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The engine fuel burn sequence is as follows:
.
Fuel from the wing tanks will be consumed first,
.
When the wing tanks get below 93%, fuel transfers from the center tank to the wing tank until it is at or above 97%,
.
When the center tank empties, fuel from the wing tanks continue to burn.
Engine Feed System Indication
The left FUEL synoptic page below represents the normal engine start mode of operation. The right engine is started using the Auxiliary Power Unit (APU) as the source of electrical power and left engine is off. The right FUEL synoptic display represents the right engine on speed.
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
ENGINE FEED SYSTEM (CONT'D)
Engine Feed System Indication (Cont’d)
The FUEL synoptic display below represents airplane configuration with the APU shutdown, both engines on speed, AC pumps running and the DC pumps on standby.
FGF1210_011
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
APU FUEL FEED
The APU start capability is normally provided by the DC AUX pump(s). The fuel supplied to the APU is taken from the right engine feed line. The APU can also be fed from the left engine feed line using the left DC AUX pump (powered by DC ESS bus) and opening the crossfeed shutoff valve (BATT bus). A motor operated fire shutoff valve is used in the APU feed line, in order to isolate the flow of fuel to the APU in case of a fire or rotor burst.
The FUEL synoptic page top view represents the APU starting with the right DC pump running and battery power only as the single source of electrical power. In the lower view, the APU is fed from the right engine feed line using the AC pumps.
TOP VIEW
NOTE
APU start in progress,
left and right engines
are off.
APU . Green outline will be indicated when the APU is on speed.
APU FEED SHUTOFF VALVE
LOWER VIEW
NOTE
APU on speed, left and right engines on and AC electrics established.
FGF1210_013 FGF1210_012
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FUEL QUANTITY AND INDICATION
The fuel quantity gauging system is an ac-type capacitance system. Fuel quantity probes, compensators, densitometers, temperature sensors and high level detectors provide inputs to the FMQGC. The FMQGC uses these acquired data to compute the fuel quantity for each tank and total fuel quantity remaining on board the airplane.
The FMQGC provides the computed individual fuel tank, total quantity and fuel temperature for EICAS display. The fuel system computer corrects for airplane pitch attitude and presents the corrected information of individual tank quantities and total fuel quantity displayed on EICAS.
Total Fuel Readout
Indicates total fuel quantity in Fuel FLow Readout pounds (lbs), of all the tanks.
Indicates fuel flow in pounds per
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