MD Helicopters CSP-900RMM-2 Servicing And Maintenance Download

Page: 1938 / 2144

CSP

−

900RMM

−

MD Helicopters, Inc.

Rotorcraft Maintenance Manual

Page 2
Revision 21

71-00-00

A. Modules

Each engine has a reduction gearbox and a
turbomachinery module. The turbomachinery
module operates the engine reduction gearbox
during normal operation. The reduction
gearbox operates the engine accessories and
helicopter drive system. This keeps the engine
and helicopter in operation.

Reduction Gearbox Module -

The reduction gearbox attaches to the front of
each engine. The engine driven accessories
attach to the reduction gearbox.

The reduction gearbox operates the engine
output shaft too deliver power to the drive
train.

The reduction gearbox operates the engine
accessories that follow:

Output Shaft -

Couples the engine to the

input drive shaft.

Torque Sensor -

Pulse type sensor. Measures

a phase shift when a special torque shaft is
torsionally twisted.

Air Conditioning Compressor Assembly -

Supplies compression for ECS vapor cycle
cooling system.

Starter Generator -

Supplies engine start

function. Supplies 28 Vdc 200-ampere
generator output to the helicopter electrical
system. On helicopters equipped with

PW207E

, a generator cooling modification

can

be installed which increases the outside air
temperature operating envelope to

125

(51.7

at sea level (Ref. Section 01-00-00,

Table 202).

Ng Speed Sensor -

Magnetic pulse pick-up

sensor. Senses the movement of the compres
sor turbine-gear wheel teeth.

Npt Speed Sensor -

Magnetic pulse pick-up

sensor. Senses the movement of the power
turbine-gear wheel teeth.

Permanent Magnetic Alternator (PMA) -

Supplies 28 Vdc to the Electronic Engine
Control (EEC).

Fuel Pump -

Compressor turbine driven

pump. The pump pressurizes fuel from the fuel
storage subsystem. The

PW206E / PW207E

have a suction feed system as a back-up feed
mode.

Pressure Oil Pump Drive Pad -

Internal

drive that drives the integral oil pump.

Accessory Drive Pad -

External drive pad

for optional gearbox driven accessories.

Turbomachinery Module -

The turbomachinery module operates the
reduction gearbox.

The system uses the EEC to give engine
operational parameters. The EEC receives
engine and helicopter performance inputs to
give fuel flow requirements to govern the
power turbine speed (Npt) at the correct speed
setting. The EEC computes the engine
transient power demands which, result in fast
engine response, minimizing rotor droops and
torque overshoots.

A high voltage ignition unit and two spark
igniters start the combustion. 25% of the air
that goes into the engine is necessary for
combustion.

The use for the remaining 75% of air that goes
into the engine is as follows:

Improve acceleration rate by compressor bleed
air control for secondary fuel flow atomization.

Pressurization of bearing compartment seals
for scavenge oil blow down.

Surface and internal cooling of combustion
chamber and hot section components.

Bleed air source for helicopter Heat/Defog and
Inlet Particle Separator systems.

Air enters the engine through a radial inlet
plenum, and flows through the radial compres
sor case inlet screen. Air is directed aft to the
centrifugal impeller. The accelerated air from
the impeller passes through diffuser tubes that
turn the air 90

, converting velocity into static

pressure. The high-pressure static air goes to
surround the combustion chamber.

The combustion chamber has various sizes of
perforations which allow compressor high
pressure static air to enter the combustion
chamber. The airflow changes direction 180

MD Helicopters CSP-900RMM-2, Servicing And Maintenance

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