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center tanks.
FUEL MANAGEMENT QUANTITY GAUGING COMPUTER (FMQGC)
The FMQGC consists of a dual channel computer with BITE, utilizing capacitance
type probes in each tank to continuously measure the quantity of usable fuel. The fuel
computer performs all digital processing related to the system control and indication
and performs computations associated with fuel gauging system requirements. The
following schematic represents inputs and outputs of various components and systems
operations.
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-20 For Training Purposes Only
Sept 04
FMQGC SCHEMATIC
ENGINE INDICATING AND CREW ALERTING SYSTEM AND
CENTRAL AIRCRAFT INFORMATION MANAGEMENT SYSTEM
FUEL SYSTEM
COMPONENTS
Boost Pumps INHIB
Wing Transfer Mode
XFEED Mode
Fire Handles
APU On
L Engine On
R Engine On
Fuel Quantities
Fuel Temperature
EICAS Messages
Caution
Advisory
Status
EICAS Inputs from
other sources
Displays Data:
Total Fuel Quantity
Individual Tank Quantities
Preselect Quantity
Alert Messages
PUMP PRESSURE SWITCHES
SOV’S POSITION FEEDBACK
COCKPIT
CONTROL
PANEL
COCKPIT FUEL
PANEL
CHANNEL
1
CHANNEL
2
FMQGC
SENSOR DATA:
TANK PROBES
COMPENSATORS
DENSITOMETER
TEMPERATURE
HI/LO LEVEL
CENTER WING
TANK
AFT TANK Legend
Input and output
Input or output
LEFT WING TANK RIGHT WING TANK
GX_appx_004
REFUEL/
DEFUEL
PANEL
For Training Purposes Only
Sept 04
Appx-21
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
FUEL CONTROL PANEL
The fuel control panel is located on the overhead panel in the flight compartment. The
fuel control panel defines the operational modes, component controls, and component
inhibits.
The fuel control panel has switches, which when selected, override the automatic
control of certain components within the fuel system. Switch selections from this
panel are sent to the ACPC. The ACPC will then control the system from the inputs
received from the panel. The switch lamps come on when selected in combination
with certain EICAS messages, which represent the panel configuration or failure
within a given system.
FUEL CONTROL PANEL
FUEL
R
WING FEED
INHIBIT
L
WING FEED
INHIBIT
XFEED SOV
FAIL
OPEN
AUX PUMP
OFF
PRI PUMPS
OFF
L RECIRC
INHIBIT
OFF
AUX PUMP
OFF
PRI PUMPS
OFF
R RECIRC
INHIBIT
OFF
OFF
AUTO
WING XFER
WING XFER Switch
AUTO
OFF
• selection – Provides a means of transferring fuel from one
wing to the other. Controlled by the FMQGC.
• or selection – A left to right, or a right to left selection,
provides a means of tranferring fuel (in the direction of the arrow) from
one wing tank to the other.
• selection – Provides a method of inhibiting wing to wing transfer.
XFEED SOV Switch
FAIL
OPEN
• light – Will come on
when the valve does not
go to the commanded
position.
• light – When the
switch is selected, the
crossfeed valve opens and
interconnects the engine
feed lines.
AUX PUMP Switch
• OFF light – Indicates that
the right auxiliary pump has
been disarmed. The left
AUX PUMP has similar
logic.
PRI PUMPS Switch
• OFF light – Indicates that
both left wing primary
pumps have been
disarmed. The right PRI
PUMPS switch has similar
logic.
GX_appx_005
RECIRC Switch
• OFF light – Indicates that
the FRTT valve is open
when commanded by flight
crew.
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-22 For Training Purposes Only
Sept 04
FUEL SYSTEM SYNOPTIC PAGE
The FUEL synoptic page provides an overview of system status, as represented below
with both left and right engines running and no transferring of fuel taking place.
FUEL SYNOPTIC PAGE
P P P
P
P P
P
P
FUEL
AUX
–1O°C
APU
–1O°C
TOTAL FUEL
362OOLBS
15O5OLBS
AUX
61OOLBS
15O5OLBS
FUEL USED
OLBS
LO PRESS
32°C 32°C
LO PRESS
DC Auxiliary Pump
AC
Boost
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GLOBAL 5000 DIFFERENCES(8)
