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crossflow and fuel transfer. The FQGC also measures the fuel quantity and temperature for
display on the EICAS.
The engine indication and crew alerting system (EICAS) shows a diagram of the fuel
distribution system. The operation of the ejectors, pumps and shut off valves are graphically
indicated and the resulting fuel flow is depicted. Any fault detected by the fuel quantity
gauging computer is annunciated in the form of a visual message.
A. Fuel Tank Quantities
LOCATION USABLE FUEL UNUSABLE FUEL TOTAL FUEL
Left Main Tank 7,493 LB (3,399 Kg) 62 LB (28 Kg) 7,554 LB (3,427 Kg)
Right Main Tank 7,493 LB (3,399 Kg) 62 LB (28 Kg) 7,554 LB (3,427 Kg)
Center Tank 4,610 LB (2,091 Kg) 32 LB (14 Kg) 4,642 LB (2,106 Kg)
Vol. 1 13--10--2
FUEL SYSTEM
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel System --- General
Figure 13---10---1
COLLECTOR
TANKS
CENTER
TANK
RH MAIN TANK
GRAVITY FILL CAP
GRAVITY FILL CAP
LH MAIN TANK
FLIGHT COMPARTMENT
FUEL CONTROL PANEL
REFUEL--DEFUEL CONTROL PANEL
REFUEL/DEFUEL
ADAPTER
Vol. 1 13--20--1
FUEL SYSTEM
Fuel Storage REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. FUEL STORAGE
Fuel is stored in two main wing tanks and one center wing tank. For extended range flights
fuel is carried in the center tank. In flight, as the wing tank fuel quantity decreases, the
FQGC will automatically transfer fuel from the center tank to the wing tanks to maintain
lateral balance.
A. Collector Tanks
Two collector tanks are located in the forward section of the center wing tank. Fuel
from each wing tank is fed under pressure to its respective collector tank by scavenge
ejectors. Fuel can also be fed from the wing tanks to the associated collector tank by
gravity. There is no migration of fuel from the center tank into the collector tanks.
B. Venting
The tanks are vented to atmosphere and slightly pressurized by a NACA scoop located
on the lower surface of each wing. A climb vent provides ventilation when the airplane
is in a nose up attitude. Relief valves eliminate the possibility of pressure build up
within the tanks.
Vol. 1 13--20--2
FUEL SYSTEM
Fuel Storage REV 1, Jan 13/03
Flight Crew Operating Manual
CSP C--013--067
Storage and Vent System
Figure 13---20---1
NACA
INLET
BALANCE
PIPES
STACK
PIPE
MOTIVE
FLOW
WING TANK
MAIN VENT
WING TANK
CLIMB VENT
WATER
DRAIN
COLLECTOR
TANK
REFUEL/ DEFUEL
ADAPTER
CENTER TANK
REFIEF VALVE
CENTER
TANK VENT
MAGNETIC LEVEL
INDICATOR
MAIN TANK
RELIEF VALVE
NACA
INLET
MOTIVE
FLOW
VENT DRAIN
CHECK VALVE
AFT
SCAVENGE
EJECTOR
Vol. 1 13--30--1
FUEL SYSTEM
Fuel Management REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. FUEL MANAGEMENT
Fuel management is accomplished by fuel transfer from the centre 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 ejectors.
The ejectors are powered by fuel pressure tapped from the engine supply lines and
automatically controlled by transfer shutoff valves. The fuel quantity gauging computer
(FQGC) commands the transfer shutoff valve to open when the associated wing tank
fuel quantity falls to 93% and commands it to close when the quantity reaches 97%.
The FQGC will cycle the transfer system on and off until the centre tank is empty.
In the event of wing tank gauging failure, the fuel quantity gauging computer will use
the high level sensors, located at the top of each tank, to control fuel transfer
operations.
B. Fuel Crossflow
Powered and gravity crossflow allows fuel transfer between the wing tanks to correct
fuel imbalance and to mantain lateral stability. Crossflow operations are controlled and
monitored through the fuel control panel located on the overhead panel.
A pump located within the centre tank provides powered crossflow in either automatic
or manual mode.
In automatic mode, the fuel quantity gauging computer controls the power crossflow. If
the computer detects a fuel imbalance between the wing tanks, the crossflow pump is
activated automatically in the required direction to correct the fuel imbalance.
The flight crew can control powered crossflow in manual mode by overriding automatic
crossflow. In manual mode, fuel flow can be selected in either direction by selecting the
　
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