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Center tank 3,142 liters 830 U.S. gal 2,550 kg 5,600 lb
Total 18,662 liters 4,930 U.S. gal 15,100 kg 33,300 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.
PRESSURE REFUEL (+0 / -1% WING TANKS, +0 / -2% CENTER TANK)
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-16 For Training Purposes Only
Sept 04
FUEL AND WATER DRAINS
All tanks have flush self-closing water drain valves, installed at various low points, to
permit draining of any accumulated water or residual fuel. They are located at the low
point of each wing. Three gravity fill caps are provided for wing and center tank
gravity refueling.
Center Fuel Tank
Water Drains
Gravity Fuel Fill
Wing Fuel Tank
and Water Drain
Center Wing
Gravity Fuel Fill
Wing Fuel Tank
and Water Drain
Wing Fuel Tank
Gravity Fuel Fill
LEGEND
UPPER SURFACE
LOWER SURFACE
GX_appx_002
For Training Purposes Only
Sept 04
Appx-17
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
AC BOOST PUMPS
Two AC boost pumps, also referred to as primary boost pumps, are located in each
feed tank. They normally supply fuel to the engines in all airplane ground and flight
mode operations. Each pump is capable of maintaining an engine (fuel demand) in all
modes of engine operation. The two pumps are continuously on, whenever the engine
is operating and AC power is available. Both boost pumps (two on each side) may be
inhibited by selection of one of the individual switches on the fuel control panel. The
boost pumps are controlled automatically through the Alternating Current Power
Center (ACPC), when a fuel command is received.
DC AUXILIARY PUMPS
DC powered auxiliary pumps (AUX pumps) one in each feed tank, are used for the
following:
• APU starting
• Wing to wing transferring of fuel
• Engine feed in the event of an AC boost pump failure
• During takeoff and landing with at least one of the following:
Flaps > 0°, landing gear down and in flight, or low wing fuel condition (600
pounds each wing)
Each AUX pump may be inhibited by selecting off a switch on the fuel control panel.
The pumps are automatically controlled by the Secondary Power Distribution
Assembly (SPDA).
NOTE
When an AUX pump is used for wing transfer mode of operation
and an AC pump fails, priority is given to the engine feed system
and the automatic wing transfer operation will be inhibited.
Manual override of the automatic selection is possible via the
fuel control panel.
CENTER TRANSFER PUMPS
Two center transfer pumps (controlled by the FMQGC) are used to transfer fuel from
the center tank to the main wing tanks. There is no manual selection available to
transfer fuel from the center tank to the wings.
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-18 For Training Purposes Only
Sept 04
VENT SYSTEM
An open vent (no float valves or flame arrestors) system is used to control the pressure
in the fuel tanks. It consists of vent line tubing and ram air inlet/outlet scoops, to
ensure adequate venting of all fuel tanks. The vent lines connect the two air scoops to
the fuel tanks, and the fuel tanks to each other. The lines are drained of fuel which is
returned to the feed tanks during operation. The low point of the main vent line is
continuously scavenged by a jet pump.
The vent line distribution is to a high point in the fuselage, preventing fuel from
reaching either of the two ram outlets and spilling overboard. If any fuel passes the
high point, it is collected by the surge box and is drained back to the tank before it
reaches the outlet. Each surge box vent line tubing runs vertically along the fuselage
side wall, and is coupled to the wing, center and aft tanks.
The vent system is fully redundant, such that any single blockage does not affect the
venting capability.
VENT SYSTEM SCHEMATIC
LEFT WING TANK
CENTER
WING
TANK
AIR
SCOOP
AIR
SCOOP
RIGHT WING TANK
GX_appx_003
RIGHT
SURGE
BOX
LEFT
SURGE
BOX
For Training Purposes Only
Sept 04
Appx-19
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
PRESSURE RELIEF VALVES
Relief valves are used to protect the tanks from over pressurization, in the case of
failure of the vent system and/or refuel shutoff valve. They are located in the wing and
　
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