Global Express-Airplane General

INTRODUCTION

The BD-700 Global is a swept-wing monoplane with a pressurized cabin. It is capable

of accommodating a pilot, a copilot, a third crew member and up to 19 passengers. The

airplane has two BMW/Rolls Royce BR710 turbo fan engines.

The airplane structure, in general, is fabricated from aluminum alloys. Alloy steels,

stainless steels, titanium, and composites are also used.

Attention and strict processes are given to surface finishes, protection against

corrosion and to external surface smoothness throughout the airplane. Sealing

requirements include environmental sealing, protection of facing surfaces (similar and

dissimilar) against corrosion, pressure sealing and integral fuel tank sealing.

At sea level, the airplane and its installed equipment is certificated for operation in

ambient temperatures ranging between -30°C (-22°F) and +50°C (122°F). The

airplane pressurization system is certificated for operations up to a maximum pressure

altitude of 51,000 feet.

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_01_001

Elevators

HorizontalStabilizer

Thrust ReverserDoors

Outer Skin

Rudder

Flaps Aileron

Winglets

Fairing

Fwd EquipmentCompartment Doors

Radome

Cabin Floor

MultifunctionSpoilers

Vertical StabilizerFairing

Engine Cowl

Ram Air TurbineCompartmentDoor

Bird StrikeBarrier

WheelBins

BellyFairings

MLG Doors(inner)

Vertical StabilizerLeading EdgeSide Panels

DorsalFairing

Glass

LEGEND

Hybrid (Mainly Graphite)

Graphite

Kevlar

Bombardier Global Express - Airplane General

AIRPLANE DIMENSION SCHEMATIC (Global 5000 – see Appendix 1)

1

NOTEFor A/C 9002 to 9126 preSB 700-23-001. Measurementat manufacturer’sempty.

For A/C 9002 to 9126 postSB 700-23-001 and A/C 9127and subs. Measurement atmanufacturer’s weight empty.

weight

23 ft 6 in(7.16 m) 13 ft 4 in

(4.06 m)

6 ft 0 in(1.83 m)

7 ft 4 in(2.24 m)

13 ft 4 in(4.06 m)

94 ft(28.65 m)

10 ft 1 in(3.07 m)

31 ft 9 in(9.68 m)

21 ft 1 in(6.43 m)

4 ft 1 in(1.24 m)

8 ft 10 in(2.70 m)

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_01_002

3 ft(0.91 m)

86 ft 5 in(26.34 m)

5 ft 10 in(1.78 m)

99 ft 5 in(30.30 m)

24 ft 10 in(7.57 m)

25 ft 6 in(7.77 m)

1

2

PASSENGER COMPARTMENTINTERIOR DIMENSIONS

Length

Width (floor line)

Height

Volume

Floor area

Width centreline

48 ft 4 in

6 ft 11 in

6 ft 3 in

2100 ft³

335 ft²

8 ft 2 in

(14.73 m)

(2.11 m)

(1.91 m)

(59.47 m³)

(31.10 m²)

(2.49 m)

1

2

42 ft 7 in(12.98 m)


DESCRIPTION

DIMENSIONS AND GENERAL DATA

The data that follows is for general information only, and is not to be used for

inspection or rejection purposes. When specific data is required, the applicable

illustration should be used.

Overall Dimension

Length 99 ft. 5 in. (30.30 m)

Height 24 ft. 10 in. (7.57 m)

Wing

Span 93 ft. 6 in. (28.50 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 side. Single 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)

(Global 5000 – see Appendix 1)


Fuselage

Diameter 8 ft. 10 in. (2.69 m)

Length 86 ft. 5 in. (26.34 m)

Landing Gear

Main Gear Nose Gear

Wheel Size 19 in. 10 in.

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.) 42 ft.10 in. (13.06 m)

Areas

Equivalent wing area (including 1022 sq.ft. (94.95 sq.m)

ailerons, flaps, spoilers and area

within the fuselage

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. (1,88 m)

Width 3 ft. (0.91 m)

Height to sill (at floor line) 5 ft. 4 in. (1,63 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)


ANTENNA LOCATION SCHEMATIC

WARNING

PERSONNEL SHOULD NOT STAND NEARBY AND IN FRONT OF THE RADAR ANTENNA WHEN IT IS TRANSMITTING.

TCAS(Directional)

MODES1

MODES2

VHFCOMM #1

GPS #1

ADF #1

ADF #2

VHF COMM #3(if installed)

VOR/LOC(LH and RH)

SATCOM(if installed)

DME#1

MarkerBeacon

TCASOMNI

DME #2

MODE S1 & 2

VHFCOMM #2

RAD ALT# 1 TX

RAD ALT# 1 RX

RAD ALT# 2 RX

RAD ALT# 2 TX

ELT(Optional)

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GlideslopeWeather Radar


VISUAL EYE REFERENCES FOR GROUND OPERATION

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NOT FOR LANDINGAPPROACH VISIBILITY10.22 ft

(3.14 m)

39.58 ft(12.18 m)

10.42 ft(3.21 m)

8.5 ft(2.62 m)

27°

15.5°

PILOT’S EYEPOSITION

MAXIMUM 135° VISION AFTWITH HEAD ROTATED

PILOT’S EYEPOSITION

45°

33°33°

45°

25°25°

28°28°

1.58 ft(0.49 m)

PILOT’SEYEPOSITION

CL

WITH HEAD MOVED0.42 ft (0.127 m)OUTBOARD


STEERING RADII

Steering radii shown below is for Global Express only.

Steering radii for the Global 5000 can be found in Appendix 1.

STEERING RADII SCHEMATIC

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_01_006

42 FT 10 IN(13.10 m)

68 FT 0 IN(20.73 m)

20 FT 8 IN(6.3 m)

7 FT 4 IN(2.3 m) 14 FT 0 IN

(4.26 m)

MINIMUMPAVEMENT

WIDTH180 DEGREE

TURN

128 FT 2 IN(39.07 m)56 FT 6 IN

(17.24 m)

53 FT 2 IN(16.23 m)

45 FT 2 IN(13.78 m)

NOTE

MAXIMUM STEERING

Symmetrical and idle thrust

No differential braking

75 deg. steering angle

3 deg. slip

Dry runway

Slow continuous turn

Max A/C weight

AFT CG


TURNING RADII

Global Express: Minimum paving width for 180° turn - 68 feet (20.73 m)

Global 5000: Minimum paving width for 180° turn - 65 feet 4 in. (19.92 m)

TURNING RADII SCHEMATIC

CL

0°20°25°30°35°40°45°50°55°60°

65°70°

75°

MAX

R2

R1

TURNING CENTERS

TURNING RADII SHOWNREPRESENT THE THEORETICALGEOMETRIC TURNING CENTERS

R5 R3

R4

R6NOTE:Actual operating data will be greaterthan values shown since tire slippageis not considered in these calculations.

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JET EXHAUST TWO ENGINE GROUND IDLE THRUST

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0

(15.24)

(30.48)

(45.73)

(61.00)

(76.22)

50

100

150

200

250

150 mph(241.40 kph)

62 mph(100.00 kph)

34 mph(54.72 kph)

102 mph(164.15 kph)

JE

TE

XH

AU

ST

KE

EP

-OU

TZ

ON

ES

TW

O-E

NG

INE

OP

ER

AT

ION

GR

OU

ND

IDLE

TH

RU

ST

AXIAL DISTANCE

(METERS) FEET

TO 275 FT (83.84m)


JET EXHAUST TWO ENGINE TAKEOFF THRUST

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0

(15.24)

(30.48)

(45.73)

(61.00)

(76.22)

50

100

150

200

250

150 mph(241.40 kph)

62 mph(100.00 kph)

34 mph(54.72 kph)

102 mph(164.15 kph)

JE

TE

XH

AU

ST

KE

EP

-OU

TZ

ON

ES

TW

O-E

NG

INE

OP

ER

AT

ION

TA

KE

OF

FT

HR

US

T

AXIAL DISTANCE

(METERS) FEET

TO 275 FT (83.84m)


AIRPLANE JACKING

Three jacking points are provided, one on the forward fuselage and one on each wing

rear spar for jacking the complete airplane.

JACKING POINTS

The nose jacking point is located on the fuselage centerline. Gear jacking points are

also provided for tire/wheel/brake changes. Jacking procedures are located in the

Aircraft Maintenance Manual (Chapter 7).

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NylonPlug

Rear Fuselage

SupportTypical Jack

JackingPoint

JackPad

LEGEND

Jack

Rear Fuselage Support


TOWING

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

NOTE

Disconnecting the nosewheel steering torque links is required for all towing operations.

TOW BAR ATTACHMENT

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TOW BAR ASSEMBLY


GROUND LOCKING SAFETY PINS

Ground safety locks are provided for the nose and each main gear, gear doors, and for

the Ram Air Turbine (RAT). Refer to the applicable chapter for the safety pin

installations.

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

45° 45°

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Jacking Pad

30.25° 30.25°

Tie Down Ring

Main and Nose AreasMooring Adapter Plate

Tail Area


AIRPLANE DOORS

The airplane is equipped with one passenger door (which serves as an emergency

exit), one overwing emergency exit, one baggage compartment door, one rear fuselage

equipment bay door and several service doors and panels.

The door warning system provides the flight crew with a visual indication (EICAS)

when any of the following exterior doors/exits are open or incorrectly latched:

• Passenger Door

• Cargo Door

• Aft Equip Bay Door

• Emergency Exit

Description and operation of the emergency features of the wing emergency exits are

in the Emergency Equipment chapter.

The door warning system also provides the flight crew with a visual indication (status

page) when any of the landing gear doors are not in their commanded position.

Description and operation of the landing gear doors are found in the Landing Gear/

Brakes chapter.

PASSENGER DOOR

The passenger door is the main entrance/exit for passengers as well as flight crew and

is located on the left side of the airplane, aft of the flight compartment. The door is a

mechanically balanced airstair with an attached door. The door assembly which opens

outwards and downwards, turn 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, and extend and retract as the door opens and closes.

The door operation is power assisted with a cable system and a DC electric motor. The

door locking mechanism is capable of operations from inside and outside the airplane.

A single operation from either handle will unlock the door and lift it clear of its

latching mechanism.

The door assembly opens under a controlled descent through a tension spring

arrangement and mechanical damping using a pulley and cable mechanism.

The door is normally closed from inside or outside of the airplane through an electrical

actuator. The door 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 of the 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 to illuminate the door area and in each step riser to illuminate the

steps, automatic shutoff is provided when the door closes.


PASSENGER DOOR SCHEMATIC

PASSENGER DOOR COMPONENTS

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

door operating system.

LIFT ARMS

Two levers are connected from either end of the lockshaft to the fixed linked arms on

the airstair structure. They are driven by the handles and assisted by the tension spring.

Their purpose is to lift the 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 in relation to the airstairs and

prevent any upward movement in the door frame during turbulence, or negative “G”

flight.

CLOSED POSITION

Handrail

CableAssembly

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VENT FLAP

A pressurization vent flap is centrally located at the top of the door under the

lockshaft. The flap prevents pressure building up until the “G” locks engage. Once the

locks are in and the flap is shut, the pressure holds the flap firmly shut. The vent flap is

opened by the lockshaft mechanism as the “G” locks are disengaged to prevent any

residual pressure from the pressurization system.

LOCKED INDICATION

Visual indication of latching and locking is given by an indicator arm that is driven

directly by the last motion of the internal handle. The indicator, in the form of a green

line, lines up with a green line on the airstairs only after the door latches and detents

are engaged. The indication is viewed through a window cutout in the internal handle

cover. A safe indication is indicated by the alignment of the two green lines. A

window in the handle exposes a red fixed plate when the handle is out of the safe

locked position.

PASSENGER DOOR OPERATING HANDLES

The external handle is set into a box in the lower door structure. It is connected by

push/pull rods inside the door to the lockshaft, at the forward end.

Lift Arm

Aft “G” Lock

Vent Flap

Forward “G” Lock

Locking HandleGX

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EXTERNAL HANDLE

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 and reduces the load on the handles.

The internal handle is a lever on the forward side of the door directly attached to a

lockshaft and to the forward door lift arm.

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Lockshaft

Note: The door is not in the fullyclosed position until the handlemoves to the full down position.


INTERNAL HANDLE

NOTE: Handle shown in the locked(stowed) position. The door is not inthe fully closed position until thehandle moves fully down.

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PASSENGER DOOR SWITCHES

The internal door operating switch is controlled on and off by the “DOOR” switch

installed internally in the door frame, next to the main passenger door.

The external door operating switch is controlled on and off by the “DOOR” switch

installed next to the main the main passenger door.

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INTERNAL SWITCH(View looking from insidethe airplane)

EXTERNAL SWITCH

Note:Both switches are guardedbut not shown.(Green aircraft switches shown)


EXTERNAL DOOR SWITCH ACCESS PANEL

PASSENGER DOOR OPERATION

The following examples are intended to familiarize the operator with events which

occur when moving the passenger door from either the open, or closed positions. The

door operations are described in detail and should be followed as per Aircraft

Maintenance Manual, Chapter 52.

EXTERNAL DOOR OPERATION

To open the passenger door externally:

• Push flap in

• Grasp handle

• Lift fully to open

• Pull outwards

To close the passenger door externally:

NOTE

Do not recycle the handle during closing operation without reopening door sufficiently to rearm door uplock lever.

• Press and hold door close switch

• Pull handle downwards to stow

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DOOR OPERATION

TO OPEN

PUSH FLAP IN GRASPHANDLE LIFT FULLY TOOPEN PULL OUTWARDS

1.OPERATE SWITCH TOROTATE DOOR FULLYINTO DOOR APERTURE

2.PULL HANDLE DOWN-WARDS TO STOW

NOTE: DO NOT RECYCLE HANDLE DURINGCLOSING OPERATION WITHOUT REOPENINGDOORS SUFFICIENTLY TO REARM DOORUPLOCK LEVER.

TO CLOSE

OperatingInstructions

DOOR OPERATINGSWITCH


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:

• 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 be brought into the cabin. The rope can be pulled, rotating the torque

shaft and raising the door via the normal cables. Once the door is raised, it may be

lowered into the frame and locked by the normal method with the lock handle.

BAGGAGE COMPARTMENT DOOR

A baggage compartment plug type access door is installed in the fuselage aft section

on the left side forward of the rear pressure bulkhead.

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 emergency exit. The door moves inward and upward to a stowed position

above and clear of the door aperture.

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Aft PassengerCompartmentBulkhead

CargoCompartment

CargoDoorOpening

BAGGAGECOMPARTMENTINTERIOR

DoorHandle


The latch mechanism consists of inner and outer handles (directly coupled together)

and are mounted on the forward and aft sides of the door. The handle contains a trigger

lock which holds the handle in the stowed position. The door is latched when the

exterior handle is rotated to engage latch pins and locked when the handle is stowed

and latched in its housing recess.

A vent door is located in the upper portion of the door and will not close until the door

is fully closed and the handle stowed in the locked position.

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Cargo Door

Outer Handle

PushTrigger

Door Handle Recess

StowedPosition

CargoDoorOpening

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Vent Door/seal

InteriorDoor Handle

ReleaseButton


BAGGAGE DOOR OPERATION

CLOSING THE BAGGAGE DOOR EXTERNALLY - Rotate the outer handle 90

degrees to latch the door. Push the handle into the recessed housing until the trigger

button is latched into the trigger mechanism.

CLOSING THE BAGGAGE DOOR INTERNALLY - Rotate the inner handle 90

degrees counter clockwise to latch the door. Pull the handle until the outer handle

trigger latches into the trigger mechanism, and the handle is stowed into the recessed

housing.

OPENING THE BAGGAGE DOOR EXTERNALLY - Press the trigger button to

release and eject the outer handle from the recessed housing. Rotate the handle 90

degrees counter clockwise to unlatch and open the door.

OPENING THE BAGGAGE DOOR INTERNALLY - Press the release button on the

inside handle to 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 door in place and the exterior handle is in

the stowed and locked position in the handle recess.

AFT EQUIPMENT BAY DOOR

The unpressurized aft equipment bay is accessed by a maintenance door in the

fuselage fairing. The door is horizontally hinged at its forward edge and swings down

and forward. When the door is opened, it is restrained from over travel and striking the

belly fairing using two door to fairing mounted lanyards.

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


AFT EQUIPMENT BAY DOOR SCHEMATIC

During the closing cycle two rollers, one on either side of the door, act as guides to

locate and center the door within its belly fairing aperture.

AFT EQUIPMENT BAY DOOR OPERATION

DOOR OPENING - Door opening is accomplished by depressing the trigger and

pulling the handle to the full open position.

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 by returning the handle flush with the door.

Visual indication of secure latching and locking is given by the door, the push trigger

and the external handle all being flush with the fuselage’s surface.

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Door LatchHandle Assembly

Lanyard

LatchMachanism


EMERGENCY EXIT

An overwing plug type emergency exit is installed on the right side of the airplane.

The exit 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 exit operating handle.

Two lower hook fittings and two upper latch fittings position the door in the door

opening. Three stop fittings on each side of the door and surround structure react to the

pressurization forces of the plug door type.

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EMERGENCYEXIT DOOR

G_ag

036_A

Latch Fitting

Quick ReleaseLatch Mechanism

Hand Hold

Hook Fitting

Door StopBoth Sides

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_01_037


When the door is removed, handling is facilitated by an interior hand hold, housed

flush within the door box structure.

To unlatch the emergency exit door from the interior, the upper door handle is pulled

inward. This motion opens the exterior push plate/vent flap to bleed any residual

pressure, and disengages the two latch pins. The door moves inward and pivots on the

lower hook fittings. A grip of the upper handle is maintained while grasping the lower

hand grip and the door is lifted inwards away from the door opening.

To unlatch the emergency exit door from the exterior, the upper push plate/vent flap is

depressed to disengage the latch pins, and the door is pushed inwards away from the

opening.

Visual indication of a locked condition of the overwing emergency exit in position is

with the interior handle recessed in the surround structure.

DOOR INDICATION AND CONTROL

The airplane door position and locked indication is provided to the EICAS by the

Landing Gear Electronic Control Unit (LGECU). The LGECU provides data that is

used to generate alerts and synoptic displays for the fuselage doors.

Door position information is displayed on the STATUS page, and message information

is displayed on the EICAS page.

The STATUS page presents the following doors:

• PASSENGER

• EMERGENCY OVERWING EXIT

• BAGGAGE

• SERVICE DOORS

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PUSH IN FLAPPUSH DOOR INWARD


STATUS PAGE

Passenger Door

The passenger door is monitored by three proximity sensors to determine the locked

and handle stowed position. They are located on the passenger door forward and aft

latch to monitor the “G” latch position and in the passenger door to monitor the outer

handle stowed condition.

The sensor information is used by the LGECU for door position 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 closed position.

Baggage Door

Two proximity sensors monitor the door position and provide signals to the LGECU

which in turn provides the EICAS display.

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SERVICE DOORS

Overwing Emergency Exit

Baggage Door Passenger Door

SERVICE DOORAnnunciation

AIRPLANE DOOR POSITION AIRPLANE DOOR GRAPHIC

CLOSED

OPEN

INVALID


Large Maintenance Doors

Two (optional third) separate large hinged and latched maintenance hatches are

monitored by the LGECU. 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 on the 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

maintenance hatches 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 storage access door

Aft Equipment Bay

An electrical proximity sensor provides indication to the EICAS system when the door

is properly closed. 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/small service doors is not properly closed.


SEAT ASSEMBLY

The crew seats provide adjustments fore and aft, inboard/outboard lateral adjustment

(at full aft position via a “J” track) height and armrest position.

InertiaReels

Fwd/AftControl

InertiaReelsControl

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Headrest

Shoulder Straps

Quick ReleaseBuckle

Armrest

Waist Straps

Flight Crew Seat

Lumbar Support

Crotch Belt

Up/DownLever

Seat ReclineLever

LumbarAdjustment

Top

Mid

Bottom

ArmrestAdjusment


EYE LOCATOR - SEAT ADJUSTMENT

An eye locator is mounted on the center windshield post to enable seat adjustment for

correct eye-to-wheel height.

FRONT VIEW

TOP VIEW

Note: The supportbracket is not shown.

PIL

OT’

S

SIG

HT

LINE C

OPILO

T’S

SIG

HT

LINE

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CONTROL WHEEL

The pilot and copilot control wheels contain the following switches:

• Master disconnect

• Pitch Trim Switch

• Autopilot/Flight Director Touch Control Steering Switch

• Radio Key

MASTER DISCONNECT

The Master Disconnect switch disengages the autopilot and deactivates the stick

pusher and the pitch trim. When released, the stick pusher and the pitch trim system

are immediately reactivated but the 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 STEERING) SWITCH

The Touch Control Steering Switch (TCS) is located on the control wheel. It enables

the pilot to maneuver the airplane without disconnecting the autopilot control.

RADIO KEY

The Radio Key activates the selected radio transmitter.

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NOSE DN

N

OS E UP

DIS C

M

ASTER

TCS

IC

R/T

1

23

(Radio keylocated behind)

1. Master Disconnect2. Pitch Trim Switch3. Autopilot/Flight Director

Touch Control Switch4. Radio Key

Indicates Chapter in which information on item may be found.

1010

2

26


SYSTEM INTEGRATION

The extensive use of the latest technology for design and operation makes the BD 700

Global one of the most advanced passenger aircraft in the world. Contrary to previous

generation passenger airplanes, which relied on analog technology for system control

and indication, the Global uses computers almost exclusively to monitor all airplane

systems and to provide crew alerting information. This use of computer technology,

with its associated digital data busses and control units, has simplified many of the

traditional flight crew duties and has reduced pilot workload tremendously.

System information that previously came from analog sources, is now provided by a

variety of control units that constantly update and share information. The systems in

the Global have built-in redundancy and provide an added margin of safety for all

operations.

All the airplane systems are designed to self-test on start-up and are continuously self-

monitored in flight. Should a fault occur, the information is analyzed and compared

with data provided by associated systems before being displayed to the flight crew.

This method of operation ensures that accurate malfunction analysis is made and

appropriate corrective action, by either the flight crew or maintenance personnel, can

be taken.

MAJOR SYSTEMS

The major contributors to this technology are the following:

EICAS

The Engine Indication and Crew Alerting System is controlled through a Central

Display System that processes airplane data and information. This system monitors all

vital information and displays the appropriate indications to the flight crew.

EPGDS

The Electrical Power Generation and Distribution System monitors and controls the

airplane electrical system.

FADEC

The Full Authority Digital Engine Control System interfaces with the various airplane

systems to provide total control over the two engines through their entire operating

regime.

EFIS

The Electronic Flight Instrument System provides flight instrument and navigation

information to the crew through two primary flight displays (PFDs) and two multi-

function displays (MFDs).


FMQGC

The Fuel Management Quantity Gauging Computer continuously monitors the various

fuel parameters for quantities and distribution. This system provides proper fuel

scheduling and fuel balance during the entire flight. The fuel system computer also

alerts the flight crew should a fault occur in the system.

IAMS

The Integrated Air Management System controls and monitors the airplane bleed-air,

environmental, cabin pressurization and anti-ice systems.

FMS

The Flight Management System allows the flight crew to select and display airplane

navigation both laterally and vertically. The system can also provide automatic tuning

of navigation receivers and manual tuning of communication transceivers.

AFCS

The Automatic Flight Control System is an integrated autopilot, flight director and

yaw damper. The system also controls various airplane flight modes and provides

airplane guidance.

EFCS

The Electronic Flight Control System controls the airplane multi-function spoilers,

ground spoilers, horizontal stabilizer trim, as well as the pitch feel control and the

rudder travel-limit control.

CAIMS

The Central Aircraft Information Maintenance System is a modifiable, distributed

maintenance system. This system provides means for maintenance and flight crew to

view history of individual airplane system faults, run LRU tests, and display and

download real-time data.


FLIGHT COMPARTMENT GENERAL ARRANGEMENT (Global Express shown)

WARNINGPRESSURE DIFFERENTIALSHALL NOT EXCEED .1 PSIDURING TAXI AND 1.0 PSIUPON INITIAL LANDING

OFF

ON

CABIN PWR

O

WINDSHIELD HEATL

ONOFF/

RESET

RON

OFF/RESET

ELECTRICALEXT AC

AVAIL

ON

FAIL

OFF

GEN 1

FAIL

OFF

EXT DC

AVAIL

ON

GEN 3 GEN 4

FAIL

OFF

GEN 2

FAIL

OFF

PUSH OFF/RESET

PUSHOFF/RESET

APU GEN

FAIL

OFF

RAT GEN

ON

OFF

BATT MASTER

EMS

OFF

ON

O

HYDRAULIC

R HYD SOV

CLOSED

L HYD SOV

CLOSED

AURAL WARNING

PUSH TO MUTE

IAC 1 IAC 2

MUTED MUTED

PASS SIGNSNO SMKG SEAT BLTS

OFF

ON

AUTO

OFF

ON

AUTO

EMER LIGHTS

OFF

ON

ARMAA A

LANDINGNLGL WING R WING

TAXI/RECOGWINGTIP

NAV BEACON STROBE WING INSP LOGO

OFF

ON

OFF

PULSE

STEADY

OFF

PULSE

STEADY

OFF

PULSE

STEADY

OFF

WINGTIP

ON

OFF

WHT

ON

OFF

ON

OFF

ON

OFF

ONO

EXTERNAL LIGHTS

OOOO

S OSS

HYDRAULIC1B 3A 3B 2B

OFF

AUTO

OFF

ON ON ON

ON

OFF

AUTO

OFF

AUTOAAOA

APU

RUNOFF START

ENGINE

ENG START

IGNITION

ON

AUTOL CRANK R CRANK

FUELR

WING FEEDINHIBIT

LWING FEED

INHIBIT

XFEED SOV

FAIL

OPEN

AUX PUMP

OFF

PRI PUMPS

OFF

L RECIRC

ON

AUX PUMP

OFF

PRI PUMPS

OFF

R RECIRC

ON

AFT XFERAUTO

OFF ON

OFF

AUTOWING XFER PACK CONTROL

L MANTEMP

R MANTEMP

BLEED/AIR COND

TEMPERATUREFWD CABIN

NORM

MAN

LO HIGH

R ENG BLEEDL ENG BLEED

ANTI-ICEL COWL R COWLWING

WING XBLEED

COLD HOT

APU BLEED

AUTOCLSD OPEN

XBLEED

L PACK R PACK

FAIL

OFF

FAIL

OFF

TRIM AIRRECIRC

OFFOFF

AUTOOFF ON

AUTOOFF ON

LD HO

RAM AIR

AUX PRESSHOT

COLD

HOT

COLD

ON

ON

AUTOOFF ON

AUTO AUTOAUTOOFFOFF OFFONON ON

AUTOFROM L FROM R

AFT CABIN

COLD HOTLD HO

COCKPIT

COLD HOTLD HO

TO FLY N 45 E 135 S 225 W 315

STEER

STBY COMPASS WITH ALL RADIOS ON SWUNG / / BY

N 3336 30

DISCH

PULL

1 2

LPULL

APU

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1 2

DISCH

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OUTFLOW VALVE

PRESSURIZATION AUTOMAN

LDG ELEV RATEMAN ALT

1

CLOSED

2

CLOSED

AUTO/MAN

MAN

EMERGDEPRESS

ON

DITCHING

ON

MAN

FMS

UP

DN

HIGH

NORM

UP

DN NF

ELT

ARM/RESET

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

AR

AIRSPEED LIMITS - (INDICATING SPEEDS)VSE (SLATS OUT, 0°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 6°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 16°FLAPS) . . . . . . . . . . .VFE (SLATS OUT, 30°FLAPS) . . . . . . . . . . .VA (MANEUVERING)(AT SEA LEVEL @ 96,000 LB) . . . . . . . . . . .(AT 20,000 FT @ 78,600 LB) . . . . . . . . . . . . .

VMOVMOMMOMMOMMOMMOVLOVLOVLE

(BELOW 8,000 FT) . . . . . . . . . . . . . .(8,000FT TO 30,267 FT) . . . . . . . . . .30,267FT TO 35,000 FT) . . . . . . . . . .(AT 41,000 FT) . . . . . . . . . . . . . . . . .(AT 47,000 FT) . . . . . . . . . . . . . . . .(AT 51,000 FT) . . . . . . . . . . . . . . . .(EXT) (L/G EXTENSION) . . . . . . . . .(RET) (L/G RETREACTION) . . . . . .(L/G EXTENDED) . . . . . . . . . . . . . . .

225210210185

254250

300340

0.890.88

0.8580.842

200200250




225210210185

254250

300340

0.890.88

0.8580.842

200200250

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L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF

GLD MANUAL ARMPARK/EMER BRAKE ON

<– FUEL XFER ON

TOTAL FUEL (LBS) 415OO

1.54

146OO 146OO1OOOO

N2

FF (PPH)

OIL TEMP

OIL PRESS

93.4575O11581

1.65

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START START

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1.54

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180

170

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HoneywellHoneywell

13000.00

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13 13

2019 20

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OXYGEN

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FWDCABIN (°C)

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OPEN OPEN

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LDG ELEV

00

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1 2

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ENG

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BRAKE TEMP

11.5

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APU

Honeywell

WX

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FMS1360

N

5 5

3

6

33

30

- 02

- 02

+ 12- 04

KABC

KLM

KKLM

TOC

TOC

GHJ

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DEF

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4000 4000

FL180

+ 09

Honeywell

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11:1350

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BRT

CIRCUIT BREAKER SYSTEM

STAT SYS BUSPREVPAGE

NEXTPAGE

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BUS

EMERCONT

DC 1

DC ESS

AC ESS

BATT

CIRCUIT BREAKER - SYSTEM 1/2

AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

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FUEL

M

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NEXTPAGE

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BUS

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DC ESS

AC ESS

BATT


AFCS

AIR COND/PRESS

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COMM

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ELEC

ENGINE

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FUEL

M

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MODE

INT

CHR

11:1350

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MACH TRANSDUCERRANSD

PITOT

CLOSED

STATIC

CLOSED

SELECT POWER

LEFT AUX RIGHT

SYSTEM SELECT FAULT

ON

FROM TO WPT

WPTLEGCHG

XTKDTK

WDWS

DISTIM

HDGSTS

POSTKGS

1MT2

BRTDIM3 TST

ENTBCK

0 CLR

7 S8

9

W4

5E6

1N2

3

88888

88

8 8888888

OXYGEN SUPPLY LOWERDISCONNECT

ON

OFF

OXYGENMASK

PRESSTO

TESTAND

RESET

EROS

EMERGENCY

100%PUSH

MASTERWARNING/CAUTION

ROLL SPLRS

PLT CONT

ROLLSEL

PLTROLL

WARNING

CAUTION

DIMOFF

BRT

HUD


ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL

WARNING

CAUTION

MINIMUMSBARO HpaRAD IN

BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


BARO SET

PUSH STD

NAV SRC

BRG V/L BRGFMS

HSI

Honeywell

SPD MANFMSCRS 1 CRS 2

PUSH DCT PUSH DCT

ALTHDG

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UP

P

I

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FD FDAP

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MICHDPH

HEADSET

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N

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DIS C

M

ASTER

MIC

NO

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N O S EUP

DIS C

M

ASTER

MIC

MIC HDPH

HEADSET

GX

_01_018

13 13

3

2

1

4

5

6

14

Flight Bag StoragePilot’s Side ConsolePilot’s Side PanelPilot’s Instrument PilotEICAS DisplayGlareshieldOverhead Panel

Standby InstrumentsSystems DisplayCopilot’s Instrument PanelCopilot’s Side PanelCopilot’s Side ConsoleControl WheelPedestal

1.2.3.4.5.6.7.

8.9.

10.11.12.13.14.

7

8

9

10

11

12

PU

SH

TO

CL

OS

EO

PE

NP

US

HO

PE

NP

US

H

PPRADV

TEST

ALRTRST

OFF

FAULT

LOWPPR

THERAPEUTICOXYGEN

ON

PASSENGER OXYGEN NORMAL

CLOSED OVERRIDETEST PORT

PASS. ON

COCKPIT VOICE RECORDER MICROPHONE MONITOR

ERASE

STATUS

TEST

HEADPHONE

OXYGENMASK

PRESSTO

TESTAND

RESET

EROS

EMERGENCY

100%PUSH


ON

OFF

TRANSMIT EMER

VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

SPKROFF

MIC M SKA

HISENS

LOSENS

VHF 3

BOTH

ID

VOICE

EGPWS

TERRAIN

OFF

G/S WARN

MUTED

FLAP OVRD

OVRD

NL NR

CH1 CH2STAB

RUD

PUSH OFF/RESET

AILTRIMS

RWD

LWD

OFF OFF

SKP

RCL

PAG

ENT

TCAS MENU TERRMAP

PLAN

NAV

APT

EMERNORM ABN

TCAS MENU

EMER

TERRMAP

PLAN

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APT

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SKP

RCL

PAG

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RADAR LSS TILTTST

FP

GMAP CLRTST

SBY OFFRCT LXWX SBY

PULLACT

+

–GAIN

MIN MAX

PULLVAR

TRB STAB TGT SECT

OFF

RADAR TILTTST

FP

GMAPSBYRCTWX

PULLACT

+

–GAIN

MIN MAX

PULLVAR

TRB STAB TGT SECT

OFF

IRS 3IRS 1 IRS 2

NAVNAV NAVALNALN ALN

OFFOFF OFF

ATTATT ATT

FLOOD

DISPLAY

COCKPIT LIGHTS

L

L

OFF

DIM

OFF

DIM

OFF

DIM

BRT

BRT

BRT

BRT

BRT

BRT

CTR

CTR

R

R

IRS ADC ADC IRS

SG 3

EICAS

SG 2SG 1

PFD 1

ALTN 3

ALTN

ALTN 1

ALTNALTN

ALTN

NORM

NORM

NORMNORM

NORM

PFD 1 PFD 2

PFD 2

ALTN 2 ALTN NORM

ENGINE

RL

EPREPR

N1N1

EP

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AUTO BRAKE

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MED

HI

MANUAL ARM

OFF

A

F

UP

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DN LCKRELEASE

LDG GEARNOSE STEER

HORN

BTMS OVHTWARN RESET

EVENT

ARMED

OFF

MUTED

STAT

HYDAC

ELECBLEED

AIRCOND

DCELEC

FUELFLT

CTRL

SCROLL

EICAS

SYSTEM SELECT

NORMMFD 2MFD 1

PARK/EMER

BRAKEPARK/EMER

BRAKE

LG

PU

LL

PU

SH

FU

LLY

TO

ST

OW

COCKPIT LIGHTS

LDIM BRTM BRDIM BRTM BR DIM BRTM BR

INTEGRAL

CTR R

CBDIM BRTM BR DIM BRTM BR

OVHDMASTER

PBA EYE REF AREA FLOOR

AUTO

DIM ON DIM ON

OFF

BRT OFF OFF OFF

O

B O O O

ON

BRT

SLAT

6

16

30

0

0

OUT

OUT

OUT

OUT

IN

FLAP

SLAT/

FLAP

MAXTHRUST

IDLEREV

MAX REV

ENGRUN

OFF OFF

RL

ELECT DC PWREMER OVRD

OVRD

NORM

TUNE

COM1 NAV1

121 .82 117 .45

118 .02 110 .00MEMORY-1

RANGE:

MEMORY-1

ATC/TCAS ADF1

1 2 0 0

1 2

NORMAL

1799 .5

1 5 4 2 3

1 5 6 0 0

1 ATC ALT ADF

LV

HF1TCAS DSPY 1

SQ

ID

DIM

PGE

1/2

TST

STO

DME

FLIGHTSPOILER

R

E

T

R

A

C

TMAX

1/2

FULL

0

1/2TUNE

COM1 NAV1

121 .82 117 .45

118 .02 110 .00MEMORY-1

RANGE:

MEMORY-1

ATC/TCAS ADF1

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1 2

NORMAL

1799 .5

1 5 4 2 3

1 5 6 0 0

1 ATC ALT ADF

LV

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SQ

ID

DIM

PGE

1/2

TST

STO

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VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

SPKROFF

MIC M SKA

HISENS

LOSENS

VHF 3

BOTH

ID

VOICE

TRANSMIT EMER

VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

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MIC M SKA

HISENS

LOSENS

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LAV CALL CABIN CALL CREW AREA PA

PUSH TO RESET

ON

CABINCALL

FWD AFT

LAVCALL

FWD AFT


FLIGHT COMPARTMENT (AFT VIEW)

PRESELINCR

DECR

CLOSE

START

STOP/SOVTEST

MANUAL AUTO

OFF

REFUEL

DEFUEL

REFUEL

REFUELNO AFT

LEFT CTR RIGHT

OPEN

AFT

MANUAL

REFUEL/DEFUEL PANEL

TOTAL PRESEL

LEFT RIGHTCENTER

AFT

OIL REPLENISHMENT

RESERVOIR

TANKLO

PUMPON

APU RH ENGLH ENG

POWER

SYSTEMON

LOOIL

LOOIL

LOOIL

VLVOPEN

VLVOPEN

VLVOPEN

DATAUPLOAD/DOWNLOAD

DAU 1AIAC 1

IAC 2IAC 3

GPWSSATCOM

SDU

GPS 1GPS 2

ADC 1ADC 2

ADC 3

DAU 1B

WXR

DAU 2ADAU 2B

DAU 3A

IRS 1IRS 2

DAU 3B

DAU 4A

DAU 4B

IRS 3

PRINT MAINTREPORT

OFF

HUMIDIFIER

ON

NORMAL

OXYGEN TEST

RESET

TEST

6 6

6

6

6

6

6

6

6

6

9

9

9

9

9

14

14

14

14

14

15

15

15

15

15

13

13

13

13

13

12

12

12

12

12

11

11

11

11

11

10

10

10

10

10

8

8

8

8

8

7 7

7

7

7

7

8

8

8

8

9

9

9

9

10

10

10

11

11 12

11 12

7

7

7

7

5 5

5

5

5

5

5

5

5

5

4 4

4

4

4

4

4

4

4

4

3 3

3

3

3

3

3

3

3

3

2 2

2

2

2

2

2

2

2

2

1 1

1

1

1

1

1

1

1

1

ENTRYHTR/FAN

CNTL

FWDMON

JUMPSEAT

LUMBAR

DC2 CBNPWR 3

ENTCOOL

AIR/GNDCNTL

CABIN TRU

ENTRY HTR

CHILLER

AFT TOILET COMP

FWD TOILET COMP

CREW

ENTRYDOME

AIRDUCT

60HzCNTL

LH

STAIRBOARD

FWD

LH UPPER

FWD

LINE

FWDLAV

RH

FWD

AFT

RH LOWER

AFT

TANK

AFTLAV

LINE 1

GALLEY

LINE 2

FWD

TANK

AFT

AFT

AFT

CNTLRS

DVD 1

FWD

TRU FEEDER

LAVORD

DVD 2

AFT

CNVTRFDR

28 VDC - DC CABIN FEED 1 115 VAC/400Hz - AC CABIN FEED 1

115 VAC/400Hz - AC CABIN FEED 1




28 VDC - DC CABIN FEED 2

28 VDC - TRU CABIN FEED

28 VDC - TRU CABIN FEEDDC2 PWR 2 BATT (SPDA3)

28 VDC - DC CABIN FEED 2CMS

T/S

WRDRB

CABIN ENTERTAINMENT

INTERIOR LIGHTS

115 VAC/60Hz - OUTLETS

EXTERIOR LIGHTS

WATER SYSTEMINDIR LTS

TOILETTANK HTRS

DRAIN/LINE HTRS

WATER HTRS MAST HTRS

FWD AFT

FANS MASTHTR

LAV

LAV

AUDIO AMPLIFIER

READ/TABLETOILET

1

2

2

5

1 5

7.5

5

5

5

5

2

2

3 5

5

5

5

5

1

2

5 5

5

FWD AFT

WATERTRTMT

1 1

3

5

7.5

5

3

5

3

5

5

1

7.5

3

3

50

1

3

5

20

J P

Q

R

T

S

L

N

M

CABINPWRMSTR

FWD

GALLEY

CELLCHGRS

EXTSVC

MID

ACCENT

FAX

WINGTIP

AFT

LH

CABIN

PULSE

FDR

AIRSHOW

RH

COFFEEMKR

FWDSYS

CKPTMON

AFT

MICRO-WAVE

CREWIND LTS

GALLEY

FWD

FWD

AFT

AFT

AFTSYS

FWDPUMP

AFTPUMP

2

10

7.5

3

10

5

5

3

10

5

7.5

1

20

3

5

10

3

3

5

10

3

10

3

15

3

15

5 5 51

5

1

5

3

K

5

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SLAT/FLAP

PWR 2

STABTRIMCH 2

ESSTRU 2

AC ESS BUS

20 15 15 15

6 9 14131211108754321

STBYPITOTHTR

AC BUS 4MONITOR

RATV/F

MONITOR

TATHT 1

L AOAHTR

PITOT 1HT B

PITOT 3HT

L ICEDETECTOR

R AOAHEAT

B

TATHT 2

LWINDOW

HEAT

2.5 5 7.5 7.5 52.5 7.5 5 7.5 157.5

E

F

6 9 131211108754321

LWSHLDHTR 1

LWSHLDHTR 2

SATCOMFREQUNIT

R AOAHTR

A

R ICEDETECT

PITOT 1HT A

A/TCTLR

AC BUS 1

2.5 7.5 2.57.5 20 205

6 9 131211108754321

SLAT/FLAPPWR 1

TRUBAYFAN

ESSTRU 1

15 20 2.5G

H

AVBATTRCCB

APUBATTRCCB

AV BATTHEAT

TATHT 3

RWSHLDHEAT 1

RWSHLDHEAT 2

TRU 2AV BATT

CHGR

PITOT 2HT

RWINDHEAT

TRU 1

6

6

6

6

8

8

8 109

7

7

7

5

5

5

5

4

4

4

4

3

3

3

3

2

2

2

2

1

1

1

1

AC BUS 2

AC BUS 3

DC

15

7.5 15

15 7.5

20205.5 5

STBYADI

2.5.5

A

B

C

D

GX

_01_019

1. Refuel/Defuel Panel2. Oil Replenishment Panel3. Cockpit Circuit Breaker Panel (CCBP)4. Halon Fire Extinguisher5. Data Upload/Download Panel6. Portable Breathing Equipment7. Crash Axe


1117

68

5

88

2

7

5

6

3

4

DATAUPLOAD/DOWNLOAD

DAU 1AIAC 1

IAC 2IAC 3

GPWSSATCOM

SDU

GPS 1GPS 2

ADC 1ADC 2

ADC 3

DAU 1B

WXR

DAU 2ADAU 2B

DAU 3A

IRS 1IRS 2

DAU 3B

DAU 4A

DAU 4B

IRS 3

OIL REPLENISHMENT

RESERVOIR

TANKLO

PUMPON

APU RH ENGLH ENG

POWER

SYSTEMON

LOOIL

LOOIL

LOOIL

VLVOPEN

VLVOPEN

VLVOPEN

PRINT MAINTREPORT

PRESELINCR

DECR

CLOSE

START

STOP/SOVTEST

MANUAL AUTO

OFF

REFUEL

DEFUEL

REFUEL

REFUELNO AFT

LEFT CTR RIGHT

OPEN

AFT

MANUAL

REFUEL/DEFUEL PANEL

TOTAL PRESEL

LEFT RIGHTCENTER

AFT

PRESELINCR

DECR

CLOSE

START

STOP/SOVTEST

MANUAL AUTO

OFF

REFUEL

DEFUEL

REFUELLEFT CTR RIGHT

OPEN

MANUAL

REFUEL/DEFUEL PANEL

TOTAL PRESEL

LEFT RIGHTCENTER

1 Global Express 1 Global 5000


PILOT’S SIDE CONSOLE

SELECT POWER

LEFT AUX RIGHT

SYSTEM SELECT FAULT

ON

FROM TO WPT

WPTLEGCHG

XTKDTK

WDWS

DISTIM

HDGSTS

POSTKGS

1MT2

BRTDIM3 TST

ENTBCK

0 CLR

7 S8

9

W4

5E6

1N2

3

88888

88

8 8888888


ON

OFF

OXYGENMASK

PRESSTO

TESTAND

RESET

EROS

EMERGENCY

100%PUSH

GX

_01_020

1. Oxygen mask/Regulator2. Headset Panel3. Navigation Display Unit4. Nosewheel Steering Handwheel5. Flashlight6. Data Loader7. Oxygen Cruise Mask Control

1614

58

2

5

FLASHLIGHT

HEADSETPANEL

FLASHLIGHT

Indicates Chapter in which informationon item may be found

MIC HDPH

HEADSET

1

7

6

4

3


PILOT’S SIDE PANEL

PUSHER

STALL

ON

OFF

ER

O

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

DC 1

DC ESS

AC ESS

BATT


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

M

SEL

RST

ET

CHR

MODE

INT

CHR

11:1350

01:43

GX

_01_021

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


6

710

13

1

23 4


PILOT’S INSTRUMENT PANEL

WX


SAT

GSPD

TERR

-56

TAT

TAS

-40

234

345

FAIL

LX

0 . 05L

MAG2HDG315

ETE 1+36

12 . 5NMKDVT

BELOWTCAS TEST

FMS1360

N

5 5

3

6

33

30

- 02

- 02

+ 12- 04

KABC

KLM

KKLM

TOC

TOC

GHJ

KGHJ

LUF

DEF

KDEF

4000 4000

FL180

+ 09

Honeywell

220

200

190

180

170

160

150

LIM HDG

9500

210 29.92 INBARO

FLCAP1

A/T1

VTA

SPD VAPP ASEL

M

0.856M

DTK360

HDG330

SRP

1000

VS 1000

54

MSG 0

1

2

3

1

2

3

9500

10500

10000

VOR 1VOR 2

ATT2ADC3

20 20

10 10

10 10

20 20

20

1300

200

1856

4

10400

20008060

95

N33

30

W24

21S

15

12

E6

3

H23.4NMFMS1

VOR1

Honeywell




225210210185

254250

300340

0.890.88

0.8580.842

200200250




225210210185

254250

300340

0.890.88

0.8580.842

200200250 G

X_01_022

1. Airspeed Placard2. Primary Flight Display3. Multifunctional Display

- MAP Format- PLAN Format- WX Radar- TCAS Traffic


7 16

1

2 3

CREW LIFE VESTUNDER SEAT

7 16


CENTER INSTRUMENT PANELS

STATIC GROUND OPERATIONPROHIBITED BETWEEN 66-80% N1

20

10

30

20

10

30

09

8

7

65

4

3

2

1100 FEET

ALT

1 00032

4

10 13

mb/hPa

29 9 2

IN HG

IAS KNOTS

220200180 250

BARO

GX

_01_023

Engine Indication and Crew AlertingSystem (EICAS) Primary Display

Note

• Engine Instruments• Caution and Warning Annunciator• Fuel Quantity• Flap/Slat and Spoiler Status• Landing Gear Status• Flight Control Trims

For Global 5000 see Appendix 1.

Standby Altimeter/Airspeed Indicator

Standby AttitudeIndicator

17

7

10

10

EICAS Systems Display

1110

14

10


133

611

10

12

• Airplane Status informationand the following synoptic pages• Bleed System• Anti-Ice• Hydraulics• Electrical System (AC and DC)• Fuel System• Flight Controls

L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF

GLD MANUAL ARMPARK/EMER BRAKE ON

<– FUEL XFER ON

TOTAL FUEL (LBS) 415OO

1.54

146OO 146OO1OOOO

N2

FF (PPH)

OIL TEMP

OIL PRESS

93.4575O11581

1.65

CRZEPR

IGN

START START

IGN

NDSTAB

1.54

1.65

73.3

T/ON1SYNC

73.3

789

ITTSYNC

789 DN DN DN

3O

OUT

GEAR

–TRIMS–

NL NRRUDDER

AIL

RWDLWD

7.2

NU

93.4575O11581

23OO

Honeywell

13000.00

00

90

13 13

2019 20

22 2220

OXYGEN

AFTCABIN (°C)

FWDCABIN (°C)

CKPT (°C)

OPEN OPEN

OUTFLOWVALVES

CAB ALT

P

CAB RATE

LDG ELEV

00

1 2

1 2

1 2

QTY

ENG

APU

RES

OIL (QTS)

RPM EGT

BRAKE TEMP

11.5

650100

0603 03 03

11.55.26.0

%

% %

APU


OVERHEAD PANEL

WARNINGPRESSURE DIFFERENTIALSHALL NOT EXCEED .1 PSIDURING TAXI AND 1.0 PSIUPON INITIAL LANDING

OFF

ON

CABIN PWR

O

WINDSHIELD HEATL

ONOFF/

RESET

RON

OFF/RESET

ELECTRICALEXT AC

AVAIL

ON

FAIL

OFF

GEN 1

FAIL

OFF

EXT DC

AVAIL

ON

GEN 3 GEN 4

FAIL

OFF

GEN 2

FAIL

OFF

PUSH OFF/RESET

PUSHOFF/RESET

APU GEN

FAIL

OFF

RAT GEN

ON

OFF

BATT MASTER

EMS

OFF

ON

O

HYDRAULIC

R HYD SOV

CLOSED

L HYD SOV

CLOSED

AURAL WARNING

PUSH TO MUTE

IAC 1 IAC 2

MUTED MUTED

PASS SIGNSNO SMKG SEAT BLTS

OFF

ON

AUTO

OFF

ON

AUTO

EMER LIGHTS

OFF

ON

ARMAA A

LANDINGNLGL WING R WING

TAXI/RECOGWINGTIP

NAV BEACON STROBE WING INSP LOGO

OFF

ON

OFF

PULSE

STEADY

OFF

PULSE

STEADY

OFF

PULSE

STEADY

OFF

WINGTIP

ON

OFF

WHT

ON

OFF

ON

OFF

ON

OFF

ONO

EXTERNAL LIGHTS

OOOO

S OSS

HYDRAULIC1B 3A 3B 2B

OFF

AUTO

OFF

ON ON ON

ON

OFF

AUTO

OFF

AUTOAAOA

APU

RUNOFF START

ENGINE

ENG START

IGNITION

ON

AUTOL CRANK R CRANK

FUELR

WING FEEDINHIBIT

LWING FEED

INHIBIT

XFEED SOV

FAIL

OPEN

AUX PUMP

OFF

PRI PUMPS

OFF

L RECIRC

ON

AUX PUMP

OFF

PRI PUMPS

OFF

R RECIRC

ON

AFT XFERAUTO

OFF ON

OFF

AUTOWING XFER PACK CONTROL

L MANTEMP

R MANTEMP

BLEED/AIR COND

TEMPERATUREFWD CABIN

NORM

MAN

LO HIGH

R ENG BLEEDL ENG BLEED

ANTI-ICEL COWL R COWLWING

WING XBLEED

COLD HOT

APU BLEED

AUTOCLSD OPEN

XBLEED

L PACK R PACK

FAIL

OFF

FAIL

OFF

TRIM AIRRECIRC

OFFOFF

AUTOOFF ON

AUTOOFF ON

LD HO

RAM AIR

AUX PRESSHOT

COLD

HOT

COLD

ON

ON

AUTOOFF ON

AUTO AUTOAUTOOFFOFF OFFONON ON

AUTOFROM L FROM R

AFT CABIN

COLD HOTLD HO

COCKPIT

COLD HOTLD HO

TO FLY N 45 E 135 S 225 W 315

STEER

STBY COMPASS WITH ALL RADIOS ON SWUNG / / BY

N 3336 30

DISCH

PULL

1 2

LPULL

APU

DISCH

1 2

DISCH

1 2

RPULL

OUTFLOW VALVE

PRESSURIZATION AUTOMAN

LDG ELEV RATEMAN ALT

1

CLOSED

2

CLOSED

AUTO/MAN

MAN

EMERGDEPRESS

ON

DITCHING

ON

MAN

FMS

UP

DN

HIGH

NORM

UP

DN NF

ELT

ARM/RESET

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

AR

GX

_0

1_

02

4

1. Electrical Panel2. Hydraulic Panel3. ELT Panel4. Gasper5. Aural Warning Panel6. Fire Discharge Handles7. Bleed/Air Conditioning

Anti-Ice Panel

612

8

137

9

17 13

8. Pressurization Panel9. Windshield Heat Panel10. External Lights Panel11. Passenger Signs/Emergency

Lights Panel12. Engine Panel13. Standby Compass14. APU Panel15. Fuel Panel16. Misc Control Panel

13

315

164

11


7

1

1514

13

12

11

10

9

2

3

4

5

16 6

8

FUELR

WING FEEDINHIBIT

LWING FEED

INHIBIT

XFEED SOV

FAIL

OPEN

AUX PUMP

OFF

PRI PUMPS

OFF

L RECIRCINHIBIT

OFF

AUX PUMP

OFF

PRI PUMPS

OFF

R RECIRCINHIBIT

OFF

OFF

AUTOWING XFER

Global 5000 Fuel Panel

15

17


GLARESHIELD


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL

WARNING

CAUTION


ROLL SPLRS

PLT CONT

ROLLSEL

PLTROLL

WARNING

CAUTION

DIMOFF

BRT

HUD

SPD MANFMSCRS 1 CRS 2

PUSH DCT PUSH DCT

ALTHDG

DN

UP

P

I

T

C

H

Honeywell

FD FDAP

CPL

YD

FLC NAV BANKHDG VNAV ALT

APR VS

BC

PUSH CHG PUSH SYNC

GX

_01_025

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

107

27


RIGHT GLARESHIELD

CENTER GLARESHIELD

LEFT GLARESHIELD

1

2

3

4


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


CENTER PEDESTAL

TRANSMIT EMER

VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

SPKROFF

MIC M SKA

HISENS

LOSENS

VHF 3

BOTH

ID

VOICE

EGPWS

TERRAIN

OFF

G/S WARN

MUTED

FLAP OVRD

OVRD

NL NR

CH1 CH2STAB

RUD

PUSH OFF/RESET

AILTRIMS

RWD

LWD

OFF OFF

SKP

RCL

PAG

ENT

TCAS MENU TERRMAP

PLAN

NAV

APT

EMERNORM ABN

TCAS MENU

EMER

TERRMAP

PLAN

NAV

APT

NORM ABN

SKP

RCL

PAG

ENT

RADAR LSS TILTTST

FP

GMAP CLRTST

SBY OFFRCT LXWX SBY

PULLACT

+

–GAIN

MIN MAX

PULLVAR

TRB STAB TGT SECT

OFF

RADAR TILTTST

FP

GMAPSBYRCTWX

PULLACT

+

–GAIN

MIN MAX

PULLVAR

TRB STAB TGT SECT

OFF

IRS 3IRS 1 IRS 2

NAVNAV NAVALNALN ALN

OFFOFF OFF

ATTATT ATT

FLOOD

DISPLAY

COCKPIT LIGHTS

L

L

OFF

DIM

OFF

DIM

OFF

DIM

BRT

BRT

BRT

BRT

BRT

BRT

CTR

CTR

R

R

IRS ADC ADC IRS

SG 3

EICAS

SG 2SG 1

PFD 1

ALTN 3

ALTN

ALTN 1

ALTNALTN

ALTN

NORM

NORM

NORMNORM

NORM

PFD 1 PFD 2

PFD 2

ALTN 2 ALTN NORM

ENGINE

RL

EPREPR

N1N1

EP

RAT

GND LIFTDUMPING

AUTO BRAKE

AUTO

OFF LOW

MED

HI

MANUAL ARM

OFF

A

F

UP

DN

DN LCKRELEASE

LDG GEARNOSE STEER

HORN

BTMS OVHTWARN RESET

EVENT

ARMED

OFF

MUTED

STAT

HYDAC

ELECBLEED

AIRCOND

DCELEC

FUELFLT

CTRL

SCROLL

EICAS

SYSTEM SELECT

NORMMFD 2MFD 1

PARK/EMER

BRAKEPARK/EMER

BRAKE

LG

PU

LL

PU

SH

FU

LLY

TO

ST

OW

COCKPIT LIGHTS

LDIM BRTM BRDIM BRTM BR DIM BRTM BR

INTEGRAL

CTR R

CBDIM BRTM BR DIM BRTM BR

OVHDMASTER

PBA EYE REF AREA FLOOR

AUTO

DIM ON DIM ON

OFF

BRT OFF OFF OFF

O

B O O O

ON

BRT

SLAT

6

16

30

0

0

OUT

OUT

OUT

OUT

IN

FLAP

SLAT/

FLAP

MAXTHRUST

IDLEREV

MAX REV

ENGRUN

OFF OFF

RL

ELECT DC PWREMER OVRD

OVRD

NORM

TUNE

COM1 NAV1

1 2 1 . 8 2 117 .45

118 .02 110 .00MEMORY-1

RANGE:

MEMORY-1

ATC/TCAS ADF1

1 2 0 0

1 2

NORMAL

1799 .5

1 5 4 2 3

1 5 6 0 0

1 ATC ALT ADF

LV

HF1TCAS DSPY 1

SQ

ID

DIM

PGE

1/2

TST

STO

DME

FLIGHTSPOILER

R

E

T

R

A

C

TMAX

1/2

FULL

0

1/2TUNE

COM1 NAV1

121 .82 117 .45

118 .02 110 .00MEMORY-1

RANGE:

MEMORY-1

ATC/TCAS ADF1

1 2 0 0

1 2

NORMAL

1799 .5

1 5 4 2 3

1 5 6 0 0

1 ATC ALT ADF

LV

HF1TCAS DSPY 1

SQ

ID

DIM

PGE

1/2

TST

STO

DME

TRANSMIT EMER

VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

SPKROFF

MIC M SKA

HISENS

LOSENS

VHF 3

BOTH

ID

VOICE

TRANSMIT EMER

VHF 1

NAV 1

SPEAKER HEADPHONE

NAV 2 ADF DME

ST MKR MUTE H'MIC

INT

VHF 2 HF 1 HF 2 PA

1 12 2

SPKRON

SPKROFF

MIC M SKA

HISENS

LOSENS

VHF 3

BOTH

ID

VOICE



0BOW PASS/@ LB0

0/170

0 00055° 154NM

15820 (00+21

00000001152ZKPHX

SJN

0 00059° 121NM

15820 (00+15 .75M/10000A

CLS

ABQ

0ORIGIN

.75M/10000A

CLS

123456789012345678901234COMPARE FUEL QUANTITY0DEPARTURE TAKEOFF0


0BOW PASS/@ LB0

0/170

0 00055° 154NM

15820 (00+21

00000001152ZKPHX

SJN

0 00059° 121NM

15820 (00+15 .75M/10000A

CLS

ABQ

0ORIGIN

.75M/10000A

CLS

123456789012345678901234



0BOW PASS/@ LB0

0/170

0 00055° 154NM

15820 (00+21

00000001152ZKPHX

SJN

0 00059° 121NM

15820 (00+15 .75M/10000A

CLS

ABQ

0ORIGIN

.75M/10000A

CLS

123456789012345678901234

LAV CALL CABIN CALL CREW AREA PA

PUSH TO RESET

ON

CABINCALL

FWD AFT

LAVCALL

FWD AFT

GX

_0

1_

02

6

1. IRS Mode Selector Panel2

10. Call Panel11. RAT Manual Release Handle12. DC Power Emergency Override

Panel13. EGPWS Panel14. FMS Control Display Unit15. Radio Management Unit16. Thrust Lever Quadrant17. MFD Control Panel

18. Audio Panel19. Flap Selector Lever20. Cockpit Lights Integral/Misc21. Cockpit Lights Flood/Display22. Reversion Control Panel23. Landing Gear Manual Release

Handle

. Landing Gear Panel3. Gnd Lift Dump/Autobrake Panel4. Engine Control Panel5. Flight Spoiler Lever6. Weather Radar Control Panel7. EICAS Control Panel8. Parking Brake Handle9. Flt Cont. Trim Panel 10

101515

7

14

166

16

51617

16

5

610 14

1

1710

16714


11

23

22

21

20

19

18

17

15

16

14

131

12

9

8

7

6

5

4

3

2

10


COPILOT’S INSTRUMENT PANEL

220

200

190

180

170

160

150

LIM HDG

9500

210 29.92 INBARO

FLCAP1

A/T1

VTA

SPD VAPP ASEL

M

0.856M

DTK360

HDG330

SRP

1000

VS 1000

54

MSG 0

1

2

3

1

2

3

9500

10500

10000

VOR 1VOR 2

ATT2ADC1

20 20

10 10

10 10

20 20

20

1300

200

1856

4

10400

20008060

95

N33

30

W24

21S

15

12

E6

3

H23.4NMFMS1

VOR1

Honeywell

WX


SAT

GSPD

TERR

-56

TAT

TAS

-40

234

345

FAIL

LX

0 . 05L

MAG2HDG315

ETE 1+36

12 . 5NMKDVT

BELOWTCAS TEST

FMS1360

N

5 5

3

6

33

30

- 02

- 02

+ 12- 04

KABC

KLM

KKLM

TOC

TOC

GHJ

KGHJ

LUF

DEF

KDEF

4000 4000

FL180

+ 09

Honeywell




225210210185

254250

3003400.890.88

0.8580.842

200200250

GX

_01_027


1. Airspeed Placard2. Primary Flight Display3. Multifunctional Display

- MAP Format- PLAN Format- WX Radar- TCAS Traffic

7

7

16

16

1

23

CREW LIFE VESTUNDER SEAT




225210210185

254250

300340

0.890.88

0.8580.842

200200250


COPILOT’S SIDE PANEL

PUSHER

STALL

ON

OFF

ER

O

PUSHER

STALL

ON

OFF

ER

O

ER

O

ER

O

ER

O

SEL

RST

ET

CHR

MODE

INT

CHR

11:1350

01:43

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

DC 1

DC ESS

AC ESS

BATT


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

M

GX

_01_028

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


6

107

13

1

234


COPILOT’S SIDE CONSOLE

PU

SH

TO

CL

OS

EO

PE

NP

US

HO

PE

NP

US

H

PPRADV

TEST

ALRTRST

OFF

FAULT

LOWPPR

THERAPEUTICOXYGEN

ON

PASSENGER OXYGEN NORMAL

CLOSED OVERRIDETEST PORT

PASS. ON

COCKPIT VOICE RECORDER MICROPHONE MONITOR

ERASE

STATUS

TEST

HEADPHONE

OXYGENMASK

PRESSTO

TESTAND

RESET

EROS

EMERGENCY

100%PUSH


ON

OFF

GX

_0

1_

02

9

1. Mach Transducer Source Selector Valves2. Headset Panel3. Oxygen Panel4. Passenger Oxygen Selector5. Cockpit Voice Recorder6. Cockpit Printer (if installed)7. Oxygen Cruise Mask Control


5

55

10

88

2

1

FLASHLIGHT

HEADSETPANEL

FLASHLIGHT

MICHDPH

HEADSET

MACH TRANSDUCERRANSD

PITOT

CLOSED

STATIC

CLOSED6

3

4 7

5


EICAS MESSAGES

GX

_01_044

789

1 . 65

PASSENGER DOORCARGO DOORR EMER EXITDOOR SYS FAILLARGE SERV DOORSSMALL SERV DOORS

PASSENGER DOORComes on to indicatethat the passengerdoor is not closed andlocked.

CARGO DOORComes on to indicatethat the cargo door isnot closed and latched.

LARGE SERV DOORSComes on to indicatethat one or more of the followingdoors are not closed:• Aft equipment bay• Rear hydraulic system access• Refuel/Defuel station• Optional belly fairing stowage access

R EMER EXITComes on to indicatethat the emergency exitdoor is not in position

DOOR SYS FAILComes on to indicatethe loss of fuselage andgear door indication

SMALL SERV DOORSComes on to indicatethat any one or more ofthe small service doorsare not closed


EMS CIRCUIT PROTECTION

BRT



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CNTL TEST

BUS

EMERCONT

DC 1

DC ESS

AC ESS

BATT


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

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1/1CB - DOORS SYSTEMS

INAV BATT DCPCPAX DOOR MOTOR


Global Express-Airplane General

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