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is displayed.
The three XFLOW switch/lights on the FUEL control panel correspond to three valves 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
The FUEL IMBALANCE caution message will be triggered in flight
whenever more than 400 lb fuel imbalance exists between the left
and right main tanks, and flaps are set at 20-degree position or
more.
FUEL SYSTEM
Description
Vol. 2 12−10−15
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FUEL TRANSFER (CONT'D)
XFLOW Switch/Lights
Figure 12−10−13
L (R) TO AUX XFLOW Switch/Lights
Pushing the L (R) TO AUX XFLOW switch/light opens a valve which allows fuel flow 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 lb 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.
NOTE
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.
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 12−10−16
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
REFUELING/DEFUELING SYSTEM (CONT'D)
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
LOCATION POUNDS KILOS
GALLONS
(US)
GALLONS
(IMP)
LITERS
Left main tank 4,874 2,210 772 601 2,733
Right main tank 4,874 2,210 772 601 2,733
Center aux tank 5,066 2,296 750 625 2,839
Forward aux tank 1,465 664 217 181 821
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 1,341 608 199 165 752
Total capacity 20,067 9,097 2,973 2,474 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
LOCATION POUNDS KILOS
GALLONS
(US)
GALLONS
(IMP)
LITERS
Left main tank 4,523 2,051 670 558 2,536
Right main tank 4,523 2,051 670 558 2,536
Auxiliary tank 6,676 3,028 989 823 3,743
Total capacity 15,722 7,130 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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庞巴迪挑战者605机组操作手册 CL605-FUEL_SYSTEM(6)
