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pressure. If pump output pressure is low, or the pump has failed, the amber INOP
indicator illuminates within the switch/light and the PRI (SEC) TAIL XFER PUMP
caution EICAS message is displayed. If the transfer is unsuccessful, the crew can
utilize the tail tank fuel DUMP system to reduce the fuel quantity in the tail tank.
Similarly, the AUX TANK HEAVY caution EICAS message indicates excessive
auxiliary tank fuel weight (relative to the tail tank system). Selecting only the
MANUAL OVRD switch/light will override FSCU automatic transfer functions,
stopping fuel transfer between the tail and auxiliary tanks, thereby allowing the
auxiliary tanks to deplete to normal levels.
When operating in manual override, the selected (PRI or SEC)
fuel pump will not automatically shut off when the tail tank is
empty. The flight crew must monitor manual transfer operations
and turn off the selected pump when the tail tank is empty.
Fuel Transfer Schematic Legend
Figure 12-10
NOTE
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 Rotor-Burst N2 Cylinder
12 Tail Dump SOV
13 APU SOV
H
I
(not shown)
Contactor = TAIL DUMP SOV (Abnormal MSG)
P604_12_010
14 APU Neg-G SOV
FUEL SYSTEM
For Training Purposes Only
Sept 04
12-15
P I LOT T R A I N I N G GU I D E
Fuel Transfer Schematic
Figure 12-11
APU
DC
DC
L
SADDLE
TANK
R
SADDLE
TANK
TAIL
CONE
TANK
AFT AUX
TANK
AC
AC
SUMP
AUXILIARY TANK
LEFT
MAIN
TANK
RIGHT
MAIN
TANK
DC
P
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
ON
FAIL
MANUAL
AUTO
INHIB
ON
FAIL
TAIL TANK TRANSFER DUMP
PRI MANUAL
OVRD
SEC DUMPS AT 0º
FLAPS ONLY
OPEN
FAIL
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
D E
9
G
I
2
11
14
13
DC
AC
AC Power Fuel Pump
DC Power Fuel Pump
One-Way Check Valve
Shutoff Valve
Ejector
Restrictor
Press Switch
12
P604_12_009
TS Temperature Sensor
FUEL SYSTEM
12-16 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Fuel Dumping
If attempts to transfer fuel from the tail tank to auxiliary tank fail, the tail tank fuel can
be dumped. Fuel dumping must be carried out with the flaps at 0°.
A guarded DUMP switch/light, powered by the DC Battery Bus, is located on the
FUEL control panel. Once pressed in, the dump valve is commanded open, and the
white OPEN indicator illuminates on the switch/light. Fuel is dumped at a rate of
approximately 100-120 lb/min (45-55 kg/min). Five minutes after the dump valve is
selected OPEN, the TAIL DUMP SOV caution EICAS message is displayed to remind
the flight crew that the dump valve is open.
If the dump valve is not in the position commanded by the switch/light, the amber
FAIL indicator will illuminate and the TAIL DUMP SOV caution EICAS message
will be displayed.
Fuel Dump Switch/Light
Figure 12-12
Fuel may be inadvertently dumped on the ground, via the fuel
dump mast, if the BATT MASTER switch is selected on, and the
fuel DUMP switch is pressed in.
Fuel Crossflow (XFLOW)
Whenever there is a fuel imbalance between the two main tanks (more than 400 lbs on
taxi, takeoff or landing, or more than 800 lbs in flight), the FUEL IMBALANCE
caution EICAS message is displayed.
The three XFLOW switch/lights on the FUEL control panel correspond to three valves
　
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