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Green . Temperature of fuel in tanks is between .35°C and +10°C.
Amber . Temperature of fuel in tanks is lower than .35°C or greater than +10°C.
FGF1210_021
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FUEL PUMP DISPLAYS
L or R DC Auxiliary Pumps
ON . For engine starting, take.off and landing, primary pump failure and wing transfer of fuel.
NOTE: 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 override is always possible.
OFF . 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 centre tank fuel to the wing tanks. No manual control.
L or R AC Boost Pumps
ON . At all times with the engines running.
OFF . When commanded by the switch on the Fuel Control Panel.
FGF1210_022
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
FUEL SHUTOFF DISPLAYS
Wing Transfer Shutoff Valve
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 shutoff valves. These are only activated by the FIRE DISCH handle.
Fuel Crossfeed Shutoff Valve
Controlled by the switch on the Fuel Control Panel. It is used to interconnect the engine feed lines.
Fuel Return To Tank (FRTT) Valve APU Feed Shutoff Valve
Activated by the RUN positionActivated by the FMQGC.
switch on the APU Control Panel.
Also controlled by the APU FIRE DISCH handle.
FGF1210_023
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
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
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.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
FMQGC SCHEMATIC
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
EICAS MESSAGES
L (R) PRI FUEL PUMPS
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