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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 above the engine pylon. The gravity transfer system is boosted
by motive flow through the refueling manifold/nozzle during refueling
operations. Fuel will flow to both wing tanks through two transfer
lines.
Pilot’s Manual
2-30 PM-126A
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. There is no fuel flow transmitter for the APU. 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 (APU fuel not included), 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
FUSELAGE
1000
L WING
1000
R WING
1600
1720 USED
3600 LBS ON BOARD
L ENG R ENG
Pilot’s Manual
PM-126A 2--31
D
S
V
P
S
V
S
D
FUEL PROBE
FUEL FILTER
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
MOTIVE FLOW
SCAVENGE
FUEL VENT/EXPANSION
AIR
DEFUEL OPEN (amber)
L R FUEL BAY LOW (white)
FUEL IMBALANCE (amber)
L R FUEL QTY LOW (amber)
FUEL XFLO (amber)
L R FWSOV CLSD (white)
L R FWSOV FAULT (amber)
L R FUEL QTY FAULT (white)
FUEL XFLO OPEN (white)
L R STBY PUMP ON (white)
CAS MESSAGES
PRESSURE
REFUELING
ADAPTER
PRECHECK
VALVE
REFUELING
MANIFOLD
FUSELAGE
FUEL TANK
PILOT
VALVE
SURGE
TANK
SURGE
FLOAT
VALVE
MAIN
VENT
SCOOP
AUXILIARY
VACUUM/PRESSURE
RELIEF VALVE
[CLOSED]
FIRE
PUSH
[CLOSED]
FIRE
PUSH
R FUEL
PRESS
LOW
L FUEL
PRESS
LOW
LEFT WING
FUEL TANK
WING FUEL
COLLECTOR
BAYS
RIGHT WING
FUEL TANK
GRAVITY
FILLER
PORT
RIGHT
ENGINE
LEFT
ENGINE
TYPICAL FOR LEFT AND
RIGHT WING TANKS
ELECTRICAL
FUEL
ON ON
L STBY XFLOW R STBY
A28-0002
FROM FUEL
SUPPLY
APU (If
installed)
APU SUPPLY
ENGINE SUPPLY
S
TO
APU
2-31 / 2-32 (Blank)
FUEL SYSTEM SCHEMATIC
Figure 2-6

Pilot’s Manual
PM-126A 2-33
STBY SWITCHES
The L and R STBY switches, within the FUEL group of the aft pedestal,
manually control the operation of the electric standby pumps. These
momentary switches normally remain off. In the event of a main jet
pump failure or during fuel crossflow, the L and R STBY switches must
be manually selected to ON by the flight crew. The standby pumps are
automatically energized during engine start (begins when the L or R
START switch is depressed, and stops at 50% N2). The right standby
pump is automatically energized during APU start and run. When the
standby pumps are operating, the L and/or R STBY switches will illuminate
ON.
The standby pumps operate on 28-vdc supplied through the 15-amp L
and R STBY PUMP PWR circuit breakers within the FUEL groups of the
pilot’s and copilot’s circuit breaker panels respectively. The automatic
and manual pump controls are powered by 28-vdc through the 3-amp
L and R STBY PUMP CTRL circuit breakers located within the FUEL
　
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