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returned to the feed tanks during operation. The low point of the main vent line is
continuously scavenged by a jet pump.
The vent line distribution is to a high point in the fuselage, preventing fuel from
reaching either of the two ram outlets and spilling overboard. If any fuel passes the
high point, it is collected by the surge box and is drained back to the tank before it
reaches the outlet. Each surge box vent line tubing runs vertically along the fuselage
side wall, and is coupled to the wing, center and aft tanks.
The vent system is fully redundant, such that any single blockage does not affect the
venting capability.
VENT SYSTEM SCHEMATIC
LEFT WING TANK
CENTER
WING
TANK
AIR
SCOOP
AIR
SCOOP
RIGHT WING TANK
AFT
TANK
GX_11_003
RIGHT
SURGE
BOX
LEFT
SURGE
BOX
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
11-8 For Training Purposes Only
Sept 04
PRESSURE RELIEF VALVES
Relief valves are used to protect the tanks from over pressurization, in the case of
failure of the vent system and/or refuel shutoff valve. They are located in the wing,
center and aft tanks. The aft tank relief valve has a similar function as the center and
wing tank relief system, but also incorporates a negative-pressure relief feature which
can activate in an emergency descent.
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.
For Training Purposes Only
Sept 04
11-9
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
FMQGC SCHEMATIC
ENGINE INDICATING AND CREW ALERTING SYSTEM AND
CENTRAL AIRCRAFT INFORMATION MANAGEMENT SYSTEM
FUEL SYSTEM
COMPONENTS
Boost Pumps INHIB
Wing Transfer Mode
Aft 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_11_004
REFUEL/
DEFUEL
PANEL
P I LOT T R A I N I N G GU I D E
FUEL SYSTEM
11-10 For Training Purposes Only
Sept 04
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
ON
AUX PUMP
OFF
PRI PUMPS
OFF
R RECIRC
ON
AFT XFER
AUTO
OFF ON
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
　
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