CSP
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902RFM207E
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1
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
Systems Description
Original
7
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29
Reissue 2
F92
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070
SOLENOID
SHUTOFF VALVE
PARTICLE SEPARATOR EJECTOR
EJECTOR
TUBE ASSEMBLY
BLEED AIR
TUBE ASSEMBLY
PARTICLE
SEPARATOR PANEL
BYPASS DOOR
SOLENOID LATCH
STANDARD INLET
SCREEN
BYPASS DOOR
NACA INLET DOOR
(IF INSTALLED)
Figure 7
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16. Engine Air Intake
7
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10. ENGINE POWER MANAGEMENT SYSTEM
Automatic Engine Control:
The Pratt and Whitney PW207E engine is equipped with a single channel Full
Authority Digital Electronic Control (FADEC) which consists of an Electronic
Engine Control (EEC), Fuel Metering Unit (FMU), and fuel pumps. A manual
backup system is provided for emergency operation in case the EEC becomes
inoperative. The pilot's controls for normal operation consist of two rotary engine
control switches on the engine control panel for the left and right engines. These
switches are gated between OFF and IDLE: the switch knobs must be lifted
to pass the gates. The other switch positions are FLY and TRAIN and are not
gated. For normal operation, the two twist grips on the collective pitch stick
are always left in their NORMAL detent position.
The EEC's of the two engines are connected together electrically for a torque-
matching function, and are both connected electrically to the collective stick
and pedal position resolvers for power change anticipation.
When the EEC's are working properly, the procedure for starting and stopping
requires no more than selection of the desired engine operation with an engine
control switch.
P&WC has built into the PW207E engine the proper shielding to protect the
EEC's from the HIRF threat, and the helicopter's wiring system components
Summary of Contents for MD900 Explorer
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