Bombardier Challenger Global 00-Airplane General

AIRPLANE GENERAL

Sep 14/2005 Flight Crew Operating Manual Volume 2REV 4 CSP 100-6 01-00-01

Introduction ......................................................................................................................... 01-02-01Aircraft Dimension Schematic ............................................................................................. 01-02-02Antenna Location Schematic............................................................................................... 01-02-05Visual Eye References For Ground Operation.................................................................... 01-02-06Steering and Turning Radii .................................................................................................. 01-02-07Steering and Turning Radii Schematic ................................................................................ 01-02-07Danger Areas ......................................................................................................................01-02-08Airplane Jacking .................................................................................................................. 01-03-01Towing ................................................................................................................................. 01-03-02Mooring ............................................................................................................................... 01-03-03Crew Seat Assembly ........................................................................................................... 01-04-01Eye Locator — Seat Adjustment ......................................................................................... 01-04-02Cockpit Layout..................................................................................................................... 01-04-03

Left Side Console....................................................................................................... 01-04-04Right Side Console .................................................................................................... 01-04-05Center Pedestal .........................................................................................................01-04-06Instrument Panel........................................................................................................ 01-04-07

Circuit Breaker Panels......................................................................................................... 01-04-08CB 1 Pilot Circuit Breaker Panel (Typical) ................................................................. 01-04-08CB 2 Copilot Circuit Breaker Panel (Typical) ............................................................. 01-04-09CB 3 Left Side Equipment Rack Circuit Breaker Panel (Typical)............................... 01-04-10CB 4 Right Side Equipment Rack Circuit Breaker Panel (Typical) ............................ 01-04-11CB 5 Left DC Power Center Circuit Breaker Panel (Typical) ..................................... 01-04-12CB 6 Right DC Power Center Circuit Breaker Panel (Typical)................................... 01-04-12

Control Wheel......................................................................................................................01-04-13Passenger Door .................................................................................................................. 01-05-01

Description ................................................................................................................. 01-05-01Components And Operation ......................................................................................01-05-01Door Latching Mechanism ......................................................................................... 01-05-04Passenger Door Annunciations ................................................................................. 01-05-04

Emergency Exit ................................................................................................................... 01-05-05Description ................................................................................................................. 01-05-05Components And Operation ......................................................................................01-05-05Emergency Exit Annunciations .................................................................................. 01-05-06

Cabin Equipment................................................................................................................. 01-05-06Description ................................................................................................................. 01-05-06Components And Operation ......................................................................................01-05-06

Cargo Bay Door................................................................................................................... 01-05-08Description ................................................................................................................. 01-05-08Components And Operation ......................................................................................01-05-08Cargo Bay Door Annunciations.................................................................................. 01-05-08

Service Doors......................................................................................................................01-05-09Components And Operation ......................................................................................01-05-10Aft Equipment Bay Door Annunciation....................................................................... 01-05-11

Door Warning System .........................................................................................................01-05-12Description ................................................................................................................. 01-05-12Components And Operation ......................................................................................01-05-12

EICAS Messages ................................................................................................................01-05-13

REV 4REV 1REV 1

AIRPLANE GENERAL


INTRODUCTION

The Challenger 300 aircraft, manufactured by Bombardier Aerospace, is an all metal, pressurized, low-wing, turbofan-powered monoplane. The high-aspect ratio, fully cantilevered, swept-back wings with winglets are of conventional rivetedconstruction except for the upper section of the winglets, which utilize full-depth honeycomb core bonded to the outer skin.The fuselage is of semimonocoque construction and utilizes a constant circular cross-sectional shape fuselage.

Thrust is provided by two pod-mounted AS907 turbofan engines manufactured by Honeywell. Independent fuel systemssupply fuel to the engines with fuel storage provided in wing tanks. Engine-driven hydraulic pumps provide hydraulic pow-er for braking, extending or retracting the landing gear, nosewheel steering, wing flaps, spoilers, thrust reversers, elevator,and rudder. The landing gear system is a fully retractable tricycle-type trailing link landing gear with dual main gear wheels,nosewheel steering, and a brake-by-wire brake control/anti-skid braking system.

The ailerons are manually controlled, and the elevator and rudder are controlled via hydraulic actuators. An electricallyactuated trim tab is installed on the left aileron to provide lateral trim. Longitudinal trim is accomplished by changing theincidence of the horizontal stabilizer with an electrically operated linear actuator. Rudder trim is accomplished via an elec-tromechanical actuator which moves the rudder surface independent of the rudder pedal position. Aircraft air-conditioningsystems which include an air-cycle machine, provide heating, cooling, and pressurization for the cockpit,passenger compartment, and lavatory.

REV 1

AIRPLANE GENERAL

Volume 2 Flight Crew Operating Manual Sep 13/200401-02-02 CSP 100-6 REV 1

AIRCRAFT DIMENSION SCHEMATIC

CF

O01

0100

2_01

5

NOTES

Measurement at manufacturerempty weight.

WING AREAWING BASE

522 ft (48.5 m )27.8 ft (8.5 m)

27°

25% CHORD LINE

10 ft 6 in(3.20 m)

63 ft 10 in(19.46 m)

3 ft 9 in(1.14 m)

23 ft 9 in(7.24 m)

13 ft 2 in(4.01 m)

7 ft 8 in(2.34 m)

28 ft 1 in(8.56 m)

2 2

1

OTHER DIMENSIONS

12 ft(3.66 m)

AIRPLANE GENERAL


AIRCRAFT DIMENSION SCHEMATIC (Cont)

CF

O01

0100

2_01

6

2 ft 6 in(0.76 m)

4 ft 3 in(1.3 m) 61 ft 1 in

(18.62 m) 68 ft 8 in(20.92 m)

20 ft(6.1 m)

23.7 ft(7.7 m)

16.5 ft(5.0 m)

28.6 ft(8.7 m)

NOTES

Measurement at manufacturerempty weight.

1

1

6 ft 3 in(1.89 m)

REV 1

AIRPLANE GENERAL


AIRCRAFT DIMENSION SCHEMATIC (Cont)

CF

O01

0100

2_01

7

6.1 ft(1.9 m)

5.1 ft(1.6 m)

7.2 ft(2.2 m)

PASSENGER COMPARTMENTDIMENSIONS

LENGTH

WIDTH (FLOOR LINE)

WIDTH CENTERLINE

HEIGHT

VOLUME

FLOOR AREA

28 ft 7 in

5 ft 1 in

7 ft 2 in

6 ft 1 in

896 ft

146 ft

8.71 m

1.55 m

2.18 m

1.85 m

25.37 m

13.5 m

3

2

3

2

AIRPLANE GENERAL


ANTENNA LOCATION SCHEMATIC

SATCOM(IF INSTALLED)

VOR/LOC(LH AND RH)

HF

ELT(OPTIONAL)

VHF COMM #3(IF INSTALLED)

MARKER BEACON

RAD ALT

ADF #1ADF #2

VHF COMM #1

TCAS (DIRECTIONAL)

GPS #1

GPS #2

ATC

DME #1TCAS OMNI

VHF COMM #2

DME #2

ATC

TELECOM

Personnel should not stand nearby and in front of the radar antenna when it is transmitting. When the antenna is not scanning, the danger increases.

WARNING

WEATHER RADAR

GLIDESLOPE

CF

O01

0100

2_00

5

LIGHTNINGSENSOR(OPTIONAL)

AIRPLANE GENERAL


VISUAL EYE REFERENCES FOR GROUND OPERATION

WITH HEAD MOVED 0.3 ft (91 mm)OUTBOARD

PILOT'S EYEPOSITION

PILOT'S EYEPOSITION

APPROACH VISIBILITY

10.5 ft(3.2 m) 19°

17°

7.7 ft(2.3 m)

26.6 ft(8.1 m)

8.7 ft(2.6 m)

MAXIMUM 139° VISION AFTWITH HEAD ROTATED

1.8 ft(0.54 m)

PILOT'S EYEPOSITION

51°

32°

17°20°

51°

17°20°

32°

CL

NOT FOR LANDING

AIRPLANE GENERAL


STEERING AND TURNING RADII

Steering and turning radii are shown below.

STEERING AND TURNING RADII SCHEMATIC

CF

O01

0100

2_00

6

NOTEMAXIMUM STEERING

SYMMETRICAL AND IDLE THRUSTNO DIFFERENTIAL BRAKING65° STEERING ANGLE3° SLIPDRY RUNWAYSLOW CONTINUOUS TURNMAX A/C WEIGHTAFT CG

27.8 ft(8.4 m)

r 37.4 ft(11.3 m)

95.5 ft(29.1 m)

58.0 ft(17.7 m)

MIN PAVEMENTWIDTH 180° TURN.WITH 5 ft MARGINOF SAFETY.

21.0 ft(6.4 m)

r 20.0 ft(6.10 m)

r 31.5 ft(9.6 m)

r 38.4 ft(11.8 m)

65.0°

AIRPLANE GENERAL


DANGER AREAS

CFO

0101

002_

019

WEATHER RADAR5 ft(1.5 m)

15 ft (4.5 m)FROM INTAKE

15 ft (4.5 m)FROM INTAKE

APU EXHAUST500 °F (260 °C)19 ft (5.8 m)

200 ft (60.9 m) FROM TAILPIPE200 °F (93.3 °C)

NOTE:

EXHAUST DANGER AREASHOWN FOR IDLE RPM.VALUES APPROXIMATELYDOUBLE FOR TAKEOFFRPM.

AIRPLANE GENERAL


AIRPLANE JACKING

Three jacking points are provided, one located forward on the fuselage, and one on each wing at the rear spar for jackingthe complete airplane.

Gear jacking points are also provided for tire/wheel/brake changes. Jacking procedures are located in theAircraft Maintenance Manual (Chapter 7).

CF

O01

0100

2_01

2

TYPICAL JACK

NYLONPLUG

JACKPAD

JACKINGPOINT

SUPPORTBEAM

REAR FUSELAGE SUPPORTJACK

REAR FUSELAGESUPPORT

LEGEND

REV 1

AIRPLANE GENERAL


TOWING

The aircraft maybe towed, with the torque links connected and the Steering Control System de-energized, up to a limit of120° of nosewheel angle. Should the nosewheel angle exceed this value a NWS LIMT EXCEEDED CAS message (C) willbe displayed. At approximately 123°, the indicator pins on the NLG will be sheared off to provide a physical indication thatdamage may have been done to the feedback linkage and surrounding area.

For special hangar operations, the torque links may be disconnected to allow towing at any angle, provided the shock strutextension exceeds the dimension in inches of chrome showing, provided on a warning plate. The warning plate is mountedon the nose landing gear to indicate to the ground crew the operational limits for towing. For further towing informationrefer to the Aircraft Maintenance Manual (chapter 9).

TOWING BAR ATTACHMENT

CF

O01

0100

2_01

0

TOW BARASSEMBLY

REV 1

AIRPLANE GENERAL


MOORING

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

MOORING ATTACHMENT POINTS

CF

O01

0100

2_01

1

MAIN AND NOSE AREAS

TAIL AREA

MOORINGADAPTERPLATE

JACKINGPAD

TIE DOWNRING

45° 45°

30.25° 30.25°

AIRPLANE GENERAL


CREW SEAT ASSEMBLY

The crew seats provide adjustments fore and aft, recline adjustment, height and armrest position.

CF

O0

10

10

02

_0

08

HEADREST

OXYGEN

MASK

ARMREST

RECLINE

ADJUSTMENT

CONTROL

SEAT BASE

VERTICAL

ADJUSTMENT

CONTROL

SHOULDER STRAP

RESTRAINT LOCK /

UNLOCK HANDLE

FORE/AFT

ADJUSTMENT

CONTROLLUMBAR

ADJUSTMENT

HANDWHEEL

SEATBACK

FRAME

TRASH BAG

HOOK

SEAT BACK

SEAT

BOTTOM

NEGATIVE-G

STRAP

SHOULDER

STRAPS

LAP

BELT

REV 1

AIRPLANE GENERAL

Volume 2 Flight Crew Operating Manual May 06/200501-04-02 CSP 100-6 REV 2

EYE LOCATOR — SEAT ADJUSTMENT

An eye locator is mounted on the center windshield post to enable seat adjustment for correct eye-to-wheel height. Propersight line is attained when the rear ball is no longer seen, as it will be covered by the white ball in front.

Correct seat placement is obtained (height, fore, aft) when: - All flight controls are unrestricted throughout full travel - Flight instruments and warning lights visible, without being obstructed- Out-of-cockpit visibility unobstructed- Seat position comfortable

CF

O010

1002_007

PILOT

SIGHT LINE

COPILOT

SIGHT LINE

FRONT VIEWTOP VIEW

NOTE:

The support bracket

is not shown.

2

AIRPLANE GENERAL


COCKPIT LAYOUT

Flight Deck (typical)

AIRPLANE GENERAL


COCKPIT LAYOUT (Cont)

LEFT SIDE CONSOLE

CF

O01

0000

2_00

2

DIM BRT DIM

ANNUNDIM BRT

PEDESTAL

DIM BRT

BRT

GSHLD/L SIDE

PFD - MFD

COCKPIT LIGHTS

1

AIRPLANE GENERAL



RIGHT SIDE CONSOLE

CF

O01

0000

2_00

3

CB PANELS

DOME GSHLD/R SIDE

PFD -MFD

COCKPIT LIGHTS

DIM BRT DIM

DIM BRT

BRT

DIM BRT

REV 1

AIRPLANE GENERAL



CENTER PEDESTAL

Center Pedestal (Typical)

CF

O01

0100

2_01

4

LG PULL

1

2a

3

5

6

4

7

8

2b

14

21

22

23

25

26

24

18

17

15

13

19

10

9

12

20

11

16

1. FUEL PANEL

2a. FMS CONTROL DISPLAY UNIT (OPTIONAL)

2b. FMS CONTROL DISPLAY UNIT (STANDARD)

3. REVERSION PANEL

4. AIR CONDITIONING/BLEED PANEL

5. ANTI-ICE PANEL

6. ELECTRICAL PANEL

7. PRESSURIZATION PANEL

8. LIGHTING PANEL

9. FLIGHT SPOILERS HANDLE

10. PITCH DISCONNECT HANDLE

11. THRUST LEVERS

12. ENGINE RUN SWITCH PANEL

13. GROUND SPOILERS/ROLL SPOILERS PANEL

14. TRIM AND STALL PANEL

15. PARK/EMER BRAKE HANDLE

16. SYSTEM TEST PANEL

17. ELT PANEL

18. COCKPIT VOICE RECORDER PANEL

19. CABIN CONTROL PANEL

20. HYDRAULIC PANEL

21. FLAP LEVER

22. MFD CONTROL PANEL (MCP)

23. ENGINE PANEL

24. APU SWITCH

25. LANDING GEAR MANUAL RELEASE HANDLE

26. PAX OXYGEN PANEL

1

AIRPLANE GENERAL



INSTRUMENT PANEL

CF

O01

0400

2_00

4

AIR OUTLETLEFT PRIMARY FLIGHT DISPLAY (PFD)LEFT MULTI FUNCTION DISPLAY (MFD)TAWS WARNING PANELLANDING GEAR HANDLERIGHT MULTI FUNCTION DISPLAY (MFD)RIGHT PRIMARY FLIGHT DISPLAY (PFD)

13.14.15.16.17.18.19.

12

45 6 7 8 9

10

1112

14 15 16 17 18 19

3

13

AIR OUTLETPILOT AUDIO CONTROL PANELPILOT COMPASS/BARO/RUDDER PEDAL ADJUSTMENTMASTER WARNING/CAUTIONPILOT DISPLAY CONTROL PANEL (DCP)FLIGHT GUIDANCE PANEL (FGP)STANDBY INSTRUMENTCLOCKCOPILOT DISPLAY CONTROL PANEL (DCP)MASTER WARNING/CAUTIONCOPILOT AUDIO CONTROL PANEL

1.2.3.4.5.6.7.8.9.

10.11.

COPILOT COMPASS/BARO/RUDDER PEDAL ADJUSTMENT12.

1

AIRPLANE GENERAL


CIRCUIT BREAKER PANELS

CB 1 PILOT CIRCUIT BREAKER PANEL (TYPICAL)

A

C

B

D

E1110987654321 1312 1514

L CH AR CH A CTRL 1 CTRL 2CH ACTRL PWR

L TRFADEC

ENGINEFIREDET

FUEL

L PUMP

NAV 1 DME 1 GPS 1 CDU 1 XPDR 1 TCAS

NAVIGATION

AVIONICS

PRI

APU

L FGP/

SERVOSL IAPS

RIU 1B/

AURAL RIU 1AHF 1COM 1

AUTO FLIGHTCOMMUNICATION

INBD

BRAKES

WOW A/

RET/EXT

NWS

PWR 1

R DC

PUMPL SOVL IND

LDG GEARHYDRAULIC

L MFDL DCPL PFD

ATT

HDG 1

AIR

DATA 1

DISPLAYS

INDICATING/RECORDING

L BLEED

VALVES

PRESS 1

/PACK

ENVIRONMENTAL

DCU A RDC A CTRL 1 L PWR 1 R PWR 2

ANNUNCIATOR

L PITOT TAT VANE CASE CTRL PWR L ENG


ANTI ICEL WINDSHIELDL AOA

15 15 7.5 7.553 253 3 3 3 3 5

335 7.5 3 5 57.53 7.53 7.5 3 3

5 5 5 53 3 0.53 3 10 103

53 35 5 3 5 5

20 5 15 10 7.5 15 5 0.5 5 5

L WINGBLD LK

L ICE

DET

L STBYSTATIC

L PROBE

CTRL

WOW

B

3

CF

O0106

002_006

5 3 0.5

3 5

WX

RAD

ALT

L AUDIO

PWR 1

CVR IND DC PUMP

AUX ALT LIM/

ECS X VLV

PWR2

1110987654321 1312 1514

A

C

B

D

E

TRIM/

RUD LIML PWR

SPOILER

CTRL 1

PRI STABFLAPSTALL

FLIGHT CONTROLS

L SHKR PUSHER L IND CTRL

REV 2

AIRPLANE GENERAL

May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 01-04-09

CIRCUIT BREAKER PANELS (Cont)

CB 2 COPILOT CIRCUIT BREAKER PANEL (TYPICAL)

A

C

B

D

E123456789101112131415

CTRL 2 CTRL 1 L CH B R CH B CH B PWR CTRL

R TR FADECENGINE FIRE

DETFUEL

R PUMP

TAWS XPDR 2 CDU 2 GPS 2 DME 2 NAV 2

NAVIGATION

AVIONICS

R SHKR R PWRSPOILERCTRL 2 SEC

FLAP STALLFLIGHT CONTROLS APU

R FGP/SERVOS R IAPS

RIU 2B/AURAL RIU 1A HF 2 COM 2

AUTO FLIGHT COMMUNICATION

OUT BDBRAKES

WOWA/RET

NWSPWR 2

L DCPUMP PTU R SOV R IND

LDG GEAR HYDRAULIC DISPLAYS


FDR L PWR 2 R PWR 1 CTRL 2 RDC B DCU B

ANNUNCIATOR

EMER DOME

LIGHTS

R ENGR WINGBLD LK PWR CTRL

R ICEDET CASE VANE

R STBYSTATIC

STBYPITOT R PITOT

R PROBECTRL


ANTI ICER WINDSHIELD R AOA

CF

O01

0600

2_00

5

7.5 7.5 15 15 5 25 3 3 3 3

3 5 3 3 5 7.5 5 3 3 3 7.5 3

5 5 5 5 0.5 3 3 3

53 3 3 5 5 3 5 5

5 3 35 0.5 5 15 7.5 10 5 15 20 3

53

SEC STABTRIM/

RUD LIMAIL

TRIMRUDTRIM

R IND/CTRL

R AUDIOPWR 1

3

STBY INSTBATT TEST

STBY INST/BATT R MFD R DCP R PFD

ATTHDG 2

AIRDATA 2

3 10 3 3 310

WOWB/EXT

3

VALVES /TRIM PWR 1 VALVE HEATERR BLEED PRESS 2 ECS XVLV XBLEED CARGO

ALT LIM/ENVIRONMENTAL

A

C

B

D

E

V 2

AIRPLANE GENERAL



CB 3 RIGHT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)

3 4 5 6 7 81 2 9

A

C

B

D

E

F

L PFD

HTR

L MFD

HTR


TR INBD

WHL SPD

ENG RUN

CH A

SYNC/

IGN A

ENG

START A

ENGINE

ELEC

L ENG

SOV

GRAVITY

X FLOW QTY 1

FUEL

FLIGHT CONTROL

PAX

DOOR

ENVIRONMENT

L SIDE WINDOWANTI ICE

L FORCE

SNSR

MSTR DISC

AUTO FLT TRIM

ENTRY

LIGHTS

L CKPT

/PED

CABIN

SIGNS

WING

INSP

MAP/

STOW

BCN/

STROBE

DISPLAYS

CLOCK

CLOCK

PWR

AVIONICSDATA

LOADER

IAPS

FAN COM 3

LIGHTNING

DET

CF

O0106002_004

3 3 3 3

3 3 3 3 3 3 15

3

3

5 25 5

7.5 3 5 5 5 3 7.5 5

10 10 3 3

LBATT

SEC BUS

20

NORM

OFF

L GEN

COMM

R AUDIO

PWR 2

3

3

OXYGEN

33

NAVELT/

AUTO DEP

THERAPTC

RAM AIR/

OFV PWR2

L FOOT

WARM PWR CTRL

REV 2

AIRPLANE GENERAL

May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 01-04-11


CB 4 LEFT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)

A

C

B

D

E

F

CF

O0106002_003

345678 129

TR OUTBD

WHL SPD

ENG RUN

CH B

SYNC/

IGN B

ENG

START B

ENGINE

NORM

ELEC

R ENG

SOV

XFER

VALVEQTY 2

FUEL

R FORCE

SENSOR

PEDAL

ADJAUTO FLTTRIM

MSTR DISC

FLIGHT CONTROL

CABINLIGHTS

BUS

CTRL

PWR1

PWR2


3 33 3

3 33 3533

3

5

50 501035 10

NORM

20

HYD GEN

APU GEN R GENR BATT

SEC BUS

7.53

PWR/

TEST HTR

0.53

ENVIRONMENTAL

PWRCTRL

R SIDE WINDOWANTI ICE

55355 25

NOSE GEAR WING

STROBE

R CKPT

/CBPCABINTAXILDGLOGONAV

NAV

101057.5 5 5 3

PRI

SEC

SATCOM3rd AUDIO OXYGEN

/INDMAN DEPLAV SMK

DET

DRN

MAST HTR

RAM AIR/

OFV PWR1

R FOOT

WARM

R PFD

HTR

R MFD

HTR

PAX

ADDRESS

COMPASS

LIGHT

COMM

15 3

FLT

PHONE

L AUDIO

PWR2

OFF OFF

V 2

AIRPLANE GENERAL



CB 5 LEFT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)

CB 6 RIGHT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)

2 345678

A

C

B

12

HF 1

PWR

L ATS/

HYD SOLA

PRI STAB

MOTORL LDG

L DCPC

ESS BUS

L SPC

BAT BUS

R DCPC

ESS BUS

AVNXENGINEFIREXFCTLLIGHTS

ELECTRICAL

EXT BAG/

AFT BAY

5 5 25 5 3 3

7.525 5

CF

O0106002_002

FAN

PWR 1

AVNX

35

PWR 2

GROUND SERVICE

PWR 1

25 25

ELECT

5

EDC

PWR

HF 2

PWR

R ATS/

HYD SOL B

SEC STAB

MOTOR R LDG

L DCPC

ESS BUS

R SPC

BATT BUS CTRL VALVES

R DCPC

ESS BUS

AVIONICS ENGINE FIREX FCTL LIGHTS

ELECTRICAL REFUEL DEFUEL

1 2 3 4 5 6 8

A

C

B

1 2

3 5 5 5 25 5

5 7.5 25 3 3

CF

O0106002_001

7

SATCOM

CTRL

PWR 1 PWR 2

ENVIRONMENT

15 15

BAG COMP HTR

FAN

PWR 2

AVNX

35

V 2

AIRPLANE GENERAL


CONTROL WHEEL

The pilot and copilot control wheels contain the following switches:

- Autopilot synchronization switch- Checklist line advance switch- Transponder identification switch- Microphone key switch- Master disconnect switch- Pitch and roll trim switch

AUTOPILOT SYNCHRONIZATION SWITCH

The autopilot synchronization switch enables the pilot to maneuver the airplane without disconnecting the autopilot.

CHECKLIST LINE ADVANCE SWITCH

The checklist line advance switch enables the pilot to advance the electronic checklist on the MFD.

TRANSPONDER IDENTIFICATION SWITCH

The transponder switch activates the transponder IDENT function.

MICROPHONE SWITCH

The microphone switch activates the selected radio transmitter when pulled outboard and the interphone when pushed in-board.

MASTER DISCONNECT SWITCH

The master disconnect switch disengages the autopilot, and deactivates the pitch trim and stall pusher. The stall pusher isnot deactivated on JAA approved aircraft. When released, the pitch trim system and pusher are immediately reactivated butthe autopilot remains disengaged.

PITCH/ROLL TRIM SWITCH

The pitch and roll trim switch enables the pilot/copilot to control the trim from each control wheel.

CF

O01

0100

2_00

9

MASTERDISCONNECTSWITCH

TRIM SWITCHDOUBLE ACTINGPITCH/ROLL ANDTRIM ARMING

AUTOPILOTSYNCHRONIZATIONSWITCH

CHECKLIST LINEADVANCE SWITCH

ID

TRANSPONDERID SWITCH(LOCATED BEHIND)

INPHTX

MICROPHONESWITCH(LOCATEDBEHIND)

REV 1

AIRPLANE GENERAL


PASSENGER DOOR

DESCRIPTION

The passenger door is located on the left side of the aircraft in the forward section of the fuselage and is the primary entryand exit for the aircraft. The passenger door is attached to the fuselage by a goose-neck hinge at the centerline of the door.The door opens out and downward. When closed and locked, the door becomes an airtight plug to prevent loss of pressur-ization in the fuselage.

COMPONENTS AND OPERATION

The passenger door consists of an integral airstair, stairway lighting, folding handrail, actuator assembly, two telescopicsupport struts, door lock mechanism, inside door lever, and an outside door handle. When the passenger door is open, thetop step of the integral airstair is one step below the cabin floor level.

The passenger door is normally closed electrically using an inside or outside switch. The door can be opened or closed man-ually.

DOOR SEAL

SUPPORTSTRUT

AIRSTAIR

SUPPORTSTRUT

HANDRAIL

CF

O01

0500

2_01

2

(INSIDE)DOOR LEVER

(OUTSIDE)SWITCH

PASSENGERDOOR

(OUTSIDE)DOOR HANDLE

(INSIDE)SWITCH

REV 1

AIRPLANE GENERAL


PASSENGER DOOR (Cont)

DOOR ACTUATOR ASSEMBLY

The door actuator assembly consists of an electric motor, inside and outside switch, lifting cable, pulley, and a hand-oper-ated cable. Normal operation of the door is accomplished by the electric motor using the push button switches. In the event of loss of power to the motor, the door can be operated manually with the use of the inside lever, outside handle, and the hand-operated cable.

HANDRAIL

A two-part folding handrail is installed on the aft side of the passenger door. As the door opens, the handrail unfolds parallelto the airstair. A nylon stabilizer is mounted between the base of the handrail and the airstair to prevent unwanted movementof the handrail. As the door closes, the handrail folds at the hinge point.

DOOR SEAL

A flexible blade-type door seal constructed of silicone rubber and fabric is installed in the frame channel in the fuselage.An airtight seal is formed when the passenger door is closed and latched. The door seal prevents a rapid decrease of cabinpressure if any part of the seal becomes unserviceable. The door seal also keeps water out of the fuselage if ditching occurs.

FO

0105

002_

007

PULLEY

DOORACTUATOR

HAND-OPERATEDCABLE ASSEMBLY

LIFTING CABLE

HANDRAILSTABILIZER

HINGEPOINT

HANDRAIL

DOORSEAL

(OUTSIDE)SWITCH PANEL

(INSIDE)SWITCH

1

AIRPLANE GENERAL



NORMAL OPERATION

To open the passenger door from the ground, use the outside handle in the center of the door. To operate the handle, pushthe spring-loaded finger-flap inward and pull the handle out of the recess in the door. Continue to lift the handle upwardsuntil the handle stops, (approximately 110° travel). As the handle is lifted upwards, the vent flap in the door opens to equal-ize cabin pressure. At the end of the handle travel, the latch mechanism disengages the door locks allowing the door to openby gravity. As the door opens downward, the actuator assembly functions as an inertia-reel to allow the door to open slowly.To close the passenger door from the ground, open the door-switch access panel forward of the passenger door and pushthe switch to activate the actuator motor. The lifting cable attached to the door wraps into the actuator housing to close thepassenger door. As the door closes, a vent flap in the handle closes to seal cabin pressure. Pull the external door handledownward and into the stowed position in the recess in the door. The door then can be locked with a key on the outsidehandle.

To open the passenger door from inside the aircraft, rotate the inside handle to the full up position, (approximately 100°travel). The door locks disengage and allow the door to open by gravity. When the door is unlocked, a red flag indicatorshows through a window in the handle. To close the passenger door from inside the aircraft, push the switch located on thebulkhead forward of the door. The switch must be held in at least 7 seconds before the electrically driven motor begins toraise the door into the closed position. To lock the door, rotate the inside lever downward until it stops (approximately 100°travel). When the door is locked, a green flag indicator will show through the window in the handle.

NOTE: In order to prevent a cabin pressure bump during door closure, it is recommended that the airconditioning supply be selected OFF prior to the door being closed. Following door closure, the air conditioningsupply can be reselected.

MANUAL OPERATION

In the event of loss of power to the actuator, the passenger door can be closed manually.

To close the passenger door manually from outside the aircraft, lift the door upward to the closed position. To engage thedoor locks, push the outer door handle into the recess in the door.

To close and lock the passenger door from inside the aircraft, raise the hinged cover located on top of the actuator housingand pull up on the T-handle. Pulling on the cable handle a number of times wraps the door lifting cable into the actuatorhousing and raise the passenger door into the closed position. To lock the door, rotate the inside handle downward until itstops. When the door is closed, a green flag indicator shows through the window in the handle.

KEYLOCKCYLINDER

(OUTSIDE)SWITCH

STOWEDPOSITION

(OUTSIDE)DOOR HANDLE

SPRING-LOADEDGRIP

CF

O01

0500

2_00

6

1

AIRPLANE GENERAL



DOOR LATCHING MECHANISM

The door latch mechanism consists of two cams which are part of a primary shaft installed horizontally on the door struc-ture. The primary shaft turns with inputs from the internal handle and the external handle. The internal handleattaches directly to the primary shaft. The external handle connects to the primary shaft through control rods and a lever.

The latch mechanism has three different primary functions as follows:.

- Vent flap function- Door lifting function- Open lock function

VENT FLAP FUNCTION

It is not possible to open the cabin door if some cabin pressure remains. A pressure lock lever, which connects to the ventflap through a control rod and link, prevents movement of the inner handle and the vent flap stays closed. After cabin pres-sure is released, the springs allow the vent flap to open. The pressure lock disengages, and the door handles can then oper-ate. The springs also insure that the vent flap opens if a part of the operating mechanism becomes unserviceable ordisconnects. If one spring breaks, the other two springs can open the vent flap to release cabin pressure.

DOOR LIFTING FUNCTION

Another cam on the primary shaft of the latch mechanism causes the door to move vertically. As the cam turns, force isapplied to a lever which connect to a lifting shaft installed parallel to the primary shaft. At each end of the lifting shaft is alever which connects to the door hinge mechanism. Movement of the two levers causes the door to move vertically in re-lation to the hinge.

The lifting shaft has a locking ratchet cam connected to the vent flap cam which stops vertical movement of the door unlessthe vent flap is fully open. A pressure lock system also stops more movement of the primary cam shaft if the vent flap iskept closed by too much cabin pressure. When the pressure decreases sufficiently, the springs can open the vent flap andthe locking cam moves to let the lifting shaft turn.

OPEN-LOCK FUNCTION

When the door is fully open it is not possible to close it until a system of mechanical locks is released. This lock mechanismalso prevents too much vertical movement of the steps when entering and exiting the aircraft.

When the door is fully open, the primary lock engages the locking cam on the external handle pivot shaft.

PASSENGER DOOR ANNUNCIATIONS

A PASSENGER DOOR status (S) CAS message is displayed if the passenger door is not fully closed and the followingconditions exist:

- The aircraft is on the ground with the left engine run switch in the OFF position- The aircraft is on the ground, the passenger door handle is not stowed, and both engines are not running

A PASSENGER DOOR caution (C) CAS message is displayed if the passenger door is not fully closed and the followingconditions exist:

- The aircraft is on the ground with the left engine run switch in the On position- The aircraft is in flight and the passenger door rollers are not fully engaged into the fitting guides

REV 1

AIRPLANE GENERAL


EMERGENCY EXIT

DESCRIPTION

The emergency exit is located over the wing on the right side of the aircraft. The emergency exit is a Type III escape hatch that measures 20 inches wide by 36 inches high and weighs approximately 45 lbs. The emergency hatch is a removable plug-type hatch, held in place by a two-pin locking mechanism and by the force of cabin pressure. A security pin can be installed on the inside of the aircraft at one of the locking pins to prevent unauthorized entry from the outside. The security pin has a small flag attached which states REMOVE BEFORE FLIGHT.

NOTE: The emergency hatch can be opened and removed from inside or outside of the aircraft, but must be installedfrom inside the aircraft.


INSIDE REMOVAL

To remove the hatch from inside the aircraft, use the upper latch handle placarded EXIT-PULL. Remove the cover fromthe latch handle and pull the spring-loaded handle inward to retract the locking pins in the top of the hatch. Rotate the hatchdownward into the aircraft, (approximately 12 inches). Using the latch handle and the handhold lift the hatch upward andaway from the hinges at the bottom of the hatch. Place the hatch clear of the exit to allow passage.

CF

O01

0300

2_00

1

LATCHPANEL

RE

MO

VEBE

FORE FLIG

HT

LOCKINGPINS

HANDHOLD

HINGES

LATCHHANDLE

SECURITY PIN

CF

O01

0500

5_00

1

REV 1

AIRPLANE GENERAL


EMERGENCY EXIT (Cont)

OUTSIDE REMOVAL

To remove the emergency hatch from outside of the aircraft, push in on the spring-loaded latch panel placarded EMER-GENCY DOOR PUSH TO OPEN DOOR OPENS INWARD. While holding the panel in, push in on the hatch to rotate thetop of the hatch into the aircraft (approximately 12 inches). With both hands, lift the hatch upward and away from the hingesat the bottom of the hatch. Move the hatch clear of the emergency exit to allow passage.

INSTALLATION

The emergency exit hatch must be installed from inside the aircraft. To install the emergency hatch, the passenger seatlocated nearest the emergency hatch must be in the full inboard position.

Install the emergency hatch into the frame in the fuselage in the opposite order of the Inside Removal procedure. Ensurethat the seal around the door is seated correctly and the locking pins at the top of the hatch are fully extended into the frame.The locking pins are fully extended when the latch handle is fully retracted. Install the cover for the latch handle and securethe hook and loop fasteners for the cover.

EMERGENCY EXIT ANNUNCIATIONS

An EMERGENCY EXIT (C) CAS message is displayed if the proximity sensor detects that the emergency hatch isnot completely closed and the locking pins fully engaged.

CABIN EQUIPMENT

DESCRIPTION

Although individual cabin layouts will vary, cabin interiors will have the following equipment installed:

- Passenger Service Units- Arm Ledge- Cabin Controlled Lighting- Galley- Tables- Entertainment Center- Lavatory


PASSENGER SERVICE UNITS

Passenger service units are installed on both sides of the main cabin and incorporate the following items:

- Manually adjustable air vents for each seat position- Drop down oxygen masks for each seat position- Manually adjustable reading and table lights for each seat location- Upwash and downwash LED lighting- Cabin entertainment system speakers- Cabin temperature sensor

ARM LEDGE

An arm ledge is installed on the left and right sides of the cabin below the window panels and incorporate the followingitems:

- Dual drink holder- Bi-fold executive table- Storage box for general storage and/or phone provisions- Cabin handset (location depending on cabin layout)- Switch panels for cabin lighting and entertainment system- 115V 60 Hz electrical outlet and fax/modem port (location depending on cabin layout)- VIP switch (location depending on cabin layout)

AIRPLANE GENERAL

Feb 22/2006 Flight Crew Operating Manual Volume 2REV 5 CSP 100-6 01-05-07

CABIN EQUIPMENT (Cont)LIGHTING

A remote switch panel is located in the cockpit center pedestal to control cabin and entry lights, cabin DC and cabin ACpower.

Interior lighting consists of airstair and entry lights, crew closet and forward wardrobe lights, galley lighting, cabin upwash and downwash lighting, cabin reading and table lights, lavatory light, lavatory upwash lighting, lavatory mirror lights, bag-gage compartment lighting, emergency lighting, NO SMOKING, FASTEN SEAT BELT, and RETURN TO SEAT lights.

GALLEY

The galley is installed in the forward entry area of the cabin on the right side and provides facilities for stowing and pre-paring food and beverages. The galley contains an insulated ice compartment, two AC outlets, two hot liquid containersand cup dispensers. Lighting, liquid waste lines and ventilation is also provided. A magazine rack is installed on the aft sideof the galley and also contains the subwoofer installation.

TABLE

Three bi-fold pullout retractable executive tables are provided as well as one right hand aft plug in table (near the emergen-cy exit). A closeout conceals the table cavity when the tables are deployed.

ENTERTAINMENT CENTER

AUDIO SYSTEM — Audio is provided through the cabin speakers and/or headphones from the audio/video system. Com-ponents include eight mid/high range speakers and two subwoofer speakers. A single CD changer is operated by two remotecontrolled transmitters located in the left forward wardrobe cabinet above the monitor or in the forward side of the right aftpartition above the monitor. A handheld remote control is also provided.

VIDEO SYSTEM — The LCD monitors are capable of displaying movies or other pre-recorded media. Components con-sist of a single channel DVD player and two 15 inch flat screen monitors. One is installed on the aft side of the left forwardwardrobe cabinet and the other is installed on the forward side of the right aft cabin partition. Also installed is a chime/page-audio/video amplifier. An Airshow 400 or 4000 system is included as part of the entertainment center. The Airshow4000 offers enhanced graphics, cockpit monitor, and interface to telephone or satellite systems. Refer to theapplicable Airshow Operator’s Manual for further system description.

LAVATORY

The lavatory is located in the aft cabin with the sink, mirror, storage compartment, soap dispenser, electrical outlet and or-dinance signs for occupants on the left side. On the right side is an electric flushing toilet with timer and overboard servic-ing, storage area, tissue and trash drawer. Access to the aircraft oxygen bottle(s) is also in this area behind an upper closeoutpanel. Fire extinguisher storage is also provided behind the closeout panel.

The toilet switch panel is located on the left side of the right lavatory partition. The switches control the toilet flush, readinglight, upwash lighting, mirror light, and a lav call that is annunciated in the cockpit and galley.

Overboard service is connected to the toilet to enable service from outside the aircraft. The connector uses a standard airlineservice cart. The service instruction placard is installed in the lavatory servicing compartment.

CF

O0

105002_014

OFF OFF

DC PWR AC PWR CAB LTS ENT LTS

CABIN

ONON

REV 5

AIRPLANE GENERAL


CARGO BAY DOOR

DESCRIPTION

The cargo bay door is a plug-type door and is located forward of the left engine nacelle. The cargo door opens inward andupward to the overhead position above the doorway.

The cargo door is accessible from inside the aircraft through the passenger compartment but is not certified as an emergencyexit.


The cargo door assembly consists of a direct-coupled inner and outer handle, trigger-lock mechanism, fore and aft lockingpin, balance springs and cables, and a roller/track assembly.

To open the door from inside the aircraft, raise the spring loaded cover on the center of the handle and push the handletowards the door pane and turn the handle clockwise. To open the cargo door from outside the aircraft, push the trigger-lock in the outer handle to release the handle from the recess in the door. Rotate the handle 90° counterclockwise to retractthe locking pins and open the door inward. As the door moves inward, the rollers engage into the door tracks allowing thedoor to be lifted and latched in the overhead position. A balance spring/cable assembly on each side of the door takes theweight off of the door as the door is lifted into the overhead position.

CARGO BAY DOOR ANNUNCIATIONS

A CARGO DOOR (C) CAS message is displayed if the aircraft is on the ground and the left engine run switch is selectedON. Otherwise, CARGO DOOR (S) CAS message is illuminated.

CF

O010

5002_002

(INSIDE)

DOOR

HANDLE

BALANCE SPRING/

CABLE (2)

ROLLER/TRACK

ASSEMBLY (2)

LOCKING

PIN (2)

V 4

AIRPLANE GENERAL


SERVICE DOORS

DESCRIPTION

The service doors allow accessibility to the various systems and components that require servicing and/or inspection.

REFUEL/DEFUELDOOR

OXYGEN FILL-AND-INDICATORDOOR

GROUND-POWERDOOR

REFUEL/DEFUELCONTROL-PANELDOOR

GROUND-AIRSERVICINGDOOR

BATTERYDOOR

COMMUNICATIONPANEL DOOR

LAVATORY-WASTE SERVICEDOOR

OUTFLOW VALVEDOOR

PASSENGER DOORSWITCH PANEL

AFT EQUIPMENTBAY DOOR

REV 1

AIRPLANE GENERAL


SERVICE DOORS (Cont)


GROUND-POWER DOOR

The ground-power door is located on the right side of the aircraft in the aft wing-fuselage fairing, and allows access to theservice panel for ground power supply.

OXYGEN FILL/INDICATOR DOOR

The oxygen fill/indicator door is located on the right side of the fuselage at the aft edge of the wing, and allows access forthe oxygen indicator and servicing.

REFUEL/DEFUEL DOOR

The refuel/defuel door is located in the forward right wing-fuselage fairing, and allows access to the refuel/defuel adapter.

REFUEL/DEFUEL CONTROL PANEL DOOR

The refuel/defuel control panel door is on the right side of the aircraft in the forward wing-fuselage fairing, and allowsaccess to the computer control panel for refueling and defueling.

LAVATORY WASTE DOOR

The lavatory waste door is located on the right side of the aircraft in the aft wing-fuselage fairing, and allows access to thelavatory-waste service panel.

COMMUNICATION PANEL DOOR

The communication door is located left of the nose wheel, and allows access to the ground communication panel.

OUTFLOW VALVE DOOR

The outflow valve door is located in the forward right wing-fuselage fairing and allows access to the outflow valve panel.

BATTERY BAY DOOR

The battery bay door is located on the left side of the aircraft in the aft wing-fuselage fairing, and allows access to the air-craft main batteries.

A proximity sensor on the battery access door prompts BATTERY BAY DOOR (C) CAS message if the door is not closed.

GROUND AIR SERVICING DOOR

The ground-air servicing door is located right of the centerline toward the rear of the fuselage, and allows access to theground air servicing connection.

REV 1

AIRPLANE GENERAL


SERVICE DOORS (Cont)

AFT EQUIPMENT BAY DOOR

The aft equipment bay door is located on the centerline of the aircraft at the rear of the fuselage. The door is hinged in frontand opens downward. The door has a lever-type latch mechanism. A support strut on the door can be connected to the fair-ing bracket to stabilize the door in the open position. The strut must be disconnected from the fairing bracket to close thedoor.

AFT EQUIPMENT BAY DOOR ANNUNCIATION

An AFT EQPT BAY DOOR (C) CAS message is displayed if the aft equipment bay door is not closed.

CF

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HINGES

LATCH

LEVER

FAIRING

BRACKET

STRUT

CLIP

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AIRPLANE GENERAL

Volume 2 Flight Crew Operating Manual Feb 22/200601-05-12 CSP 100-6 REV 5

DOOR WARNING SYSTEM

DESCRIPTION

The door warning system monitors the position of the following doors while the aircraft is on the ground or in flight:

- Passenger door- Emergency exit hatch- Cargo bay door- Aft equipment bay door- Battery bay door

COMPONENTS AND DESCRIPTION

A magnet with an electronic proximity sensor is mounted at each door. The proximity sensors interface with the proximitysensor electronic unit (PSEU), data concentrator unit (DCU), and the multifunction display. The flight crew receives a sin-gle chime and a visual CAS annunciation if a door is not in the correct position under specific conditions. For the specificconditions, refer to the annunciation description for each door in this section.

On the ground the CAS displays EMERGENCY EXIT (C) and other door warnings in amber. However, if the left engineis set to RUN, the PASSENGER DOOR (C) and CARGO DOOR (C) will also be illuminated. In flight, the door warningson the CAS are displayed in amber.

1

PROXIMITY-SENSOR ELECTRONIC UNIT

(PSEU)

DATA

CONCENTRATOR

UNIT

(DCU)

IN FLIGHTGROUND

PASSENGER

DOOR

HANDLE

EMERGENCY

EXIT HATCH

PASSENGER

DOOR

BAGGAGE

DOOR

BAGGAGE

DOOR

HANDLE

AFT

EQUIPMENT

COMPARTMENT

DOOR

BATTERY

BAY

DOOR

PASSENGER

DOOR

LOCK

AFT EQPT BAY DOOR

CARGO DOOR

PASSENGER DOOR

BATTERY BAY DOOR

EMERGENCY EXIT

PASSENGER DOOR

CARGO DOOR

EMERGENCY EXIT

AFT EQPT BAY DOOR

BATTERY BAY DOOR

REV 5

AIRPLANE GENERAL


EICAS MESSAGES

The following door and exit messages are shown on the EICAS. In the table below are the messages, meanings, inhibits,

and aural warnings along with a brief explanation of each message.

MESSAGE INHIBITS MEANINGAURAL

WARNING

AFT EQPT BAY DOOR TO/LANDThe electronic proximity sensor is indicating that the aft equipment bay door is not in the correct position when on the ground or in flight

BATTERY BAY DOOR TO/LANDThe electronic proximity sensor is indicating that the battery bay door is not in the correct position position when on the ground or in flight

CARGO DOOR TO/LANDThe electronic proximity sensor is indicating that the cargo door is not in the correct position posi-tion when the airplane is in flight

EMERGENCY EXIT TO/LANDThe electronic proximity sensor is indicating that the emergency exit is not in the correct position position when in flight

PASSENGER DOOR LANDThe electronic proximity sensor is indicating that the passenger door is not in the correct position position when in flight

CARGO DOOR TO/LANDThe electronic proximity sensor is indicating that the cargo door is not in the correct position posi-tion when the airplane is in on the ground

PASSENGER DOOR TO/LANDThe electronic proximity sensor is indicating that the passenger door is not in the correct position position when the airplane is in on the ground

REV 4

Documents

Bombardier Challenger Global 00-Airplane General