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in the FMU not these shutoff
valves. These are only
activated by the
FIRE DISCH handle.
FUEL
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−27
FUEL SYNOPTIC PAGE SYMBOLS
The following represents the EICAS symbols and flow line logic for the fuel synoptic page. The
symbols are shown in serviceable and failure conditions.
EICAS Philosophy
GF1210_029
VALVE AND FLOW LINE LOGIC
OPEN
VALVE
NOT FAILED
CLOSED
TRANSIT
INVALID
VALVE
FAILED
DIRECTION OF FLOW
PUMP AND FLOW LINE LOGIC
ON
PUMP
INVALID
OFF
FAILED
OFF
PUMP
FAILED
ON
P
P
P
P
P
DIRECTION OF FLOW
FUEL MANAGEMENT QUANTITY GAUGING SYSTEM (FMQGS)
The FMQGS 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.
FUEL
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
12−10−28
FMQGC SCHEMATIC
ENGINE INDICATING AND CREW ALERTING SYSTEM
AND
CENTRAL AIRCRAFT INFORMATION MANAGEMENT SYSTEM
FMQGC
CHANNEL
1
CHANNEL
2
LEFT WING TANK RIGHT WING TANK
CENTER WING TANK
Fuel Quantities
Fuel Temperature
EICAS Messages
Caution
Advisory
Status
EICAS Inputs from
other sources
Sensor Data:
Tank Probes
Compensators
Densitometer
Temperature
Hi/Lo Level
Pump Pressure Switches
SOVs Position Feedback
Cockpit Control
Panel
Cockpit Fuel
Fire Handles
Panel
APU On
L Engine On
R Engine On
Fuel System
Components
Refuel
Defuel
Panel
Displays Data:
Total Fuel Quantity
Individual Tank Quantities
Preselect Quantity
Alert Messages
Boost Pumps INHIB
Wing Transfer Mode
XFEED Mode
Input and output
Input or output
LEGEND
Engine Start
FGF1210_024
FUEL
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−29
EICAS MESSAGES
FGF1210_025
WING TO CTR LEAK
Indicates that the fuel
level in the center tank
has increased by 600
lbs or more.
L (R) PRI FUEL PUMPS
Indicates that the forward
and aft primary AC pumps
on the affected side have
failed to operate when
requested.
FUEL COMPUTR FAIL
Indicates that both
channels of the fuel
system computer have
failed.
−> FUEL XFER FAIL
Transfer from the left
wing to the right wing
has been requested and
failed.
FUEL UNIT MISMATCH
The refuel/defuel panel
and EICAS indications
are correct but in different
units of measurements.
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.
CTR TANK FULL
Center tank has reached or exceeded
its computer controlled maximum
capacity of 6100 lbs.
<− FUEL XFER FAIL
Transfer from right wing
to left wing has been
requested and failed.
−> 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 TEMP SENSOR FAIL
On ground, indicates that a
fuel temperature sensor is
failed. With flaps deployed,
will be posted only if the failure
requires corrective action.
L (R) FUEL RECIRC FAIL
Indicates that the FRTT
valve is not in the
commanded or allowed
position.
FUEL IMBALANCE
FUEL COMPUTR FAIL
L PRI FUEL PUMPS
FUEL UNIT MISMATCH
WING TO CTR LEAK
FUEL TEMP SENSOR FAIL
L FUEL RECIRC FAIL
FUEL LO QTY
−> FUEL XFER FAIL
−> FUEL XFER ON
<− FUEL XFER FAIL
<− FUEL XFER ON
　
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