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in the crossflow line. The motorized gate-valves, located in the auxiliary tank are
powered by 28 VDC. Pushing one of the XFLOW switch/lights allows manual fuel
transfer between the designated tanks.
NOTE
P604_12_020
ON
FAIL
MANUAL
AUTO
INHIB
ON
FAIL
TAIL TANK TRANSFER DUMP
PRI MANUAL
OVRD
SEC DUMPS AT 0º
FLAPS ONLY
OPEN
FAIL
FUEL SYSTEM
For Training Purposes Only
Jan 04
12-17
P I LOT T R A I N I N G GU I D E
The FUEL IMBALANCE message will be triggered in flight
whenever more than 400 pounds’ fuel imbalance exists between
the left and right main tanks, and flaps are set at 20-degree
position or more.
XFLOW Switch/Lights
Figure 12-13
L (R) TO AUX XFLOW Switch/Lights
Pushing the L (R) TO AUX switch/light opens a valve which allows fuel from the
selected wing tank into the auxiliary tank. Fuel is then evenly distributed by the
transfer ejectors to both LEFT and RIGHT main tanks. When the fuel imbalance
reduces to less than 100 lbs after a 50-second time delay, the FUEL XFLOW SOV
OPEN caution EICAS message will be displayed to remind the crew to deselect the
appropriate XFLOW switch/light.
An electric switch interlock inhibits simultaneous opening of both
L TO AUX and R TO AUX valves.
GRAVITY XFLOW Switch/Light
Pushing the GRAVITY XFLOW switch/light opens the gravity crossflow valve,
allowing fuel to flow freely between the main tanks and to balance evenly. Flying in a
slight sideslip with the heavy wing up can accelerate the balancing process. When the
GRAVITY XFLOW switch/light is selected, the OPEN indicator illuminates to
indicate gravity crossflow valve operation. There are no EICAS messages associated
with gravity crossflow valve operation. The flight crew must monitor main tank fuel
quantity indications to determine when the imbalance has been corrected.
An L (R) TO AUX crossflow switch/light should not be selected in combination with
the GRAVITY XFLOW switch/light.
NOTE
NOTE
P604_12_019
XFLOW
L TO AUX GRAVITY R TO AUX
ON OPEN ON
FUEL SYSTEM
12-18 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
GRAVITY XFLOW valve operation on the ground should be
closely monitored since fuel will flow from the higher wing to the
lower wing without any EICAS messages to indicate when the
imbalance has been corrected.
NOTE
FUEL SYSTEM
For Training Purposes Only
May 03
12-19
P I LOT T R A I N I N G GU I D E
Refueling/Defueling System
Description
A single-point refuel/defuel adapter is located in the right wing root area. The FUEL/
DEFUEL control panel is situated above the adapter on the side of the fuselage. The
FUEL/DEFUEL panel is used to test the integrity of the components of the fuel
system, and to select the individual fuel tanks for refueling and defueling.
An optional refuel/defuel panel is installed on the flight deck behind the copilot seat.
This panel has priority over the external panel, and displays individual fuel tank
quantity information and valve status.
Both internal and external FUEL /DEFUEL panels are normally powered by the APU
BATT DIR BUS.
To prevent overfilling the tanks, each tank system is equipped with high level sensors.
The high level sensor closes the associated shutoff valve(s) when the respective tank is
filled to capacity. The tank vent system ensures overfill protection during refueling.
Manual vent relief valves augment the normal vent system to prevent main and
auxiliary tank overpressure during refueling.
Maximum usable fuel capacities are attainable through pressure
refueling only.
NOTE
FUEL SYSTEM
12-20 For Training Purposes Only
Jan 04
P I LOT T R A I N I N G GU I D E
LOCATION POUNDS KILOS GALLONS
(US)
GALLONS
(IMP) LITERS
Left main tank 4874 2210 722 601 2733
Right main tank 4874 2210 722 601 2733
Center aux tank 5066 2296 750 625 2839
Forward aux tank 1465 664 217 181 821
Aft aux tank 641 291 95 79 360
Left saddle tank 903 409 134 111 506
Right saddle tank 903 409 134 111 506
Tail cone tank 1341 608 199 165 752
Total capacity 20067 9097 2973 2474 11250
Based on a fuel density of 6.75 lb (3.06 kg) / US gallon, and aircraft parked with 0.5° nose down and wings
level.
Max Usable Capacities Attainable through Pressure Refueling
Table 12-1
LOCATION POUNDS KILOS GALLONS
(US)
GALLONS
(IMP) LITERS
Left main tank 4523 2051 670 558 2536
Right main tank 4523 2051 670 558 2536
Auxiliary tank 6676 3028 989 823 3743
　
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