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collector tanks. They receive pressurized fuel from their on-side engine's motive flow
supply, and deliver an uninterrupted fuel supply from the collector tank to the
respective engine. In addition, the main ejector provides the motive flow fuel supply to
the on-side transfer ejector pump. Main ejector motive flow fuel is prevented from
feeding the cross-side engine by a one-way check valve.
Scavenge Ejector Pump
The left and right scavenge ejector pumps are located at the lowest inboard point in
each main (wing) tank. The scavenge ejectors’ motive flow is created by the highpressure
fuel output of the engine-driven pumps. The scavenge ejectors transfer fuel
from the main tanks to the collector tanks.
Transfer Ejector Pump
The left and right transfer ejector pumps are located at the lowest point of the center
auxiliary tank. Their motive flow supply is derived from their on-side main ejector
pump output. The transfer ejectors continuously transfer fuel to the main tanks,
maintaining them filled to 93% capacity. A float valve located in the forward area of
each main tank prevents this transfer until main tank fuel quantity is at or below 93%
capacity.
Engine Fuel Shutoff Valves
One electrically controlled engine fuel shutoff valve (“firewall” SOV) is installed on
each engine fuel feed line ahead of the engine-driven pump. When activated by
pushing the L (R) ENG FIRE PUSH switch/light on the pilot's or copilot's glareshield,
the SOV will close, stopping the flow of fuel to the engine, and the BOTTLE ARMED
PUSH TO DISCHARGE switch/lights will illuminate. Successful closing of the
engine fuel shutoff valve is indicated by a L (R) ENG SOV CLOSED advisory EICAS
message. If the valve fails to close, a L (R) ENG SOV caution EICAS message is
displayed.
The engine fuel shutoff valves are powered by the DC Emergency Bus. For additional
information, see Chapter 9 Fire Protection.
Fuel Filter
The engine-driven pumps are each equipped with a fuel filter. The filters are mounted
adjacent to the oil tank within the engine nacelle, and are monitored for contamination
by an impending bypass switch. Indications of impending bypass (filter clogged) are
the L (R) FUEL FILTER caution EICAS message, and a magnetic trip indicator, or red
LED, tripped on Junction Box 5 (JB-5) in the aft equipment bay.
FUEL SYSTEM
12-10 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Wash Filter
The wash filters are installed along the motive flow fuel feed lines from the enginedriven
pump to the main and scavenge ejector pumps. The wash filter separates ice
crystals which may have formed in the fuel and channels them to the larger main
ejector pump, thus protecting the smaller scavenge ejector pump from possible
clogging. There are no cockpit indications associated with wash filter operation.
Fuel Distribution Schematic Legend
Figure 12-7
L (R) Collector Tank
8
7
6
5
4
3
2
1
9
10 Gravity Crossflow Valve
L (R) to Aux X-Flow Valve
L (R) Wash Filter
L (R) Engine Fuel SOV
L (R) Transfer Ejector Float Valve
L (R) Transfer Ejector
L (R) Scavenge Ejector
L (R) Main Ejector
L (R) Boost Pump / APU Boost Pump
L (R) P Switch = MAIN EJECTOR (Status MSG)
G
F
E
D
C
B
A
L (R) = FUEL XFLOW SOV OPEN (Abnormal MSG)
(L) T Switch = BULK FUEL TEMP (Abnormal MSG)
L (R) P Switch = FUEL FILTER (Abnormal MSG)
L (R) T Switch = FUEL LO TEMP (Abnormal MSG)
L (R) ΔP Switch = SCAV EJECTOR (Abnormal MSG)
L (R) P Switch = FUEL LO PRESS (Abnormal MSG)
Legend
11 (not shown)
12 (not shown)
13 APU SOV
H Engine-Driven Pump
P604_12_023
14 APU Neg-G SOV
FUEL SYSTEM
For Training Purposes Only
Sept 04
12-11
P I LOT T R A I N I N G GU I D E
Fuel Distribution Schematic
Figure 12-8
APU
DC
DC
AFT AUX
TANK
AUXILIARY TANK
LEFT
MAIN
TANK
RIGHT
MAIN
TANK
DC
FWD AUX
TANK
TS
FUEL
BOOST PUMP
XFLOW
TAIL TANK TRANSFER DUMP
L TO AUX GRAVITY R TO AUX
L R
ON
INOP
ON
INOP
ON OPEN ON
8
7
6
5
4
3
2
1
9
G 10
F
E D
C
B
A
1
8
A
2
B
5
7
3
C 4
6
H H D E
9
G
2
14
13
DC
DC Power Fuel Pump
One-Way Check Valve
Shutoff Valve
Ejector
　
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