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LO PRESS
WING Transfer SOV
Controlled by the FMQGC or the
WING XFER switch on the fuel
control panel.
Engine Feed
Shutoff Valve
• Applicable engine FIRE
DISCH handle.
NOTE: The engine run
switches activate the
HPSOV located in the
FMU not these shut-off
valves. These are only
activated by the “FIRE
DISCH” handle.
Fuel Crossfeed SOV
Controlled by the
switch on the Fuel
Control Panel. It is
used to interconnect
the engine feed lines.
APU Feed Shutoff Valve
• Activated by the RUN
position switch on the
APU control panel.
• Also controlled by the
APU FIRE DISCH
handle.
GX_appx_008
For Training Purposes Only
Sept 04
Appx-25
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
FUEL FILTER, QUANTITY AND TEMPERATURE READOUT
P P P
P
P P
P
P
FUEL
AUX
23°C
APU
23°C
TOTAL FUEL
359OOLBS
149OOLBS
AUX
61OOLBS
149OOLBS
FUEL USED
2OOLBS
LO PRESS
32°C 32°C
LO PRESS
Wing Fuel Quantity
Indicates fuel quantity, in the
respective wing tank, in
pounds (lbs).
Total Fuel Quantity
Indicates fuel quantity, in all
fuel tanks, in pounds (lbs).
Fuel Used Quantity Readout
Indicates fuel quantity burned.
Fuel Filter
• Green
• Amber
– Indicates normal
fuel flow through the filter.
– Fuel pressure
drop exists across the
filter.
Fuel Quantity Readout
(Center Fuselage Tank)
Indicates fuel quantity, in the
center tank, in pounds (lbs).
Engine Inlet Fuel Temperature
• Green
• Amber
– Engine fuel
temperature is 5°C.
– Engine fuel
temperature is < 5°C.
>
Fuel Filter Flow Line
Green
Amber
• – Indicates normal
fuel flow to the engine.
• Fuel pressure
drop exists across the filter,
flow line from the filter to
the engine turns amber.
–
GX_appx_009
Bulk Fuel Temperature
Readout
• Green
• Amber
With Fuel Recirculation
system On:
• Green
• Amber
– Temperature of
fuel in tanks is between
-35°C and +54°C.
– Temperature of
fuel in tanks is lower than
-35°C or greater than
+54°C.
– Temperature of
fuel in tanks is between
-35°C and +10°C.
– Temperature of
fuel in tanks is lower than
-35°C or greater than
+10°C.
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-26 For Training Purposes Only
Sept 04
FUEL PUMP DISPLAYS
P P P
P
P P
P
P
FUEL
AUX
23°C
APU
23°C
TOTAL FUEL
325OOLBS
132OOLBS
AUX
61OOLBS
132OOLBS
FUEL USED
56OOLBS
LO PRESS
32°C 32°C
LO PRESS
L or R DC Auxiliary Pumps
ON
NOTE
OFF
• – For takeoff and landing, primary pump
failure, and wing transfer of fuel.
: The AUX PUMP cannot be used to support
the engine feed system and wing transfer at the
same time. In auto, engine feed will have priority
over wing transfer. Manual overide is always
possible.
• – When commanded by the switch on the
Fuel Control Panel.
– When both primary pumps are on and no wing
transfer is required.
Center Transfer Pumps
Controlled by the FMQGC and
transfers center tank fuel to the
wing tanks. No manual control.
L or R AC Boost Pumps
ON
OFF
• – At all times with the engines
running.
• – When commanded by the
switch on the Fuel Control Panel.
GX_appx_010
For Training Purposes Only
Sept 04
Appx-27
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
FUEL QUANTITY AND INDICATION
The fuel quantity gauging system is an ac-type capacitance system. Fuel quantity
probes, compensators, densitometers, temperature sensors and high level detectors are
inputs received by the FMQGC. The FMQGC uses this acquired data to compute the
fuel quantity for each tank and total fuel quantity remaining on board the airplane.
The FMQGC outputs the computed individual fuel tank, total quantity and fuel
temperature for EICAS display. The fuel system computer corrects for airplane pitch
　
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