Bombardier Global Express - Airplane General

TURNING RADII SCHEMATIC CL 0° 20° 25° 30° 35° 40° 45° 50° 55° 60° 65° 70° 75° MAX R2 R1 TURNING CENTERS TURNING RADII SHOWN REPRESENT THE THEORETICAL GEOMETRIC TURNING CENTERS R5 R3 R4 R6 NOTE: Actual operating data will be greater than values shown since tire slippage is 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) JET EXHAUST KEEP-OUT ZONES TWO-ENGINE OPERATION GROUND IDLE THRUST 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) JET EXHAUST KEEP-OUT ZONES TWO-ENGINE OPERATION TAKEOFF THRUST 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 Nylon Plug Rear Fuselage Support Typical Jack Jacking Point Jack Pad 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 Areas Mooring 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 Cable Assembly 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 Handle GX_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 fully closed position until the handle moves 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 in the fully closed position until the handle 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 inside the airplane) EXTERNAL SWITCH Note: Both switches are guarded but 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 GRASP HANDLE LIFT FULLY TO OPEN PULL OUTWARDS 1.OPERATE SWITCH TO ROTATE DOOR FULLY INTO DOOR APERTURE 2.PULL HANDLE DOWN- WARDS TO STOW NOTE: DO NOT RECYCLE HANDLE DURING CLOSING OPERATION WITHOUT REOPENING DOORS SUFFICIENTLY TO REARM DOOR UPLOCK LEVER. TO CLOSE Operating Instructions DOOR OPERATING SWITCH 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 Passenger Compartment Bulkhead Cargo Compartment Cargo Door Opening BAGGAGE COMPARTMENT INTERIOR Door Handle 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 Push Trigger Door Handle Recess Stowed Position Cargo Door Opening GX_01_042 Vent Door/seal Interior Door Handle Release Button 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 Latch Handle Assembly Lanyard Latch Machanism 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 EMERGENCY EXIT DOOR G_ag036_A Latch Fitting Quick Release Latch Mechanism Hand Hold Hook Fitting Door Stop Both 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 FLAP PUSH 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 DOOR Annunciation 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. Inertia Reels Fwd/Aft Control Inertia Reels Control GX_01_015 Headrest Shoulder Straps Quick Release Buckle Armrest Waist Straps Flight Crew Seat Lumbar Support Crotch Belt Up/Down Lever Seat Recline Lever Lumbar Adjustment Top Mid Bottom Armrest Adjusment 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 support bracket is not shown. PILOT’S SIGHT LINE COPILOT’S SIGHT 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 N O S E D N N O S E U P D I S C M A S T E R T C S IC R/T 1 2 3 (Radio key located behind) 1. Master Disconnect 2. Pitch Trim Switch 3. Autopilot/Flight Director Touch Control Switch 4. Radio Key Indicates Chapter in which information on item may be found. 10 10 2 2 6 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) WARNING PRESSURE DIFFERENTIAL SHALL NOT EXCEED .1 PSI DURING TAXI AND 1.0 PSI UPON INITIAL LANDING OFF ON CABIN PWR O WINDSHIELD HEAT L ON OFF/ RESET R ON OFF/ RESET ELECTRICAL EXT 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 PUSH OFF/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 SIGNS NO SMKG SEAT BLTS OFF ON AUTO OFF ON AUTO EMER LIGHTS OFF ON ARMA A A LANDING NLGL WING R WING TAXI/RECOG WINGTIP 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 O SS HYDRAULIC 1B 3A 3B 2B OFF AUTO OFF ON ON ON ON OFF AUTO OFF AUTOAAOA APU RUN OFF START ENGINE ENG START IGNITION ON AUTO L CRANK R CRANK FUEL R WING FEED INHIBIT L WING 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 XFER AUTO OFF ON OFF AUTO WING XFER PACK CONTROL L MAN TEMP R MAN TEMP BLEED/AIR COND TEMPERATURE FWD CABIN NORM MAN LO HIGH R ENG BLEED L ENG BLEED ANTI-ICE L COWL R COWL WING WING XBLEED COLD HOT APU BLEED AUTO CLSD OPEN XBLEED L PACK R PACK FAIL OFF FAIL OFF TRIM AIR RECIRC OFFOFF AUTO OFF ON AUTO OFF ON LD HO RAM AIR AUX PRESS HOT COLD HOT COLD ON ON AUTO OFF ON AUTO AUTO AUTO OFF OFF OFFON ON ON AUTO FROM 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 L PULL A P U DISCH 1 2 DISCH 1 2 RPULL OUTFLOW VALVE PRESSURIZATION AUTO MAN LDG ELEV RATE MAN ALT 1 CLOSED 2 CLOSED AUTO/ MAN MAN EMERG DEPRESS ON DITCHING ON MAN FMS UP DN HIGH NORM UP DN N F ELT ARM/ RESET FOR AVIATION EMER USE ONLY UNAUTHORIZED OPERATION PROHIBITED ON A R 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) . . . . . . . . . . . . . VMO VMO MMO MMO MMO MMO VLO VLO VLE (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) . . . . . . . . . . . . . . . 225 210 210 185 254 250 300 340 0.89 0.88 0.858 0.842 200 200 250 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) . . . . . . . . . . . . . VMO VMO MMO MMO MMO MMO VLO VLO VLE (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) . . . . . . . . . . . . . . . 225 210 210 185 254 250 300 340 0.89 0.88 0.858 0.842 200 200 250 20 10 30 20 10 30 0 9 8 7 6 5 4 3 2 1 10 0 F E E T ALT 1 0003 2 4 10 1 3 mb/hPa 29 9 2 IN HG IAS KNOTS 220200180 250 BARO L ENG FLAMEOUT FUEL LO QTY FUEL IMBALANCE YD OFF GLD MANUAL ARM PARK/EMER BRAKE ON <– FUEL XFER ON TOTAL FUEL (LBS) 415OO 1.54 146OO 146OO1OOOO N2 FF (PPH) OIL TEMP OIL PRESS 93.4 575O 115 81 1.65 CRZ EPR I G N START START I G N ND STAB 1.54 1.65 73.3 T/O N1 SYNC 73.3 789 ITT SYNC 789 DN DN DN 3O OUT GEAR –TRIMS– NL NRRUDDER AIL RWDLWD 7.2 NU 93.4 575O 115 81 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 DTK 360 HDG 330 SRP 1000 VS 1000 54 MSG 0 1 2 3 1 2 3 9500 10500 10000 VOR 1 VOR 2 ATT2 ADC3 20 20 10 10 10 10 20 20 20 1300 200 185 6 4 104 00 20 00 80 60 95 N 33 30 W 24 21 S 15 12 E 6 3 H23.4NM FMS1 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 DTK 360 HDG 330 SRP 1000 VS 1000 54 MSG 0 1 2 3 1 2 3 9500 10500 10000 VOR 1 VOR 2 ATT2 ADC1 20 20 10 10 10 10 20 20 20 1300 200 185 6 4 104 00 20 00 80 60 95 N 33 30 W 24 21 S 15 12 E 6 3 H23.4NM FMS1 VOR1 Honeywell Honeywell 1300 0.00 0 0 90 13 13 20 19 20 22 22 20 OXYGEN AFT CABIN (°C) FWD CABIN (°C) CKPT (°C) OPEN OPEN OUTFLOW VALVES CAB ALT P CAB RATE LDG ELEV 00 1 2 1 2 1 2 QTY ENG APU RES OIL (QTS) RPM EGT BRAKE TEMP 11.5 650 100 0603 03 03 11.5 5.2 6.0 % % % APU Honeywell WX NO BEARING RA 9 . 8NM +13 TA 4 . 5NM -04 SAT GSPD TERR -56 TAT TAS -40 234 345 FAIL LX 0 . 05L MAG2 HDG 315 ETE 1+36 12 . 5NM KDVT BELOW TCAS TEST FMS1 360 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 BEARING RA 9 . 8NM +13 TA 4 . 5NM -04 SAT GSPD TERR -56 TAT TAS -40 234 345 FAIL LX 0 . 05L MAG2 HDG 315 ETE 1+36 12 . 5NM KDVT BELOW TCAS TEST FMS1 360 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 11:13 50 01:43 BRT CIRCUIT BREAKER SYSTEM STAT SYS BUS PREV PAGE NEXT PAGE CNTL TEST BUS EMER CONT 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 BUS PREV PAGE NEXT PAGE CNTL TEST BUS EMER CONT 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 11:13 50 01:43 MACH TRANSDUCERRANSD PITOT CLOSED STATIC CLOSED SELECT POWER LEFT AUX RIGHT SYSTEM SELECT FAULT ON FROM TO WPT WPT LEG CHG XTK DTK WD WS DIS TIM HDG STS POS TK GS 1 M T 2 BRT DIM 3 TST ENT BCK 0 CLR 7 S 8 9 W 4 5 E 6 1 N 2 3 8 8 8 8 8 88 8 8 8 8 8 8 8 8 OXYGEN SUPPLY LOWER DISCONNECT ON OFF OXYGEN MASK PRESS TO TEST AND RESET EROS EMERGENCY 100% PUSH MASTER WARNING/CAUTION ROLL SPLRS PLT CONT ROLL SEL PLT ROLL WARNING CAUTION DIMOFF BRT HUD MASTER WARNING/CAUTION ROLL SPLRS CPLT CONT ROLL SEL CPLT ROLL WARNING CAUTION MINIMUMS BARO Hpa RAD IN BARO SET NAV SRC BRG V/L BRGFMS HSI Honeywell PUSH STD MINIMUMS BARO Hpa RAD IN BARO SET PUSH STD NAV SRC BRG V/L BRGFMS HSI Honeywell SPD MANFMSCRS 1 CRS 2 PUSH DCT PUSH DCT ALT HDG 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 N O S E D N N O S E U P D I S C M A S T E R MIC N O S E D N N O S E U P D I S C M A S T E R MIC MIC HDPH HEADSET GX_01_018 13 13 3 2 1 4 5 6 14 Flight Bag Storage Pilot’s Side Console Pilot’s Side Panel Pilot’s Instrument Pilot EICAS Display Glareshield Overhead Panel Standby Instruments Systems Display Copilot’s Instrument Panel Copilot’s Side Panel Copilot’s Side Console Control Wheel Pedestal 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 7 8 9 10 11 12 PUSH TO CLOSE OPEN PUSH OPEN PUSH PPR ADV TEST ALRT RST OFF FAULT LOW PPR THERAPEUTIC OXYGEN ON PASSENGER OXYGEN NORMAL CLOSED OVERRIDE TEST PORT PASS. ON COCKPIT VOICE RECORDER MICROPHONE MONITOR ERASE STATUS TEST HEADPHONE OXYGEN MASK PRESS TO TEST AND RESET EROS EMERGENCY 100% PUSH OXYGEN SUPPLY LOWER DISCONNECT 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 SPKR ON SPKR OFF MIC M SKA HI SENS LO SENS VHF 3 BOTH I D V O I C E EGPWS TERRAIN OFF G/S WARN MUTED FLAP OVRD OVRD NL NR CH1 CH2 STAB RUD PUSH OFF/RESET AIL TRIMS R W D L W D OFF OFF SKP RCL PAG ENT TCAS MENU TERR MAP PLAN NAV APT EMERNORM ABN TCAS MENU EMER TERR MAP PLAN NAV APT NORM ABN SKP RCL PAG ENT RADAR LSS TILT TST FP GMAP CLR TST SBY OFF RCT LX WX SBY PULL ACT + – GAIN MIN MAX PULL VAR TRB STAB TGT SECT OFF RADAR TILT TST FP GMAPSBY RCTWX PULL ACT + – GAIN MIN MAX PULL VAR TRB STAB TGT SECT OFF IRS 3 IRS 1 IRS 2 NAV NAV NAV ALN ALN ALN OFF OFF 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 2 SG 1 PFD 1 ALTN 3 ALTN ALTN 1 ALTN ALTN ALTN NORM NORM NORM NORM NORM PFD 1 PFD 2 PFD 2 ALTN 2 ALTN NORM ENGINE RL EPREPR N1N1 EP RAT GND LIFT DUMPING AUTO BRAKE AUTO OFF LOW MED HI MANUAL ARM OFF A F UP DN DN LCK RELEASE LDG GEAR NOSE STEER HORN BTMS OVHT WARN RESET EVENT ARMED OFF MUTED STAT HYD AC ELEC BLEED AIR COND DC ELEC FUEL FLT CTRL SCROLL EICAS SYSTEM SELECT NORM MFD 2MFD 1 PARK/EMER BRAKE PARK/EMER BRAKE LG PULL PUSH FULLY TO STOW COCKPIT LIGHTS L DIM BRTM BR DIM BRTM BR DIM BRTM BR INTEGRAL CTR R CB DIM BRTM BR DIM BRTM BR OVHD MASTER 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 MAX THRUST IDLE REV MAX REV ENG RUN OFF OFF RL ELECT DC PWR EMER OVRD OVRD NORM TUNE COM1 NAV1 1 2 1 . 8 2 11 7 . 4 5 11 8 . 0 2 11 0 . 0 0 MEMORY-1 RANGE: MEMORY-1 ATC/TCAS ADF1 1 2 0 0 1 2 NORMAL 1 7 9 9 . 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 FLIGHT SPOILER R E T R A C TMAX 1/2 FULL 0 1/2 TUNE COM1 NAV1 1 2 1 . 8 2 11 7 . 4 5 11 8 . 0 2 11 0 . 0 0 MEMORY-1 RANGE: MEMORY-1 ATC/TCAS ADF1 1 2 0 0 1 2 NORMAL 1 7 9 9 . 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 SPKR ON SPKR OFF MIC M SKA HI SENS LO SENS VHF 3 BOTH I D V O I C E 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 SPKR ON SPKR OFF MIC M SKA HI SENS LO SENS VHF 3 BOTH I D V O I C E COMPARE FUEL QUANTITY 0DEPARTURE TAKEOFF0 000ACTIVE FLT PLAN 1/4 0BOW PASS/@ LB0 0/170 0 00055° 154NM 15820 (00+21 00000001152Z KPHX SJN 0 00059° 121NM 15820 (00+15 .75M/10000A CLS ABQ 0ORIGIN .75M/10000A CLS 123456789012345678901234 COMPARE FUEL QUANTITY 0DEPARTURE TAKEOFF0 000ACTIVE FLT PLAN 1/4 0BOW PASS/@ LB0 0/170 0 00055° 154NM 15820 (00+21 00000001152Z KPHX SJN 0 00059° 121NM 15820 (00+15 .75M/10000A CLS ABQ 0ORIGIN .75M/10000A CLS 123456789012345678901234 COMPARE FUEL QUANTITY 0DEPARTURE TAKEOFF0 000ACTIVE FLT PLAN 1/4 0BOW PASS/@ LB0 0/170 0 00055° 154NM 15820 (00+21 00000001152Z KPHX 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 CABIN CALL FWD AFT LAV CALL FWD AFT Bombardier Global Express - Airplane General Page 34 FLIGHT COMPARTMENT (AFT VIEW) PRESEL INCR DECR CLOSE START STOP/ SOV TEST MANUAL AUTO OFF REFUEL DEFUEL REFUEL REFUEL NO AFT LEFT CTR RIGHT OPEN AFT MANUAL REFUEL/DEFUEL PANEL TOTAL PRESEL LEFT RIGHT CENTER AFT OIL REPLENISHMENT RESERVOIR TANK LO PUMP ON APU RH ENG LH ENG POWER SYSTEM ON LO OIL LO OIL LO OIL VLV OPEN VLV OPEN VLV OPEN DATA UPLOAD/DOWNLOAD DAU 1A IAC 1 IAC 2 IAC 3 GPWS SATCOM SDU GPS 1 GPS 2 ADC 1 ADC 2 ADC 3 DAU 1B WXR DAU 2A DAU 2B DAU 3A IRS 1 IRS 2 DAU 3B DAU 4A DAU 4B IRS 3 PRINT MAINT REPORT 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 ENTRY HTR/FAN CNTL FWD MON JUMP SEAT LUMBAR DC2 CBN PWR 3 ENT COOL AIR/GND CNTL CABIN TRU ENTRY HTR CHILLER AFT TOILET COMP FWD TOILET COMP CREW ENTRY DOME AIR DUCT 60Hz CNTL LH STAIR BOARD FWD LH UPPER FWD LINE FWD LAV RH FWD AFT RH LOWER AFT TANK AFT LAV LINE 1 GALLEY LINE 2 FWD TANK AFT AFT AFT CNTLRS DVD 1 FWD TRU FEEDER LAV ORD DVD 2 AFT CNVTR FDR 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 FEED DC2 PWR 2 BATT (SPDA3) 28 VDC - DC CABIN FEED 2 CMS T/S WRDRB CABIN ENTERTAINMENT INTERIOR LIGHTS 115 VAC/60Hz - OUTLETS EXTERIOR LIGHTS WATER SYSTEM INDIR LTS TOILET TANK HTRS DRAIN/LINE HTRS WATER HTRS MAST HTRS FWD AFT FANS MAST HTR LAV LAV AUDIO AMPLIFIER READ/TABLE TOILET 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 WATER TRTMT 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 CABIN PWR MSTR FWD GALLEY CELL CHGRS EXT SVC MID ACCENT FAX WING TIP AFT LH CABIN PULSE FDR AIR SHOW RH COFFEE MKR FWD SYS CKPT MON AFT MICRO- WAVE CREW IND LTS GALLEY FWD FWD AFT AFT AFT SYS FWD PUMP AFT PUMP 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 5 1 5 1 5 3 K 5 6 9 14131211108754321 ESS TRU 1 ALT SLAT/ FLAP PWR 2 STAB TRIM CH 2 ESS TRU 2 AC ESS BUS 20 15 15 15 6 9 14131211108754321 STBY PITOT HTR AC BUS 4 MONITOR RAT V/F MONITOR TAT HT 1 L AOA HTR PITOT 1 HT B PITOT 3 HT L ICE DETECTOR R AOA HEAT B TAT HT 2 L WINDOW HEAT 2.5 5 7.5 7.5 5 2.5 7.5 5 7.5 15 7.5 E F 6 9 131211108754321 L WSHLD HTR 1 L WSHLD HTR 2 SATCOM FREQ UNIT R AOA HTR A R ICE DETECT PITOT 1 HT A A/T CTLR AC BUS 1 2.5 7.5 2.5 7.5 20 20 5 6 9 131211108754321 SLAT/ FLAP PWR 1 TRU BAY FAN ESS TRU 1 15 20 2.5 G H AV BATT RCCB APU BATT RCCB AV BATT HEAT TAT HT 3 R WSHLD HEAT 1 R WSHLD HEAT 2 TRU 2 AV BATT CHGR PITOT 2 HT R WIND HEAT 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 STBY ADI 2.5 .5 A B C D GX_01_019 1. Refuel/Defuel Panel 2. Oil Replenishment Panel 3. Cockpit Circuit Breaker Panel (CCBP) 4. Halon Fire Extinguisher 5. Data Upload/Download Panel 6. Portable Breathing Equipment 7. Crash Axe Indicates Chapter in which information on item may be found. 11 17 6 8 5 8 8 2 7 5 6 3 4 DATA UPLOAD/DOWNLOAD DAU 1A IAC 1 IAC 2 IAC 3 GPWS SATCOM SDU GPS 1 GPS 2 ADC 1 ADC 2 ADC 3 DAU 1B WXR DAU 2A DAU 2B DAU 3A IRS 1 IRS 2 DAU 3B DAU 4A DAU 4B IRS 3 OIL REPLENISHMENT RESERVOIR TANK LO PUMP ON APU RH ENG LH ENG POWER SYSTEM ON LO OIL LO OIL LO OIL VLV OPEN VLV OPEN VLV OPEN PRINT MAINT REPORT PRESEL INCR DECR CLOSE START STOP/ SOV TEST MANUAL AUTO OFF REFUEL DEFUEL REFUEL REFUEL NO AFT LEFT CTR RIGHT OPEN AFT MANUAL REFUEL/DEFUEL PANEL TOTAL PRESEL LEFT RIGHT CENTER AFT PRESEL INCR DECR CLOSE START STOP/ SOV TEST MANUAL AUTO OFF REFUEL DEFUEL REFUEL LEFT CTR RIGHT OPEN MANUAL REFUEL/DEFUEL PANEL TOTAL PRESEL LEFT RIGHT CENTER 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 WPT LEG CHG XTK DTK WD WS DIS TIM HDG STS POS TK GS 1 M T 2 BRT DIM 3 TST ENT BCK 0 CLR 7 S 8 9 W 4 5 E 6 1 N 2 3 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 OXYGEN SUPPLY LOWER DISCONNECT ON OFF OXYGEN MASK PRESS TO TEST AND RESET EROS EMERGENCY 100% PUSH GX_01_020 1. Oxygen mask/Regulator 2. Headset Panel 3. Navigation Display Unit 4. Nosewheel Steering Handwheel 5. Flashlight 6. Data Loader 7. Oxygen Cruise Mask Control 16 14 5 8 2 5 FLASHLIGHT HEADSET PANEL FLASHLIGHT Indicates Chapter in which information on 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 BUS PREV PAGE NEXT PAGE CNTL TEST BUS EMER CONT 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 11:13 50 01:43 GX_01_021 1. Electrical Management System 2. Stall Pusher Switch 3. Clock 4. Air Conditioning Gasper Indicates Chapter in which information on item may be found. 6 7 10 13 1 2 3 4 Bombardier Global Express - Airplane General Page 37 PILOT’S INSTRUMENT PANEL WX NO BEARING RA 9 . 8NM +13 TA 4 . 5NM -04 SAT GSPD TERR -56 TAT TAS -40 234 345 FAIL LX 0 . 05L MAG2 HDG 315 ETE 1+36 12 . 5NM KDVT BELOW TCAS TEST FMS1 360 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 IN BARO FLC AP1 A/T1 VTA SPD VAPP ASEL M 0.856M DTK 360 HDG 330 SRP 1000 VS 1000 54 MSG 0 1 2 3 1 2 3 9500 10500 10000 VOR 1 VOR 2 ATT2 ADC3 20 20 10 10 10 10 20 20 20 1300 200 185 6 4 104 00 20 00 80 60 95 N 33 30 W 24 21 S 15 12 E 6 3 H23.4NM FMS1 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) . . . . . . . . . . . . . VMO VMO MMO MMO MMO MMO VLO VLO VLE (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) . . . . . . . . . . . . . . . 225 210 210 185 254 250 300 340 0.89 0.88 0.858 0.842 200 200 250 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) . . . . . . . . . . . . . VMO VMO MMO MMO MMO MMO VLO VLO VLE (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) . . . . . . . . . . . . . . . 225 210 210 185 254 250 300 340 0.89 0.88 0.858 0.842 200 200 250 GX_01_022 1. Airspeed Placard 2. Primary Flight Display 3. 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 VEST UNDER SEAT 7 16 Bombardier Global Express - Airplane General Page 38 CENTER INSTRUMENT PANELS STATIC GROUND OPERATION PROHIBITED BETWEEN 66-80% N1 20 10 30 20 10 30 0 9 8 7 6 5 4 3 2 1 10 0 F E E T ALT 1 000 3 2 4 10 1 3 mb/hPa 29 9 2 IN HG IAS KNOTS 220 200 180 250 BARO GX_01_023 Engine Indication and Crew Alerting System (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 Attitude Indicator 17 7 10 10 EICAS Systems Display 11 10 14 10 Indicates Chapter in which information on item may be found. 13 3 6 11 10 12 • Airplane Status information and the following synoptic pages • Bleed System • Anti-Ice • Hydraulics • Electrical System (AC and DC) • Fuel System • Flight Controls L ENG FLAMEOUT FUEL LO QTY FUEL IMBALANCE YD OFF GLD MANUAL ARM PARK/EMER BRAKE ON <– FUEL XFER ON TOTAL FUEL (LBS) 415OO 1.54 146OO 146OO 1OOOO N2 FF (PPH) OIL TEMP OIL PRESS 93.4 575O 115 81 1.65 CRZ EPR I G N START START I G N ND STAB 1.54 1.65 73.3 T/O N1 SYNC 73.3 789 ITT SYNC 789 DN DN DN 3O OUT GEAR –TRIMS– NL NR RUDDER AIL RWD LWD 7.2 NU 93.4 575O 115 81 23OO Honeywell 1300 0.00 0 0 90 13 13 20 19 20 22 22 20 OXYGEN AFT CABIN (°C) FWD CABIN (°C) CKPT (°C) OPEN OPEN OUTFLOW VALVES CAB ALT P CAB RATE LDG ELEV 0 0 1 2 1 2 1 2 QTY ENG APU RES OIL (QTS) RPM EGT BRAKE TEMP 11.5 650 100 06 03 03 03 11.5 5.2 6.0 % % % APU Bombardier Global Express - Airplane General Page 39 OVERHEAD PANEL WARNING PRESSURE DIFFERENTIAL SHALL NOT EXCEED .1 PSI DURING TAXI AND 1.0 PSI UPON INITIAL LANDING OFF ON CABIN PWR O WINDSHIELD HEAT L ON OFF/ RESET R ON OFF/ RESET ELECTRICAL EXT 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 PUSH OFF/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 SIGNS NO SMKG SEAT BLTS OFF ON AUTO OFF ON AUTO EMER LIGHTS OFF ON ARMA A A LANDING NLG L WING R WING TAXI/RECOG WINGTIP 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 O O O O S O S S HYDRAULIC 1B 3A 3B 2B OFF AUTO OFF ON ON ON ON OFF AUTO OFF AUTOA A O A APU RUN OFF START ENGINE ENG START IGNITION ON AUTO L CRANK R CRANK FUEL R WING FEED INHIBIT L WING 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 XFER AUTO OFF ON OFF AUTO WING XFER PACK CONTROL L MAN TEMP R MAN TEMP BLEED/AIR COND TEMPERATURE FWD CABIN NORM MAN LO HIGH R ENG BLEED L ENG BLEED ANTI-ICE L COWL R COWL WING WING XBLEED COLD HOT APU BLEED AUTO CLSD OPEN XBLEED L PACK R PACK FAIL OFF FAIL OFF TRIM AIR RECIRC OFF OFF AUTO OFF ON AUTO OFF ON LD HO RAM AIR AUX PRESS HOT COLD HOT COLD ON ON AUTO OFF ON AUTO AUTO AUTO OFF OFF OFF ON ON ON AUTO FROM L FROM R AFT CABIN COLD HOT LD HO COCKPIT COLD HOT LD HO TO FLY N 45 E 135 S 225 W 315 STEER STBY COMPASS WITH ALL RADIOS ON SWUNG / / BY N 33 36 30 DISCH PULL 1 2 L PULL A P U DISCH 1 2 DISCH 1 2 R PULL OUTFLOW VALVE PRESSURIZATION AUTO MAN LDG ELEV RATE MAN ALT 1 CLOSED 2 CLOSED AUTO/ MAN MAN EMERG DEPRESS ON DITCHING ON MAN FMS UP DN HIGH NORM UP DN N F ELT ARM/ RESET FOR AVIATION EMER USE ONLY UNAUTHORIZED OPERATION PROHIBITED ON A R GX_01_024 1. Electrical Panel 2. Hydraulic Panel 3. ELT Panel 4. Gasper 5. Aural Warning Panel 6. Fire Discharge Handles 7. Bleed/Air Conditioning Anti-Ice Panel 6 12 8 13 7 9 17 13 8. Pressurization Panel 9. Windshield Heat Panel 10. External Lights Panel 11. Passenger Signs/Emergency Lights Panel 12. Engine Panel 13. Standby Compass 14. APU Panel 15. Fuel Panel 16. Misc Control Panel 13 3 15 16 4 11 Indicates Chapter in which information on item may be found. 7 1 15 14 13 12 11 10 9 2 3 4 5 16 6 8 FUEL R WING FEED INHIBIT L WING FEED INHIBIT XFEED SOV FAIL OPEN AUX PUMP OFF PRI PUMPS OFF L RECIRC INHIBIT OFF AUX PUMP OFF PRI PUMPS OFF R RECIRC INHIBIT OFF OFF AUTO WING XFER Global 5000 Fuel Panel 15 17 Bombardier Global Express - Airplane General Page 40