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BombardierGlobal ExpressAviation SystemsBusiness Jets
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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.
GX
_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
Page 1
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)
GX
_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)
Bombardier Global Express - Airplane General
Page 2
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)
Bombardier Global Express - Airplane General
Page 3
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)
Bombardier Global Express - Airplane General
Page 4
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)
GX
_01_003
GX
_01_004
GlideslopeWeather Radar
Bombardier Global Express - Airplane General
Page 5
VISUAL EYE REFERENCES FOR GROUND OPERATION
GX
_01_005
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
Bombardier Global Express - Airplane General
Page 6
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
GX
_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
Bombardier Global Express - Airplane General
Page 7
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.
GX
_01_007
Bombardier Global Express - Airplane General
Page 8
JET EXHAUST TWO ENGINE GROUND IDLE THRUST
GX
_01_010
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)
Bombardier Global Express - Airplane General
Page 9
JET EXHAUST TWO ENGINE TAKEOFF THRUST
GX
_01_011
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)
Bombardier Global Express - Airplane General
Page 10
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).
GX
_01_012
NylonPlug
Rear Fuselage
SupportTypical Jack
JackingPoint
JackPad
LEGEND
Jack
Rear Fuselage Support
Bombardier Global Express - Airplane General
Page 11
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
GX
_01_013
TOW BAR ASSEMBLY
Bombardier Global Express - Airplane General
Page 12
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°
GX
_01_014
Jacking Pad
30.25° 30.25°
Tie Down Ring
Main and Nose AreasMooring Adapter Plate
Tail Area
Bombardier Global Express - Airplane General
Page 13
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.
Bombardier Global Express - Airplane General
Page 14
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
GX
_01_030
Bombardier Global Express - Airplane General
Page 15
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
_01_031
Bombardier Global Express - Airplane General
Page 16
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.
GX
_01_032
Lockshaft
Note: The door is not in the fullyclosed position until the handlemoves to the full down position.
Bombardier Global Express - Airplane General
Page 17
INTERNAL HANDLE
NOTE: Handle shown in the locked(stowed) position. The door is not inthe fully closed position until thehandle moves fully down.
GX
_01_033
Bombardier Global Express - Airplane General
Page 18
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.
GX
_01_034
INTERNAL SWITCH(View looking from insidethe airplane)
EXTERNAL SWITCH
Note:Both switches are guardedbut not shown.(Green aircraft switches shown)
Bombardier Global Express - Airplane General
Page 19
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
GX
_01_035
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
Bombardier Global Express - Airplane General
Page 20
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.
GX
_01_040
Aft PassengerCompartmentBulkhead
CargoCompartment
CargoDoorOpening
BAGGAGECOMPARTMENTINTERIOR
DoorHandle
Bombardier Global Express - Airplane General
Page 21
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.
GX
_01_041
Cargo Door
Outer Handle
PushTrigger
Door Handle Recess
StowedPosition
CargoDoorOpening
GX
_01_042
Vent Door/seal
InteriorDoor Handle
ReleaseButton
Bombardier Global Express - Airplane General
Page 22
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.
Bombardier Global Express - Airplane General
Page 23
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.
GX
_01_039
Door LatchHandle Assembly
Lanyard
LatchMachanism
Bombardier Global Express - Airplane General
Page 24
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.
GX
_01_036
EMERGENCYEXIT DOOR
G_ag
036_A
Latch Fitting
Quick ReleaseLatch Mechanism
Hand Hold
Hook Fitting
Door StopBoth Sides
GX
_01_037
Bombardier Global Express - Airplane General
Page 25
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
GX
_01_038
PUSH IN FLAPPUSH DOOR INWARD
Bombardier Global Express - Airplane General
Page 26
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.
GX
_01_043
SERVICE DOORS
Overwing Emergency Exit
Baggage Door Passenger Door
SERVICE DOORAnnunciation
AIRPLANE DOOR POSITION AIRPLANE DOOR GRAPHIC
CLOSED
OPEN
INVALID
Bombardier Global Express - Airplane General
Page 27
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.
Bombardier Global Express - Airplane General
Page 28
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
GX
_01_015
Headrest
Shoulder Straps
Quick ReleaseBuckle
Armrest
Waist Straps
Flight Crew Seat
Lumbar Support
Crotch Belt
Up/DownLever
Seat ReclineLever
LumbarAdjustment
Top
Mid
Bottom
ArmrestAdjusment
Bombardier Global Express - Airplane General
Page 29
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
GX
_01_016
Bombardier Global Express - Airplane General
Page 30
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.
GX
_01_017
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
Bombardier Global Express - Airplane General
Page 31
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).
Bombardier Global Express - Airplane General
Page 32
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.
Bombardier Global Express - Airplane General
Page 33
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
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
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
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
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
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
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
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
HoneywellHoneywell
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
Honeywell
WX
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
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
WX
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
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
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
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
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
FLT CONTROLS
FUEL
M
PUSHER
STALL
ON
OFF
ER
O
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
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
FLT CONTROLS
FUEL
M
SEL
RST
ET
CHR
MODE
INT
CHR
11:1350
01:43
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
MASTERWARNING/CAUTION
ROLL SPLRS
CPLT CONT
ROLLSEL
CPLTROLL
WARNING
CAUTION
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MINIMUMSBARO HpaRAD IN
BARO SET
PUSH STD
NAV SRC
BRG V/L BRGFMS
HSI
Honeywell
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
MICHDPH
HEADSET
NOSE DN
N
OS E UP
DIS C
M
ASTER
MIC
NO
SE DN
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
OXYGEN SUPPLY LOWERDISCONNECT
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
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
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
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
COMPARE FUEL QUANTITY0DEPARTURE TAKEOFF0
000ACTIVE FLT PLAN 1/4
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
000ACTIVE FLT PLAN 1/4
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
COMPARE FUEL QUANTITY0DEPARTURE TAKEOFF0
000ACTIVE FLT PLAN 1/4
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
Bombardier Global Express - Airplane General
Page 34
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
115 VAC/400Hz - AC CABIN FEED 3
115 VAC/400Hz - AC CABIN FEED 4
115 VAC/400Hz - AC CABIN FEED 3
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
6 9 14131211108754321
ESSTRU 1ALT
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
Indicates Chapter in which information on item may be found.
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
Bombardier Global Express - Airplane General
Page 35
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
OXYGEN SUPPLY LOWERDISCONNECT
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
Bombardier Global Express - Airplane General
Page 36
PILOT’S SIDE PANEL
PUSHER
STALL
ON
OFF
ER
O
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
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
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
Indicates Chapter in which information on item may be found.
6
710
13
1
23 4
Bombardier Global Express - Airplane General
Page 37
PILOT’S INSTRUMENT PANEL
WX
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
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
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
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 G
X_01_022
1. Airspeed Placard2. Primary Flight Display3. Multifunctional Display
- MAP Format- PLAN Format- WX Radar- TCAS Traffic
Indicates Chapter in which information on item may be found.
7 16
1
2 3
CREW LIFE VESTUNDER SEAT
7 16
Bombardier Global Express - Airplane General
Page 38
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
Indicates Chapter in which information on item may be found.
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
Bombardier Global Express - Airplane General
Page 39
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
Indicates Chapter in which information on item may be found.
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
Bombardier Global Express - Airplane General
Page 40
GLARESHIELD
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MASTERWARNING/CAUTION
ROLL SPLRS
CPLT CONT
ROLLSEL
CPLTROLL
WARNING
CAUTION
MASTERWARNING/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
Indicates Chapter in which information on item may be found.
RIGHT GLARESHIELD
CENTER GLARESHIELD
LEFT GLARESHIELD
1
2
3
4
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
Bombardier Global Express - Airplane General
Page 41
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
COMPARE FUEL QUANTITY0DEPARTURE TAKEOFF0
000ACTIVE FLT PLAN 1/4
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
000ACTIVE FLT PLAN 1/4
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
COMPARE FUEL QUANTITY0DEPARTURE TAKEOFF0
000ACTIVE FLT PLAN 1/4
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
Indicates Chapter in which information on item may be found.
11
23
22
21
20
19
18
17
15
16
14
131
12
9
8
7
6
5
4
3
2
10
Bombardier Global Express - Airplane General
Page 42
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
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
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
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
3003400.890.88
0.8580.842
200200250
GX
_01_027
Indicates Chapter in which information on item may be found.
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
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
Bombardier Global Express - Airplane General
Page 43
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
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
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
FLT CONTROLS
FUEL
M
GX
_01_028
1. Electrical Management System2. Stall Pusher Switch3. Clock4. Air Conditioning Gasper
Indicates Chapter in which information on item may be found.
6
107
13
1
234
Bombardier Global Express - Airplane General
Page 44
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
OXYGEN SUPPLY LOWERDISCONNECT
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
Indicates Chapter in which information on item may be found.
5
55
10
88
2
1
FLASHLIGHT
HEADSETPANEL
FLASHLIGHT
MICHDPH
HEADSET
MACH TRANSDUCERRANSD
PITOT
CLOSED
STATIC
CLOSED6
3
4 7
5
Bombardier Global Express - Airplane General
Page 45
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
Bombardier Global Express - Airplane General
Page 46
EMS CIRCUIT PROTECTION
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
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
FLT CONTROLS
FUEL
M
GX
_01_045
1/1CB - DOORS SYSTEMS
INAV BATT DCPCPAX DOOR MOTOR
Bombardier Global Express - Airplane General
Page 47