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Fill Valve installed inside the center tank shuts off the gravity refueling when the
maximum capacity is reached. Also, the change in aircraft gravity refuel quantity is
reflected in the placard located near the center tank gravity port and in the AFM
Limitations section.
AUTOMATIC CONTROL OF FUEL RECIRCULATION SYSTEM
The fuel recirculation system is automatically controlled by the fuel computer
(-9 FMQGC), in order to provide the ability to maintain fuel tanks temperature within
the approved limits for prolonged flight at cold ambient temperatures.
For Training Purposes Only
Sept 04
Appx-13
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
GLOBAL 5000 FUEL SYSTEM – DETAILS
Fuel is contained in a wet wing box structure, which is sealed to form the three main
separate wing tanks. The tanks are vented to atmosphere and slightly pressurized by an
air scoop located on the lower surface of each wing. A scavenge pump purges fuel
from the vent lines and a climb vent, located in each main wing tank, provides
ventilation when the airplane is in a nose up attitude.
Each engine is supplied with fuel from its respective feed tank which contains two
alternating current or AC primary pumps, and one Direct Current (DC) backup (or
Aux) electrical boost pump. The transfer system maintains the feed tanks full during
all attitudes, and provides automatic transfer of fuel from the center tank and aft tank
to the main wing tanks.
Lateral balance between left and right main tanks is controlled automatically by the
Fuel Management and Quantity Gauging Computer (FMQGC), or manually through
switch selections in the flight compartment.
GX_appx_001
Main Wing Tank
Engine Driven
Pumps
Feed Tanks
DC Pumps
(start, emergency
and wing transfer)
AC Motor Pumps
(transfer)
AC Motor Pumps
(engine feed)
Center Tank
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-14 For Training Purposes Only
Sept 04
Flight deck control is provided on the overhead panel, and fuel quantity and warnings
are displayed on EICAS.
A single point pressure refuel/defuel adapter is provided which is connected to a
manifold containing shutoff valves. Pressure refueling can be done either
automatically or manually. Gravity filling is provided for each wing tank and for the
center tank.
A dual channel FMQGC continuously monitors the following:
• Fuel quantity indicating
• Left, right engine and APU feed
• Wing to wing balance (wing XFER)
• Center tank transfer
• Refuel/Defuel
Any fault detected by the fuel system computer is annunciated on Engine Indication
and Crew Alerting System (EICAS) in the form of a visual and/or aural alert, and/or
maintenance diagnostics.
FUEL TANKS
All fuel is carried in three integral tanks (left wing, right wing and center wing).
The inboard section of each wing is designated as a feed tank, from which each engine
draws its fuel. Fuel flows from the outboard sections of each wing tank, into the feed
tank (by gravity), through swing check valves in the baffles of each main tank. The
check valves allow fuel flow in the inboard direction only. This will restrict large fuel
movements, and limit center of gravity shifts in airplane changes of attitude. Fuel is
also transferred into the feed tanks, from the center fuselage by the transfer system.
DESCRIPTION
FUEL SPECIFICATIONS
For information on fuel additives, temperature limitations and approved fuels, refer to
AFM - LIMITATIONS Chapter 2.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not
usable. Based upon a fuel density of 6.75 lb/U.S. gallon, the maximum usable fuel
load for each fuel tank is given below:
PRESSURE REFUEL (+0 / -1% WING TANKS, +0 / -2% CENTER TANK)
Tank Volume Fuel Mass †
Left main tank 8,435 liters 2,229 U.S. gal 6,825 kg 15,050 lb
Right main tank 8,435 liters 2,229 U.S. gal 6,825 kg 15,050 lb
For Training Purposes Only
Sept 04
Appx-15
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Center tank 3,418 liters 903 U.S. gal 2,775 kg 6,100 lb
Total 20,288 liters 5,361 U.S. gal 16,425 kg 36,200 lb
† based on a fuel density of 0.809 kg/liter (6.75 lb/U.S. gal), rounded to the nearest 25 kg or 50 lb. Fuel Mass is
provided for reference only and should not be considered limiting.
GRAVITY REFUEL (AIRPLANE LEVEL)
Tank Volume Fuel Mass †
Left main tank 7,760 liters 2,050 U.S. gal 6,275 kg 13,850 lb
Right main tank 7,760 liters 2,050 U.S. gal 6,275 kg 13,850 lb
　
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