MD Helicopters CSP-900RMM-2, Техническое обслуживание и ремонт

Страница: 1937 / 2144

CSP − 900RMM − 2 MD Helicopters, Inc.
Rotorcraft Maintenance Manual
Page 1
Revision 14
71-00-00
POWERPLANT
DESCRIPTION AND OPERATION
1. Powerplant
The powerplant system is approved for Pratt
and Whitney engines; two (2) PW206A, or two
(2) PW206E, or two (2) PW207E. The turbo­
shaft engines supply energy (torque, bleed air,
electrical power) to the helicopter systems.
The 900 CONFIG can have the following
engine models installed;
- PW206A engines,
- PW206E engines,
- PW207E engines.
The 902 CONFIG can have the following
engine models installed;
- PW206E engines,
- PW207E engines.
Each engine model requires a specific
Electronic Engine Control (EEC) and Inte­
grated Instrument Display System (IIDS).
The engines supply power to the helicopter
drivetrain for operation of the main rotor and
Anti-Torque systems. The engines supply
bleed air to operate the engine Inlet Particle
Separator (IPS) and Heat/Defog system. The
engines supply mechanical power to the
electrical system. The electrical system
changes the mechanical power to electrical
energy for power distribution and lighting.
The components that follow make the power­
plant system:
Engine - The engine supplies mechanical
energy for operation of the helicopter systems.
Air Intake - Airframe inlet duct for each
engine.
Engine Fuel and Control - A full authority
electronic engine control (EEC) system for
integrated control of each engine.
Ignition - Ignition source for engine start
along a wide temperature range.
Exhaust - Airframe exhaust duct for each
engine.
Oil - Pressure lubrication, oil scavenge and
filtration for each engine.
Powerplant Controls - Controls inputs for
each engine EEC system operation, or backup
mechanical throttle control for each engine.
Engine Indicating - Supplies cockpit
indications of each engines operational
performance.
Starting - Start system for each engine.
Drains - Drain system for each engine's oil
and fuel.
Bleed Air - Pneumatic source for Environ­
mental Control System (ECS) and engine Inlet
Particle Separator (IPS).
Fire Detection - Fire/overheat warning
system for each engine bay.
Fire Extinguishing - Extinguishing system
for each engine bay.
Engine Wash - Supplies wash capability for
both engines.
2. PW206A / PW206E / PW207E Engine
The engines attach to the engine deck aft of
the main transmission. Each engine has three
adjustable mounts that attach the engine to
the helicopter structure.
The PW206A, PW206E and PW207E turbo­
shaft engines are of modular design. They
incorporate a single-stage centrifugal com­
pressor driven by a single-stage compressor
turbine. The engines also have a single-stage
free spool power turbine that drives the
engine's two-stage reduction gearbox.
Each engine must have air intake, fuel,
ignition, exhaust, lubrication, powerplant
control, and indicating systems to support
engine start and normal operation. Each
engine bleed air system supplies a pneumatic
source for operation of the ECS system and
Inlet Air Particle Separator (IPS) during
normal operation.
The engines use fireseals to isolate the engine
hot section from the inlet plenum.
An engine wash system supplies a means to
wash either engine.
The PW207E does not have combuster drain
tube assemblies.