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Indicates that a fuel quantity imbalance
exists between left and right wing tanks.
L or R XFER SOV caution (amber)
Indicates that respective transfer
shut--off has failed.
AUTO XFLOW INHIB status (white)
Indicates that powered crossflow is
inhibited in automatic mode.
L or R XFLOW ON status (white)
Indicates that crossflow shut--off
valve has been manually selected
open.
GRAV XFLOW OPEN advisory (green)
Indicates that gravity crossflow shut--off
valve is open.
GRAV XFLOW FAIL status (white)
Indicates that gravity crossflow shut--off
valve is not in selected position.
L or R AUTO XFLOW ON status (white)
Indicates that automatic powered crossflow
is operating on the respective side.
MAN XFLOW status (white)
Indicates that manual crossflow has
been selected.
Primary Page
Status Page
Vol. 1 13--30--5
FUEL SYSTEM
Fuel Management REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
C. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Transfer
L XFER FUEL
SOV 1 N9
R XFER FUEL
SOV BATTERY
BUS
2 P8
Fuel
Management
Gravity
Crossflow
FUEL
GRAVITY
XFLOW
1
N8
Powered
CROSSFLOW
PUMP
AC
ESSENTIAL
S5
Crossflow CROSSFLOW
PUMP CONT
DC
ESSENTIAL 2 R7
Vol. 1 13--30--6
FUEL SYSTEM
Fuel Management REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 13--40--1
FUEL SYSTEM
Fuel Distribution Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
1. FUEL DISTRIBUTION
Fuel is distributed to each engine from a respective side collector tank which is an integral
part of the center wing tank. Two scavenge ejectors, located at the lowest part of each wing
tank, supplies fuel to each collector tank to keep it in a full condition. The collector tank is
designed to maintain engine fuel feed under all normal flight and transient maneuver
conditions. A main ejector, within each collector tank, supplies fuel to the respective side
engine. The main and scavenge ejectors are powered by pressurized fuel tapped from the
motive flow line of the respective engine fuel pump.
During engine start, a boost pump within each collector tank supplies fuel to the engines.
The fuel control panel, located on the overhead panel, is used to control and monitor boost
pump operation. Normally both boost pumps operate simultaneously and are capable of
feeding either engine.
The fuel output pressure from the main ejector is monitored by a pressure switch and when
the output pressure is sufficient to supply the engines, the boost pumps are automatically
turned off. The boost pumps will remain in standby mode with the engines running, as a
back up to the main ejectors in the event of a failure.
A dedicated fuel pump within the left collector tank supplies fuel to the APU. The APU pump
is controlled by the APU control panel located on the overhead panel. In the event of fuel
pump failure, the APU has suction feed capability.
In the event of a fire, fuel flow to the engine or APU is terminated by the closure of a shut-off
valve when the associated fire push switchlight is selected.
Vol. 1 13--40--2
FUEL SYSTEM
Fuel Distribution REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Fuel Distribution Schematic
Figure 13---40---1
OPEN
FAIL
SDS70
GRAVITY
XFLOW
FORWARD
SCAV
EJECT P
P
PRIME
FEED
EJECT
HIGH LEVEL
SENSOR
XFER
EJECT
MOTIVE
FLOW
SOV
LEFT
ENGINE
FMU
COLLECTOR TANK
INOP
ON
LEFT
PUMP
AFT
SCAV
EJECT
FORWARD
SCAV EJECT
RH ENG
FIRE
PUSH
RIGHT ENGINE
FIRE PBA
P
PRIME
FEED
EJECT
XFER
EJECT
HIGH LEVEL
SENSOR
MOTIVE
FLOW
SOV
RIGHT
ENGINE
FMU
COLLECTOR TANK
INOP
ON
RIGHT
PUMP
AFT
SCAV
EJECT
LH ENG
FIRE
PUSH
LEFT ENGINE
FIRE PBA
P
FAIL
ON
SDS67
LEFT XFLOW
SOV
MAN
SDS69
AUTO
OVERRIDE
FAIL
ON
SDS68
RIGHT XFLOW
SOV
APU FUEL
PUMP
FRONT SPAR
FRONT SPAR
FUEL PORT
REFUEL/ DEFUEL
MANIFOLD
B7 XFLOW PUMP
　
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