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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%)
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
Center tank 6,265 liters 1,655 U.S. gal 5,075 kg 11,150 lb
Aft tank 1,275 liters 337 U.S. gal 1,025 kg 2,300 lb
Total 24,410 liters 6,450 U.S. gal 19,750 kg 43,550 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
Center tank 6,245 liters 1,650 U.S. gal 5,050 kg 11,150 lb
Aft tank not available not available not available not available
Total 21,765 liters 5,750 U.S. gal 17,600 kg 38,850 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.
For Training Purposes Only
Sept 04
11-5
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
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
Aft Fuel Tank Fuel
and Water Drain
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
GX_11_002
LEGEND
UPPER SURFACE
LOWER SURFACE
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
11-6 For Training Purposes Only
Sept 04
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.
AFT TRANSFER PUMPS
Two aft transfer pumps and associated shutoff valves are used to transfer fuel from the
aft fuel tank to the wing tanks. Transfer is scheduled by the fuel computer or by a
switch selection on the fuel control panel.
For Training Purposes Only
Sept 04
11-7
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
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
　
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