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proceeding on to the HP pump. The fuel filter contains a combined DP switch /indicator. The
combined unit provides indications on EICAS of low pressure fuel or an impending LP fuel filter
blockage. A FUEL FILTER (single) or L−R FUEL FILTER (both) message is displayed on
EICAS. If a fuel low pressure switch is also provide to alert the crew of low fuel pressure in the
supply line to the HP pump. A FUEL LO PRESS message will be displayed on EICAS.
· HP Fuel Pump − The HP fuel pump increase the pressure of the fuel for delivery to the Fuel
Metering Unit (FMU).
· The FMU meters the fuel required by the engine in response to the Electronic Engine
Controller (EEC) and provides pressure which is used as a motive force for the VSVs. The
variable inlet guide vanes and the first three stages of stators of the HP compressor adjust the
airflow entering the compressor to assist during engine starts, help prevent compressor surges
and maintain best specific fuel consumption. The FMU also prevents fuel flowing to the fuel
spray nozzles in the event of an engine overspeed and drains the fuel manifold into the drains
tank on engine shut down. The desired fuel flow is maintained by controlling the position of the
fuel metering valve. A constant pressure drop is maintained across the fuel metering valve by
the spill valve, which diverts unused fuel back to the fuel pump. The spill diverter valve allows
spill return fuel to the FCOC at low engine speeds to prevent fuel from recirculating around the
HP pump, which could cause excessive fuel temperatures. The high pressure shutoff
valve
(HPSOV) allows the fuel to enter the HP fuel filter and is controlled by the FMU and the engine
run switches.
· Fuel Flow Transmitter − Provides an indication of fuel flow to the EEC and to EICAS.
5750 FF (PPH) 5750 NOTE: Can be FFd (PPiH)splayed in Pounds/Hour (PPH) or Kilograms/Hour (KPH).
· HP Filter − Prevents debris from entering the fuel manifold and causing possible blockage of
the fuel spray nozzles.
· 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.
GF1810_017
32 °C
· 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 shutoff
mechanism that will open an overspeed valve to allow fuel pressure to close the splitter valve.
· 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.
· 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.
POWER PLANT
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
18−10−10
ENGINE FUEL SYSTEM (CONT'D)
Fuel System Schematic
GF1810_018
FUELCOOLED
OIL COOLER
(FCOC)
HP FUEL PUMP
RELIEF VALVE
FUEL METERING
UNIT (FMU)
T
FUEL FLOW
TRANSMITTER
VARIABLE
STATORVANE
(VSV) ACTUATOR
DRAINS TANK
AND EJECTOR
LOWER UPPER
AIRCRAFT
TANK
A B
FROM
DV
CONTROLLER
SDV VSV
SPILL
VALVE
TO
DRAINS
TANK
EEC
TO
TO
METERING
VALVE
COCKPIT
EJECTOR
LP FILTER
DIFFERENTIAL
PRESSURE
SWITCH
ENGINE
TO
HP
SOV
FUEL
BYPASS
VALVE
EEC
TO
EEC
TO
EEC
TO
OVERSPEED
SPLITTER UNIT
(ELECTRICAL)
(OSU)
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMP
OFF
R
ENGINE
L RUN R
OFF OFF
POWER PLANT
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
18−10−11
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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