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Fuel Flow Transmitter . Provides an indication of fuel flow to the EEC and to EICAS.
NOTE: Can be displayed in Pounds/Hour (PPH) or Kilograms/Hour (KPH).
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HP Filter . Prevents debris from entering the fuel manifold and causing possible blockage of the fuel spray nozzles.
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Fuel Temperature Transducers . Fuel enters the fuel filter and passes over the temperature transducers which relay the information to the EEC for the heat management system and displays the temperature on the FUEL synoptic.
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Overspeed and Splitter Unit (OSU) . Splits the fuel flow equally between the lower and upper fuel manifolds. In the event of LP shaft breakage detection, the OSU has a fuel shut-off mechanism that will open an overspeed valve to allow fuel pressure to close the splitter valve.
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Fuel Spray Nozzles . Deliver the metered fuel into the combustion chamber. The combination of HP air and narrow fuel orifice in the nozzle causes the fuel to be forced into a fine spray for maximum efficiency combustion.
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Fuel Drain Tank . The fuel is drained from the fuel manifold after engine shut down and is passed through a drain valve in the FMU to the drains tank. The drains tank delivers the fuel to the LP pump during the next engine run. The tank has an integral injector which uses LP pump delivery fuel as a motive force to empty the tank.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
POWER PLANT
ENGINE FUEL SYSTEM (CONT'D)
Fuel System Schematic
TO TO
EEC EEC
FUEL-COOLED FUEL FLOWTO TOOIL COOLER TRANSMITTERENGINE EEC(FCOC)
VARIABLE STATOR-VANE (VSV) ACTUATOR
TO EEC LP FILTER DIFFERENTIAL
T PRESSURE SWITCH
FUEL BYPASS VALVE
TO COCKPIT OVERSPEED SPLITTER UNIT
(OSU)TO DRAINS
SDV
TANK
HP FUEL PUMP VSV
CONTROLLER
EJECTOR
SPILL METERING HP
VALVE VALVE SOV
FROM
AIRCRAFT
FUEL METERING
DVUNIT (FMU)TANK
RELIEF VALVE
A
B
DRAINS TANK (ELECTRICAL)
AND EJECTOR
LOWER UPPER
ENGINE
R
RUN
LR
WING FEED INHIBIT
AUX PUMP
OFF
OFF
OFF
PRI PUMP
OFF
R RECIRC INHIBIT
ON
FGF1810_001
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
CSP 700.5000.6 18.10.11
POWER PLANT
FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC)
Thrust management is controlled throughout all phases of operation by the Full Authority Digital Engine Control (FADEC). An Electronic Engine Controller (EEC) is the major part of the FADEC, interfacing between the airplane systems and the engine.
The EEC provides the following control functions:
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Fuel metering through the FMU for:
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