chapter 1: airplane general table of contents · airplane has two bmw/rolls royce br710 turbo fan...

For Training Purposes OnlySept 04

1-i

P I L O T T R A I N I N G G U I D E

AIRPLANE GENERAL

Chapter 1: Airplane General

TABLE OF CONTENTS

Page

Introduction .........................................................................................................................1-1Airplane Dimension Schematic .....................................................................................1-2

Description ..........................................................................................................................1-3Dimensions and General Data ......................................................................................1-3Antenna Location Schematic ........................................................................................1-5Visual Eye References for Ground Operation...............................................................1-6Steering Radii................................................................................................................1-7Steering Radii Schematic..............................................................................................1-7Turning Radii.................................................................................................................1-8Turning Radii Schematic ...............................................................................................1-8Jet Exhaust Two Engine Ground Idle Thrust ................................................................1-9Jet Exhaust Two Engine Takeoff Thrust .....................................................................1-10Airplane Jacking..........................................................................................................1-11Jacking Points .............................................................................................................1-11Towing.........................................................................................................................1-12Tow Bar Attachment....................................................................................................1-12

Ground Locking Safety Pins..................................................................................1-13Mooring .......................................................................................................................1-13

Mooring Attachment Points ..................................................................................1-13Airplane Doors ............................................................................................................1-14

Passenger Door ....................................................................................................1-14Passenger Door Schematic ........................................................................................1-15Passenger Door Components.....................................................................................1-15

Lift Arms ................................................................................................................1-15“G” Locks...............................................................................................................1-15Vent Flap...............................................................................................................1-16Locked Indication ..................................................................................................1-16

Passenger Door Operating Handles ...........................................................................1-16External Handle.....................................................................................................1-17Internal Handle......................................................................................................1-18

Passenger Door Switches...........................................................................................1-19External Door Switch Access Panel............................................................................1-20Passenger Door Operation .........................................................................................1-20

External Door Operation .......................................................................................1-20Internal Door Operation.........................................................................................1-21Manual Closing .....................................................................................................1-21

Baggage Compartment Door ......................................................................................1-21Baggage Door Operation ......................................................................................1-23Baggage Door Indication.......................................................................................1-23

Aft Equipment Bay Door..............................................................................................1-23Aft Equipment Bay Door Schematic............................................................................1-24

Aft Equipment Bay Door Operation.......................................................................1-24

1-ii For Training Purposes OnlySept 04


AIRPLANE GENERAL

Emergency Exit ........................................................................................................... 1-25Door Indication and Control ........................................................................................ 1-26

Status Page........................................................................................................... 1-27Seat Assembly ............................................................................................................ 1-29Eye Locator - Seat Adjustment ................................................................................... 1-30Control Wheel ............................................................................................................. 1-31

Master Disconnect ................................................................................................ 1-31Pitch Trim Switch .................................................................................................. 1-31Autopilot/Flight Director (Touch Control Steering) Switch..................................... 1-31Radio Key.............................................................................................................. 1-31

System Integration ............................................................................................................ 1-32Major Systems ............................................................................................................ 1-32EICAS ......................................................................................................................... 1-32EPGDS ....................................................................................................................... 1-32FADEC........................................................................................................................ 1-32EFIS ............................................................................................................................ 1-32FMQGC....................................................................................................................... 1-33IAMS ........................................................................................................................... 1-33FMS ............................................................................................................................1-33AFCS .......................................................................................................................... 1-33EFCS .......................................................................................................................... 1-33CAIMS......................................................................................................................... 1-33Flight Compartment General Arrangement................................................................. 1-34Flight Compartment (Aft View).................................................................................... 1-35Pilot’s Side Console .................................................................................................... 1-36Pilot’s Side Panel ........................................................................................................ 1-37Pilot’s Instrument Panel .............................................................................................. 1-38Center Instrument Panels ........................................................................................... 1-39Overhead Panel .......................................................................................................... 1-40Glareshield.................................................................................................................. 1-41Center Pedestal .......................................................................................................... 1-42Copilot’s Instrument Panel .......................................................................................... 1-43Copilot’s Side Panel.................................................................................................... 1-44Copilot’s Side Console................................................................................................ 1-45EICAS Messages........................................................................................................ 1-46EMS Circuit Protection................................................................................................ 1-47


1-1


AIRPLANE GENERAL

INTRODUCTIONThe 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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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

1-2 For Training Purposes OnlySept 04


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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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)


1-3


AIRPLANE GENERAL

DESCRIPTION

DIMENSIONS AND GENERAL DATAThe 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 DimensionLength 99 ft. 5 in. (30.30 m)

Height 24 ft. 10 in. (7.57 m)

WingSpan 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 LocationsFront 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 SurfaceSpan 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 SurfaceSpan 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)



AIRPLANE GENERAL

FuselageDiameter 8 ft. 10 in. (2.69 m)

Length 86 ft. 5 in. (26.34 m)

Landing GearMain 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)

AreasEquivalent 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)

DoorsPassenger door (LH.fwd) Height to sill (one step below thefloor 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)


1-5


AIRPLANE GENERAL

ANTENNA LOCATION SCHEMATIC

WARNINGPERSONNEL 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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4Glideslope

Weather Radar



AIRPLANE GENERAL

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


1-7


AIRPLANE GENERAL

STEERING RADIISteering 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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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



AIRPLANE GENERAL

TURNING RADIIGlobal 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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1-9


AIRPLANE GENERAL

JET EXHAUST TWO ENGINE GROUND IDLE THRUST

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0

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)

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ON

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IDL

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AXIAL DISTANCE

(METERS) FEET

TO 275 FT (83.84m)



AIRPLANE GENERAL

JET EXHAUST TWO ENGINE TAKEOFF THRUST

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(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)

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ON

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TW

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OP

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TA

KE

OF

FT

HR

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AXIAL DISTANCE

(METERS) FEET

TO 275 FT (83.84m)


1-11


AIRPLANE GENERAL

AIRPLANE JACKINGThree 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



AIRPLANE GENERAL

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

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

TOW BAR ATTACHMENT

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3TOW BAR ASSEMBLY


1-13


AIRPLANE GENERAL

GROUND LOCKING SAFETY PINSGround 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.

MOORINGFittings 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°G

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14

Jacking Pad

30.25° 30.25°

Tie Down Ring

Main and Nose AreasMooring Adapter Plate

Tail Area



AIRPLANE GENERAL

AIRPLANE DOORSThe 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 DOORThe 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.


1-15


AIRPLANE GENERAL

PASSENGER DOOR SCHEMATIC

PASSENGER DOOR COMPONENTSThe following components are described to provide an understanding of the passenger door operating system.

LIFT ARMSTwo 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” LOCKSIn 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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AIRPLANE GENERAL

VENT FLAPA 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 INDICATIONVisual 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 HANDLESThe 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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1-17


AIRPLANE GENERAL

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.



AIRPLANE GENERAL

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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1-19


AIRPLANE GENERAL

PASSENGER DOOR SWITCHESThe 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)



AIRPLANE GENERAL

EXTERNAL DOOR SWITCH ACCESS PANEL

PASSENGER DOOR OPERATIONThe 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 OPERATIONTo open the passenger door externally:

• Push flap in• Grasp handle• Lift fully to open• Pull outwards

To close the passenger door externally:

NOTEDo 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


1-21


AIRPLANE GENERAL

INTERNAL DOOR OPERATIONTo 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 CLOSINGA 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 DOORA 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



AIRPLANE GENERAL

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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1

Cargo Door

Outer Handle

PushTrigger

Door Handle Recess

StowedPosition

CargoDoorOpening

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2

Vent Door/seal

InteriorDoor Handle

ReleaseButton


1-23


AIRPLANE GENERAL

BAGGAGE DOOR OPERATIONCLOSING 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 INDICATIONVisual 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 DOORThe 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.



AIRPLANE GENERAL

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 OPERATIONDOOR 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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9

Door LatchHandle Assembly

Lanyard

LatchMachanism


1-25


AIRPLANE GENERAL

EMERGENCY EXITAn 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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6

EMERGENCYEXIT DOOR

G_

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6_

A

Latch Fitting

Quick ReleaseLatch Mechanism

Hand Hold

Hook Fitting

Door StopBoth Sides

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AIRPLANE GENERAL

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 CONTROLThe 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


1-27


AIRPLANE GENERAL

STATUS PAGE

Passenger DoorThe 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 ExitOne proximity sensor is installed at the top of the door position, and senses the door in the closed position.

Baggage DoorTwo 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



AIRPLANE GENERAL

Large Maintenance DoorsTwo (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 BayAn 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 DoorsThe LGECU monitors the signals and provides input to EICAS when any one of the access/small service doors is not properly closed.


1-29


AIRPLANE GENERAL

SEAT ASSEMBLYThe 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

_0

1_

01

5

Headrest

Shoulder Straps

Quick ReleaseBuckle

Armrest

Waist Straps

Flight Crew Seat

Lumbar Support

Crotch Belt

Up/DownLever

Seat ReclineLever

LumbarAdjustment

Top

Mid

Bottom

ArmrestAdjusment



AIRPLANE GENERAL

EYE LOCATOR - SEAT ADJUSTMENTAn 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

_0

1_

01

6


1-31


AIRPLANE GENERAL

CONTROL WHEELThe pilot and copilot control wheels contain the following switches:

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

MASTER DISCONNECTThe 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 SWITCHThe Pitch Trim Switch enables the pilot/copilot to control the trim from each control wheel.

AUTOPILOT/FLIGHT DIRECTOR (TOUCH CONTROL STEERING) SWITCHThe 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 KEYThe Radio Key activates the selected radio transmitter.

GX

_0

1_

01

7

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



AIRPLANE GENERAL

SYSTEM INTEGRATIONThe 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 SYSTEMSThe major contributors to this technology are the following:

EICASThe 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.

EPGDSThe Electrical Power Generation and Distribution System monitors and controls the airplane electrical system.

FADECThe 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.

EFISThe 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).


1-33


AIRPLANE GENERAL

FMQGCThe 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.

IAMSThe Integrated Air Management System controls and monitors the airplane bleed-air, environmental, cabin pressurization and anti-ice systems.

FMSThe 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.

AFCSThe 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.

EFCSThe 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.

CAIMSThe 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.



AIRPLANE GENERAL

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

ASTE

E

OF

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

ARM

O

ARM

O

AU

O

AU

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

ON

O

ON

EXTERNAL LIGHTS

O

ON

O

ON

O

ON

O

ON

O

ST

O

ON

O

ST

O

ST

HYDRAULIC1B 3A 3B 2B

OFF

AUTO

OFF

ON ON ON

ON

OFF

AUTO

OFF

AUTO

O

AU

O

AU

O

ON

O

AU

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

OLD HO

RAM AIR

AUX PRESSHOT

COLD

HOT

COLD

ON

ON

HOT HOT

AUTOOFF ON

AUTO AUTOAUTOOFFOFF OFFONON ON

AUTOFROM L FROM R

AFT CABIN

COLD HOTOLD HO

COCKPIT

COLD HOTOLD 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 NFD D

ELT

ARM/RESET

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

ARRE

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




225210210185

254250

3003400.890.88

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


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

ON

PUSHER

STALL

ON

OFF

ER

ON

ER

ON

ER

ON

ER

ON

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

ON

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

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

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

_0

1_

01

8

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

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

EPR

RAT

GND LIFTDUMPING

AUTO BRAKE

AUTO

OFF LOW

MED

HI

MANUAL ARM

OFF

AU

F

UP

DN

DN LCKRELEASE

LDG GEARNOSE STEER

HORN

BTMS OVHTWARN RESET

EVENT

ARMED

OFF

RMED

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 BRTIM BRDIM BRT

LIM BR DIM BRTIM BR

INTEGRAL

CTR R

CBDIM BRT

CBIM BR DIM BRTIM BR

OVHDMASTER

PBA EYE REF AREA FLOOR

AUTO

DIM ON DIM ON

OFF

BRT OFF OFF OFF

STER

A

OF

BA

D

BR

E REF

O

OF

REA

D

OF

OOR

O

OF

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

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0BOW PASS/@ LB0

0/170

0 00055° 154NM

15820 (00+21

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0 00059° 121NM

15820 (00+15 .75M/10000A

CLS

ABQ

0ORIGIN

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0BOW PASS/@ LB0

0/170

0 00055° 154NM

15820 (00+21

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0BOW PASS/@ LB0

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15820 (00+21

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15820 (00+15 .75M/10000A

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0ORIGIN

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LAV CALL CABIN CALL CREW AREA PA

PUSH TO RESET

ON

CABINCALL

FWD AFT

LAVCALL

FWD AFT


1-35


AIRPLANE GENERAL

FLIGHT COMPARTMENT (AFT VIEW)

PRESELINCR

DECR

CLOSE

START

STOP/SOVTEST

MANUAL AUTO

OFF

REFUEL

DEFUEL

REFUEL

REFUELNO AFT

LEFT CTR RIGHT

OPEN

AFT

MANUAL

CL

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

O

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

6 9 14131211108754321

ESSTRU 1ALT

SLAT/FLAPPWR 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

_0

1_

01

9

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

CL

REFUEL/DEFUEL PANEL

TOTAL PRESEL

LEFT RIGHTCENTER

AFT

PRESELINCR

DECR

CLOSE

START

STOP/SOVTEST

MANUAL AUTO

OFF

REFUEL

DEFUEL

REFUELLEFT CTR RIGHT

OPEN

MANUAL

C

REFUEL/DEFUEL PANEL

TOTAL PRESEL

LEFT RIGHTCENTER

1 Global Express 1 Global 5000



AIRPLANE GENERAL

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

_0

1_

02

0

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


1-37


AIRPLANE GENERAL

PILOT’S SIDE PANEL

PUSHER

STALL

ON

OFF

ER

ON

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

_0

1_

02

1

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


6

710

13

1

23 4



AIRPLANE GENERAL

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

3003400.890.88

0.8580.842

200200250




225210210185

254250

3003400.890.88

0.8580.842

200200250 G

X_

01

_0

22

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


1-39


AIRPLANE GENERAL

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

_0

1_

02

3

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



AIRPLANE GENERAL

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

ASTE

E

OF

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

ARM

O

ARM

O

AU

O

AU

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

ON

O

ON

EXTERNAL LIGHTS

O

ON

O

ON

O

ON

O

ON

O

ST

O

ON

O

ST

O

ST

HYDRAULIC1B 3A 3B 2B

OFF

AUTO

OFF

ON ON ON

ON

OFF

AUTO

OFF

AUTO

O

AU

O

AU

O

ON

O

AU

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

OLD HO

RAM AIR

AUX PRESSHOT

COLD

HOT

COLD

ON

ON

HOT HOT

AUTOOFF ON

AUTO AUTOAUTOOFFOFF OFFONON ON

AUTOFROM L FROM R

AFT CABIN

COLD HOTOLD HO

COCKPIT

COLD HOTOLD 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 NFD D

ELT

ARM/RESET

FOR AVIATIONEMER USE ONLY

UNAUTHORIZED OPERATION PROHIBITED

ON

ARRE

GX

_01_024

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


1-41


AIRPLANE GENERAL

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

_0

1_

02

5

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



AIRPLANE GENERAL

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

EPR

RAT

GND LIFTDUMPING

AUTO BRAKE

AUTO

OFF LOW

MED

HI

MANUAL ARM

OFF

AU

F

UP

DN

DN LCKRELEASE

LDG GEARNOSE STEER

HORN

BTMS OVHTWARN RESET

EVENT

ARMED

OFF

RMED

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 BRTIM BRDIM BRT

LIM BR DIM BRTIM BR

INTEGRAL

CTR R

CBDIM BRT

CBIM BR DIM BRTIM BR

OVHDMASTER

PBA EYE REF AREA FLOOR

AUTO

DIM ON DIM ON

OFF

BRT OFF OFF OFF

STER

A

OF

BA

D

BR

E REF

O

OF

REA

D

OF

OOR

O

OF

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

_01_026

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


1-43


AIRPLANE GENERAL

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

_0

1_

02

7


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

3003400.890.88

0.8580.842

200200250



AIRPLANE GENERAL

COPILOT’S SIDE PANEL

PUSHER

STALL

ON

OFF

ER

ON

PUSHER

STALL

ON

OFF

ER

ON

ER

ON

ER

ON

ER

ON

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

_0

1_

02

8

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


6

107

13

1

234


1-45


AIRPLANE GENERAL

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



AIRPLANE GENERAL

EICAS MESSAGES

GX

_0

1_

04

4

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


1-47


AIRPLANE GENERAL

EMS CIRCUIT PROTECTION

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

_0

1_

04

5

1/1CB - DOORS SYSTEMS

INAV BATT DCPCPAX DOOR MOTOR



AIRPLANE GENERAL

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