曝光台 注意防骗
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groups of the pilot’s and copilot’s circuit breaker panels respectively.
The following CAS illuminations are specific to the standby fuel
pumps:
XFLOW SWITCH AND CROSSFLOW SHUTOFF VALVE
The XFLOW switch, within the FUEL group of the aft pedestal, controls
the crossflow shutoff valve. The valve is normally in the closed position.
Depressing the XFLOW switch illuminates a white bar and power
is applied to open the motorized crossflow shutoff valve allowing fuel
to flow between the wing tanks.
To balance wing fuel, the XFLOW switch should be set to open (white
bar illuminated) and the heavy side L or R STBY switch set to ON. The
standby pump will continue to operate until the L or R STBY switch is
deselected. The crossflow shutoff valve allows all usable fuel aboard
the aircraft to be available to either engine. The switch should not be selected
except when correcting an out-of-balance condition.
The crossflow shutoff valve operates on 28-vdc supplied from the rear
hot bus through the 5-amp XFLOW VALVE CTRL circuit breaker located
within the FUEL group of the copilot’s circuit breaker panel. Loss of
power to the crossflow shutoff valve causes the valve to remain in its
last commanded position.
CAS Color Description
FUEL PRESS LOW Red Fuel pressure is low at the associated (L or
R) engine’s fuel pump inlet.
STBY PUMP ON White The associated (L or R) standby fuel pump is
receiving electrical power.
Pilot’s Manual
2-34 PM-126A
The following CAS illuminations are specific to the XFLOW switch and
crossflow shutoff valve:
FUEL INDICATING SYSTEM
The fuel indicating system consists of a refueling control panel, a fuel
quantity signal conditioner, 16 wing tank fuel quantity probes (8 each
wing), and a fuselage tank fuel quantity probe. The system provides
fuel quantity accuracy which indicates zero at zero fuel and is corrected
for pitch and roll through the AHRS system.
Power for the fuel indicating system is 28-vdc supplied through the 1-
amp L and R QTY circuit breakers located within the FUEL groups of
the pilot and copilot circuit breaker panels respectively.
REFUELING CONTROL PANEL
The refueling control panel is located on the exterior of the aircraft below
the right engine pylon. The panel is energized by the FUEL PNL
ON/OFF switch. This switch also activates a floodlight when placed in
the ON/FLD LT position. This floodlight is installed below the right engine
pylon and is energized from the EMER BATT hot bus to allow refueling
without accessing the aircraft. The DEFUEL/READY/OFF
switch opens the defuel shutoff valve and the crossflow shutoff valve
when selected to READY for defueling operations. An amber LED indicator
above the READY will illuminate when both valves are open. A
green LED indicator below the OFF will illuminate when both valves
are closed. A four-digit LED labeled TOTAL FUEL QTY will indicate
total usable fuel in LB or KG depending on aircraft configuration.
CAS Color Description
FUEL PRESS LOW Red Fuel pressure is low at the associated (L or
R) engine’s fuel pump inlet.
FUEL XFLO Amber The fuel crossflow valve is not fully opened or
closed as commanded.
FUEL XFLO OPEN White The fuel crossflow valve is open.
STBY PUMP ON White The associated (L or R) standby fuel pump is
receiving electrical power.
Pilot’s Manual
PM-126A 2-35
FUEL QUANTITY SIGNAL CONDITIONER AND PROBES
The fuel quantity signal conditioner is based on two independently
powered left and right wing channels. Each channel receives DC inputs
from their respective wing probes. Both channels independently monitor
the fuselage probe and receive aircraft pitch information from the
AHRS #1 unit. This data significantly increases the accuracy of the fuel
indicating system during climb and descent. Each channel monitors the
data output of the other for calculating total fuel quantity for transmittal
to the DAUs. Although each channel outputs the same fuel quantity
information, the DAUs will only read specific information. DAU #1
reads left quantity and total quantity. DAU #2 reads right quantity and
fuselage quantity. A weight-on-wheels input allows for separate calculation
software to operate “on the ground” or “in the air”, making the
system more accurate in both environments.
Aircraft 45-002 thru 45-258, and 45-260:
A wing fuel imbalance greater than 500 lb (227 kg) with flaps up or
greater than 200 lb (91 kg) with flaps greater than 3° will generate the
FUEL IMBALANCE amber CAS.
Aircraft 45-259, 45-261 thru 45-2000:
A wing fuel imbalance greater than or equal to 200 lb (91 kg) will generate
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