only applicable to EMB-145 XR

model).− Changes to cabin altitude indication on EICAS display.


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VERSION 20.5

The EICAS 20.5 features implemented in the software are describedbelow:

Air conditioning system− "BLEED 1(2) VLV CLSD" message logic improved in order to avoid

spurious alarms.

Fuel System− "FUEL VENT OPEN" and "FUEL XFER INOP" messages logic

improved in order to avoid spurious alarms (only applicable toEMB-145 XR model).

Powerplant System− "ENG1(2) REV DISAGREE" message logic improved in order to

avoid spurious alarms.

Pressurization System− "HI ALT LDG-T/O" message changed from caution to advisory

(only applicable to airplanes properly equipped for HighAltitude Operation).

Navigation System− The Radio Altimeter indication was modified in order to reduce the

discrepancy between the current altitude of the aircraft and the PFDRadio Altitude indication.

Autopilot System− Pitch Wheel Command Integrator - Correction to avoid poor

Autopilot response when using the Pitch Wheel while coupled to thecopilot’s Flight Director, which may cause the Autopilot logic toreset an integrator, resulting in sluggish Autopilot response.

− Pitch Axes - Correction to avoid Autopilot nuisance disconnectiondue to the Pitch Primary Monitor during the Coupled Autopilot Go-Around test (only applicable to EMB-145 XR model).

General Changes− New AZ-950 MADC Maintenance Page on PFD.

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VERSION 20.7

The EICAS 20.7 features implemented in the software are describedbelow:

Autopilot:− Autopilot disengagement without aural warning Correction: It was

verified that under certain circumstances the autopilot candisengage without aural warning. It occurs when autopilot isengaged and TCS button pressed. If any pitch trim switch iscommanded while the TCS is being released the autopilotdisengages with no aural warning. The same situation can occurswhen deploying/retracting speed brake simultaneously to TCSreleasing, due to the automatic pitch trim command during speedbrake actuation.

− Symbol Generator Reversion Correction: It was verified anabnormal behavior in the Automatic Flight Control System when aSymbol Generator reversion occurs on the pilot side. In this casethe Autopilot reverts to basic mode and automatically couples to theco-pilot Flight Director as expected. If a vertical mode is selected toeither climbing or descending following the Symbol Generatorreversion, the Autopilot will not hold the pre-selected altitudealthough the Flight Director bars indicate level off and the PFDshows the correct mode transition from the selected vertical modeto ASEL mode and from ASEL mode to ALT HOLD mode.

− CAT II operation at Providence Airport: Automatic Flight ControlSystem changes were required in order to allow CAT II operation atProvidence Airport, which has a RA Minimums of 80 ft. The currentRA Minimums interval does not include 80 ft. Therefore, the 80 ftRA Minimums was included in the CAT II logic to allow properoperation in this airport.

− Roll Oscillation Solution at high altitudes: Yaw Damper control lawwas modified in order to minimize the roll oscillation observed athigh altitudes when autopilot is engaged. This modification isenabled only in the 135 family airplane (EMB-135ER, EMB-135LRand EMB-135BJ) via IM-600 new parameter called RUDDER BIAS.


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HGS:

− HGS compatibility issue: version 20.7 (Phase 10.7) shall correct thecompatibility issue between EICAS Version 20.5 (Phase 10.5) andHGS equipped airplane. Therefore the RA value shall be displayedagain on the HGS combiner. There will be no modifications on theHGS system.

Ice Protection:

− “ICE COND – A/ICE INOP” message logic change: in the currentlogic, under ice condition on the ground, this message mayundesirably appear because the Anti-Ice protection cannot beactivated. The reason for this modification is to inhibit this messageonly on the ground, when the airplane speed is below 25 kt.

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SERVICE BULLETIN TABLE

SB SUBJECT

SB 145-34-0049 Changes the Integrated Standby Instrument System (ISIS) into new P/N C16221GC03 - Amendment A.

SB 145-34-0089 Incorporates modifications related to Mode S Elementary Surveillance Transponders.

SB 145-34-0096 Incorporates modifications related to Mode S Enhanced Surveillance Transponders.

SB 145-34-0106 Reconfiguration of the TCAS Performance Limit.

SB 145-36-0028 Changes EBV S/O Valve by a Pressure Regulator Valve.

SB 145-49-0010 Improves the Airborne Auxiliary Power (APU).

SB 145-49-0012 Changes Auxiliary Power Unit (APU) Electronic Sequence Unit (ESU) feeder bus.

SB 145-49-0014 Replaces the APU Air Inlet Frame.

SB 145-52-0040 Lock Pin Installation.

SB 145-53-0064 Increases the MZFW of the EMB-145ER and EP Models.

SB 145-53-0065 Reduces MTOW of the EMB-145LR Model.

SB 145-53-0066 Updates MTOW of the EMB-145LR Model.

SB 145-53-0068 Increases the maximum gross weights of the EMB-145LR Model.

SB 145-71-0003 Implements the Protection Guard for the Engine Start Switches.

SB 145-73-0010 Incorporates FADEC B5.1.1 Version on AE3007A and A1/1 Engines.

SB 145-73-0011 Incorporates FADEC B5.1.1 Version on AE3007A1 Engines.

SB 145-73-0012 Incorporates FADEC B5.1.1 Version on AE3007A1P Engines.

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SB SUBJECT

SB 145-73-0013 Incorporates FADEC B5.1.1 Version on AE3007A1/3 Engines.


SB 145-73-0021 Incorporates FADEC B7.6 Version on AE3007A and A1/1 Engines.

SB 145-73-0022 Incorporates FADEC B7.6 Version on AE3007A1 Engines.

SB 145-73-0023 Incorporates FADEC B7.6 Version on AE3007A1P Engines.

SB 145-73-0024 Incorporates FADEC B7.6 Version on AE3007A1/3 Engines.


SB 145-73-0026 Incorporates FADEC B7.6 Version on AE3007A1E Engines.






SB 145-77-0002 Includes Placard for 95 psi Oil Pressure Limit. SB 145-77-0003 Includes Placard for 115 psi Oil Pressure Limit. SB T-62T-49-152 Incorporates Modification to Permit APU Start

Above 25000 ft.

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SB SUBJECT

SB 145-34-0049 Changes the Integrated Standby Instrument System (ISIS) into new P/N C16221GC03 - Amendment A.

SB 145-34-0089 Incorporates modifications related to Mode S Elementary Surveillance Transponders.

SB 145-34-0096 Incorporates modifications related to Mode S Enhanced Surveillance Transponders.

SB 145-36-0028 Changes EBV S/O Valve by a Pressure Regulator Valve.

SB 145-49-0010 Improves the Airborne Auxiliary Power (APU).

SB 145-49-0012 Changes Auxiliary Power Unit (APU) Electronic Sequence Unit (ESU) feeder bus.

SB 145-49-0014 Replaces the APU Air Inlet Frame.

SB 145-52-0040 Lock Pin Installation.

SB 145-53-0064 Increases the MZFW of the EMB-145ER and EP Models.

SB 145-53-0065 Reduces MTOW of the EMB-145LR Model.

SB 145-53-0066 Updates MTOW of the EMB-145LR Model.

SB 145-53-0068 Increases the maximum gross weights of the EMB-145LR Model.

SB 145-71-0003 Implements the Protection Guard for the Engine Start Switches.

SB 145-73-0010 Incorporates FADEC B5.1.1 Version on AE3007A and A1/1 Engines.


SB 145-73-0012 Incorporates FADEC B5.1.1 Version on AE3007A1P Engines.

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SB SUBJECT

SB 145-73-0013 Incorporates FADEC B5.1.1 Version on AE3007A1/3 Engines.


SB 145-73-0021 Incorporates FADEC B7.6 Version on AE3007A and A1/1 Engines.











SB 145-77-0002 Includes Placard for 95 psi Oil Pressure Limit. SB 145-77-0003 Includes Placard for 115 psi Oil Pressure Limit. SB T-62T-49-152 Incorporates Modification to Permit APU Start

Above 25000 ft.

AOM-145-1114-71-SEC-1-00

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