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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.
A L (R) TO AUX XFLOW switch/light should not be selected in combination with the GRAVITY XFLOW switch/light.
NOTE
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.
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.
FUEL SYSTEM Description Vol. 2 12.10.17
Oct 05/06
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.
NOTE
Maximum usable fuel capacities are attainable through pressure refueling only.
Max Usable Capacities Attainable Through Pressure Refueling
GALLONS GALLONS
LOCATION POUNDS KILOS LITERS
(US) (IMP)
Left main tank 2,733 Right main tank 4,874 2,210 772 601 2,733 Center aux tank 2,839 Forward aux tank 1,465 664 217 181 821 Aft aux tank 360 Left saddle tank 903 409 134 111 506 Right saddle tank 506 Tail cone tank 1,341 608 199 165 752 Total capacity 11,250 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 Overwing Refueling
GALLONS GALLONS
LOCATION POUNDS KILOS LITERS(US) (IMP)
Left main tank 4,523 2,051 670 2,536 Right main tank 670 2,536 Auxiliary tank 6,676 3,028 989 3,743 Total capacity 2,329 1,939 8,815 Based on a fuel density of 6.75 lb (3.06 kg)/US gallon, and aircraft parked with 0.5° nose down and wings
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