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Fuel quantity is measured using fuel probes which provide a signal directly proportional to
fuel level. There are 6 probes in each wing tank, 1 in each collector tank and 3 in the centre
tank. A compensator probe in the bottom of each wing tank supplies data to compute the
fuel density correction. The temperature of the fuel is continuously monitored by a fuel
temperature sensor installed in the right wing tank.
Fuel quantity gauging is calibrated for both ground and flight operations. The computer
receives weight-on-wheel signals to determine if the aircraft is on the ground or in flight. In
flight, the computer takes into account the effects of wing deflection and aircraft attitude on
the fuel quantity measurement.
Corrected individual tank quantities, total fuel quantity, fuel used quantity and fuel
temperature are displayed on the Engine Indication and Crew Alerting System (EICAS) as
well as any fault detected in the fuel quantity gauging computer.
Vol. 1 13--60--2
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel Quantity System --- Schematic <1025>
Figure 13---60---1
CENTER TANK
COLLECTOR
TANKS
QTY SENSORS
28 VDC
BATT BUS
WOW
IRS
RIGHT/LEFT
COMPENSATORS
HIGH LEVEL
SENSORS
QUANTITY
SENSORS
FQGC
CHANNEL 1
AND
CHANNEL 2
REFUEL/DEFUEL
SOV MANIFOLD
FUEL TRANSFER
SOV S
X--FLOW PUMP
28 VDC
ESS BUS
CBP2--U11
CBP1--M11
LEFT
TANK
RIGHT
TANK
FUEL TEMP
SENSOR
FAULT
ANNUNCIATION
LOW FUEL
(CAUTION)
FUEL
SYNOPTIC
PAGE
EICAS
Vol. 1 13--60--3
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel System Synoptic Page --- Gauging <1001>
Figure 13---60---2
FUEL USED (white)
Displays amount of fuel used (in 5 kg increments).
Reset to zero through the EICAS MENU page.
FUEL CH 1 or 2 FAIL (white)
Indicates that respective channel of fuel
quantity gauging computer has failed.
FUEL CH 1/2 FAIL (amber)
Indicates that both channels of fuel
quantity gauging computer have failed.
Fuel Page
Vol. 1 13--60--4
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel System Gauging EICAS Indications --- Primary Page <1001>
Figure 13---60---3
FUEL CH 1/2 FAIL caution (amber)
Indicates that fuel quantity gauging
computer has failed.
Primary Page
Vol. 1 13--60--5
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel System Gauging EICAS Indications --- Status Page
Figure 13---60---4
FUEL CH 1 or 2 FAIL status (white)
Indicates that respective channel of fuel
quantity gauging computer has failed.
FUEL QTY DEGRADED status (white)
Indicates an error in the attitude input to
the fuel quantity gauging computer.
Status Page
Vol. 1 13--60--6
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel System --- Menu Page
Figure 13---60---5
Data Entry Message
Comes on when the
cursor goes to the
ACCEPT line after
selection of the FUEL
USED RESET line.
Menu Page
Vol. 1 13--60--7
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. Magnetic Level Indicators
Two magnetic level indicators (MLIs) are installed in each wing tank and one is installed
in the center tank.The MLIs are located under the wing and are used to manually check
the fuel level in each tank.
To make sure that the MLI readings are acurate, the airplane must be level. Pitch and
roll inclinometers are provided on the right flight compartment bulkhead to verify that
the airplane is level. After the MLI readings are taken they are then converted to units
of fuel quantity using tabulated charts contained in FCOM 2, Supplementary
Procedures.
Vol. 1 13--60--8
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Magnetic Level Indicators
Figure 13---60---6
LOCKED
POSITION
UNLOCKED
POSITION
VIEW LOOKING UP WITH
THE MLI LOCKED IN
THE CLOSED POSITION
STOWED IN USE
ROD
MAGNET
FLOAT
MAGNET
FUEL
LEVEL
READ
HERE
ROD
MAGNET FLOAT
　
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