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EICAS
NOTE
Can be displayed in pounds/hour (pph) or kilograms/hour (kph).
GX_17_037
575O FF (PPH) 575O
17-20 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
POWER PLANT
• 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
• 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 shutdown
and is passed through a drain valve in the FMU to the drain tank. The drain 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
GX_17_038
32 °C
For Training Purposes Only
Sept 04
17-21
P I LOT T R A I N I N G GU I D E
POWER PLANT
FUEL SYSTEM SCHEMATIC
GX_17_039
HP FUEL
FILTER
FUELMANIFOLD
SPLITTER UNIT
T
FUEL TEMP
TRANSDUCERS
10 FUEL
NOZZLES
10 FUEL
NOZZLES
LOWER UPPER
FUEL
MANIFOLDS
TO
EEC
TO
EEC
VSV
CONTROLLER
METERING
VALVE
HP
SOV
DV
FUEL METERING
UNIT (FMU)
SPILL
VALVE
HP FUEL PUMP
LP
FUEL
PUMP
FUEL FLOW
TRANSMITTER
FUEL-COOLED
OILCOOLER
(FCOC)
LP FUEL
FILTER
LP FILTER
DIFFERENTIAL
PRESSURE
SWITCH
SDV
TO
ENGINE
TO
COCKPIT
VARIABLE
STATOR-VANE
(VSV) ACTUATOR
TO
EEC
TO
EEC
FROM
LP
FUEL
PUMP
DRAIN
TANK &
EJECTOR
MAX REV
ENG
RUN
OFF OFF
L R
Fuel Low-
Pressure
Switch
L
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMPS
OFF
L RECIRC
ON
L
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMPS
OFF
L RECIRC
INHIBIT
OFF
Global 5000 and
A/C equipped with
-9 FMQGC or later
17-22 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
POWER PLANT
ENGINE BLEED AIR SYSTEM
The pneumatic system supplies compressed air for air conditioning and pressurization,
Ice and Rain Protection and Engine starting. The pneumatic air supply normally comes
from the engines (inflight), and the APU or a high pressure ground air supply unit (on
the ground).
The engine bleed air system is controlled during all phases of operation by two Bleed
Management Controllers (BMC).
The BMC selects air from either the low pressure port (5th stage of the high pressure
compressor) or the high pressure port (8th stage of the high pressure compressor)
depending on the demand. Under normal operation (inflight), the air is selected from
the 5th stage of compression. When the airflow is insufficient, the BMC will select the
8th stage of compression.
L and R ENG BLEED AIR selection, AUTO or ON, is accomplished via the BLEED/
AIR COND/ANTI-ICE panel on the overhead panel. A crossbleed valve (CBV) is
installed between the left and right pneumatic ducts, which can be opened,
automatically by the BMC or manually, to provide bleed air for engine starting. The
APU is normal source of bleed air used for engine starting.
GX_17_040
APU
ENGINES
GROUND
SOURCE
BLEED
MANAGEMENT
CONTROLLER
AIR
CONDITIONING
SYSTEM
ENGINE
STARTING
ANTI-ICING
SYSTEM
EICAS
DISTRIBUTION
INDICATING
BLEED
AIR
SYSTEM
For Training Purposes Only
Sept 04
17-23
P I LOT T R A I N I N G GU I D E
POWER PLANT
For more information on ECS, see chapter 13, Integrated Air Management System.
For more information on cowl and wing anti-icing, see chapter 3, Anti-Ice System.
THRUST MANAGEMENT SYSTEM
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航空翻译 www.aviation.cn
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庞巴迪挑战者手册9(134)
