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wing tanks to the associated collector tank by gravity. There is no migration of fuel from
the center tank into the collector tanks. A main fuel ejector in each collector tank is
immersed in fuel and is used to ensure a positive supply of fuel to the engines. The
boost pumps normally supply fuel to the engines for start.
B. Venting
The tanks are vented through interconnecting vent lines to NACA scoops located on
the lower surface of each wing.
In flight, the NACA scoops supply ram air to slightly pressurize the wing tanks.
On the ground, the tanks are vented to atmosphere through the NACA scoops to
prevent pressure buildup within the tanks caused by the refueling process or from
thermal expansion of the fuel.
NOTE
During climb, fuel could enter the center tank from the
vent system. This fuel can cause erroneous center
tank quantity indications as high as 300 lbs (135kg).
Fuel tank capacities for pressure fueling operation:
TANK USABLE FUEL UNUSABLE FUEL TOTAL FUEL
Left Wing 4760 lb (2159 kg) 20.4 lb (9.2 kg) 4780.4 lb (2168.2 kg)
Right Wing 4760 lb (2159 kg) 20.4 lb (9.2 kg) 4780.4 lb (2168.2 kg)
Center 4998 lb (2267 kg) 6.8 lb (3 kg) 5004.8 lb (2270 kg)
Total 14518 lb (6585.2 kg) 47.6 lb (21.6 kg) 14565 lb (6606.8 kg)
Fuel tank capacities for gravity fueling operation:
TANK USABLE FUEL UNUSABLE FUEL TOTAL FUEL
Left Wing 4488 lb (2036 kg) 20.4 lb (9.2 kg) 4508.4 lb (2145.2 kg)
Right Wing 4488 lb (2036 kg) 20.4 lb (9.2 kg) 4508.4 lb (2145.2 kg)
Center 4930 lb (2236 kg) 6.8 lb (3 kg) 4936.8 lb (2239 kg)
Total 13906 lb (6308 kg) 47.6 lb (21.6 kg) 13953.6 lb (6329 kg)
REV 56, Jan 31/03
Vol. 1 13--20--2
FUEL SYSTEM
Fuel Storage
Flight Crew Operating Manual MASTER
CSP A--013
Collector Tank and Vent System --- General
Figure 13---20---1
VENT LINE TUBING
SCAVENGE
EJECTOR
VENT
LINE
PURGE
CHECK
VALVE
MAIN TANK
RELIEF
VALVE
NACA
SCOOP
CENTER TANK
RELIEF VALVE
NACA
SCOOP
SCAVENGE
EJECTOR
VENT
LINE
PURGE
CHECK
VALVE
MAIN TANK
RELIEF
VALVE
BOOST
PUMPS MAIN
EJECTOR
COLLECTOR
TANK
TO ENGINES MOTIVE
FLOW
MOTIVE
FLOW
Vol. 1 13--30--1
REV 56, Jan 31/03
FUEL SYSTEM
Fuel Management
Flight Crew Operating Manual
CSP A--013
MASTER
1. FUEL MANAGEMENT
Fuel management is accomplished by fuel transfer from the center tank to the wing tanks
and by fuel crossflow from one wing tank to the other wing tank.
A. Fuel Transfer
Fuel transfer from the centre tank to the wing tanks is provided by transfer ejector
pumps to maintain the wing tanks at full capacity as long as possible. This is an
automatic function with no manual control. The ejectors are powered by fuel pressure
tapped from the engine supply lines via the fuel transfer shutoff valves which are
automatically controlled by the fuel system computer (FSC). The FSC commands the
respective transfer shutoff valve to open when the associated wing tank fuel quantity
falls below 94% of full, and commands it to close when the tank quantity reaches 97%.
The FSC will cycle the transfer system on and off until the center tank is empty.
If the fuel imbalance between the wing tanks exceeds 400 lbs (181 kg), a FUEL
IMBALANCE caution message is displayed on the EICAS primary page. If the total fuel
quantity is less than 900 lbs (408 kg) the fuel quantity indication on the primary page
turns amber.
Effectivity:
S Airplanes 7002, 7042 and subsequent. Aircraft 7003 to 7081 incorporating SB 601R--28--015
If the fuel imbalance between the wing tanks exceeds 800 lbs (360 kg), a FUEL
IMBALANCE caution message is displayed on the EICAS primary page. If the total fuel
quantity is less than 900 lbs (408 kg) the fuel quantity indication on the primary page turns
amber.
If the fuel imbalance between the wing tanks exceeds 800 lbs (360 kg), a FUEL
IMBALANCE caution message is displayed on the EICAS primary page and both wing
tank quantity indicators turn amber. If one wings fuel quantity is less than 450 lbs (204
kg), then that wings fuel quantity indicator will turn amber.<0039>
In the event of wing tank gauging failure, the FSC will use the high level sensors,
located at the top of each tank, to control the fuel transfer operations.
B. Fuel Crossflow
To correct fuel imbalance and to maintain aircraft lateral stability, the FSC automatically
initiates fuel crossflow upon detecting a fuel imbalance between wing tanks. The
crossflow/APU pump located within the center tank provides powered crossflow in
　
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