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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 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−10
ENGINE FUEL SYSTEM (CONT'D)
Fuel System Schematic
FGF1810_001
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)
ENGINE
L RUN R
OFF OFF
WING FEED
INHIBIT
AUX PUMP
PRI PUMP
R
OFF
OFF
R RECIRC
ON
INHIBIT
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
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:
· Fuel metering through the FMU for:
− Automatic start and relight.
− Idle Speed Control.
− Acceleration and deceleration.
− Engine power setting.
− Limit protection for N1 and N2 speeds.
− Limit protection for temperature.
− Independent overspeed protection of N1 and N2.
· Compressor airflow control via the VSV and HP compressor bleed valves, to ensure:
− Surge free acceleration and deceleration.
− Surge recovery.
− Stable operation.
· Control of oil and fuel temperature.
· Control of the ignitors and start air valve.
· Partial control of the thrust reverser system functions.
· Control of the engine power in reverse thrust.
· Control of system electrical supply, either 28VDC or dedicated generator output to the EEC
and through to the FADEC.
GF1810_019
THROTTLE
MODULE
EEC
28 VDC
DEDICATED GEN
FMU
HP 5 & 8 BLEED VALVES
STATOR VANE SYSTEM
STARTER AIR VALVE
IGNITION SYSTEM
FUEL COOLED OIL COOLER
THRUST REVERSER
OTHER AVIONICS SYSTEMS
ENGINE INPUTS
DAU 1
DAU 2
DAU 3
IAC 1
IAC 2
IAC 3
ADC 1
ADC 2
ADC 3
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−12
ENGINE ELECTRONIC CONTROLLER (EEC)
The EEC is the controlling unit of the FADEC system and is located on the top of the engine in a
fireproof trough.
GF1810_020
ENGINE ELECTRONIC
CONTROLLER(EEC)
The EEC is an electronic control unit containing two channels A and B. Each channel is comprised of
a Central Processor Unit (CPU), Power Supply Unit (PSU) and two Independent Overspeed
Protection (IOP) units.
The PSU controls the power supplies to the FADEC system and to the EECs, CPU and IOP.
The PSU will control the switch over from the airplane 28VDC supply to power supplied by the
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