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GF1210_012
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200LBS
AUX AUX
23 °C 23 °C
32 °C
APU
P P
LOPRESS
P
P
P P
P
P
P P
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200LBS
0 LBS
AUX AUX
23 °C 23 °C
32 °C 32 °C
APU
P P
LOPRESS
P
P
P
P P
P
P
P
32 °C
0 LBS
The FUEL synoptic display below represents airplane configuration with the APU shut down, both
engines on speed, AC pumps running and the DC pumps on standby.
GF1210_013
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200LBS
0 LBS
AUX AUX
23 °C 23 °C
32 °C
APU
P P
P P
P
P
P
32 °C
P
P
P
FUEL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
12−10−14
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. 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.
APU start in progress,
left and right engines
are off.
APU FEED
SHUTOFF
VALVE
Green outline
will be indicated when
the APU is on speed.
TOP VIEW
GF1210_014 NOTE
APU −
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200LBS
0 LBS
AUX AUX
23 °C 23 °C
32 °C 32 °C
APU
P P
LOPRESS
P
P
P
P P
P
P
P
LOPRESS
APU on speed,
left and right engines
on and AC electrics
established.
LOWER VIEW
GF1210_015
NOTE
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200LBS
0 LBS
AUX AUX
23 °C 23 °C
APU
P P
P P
32 °C
P
P
P
P
P
P
32 °C
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−10−15
FUEL QUANTITY AND INDICATION
The fuel quantity gauging system is an actype
capacitance system. Fuel quantity probes,
compensators, densitometers, temperature sensors and high level detectors are inputs received by
the FMQGC. The FMQGC uses this acquired data to compute the fuel quantity for each tank and
total fuel quantity remaining on board the airplane.
The FMQGC outputs 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.
Fuel FLow Readout
Indicates fuel flow in pounds per
hour (PPH) to the respective
engine.
EICAS PRIMARY DISPLAY
Total Fuel Readout
Indicates total fuel quantity in
pounds (lbs), of all the tanks.
Green − Total fuel quantity is
valid and in normal range.
Amber − The fuel quantity is low.
Dashed − Fuel quantity is not valid.
Fuel Quantity Readout
(wing tank)
Indicates fuel quantity in the
respective wing tank, in
pounds (lbs).
Green − Left and right tanks
are balanced.
Amber − A fuel quantity
imbalance exists or applicable
tank is less than 600 lbs
(272 KG).
Dashed − Fuel quantity
is not valid
Fuel Quantity Readout
(aft tank)
Indicates fuel quantity in the aft
tank, in pounds (lbs).
Green − Quantity is valid.
Amber − The aft tank fuel
transfer is off schedule.
Dashed − Fuel quantity is not valid.
Fuel Quantity Readout
(center fuselage tank)
Indicates fuel quantity in the
centre tank, in pounds (lbs).
Green − Quantity is valid.
　
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