Bombardier Global 000-Airplane General

GENERAL

Abbreviations 01−10−1

Conversion Factors 01−10−13

Temperature Conversion Table 01−10−14

General Airplane Description 01−10−15

Airplane Dimension Schematic 01−10−16

Dimensions and General Data 01−10−17Overall dimension 01−10−17Wing 01−10−17Spar locations 01−10−17Horizontal tail surface 01−10−17Vertical tail surface 01−10−17Fuselage 01−10−17Landing gear 01−10−17Areas 01−10−18Doors 01−10−18Baggage compartment door (LH, aft) 01−10−18

Antenna Location Schematic 01−10−19

Visual Eye References For Ground Operation 01−10−20

Steering Radii 01−10−21

Steering Radii Schematic 01−10−21

Turning Radii 01−10−22

Turning Radii Schematic 01−10−22

Jet Exhaust Single Engine Ground Idle Thrust 01−10−23

Jet Exhaust Single Engine Take-off Thrust 01−10−24

Jet Exhaust Two Engine Ground Idle Thrust 01−10−25

Jet Exhaust Two Engine Take-off Thrust 01−10−26

Airplane Jacking 01−10−27

Jacking Points Schematic 01−10−27

Towing 01−10−28

Tow Bar Attachment Schematic 01−10−28

Towbarless Schematic 01−10−29Ground Locking Safety Pins 01−10−29

Mooring 01−10−30

AIRPLANE GENERAL

TABLE OF CONTENTS

CHAPTER 1

01−00−1

Rev 12, Aug 14, 2006 Flight Crew Operating Manual

CSP 700−5000−6

Volume 201−00−1

Page

TABLE OF CONTENTS

GENERAL

Mooring Attachment Points Schematic 01−10−30

Seat Assembly 01−10−31Seat Egression 01−10−32Moving the Seat Forward 01−10−32

Eye Locator−Seat Adjustment 01−10−33

Control Wheel 01−10−34Master Disconnect 01−10−34Pitch Trim Switch 01−10−34Autopilot/Flight Director (Touch Control) 01−10−34Radio Transmit Switch 01−10−34

Flight Compartment General Arrangement 01−10−35

Flight Compartment (Aft View) 01−10−36

Pilot’s Side Console 01−10−37

Pilot’s Side Panel 01−10−38

Pilot’s Instrument Panel 01−10−39

Centre Instrument Panels 01−10−40

Overhead Panel 01−10−41

Glareshield 01−10−42

Centre Pedestal 01−10−43

Copilot’s Instrument Panel 01−10−44

Copilot’s Side Panel 01−10−45

Copilot’s Side Console 01−10−46

Airplane Doors 01−10−47

Passenger Door 01−10−47

Passenger Door Schematic 01−10−48

Passenger Door Components 01−10−48Airstair and Handrails Assembly 01−10−48Lift arms 01−10−49“G” Locks 01−10−49Vent Flap 01−10−49Locked Indication 01−10−49

Passenger Door Operating Handles 01−10−50

Passenger Door Switches 01−10−51

External Door Switch Access Panel 01−10−51

Passenger Door Operation 01−10−52External Door Operation 01−10−52

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TABLE OF CONTENTS

Rev 12, Aug 14, 2006Flight Crew Operating Manual

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Page

GENERALInternal Door Operation 01−10−52Manual Closing 01−10−52

Emergency Exit 01−10−53

Aft Equipment Bay Door 01−10−55

Aft Equipment Bay Door Schematic 01−10−55Aft Equipment Bay Door Operation 01−10−56

Baggage Compartment Door 01−10−57Baggage Door Operation 01−10−58Baggage Door Indication 01−10−58

Door Indication and Control 01−10−59STAT Page 01−10−59Passenger Door 01−10−59Emergency Exit 01−10−59Baggage Door 01−10−60Large Maintenance Doors 01−10−60Aft Equipment Bay Door 01−10−60Small Service Doors 01−10−60

EICAS Messages 01−10−61

EMS CIRCUIT PROTECTION

CB − Doors Systems 01−20−1

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TABLE OF CONTENTS

Rev 2A, Apr 11, 2005Flight Crew Operating Manual

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Volume 201−00−4

THIS PAGE INTENTIONALLY LEFT BLANK

ABBREVIATIONS

The following abbreviations may be used by cockpit displays, radio tuning units and flightmanagement system or be found throughout the manual. Some abbreviations may also appear inlower case letters. Abbreviations having very limited usage are explained in the systems chapterswhere they are used.

A

A/C Air ConditioningA/G Air/GroundA/ICE Anti-iceA/P AutopilotA/S AirspeedA/SKID Anti-skidABS AbsoluteAC Alternating CurrentACARS ARINC Communications

Addressing and ReportingSystem

ACSC Air Conditioning SystemController

ACCEL Acceleration, accelerate(d),accelerometers

ACM Air Cycle MachineACMP Alternating Current Motor

Pump/Electric HydraulicPump

ACPC Alternating Current PowerCenter

ACT ActiveACU Air Conditioning UnitACV Air Control ValveADC Air Data ComputerADDR AddressADF Automatic Direction FinderADI Attitude Director IndicatorADS Air Data SystemAFCS Automatic Flight Control

SystemAFT AftwardAGL Above Ground LevelAHC Attitude Heading ComputerAIL AileronALIGN Aligning, alignmentALPHA alphaALT Altitude, Altimeter

ALT Altitude Hold (PFD/FD)ALT CAP Altitude Capture (PFD/FD)ALT HOLD Altitude HoldALTN AlternateALTS Selected Altitude Arm/Abort

(PFD/FD)AM Amplitude ModulationAMB AmbientAMP AmperesANNUN AnnunciatorANT AntennaAOA Angle of AttackAP AutopilotAPC Auxiliary Power ControlAPP, APR ApproachAPPROX ApproximatelyAPU Auxiliary Power UnitARINC Aeronautical Radio

IncorporatedARP Air Data Reference PanelASCB Avionic Standard

Communication BusASYM AsymmetricalAT Auto ThrottleATA Air Transport AssociationATC Air Traffic ControlATS Air Turbine StarterATT AttitudeATTD AttitudeATTND AttendantAUTO AutomaticAUTO BAL Automatic BalanceAUTO XFER Automatic TransferAUX AuxiliaryAV AvionicsAVAIL AvailableAZ Azimuth

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ABBREVIATIONS (CONT'D)

B

B/AIR Bleed AirB/C, BC Back CourseB/CRS Back CourseBCU Brake Control UnitB/LEAK Bleed LeakBARO BarometricBAT BatteryBATT BatteryBDI Bearing Distance IndicatorBIT Built-In-TestBITE Built-In-Test EquipmentBRK Brake

BLD BleedBMC Bleed Management

ControllerBOOM Headset microphoneBRG BearingBRKR(s) Breaker(s)BRT BrightBTL BottleBTMS Brake Temperature

Monitoring SystemBTMU Brake Temperature

Monitoring UnitBYPS Bypass

C

C Center, Caution, CabinCAI Cowl Anti-IceCAA Civil Aviation Authority (UK)CAIMS Central Aircraft Information

Maintenance SystemCAL CalibrateCAP CaptureCAPT CaptainCAS Calibrated Air SpeedCAS Crew Alerting SystemCAT CategoryCAT II Category IICB, C/B Circuit BreakerCBP Circuit Breaker PanelCCBP Cockpit Circuit Breaker PanelCCW Counter ClockwiseCDL Configuration Deviation ListCDP Compressor Discharge

PressureCDU Control Display UnitCFM Cubic Feet Per MinuteCG Center of GravityCH Chapter, ChannelCL CentrelineCHG Change

CHAN ChannelCHGR ChargerCHRT ChartCK CheckCKPT CockpitCKT CircuitCL ClosedCLB ClimbCLK Clockcm CentimetersCMD CommandCMPS CompassCMPTR ComputerCO2 Carbon DioxideCOM CommunicationCOMM CommunicationCOMP Compressor, ComparatorCOMPT CompartmentCOND Condition, ContinuedCONFIG ConfigurationCONN ConnectionCONT Control, Continuous,

Contactor, ControllerCORR Correction

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CPAM Cabin Pressure AcquisitionModule

CPCP Cabin Pressure ControlPanel

CPC Cabin Pressure ControllerCPCS Cabin Pressure Control

SystemCPL CoupleCPLT CopilotCRS Course

CRT Cathode Ray TubeCRZ CruiseCTR CenterCPCS Cabin Pressure Control

SystemCTRL ControlCVR Cockpit Voice RecorderCW ClockwiseCYL Cylinder

D

DA Drift AngleDCT DirectDAU Data Acquisition UnitDBU Data Base UnitDC Direct CurrentDCP Display Control PanelDCPC Direct Current Power CenterDECEL Decelerate(d)DECR DecreaseDEFL DefuelDEG DegreeDEGRAD DegradedDEPR DepressurizeDEPT DepartureDEST DestinationDET DetectorDEV DeviationDFDAU Digital Flight Data Acquisition

Unit

DFDR Digital Flight Data RecorderDG Directional GyroDH Decision HeightDIFF DifferentialDIM DimmingDIR DirectDIS Distance (to way point),

DisconnectDISC DisconnectDISCH DischargeDISP Dispatch, DisplayDIST DistanceDME Distance Measuring

EquipmentDN DownDOT Department of Transport

(Canada)DR DoorDSPY Display

E

EAS Equivalent AirspeedECP EICAS Control PanelECS Environmental Control

SystemECU Electronic Control UnitED EICAS DisplayEEC Engine Electronic Controller

EDP Engine Driven Pump/EnginePrimary Hydraulic Pump

EFIS Electronic Flight InstrumentSystem

EGPWS Enhanced Ground ProximityWarning System ( includingwindshear)

EGT Exhaust Gas Temperature

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EICAS Engine Indication and CrewAlerting System

EL ElevationELEC ElectricalELEV Elevator, ElevationELT Emergency Locator

TransmitterEMER(G) EmergencyEMS Electrical Management

SystemEMS CDU Electrical Management

System Control Display UnitENG EngineEPC External Power ContactorEPLC External Power Line

ContactorEPCU External Power Control UnitEPGDS External Power Generation

and Distribution System

EPR Engine Pressure RatioEQUIP EquipmentERP Eye Reference Position

(datum)ESS EssentialET Elapsed TimeETA Estimated Time of ArrivalETTC Essential TRU Tie ContactorETOPS Extended Range Twin

Engine OperationEVAC EvacuationEXH ExhaustEXT PWR External PowerEXTIN Extinguish(ed)EVMU Engine Vibration Monitor UnitEVMS Engine Vibration Monitor

System

F

F/CTL Flight ControlsFAA Federal Aviation

Administration (USA)FADEC Full Authority Digital

Electronic ControlFAIL FailureFCC Flight Control ComputerFCU Flight Control UnitFD, F/D Flight DirectorFDAU Flight Data Acquisition UnitFDR Flight Data RecorderFEED FeederFF, F/F Fuel FlowFIDEEX Fire Detection and

Extinguishing SystemFIRE BTL Fire BottleFIREX Fire ExtinguisherFECU Flap Electronic Control Unit

FL Flight LevelFL CH, FLC Flight Level ChangeFLD FieldFLT FlightFLT DIR Flight DirectorFLUOR FluorescentFM Fan MarkerFMS Flight Management SystemFPM Feet Per MinuteFQMC Fuel Quantity Management

ComputerFMQGS Fuel Management Quantity

Gauging SystemFREQ FrequencyFT Feet, FootFW Fire WallFWD ForwardFWC Fault Warning Computer

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G

G (+/−) Receiver GainG/S GlideslopeGA Go-aroundGAL GallonGALY GalleyGCS Ground Clutter SuppressionGCU Generator Control UnitGE General ElectricGEN GeneratorGLC Generator Line ContactorGLD Ground Lift Dumper (ing)GMT Greenwich Mean Time

GND GroundGPM Gallons Per MinuteGPWS Ground Proximity Warning

SystemGR GearG GravityGS,G/S GlideslopeGS Ground SpeedGTC Generator Transfer

ContactorGP Guidance PanelGUIDE GuidanceGW Gross Weight

H

HBMU Heater Current/Brake TempMonitor Unit

HDG HeadingHDG HOLD Heading HoldHDG SEL Heading SelectHEAT HeaterHF High Frequency (3 − 30

MHz)Hg MercuryHI HighHLDR HolderHOR, HORIZ HorizontalHOT Hot Oil Temperature

HP High PressureHPSOV High Pressure Shut-off ValveHPA Hecto PascalsHSI Horizontal Situation IndicatorHSTA Horizontal Stabilizer Trim

ActuatorHSTCU Horizontal Stabilizer Trim

Control UnitHTR HeaterHUD Heads-up DisplayHYD HydraulicHz Hertz

I

I/B InboardI/C Intercom, Inspection CheckIAC Integrated Avionics

ComputerIAPS Integrated Avionics

Processor SystemIAS Indicated Air SpeedICAO International Civil Aviation

Organization

ICS Idle Corrected Speed,Inter-Communication System

ID IdentificationIDENT IdentificationIFR Instrument Flight RulesIGN IgnitionIGV Inlet Guide VanesILS Instrument Landing SystemIM ILS Inner Marker

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IMBAL ImbalanceIMC Instrument Meteorological

ConditionsIMP ImperialIN Inch, InchesIN Hg Inches of MercuryINBD InboardINCR IncreaseIND Indication, IndicatorINFLT In FlightINHIB, INHB InhibitINOP InoperativeINPH InterphoneINSP Inspection

INST(S) Instrument(s)INST, INSTR InstrumentINT Internal, Integral, IntersectionINTEG IntegralI/O Input/OutputIRS Inertial Reference SystemIRU Inertial Reference UnitISA International Standard

AtmosphereISO International Standard

OrganizationISOL Isolation, IsolatedITT Inter Turbine TemperatureIOP Input/Output Processor

J

JAA Joint Airworthiness Authority

K

K, KT, KTS Knotskg(s) Kilogram(s)kHz KiloHertz

KIAS Knots Indicated AirspeedkW(s) KiloWatt(s)

L

L Left, LandingL/T Landing/TaxiLAV LavatoryLB(s) Pound(s)LCN Load Classification NumberLCV Load Control ValveLDG LandingLGDCIS Landing Gear and Door

Control Indicating SystemLDG GR Landing GearLDU Lamp Driver UnitLE Leading EdgeLFE Landing Field ElevationLG Landing Gear

LGECU Landing Gear ElectronicControl Unit

LGW Landing Gross WeightLH Left HandLIM LimitLK LeakLN Left NoseLNAV Lateral NavigationLOC LocalizerLOGO Logo GraphicLOM, MM Compass Locator at Outer

MarkerLOP Low Oil PressureLP Low PressureLPM Liter Per Minute

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LPT Lo Pressure TurbineLR Left RearLRC Long Range CruiseLRN Long Range NavigationLSB Lower Side Band

LTG(s) Light(s)LW Left WingLWD Left Wing DownLWR Lower

M

M Mach Numberm MeterMAA Maximum Authorized IFR

AltitudeMAC Mean Aerodynamic ChordMADC Micro Air Data ComputerMAG MagneticMAINT MaintenanceMALF MalfunctionMAN ManualMAP Ground Map (WXR)MAX MaximumMAZ MLS AzimuthMB MillibarsMCA Minimum Crossing AltitudeMCL Maximum ClimbMCR Maximum CruiseMCT Maximum Continuous ThrustMDA Minimum Descent AltitudeMEA Minimum Enroute IFR

AltitudeMECH MechanicMED MediumMEL Minimum Equipment ListMFD Multi-function DisplayMGP MLS GlideslopeMHz MegaHertz

MI MilesMIC MicrophoneMID AFT Middle AftwardMID FWD Middle ForwardMILS .001 of an inchMIN MinimumMISC MiscellaneousMKR MarkerMLG Main Landing GearMLS Microwave Landing SystemMLW Maximum Landing WeightMM Middle MarkerMMEL Master Minimum Equipment

ListMMO Maximum Operating Speed

in Mach NumberMOCA Minimum Obstruction

Clearance AltitudeMOD ModuleMON MonitorMPH Miles Per HourMRA Minimum Reception AltitudeMSG MessageMSL Mean Sea LevelMTG Miles to GoMTO/MTOW Maximum Take-off WeightMTW Maximum Taxi WeightMZFW Maximum Zero Fuel Weight

Misc

% Percent& and

° C Degrees Centigrade° F Degrees Fahrenheit

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N

N/A Not ApplicableN2 High Pressure Rotor RPMNAV NavigationND Nose Down, Navigation

DisplayNDB (ADF) Nondirectional Beacon

(Automatic Direction Finder)NEG NegativeNEUT Neutral

NL Nose LeftNLG Nose Landing GearNM Nautical Mile(s)No. NumberNOPT No Procedure Turn RequiredNORM NormalNOSE, N/W Nose WheelNR Nose RightNU Nose Up

O

OAT Outside Air TemperatureOB/OUTBD OutboardOBS ObserverOEI One Engine InoperativeOEW Operating Empty WeightOH, OVHD OverheadOK OkayOM Outer Marker

OVBD OverboardOVHT, OH OverheatOVLD OverloadOVSP OverspeedOVSPD OverspeedOVTEMP Over TemperatureOXY, O2 Oxygen

P

P#6 Panel 6P/S Pitot/StaticPA Passenger AddressPASS PassengerPBE Portable Breathing

Equipment (Smoke Hood)PCU Power Control UnitPFD Primary Flight DisplayPLA Power Lever AnglePLT(s) Pilot(s)PNLS(s) Panel(s)PO Outside Air PressurePOS PositionPPH Pounds Per HourPRESS Pressure, Pressurization

PRI/PRIM PrimaryPROC ProcedurePROT ProtectionPROX ProximityPRV Bleed Pressure Regulating

and Shut-off ValvePSI Pounds Per Square InchPSID Pounds Per Square Inch

DifferentialPSIG Pounds Per Square Inch

GaugePSU Passenger Service UnitPTCT ProtectPTT Push To TalkPWR Power

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Q

QAR Quick Access RecorderQEC Quick Engine ChangeQFE Local Station Pressure

QNH Altimeter SettingQTY Quantity

R

R RightRA Radio AltitudeRA Resolution Advisory (TCAS)RAT Ram Air TurbineRAT GEN Ram Air Turbine GeneratorRATLC Ram Air Turbine Line

ContactorRADALT Radio AltimeterRCCB Remote Controlled Circuit

BreakerRCDR RecorderRCVR ReceiverR/D Refuel/DefuelRDCP Refuel/Defuel Control PanelRDR RadarREC Receiver, RecorderRECIRC RecirculationRECOG RecognitionREF(s) Reference(s)

REFL RefuelREV ReverseRH Right HandRMI Radio Magnetic IndicatorRMU Radio Management UnitROT RotationRPM Revolutions Per MinuteRSB Radio System BusRT, R/T Receiver-TransmitterRTE RouteRTE DATA Route DataRTO Rejected Take-offRTU Radio Tuning UnitRUD RudderRVR Runway Visual RangeRVSR ReverserRW Right WingRWD Right Wing DownRWY Runway

S

S StatusSAT Static Air TemperatureSBY, STBY StandbySCAV ScavengeSCV Surge Control ValveSCR Selector (Nav source)SEC Second, SecondarySEL Select, SelectorSELCAL Selected CallSENS Sensitivity, SensorSERV, SVCE ServiceSFCU Slats and Flaps Control Unit

SID Standard InstrumentDeparture

SMKG SmokingSOV Shut-off ValveSP, SPD SpeedSPC Stall Protection ComputerSPS Stall Protection SystemSPKR SpeakerSPLR(s) Spoiler(s)SQ SquelchSSB Single Side BandSTA Station

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STAB StabilizerSTAT StatusSTEER SteeringSUPPL SupplySW(s) Switches

SYN SynchronizeSYNC SynchronousSYS, SYST SystemSTD Standard

T

TA Traffic Advisory (TCAS)TACAN UHF Tactical Air Navigation

AidTAS True AirspeedTAT Total Air TemperatureTCAS Traffic Alert and Collision

Avoidance SystemTCS Touch Control SteeringT/C Top of ClimbT/D Top of DescentTE Trailing EdgeTEMP TemperatureTGT Turbine Gas Temperature or

Target

TLC TRU Line ContactorTMS Thermal Management

SystemTO, T/O Take-offTOL ToleranceT/R Thrust ReverserTRB, TURB TurbulenceTRK TrackTRM TrimTRU Transformer Rectifier UnitTST TestTTC TRU Transfer Contactor

U

UNSCHD UnscheduledUSB Upper Side Band

USG United States GallonsUTIL Utility

V

V VoltVA Design Maneuvering SpeedVB Design Speed for Maximum

Gust IntensityVC Design Cruising SpeedVD Design Diving SpeedVDF/MDF Demonstrated flight diving

speedVEF Engine Failure SpeedVF Design Flap SpeedVFC/MFC Maximum Speed for Stability

Characteristics

VFE Maximum Flap ExtendedSpeed

VLE Maximum Landing GearExtended Speed

VLO Maximum Landing GearOperating Speed

VLOF Lift-off SpeedVMC Minimum Control Speed with

the Critical EngineInoperative

VMO/MMO Maximum Operating LimitSpeed

VMU Minimum Unstick SpeedVR Rotation Speed

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VS Stalling Speed or theMinimum Steady FlightSpeed at which the Airplaneis Controllable

VS0 Stalling Speed or theMinimum Steady FlightSpeed in the LandingConfiguration

VS1 Stalling Speed or theMinimum Steady FlightSpeed Obtained in a SpecificConfiguration

V1 Take-off Decision Speed(formerly Denoted as CriticalEngine Failure Speed)

V2 Take-off Safety SpeedV2 MIN Minimum Take-off Safety

SpeedV/S, VS Vertical SpeedVERT VerticalVF Variable Frequency

VFG Variable FrequencyGenerator

VFR Visual Flight RulesVG Vertical GyroVHF Very High Frequency

(30 − 300 MHz)VIB VibrationVIGB Variable Inlet Guide VanesVMC Visual Meteorological

ConditionsVNAV Vertical NavigationVOL VolumeVOLT VoltageVOR VHF Omnidirectional Range

StationVORTAC VOR and TACAN

Co−locatedV/L VOR/LocalizerVSI Vertical Speed Indicator

W

WAIV Wing Anti-Ice modulating andShut-off Valve

WAI Wing Anti-IceW WarningW/C Wind ComponentW/S Wind ShearW/W Wheel WellWARN WarningWF Runway Length Limited

WeightWf Fuel Flow In Pounds Per

HourWGT Weight

WHLS WheelsWIND WindowWOW Weight-On-WheelWPT(s) Waypoint(s)WRN WarningWS Second Segment Limited

WeightWTC Windshield Temperature

ControlWSHLD WindshieldWX WeatherWXR Weather Radar

X

X Cross TransferXFEED CrossfeedXFER, XFR TransferXFLOW Cross Flow

XMIT TransmitXPNDR TransponderXTK Cross TrackXWC Cross Wind Component

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Y

YD, Y/D Yaw Damper

Z

ZFW Zero Fuel Weight

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CONVERSION FACTORS

Multiply By To Obtain

Centimeters 0.3937 in

Centimeters² 0.155 in²

Centimeters³ 0.061 in³

Cu ft³ 0.0283 meters³

Ft 0.3048 meters

Ft² 0.0929 m²

Gal, Imperial 1.20094.546

USGliters

Gal, US 3.78540.8327

litersImperial gal

In 2.54 cm

In² 6.452 cm²

In³ 16.387 cm³

Kilograms 2.205 lb

Kilometers 0.62140.54

milesnautical miles

Km/hr 0.540.6214

knotsmph

Knots 1.1511.852

mphkm/hr

kPa 0.145 psi

Liters 0.26420.22

USGImperial gal

Meters 3.281 ft

Meters² 10.76 ft²

Meters³ 35.3115 ft³

Miles 52801.6090.869

ftkmnautical miles

Mph 1.6090.869

km/hrknots

Nautical Miles 1.1511.852

milesm

Pounds (lb) 0.4536 kilograms

PSI 6.895 kPa

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TEMPERATURE CONVERSION TABLE

°C °F °C °F °C °F °C °F °C °F °C °F °C °F °C °F °C °F °C °F °C °F °C °F−73.3−72.8−72.2−71.7−71.1

−100−99−98−97−96

−148.0−146.2−144.4−142.6−140.8

−45.6−45.0−44.4−43.9−43.3

−50−49−48−47−46

−58.0−56.2−54.4−52.6−50.8

−17.8−17.2−16.7−16.1−15.6

01234

32.033.835.637.439.2

10.010.611.111.712.2

5051525354

122.0123.8125.6127.4129.2

37.838.338.939.440.0

100101102103104

212.0213.8215.6217.4219.2

65.666.166.767.267.8

150151152153154

302.0303.8305.6307.4309.2

−70.6−70.0−69.4−68.9−68.3

−95−94−93−92−91

−139.0−137.2−135.4−133.6−131.8

−42.8−42.2−41.7−41.1−40.6

−45−44−43−42−41

−49.0−47.2−45.4−43.6−41.8

−15.0−14.4−13.9−13.3−12.8

56789

41.042.844.646.448.2

12.813.313.914.415.0

5556575859

131.0132.8134.6136.4138.2

40.641.141.742.242.8

105106107108109

221.0222.8224.6226.4228.2

68.368.969.470.070.6

155156157158159

311.0312.8314.6316.4318.2

−67.8−67.2−66.7−66.1−65.6

−90−89−88−87−86

−130.0−128.2−126.4−124.6−122.8

−40.0−39.4−38.9−38.3−37.8

−40−39−38−38−36

−40.0−38.2−36.4−34.6−32.8

−12.2−11.7−11.1−10.6−10.0

1011121314

50.051.853.655.457.2

15.616.116.717.217.8

6061626364

140.0141.8143.6145.4147.2

43.343.944.445.045.6

110111112113114

230.0231.8233.6235.4237.2

71.171.772.272.873.3

160161162163164

320.0321.8323.6325.4327.2

−65.0−64.4−63.9−63.3−62.8

−85−84−83−82−81

−121.0−119.2−117.4−115.6−113.8

−37.2−36.7−36.1−35.6−35.0

−35−34−33−32−31

−31.0−29.0−27.4−25.6−23.8

−9.4−8.9−8.3−7.8−7.2

1516171819

59.060.862.664.466.2

18.318.919.420.020.6

6566676869

149.0150.8152.6154.4156.2

46.146.747.247.848.3

115116117118119

239.0240.8242.6244.4246.2

73.974.475.075.676.1

165166167168169

329.0330.8332.6334.4336.2

−62.2−61.7−61.1−60.6−60.0

−80−79−78−77−76

−112.0−110.2−108.4−106.6−104.8

−34.4−33.9−33.3−32.8−32.2

−30−29−28−27−26

−22.0−20.2−18.4−16.6−14.8

−6.7−6.1−5.6−5.0−4.4

2021222324

68.069.871.673.475.2

21.121.722.222.823.3

7071727374

158.0159.8161.6163.4165.2

48.949.450.050.651.1

120121122123124

248.0249.8251.6253.4255.2

76.177.277.878.378.9

170171172173174

338.0339.8341.6343.4345.2

−59.4−58.9−58.3−57.8−57.2

−75−74−73−72−71

−103.0−101.2−99.4−97.6−95.8

−31.7−31.1−30.6−30.0−29.4

−25−24−23−22−21

−13.0−11.2−9.4−7.6−5.8

−3.9−3.3−2.8−2.2−1.7

2526272829

77.078.880.682.484.2

23.924.425.025.626.1

7576777879

167.0168.8170.6172.4174.2

51.752.252.853.353.9

125126127128129

257.0258.8260.6262.4264.2

79.480.080.681.181.7

175176177178179

347.0348.8350.6352.4354.2

−56.7−56.1−55.6−55.0−54.4

−70−69−68−67−66

−90.0−92.2−90.4−88.6−86.8

−28.9−28.3−27.8−27.2−26.7

−20−19−18−17−16

−4.0−2.2−0.41.43.2

−1.1−0.60.00.61.1

3031323334

86.087.889.691.493.2

26.727.227.828.328.9

8081828384

176.0177.8179.6181.4183.2

54.455.055.656.156.7

130131132133134

266.0267.8269.6271.4273.2

82.282.883.383.984.4

180181182183184

356.0357.8359.6361.4363.2

−53.9−53.3−52.8−52.2−51.7

−65−64−63−62−61

−85.0−83.2−81.4−79.6−77.8

−26.1−25.6−25.0−24.4−23.9

−15−14−13−12−11

5.06.88.6

10.412.2

1.72.22.83.33.9

3536373839

95.096.898.6

100.4102.2

29.430.030.631.131.7

8586878889

185.0186.8188.6190.4192.2

57.257.858.358.959.4

135136137138139

275.0276.8278.6280.4282.2

85.085.686.186.787.2

185186187188189

365.0366.8368.6370.4372.2

−51.1−50.6−50.0−49.4−48.9

−60−59−58−57−56

−76.0−74.2−72.4−70.6−68.8

−23.3−22.8−22.2−21.7−21.1

−10−9−8−7−6

14.015.817.619.421.2

4.45.05.66.16.7

4041424344

104.0105.8107.6109.4111.2

32.232.833.333.934.4

9091929394

194.0195.8197.6199.4201.2

60.060.661.161.762.2

140141142143144

284.0285.8287.6289.4291.2

87.888.388.989.490.0

190191192193194

374.0375.8377.6379.4381.2

−48.3−47.8−47.2−46.7−46.1

−55−54−53−52−51

−67.0−65.2−63.4−61.6−59.8

−20.6−20.0−19.4−18.9−18.3

−5−4−3−2−1

23.024.826.628.430.2

7.27.88.38.99.4

4546474849

113.0114.8116.6118.4120.2

35.035.636.136.737.2

9596979899

203.0204.8206.6208.4210.2

72.863.363.964.465.0

145146147148149

293.0294.8296.6298.4300.2

90.691.191.792.292.8

195196197198199

383.0384.8386.6388.4390.2 G

F01

10_0

47

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−14

GENERAL AIRPLANE DESCRIPTION

The airplane is a swept-wing monoplane with a pressurized cabin. It is capable of accommodating apilot, a copilot, a third crew member and up to 19 passengers. The airplane has two BMW/RollsRoyce BR 710 turbofan engines.

The airplane structure, in general, is fabricated from aluminum alloys. Alloy steels, stainless steels,titanium and composites are also used.

FG

F01

10_0

01aLEGEND

Kevlar

Graphite

Hybrid (Mainly Graphite)

Glass

Strict attention is given to surface finishes, protection against corrosion and to external surfacesmoothness throughout the airplane. Sealing requirements include environmental sealing, protectionof faying surfaces (similar and dissimilar) against corrosion, pressure sealing and integral fuel tanksealing.

At sea level, the airplane and its installed equipment is certificated for operation in ambienttemperatures ranging between −30°C (−22°F) and + 50°C (122°F). The airplane pressurizationsystem is certified for operations up to a maximum pressure altitude of 51,000 feet.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−15

AIRPLANE DIMENSION SCHEMATIC

FG

F01

10_0

02

(3.07 m)

94 ft 0 in(28.65 m)

13 ft 4 in(4.06 m)

8 ft 10 in(2.70 m)

42 ft 7 in(12.98 m)

25 ft 6 in(7.77 m)

96 ft 9 in(29.49 m)

83 ft 9 in(25.53 m)

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−16

DIMENSIONS AND GENERAL DATA

The data that follows is for general information only and is not to be used for inspection or rejectionpurposes. When specific data is required, the applicable illustration should be used.

Overall dimension

Length 96 ft. 9 in. (29.49 m)

Height 25 ft. 6 in. (7.77 m)

Wing

Span 93 ft. 6 in. (28.5 m)

Root chord (BL 47.61) 21 ft. 1 in. (6.43 m)

Tip chord (W/STA 544) 4 ft. 1 in. (1.24 m)

Dihedral of Wing Ref. Plane 2.5°

Spar locations

Front 14.0%

Rear 67.0%

Flaps 3 per sideSingle Slotted Fowler Flaps

Slats 4 L.E. segments per side

Ground spoilers 2 per side

Multi-function spoilers 4 per side

Horizontal tail surface

Span 31 ft. 9 in. (9.68 m)

Root chord 10 ft. 5 in. (3.18 m)

Tip chord 5 ft. (1.52 m)

Anhedral 5.0°

Vertical tail surface

Span 13 ft. 8 in. (4.17 m)

Root chord 16 ft. 7 in. (5.05 m)

Tip chord 10 ft. 7 in. (3.22 m)

Fuselage

Diameter 8 ft. 10 in. (2.69 m)

Length 83 ft. 9 in. (23.53 m)

Landing gear

Main gear Nose gear

Wheel size 19 in. 10 in.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−17

DIMENSIONS AND GENERAL DATA (CONT'D)Landing gear (Cont’d)

Tire size 38 in. 21 in.

Max loaded tire pressure 172 psi. 154 psi

Main gear track 13 ft. 8 in.(4.18 m)

Nose gear track 13.14 in.(33.4 cm)

Wheel base (max.) 40 ft. 2 in.(12.25 m)

Areas

Equivalent wing area (including ailerons,flaps spoilers and area within the fuselage)

1022 sq. ft. (94.95 sq. m)

Horizontal tail area (Gross) 245 sq. ft. (22.76 sq. m)

Vertical tail area (Gross) 186 sq. ft. (17.28 sq. m)

Doors

Passenger door (LH. fwd)

Height to sill (one step below the floor line) 6 ft. 2 in. (188 m)

Width 3 ft. (0.91 m)

Height to sill (at floor line) 5 ft. 4 in. (163 m)

Baggage compartment door (LH, aft)

Height 2 ft. 9 in. (0.84 m)

Width 3 ft. 7 in. (1.09 m)

Height to sill (floor line) 6 ft. 7 in. (2.01 m)

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−18

ANTENNA LOCATION SCHEMATIC

TCAS(Directional)

MODE

MODES 1

S 2

DME#1

DME#2

MARKERBEACON

TCASOMNI

VHF COMM #2

MODE S1 & 2

VHF COMM #1

GPS #1ADF #1

ADF #2

ELT

VOR/LOC

RAD ALTRAD ALT

RAD ALT

RAD ALT

#1 TX#2 TX

#1 RX

#2 RX

HF

(LH AND RH)(If installed)

FG

F01

10_0

03

VHF COMM #3SATCOM

WARNING

Personnel should not stand nearby and in front of the radar antennawhen it is transmitting. When the antenna is not scanning, the dangerincreases.

GLIDESLOPE

WEATHER RADAR

RADAR 5 mW/cm

PERSONNEL DANGER AREA

366 cm (12 ft.) Refer to Pilot’s Manual Pub. No. A28−1146−056−02 G

F01

10_0

04

2

AIRPLANE GENERAL

Rev 3, Apr 25, 2005 Flight Crew Operating Manual

CSP 700−5000−6

Volume 201−10−19

VISUAL EYE REFERENCES FOR GROUND OPERATION

FG

F01

10_0

04

AIRPLANE GENERAL

Rev 3, Apr 25, 2005Flight Crew Operating Manual

CSP 700−5000−6

Volume 201−10−20

STEERING RADII

Steering radii are shown below.

STEERING RADII SCHEMATIC

FG

F01

10_0

05

NOTEMaximum steering

Symmetrical and idle thrustNo differential braking75° steering angle3° slipDry runwaySlow continuous turnMax A/C weightAFT CG.

40 ft 4 in(12.30 m)

56 ft 6 in(17.24 m)

128 ft 2 in(39.07 m)

14 ft 0 in(4.26 m)

65 ft 4 in(19.92 m)

52 ft 5 in(15.97 m)

44 ft 9 in(13.64 m)

20 ft 8 in(4.23 m)

7 ft 4 in(2.3 m)

MINIMUMPAVEMENTWIDTH180° TURN

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−21

TURNING RADII

Minimum paving width for 180° turn − 65 ft. (19.92 m)

TURNING RADII SCHEMATIC

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−22

JET EXHAUST SINGLE ENGINE GROUND IDLE THRUST

GF

0110

_008

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−23

JET EXHAUST SINGLE ENGINE TAKE-OFF THRUST

GF

0110

_009

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−24

JET EXHAUST TWO ENGINE GROUND IDLE THRUST

GF

0110

_010

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−25

JET EXHAUST TWO ENGINE TAKE-OFF THRUST

GF

0110

_011

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−26

AIRPLANE JACKING

Three jacking points are provided, one on the forward fuselage and one on each wing rear spar forjacking the complete airplane.

JACKING POINTS SCHEMATIC

TYPICAL JACK

JACK

REAR FUSELAGE SUPPORT

NYLON PLUG JACK PAD

JACKING POINT

SUPPORT BEAM

REAR FUSELAGE SUPPORT

LEGEND

GF

0110

_012

The nose jacking point is located on the fuselage centerline. Gear jacking points are also provided fortire/wheel/brake changes. Jacking procedures are located in the Aircraft Maintenance Manual(Chapter 07).

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−27

TOWING

A fitting for towing or pushing the airplane is located on the nose landing gear.

During towing, nose wheel swivel through the range of ±75° each side of center is possible, withoutdisconnecting the nose wheel steering torque links. The Aircraft Maintenance Manual (Chapter 09)has a detailed description of towing operations.

NOTE

Disconnecting the nose wheel steering torque links is recommended forall towing operations.

TOW BAR ATTACHMENT SCHEMATIC

TOW BAR ASSEMBLY

GF

0110

_013

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−28

TOWBARLESS SCHEMATIC

FG

F01

10_0

13

WINCH STRAP

TOW VEHICLE

WINCH CUT−OFFSWITCH PLATE

STRUT−STRAP

NOSE LANDINGGEAR

TOWBARLESS

REAR GATE CRADLE

Ground Locking Safety Pins

Ground safety locks are provided for the nose and each main gear, gear doors and for the Ram AirTurbine (RAT). Refer to the applicable chapter for the safety pin installations.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−29

MOORING

Fittings are provided on the fuselage and on the wing jacking points for mooring the airplane.Mooring procedures are located in the Aircraft Maintenance Manual (Chapter 10).

MOORING ATTACHMENT POINTS SCHEMATIC

MAIN AND NOSE AREAS

TAIL AREA

MOORING ADAPTER PLATE

JACKING PAD

TIE DOWN RING

GF

0110

_014

30.25° 30.25°

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−30

SEAT ASSEMBLY

The crew seats provide adjustments fore and aft, inboard/outboard lateral adjustment (“J” track),height and armrest position.

GF

0110

_015

a

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−31

SEAT ASSEMBLY (CONT'D)Seat Egression

Make sure the seat is in the fully upright position, then pull on the fore/aft lever and move the seatto its fully aft position.

NOTE

The lateral tracking is now automatically enabled.

CAUTION

Do not try to move the seat laterally with the fore/aft lever in the upposition. This could cause damage to the mechanism.

Release the fore/aft lever.

Move the seat to its fully outboard position to facilitate egress from the seat.

Moving the Seat Forward

CAUTION

If the seat is moved forward when it is not in its fully inboard position,it can jam.

After getting back onto the seat, before touching the fore/aft lever, move the seat laterally to itsfully inboard position.

NOTE

There is no mechanical lock to keep the seat in its position until youmove it forward.

Keeping the seat in its fully inboard position, raise the fore/aft lever to move the seat forward. Theseat must be moved forward at least one inch (2.54 cm) before the lateral tracking latch isautomatically locked. Release the lever when the desired forward position is reached.

NOTE

When the seat moves forward, the lateral tracking mechanism isdisabled, and the seat should not move laterally.

CAUTION

If the seat jams or moves laterally when it is not in its fully aftposition, do not attempt to reset it using force, as damage to themechanism may occur. Call a maintenance technician fortroubleshooting and repair.

AIRPLANE GENERAL

Rev 13, NOV 10, 2006Flight Crew Operating Manual

CSP 700−5000−6

Volume 201−10−32

EYE LOCATOR-SEAT ADJUSTMENT

An eye locator is mounted on the centre windshield post to enable seat adjustment for correcteye-to-wheel height.

FRONT VIEWTOP VIEW

The support bracket is not shown.

GF

0110

_016

PILOT’S

SIGHT LI

NE COPILOT’S

SIGHT LINE

NOTE

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−33

CONTROL WHEEL

The pilot and copilot control wheels contain the following switches:

• Master disconnect.• Pitch Trim Switch.• Autopilot/Flight Director Touch Control.• Radio Key.

Master Disconnect

The Master Disconnect switch disengages the autopilot, deactivates the stick pusher and the pitchtrim. When released, the stick pusher and the pitch trim system are immediately reactivated butthe autopilot remains disengaged.

Pitch Trim Switch

The Pitch Trim Switch enables the pilot/copilot to control the trim from each control wheel.

Autopilot/Flight Director (Touch Control)

The Touch Control Switch (TCS) is located on the control wheel. It enables the pilot to maneuverthe airplane without disconnecting the autopilot control.

Radio Transmit Switch

The Radio Transmit Switch activates the selected radio transmitter or the interphone.

FG

F01

10_0

12

32

1

1. Master Disconnect2. Pitch Trim Switch3. Autopilot/Flight Director Touch Control4. Radio Transmit Switch

Indicates Chapter in which information on item may be found.

4

10

6

4

4

(radio transmitswitch locatedbehind)

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−34

FLIGHT COMPARTMENT GENERAL ARRANGEMENT

GF

0110

_018

1. Flight Bag Storage2. Pilot’s Side Console3. Pilot’s Side Panel 4. Pilot’s Instrument Panel5. EICAS Display6. Glareshield7. Overhead Panel

8. Standby Instruments9. Systems Display10. Copilot’s Instrument Panel 11. Copilot’s Side Panel12. Copilot’s Side Console13. Control Wheel14. Pedestal


8 15 17

7 10 11

11 17

10

3

3 4

2 3 5 7 9

12 13 14 16 18

7

11

32 10 12 13 18

11 17

7 10 11

8 15 176

6 104

3 6 7

15 16 17 18

10 11

1

2

3

4

5

6

7

89

10

11

12

1313

14

COM1 NAV1

ATC/TCAS ADF1

TCAS DSPY 1 HF1

NB

MEMORY−1

STANDBY

ALT:

118.00

131.27TEMP−1

131.10

112.00

1605ANT

620.0

REL

NORMAL 2000

15423LV

COM1 NAV1

ATC/TCAS ADF1

TCAS DSPY 1 HF1

NB

MEMORY−1

STANDBY

ALT:

118.00

131.27TEMP−1

131.10

112.00

1605ANT

620.0

REL

NORMAL 2000

15423LV

TUNE TUNE

TRIMS

L

AIL RUD

NL NR

WD

RWD

STABCH1 CH2

PUSH OFF/RESET

OFFOFF

PUSH TO RESET

LAV CALL CABIN CALL CREW AREA PA

ON

CABINCALL

FWD AFT

LAVCALL

FWD AFT

IRS1 IRS2 IRS3

PARK/EMERBRAKE

PARK/EMERBRAKE

EICAS

SCROLL SYSTEM SELECT

IDLE

REV

MAX REV

MAXTHRUST

ENGINERUNL R

OFF OFF

FLIGHTSPOILER

MAX

FULL

1/2

ENGINE

LN1

EPR

RN1

EPR

GND LIFTDUMPING

AUTO BRAKE

NOSE STEER LDG GEAR

HORN PILOTEVENT

EGPWS

OFFOVRDMUTED

INTEGRALCOCKPIT LIGHTS

DIM BRTL

DIM BRTCTR

DIM BRTR

DIM BRTCB

DIM BRTOVHD

ON

AUTO

OFFMASTER

BRT

DIM

OFFAREA

ON

OFFEYE REF

DIM

BRTPBA

ON

OFFFLOOR

FLOODCOCKPIT LIGHTS

OFF BRTL CTR R

OFF BRT OFF BRT

DISPLAY

DIM BRTL CTR R

DIM BRT DIM BRT

NORMALTN

PFD1

NORMALTN1

EICAS

NORMALTN

PFD2

ALTN2ALTN3

PFD1 PFD2

NORMALTN

SG1

NORMALTN

SG3

NORMALTN

SG2

IRS IRSADC ADC

MASTERWARNING/CAUTION

WARNING

CAUTION

ROLL SPLRS

PLT CONT

ROLLSELPLT

ROLL


WARNING

CAUTION

ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL

RAD BAROMINIMUMS NAV SCR BARO SET

PUSH STD

HPaIN RAD BAROMINIMUMS NAV SCR BARO SET

PUSH STD

HPaINSPD

PUSH CHG

MANFMSCRS 1

PUSH DCT

HDG

PUSH SYNC

DN

UP

ALT CRS 1

PUSH DCT

B C10 10

DISCH

PULL

1 2

DISCH

PULL

1 2

DISCH

PULL

1 2

ELT

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

ARM/RESET

L HYD SOV

HYDRAULIC

CLOSED

L HYD SOV

CLOSED

HYDRAULIC

ELECTRICAL

ONOFF

AUTOON

OFF

ONOFF

AUTO

ONOFF

AUTO

1B 3A 3B 2B

ON

BATT MASTER

OFFEMS

ON ON

AVAIL AVAIL

EXT AC EXT DC

PUSH OFF/RESET

OFF OFF

FAIL FAIL

GEN 3 GEN 4

OFF

FAIL

GEN 2

OFF

FAIL

GEN 1

OFF

FAIL

APU GEN

PUSHOFF/RESET

OFF

FAIL

RAT GEN

ENGINE

APU

RUNOFF START

IGNITION L CRANK L CRANKAUTO

ENG START

AUTOWING XFER

OFF

AUTOAFT XFER

OFF ON

WING FEEDINHIBIT

AUX PUMP

OFF

PRI PUMP

OFF

L RECIRC

OFF

LWING FEED

INHIBIT

AUX PUMP

OFF

PRI PUMP

OFF

R RECIRC

OFF

R

XFEED SOV

FAIL

OPEN

PUSH TO MUTE

IAC 1 IAC 2

AURAL WARNING

MUTEDMUTED

TEMPERATURE

COCKPIT

COLD HOT

FWD CABIN

COLD HOT

AFT CABIN

COLD HOT

OFF OFF ON

RECIRC TRIM AIR RAM AIR

AUX PRESS

ON

HOT

COLD

L MANTEMP

R MANTEMP

HOT

COLD

LO HIGH

PACK CONTROLNORM

MAN

R PACK

OFF

FAIL

L PACK

OFF

FAIL

XBLEEDAUTO

CLSD OPEN

L ENG BLEEDAUTO

OFF ON

R ENG BLEEDAUTO

OFF ON

R ENG BLEEDAUTO

OFF ON

AUTOOFF ON

AUTOOFF ON

AUTOOFF ON

R COWLWINGL COWL

ANTI−ICE

AUTOFROM L FROM R

WING XBLEED

R

WINDSHIELD HEAT

MAN AUTOPRESSURIZATIONAUTO/MAN

MAN

MAN ALT

UP

DN

OUTFLOW VALVE

CLOSED

1

CLOSED

2DITCHING

ON

MAN

FMS

UP

DN

HIGH

NORM

LDG ELEV RATE

DEPRESS

ON

EMER

ONOFF/RESET

LONOFF/

RESET

EXTERNAL LIGHTS

LANDING

NAV BEACON STROBE WING INSP LOGO

WHT

OFFRED

OFFON

OFFON

OFFON

OFFON

L WING NLG R WING TAXI/RECOG/

OFFON

OFFON

OFFON

OFFON

PASS SIGNS EMER LIGHTSNO SMKG SEAT BELTS

OFFAUTO

ON

OFFAUTO

ON

OFFARM

ON

NO SMOKING

CIRCUIT BREAKER − SYSTEM 1/2

AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

BRT

STALLPUSHER

ON

OFF

CHR

ET


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

STALLPUSHER

ON

OFF

CHR

ET

STSGSTK

SYSTEM SELECT

FROM TO WPT

ON

OXYGEN MASK

RESET

TEST

NPUSH100%

COCKPIT VOICE RECORDER MICROPHONE MONITOR

TESTERASE

STATUS HEADPHONE

PASSENGER OXYGEN

CLOSED OVERRIDE

NORMAL

FIRST AID

TEST PORT

PASS ONOFF

FAULT

LOWPPR

OP

EN

PU

SH

PU

SH

TO

CLO

SE

OP

EN

PU

SH

OXYGEN MASK

RESET

TEST

NPUSH100%

SYSTEMSEICASMFDPFD MFD PFD

STBY

STBY

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−35

FLIGHT COMPARTMENT (AFT VIEW)

FG

F01

10_0

07


2

5

3

4

7

6

280 BULKHEADFWD FACERH SIDE

280 BULKHEADFWD FACELH SIDE

1. Refuel/Defuel Panel2. Oil Replenishment Panel3. Circuit Breaker Panel4. Halon Fire Extinguisher

5. Data Upload/Download Panel6. Portable Breathing Equipment7. Crash Axe

12

18

7

8

8

8

6

OIL REPLENISHMENTPOWER

RESERVOIR LH ENG APU RH ENG

SYSTEMON

TANKLO

PUMPON

LOOILVLV

OPEN

LOOILVLV

OPEN

LOOILVLV

OPEN

PRINT MAINTREPORT

DATAUPLOAD/DOWNLOAD

DAU 1ADAU 1B

DAU 2ADAU 2B

DAU 3A

DAU 3B

DAU 4A

DAU 4BIRS 1

IRS 2IRS 3

WX

SPARE

IAC 1IAC 2

IAC 3GPWS

SATCOM SDU

CABIN COMM

GPS 1GPS 2

ADC 1ADC 2

ADC 3

REFUEL/DEFUEL PANEL

LEFT CENTER RIGHT

PRESELTOTAL

MANUAL

LEFT CTR RIGHT

OPEN

CLOSE

INCR

DECR

PRESEL

START

STOP/SOVTEST

REFUEL

DEFUEL

AUTOOFF

MANUAL

REFUEL

1

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−36

PILOT'S SIDE CONSOLE

GF

0110

_020

1. Oxygen Mask/Regulator2. Headset Panel3. Navigation Display Unit4. Nosewheel Steering Handwheel

4

3

1

2

HEADSET PANEL

FLASHLIGHT

FLASHLIGHT


8

6

17

15

STSGSTK

SYSTEM SELECT

FROM TO WPT

ON

OXYGEN MASK

RESET

TEST

NPUSH100%

MICHEADSET

HDPH

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−37

PILOT'S SIDE PANEL

FG

F01

10_0

08


1. Electrical Management System2. Stall Pusher Switch3. Clock4. Air Conditioning Gasper

7

10

2

11

1

23

4


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

BRT

STALLPUSHER

ON

OFF

SEL

DT GPS INT LT

ETCHR

MODE

ET

RST

CHR

M

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−38

PILOT'S INSTRUMENT PANEL

FG

F01

10_0

14

TOC3

KSRP

KPHX

WX SAT

GSPD

−56TATTAS

−40234345

LX

HDG330

ETE 1+36

KLAX

KPHXTOC

KSRPKDVT

4000 4000

FL180

12.5 NMKDVT

LUF

KDVT

5

N

5

360

TERROFF

30

6

33


1. Airspeed Placard2. Primary Flight Display3. Multi−Functional Display

MAP ModePLAN FormatWX RadarTCAS Traffic

CREW LIFE VESTUNDER SEAT

11 17

11 17

2 3

1

2020

1010

1010

2020

VALTLNAV AP1VNAVVAPP

29.92 IN600 RAD

AIRSPEED LIMITS − (INDICATED SPEEDS)

VFE (SLATS OUT, 0° FLAPS).............. 225VFE (SLATS OUT, 6° FLAPS).............. 210VFE (SLATS OUT, 16° FLAPS)............ 210VFE (SLATS OUT, 30° FLAPS)............ 185VA (MANEUVERING)(AT SEA LEVEL AT 87,700 LB)............ 240(AT 20,000 FT AT 78,600 LB)............... 250

VMO (BELOW 8,000 FT)...................... 300VMO (8,000 TO 30,267 FT).................. 340MMO (30,267 FT TO 35,000 FT).......... 0.89

MMO (AT 47,000 FT).......................... 0.858MMO (AT 51,000 FT).......................... 0.842VLO (EXT) (L/G EXTENSION)...............200VLO (RET) (L/G RETRACTION)............200VLE (L/G EXTENDED)...........................250

MMO (AT 41,400 FT)............................ 0.88





MMO (AT 41,400 FT)............................ 0.88

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−39

CENTRE INSTRUMENT PANELS

FG

F01

10_0

09

102030

302010

01

2

3

4

7

9

65 29 9 210 13

ALT

1 0 1 30

001 FEET

mb/hPa in Hg

180 200

IAS KNOTS

BARO

Standby AttitudeIndicator

Engine Indication and Crew AlertingSystem (EICAS) Primary Display

EICAS Sytem DisplayStandby Altimeter/Airspeed Indicator


Engine InstrumentsCaution and Warning AnnunciatorFuel QuantityFlap/Slat and Spoiler StatusLanding Gear StatusFlight Control Trims

Bleed SystemAnti−Ice SystemElectrical System (AC and DC)Fuel SystemFlight ControlsHydraulics

Airplane Status Information andthe following synoptic pages:

11

11

18

3

12

10

15

10

2

2

7

12

10

13

OIL QTY (QTS)ENGAPURES

RPM EGT

BRAKE TEMP

10.4

90

13% 13%

400100

0303 03 03

4.55.0

10.4

OXYGEN

OPEN OPEN

OUTFLOW VALVES00

1 2

1 2

2

APU

%

1

CKPT (°C) AFTCABIN (°C)CABIN (°C)

FWD

20

1300

0.0020

CAB ALT

CAB RATE

P2319 21 22

TOTALFUEL(LBS) 41550

1.541.54

73.373.3

789789

14600 1460010000 NDSTAB

NU

RUDDERNL

LWD RWD

NR

TRIMS

7.2

N2FF (PPH)OIL TEMPOIL PRESS

93.45750 115 81

93.45750 115 81

EPR

N1

ITT

AIL

1.651.65

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−40

OVERHEAD PANEL

GF

0110

_024

1

2

3

4

56

7

8

9

10

12

11

13

161415

1. Electrical Panel2. Hydraulic Panels3. ELT Panel4. Gasper5. Aural Warning Panel6. Fire Discharge Handles7. Bleed/Air Conditioning/Anti−Ice Panel8. Pressurization Panel

9. Windshield Heat Panel10. External Lights Panel11. Passenger Signs/Emergency Lights Panel12. Engine Panel13. Standby Compass14. APU Panel15. Fuel Panel16. CVR Area Microphone

7

13

6

2

3

9

2

2 14 18

14

16

16

18

17

5

12

6


B C10 10

DISCH

PULL

1 2

DISCH

PULL

1 2

DISCH

PULL

1 2

ELT

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

ARM/RESET

L HYD SOV

HYDRAULIC

CLOSED

L HYD SOV

CLOSED

HYDRAULIC

ELECTRICAL

ONOFF

AUTOON

OFF

ONOFF

AUTO

ONOFF

AUTO

1B 3A 3B 2B

ON

BATT MASTER

OFFEMS

ON ON

AVAIL AVAIL

EXT AC EXT DC

PUSH OFF/RESET

OFF OFF

FAIL FAIL

GEN 3 GEN 4

OFF

FAIL

GEN 2

OFF

FAIL

GEN 1

OFF

FAIL

APU GEN

PUSHOFF/RESET

OFF

FAIL

RAT GEN

ENGINE

APU

RUNOFF START

IGNITION L CRANK L CRANKAUTO

ENG START

AUTOWING XFER

OFF

AUTOAFT XFER

OFF ON

WING FEEDINHIBIT

AUX PUMP

OFF

PRI PUMP

OFF

L RECIRC

OFF

LWING FEED

INHIBIT

AUX PUMP

OFF

PRI PUMP

OFF

R RECIRC

OFF

R

XFEED SOV

FAIL

OPEN

PUSH TO MUTE

IAC 1 IAC 2

AURAL WARNING

MUTEDMUTED

TEMPERATURE

COCKPIT

COLD HOT

FWD CABIN

COLD HOT

AFT CABIN

COLD HOT

OFF OFF ON

RECIRC TRIM AIR RAM AIR

AUX PRESS

ON

HOT

COLD

L MANTEMP

R MANTEMP

HOT

COLD

LO HIGH

PACK CONTROLNORM

MAN

R PACK

OFF

FAIL

L PACK

OFF

FAIL

XBLEEDAUTO

CLSD OPEN

L ENG BLEEDAUTO

OFF ON

R ENG BLEEDAUTO

OFF ON

APU BLEEDAUTO

OFF ON

AUTOOFF ON

AUTOOFF ON

AUTOOFF ON

R COWLWINGL COWL

ANTI−ICE

AUTOFROM L FROM R

WING XBLEED

R

WINDSHIELD HEAT

MAN AUTOPRESSURIZATIONAUTO/MAN

MAN

MAN ALT

UP

OUTFLOW VALVE

CLOSED

1

CLOSED

2DITCHING

ON

MAN

FMS

UP HIGH

NORM

LDG ELEV RATE

DEPRESS

ON

EMER

ONOFF/RESET

LONOFF/

RESET

EXTERNAL LIGHTS

LANDING

NAV BEACON STROBE WING INSP LOGO

WHTOFF

REDOFFON

OFFON

OFFON

OFFON

L WING NLG R WING TAXI/RECOG/

OFFON

OFFON

OFFON

OFFON

PASS SIGNS EMER LIGHTSNO SMKG SEAT BELTS

OFFAUTO

ON

OFFAUTO

ON

OFFARM

ON

NO SMOKING

DN DN

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−41

GLARESHIELD

Left Glareshield

Centre Glareshield

Right Glareshield

2

3

FG

F01

10_0

11

4


1. Roll Select Switch2. Primary Flight Display Controller3. Guidance Panel4. Master Warning/Caution Switch

10

11

4

3


WARNING

CAUTION

ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL


PUSH STD

HPaIN


PUSH STD

HPaIN

SPD

PUSH CHG

MANFMSCRS 1

PUSH DCT

HDG

PUSH SYNC

DN

UP

ALT CRS 1

PUSH DCT


ROLL SPLRS

PLT CONT

HUD

BRTDIMOFF

WARNING

CAUTION

ROLLSELPLT

ROLL

1

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−42

CENTRE PEDESTAL

GF

0110

_026

a

1

2

4

5

6

7

8

9

10

3

11

12

14

16

18

19

20

21

22

13

17

15

1. Landing Gear Panel

2. Gnd Lift Dump/Autobrake Panel

3. Engine Control Panel

4. Flight Spoiler Lever

5. Weather Radar Control Panel

6. EICAS Control Panel

7. Parking Brake Handle

8. Flt Control Trim Panel

9. DC Power Emergency Ovrd

10. IRS Mode Selector Panel

11. EGPWS Panel

12. FMS Control Display Panel.

13. Radio Management Unit

14. Thrust Lever Quadrant

15. MFD Control Panel

17. Flap Selector Panel

18. Cockpit Lights − Integral/Misc

19. Cockpit Lights − Flood/Display

20. Reversion Control Panel

21. Landing Gear Manual Release Handle

22. RAT Manual Release Handle

16. Audio Panel


15

15 10

18

10

17

3

15

10

7

17

17

17

6

18

13

6

17

10

16

16

3

15

3

COM1 NAV1

ATC/TCAS ADF1

TCAS DSPY 1 HF1

NB

MEMORY−1

STANDBY

ALT:

118.00

131.27TEMP−1

131.10

112.00

1605ANT

620.0

REL

NORMAL 2000

15423LV

COM1 NAV1

ATC/TCAS ADF1

TCAS DSPY 1 HF1

NB

MEMORY−1

STANDBY

ALT:

118.00

131.27TEMP−1

131.10

112.00

1605ANT

620.0

REL

NORMAL 2000

15423LV

TUNE TUNE

TRIMS

L

AIL RUD

NL NR

WD

RWD

STABCH1 CH2

PUSH OFF/RESET

OFFOFF

IRS1 IRS2 IRS3

PARK/EMERBRAKE

PARK/EMERBRAKE

EICAS

SCROLL SYSTEM SELECT

IDLE

REV

MAX REV

MAXTHRUST

ENGINERUNL R

OFF OFF

FLIGHTSPOILER

MAX

FULL

1/2

ENGINE

LN1

EPR

RN1

EPR

GND LIFTDUMPING

AUTO BRAKE

NOSE STEER LDG GEAR

HORN PILOTEVENT

EGPWS

OFFOVRDMUTED

INTEGRALCOCKPIT LIGHTS

DIM BRTL

DIM BRTCTR

DIM BRTR

DIM BRTCB

DIM BRTOVHD

ON

AUTO

OFFMASTER

BRT

DIM

OFFAREA

ON

OFFEYE REF

DIM

BRTPBA

ON

OFFFLOOR

FLOODCOCKPIT LIGHTS

OFF BRTL CTR R

OFF BRT OFF BRT

DISPLAY

DIM BRTL CTR R

DIM BRT DIM BRT

NORMALTN

PFD1

NORMALTN1

EICAS

NORMALTN

PFD2

ALTN2ALTN3

PFD1 PFD2

NORMALTN

SG1

NORMALTN

SG3

NORMALTN

SG2

IRS IRSADC ADC

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−43

COPILOT'S INSTRUMENT PANEL

FG

F01

10_0

15


1. Airspeed Placard2. Primary Flight Display3. Multi−Functional Display

MAP ModePLAN FormatWX RadarTCAS Traffic

11 17

11 17

TOC3

KSRP

KPHX

WX SAT

GSPD

−56TATTAS

−40234345

LX

HDG330

ETE 1+36

KLAX

KPHXTOC

KSRPKDVT

4000 4000

FL180

12.5 NMKDVT

LUF

KDVT

5

N

5

360

TERROFF

30

6

33

CREW LIFE VESTUNDER SEAT

3 2

1

2020

1010

1010

2020

VALTLNAV AP1VNAVVAPP

29.92 IN600RAD





MMO (AT 41,400 FT)............................ 0.88





MMO (AT 41,400 FT)............................ 0.88

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−44

COPILOT'S SIDE PANEL

FG

F01

10_0

10


1. Electrical Management System2. Stall Pusher Switch3. Clock4. Air Conditioning Gasper

7

10

2

11

1

234


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

STALLPUSHER

ON

OFF

SEL

DT GPS INT LT

ETCHR

MODE

ET

RST

CHR

M

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−45

COPILOT'S SIDE CONSOLE

GF

0110

_029

1. Mach Transducer Source Selector Valve2. Headset Panel3. Oxygen Mask/Regulator4. Passenger Oxygen Selector

FLASHLIGHT


10

6

8

8

6

4

5

2

1

5. Cockpit Voice Recorder6. Cockpit Printer (If installed)

6

6

3

COCKPIT VOICE RECORDER MICROPHONE MONITOR

TESTERASE

STATUS HEADPHONE

PASSENGER OXYGEN

CLOSED OVERRIDE

NORMAL

FIRST AID

TEST PORT

PASS ONOFF

FAULT

LOWPPR

OP

EN

PU

SH

PU

SH

TO

CLO

SE

OP

EN

PU

SH

SELECT VALVECLOSED

SELECT VALVECLOSED

PITOT STATIC

OXYGEN MASK

RESET

TEST

NPUSH100%

MICHEADSET

HDPH

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−46

AIRPLANE DOORS

The airplane is equipped with the one passenger door (which serves as an emergency exit), oneoverwing emergency exit, one baggage compartment door, one rear fuselage equipment bay doorand several service doors and panels.

The door warning system provides the flight crew with a visual indication (EICAS), when any of thefollowing exterior doors/exits are opened or incorrectly latched:

• Passenger door.• Cargo door.• Aft equipment bay door.• Left or right emergency exit.

Description and operation of the emergency features of the wing emergency exits are in this manualChapter 8, EMERGENCY EQUIPMENT.

The door warning system also provides the flight crew with a visual indication (EICAS), when any ofthe landing gear doors are not in their commanded position. Description and operation of the landinggear doors are in this manual Chapter 15, LANDING GEAR.

PASSENGER DOOR

The passenger door is the main entrance /exit for passengers as well as the flight crew and islocated on the left side of the airplane, aft of the flight compartment. The door is a mechanicallybalanced airstair with an attached door. The door assembly which opens outwards and downwards,turns on two brackets attached to each side of the airstairs and hinge points in the fuselage.Handrails are attached to each side of the airstairs and the fuselage. They extend and retract as thedoor opens and closes.

The door operation is power assisted with a cable system and a DC electric motor. The door lockingmechanism is capable of operations from inside and outside the airplane. A single operation fromeither handle will unlock the door and lift it clear of its latching mechanism.

The door opens under a controlled descent through a tension spring arrangement and mechanicaldamping using a pulley and cable mechanism.

The door is normally closed from inside or outside of the airplane through an electrical actuator. Thedoor can also be manually closed without electrical power.

A hinged flap (vent flap) opens in the exterior surface of the door to protect against pressurization ofthe fuselage, to an unsafe level, until the door is closed and locked.

The door locks have proximity switches to display an EICAS indication of closed and locked.

Lights are provided in each step riser to illuminate the steps. Door lighting automatically shuts-offwhen the passenger door closes.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−47

PASSENGER DOOR SCHEMATIC

CABLE ASSEMBLY

HANDRAIL ASSEMBLY

CLOSED POSITION

GF

0110

_030

a

OP

NE

OPEN

PASSENGER DOOR COMPONENTS

The following components are described to provide an understanding of the passenger dooroperating system.

Airstair and Handrails Assembly

The airstairs act as the steps for embarking/disembarking the airplane. They also act as supportfor the door structure, which hangs below the airstairs when open. The airstairs are hinged to theairplane via two hinges and two pins.

The handrails are attached to the fuselage and the airstairs. They support the weight of the doorand airstair assembly and passenger loading. Handrails are capable of supporting the weight ofthe door and passenger loading.

The design of the door is such that there is no contact with the ground when the door is in theopen position.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−48

PASSENGER DOOR COMPONENTS (CONT'D)Lift arms

Two levers are connected from either end of the lockshaft to the fixed linked arms on the airstairstructure. They are driven by the handles, assisted by the tension spring. Their purpose is to liftthe door out of its frame and hold it up and out in relation to the airstair, while the door is opening.

“G” Locks

In the locked position, the “G” lock hooks hold the door relative to the airstairs and prevent anyupward movement in the door frame during turbulence or negative “G” flight.

Vent Flap

A pressurization vent flap is centrally located at the top of the door under the lockshaft. The flapprevents pressure building up until the “G” locks engage. Once the locks are in and the flap isshut, the pressure holds the flap firmly shut. The vent flap is opened by the lockshaft mechanismas the “G” locks are disengaged, to release any residual pressure from the pressurization system.

LIFT ARM

VENT FLAP

FORWARD "G" LOCK

AFT "G"

LOCKING HANDLE G

F01

10_0

31a

LOCK

OPEN

Locked Indication

Visual indication of latching and locking is given by an indicator arm that is driven directly by thelast motion of the internal handle. The internal handle cover provides an indication to the cabincrew by the red band indicators to the cover and the handle. The red band across the handle andcover clearly shows the handle in the locked position. A safe indication is indicated by thealignment of the two red lines.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−49

PASSENGER DOOR OPERATING HANDLES

The external handle is set into a box in the lower door structure. It is connected by push/pull rodsinside the door to the lockshaft, at the forward end.

position until the handle moves to the full down position.

LOCKSHAFT

GF

0110

_032

The door is not in the fully closed

EXTERNAL HANDLE

NOTE

As the lockshaft reaches its fully locked position, the handles are held in position with spring tension.When the handles are moved out of the locked position, the spring assists in lifting the door andreduces the load on the handles.

The internal handle is a lever on the forward side of the door directly attached to a lockshaft and tothe forward door lift arm.

(stowed) position. The door is not in the fully closed position until the handle moves fully down.

GF

0110

_033

NOTE Handle shown in the locked

INTERNAL HANDLE

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−50

PASSENGER DOOR SWITCHES

The internal door operating switch is controlled on and off by the “DOOR” switch installed internally inthe door frame, next to the main passenger door.

INTERNAL SWITCH (view looking from inside the airplane)

EXTERNAL SWITCH

NOTE Both switches are guarded but not shown.

GF

0110

_034

The external door operating switch is controlled on and off by the “DOOR” switch installed next to themain passenger door.

EXTERNAL DOOR SWITCH ACCESS PANEL

DOOR OPERATINGSWITCH

DOOR OPERATION

PUSH IN FLAP TOGRASP HANDLE

LIFT HANDLE FULL UPPULL DOOR OUT

1. OPERATE SWITCH TOROTATE DOOR FULLYINTO DOOR APERTURE

2. PULL HANDLEDOWNWARDS TO STOW

TO OPEN TO CLOSE

NOTE: DO NOT RE−CYCLE HANDLE DURING CLOSING OPERATION WITHOUT RE− OPENING DOOR SUFFICIENTLY TO RE−ARM DOOR UPLOCK LEVER

OperatingInstructions

GF

0110

_035

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−51

PASSENGER DOOR OPERATION

The following examples are intended to familiarize the operator with events which occur whenmoving the passenger door from either the open or closed positions. The door operations aredescribed in detail and should be followed as per Aircraft Maintenance Manual Chapter 52.

External Door Operation

To open the passenger door externally:

• PUSH IN FLAP TO GRASP HANDLE• LIFT HANDLE FULL UP• PULL DOOR OUT

To close the passenger door externally:

NOTE

Do not re-cycle the handle during closing operation withoutre-opening door sufficiently to re-arm door uplock lever.

• DISENGAGE HANDRAIL LOCK• PRESS AND HOLD DOOR CLOSE SWITCH• PULL HANDLE DOWNWARDS TO STOW

Internal Door Operation

To open the passenger door internally:

• OPERATE DOOR HANDLE FROM THE LOCKED POSITION• DOOR MOVES INWARD AND UPWARD• PUSH DOOR OUT TO OPEN

To close the passenger door internally:

• PUSH FOOT PEDAL (to disengage handrail lock)• PRESS AND HOLD DOOR CLOSE SWITCH• MOVE DOOR HANDLE FULLY DOWN• CHECK GREEN VISUAL INDICATION IN THE HANDLE

Manual Closing

A rope wound around a pulley on the aft end of the torque shaft must be unwound sufficiently to bebrought into the cabin. The handrail latch must be released and then the rope can be pulled,rotating the torque shaft and raising the door via the normal cables. Once the door is raised it maybe lowered into the frame and locked by the normal method with the lock handle.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−52

EMERGENCY EXIT

An overwing emergency plug type emergency exit is installed on the right side of the airplane. Theexit is an inward opening plug type and can be unlatched from the interior or exterior of the airplane.Emergency door operation from inside the cabin is achieved by single action of the emergency exitoperating handle.

EMERGENCY EXIT DOOR GF

0110

_036

Two lower hook fittings and two upper latch fittings position the door in the door opening. Three stopfittings on each side of the door and surround structure react to the pressurization forces of the plugdoor type.

HOOK FITTING

LATCH FITTING

HAND HOLD

LATCH MECHANISM

DOOR STOP BOTH SIDES

GF

0110

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When the door is removed, handling is facilitated by an interior hand grip, flush-mounted within thedoor box structure.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−53

EMERGENCY EXIT (CONT'D)

To unlatch the emergency exit door from the interior, the upper door handle is pulled inward. Thismotion opens the exterior push plate/vent flap to bleed any residual pressure and disengages the twolatch pins. The door moves inward and pivots on the lower hook fittings. A grip of the upper handle ismaintained while grasping the lower hand grip and the door is lifted inwards away from the dooropening.

QUICK RELEASE LATCH MECHANISM

HAND GRIP

GF

0110

_038

To unlatch the emergency exit door from the exterior, the upper push plate/vent flap is depressed todisengage the latch pins and the door is pushed inwards away from the opening.

PUSH IN FLAPPUSH DOOR INWARD

GF

0110

_039

Visual indication of a locked condition of the overwing emergency is the exit door secured in position,with the interior handle recessed in the surround structure.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−54

AFT EQUIPMENT BAY DOOR

The unpressurized aft equipment bay is accessed by a maintenance door in the fuselage fairing. Thedoor is horizontally hinged at it’s forward edge with initial and subsequent opening movements beingdownward and outward. When the door is opened, it is restrained from over travel and striking thebelly fairing using two, door-to-fairing mounted lanyards.

The door locking mechanism is capable of operation only from outside of the airplane.

AFT EQUIPMENT BAY DOOR SCHEMATIC

LANYARD

LATCH MECHANISM

GF

0110

_040

During the closing cycle, two rollers, one on either side of the door, act as guides to locate and centrethe door within its belly fairing aperture.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−55

AFT EQUIPMENT BAY DOOR SCHEMATIC (CONT'D)Aft Equipment Bay Door Operation

DOOR OPENING − Door opening is accomplished by depressing the trigger and pulling thehandle to the full open position.

DOOR LATCH HANDLE ASSEMBLY

GF

0110

_041

DOOR CLOSING − The door latch handle is flush fitting and is secured by an integral push trigger,which when depressed, releases the handle to the free open position. The door is secured byreturning the handle flush with the door.

Visual indication of secure latching and locking is given by the door, the push trigger and theexternal handle all being flush with the fuselage’s surface.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−56

BAGGAGE COMPARTMENT DOOR

A baggage compartment plug type access door is installed in the fuselage aft section on the left sideforward of the rear pressure bulkhead.

Aft Passenger Compartment Bulkhead

Cargo Compartment

CARGO DOOR OPENING

BAGGAGE COMPARTMENT INTERIOR

DOOR HANDLE

GF

0110

_042

The door is an inward opening plug type and can be unlatched from outside or inside the airplane.The door is accessible, but not visible, from the passenger compartment and is not an emergencyexit. The door moves inward and upward to a stowed position above and clear of the door aperture.

DOOR HANDLE RECESS

PUSH TRIGGER

OUTER HANDLE

CARGO DOOR OPEN

STOWED POSITION

GF

0110

_043

The latch mechanism consists of inner and outer handles directly coupled together and mounted onthe forward and aft sides of the door. The handle assembly contains a trigger lock which holds thehandle in the stowed position. The door is latched when the exterior handle is rotated to engage latchpins and locked when the handle is stowed and latched in its housing recess.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−57

BAGGAGE COMPARTMENT DOOR (CONT'D)

A vent door is located in the upper portion of the door and will not close until the door is fully closedand the handle stowed in the locked position.

VENT DOOR/SEAL

INTERIOR DOOR HANDLE

DETENT BUTTON GF

0110

_044

Baggage Door Operation

CLOSING THE BAGGAGE DOOR EXTERNALLY − Rotate the outer handle 90 degrees to latchthe door. Push the handle into the recessed housing until the trigger button is latched into thetrigger mechanism.

CLOSING THE BAGGAGE DOOR INTERNALLY − Rotate the inner handle 90 degrees counterclockwise to latch the door. Pull the handle until the outer handle trigger latches into the triggermechanism and the handle is stowed into the recessed housing.

OPENING THE BAGGAGE DOOR EXTERNALLY − Press the trigger button to release and ejectthe outer handle from the recessed housing. Rotate the handle 90 degrees counter clockwise tounlatch and open the door.

OPENING THE BAGGAGE DOOR INTERNALLY − Press the release button on the inside handleto unlock the handle from the trigger. Rotate the handle 90 degrees clockwise to open the door.

Baggage Door Indication

Visual indication of a locked condition is the baggage door secured in position and the exteriorhandle stowed and locked in the handle recess.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−58

DOOR INDICATION AND CONTROL

The airplane door position and locked indication is provided to the EICAS by the LGECU. TheLGECU provides data that is used to generate alerts and synoptic displays for the fuselage doors.

Door position information is displayed on the STAT page and message information is displayed onthe PRIMARY page.

The STAT page presents the following doors:

• PASSENGER• EMERGENCY OVERWING EXIT• BAGGAGE

STAT Page

PASSENGER DOORBAGGAGE DOOR

OVER WING EMERGENCY EXIT

SERVICE DOOR ANNUNCIATION

Airplane Door Position Airplane Door Graphic

CLOSED

OPEN

INVALID

GF

0110

_045

SERVICE DOORS

Passenger Door

The passenger door is monitored by three proximity sensors to determine the locked and handlestowed position. Proximity sensors (one at each location) are located on the passenger doorforward and aft latch to monitor the “G” latch position. A proximity sensor is mounted in thepassenger door to monitor the outer handle stowed condition.

The sensor information is used by the Landing Gear Electronic Control Unit (LGECU) for doorposition and locked indication and sends the results to EICAS for position and locked displays.

Emergency Exit

One proximity sensor is installed at the top of the door position and senses the door in the closedposition.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−59

DOOR INDICATION AND CONTROL (CONT'D)Baggage Door

Two proximity sensors monitor the door position and provide signals to the LGECU which in turnprovides the EICAS display.

Large Maintenance Doors

Two (optional third) separate large hinged and latched maintenance hatches, are monitored by theLGECU. Each door is monitored by one proximity sensor to determine the door closed condition.In each case, the proximity sensor is mounted on the airplane structure and monitors a sensor onthe hatch. The information is used by the LGECU for door position indication.

The LGECU combines the status of the aft equipment bay door with the status of the maintenancehatches to produce a single EICAS indication.

The maintenance hatches that are monitored are:

• Rear hydraulic system access door.• Refuel/defuel station door.• Optional belly fairing stowage access door.

Aft Equipment Bay Door

An electrical proximity sensor provides indication to the EICAS system when the door is properlyclosed. The LGECU monitors the signals and provides the input to EICAS.

Small Service Doors

The LGECU monitors the signals and provides input to EICAS when any one of the access/smallservice doors is not properly closed.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−60

EICAS MESSAGES

GF

0110

_046

c

PASSENGER DOORCARGO DOORL−R EMER EXITDOOR SYS FAILLARGE SERV DOORSSMALL SERV DOORS

PASSENGER DOOR Comes on to indicate that the passenger door is not closed and locked.

DOOR SYS FAILComes on to indicatethe loss of fuselage and gear door indication.

CARGO DOORComes on to indicatethat the cargo door is not closed and latched.

L−R EMER EXITComes on to indicatethat the applicable emergency exit door is not in position.

SMALL SERV DOORSComes on to indicatethat any one or more of the small service doors are not closed.

LARGE SERV DOORSComes on to indicatethat one or more of the following doors are not closed:

Equipment bay.

Rear hydraulic system access.

Refuel/defuel station.

Optional belly fairing stowage access.

INT CABIN DOOR

INT CABIN DOORComes on to indicate that the interiorcabin door is closed for takeoff and landing.

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−61

AIRPLANE GENERAL


CSP 700−5000−6

Volume 201−10−62


CB - DOORS SYSTEMS

GF

0120

_001

STAT SYS BUS PREV CNTL TESTPAGE

NEXTPAGE

EMERCNTL

BUS


SYSTEMCIRCUIT BREAKER

AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

PAX DOOR MOTOR

1/1CB − DOORS SYSTEMS

AV BATT DCPC IN

BRT

AIRPLANE GENERAL



CSP 700−5000−6

Volume 201−20−1

AIRPLANE GENERAL



CSP 700−5000−6

Volume 201−20−2


Bombardier Global 000-Airplane General

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