Book 1 Short Emb 190
Transcript of Book 1 Short Emb 190
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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
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FOR TRAINING ONLYGE Capital Aviation Training. Reproduction Prohibited Chapter 27-00
XLMTTextfeldIssue: Jan07
XLMTRechteck
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Abbreviatio d parts locationsns an
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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
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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
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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
FOR TRAINING ONLY Reproduction Prohibited
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
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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
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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
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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
FOR TRAINING ONLY Reproduction Prohibited
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
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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
FOR TRAINING ONLY Reproduction Prohibited
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
FOR TRAINING ONLY Reproduction Prohibited
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
FOR TRAINING ONLY Reproduction Prohibited
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
FOR TRAINING ONLY Reproduction Prohibited
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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S
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igure 1: Cockpit Instruments Location
Audio panel
MCDU
EICA
GP
M
CCD
Provision forfuture MCDU
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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
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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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F
INVERTER
MAU 1
C
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igure 3: Fwd E-Bay back
Forward E-Bay
MAU 2
GCU (RAT) PRESSURE
CONTROLLER
SMART-PROBE
DIMMER
EIC
RH
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Fig
SF-ACE
MS
CC ue: June06ision: 00
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ure 4 : Center E-Bay
Center E-BAY
SPDA 2
LIRICC
FIREX BOTTLES
FCU
MAU 3
SF-ACE MRC 2
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F
ANT UPLER
P-ACE 3
APU-FADEC sue: June06evision: 00
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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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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
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Introdu
All mainshootingrelated d190
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Documentation
ction
tenance checks, inspections, repairs, replacements and trouble- must be performed in accordance with valid documentation. Theocumentation necessary to maintain the aircraft includes:
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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
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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
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E
M
1
7
0
S
D
S
2
4
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3
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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.
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AMM PPROCE
COMPONE
LOCATIO
(100)
COMPONE
LOCATIO
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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)
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: June06ion: 00 Page 6
FOR TRAINING ONLYReproduction Prohibited Chapter 0-00
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)
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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
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Issue: JunRevision: Page 7Chapter 0-00
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
FOR TRAINING ONLY Reproduction Prohibited
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
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: June06ion: 00 Page 8
FOR TRAINING ONLYReproduction Prohibited Chapter 0-00
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)
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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
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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
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FOR TRAINING ONLY Reproduction Prohibited
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
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: June06ion: 00 Page 10
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OPERATORS
LX
E 26- - 018
e 5: Aircraft Maintenance ManualIssueRevis
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FAULT
FIMFIM190
e0600
FOR TRAINING ONLY Reproduction Prohibited
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
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: June06ion: 00 Page 12
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e 6: Fault Isolation Manual used with aircraft CMC (Central Maintenance Computer)IssueRevis
Figur
-
Issue: JunRevision: Page 13Chapter 0-00
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
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FOR TRAINING ONLY Reproduction Prohibited
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
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: June06ion: 00 Page 14
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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
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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
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FOR TRAINING ONLY Reproduction Prohibited
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
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S
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D
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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
FORWARD AVIONICS COMPARTMENT
INVERTERPWR
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24 - 24 - 50
WIRING DIAGRAM
SYSTEM SCHEMATICMANUAL
EFFECTIVITY: ALL STATIC INVERTER - SCHEMATIC DIAGRAM 24-24-80Page 101Dec 16/03
w
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AIRCRAFTWIRING MANUAL
00008-99999 STATIC INVERTER SYSTEM 24-24-50Page 1
Dec 01/03
e 8: Wiring Manual and System Schematic ManualIssueRevis
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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
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FOR TRAINING ONLY Reproduction Prohibited
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
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: June06ion: 00 Page 18
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A
B
TYPICAL
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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
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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:
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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:
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- Available links: APUNDT, WM, SWPM.
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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.
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ications190
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Purpose:
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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
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SSI 56-10-005
FWD LOWER TRACKSSI 56-10-005
AFT LOWER ROLLER
AFT LOWER TRACK
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UPPER TRACK
SSI 56-10-005ROLLER D
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Internal Detailed Visual-Inspection of the Direct Vision Stops, Tracks, Roller Studs and BellcrancksFigure 1
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Purpose:
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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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-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
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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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34 ft 5 in
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ft 7 in15 m)
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igure 1: The Embraer 190-100(Emb 190)
93 ft 8 in(28.56 m)
118(36.
Embraer 190-100 Emb 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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Conditioning packs
conditioned air is provided by two air ditioning packs located in theressurized area forward of the wing root.sue: June06evision: 00
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igure 2: The fuselage and conditioning packs
Fwd pressure bulk head Aft pressure bulk head
Normal pressurization control is automatic
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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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ight attendants seats
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igure 3: Cockpit and cabin sections
Two pilots seats
Wardrobe98 passenger seats
One jump seat
Two fl
Two g
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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
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igure 4: The landing gear
The main landsideways.
The NLG has a normal steering angle of about76, making the aircraft highly manuverable.
EMBRAER 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.).
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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
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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
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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
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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
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igure 7: The Embraer Emb 190
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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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ilers
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Ground spo
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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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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
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Embra108
igure 1: Seat capacity
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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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igure 1: Chapter 05
States inspection procedures for vscheduled and unscheduled check
Chapter 5:
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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
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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
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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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ear pressurebulkhead
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igure 1: Horizontal measurements
FS 0
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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
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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
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igure 3: The aircraft measurement Embraer 190 - 200
3
12.08 m
13.83 m
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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
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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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selage 3 Rear Fuselage Tail Cone
X X=29632 X=33427 X=36237sue: June06evision: 00
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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
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AT 1
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WING SPAR 3
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WING REF.POINT
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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
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YH -6100.00
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190Fig
5589.90
XP7201.0
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ure 9: Power plant and engine pylons
X ENGX ENG 3877.60
CANTXP
3256.97
XP4722.0
XP6340.0
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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
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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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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.
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190
NE 150
SUBZONE 160
SUBZONE 170
ZONE 115
Zone number
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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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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.
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190Fig
5 JL
195 KL
195 GL
195 EL
195 DL
19 S
anel has a fastener identification code:
L = Latch
S = Screw
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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
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ATA 07 Lifting and Shoring
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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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Intentionally left blank
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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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N
Jacking points
igure 1: Landing gear jacking, jacking points
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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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igure 2: Complete aircraft jacking
Complete aircraft jacking(three point fuselage jacking)
Landing gear:
replacement
pair
nctional checks
rcraft weighing
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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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igure 3: CG position
CG position
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cking points location
e aircraft is fully lifted by the