book 1 short emb 190

170/190MAINTENANCE TRAINING MANUAL

This document is to be used for training purposes only.

Under no circumstances it supercedes or replaces any official information published by the manufacturer.

The information contained herein is proprietary to GE Commercial Finance Aviation Training (GECAT)

and is disclosed in confidence. It is the property of GECAT, and shall not be reproduced or disclosed in whole or in part, or used for any purpose whatsoever

without the express written consent of GECAT.

XLMTTextfeldIssue: Jan07

Issue: Feb02Revision: 00 Page 2

FOR TRAINING ONLYGE Capital Aviation Training. Reproduction Prohibited Chapter 27-00

XLMTTextfeldIssue: Jan07

XLMTRechteck

190

Abbreviatio d parts locationsns an

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Page 1Chapter 0-00

AABABACACACACACACADADADADADADAEAEAFAFAGAGAGAHAICA/IA/IAIPAIOALALALAM

ry Material Joint Matrix Liquid Crystal Display Maintenance Manualagement System

ace Force-Navy

f Attackssure Moduletic Power Reserve y power unitutical Radio Incorporatedace Recommended Practiceace Standardtart Contactors Standard Communication Busrge Valverottle

nsport Associationffic Controltic Test Equipment

bine Startertic Takeoff Thrust Control Systemnt

Take-off Altitudeyy Generatorarning Computer

tric Settingue: June06ision: 00

FOR TRAINING ONLY Reproduction Prohibited

C Av. Bus ControlS Absolute Value

Alternating CurrentC Aft Core Cowl/ Active Clearance ControlE Actuator Control ElectronicsMP AC Motor Pump controlOC Air Cooled Oil CoolerARS Airborne Communication Adressing & Recording SystemA Air Data Application ModuleC Air Data ComputerF Automatic Direction FinderG Air Driven GeneratorS Air Data SystemSP Air Data Smart ProbeO All Engines OperatingTC AC Essential Transfer ContactorCS Automatic Flight Control SystemM Airplane Flight ManualB Accessory GearboxCU Auxiliary Generator Control UnitT Agent

Amp HourC Auxiliary Integrated Control Centre

Anti-IceApproach IdleAutonomous Input Processor

P Actuated Input Output ProcessorC Auxiliary Generator Line ContactorF Aft Looking ForwardT AltitudeS Air Management System

AMJ AdvisoAMLCD Active AMM AircraftAMS Air ManAN AerospA/O Air/ OilAOA Angle oAPM Air PreAPR AutomaAPU AuxiliarARINC AeronaARP AerospAS AerospASC APU SASCB AvionicASV Anti-SuA/T Auto ThATA Air TraATC Air TraATE AutomaATS Air TurATTCS AutomaATTD AttendaATOA Above AUX AuxiliarAUX GEN AuxiliarAWC Aural W

BB BallBARO Barome

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BBBBBBBBBBBBBBBBBBBB

CCCCCCCCCCC

hannel Datalinktimeter per hourontrol Panel ontrol Position Semsorsmmunications Systemontrol Transducer

clockwisesor Discharge Pressureisplay Unit

cial Faniber Compositer Furnished Equipmentederal Regulations (USA)

re Suppression Panelf Gravity

atingatingaintenance Computer

ications Management Functionnt Maintenance Manual

ications Continuous ratingtionr Program Configuration Item essure Control Systemrocessing Unitdundancy Check Resisting Steel

ion Review ItemRay Tubesue: June06evision: 00


ARO-ALT Barometric AltitudeATT BatteryC Battery ContactorCD Binary Coded DecimalCM Brake Control ModuleCS Brake Control SystemCV Brake Control ValveFE Buyer Furnished EquipmentIC Backplane Interface ControllerIC Bus Interface ControllerIT Built-In TestITE Built-in Test EquipmentLWR BlowerNR Binary Numeric RepresentationPT Break Power TransferRG BearingRK BrakeTC Bus Tie ContactorTL BottleTMS Brake Temperature Monitoring System

Centigrade/ CelsiusAN Control Area NetworkAS Crew Alerting SystemAWS Central Aural Warning SystemB Circuit BreakerBM Circuit Breaker ModuleBP Circuit Breaker PanelCA Control Card AssemblyCD Cursor Control DeviceCD Compliance Check Database

CCDL Chross Ccc/h cubic cenCCP Cockpit CCCPS Cockpit CCCS Cabin CoCCT Cockpit CCCW Counter CDP CompresCDU Control DCF CommerCFC Carbon FCFE CustomeCFR Code of FCFSP Cargo FiCG Centre oCH Channel CLB ClimbCLB-1 Climb 1 rCLB-2 Climb 2 rCMC Central MCMF CommunCMM ComponeCOM CommunCON MaximumCONFIG ConfiguraCPCI ComputeCPCS Cabin PrCPU Central PCRC Cyclic ReCRES CorrosionCRG CargoCRI CertificatCRT Cathode

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CRCSCTCTCTCTCVCVCW

DDaDADAdBDBDCDCDCDCDDDEDEDFD/DIDID/DMDMDM

etering Unitader Management Unitenttial Currentias Sensor

ole Double Throwsponder Heritageesponders (revision L) UnitVoice and Data Recorderck

1 2nic Bay Built Unit / Engine Built-upial Contactormental Control Systemnic Control Unit Configuration Plug Driven Pump nic Display Systems-explosive Device nically Erasable Programmable Read Only Memoryed Ground Proximity Warning Systemt Gas Temperature Hydraulic Cowl Lock Hydraulic Servo Valve Indicating and Crew Alerting Systemial (Emergency) Integrated Control Centreue: June06ision: 00


Z Cruise ratingD Constant Speed Drive

Current TransformerA Current Transformer AssemblyA Centro Tecnico Aerospacial R CentreFC Cargo Vent Fan ContactorR Cockpit Voice Recorder

Clockwise

Double amplitudeDC Digital Air Data ComputerU Data Acquisition Unit

decibelDatabaseDirect Current, electrical

U Direction Control UnitPC DC Power CentreTC DC Tie ContactorG Dispatch Deviation GuideOS Digital Engine Operating SystemT DetectorDAU Digital Flight Data Acquisition Unit

I Descent IdleSAG DisagreeSC DisconnectedLNA Diplexer/Low Noise AmplifierC Direct Maintenance CostE Distance Measuring EquipmentM Data Memory Module

DMU Drier/MDMU Data loDOC DocumDP DifferenDP3(190) Bleed BDPDT Dole PDRH Dual reDRL Dual RDU DisplayDVDR Digital DWLK Downlo

EE1 EngineE2 EngineEBAY ElectroEBU EngineEC EssentECS EnvironECU ElectroECP EngineEDP EngineEDS ElectroEED ElectroEEPROM ElectroEGPWS EnhancEGT ExhausEHCL ElectroEHSV ElectroEICAS EngineEICC Essent

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EEEEEEEEEEEEEEEEEEEEEEEE

FFFFFFF

irentrol Modulentrol System (primary and secondary)ditioning Unitntrol Unittrol Valve led Oil Coolerta RecorderFlight Attendant Panelural Hazard Assessment

irst Outguisher

ake-off nagement Computernagement Systemering Unitering Valve

bject Damagerhead PanelOuter Sealgrammable Gate Arrayntity Gauging Systemntity Processor Station

e Deflectione Output

e Analysissfer Protocolsue: June06evision: 00


ICD Essential Integrated Control DocumentLEB Embraer Liebherr Equipamentos do BrasilMB Empresa Brasileira de AeronauticaMC Electromagnetic CompabilityMER EmergencyMI Electro-Magnetic InterferenceNG EnginePAC External Power AC ContactorPBS Emergency Parking Brake SystemPBV Emergency Parking Brake ValvePDC External Power DC ContactorPGDS Electrical Power Generating and Distribution SystemPLD Erasable Programmable Logic DevicePM External Power ModePROM Erasable Programmable Read Only MemoryRJ Embraer Regional JetSC Electronic Starter ControlSS Essential (Power bus)TC Essential Transfer ContactorTC Engine Thrust CompensationTTS Electronic Thrust Trim systemVM Engine Vibration MonitorVCS Engine Vibration Control SystemXT PWR External Power

FahrenheitAA Federal Aviation AdministrationADEC Full Authority Digital Engine Control (Electronic Controller)AN FanAP Flight Attendant PanelAR Federal Aviation Regulations (U.S.A.)

FBW Fly By WFCM Flight CoFCS Flight CoFCU Fuel ConFCU Flush CoFCV Flow ConFCOC Fuel CooFDR Flight DaFFAP Forward FH Flight HoFHA FunctionF/I Flight IdleFIFO First In FFIREX Fire ExtinFLT FlightFLEX Flexible tFMC Flight MaFMS Flight MaFMU Fuel MetFMV Fuel MetF/O Fuel/OilFOD Foreign OFOP Fuel OveFOS Forward FPGA Field ProFQGS Fuel QuaFQP Fuel QuaFS FuselageFSD Full ScalFSO Full Scalft FeetFTA Fault TreFTP File Tran

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FWFW

GGAGAGCGCGCGEGEGEG/GLGMGMGNGPGPGPGPGSGSGSGS

HHDHEHF

tensity Radiated Fieldspen Rodowerressureassower Amplifierlic Pump Contactorressure Compressorressure Regulation Valveressure Shut-Off Valveressure Turbineressure Turbine Clearance Control Valveower Extraction

ate Dischargetal Situation Indicatorlic Synoptic Page

ermal Stabilityre

xchanger licCycles per second)

ted Avionics Computerd Air Speed

ted Control Circuite Control Documentn Control Unitation Keyue: June06ision: 00


D ForwardSOV Fire-wall Shut-off Valve

Go-around rating RSV Go-around reserveR Generator Control RelayS Generator Control SwitchU Generator Control Unit

General Electric Company/ GEAE General Electric Aircraft EnginesN Generator

I Ground IdleC Generator Line ContactorAP Ground Mapping O Ground Maintenance OverrideD Ground

Guidance/Display Control PanelM US Gallons per MinuteS Global Positioning SystemU Ground Power Unit

GlideslopeGround Spoilers

E Ground Support EquipmentTC Ground Service Transfer Contactor

LC High Definition Data Link ControlPA High Efficiency Particulate

High Frequency

HIRF High InHOR Hold OHP HorsepHP High PHP High PHPA High PHPC HydrauHPC (190) High PHPRSOV High PHPSOV High PHPT High PHPTCC (190) High PHPX HorsepHr HourHRD High RHSI HorizonHSP HydrauHTR HeaterHTS High ThHW HardwaHX/ Hex Heat EHYD HydrauHz Hertz (

IIAC IntegraIAS IndicateICC IntegraICD InterfacICU IsolatioID Identific

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IDIEIFIFIGIGIGILIMIMINIninI/IOI/IPIPIPIRISISIT

JJAJAJT

KK

zrs

alal deltaal gage per hour

Amp

a Network

nder hourer minuteer secondorceystal Display(Gear)Gear Electronic Control UnitGear System Engine

Idlerated Control Centreed Partvel Sensort Valvenagement System

ressuresue: June06evision: 00


G Integrated Drive GeneratorVM Integrated Engine Vibration MonitorS Inner Fixed Structure (Forward Core Cowl)SD Inflight ShutdownA Intermediate Gain AntennaB (190) Inlet GearboxV Inlet Guide VaneS Instrument Landing System

Inner MarkerP ImpendingBD Inboardco InconelHG Inches of Mercury O Input/Output M Input/Output Module

P InputSA Integrated Pitot Static Angle of Attack ProbeT Inadvertent Parallel TripV (190) Inlet Pressurizing ValveS Inertial Reference System A International Standard AtmosphereO International Standards Organization T Inter-Turbine Temperature

A Joint Aviation AuthoritiesR Joint Aviation Regulations (Europe)SO JAA Technical Standard Order

G Kilogram

kHz Kilo Hertkm Kilometekohm kilo-ohmKPa Kilo-PascKPad Kilo-PascKPag Kilo-Pasckph kilogramsKVA Kilo Volt kW Kilowatt

LL LiterLAN Local AreLAV LavatoryLB/ Lbs Poulbs/hr pounds pLbs/Min pounds pLbs/sec pounds plbf Pounds-fLCD Liquid CrLDG Landing LG ECU Landing LGS Landing LHE Left HandL/I LamdingLICC Left IntegLLP Life LimitLLS Liquid LeLLV Low LimiLMS Load MaLOC LocalizerLOP Low Oil P

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LOLPLPLRLRLRLSLSLV

MmmAMAMamBMCMCMCMCMEMEMFMFMFMFMhMIMiMIMK

anding Geartic Level Indicatorsm Landing WeightMarkerr Warning Functionterumber

rl and Processes Directivesl Power Reservetic Pickup Unitr Radio Cabinet Specificationondondtarting Relay

t

n Speedplicablel Advisory Committee for Aeronautics Anti Ice Pressure Regulating and Shut off Valvel Aerospace Standard

ndPower Transfereted DatadAcceleration Rateue: June06ision: 00


TC Loss of Thrust ControlLow Pressure

T Low Pressure TurbineD (190) Low Rate Discharge M Line Replaceable ModuleU Line Replaceable Unit B Low Significant BitS Lightning Sensor SystemDT Linear Variable Differential Transducer

Metermilli-amperes

U Modular Avionics Unitx Maximum

milli BarDU Multi-Function Control Display Unit OEI Max Continuous One Engine InoperativeU Modular Concept UnitU Motor Controller UnitL Minimum Equipment ListS Main Engine Start

Multi-FunctionD Multi-Function DisplayP Multi-Function ProbeS Multi-Function Spoilerz MegahertzC Microphonels Measuring unit. equivalent to 1/1000 inchN MinutesR BCN Marker Beacon

MLG Main LMLI MagneMLW MaximuMM Middle MMF Monitomm MillimeMn Mach NMON MonitoMPD MateriaMPR ManuaMPU MagneMRC ModulaMS Militaryms millisecmsec millisecMSR Motor SmV Millivol

NN RotatioN/A Not ApNACA NationaNAI NacelleNAPRSOV NacelleNAS NationaNAV NavigationNB Narrow BaNBPT No Break NC No ChangNCD No CompuNDOT Core Spee

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NNNNNNNNNNNN

OOOOOOOOOOOOOOOO

PP

Pressuretuator Control Electronic

er Adress & Cabin Interphone Systemmable Array Logicvated Self Testerton Annunciatedton ActuatorBuilt In Testrake Valve Applied

Ontrol Actuator compressor dischargeontrol Unitr Dispenser& Collector State machine

lombs per unit accelerationDevice Driverrive Unit Double Throwlight Displayr Take Off

yted Built In Test ver Angle (TLA)

mable Logic Deviceng Modulent Magnet Alternatornt Magnet Generator

nt Magnet StarterberPressureegulationsue: June06evision: 00


IC Network Interface Controller/ ComputerIM Network Interface ModuleLG Nose Landing Gearo. NumberTO Normal TakeoffVM Non Volatile Memory/W Nose WheelWS Nose Wheel SteeringWSCM Nose Wheel Steering Control Module1 Engine Low Pressure Rotor Speed/ Physical Fan Speed2 Engine High Pressure Rotor Speed/ Physical Core Speed2S Corrected High Pressure Rotor Speed

AT Outside Air TemperatureBV Operational (Operability) Bleed ValveC OvercurrentD Outside DiameterDS Overheat Detection SystemEI One Engine InoperativeF OverfrequencyFV Outflow ValveGV Outlet Guide VaneM Outer Marker/P OutputTC Outer Torque CouplingUTBD OutboardV OvervoltageVHT Overheat

Pressure Port

P0 Ambient P-ACE Power AcPACIC PassengPAL ProgramPAST Pilot ActiPAX PassengPBA Push ButPBA Push ButP-BIT Periodic PBVA Parking BPCA Power CPcd PressurePCU Power CPDCSM ParametepC/g pico CouPDD Periodic PDU Power D1PDT One PolePFD Primary FPFTO Power FoPGE Page KePI-BIT Pilot InitiaPLA Power LePLD ProgramPM ProcessiPMA PermanePMG PermanePMP PumpPMS PermaneP/N Part numPO Ambient POR Point of RPOS Position

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POppPRPRPRPRPSPsPSPSPSPSpsPSPSPtPTPTPTPUPUPWPW

RRRARARCRBRD

Defuel Panel REFReferenceDrive Shafter / Reverse Thrustevolutionrequency

enerator Control Unitand Enginee Idletegrated Control Centre

ne Contactoresistanceanagement Unit

Resistancenly Memory

tion Per Minuteystem Bus

um Square Resistanceeechnical Commission for Aeronautics

ve Thermal Device to Loadd Take OffVariable Differential Transformerd Vertical Separationrd

id1, 2ary Actuator Control Electronics

Annular Combusterue: June06ision: 00


ST Power-on Self Testh pounds per hour

Power readyOC ProcessorOT ProtectionSOV Pressure Regulating and Shutt off Valve

Phase SequenceStatic Pressure

3 Compressor Discharge PressureEM Proximity Sensor Evaluation ModuleM Power Supply ModuleIA Pounds per square inch, absoluteid Pounds per Spuare inch (psi)IG Pounds per square inch, gaugeS Proximity Sensing System

Total PressureFE PolytetrafluoroethyleneO Power Takeoff AssemblyU Power Transfer Unit

Per Unit-BIT Power-up Built In TestM Pulse-Width ModulatedR Power

Return Port/ RollerM Random Access MemoryT Ram Air TurbineB Radio Control BusHA Regulamentos Brasileiros de Homologao Aeronutica I Refuel Defuel Indicator

RDP Refuel RDS Radial REV Revers1/ REV 1 per RRF Radio FRGCU RAT GRHE Right HR/I ReversRICC Right InRLC RAT LiRload Load RRMU Radio MRout OutputROM Read ORPM RevoluRSB Radio SRSS Root SRsource SourceRSV ReservRTCA Radio TRTD ResistiRTL Ready RTO RejecteRVDT Rotary RVSM ReduceRWD Rearwa

SS1, S2 SolenoS-ACE SecondSAC Single

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SSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSS

urce Error Correctionus Matrixte Power Controller

Contactor Dayyest Specification

lve Switch

ole Aole Bning Protection SystemSYNCSynchronousousACThrust Asymmetry Compensation

peratureymmetry Compensationir Navigation

TemperatureTemperaturelculated/Confirmedfinedt Bleed Valveoupleert and Collision Avoidance Systemture Compensated Pressure Switchontrol Quadrantntrol Stearingsue: June06evision: 00


AE Society of Automotive EngineersATCOM Satellite CommunicationsAV (190) Starter Air ValveCL Software Critical LevelCU Signal Control UnitCV Starter Control ValveD Set DelayD System DescriptionDI Source Destination IdentifierDD System Definition DrawingDFS Smoke Detection and Fire Suppression DN System Description NoteDU Satellite Data Unitec SecondERV ServiceFA Synchronized Feedback ActuatorFC Specific Fuel ConsumptionHP Shaft HorsepowerLA Synchronized Locking ActuatorsLS Sea Level StaticM Status MatrixMK SmokeOV Shut Off ValveOV Solenoid Operated ValvePDA Secondary Power Distribution AssemblyPDT Single Pole Double ThrowPKR SpeakerQ SquelchRAM Static Random Access MemoryRD System Requirements DocumentRM Structural Repair ManualRS System Requirement SpecificationsSA System Safety Assessment

SSEC Static SoSSM Sign StatSSPC Solid StaSTBY Stand-bySTBYC Stand-bySTD StandardSTO Store KeSTS System TSVC ServiceSVS Servo VaSW SwitchSW SoftwareSWA Switch, PSWB Switch, PSWPS Stall WarSYNC SynchronSYS SystemT

TT2 Inlet TemTAC Thrust AsTACAN Tactical ATAMB Static AirTAT Total Air TBC To Be CaTBD To be deTBV (190) TransienTC ThermocTCAS Traffic AlTCPS TemperaTCQ Thrust CTCS Touch Co

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TDTDTGTiTLTLTMTOTOTOTOTOT/RT2T3T2T2T4TQT/RTRTRTRTRTRTRTSTSTSTV

requencyllonal Time Coordinationoltage

imum speed in the takeofflternating CurrentBackplane Peripheral Componente Bleed Valveirect Currentata Radiole Differential Transducere Geometrye Guide Vanee Geometry Actuator Position Feedbackigh FrequencynS Datalinkl Navigation

igh Frequency Omnidirectional Radio Referenceoot Mean Squaree Speed Constant Frequencye Speed Constant Frequencye Stator Vaneue: June06ision: 00


C Top Dead CentreS Takeoff Data SetB(190) Transfer Gearbox

TitaniumA Throttle Lever Angle / Thrust Lever AngleD Time Limited DispatchS Thrust Lever Angle

Take-off-1 Takeoff Mode 1-2 Takeoff Mode 2-3 Takeoff Mode 3/GA Take Off and Go Around

Thrust ReverserFan Total Inlet TemperatureCompressor Discharge Temperature

2 Compressor Inlet Temperature5 (190) Compressor Inlet Temperature5 Inter-Turbine TemperatureA Throttle Quadrant Assembly

Thrust ReverserAS Thrust Reverser Actuation SystemF (190) Turbine Rear FrameS Thrust Rating SelectorU Transformer Rectifier UnitUEC Transformer Rectifier Unit Essential ContactorX Thrust Reverser Position

Technical SpecificationO Technical Standard OrderT Test KeyP True Vapor Pressure

UUF UnderfUS G US GaUTC UniversUV Underv

VV VoltsV1 the minVAC Volts AVBPCI Virtual VBV (190) VariablVDC Volts DVDR VHF DVDT VarialbVG VariablVGV VariablVGX VariablVHF Very HVibe VibratioVIDL VOR/ILVNAV VerticaVOL VolumeVOR Very HVREF VoltageVRMS Volts RVSCF VariablVSCV VariablVSV Variabl

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WWWWWWWWWWWWWWW

XXXXX

YY

ZZ

CelsiusFahrenheitr thananinus

ialsue: June06evision: 00


AI Wing Anti-IceF Fuel FlowF/P3 Ratio Units: ratio of fuel flow to PS3FX HMU Metering Valve Position FeedbackKA Walter Kidde Aerospace OFW Weight Off WheelsOW Weight On WheelsOWA Weight On Wheels PSEM1OWB Weight On Wheels PSEM2RN WarningS Wheel SpinSD Wheel Spin DiscreteWSC Water Waste System ControllerX Weather

DCR TransducerFER TransferFEED Cross feedPDR Transponder

D Yaw Damper

ID Zone Isolation Device

DegreesC Degrees F Degrees > is greate< is less th+/- plus or m

Ohm

Different

% Percent

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ankue: June06ision: 00


Intentionally Left Bl

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F

S

PFD

FDsue: June06evision: 00


igure 1: Cockpit Instruments Location

Audio panel

MCDU

EICA

GP

M

CCD

Provision forfuture MCDU

190

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Fig

ICE-DETECTOR

SPDA 1

PA

LSS

TAT

SMART-PROBE 2

IRU 2

P-ACE 2

DVDR

WSWIPER ue: June06ision: 00


ure 2 : Fwd E-Bay Equipment

Forward E-Bay

BATT 1

ICE-DETECTOR

ALTITUDE SENSOR

MRC 1

P-ACE 1

IRU 1

TCAS

SMART-PROBE 1

TAT

L WS WIPER R

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Page 16Chapter 0-00

F

INVERTER

MAU 1

C

LHsue: June06evision: 00


igure 3: Fwd E-Bay back

Forward E-Bay

MAU 2

GCU (RAT) PRESSURE

CONTROLLER

SMART-PROBE

DIMMER

EIC

RH

190

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Page 17Chapter 0-00

Fig

SF-ACE

MS

CC ue: June06ision: 00


ure 4 : Center E-Bay

Center E-BAY

SPDA 2

LIRICC

FIREX BOTTLES

FCU

MAU 3

SF-ACE MRC 2

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Page 18Chapter 0-00

F

ANT UPLER

P-ACE 3

APU-FADEC sue: June06evision: 00


igure 5 : Aft E-Bay

ELT LIGHT

HF

SATCOM

VHF

VOR 3

DVDR

HS ACE

WATER CTL

AICC

BATT 2

HF CO

DVDR

AFT E-BAY

ELT- NAV

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190

ATA 0 umentation0 Doc

190

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Table of Content

00-00 DocumentationIntroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1AMM PART I - SYSTEM DESCRIPTION SYSTEM (SDS) . . . . . . . 3AMM PART II - MAINTENANCE PRACTICES AND PROCEDURES (MPP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5MAINTENANCE PRACTICES AND PROCEDURES (MPP),Aircraft Maintenance Task Oriented Support System (AMTOSS),Function Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7AIRCRAFT MAINTENANCE MANUAL. . . . . . . . . . . . . . . . . . . . . . 9FAULT ISOLATION MANUAL (FIM) . . . . . . . . . . . . . . . . . . . . . . . 11RAMP MAINTENANCE MANUAL (RMM),COMPONENT MAINTENANCE MANUAL (CMM) . . . . . . . . . . . . 13WIRING MANUAL (WM),SYSTEM SCHEMATIC MANUAL (SSM) . . . . . . . . . . . . . . . . . . . . 15AIRCRAFT ILLUSTRATED PARTS CATALOGUE (AIPC) . . . . . . 17OTHER DOCUMENTATION,AIRCRAFT RECOVERY MANUAL (ARM),AIRPORT PLANNING MANUAL (APM),CONSUMABLE PRODUCTS CATALOGUE (CPC),CORROSION PREVENTION MANUAL (CPM),ILLUSTRATED TOOL AND EQUIPMENT MANUAL (ITEM),INSTRUCTIONS FOR GROUND FIRE

EXTINGUISHING AND RESCUE MANUAL (IGFER). . . . . . . . . . 19MAINTENANCE FACILITY AND EQUIPMENT PLANNING (MFEP),NONDESTRUCTIVE TESTING MANUAL (NDT),SERVICE BULLETIN (SB),INFORMATION BULLETIN (IB) . . . . . . . . . . . . . . . . . . . . . . . . . . .21STRUCTURAL REPAIR MANUAL (SRM),Available links: MPP, NDT, CPM, SM, ITEM, CPC.,STANDARD WIRING PRACTICES MANUAL (SWPM),TASK CARD SYSTEM (TCS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

190

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Issue: JunRevision: Page 1Chapter 0-00

0-00

Introdu

All mainshootingrelated d190

e0600


Documentation

ction

tenance checks, inspections, repairs, replacements and trouble- must be performed in accordance with valid documentation. Theocumentation necessary to maintain the aircraft includes:

: June06ion: 00 Page 2

FOR TRAINING ONLYReproduction Prohibited Chapter 0-00

TECHNICAL PUBLICATION

TECHNICAL PUBLICATION

REVISION

REVISION

CUSTOMIZATION

CUSTOMIZATION

AIPC Aircraft Illustrated Parts Catalog Monthly AlwaysAMM Aircraft Maintenance Manual Quarterly AlwaysARM Aircraft Recovery Manual Semiannually On requestAPM Aircraft Planning Manual Semiannually On requestCMM Component Maintenance Manual Semiannually Not ApplicableCPC Consumable Products Catalog Semiannually Not ApplicableCPM Corrosion Prevention Manual Annually AlwaysFIM Fault Isolation Manual Quarterly AlwaysITEM Illustrated Tool and Equipment Manual Quarterly On request

IGFER Instruction for Ground Fire Extinguishingand Rescue

Semiannually On request

MFEP Maintenance Facility&Equipment Planning Semiannually On request

MPD Maintenance Planning Document Annually On request

NDT Nondestructive Testing Manual Annually AlwaysPIL Parts Information Letter As required Not ApplicablePPBM Power Plant Buildup Manual Quarterly Not ApplicableRMM Ramp Maintenance Manual QuarterlySB / IB Service / Information Bulletin As required Not Applicable

Always

SNL Service News Letter (SNL) As required Not ApplicableSWPM Standard Wiring Practices Manual Semiannually On requestSM Standards Manual Semiannually Not ApplicableSRM Structural Repair Manual Quarterly AlwaysSSM System Schematic Manual Semiannually AlwaysTCS Task Card System - AlwaysWM Wiring Manual Quarterly Always

e 1: DocumentationIssueRevis

Figur


AMM P

SeSe190

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ART I - SYSTEM DESCRIPTION SYSTEM (SDS)

Purpose:

- Detailed description and explanation of the location, configuration,function, operation and control of the complete system (chapter),and its subsystems.

- Enable the operator / mechanic / trainee to understand the threelevels of overall construction, operation and function to the extentnecessary to perform adequate maintenance and fault isolation ofthe system.

Available links: FIM, AIPC, ITEM, MPP, SM, SSM, WM.

Arrangement:

INTRODUCTION

GENERAL DESCRIPTION

COMPONENTS

OPERATION

TRAINING INFORMATION POINTS

SDSctions

INTRODUCTION

GENERAL DESCRIPTION

COMPONENTS

OPERATION

TRAINING INFORMATION POINTS

SDSctions



E

M

1

7

0

S

D

S

2

4

0

0

4

3

.

D

G

N

RICC

LICC

IDG 2

IDG 1

RAT

RAT GCU

EICC

STATICINVERTER

APU GEN

AC GENERATION - BLOCK DIAGRAM

AIRCRAFTMAINTENANCE MANUAL

EFFECTIVITY: ALL 24-20-00 Page 7Dec 08/03

AMM Part 1 - System Description Section (SDS) Example:

ComponentsGENERATOR DRIVE SYSTEM (24-21)The generator drive system is the usual source of aircraft electricalAC (Alternating Current) power in flight and on the ground during taxiand takeoff procedures.APU AC GENERATION (24-22)The APU (Auxiliary Power Unit) generation system is used primarilywhen the aircraft is on the ground for aircraft maintenance or flightpreparation. This system can also be used to let the aircraft bedispatched with an altitude restriction or as a backup source ofelectric power in flight.EMERGENCY AC POWER GENERATION (24-23)The EPGDS (Electrical-Power Generation-and-Distribution System)is capable of generating electrical power in an emergency condition.This ensures that the essential loads will be supplied with power foran unlimited time if the main AC (Alternating Current) generators arelost.STATIC INVERTER (24-24)The Static Inverter converts aircraft 28 VDC (Volt Direct Current) tosingle phase 115 VAC.The figure AC GENERATION - BLOCK DIAGRAM provides furtherdata on the preceding text.

e 2: AMM Part 1 - SDS ExampleIssueRevis

Figur


AMM PPROCE

COMPONE

LOCATIO

(100)

COMPONE

LOCATIO

(100)190

e0600


ART II - MAINTENANCE PRACTICES AND DURES (MPP)

Purpose:

- Contains all necessary maintenance practice and procedure datato enable the mechanic to maintain the aircraft properly, at the levelof line, hangar / service centre maintenance actions, or line ramplevel.

Available links:

- WM, AIPC, CMM, SWPM, CPM, FIM, MPP, SDS, SM, SRM,SSM, ITEM.

Arrangement:

PAGEBLOCKS

NT

N

MAINTENANCE

PRACTICESSERVICING

REMOVAL

INSTALLATION

ADJUSTMENT

TEST

INSPECTION

CHECK

CLEANING

PAINTINGREPAIRS

(200) (300) (400) (700) (800)(500) (600)

PAGEBLOCKS

NT

N

MAINTENANCE

PRACTICESSERVICING

REMOVAL

INSTALLATION

ADJUSTMENT

TEST

INSPECTION

CHECK

CLEANING

PAINTINGREPAIRS

(200) (300) (400) (700) (800)(500) (600)



INTEGRATED DRIVE GENERATOR (IDG) - REMOVAL/INSTALLATION

1. General

A. This section gives the procedures to remove/install the IDGs.

B. The IDG 1 is installed on the left engine gearbox and the IDG 2 is installed on the right enginegearbox.

C. The procedures in this section are given in the sequence below.

TASK NUMBER DESCRIPTION EFFECTIVITY

24-21-01-000-801-A Integrated Drive Generator (IDG) -Removal

ALL

24-21-01-400-801-A Integrated Drive Generator (IDG) -Installation

ALL

D. The abbreviations and acronyms used in this section are given in the sequence below:

ABBREVIATION DESCRIPTION

AC Alternating Current

IDG Integrated Drive Generator

lb.in Pound Inch

MCDU Multifunction Control Display Unit

N.m Newton Meter

SSPC Solid State Power Controller

ZONES416426

A

A

BD

E4. O-RING

5. OIL-OUT FITTING 6. OIL-OUT

LINE

7. OIL-IN LINE

8. OIL-IN FITTING

9. O-RING12. HEXAGONAL SOCKET SCREW (2x)

13. WASHER (2x)

16. HEXAGONAL SOCKET SCREW (2x)

E

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1

7

0

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P

P

2

4

0

0

0

9

.

D

G

N

12

345

1

4

3

2

5

6

1. ELECTRICAL CONNECTOR (IDG J1)

2. ELECTRICAL CONNECTOR J1

15. ELECTRICAL CONNECTOR (IDG J2)

6

3. OIL-OUT PORT

11. TERMINAL BLOCK COVER 10. OIL-IN

PORT

TORQUE: 27.2 - 33.8 N.m (240 - 300 lb.in.)

TORQUE: 53.7 - 59.3 N.m (475 - 525 lb.in.)

TORQUE: 77.3 - 85.4 N.m (684 - 756 lb.in.)

TORQUE: 33.9 - 47.4 N.m (300 - 420 lb.in.)

TORQUE: 2.3 - 2.4 N.m (20 - 22 lb.in.)

TORQUE: 3.7 - 4.2 N.m (32 - 38 lb.in.)

17. HARNESS SUPPORT

14. ELECTRICAL CONNECTOR J2

Integrated Drive Generator (IDG) - Removal/InstallationFigure 401

Sheet 1

AIRCRAFTMAINTENANCE MANUAL

EFFECTIVITY: ALL 24-21-01 000-801-APage 408Dec 08/03

e 3: AMM Part II - MPP ExampleIssueRevis

Figur


MAINT(MPP)

The AMMtroubleshcomponewith the other thin

Simpl Prepa

Syste

Aircraf(AMTO

AMTOSS(task) anidentifica

The idenmaximum An ex

ing. After t

fies th The fi

numbquenc001 th

The sed pro

re special to the operator, or which are written byntified in the seventh element.

in AMTOSS are from 000 thru 900. Each code rep-tion:

ing, lubrication

.rigging, fault isolationl and installation

ents the task. The codes are subdivided to identifyllowing. The page below shows the application of

nd in the AMM Introduction section.190

e0600


ENANCE PRACTICES AND PROCEDURES

provides sufficient information to enable a mechanic to serviceoot, test, adjust and repair systems and to remove and install anynt on the line or in the hangar. This AMM is written in accordance

ATA 100 Revision 28 recommendations. Revision 28 has, amonggs, these two recommendations

ified Englishred for AMTOSS (Aircraft Maintenance Task Oriented Supportm)

t Maintenance Task Oriented Support System SS)

eases maintenance procedures by giving the specific procedured the primary steps of procedures (sub tasks) a different numbertion code.

tification code numbers have a minimum of five elements and a of seven. The elements are:

tension to the three ATA 100 Chapter, section and subject number-

he first three elements a function code will follow. This code identi-e type of work that has to be done.fth element shows the task or sub task identification number. Thiser is applicable to the task/sub task only and is counting the se-e of the task or sub task. Numbers 801 thru 999 are for tasks andru 800 for sub tasks.

ixth element identifies the differences in configuration and the relat-cedures and techniques.

Tasks/sub tasks that asub contractors are ide

Function Codes

The function codes used resents the following func

000 Removal 100 Cleaning 200 Inspection/Check 300 Repair 400 Installation 500 Material Handling 600 Servicing, preserv 700 Testing 800 Miscellaneous,e.g 900 Change - Remova

Each of the codes represthe tasks or sub tasks fothe function codes 400.

Further information is fou



MANUFACTURER

ATA (REF. 1-3-1)

ASSIGNED BY

EQUIPMENTIDENTIFIER

INSTALLATION No. 1ON N0001-N9999

RESERVED FORMANUFACTURER'SDISCRETIONARY USE, FORFURTHER DEFINITION OF THEFUNCTION

ASSIGNED BY OPERATOR

PRIMARY TASKNUMBERS

SUBTASKNUMBER(SEE NOTE)

ELEMENTNUMBERS

NOTE:SUBTASK ARE THE MAINTENANCE ACTIONS REQUIRED TO ACCOMPLISH A TASK. UNIQUE

IDENTIFIERS FOR SUBTASK FUNCTIONS SHALL COMMENCE AT 001 AND TERMINATE AT 800.

SUB-SUBSYSTEM DIFFERENCES IN CONFIGURATIONS(SB) SHOWN AS AN ALPHA CHARACTERIN THE FIRST DIGITDIFFERENCES IN METHODS/TECHNIQUESOF TASK ACCOMPLISHMENTSEQUENCE VARIATIONS OF STANDARDPRACTICES AT HARDWARE LEVELMULTIPLE SHEETS OF AN ILLUSTRATIONOR TABLE

CREATION OF SEQUENTIAL ORDERWITH THE SAME FUNCTION CODE WITHIN THE SUBJECT(TASK-801 TO 999SUBTASK-001 TO 800)

E

M

1

7

0

M

P

P

0

0

0

0

0

7

.

D

G

N

FUNCTION CODE

26 - 22 - 03 - 400 - 801 - B

ASSIGNED BY

CONFIGURATION

2 431 5 6

26 - 22 - 03 42X - - XXX - CC1 A01 -

7

(INSTALLATION NO. 1)

(INSTALLATION)

SEQUENTIAL ORDER

SYSTEM/CHAPTER(FIRE PROTECTION)

SUBSYSTEM/SECTION( EXTINGUISHING.)

(ENGINE FIRE EXTING.)

UNIT/SUBJECT(BOTTLES)

FUNCTION CODE(INSTALL UNIT)

NECESSARY TO IDENTIFY:

(ENG. FIRE EXTING. BOTTLES)

e 4: AMTOSS Codes and SubdivisionIssueRevis

Figur


AIRCR

Division

The first This secuse the mthe manuThe introin the ma

Each cha Effect Highli List of List of Servic Table

Effectivit

Effectivitconfigurafectivity ifollowing MAST ALL O An op An E

If a chapfectivity cidentifies

ve more information, e.g. Collins, to point out anration.

manual. It is possible for an operator to have a

ther with an operator prefix or ALL OPERATORS

t the page applies to all LX aircraft.RATORSircraft.

ther with MASTER or an operator prefix. Example:MASTERre pages with an E code, there will be a green Ef-

ence list in the beginning of the chapter. This listl numbers that are affected by the E code.190

e0600


AFT MAINTENANCE MANUAL

of Subject Matter:

section of the AMM is the Introduction.tion provides an introduction to the manual and instructions how to

anual correctly. It is strongly recommended to read this section ofal.duction section also includes a list of the chapters that are includednual.

pter has the following items filed at the front:ivity Code Cross Reference Listghts page(s) for each revision Effective Pages Effective Temporary Revisionse Bulletins

of Content

y:

y Codes are used in the AMM to allow many operators with differenttion aircraft to correctly apply the manual to their aircraft. The ef-

s shown in the lower left hand corner of each page in the AMM. The are the effectivities used:ERPERATORSerators prefix e.g. LX (Swiss) Code (E + a number, e.g. E26-018

ter has one or more pages with an E code, there will be a green Ef-ode cross reference list in the beginning of the chapter. This list the aircraft serial numbers that are affected by the E-code.

An Effectivity box may haitem that differs in configu

MASTER:Always means a mastermaster manual.

ALL:All is always shown togein the box. Example:EFFECTIVITY: ALL LXIn this case, it means thaEFFECTIVITY: ALL OPEThis page applies to all a

E Codes:The E code is shown togeEFFECTIVITY: E26-018 If a chapter has one or mofectivity code cross referidentifies the aircraft seria



OPERATORS

LX

E 26- - 018

e 5: Aircraft Maintenance ManualIssueRevis

Figur


FAULT

FIMFIM190

e0600


ISOLATION MANUAL (FIM)

Purpose:

- Provides all information needed to report and correct aircraftfaults to avoid or reduce dispatch delays and fix defective items orsystems.

Available links : AMM, WM, AIPC.

Arrangement:

MAINTENANCE MESSAGES INDEX

CAS MESSAGES LIST

OBSERVED FAULTS

CABIN FAULTS

FAULT CODE INDEX

FAULT ISOLATION PROCEDURES

TASK SUPPORT DATA

INTRODUCTION

FIM USAGE

FAULT REPORT SECTION

FAULT ISOLATION SECTION

CAS MESSAGES LIST

OBSERVED FAULTS LIST

CABIN FAULTS LIST

MAINTENANCE MESSAGES LIST

CHAPTERS

CAS MESSAGES LIST

OBSERVED FAULTS

CABIN FAULTS

FAULT CODE INDEX

FAULT ISOLATION PROCEDURES

TASK SUPPORT DATA

INTRODUCTION

FIM USAGE

FAULT REPORT SECTION

FAULT ISOLATION SECTION

CAS MESSAGES LIST

OBSERVED FAULTS LIST

CABIN FAULTS LIST

MAINTENANCE MESSAGES LIST

CHAPTERS



e 6: Fault Isolation Manual used with aircraft CMC (Central Maintenance Computer)IssueRevis

Figur


RAMP

NTENANCE MANUAL (CMM)

mation and procedures applicable to a workshopthe return of a component to a serviceable condi-

RMMRMM

CMMSections

S

SPECIAL TOOLS, FIXTURES AND EQUIPMENT

ILLUSTRATED PARTS LIST

SPECIAL PROCEDURES

REMOVAL

INSTALLATION

SERVICING

STORAGE

N

N

Y

G

K

IR

REWORK

APPENDICES

Y

S

CMMSections

S

SPECIAL TOOLS, FIXTURES AND EQUIPMENT

ILLUSTRATED PARTS LIST

SPECIAL PROCEDURES

REMOVAL

INSTALLATION

SERVICING

STORAGE

N

N

Y

G

K

IR

REWORK

APPENDICES

Y

S190

e0600


MAINTENANCE MANUAL (RMM)

Purpose: - Provides information which can improve the ground handling andavoid delays when difficulties are encountered for the dispatchabil-ity, at ramp level.

Arrangement :

COMPONENT MAI

Purpose :

- Provides inforenvironment for tion.

Arrangement:

PART I

INTRODUCTION

PART II

CHAPTERS

CHAPTERSAMM

TASKS

REFERENCE TABLES (RT)

ADJUSTMENT ALLOWANCES (AA)

COMPONENT LOCATION (CL)

SERVICING (SE)

DEACTIVATION PROCEDURES (DP)

AIRCRAFT OPERATION PROCEDURES (OP)

PART I

INTRODUCTION

PART II

CHAPTERS

CHAPTERSAMM

TASKS

REFERENCE TABLES (RT)

ADJUSTMENT ALLOWANCES (AA)

COMPONENT LOCATION (CL)

SERVICING (SE)

DEACTIVATION PROCEDURES (DP)

AIRCRAFT OPERATION PROCEDURES (OP)

SCHEMATICS AND WIRING DIAGRAM

DESCRIPTION AND OPERATIO

TESTING AND FAULT ISOLATIO

DISASSEMBL

CLEANIN

INSPECTION/CHEC

REPA

ASSEMBL

FITS AND CLEARANCE

SCHEMATICS AND WIRING DIAGRAM

DESCRIPTION AND OPERATIO

TESTING AND FAULT ISOLATIO

DISASSEMBL

CLEANIN

INSPECTION/CHEC

REPA

ASSEMBL

FITS AND CLEARANCE



AZONES

123124

A

C

B

C

BATTERY 2

TYPICAL

B

ZONE252

C

BATTERY 1

Main Batteries (24-36-00)Figure 2

RAMPMAINTENANCE MANUAL

EFFECTIVITY: ALL24-30-00

Part 1Page 8

Dec 08/03

COMPONENT LOCATION

e 7: Ramp Maintenance Manual ExampleIssueRevis

Figur


WIRIN

TIC MANUAL (SSM)

ical information to aid the maintenance personnel the aircraft systems and performing the fault iso-s at the LRU (Line Replaceable Unit) level.

on is presented through diagrams, with indicationcation, system interface, and references to otherSDS, MPP and WM).

SSM-Internal link, SDS MPP, WM.

WMWM

FIRST LEVEL - SYSTEM BLOCK DIAGRAMS

SECOND LEVEL - SYSTEM SCHEMATIC DIAGRAMS

THIRD LEVEL - SYSTEM LOGIC DIAGRAMS

FIRST LEVEL - SYSTEM BLOCK DIAGRAMS

SECOND LEVEL - SYSTEM SCHEMATIC DIAGRAMS

THIRD LEVEL - SYSTEM LOGIC DIAGRAMS190

e0600


G MANUAL (WM)

Purpose:

- Provides the necessary information concerning the wiring dia-grams to enable fault isolation and maintenance.

Arrangement :

SYSTEM SCHEMA

Purpose:

- Provides technin understandinglation procedure

- The informatiof component lomanuals (SSM,

Available links :

Arrangement:

INTRODUCTION

CHAPTERS 21 TO 80 WIRING DIAGRAMS

CHAPTER 91 ELECTRICAL AND ELECTRONIC CHARTS AND LISTS

INTRODUCTION

CHAPTERS 21 TO 80 WIRING DIAGRAMS

CHAPTER 91 ELECTRICAL AND ELECTRONIC CHARTS AND LISTS

SSM

INTRODUCTION

SECTIONS

SSM

INTRODUCTION

SECTIONS



S

K

1

7

0

S

S

M

2

4

0

0

0

5

.

D

G

N

FWD AVIONICS COMPARTMENT

AC STATIC INVERTER

(SDS 24-24)(MPP 24-24-01)

FORWARD AVIONICS COMPARTMENT

DC ESS BUS 1

28 VDC

115 VAC

AC ESS BUS (PH B)

STBY AC BUS

EICC(SSM 24-51-80)

15

A

A

A

1


INVERTERPWR

SEN

D

I

S

C

R

E

T

I

/

O

(

S

L

O

T

9

)

I

N

V

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M

T

O

N

/

O

F

F

C

M

D

D

C

P

O

W

E

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(

S

L

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T

2

)

I

N

V

F

A

U

L

T

S

T

A

T

D

C

P

O

W

E

R

(

S

L

O

T

5

)

S

T

B

Y

C

R

L

Y

S

T

A

T

SPDA 1 (SSM 24-61-80)

A

N

A

L

O

G

I

/

O

(

S

L

O

T

1

7

)

S

T

B

Y

A

C

P

H

B

S

E

N

S

T

B

Y

A

C

P

H

B

S

E

N

C

O

M

EF 2

STBYC(SSM 24-51-80)

24 - 24 - 50

WIRING DIAGRAM

SYSTEM SCHEMATICMANUAL

EFFECTIVITY: ALL STATIC INVERTER - SCHEMATIC DIAGRAM 24-24-80Page 101Dec 16/03

w

-

s

s

m

1

7

9

9

W

1

0

1

-

0

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5

6

-

2

2

W

1

0

1

-

0

1

0

6

0

W

1

0

1

-

0

1

0

5

9

-

1

8

B

L

W

1

0

1

-

0

1

0

5

9

-

1

8

W

H

W

1

0

1

-

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1

0

5

5

-

1

6

W

1

0

1

-

0

1

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5

4

-

1

6

W101-01058-24BL

W101-01058-24WH

W101-01053-24

W

1

0

1

-

0

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6

1

W

1

0

1

-

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5

7

-

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3

6

3

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W

1

0

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6

3

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3

3

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5

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B

2

1

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F

A

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A

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0

1

0

1

170-11787

1421610

(24-61-50)(24-61-56)

PS0001

J

1

DC ESS BUS 1

E

N

G

2

E

X

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I

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E

R

2

A

I

N

V

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E

R

P

W

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A

1

A

1

A

3

A

2

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1

1

5

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A

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2

8

V

D

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D

C

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A

2

B

1

B

3

B

2

2

S

T

B

Y

A

C

P

H

B

S

E

N

STANDBY AC BUS

5

C

B

2

2

S

T

B

Y

A

C

P

H

B

S

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N

C

O

M

1

1

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N

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1

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X

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1

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AC ESS BUS

B

STATIC INVERTER- 123

J

3


K

1

F

3

F

2


I

N

V

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F

F

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D

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Y

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1

2

J

2

X

1

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9

EICC

F

A

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SPDA 1

74-10-51

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2

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- 123

J

5

- 123/124

J

5

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8

-

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X

1

(E )

E

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1

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2

74-10-50

1

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A

3

A

2

X

2

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1

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F

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1

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1

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3

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1

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1

6

2

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1

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2

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2

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B

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0

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9

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0

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EAIHBC

P

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1

1

AIRCRAFTWIRING MANUAL

00008-99999 STATIC INVERTER SYSTEM 24-24-50Page 1

Dec 01/03

e 8: Wiring Manual and System Schematic ManualIssueRevis

Figur


AIRCR

General

The AIPCtioning, sparts. Thfor which

Section N

The sectond elem

To enablcating itedesignat

00 Ele 01 Fo 02 Ce 03 Aft 04 Wi 05 En190

e0600


AFT ILLUSTRATED PARTS CATALOGUE (AIPC)

is provided by the manufacturer for use in provisioning, requisi-toring and issuing replaceable parts and units, and for identifyinge AIPC is a companion document to the AMM and includes all parts maintenance practice has been provided.

umbering

ion numbering is made of three elements, whereby the first and sec-ent represents the chapter/section breakdown according ATA 100.

e quick location of installation figures and to simplify the task of lo-ms within the IPC, the third element in the Chapter numbering is

ed to aircraft major zones as follos:

ctrical installations in all applicable zonesrward fuselage and cockpitnter fuselage and cabin fuselage and cargo compartmentngsgine and nacelles



A

B

TYPICAL

B

A

416ZONE

A426

ZONE

20

30

10

40

50

50

E

M

1

7

0

A

I

P

C

2

4

0

1

4

7

B

Figure 01 - INTEGRATED DRIVE GENERATORS 1/2 (IDG) INSTL, AC GENERATION 1/2, LH/RHNACELLE

AIRCRAFT ILLUSTRATEDPARTS CATALOG

24-21-01 Fig. 01Page 0

Mar 29/04

01 1 170-48011-501 REFENGINE INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 170-48011-501 REFENGINE INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

10 1701317A 1.GENERATOR INTEGRATED DRIVE . . . . . . . . . . . . . . . . . . . . . . . . .FOR DETAILS SEE FIGURE 24-21-01-03FOR DETAILS SEE FIGURE 24-21-11-01FOR DETAILS SEE FIGURE 24-21-15-01FOR DETAILS SEE FIGURE 24-21-17-01

20 15E0420003 1.BRACKET ASSEMBLY W8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATTACHING PARTS

30 J644P06A 3.BOLT MACHINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .40 5911541 REF.COUPLING CLAMP V . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

* * *50 REF.HARNESS W8 AND W9 INSTL ENGINE LH/RH . . . . . . . . . . . . .

SEE FIGURE 71-50-01-01

FIG. ITEM PART NUMBER

AIRLINESTOCK

NUMBERNOMENCLATURE1234567

VENDORCODE

USAGERANGE

UNITSPER

ASSY

INTEGRATED DRIVE GENERATORS 1/2 (IDG) INSTL, AC GENERATION 1/2, LH/RH NACELLE

AIRCRAFT ILLUSTRATEDPARTS CATALOG

24-21-01 ITEM NOT ILLUSTRATED Fig. 01Page 1

Mar 29/04

e 9: Aircraft Illustrated Parts Catalogue (AIPC)IssueRevis

Figur


OTHER

AIRCR

AIRPO

- Providefor the ai

CONSU

ENTION MANUAL (CPM)

n materials and procedures for prevention and re-e to aircraft as well as to display EMBRAERs rec-uent corrosion troubles.

OL AND EQUIPMENT MANUAL

about GSE (Ground Support Equipment) to sup-intenance of the aircraft and all its onboard equip-

R GROUND FIRE EXTINGUISHING UAL (IGFER)

e necessary information to guide ground rescueuing passengers in case of aircraft accidents.

BM, CPM, FIM, MPP, PPBM, SDS, SM, SRM, ITM,190

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DOCUMENTATION

AFT RECOVERY MANUAL (ARM)

Purpose:

- Contains information in sufficient detail to effect recovery in themost expeditious manner while maintaining consideration of recov-ery personnel safety and prevention of additional damage to the air-craft.

RT PLANNING MANUAL (APM)

Purpose:

s necessary information to enable a proper planning of the airportsrcraft operation.

MABLE PRODUCTS CATALOGUE (CPC)

Purpose:

- Provides the information about the consumable materials used tooverhaul and repair the aircraft.

CORROSION PREV

Purpose:

- Provides information omoval of corrosion damagommendations about freq

ILLUSTRATED TO(ITEM)

Purpose:

- Provides all informationport the operation and mament.

INSTRUCTIONS FOAND RESCUE MAN

Purpose:

- To provide thteams while resc

- Available links: APUNDT, WM, SWPM.



I

F

1

7

0

A

R

M

0

3

0

0

0

5

.

D

G

N

A

A

SOFT MATERIAL(RUBBER, FELT, ETC.)

HARD WOODBEAM

JACKADAPTER (2x)

200 mm(20 in.)

Lifting the Aircraft with JacksFigure 3-30-05-1

Sheet 1

AIRCRAFTRECOVERY MANUAL

EFFECTIVITY: ALL 3-30-05Page 4

Feb 10/04

e 10: Example of Aircraft Recovery ManualIssueRevis

Figur


MAINTPLANN

- It identrequirem

NOND

- Providebraer for

SERVI

IN (SB)

fications or special inspections to be carried out onft.

mation: involves those aspects related to plan theance opportunity/necessity for the SB incorpora-

ation to assist the operator in obtaining the mate-r the SB incorporation.nt instructions: presents the step-by-step instruc trations for accomplishing the work.

LLETIN (IB)

nsmit information, which are not related to actionsd of accomplishment.

licability)

ications190

e0600


ENANCE FACILITY AND EQUIPMENT ING (MFEP)

Purpose:

- Provides aircraft characteristics to assist airline personnel re-sponsible for service, line maintenance, overhaul facilities andequipment planning.

ifies and describes aircraft maintenance and operational facility ents.

ESTRUCTIVE TESTING MANUAL (NDT)

Purpose:

s all general procedures of nondestructive tests acceptable by Em- investigating the quality and integrity of materials and components.

CE BULLETIN (SB)

Purpose:

- Presents modifications or special inspections to be carried out onin-service aircraft.

Arrangement:

SERVICE BULLET Purpose:

- Presents modiin-service aircra

Arrangement: - Planning infor

aircraft maintention.- Material: informrial necessary fo

- Accomplishme tions and illus

INFORMATION BU

Purpose:

- It is used to trarequiring a recor

Arrangement:- Purpose- Effectivity (app- Description- Approval- References

- Affected Publ



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STOP M

SSI 56-10-005

STOP N

SSI 56-10-005

SSI 56-10-005

FWD LOWER ROLLERS

SSI 56-10-005

FWD LOWER TRACKSSI 56-10-005

AFT LOWER ROLLER

AFT LOWER TRACK

SSI 56-10-005

SSI 56-10-005

STOP O

SSI 56-10-005

SSI 56-10-005

UPPER ROLLER

UPPER TRACK

SSI 56-10-005ROLLER D

A

B

ROLLER

Internal Detailed Visual-Inspection of the Direct Vision Stops, Tracks, Roller Studs and BellcrancksFigure 1

NONDESTRUCTIVETESTING MANUAL

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1

8

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EFFECTIVITY: ALL 56-10-00Part 5

213-802Page 4

Dec 08/03

e 11: Example of Nondestructive Testing ManualIssueRevis

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STRUC

Available

STAND

- Allolated com

TASK

- Prsupport t190

e0600


TURAL REPAIR MANUAL (SRM)

Purpose:

- To permit the operators to identify and evaluate the damage andrestore the structural integrity of the aircraft by means of a repair orby replacing the damage part.

links: MPP, NDT, CPM, SM, ITEM, CPC.

ARD WIRING PRACTICES MANUAL (SWPM)

Purpose:

ws the operator to repair, manufacture and handle all harness-re-ponents.

CARD SYSTEM (TCS)

Purpose:

ovides a reliable tasks list that can be customized by operators tohe MPD and suit the operators needs.



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Dent on Forward Passenger Door Skin - LocationFigure 101

STRUCTURALREPAIR MANUAL

EFFECTIVITY: ALL 52-11-01 Allowable Damage 2Page 103Oct 10/03

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Intentionally left balnk

190

ATA 0 raft General4 Airc

190

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Ta

04IntThCoThERCFThER

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ble of Content

-00 Aircraft Generalroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1e fuselage and conditioning packs . . . . . . . . . . . . . . . . . . . . . . . 3ckpit and cabin sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5e landing gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7J 190 turning radius . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 934-10E high bypass turbofan engines . . . . . . . . . . . . . . . . . . . 13e Embraer ERJ 190 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15J 190 composite structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

-01 Differences EMB 190-100/ 190-200ferences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

190

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190

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-00 Aircraft General

troduction

e following short introduction will give you a general overview of the Em-er 190-100 and 190-200.The Emb 190 is a low wing, twin engine jet air-ne of conventional structure, designed for medium to short rangeerations. The Emb 190-100 has a total length of 36.15 meters (118 ft 7), a wing span of 28.56 meters (93 ft 8 in.) and an approximate height of.48 meters (34 ft 5 in.). The EMB 190-200 has a total length of 38-67 (1260 in), a wing span of 28.72 m (94 ft 3 in) and an approximate height of

.55 m (34 ft 7 in).

lso features a pressurized cabin. The fuselage has a so-called doublebble design.

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Page 2Chapter 04-00

F

34 ft 5 in

(10.48 m)

ft 7 in15 m)

32 ft 10 in

(10.00 m)sue: June06evision: 00


igure 1: The Embraer 190-100(Emb 190)

93 ft 8 in(28.56 m)

118(36.

Embraer 190-100 Emb 190

190

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e fuselage and conditioning packs

e fuselage is pressurized between the forward pressure bulkhead, locat- forward of the cockpit, and the aft pressure bulkhead, which is locatedhind the aft electronics bay.

rmal pressurization control is automatic, and the conditioned air is provid- by two air conditioning packs located in the unpressurized area forwardthe wing root.

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F

Conditioning packs

conditioned air is provided by two air ditioning packs located in theressurized area forward of the wing root.sue: June06evision: 00


igure 2: The fuselage and conditioning packs

Fwd pressure bulk head Aft pressure bulk head

Normal pressurization control is automatic

Theconunp

190

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ckpit and cabin sections

e cockpit can accommodate 2 crew members in the pilot seats and oneserver on the jump seat. Two flight attendants. The Embraer 190-100 issigned for 98 passengers and the Embraer 190-200 is designed for 108ssengers. There are 2 Galleys and 2 toilets - one of each in the front and aft sections of the cabin.

e cabin also features a wardrobe, built next to the front passenger en-nce. There are 2 cargo compartments below the passenger cabin - onefront and one behind the wing fairing.

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F

ight attendants seats

alleys and two toiletssue: June06evision: 00


igure 3: Cockpit and cabin sections

Two pilots seats

Wardrobe98 passenger seats

One jump seat

Two fl

Two g

Cargo compartments

190

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e landing gear

e Emb 190 has a forward retracting twin-wheel nose landing gear (NLG).

e NLG has a normal steering angle of about 76, making the aircraft high-manoeuvrable. The shock absorbers are of oleo-pneumatic type. Theering motor, taxi light and one landing light are mounted on the NLG.en the NLG is extended, the rear doors remain open while the front doorslose after extension or retraction.

e main landing gears (MLG) also have oleo-pneumatic shock absorbersd twin wheels retract sideways.

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ing gears (MLG) retract sue: June06evision: 00


igure 4: The landing gear

The main landsideways.

The NLG has a normal steering angle of about76, making the aircraft highly manuverable.

EMBRAER 190

190

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b 190 turning radius

th a full deflection of the nose wheel, the Emb190-100 can theoreticallyn on taxiways as narrow as 21.40 m (70 ft 3 in.). The Emb 190-200 cann on taxiways as narrow as 22.68 m (74 ft 5 in). Note that the largestarance is required by the tail, which is not visible. In a maximum turn, ei-r the left or the right MLG remains stationary, marking the centre of then.

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igure 5: Emb 190-100 turning radius

Nosetip 18.12 m (59 ft 5 in.)

Nosewheel 14.07 m (46 ft 2 in.)

Wingtip 18.39 m (60 ft 4 in.)

Tail 20.51 m (67 ft 4 in.)

With a full deflection of thenose wheel, the Emb190-100can theoretically turn on taxiways as narrow as 21.40 m (70 ft 3 in.).

Issue: June06Revision: 00

Page 11FOR TRAINING ONLY Reproduction Prohibited

Chapter 04-00

Notes:

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Nosetip 19.13 m (62 ft 9 in.)

Nosewheel 15.10 m (49 ft 7 in.)

Wingtip 18.61 m (61 ft 1 in.)

Tail 21.9 m (71 ft 10 in.)

With a full deflection of thenose wheel, the Emb190-200can theoretically turn on taxiways as narrow as 22.68 m (74 ft 5 in.).

Figure 6: Emb 190-200 turning radius

190

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34-10E high bypass turbofan engines

e two wing-mounted CF34-10E high bypass turbofan engines are based the CF34 engine family, which is widely used in aviation. Engine controlsd fuel scheduling are provided by a full-authority digital engine controlDEC) with fully modular design.

e CF34-10E incorporates the aerodynamic efficiency of wide cord fan,ich produces most of the engine's 18,500 Lbs maximum thrust. To en-nce aircraft braking capability, the fan by-pass air is reversed not the en-e.

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craft braking capability, air is reversed.

FADEC Vent to Compartment

RHS Cooling Scoop



Side View

Top View

CF34-10E high bypass turbofan engine

To enhance airthe fan by-pass

FADEC

igure 6: CF34-10E high bypass turbofan engines

190

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e Embraer Emb 190-100

e Emb 190-100 can climb to 30,000 ft within 15 minutes, and has a certi-d ceiling of 41,000 ft.

e Emb 190-100 has a maximum cruising speed of mach.80

pending on the long or normal range version, it can reach destinationswards of 2,000 nautical miles with standard reserves left in the tanks.

e Embraer Emb 190-200

e Emb 190-200 can climb to 30,000 ft within 17 minutes and has a certi-d ceiling of 41,000 ft.

e Emb 190-200 has a maximum cruising speed of mach.80

pending on the long or normal range version, it can reach destinationswards of 2,000 nautical miles with standard reserves left in the tanks.

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b 190:

to 30,000ft within 15 minutes

eiling of 41,000 ft

cruising speed of mach .80

to 2,000 nautical miles



The Em

Can climb

Certified c

Maximum

Range up

igure 7: The Embraer Emb 190

190

IssRev


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b 190 composite structure

maximize performance, a variety of modern composites like fiberglassd carbon have been used. These materials are lighter in weight and morerable than conventional aluminium, improving aircraft performance.

sides the conventional flight controls, the aircraft is equipped with an ad-table stabilizer and multi functional spoilers.

rodynamic characteristics are enhanced by leading edge slats andund spoilers.

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F

ilers

ion spoilerssue: June06evision: 00


igure 8: ERJ 190 composite structure

Ground spo

Multi funct

190

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-01 Differences EMB 190-100 /190-200

e Embraer 190-100 has a seat capacity of 98 seats.e Embraer 190-200 has a seat capacity of 108 seats.

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Page 2Chapter 04-01

er 190-100eats

er 190-200 Seats

EMBRAER 190-100

98 seats

MTOW : 47790 kg / 105357 lbs

MLW : 43000 kg / 94797 lbs

MZFW : 40800 kg / 89947 lbs

EMBRAER 190-200

108 seats

MTOW : 48790 kg / 107562 lbs

MLW : 45000 kg / 99206 lbs

MZFW : 42500 kg / 93695 lbs



Embra98 S

Embra108

igure 1: Seat capacity

190

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190

ATA 05 Time Lim d Maintenance checksits an

190

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me Limits and Maintenance checksroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1scheduled maintenance checks . . . . . . . . . . . . . . . . . . . . . . . .3

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00 Time Limits and Maintenance checks

troduction

apter 05, time limits and maintenance checks of the aircraft maintenancenual, provides inspection procedures for various scheduled and un-

heduled checks.

e data concerning detailed time limits and scheduled maintenanceecks can be found in the "Maintenance Planning Guide".

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ariousssue: June06evision: 00


igure 1: Chapter 05

States inspection procedures for vscheduled and unscheduled check

Chapter 5:

190

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scheduled maintenance checks

scheduled maintenance checks have to be performed after the followingcurrences:

Lightning strike Hard landing or overweight landing High drag/side-load landing conditions Strong turbulence or buffeting conditions High-load-factor flight Landing-gear-down overspeed Exceeding flap/down speed condition Bird strike Engine fire warning or overheat indication Ice or snow condition APU fire warning or overheat indication Toilet overservicing Landing gear free-fall condition Overheated wheels Landing-gear tire tread failure

190

ATA 06 Aircra as and dimensionsft are

190

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FOR TRAINING ONLY Reproduction Prohibited TOC 06

Table of Content

06-00 Aircraft areas and dimensionsIntroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1The aircraft measurement Embraer 190. . . . . . . . . . . . . . . . . . . . . 3The aircraft measurement Embraer 195. . . . . . . . . . . . . . . . . . . . . 5The aircraft measurement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7The aircraft stations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9Wing station diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11The vertical stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12The horizontal stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14The power plant and the engine pylons . . . . . . . . . . . . . . . . . . . . 15The aircraft zoning system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16The major aircraft zones . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17Sub zones. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18Access panels. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

190

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-00 Aircraft areas and dimensions

troduction

is chapter describes the aircrafts general external dimensions, aircraftning and station identification. The fuselage stations show the lengthasurements along the longitudinal axis.

horizontal measurements are taken from the datum line FS 0 which is lo-ted at the nose tip. The forward pressure bulkhead is located at station0 and the fuselage is pressurized between the forward pressure bulkheadd the rear pressure bulkhead, which is located at station 29427.

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FS 29427

ear pressurebulkhead

Longitudinal axissue: June06evision: 00


igure 1: Horizontal measurements

FS 0

R

FS 610

Forward pressurebulkhead

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e aircraft measurement Embraer 190-100

e aircraft has a total length from the nose to the tail of 36.24m, the heightm the ground to the top of the vertical tail is 10.55m and a vertical tail area16.20 m.

e distance from the nose gear to the main gear is 10.60 meters. The air-ft has a total wing span of 28.72m with a total wing area of 92.50 m, arizontal tail span of 12.01 m, with a horizontal tail area of 26.00 m and aelage external diameter of 3.01 m.

e distance from the left to right main gear is 5.94 meters.

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m

10.55 m

ea: 16.20 m 2sue: June06evision: 00


igure 2: Aircraft measurements Embraer 190 - 100

36.24

Vertical tail ar

Distance from nose gear to main gear:13.83 m

Total wing area: 92.50 m2

Total wingspan: 28.72 m

Horizontal tail span:12.01 m

Horizontal tail area:26.00 m 2

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e aircraft measurement Embraer 190 - 200

e aircraft has a total length from the nose to the tail of 38.67m, the heightm the ground to the top of the vertical tail is 10.55m and a vertical tail area16.20m.

e distance from the nose gear to the main gear is 13.83 meters. The air-ft has a total wing span of 28.72 meters with a total wing area of 92.05, a horizontal tail span of 12.08 meters, with a horizontal tail area of 26md a fuselage external diameter of 3.01 m.

e distance from the left to the right main gear is 5.94 meters.

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5.94 m

28.72 m

8.67 msue: June06evision: 00


igure 3: The aircraft measurement Embraer 190 - 200

3

12.08 m

13.83 m

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190Th

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e aircraft measurement

cated on the left side of the fuselage are two main doors, which qualifies type 1 emergency exits. Located on the right side of the fuselage are tworvice doors, which qualify as type 1 exits, and two baggage compartmentors.

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ype 1 emergency exitssue: June06evision: 00


igure 4: The aircraft measurement

Type 1 exits

TOVERWING EXITS

OVERWING EXITS

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e aircraft stations

e aircraft stations are defined by a coordinate system using three mainerence axes. The point of origin for the longitudinal axis X, laterall axis Yd vertical axis Z is in front of the aircraft.

e ordinates are identified by the letter for the major axes, followed by theension in inches from the point of origin.

ere are additional points of origin selected for locating major assemblies.ese points are identified with a suffix letter indicating the assembly. Thesesemblies are the wings, the vertical stabilizer, the horizontal stabilizer, thewer plant and the engine pylons.

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F

selage 3 Rear Fuselage Tail Cone

X X=29632 X=33427 X=36237sue: June06evision: 00


igure 5: Fuselage dimension

EMBRAER 190

FWD Fuselage Center Fuselage 1 Center Fuselage 2 Center Fu

=0 X=610 X=6232.5 X=11035 X=19429

FWD CentralFuselage II

X=13442 X=23146

AFT CentralFuselage II

IssRev


190Fig

RIB 1 Y= -1380.00

AT 1

BOARD FLAP

WING SPAR 3

Y = 00.00YA = 00.00

WING REF.POINT

YA = 00.00ue: June06ision: 00


ure 6: Wing station diagram

RIB 26 YA= -12196.00

RIB 10 YA= -4617.57

SLAT 4

WING SPAR 1

SLAT 3

SLAT 2

ENGINE

DRY BAYSL

WING TRAILINGEDGE

AILERON

OUTBOARD FLAPWING SPAR 2

IN

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igure 7: Vertical stabilizer

Z= 00,00ZV= 00,00

XV= 00,00A

ZV7020,10

ZV4269,00

ZV1069,00

ZV622,98

IssRev


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F

Y = 00.00sue: June06evision: 00


igure 8: Horizontal stabilizer

YH -6100.00

IssRev


190Fig

5589.90

XP7201.0

XP8191.0ue: June06ision: 00


ure 9: Power plant and engine pylons

X ENGX ENG 3877.60

CANTXP

3256.97

XP4722.0

XP6340.0

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T

Tco

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he aircraft zoning system

he aircraft zoning system provides identification of areas in the aircraft ac-rding to 8 major zones, major sub-zones and zones.

he major aircraft zones are:

The lower fuselage, zone 100

The upper fuselage, zone 200

The tail cone and horizontal and vertical tail, zone 300

The power plants and pylons, zone 400

The left wing, zone 500

The right wing, zone 600

The landing gear and landing gear wheel well doors, zone 700

The aircraft doors, zone 800

IssRev


190Fig

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TAIL CONE300ue: June06ision: 00


ure 10: The major aircraft zones

RIGHT WING600

LEFT W50

LOWER FUSELAGE100

UPPER FUSELAGE200

DOORS800

DOORS800

HORIZONTAL/ VERTICAL TAIL300

MAIN LANDING GEARAND WHELLWELL

700

POWERPLANTAND PYLONS

400

NOSE LANDING GEAR ANDWHEELWELL DOOR

700

DOORS800

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S

Tsevisue: June06evision: 00


ub zones

he major zones are divided into major sub-zones, which are shown by thecond digit of the major zone number.The major sub-zones are further di-

ded into zones using the third digit of the major zone number.

IssRev


190

NE 150

SUBZONE 160

SUBZONE 170

ZONE 115

Zone number

Figue: June06ision: 00


SUBZONE 110

SUBZONE 120

SUBZONE 130

SUBZONE 140

SUBZO

Subzone number

ZONE 111

ZONE 113

ZONE 116

ZONE 114

ure 11: Sub-zones

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A

Tpd

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Ethsue: June06evision: 00


ccess panels

o carry out maintenance on aircraft systems and their components, or toerform inspection of the aircraft structure, adequate access panels andoors are provided in the aircraft surface.

ach access panel has an identification number which consists of a threeigit zone number followed by two or three letters.The first letter shows theumber of the panel within the zone in a logical in a logical sequence ande second letter indicates the location of the panel in relation to the air-aft.An optional third letter is used to identify a floor, wall or ceiling panel.

ach panel has a fastener identification code, which identifies the type ande quantity of the fasteners for each panel.

IssRev


190Fig

5 JL

195 KL

195 GL

195 EL

195 DL

19 S

anel has a fastener identification code:

L = Latch

S = Screw

C = Camlocue: June06ision: 00


ure 12: Access panels identification letters

191 DL

191 EL

192 CL

192 BL

192 AL

195 HL

195 FL

19

195 CL195 BL195 AL

191 CL

191 AL

Shows the number of thepanel within the zone

Indicates the location of thepanel in relation to the aircraft

An optional third letter is used to identify a floor(F), wall(W) or ceiling(C) panel.

191 BL

19 S

Each p

190

ATA 07 Lifting and Shoring

190

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ble of Content

fting and Shoringroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1mplete aircraft jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3fore complete aircraft jacking . . . . . . . . . . . . . . . . . . . . . . . . . .5cking points location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7se and main gear jacking points . . . . . . . . . . . . . . . . . . . . . . . .9

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FOR TRAINING ONLYReproduction Prohibited


190

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00 Aircraft jacking

troduction

replace components, the aircraft can be lifted either by using individualding gear jacking, which permits replacement of wheels and brakes or by

mpletely lifting the aircraft via the jacking points.

ere are two main jacking points on the wing lower side and one jack point the rear fuselage lower side. Procedures for lifting a damaged aircraft arescribed in the Instructions for Ground Fire Extinguishing and Rescuenual.

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LG



N

Jacking points

igure 1: Landing gear jacking, jacking points

190

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mplete aircraft jacking

mplete aircraft jacking, also called three point fuselage jacking, is neces-ry to perform maintenance such as replacement, repair or functionalecks to the landing gear and its components. It can also be used for air-ft weighing.

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Page 4Chapter 7-00



igure 2: Complete aircraft jacking

Complete aircraft jacking(three point fuselage jacking)

Landing gear:

replacement

pair

nctional checks

rcraft weighing

190

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Be

Coof

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fore complete aircraft jacking

mplete aircraft jacking must be performed in accordance with chapter 7the aircraft maintenance manual.

fore complete jacking of the aircraft several conditions have to be fulfilled:

All unnecessary equipment below and around the aircraft must beremoved.

The aircraft should only be jacked on level ground with the nosepointing into the wind, but preferably in a hangar with closed doors.

Both main landing gears and the nose gear have to be safetylocked to prevent inadvertent landing gear retraction.

Install the GSE 070 on all landing gear wheels to prevent the air-plane forward and aft movement before the jacks are set.

The emergency/parking brake must be released before jacking. Noone is allowed to enter the aircraft during jacking operation.

The aircraft must be lifted to achieve a minimum clearance be-tween the ground and the aircraft tires to assure sufficient clear-ance for main gear retraction.

te: Before aircraft jacking, refer to the table mentioned in the AMM foright limitations to ensure that the centre of gravity is within the jacking en-lope.

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F

26982

3254

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igure 3: CG position

CG position

190

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cking points location

e aircraft is fully lifted by the

book 1 short emb 190

Documents

training purposes

reproduction prohibitedc

official information

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