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line. The
recirculation
line joins the aft tank transfer line. This slightly decreases the transfer rate of the aft
tank to the feed tanks. Heated fuel is then distributed to the number 1 and 2 cell of the wing fuel
tank. No fuel is distributed to the number 3 cell as it will have emptied before the local fuel
temperature reaches −40°C (°F). Both the recirculation
line and the aft tank transfer line are fitted
with a check valve to prevent crossflow or fuel propagation due to a ruptured line.
The wing fuel tanks are fitted with many fuel temperature sensors; the left wing has two and the
right wing has three. During normal operation (with the Fuel ReCirculation
selected OFF), the
Fuel Management and Quantity Gauging System (FMQGS) computer reads all temperature
sensors but will display only the lowest temperature. When the Fuel ReCirculation
system is
selected ON, the FMQGS computer reads the inboard temperature sensor as it will be the one
who reads the highest temperature. This logic is also used to determine the credibility of a failed
temperature sensor in order to display the FUEL TEMP SENSOR FAIL caution message. In the
event that only one side has been selected ON, the temperature displayed on the OFF side will be
the lowest among all submerged temperature sensors of that side.
Operation of the Fuel Re−Circulation System is allowed only during cruise flight above 34,000 feet
to ensure an additional safety margin in case of a main fuel pump failure. Wide Cut Fuel
operations are limited to 13,000 feet until the bulk fuel temperature is below 15°C.
Display of system status is provided through EICAS messages. A L (R) FUEL RECIRC FAIL
caution message will be displayed on the EICAS status page when the FRTT valve is not in the
commanded or allowed position. Finally, the L (R) FUEL RECIRC ON status message will be
displayed when the system operates properly and within specification.
The FUEL HI TEMP caution message is posted when the bulkhead fuel temperature exceeds
43°C when the Fuel Recirculation
System is inoperative. To prevent the system from operating
above the freezing level, the set point has been reduced to 0°C when the system is selected on.
FUEL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
12−10−26
REFUEL/DEFUEL SCHEMATIC
GF1210_025
CELL 1 CELL 2 CELL 3
RV
RV
RV
SHUTOFF
VALVES
Refuel/
Defuel
Panel TO
FMQGC
BALANCE
TUBE
BAFFLED RIBS
RELIEF
VALVE
SUCTION DEFUEL
CHECK VALVE
DEFUEL SHUTOFF
VALVE
CROSSFEED
VALVE
SHUTOFF
VALVE TO
AFT TANK
CENTRE TANK
REFUEL/DEFUEL CHECK
VALVE
SINGLE POINT
REFUEL ADAPTER
H H
H H
HIGH LEVEL
SENSOR
REFUEL/DEFUEL
MANIFOLD
RV
PRESSURE REFUEL
CHECK VALVE
Left main refuel
Fuel distribution lines
Right main refuel
Centre refuel/defuel
Aft refuel/defuel
and main defuel
LEGEND
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−10−27
FUEL FILTERS, QUANTITY AND TEMPERATURE READOUTS
GF1210_026
Engine Inlet Fuel
Temperature
Green − Engine fuel
temperature is > 5°C.
Amber − Engine fuel
temperature is < 5°C .
Wing Fuel Quantity
Indicates fuel quantity in the
respective wing tank, in pounds (lbs)
Fuel Quantity Readout
(Centre Fuselage Tank)
Indicates fuel quantity in the
centre tank, in pounds (lbs).
Fuel Quantity Readout (aft tank)
Indicates fuel quantity in the aft tank, in
pounds (lbs).
Fuel Used Quantity Readout
Indicates fuel quantity burned.
Fuel Filter
Green − Indicates normal fuel
flow through the filter.
Amber − Fuel pressure drop
exists across the filter.
Total Fuel Quantity
Indicates fuel quantity in all fuel
tanks, in pounds (lbs).
Fuel Filter Flow Line
Green − Indicates
normal fuel flow to the
engine.
Amber − Fuel pressure
drop exists across the
filter, flow line from the
filter to the engine turns
amber.
Bulk Fuel Temperature
Readout
Green − Temperature of
fuel in tanks is between
−35°C and +42°C.
Amber − Temperature of
fuel in tanks is lower than
−35°C or greater than +42°C.
On airplanes with
SB 700−28−034
incorporated:
If Fuel Re−Circulation
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