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Volume 2
12−10−12
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.
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
FGF1210_012 NOTE
APU −
FUEL
TOTAL FUEL
38400 LBS
FUEL USED
300 LBS
14600 LBS 14600 LBS
9200 LBS
AUX AUX
23 °C 23 °C
P
P
P
APU
32 °C
P
P
P
32 °C
P P
LO PRESS LO PRESS
APU on speed,
left and right engines
on and AC electrics
established.
LOWER VIEW
FGF1210_013
NOTE
FUEL
TOTAL FUEL
35616 LBS
FUEL USED
0 LBS
14900 LBS 14900 LBS
5816 LBS
AUX AUX
23 °C 23 °C
P
P
P
APU
32 °C
P
P
P
32 °C
P P
FUEL
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−13
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 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.
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
(center fuselage tank)
Indicates fuel quantity in the
center tank, in pounds (lbs).
Green − Quantity is valid.
Dashed − Fuel quantity is not valid.
TOTAL FUEL (LBS) 35016
14600 5816 14600 ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
5750
115
81
93.4
5750
115
81 AIL
FGF1210_014
The FMQGS can display fuel quantity in either LB (standard) or KG (optional). The primary EICAS
page displays fuel quantity in all fuel tanks and total fuel in the airplane.
FUEL
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
12−10−14
FLIGHT MANAGEMENT DISPLAY
When both engines are started, the Fuel Management System (FMS) fuel quantity switches from
Fuel Management Quantity Gauging System (FMQGS), to computed fuel quantity, based on fuel flow
data from the engines and APU.
GF1210_017a
Compare Fuel Quantity
Displays when the gauge fuel
weight and the FMS fuel weight
differ by more than 2% of the
Basic Operating Weight (BOW).
BOW
48500 5/170
PASS / @ LB
PERFORMANCE INIT−LB 5/5
FUEL (GAUGE)
25300 (25300)
ACTIVE FLT PLAN
ORIGIN
KPHX
055 154 NM CLS
1/4
SJN 00 + 21 .75M/1 0 0 0 0 A
059 121 NM
00 + 15 .75M/10000 A
TAKEOFF INIT
ABQ
DEPARTURE
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Bombardier_Global_000-Fuel(6)
