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Pilot’s Manual
2-28 PM-132A
AIRCRAFT FUEL SYSTEM
The aircraft fuel system consists of two wing tanks, a fuselage tank, a
fuel flow indicating system, a fuel quantity indicating system, a fuel
transfer system, a fuel vent/expansion system and a single-point pressure
refueling system.
WING TANKS
The wing is divided into two separate fuel-tight compartments which
serve as fuel tanks. Each tank extends from the wing root to a point just
short of the winglets, thus providing a separate fuel supply for each engine.
A crossflow shutoff valve is installed to permit fuel transfer between
wing tanks. Wing tank over-pressurization is prevented by
vent/expansion lines between the wing tanks and fuselage tank. This
allows access to the main fuel vent/expansion system of the fuselage
tank. Flapper-type check valves, located in the various wing ribs, allow
free fuel flow inboard but restricted outboard fuel flow. A main jet
pump is mounted in each wing collector bay tank near the center bulkhead
to supply fuel under pressure to the respective engine fuel system.
A standby pump also located at this location can be utilized as a
back-up for the main jet pump, or be used to transfer fuel from wing
tank to wing tank or defuel the aircraft. Three scavenge jet pumps, located
throughout each wing tank, are used to transfer fuel to the inboard
collector bay containing the main fuel jet pump. A fourth
scavenge jet pump, located in the forward end of the collector tank, is
used to transfer fuel to the inlet of the main fuel pumps. A fifth scavenge
jet pump, located in the outlet of the fuselage to wing transfer line,
is used to assist gravity in the transfer of fuel from fuselage to wing
during normal aircraft operation. The wings are filled from the fuselage
tank through the refueling manifold or the gravity filler port.
FUSELAGE TANK
The fuselage tank consists of a single bladder-type cell located in the aft
fuselage. The tank is equipped with a pressure refueling adapter, a
gravity filler port, a fuel probe, a refueling manifold/nozzle, and a fuel
vent/expansion system with an auxiliary vacuum/pressure relief
valve. The tank allows the entire fuel system to be serviced through a
pressure refueling adapter located on the right side of the aircraft below
the engine pylon, or a gravity filler port located on the right side of the
aircraft forward of the engine pylon. The gravity transfer system is
boosted by motive flow through the refueling manifold/nozzle during
pressure refueling operations. Fuel will flow to both wing tanks
through two transfer lines.
Pilot’s Manual
PM-132A 2-29
FUEL FLOW INDICATING SYSTEM
The fuel flow indicating system consists of a Dual Fuel Flow Converter
(DFFC) and a fuel flow transmitter located in the main fuel line of each
engine. The fuel flow transmitters sense flow rate and fuel temperature,
and provide these parameters to the DFFC. The DFFC processes these
signals and sends a flow rate, along with the total fuel burned, to a Data
Acquisition Unit (DAU). The DAU transfers the information to the
flight management system for fuel monitoring and to EICAS for flight
deck display to show Fuel Flow (FF) left and right engine, and total fuel
used (refer to Figure 2-5 for the EICAS Fuel Page).
A TOTALIZER RESET switch, located within the FUEL group of the
pedestal control panel, will reset the fuel burned information held in
the DFFC’s nonvolatile memory after fuel servicing. The fuel used can
be zeroed out by depressing and holding the TOTALIZER RESET button
for a minimum of two seconds.
The DFFC is powered by 28-vdc supplied by the 1-amp L and R FUEL
FLOW circuit breakers located within the ENGINE groups of the pilot’s
and copilot’s circuit breaker panels, respectively.
FUEL PAGE
Figure 2-5
3000 LBS ON BOARD
L WING
1000
FUSELAGE
L ENG 1000 R ENG
R WING
1000
1500 USED
Pilot’s Manual
PM-132A
D
S
V
P
S
V
S
D
FUEL PROBE
FLOAT SWITCH
FILLER
ENGINE FUEL PUMP
STANDBY PUMP
JET PUMP
REFUEL SHUTOFF VALVE
CHECK VALVE
PRESSURE SWITCH
PRECHECK VALVE
DEFUEL VALVE
SHUTOFF VALVE
CROSSFLOW VALVE
P
AUXILIARY VACUUM/PRESSURE
RELIEF VALVE
TRANSFER
ENGINE SUPPLY
MOTIVE FLOW
SCAVENGE
FUEL VENT/EXPANSION
AIR
DEFUEL OPEN (amber)
FUEL IMBALANCE (amber)
L R FUEL QTY LOW (amber)
FUEL XFLO (amber)
L R FWSOV CLSD (wh te)
L R FWSOV FAULT (amber)
L R FUEL QTY FAULT (white)
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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