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• Move the MODE SELECTOR switch to AUTO REFUEL
• Disconnect the tender as required and return the RDCP MASTER switch to the
OFF position
• Secure RDCP access panel
For Training Purposes Only
Sept 04
Appx-49
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
PRESSURE DEFUELING
Pressure defueling of the fuel tanks is accomplished through the fuel shutoff valves
and single point adapter. Pressure defueling is identical to suction defueling, except
that primary defueling flow is provided by the AC boost pumps or DC auxiliary pump
in each feed tank.
NOTE
AC or DC electrical power is required to operate the airplane
pumps for this procedure.
Direct pressure defueling of the wing tank is accomplished using the AC boost pumps
or DC auxiliary pump in each feed tank.
Direct pressure defueling of the center tank is not possible. Center tank fuel may
however be transferred to the wing tanks using the center tank transfer pumps. From
there, it may then be defueled via the wing tank.
LATER VERSION RDCP REFUEL/DEFUEL PROCEDURES
Differences in Later Refuel/Defuel Panel are as follows:
• The MODE SELECTOR switch is now rotary
• The START/STOP switch now includes the SOV test function
• The master ON/OFF switch is part of the mode selector switch
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-50 For Training Purposes Only
Sept 04
EICAS MESSAGES
GX_appx_025
CTR TANK FULL
FUEL COMPUTR FAIL
FUEL LO QTY
L (R) FUEL RECIRC FAIL
L (R) PRI FUEL PUMPS
WING TO CTR LEAK
FUEL IMBALANCE
FUEL UNIT MISMATCH
FUEL XFER FAIL
FUEL XFER ON
FUEL XFER FAIL
FUEL XFER ON
FUEL TEMP SENSOR
FUEL UNIT MISMATCH
The refuel/defuel panel and
EICAS indications are correct
but in different units of
measurements.
CTR TANK FULL
Center tank has reached or
exceeded its computer
controlled maximum capacity
of 6100 lbs.
FUEL XFER ON
Indicates that fuel is being
transferred from the left wing
tank to the right wing
unrequested.
FUEL XFER ON
Indicates that fuel is being
transferred from the right wing
tank to the left wing
unrequested.
FUEL COMPUTR FAIL
Indicates that both channels of
the fuel system computer have
failed.
L (R) PRI FUEL PUMPS
Indicates both left or both right
forward and aft primary AC
pumps have failed to operate
when requested.
WING TO CTR LEAK
Indicates that the fuel level in
the center tank has increased by
600 lbs or more.
FUEL XFER FAIL
Transfer from the left wing to the
right wing has been requested
and failed.
FUEL XFER FAIL
Transfer from right wing to left
wing has been requested and
failed.
FUEL TEMP SENSOR
On ground, indicates that a fuel
temperature sensor is failed.
With flaps deployed, will be
posted only if the failure requires
corrective action.
FUEL IMBALANCE
Indicates that a fuel quantity imbalance
exists between the left and right wing
tanks of:
– More than 1100 lbs (499 kg) in flight
– Between 600 lbs (272 kg) and 1100
lbs (499 kg) on ground or in Takeoff /
Approach configuration.
FUEL LO QTY
Indicates fuel in the left or right
wing tank is less than 600 lbs
L (R) FUEL RECIRC FAIL (272 kg).
Indicates that the FRTT valve is
not in the commanded or
allowed position.
For Training Purposes Only
Sept 04
Appx-51
P I LOT T R A I N I N G G U I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
EICAS MESSAGES (Cont)
APU FUEL SOV
L (R) ENG FUEL SOV
CTR FUEL XFER FAIL
WING FUEL HI TEMP
WING FUEL LO TEMP
L (R) WING FULL
L (R) PRI FUEL PUMP
L (R) AUX FUEL PUMP
CTR XFER FAULT
XFER VALVE OPEN
FUEL XFER ON
XFEED VALVE FAIL
APU FUEL SOV
Indicates that the APU fuel
shutoff valve has failed.
GX_appx_026
L (R) WING FULL
Indicates that fuel quantity in
the left or right wing tank has
exceeded its maximum
allowable value.
L (R) AUX FUEL PUMP
Indicates that the auxiliary fuel
pump on the affected side has
failed to operate when
requested.
WING FUEL HI TEMP
Indicates that the left or right
wing fuel bulk temperature is
above the high temperature
limit.
L (R) ENG FUEL SOV
Indicates that the engine fuel
shutoff valve on the affected
side is not in its commanded
　
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