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bottle. Bottle discharge is indicated on the FIRE
TEST panel by illumination of the PRI DISCH and
RES DISCH displays. The fire extinguishing
equipment receives 28 vdc from the emergency dc bus
through the PILOT, CPG and APU FIRE EXTGH
circuit breakers on the pilot overhead circuit breaker
panel.
2.18 FIRST AID KITS.
Two first aid kits are provided: one on the inside, aft
portion of the pilots right canopy panel and one on the
lower side of the CPG left console.
2.19 CHEMICAL, BIOLOGICAL, AND
RADIOLOGICAL (CBR) FILTER/BLOWER.
The CBR filter/blower provides filtered air to the flight
crew when cockpit air is contaminated. Each crew
member carries his own CBR blower/mask on board
and connects it to the external power source, located on
the left side armored wing of his seat (fig 2-14).
Refer to TM 3-4240-312-12&P for CBR filter blower operation,
installation and maintenance instructions.
2.20 EMERGENCY PROCEDURES.
Chapter 9 describes emergency procedures.
2-21
TM 1-1520-238-10
Section Ill. ENGINES AND RELATED SYSTEMS
2.21 ENGINES.
The AH-64A helicopter can be equipped with either two
T700-GE-701 engines or two T700-GE-701C
engines. The engines are mounted horizontally and
housed in engine nacelles one on each side of the fuselage
aft of the main transmission above the wing. The
engines (fig 2-16) are a front-drive turboshaft engine of
modular construction. The engines are divided into four
modules: cold section, hot section, power turbine section,
and accessory section.
2.21.1 Cold Section Module. The cold section module
(fig 2-16) includes the main frame, diffuser and mid
frame assembly, the inlet particle separator, the compressor,
the output shaft assembly, and associated components.
The compressor has five axial stages and one
centrifugal stage. There are variable inlet guide vanes
and variable stage-1 and stage-2 stator vanes. Components
mounted on the cold section module are: the digital
electronic control unit (DECU) , the electrical
control unit (ECU) , anti-icing and start bleed valve,
history recorder/history counter, ignition system, and
electrical cables as well as the accessory section module.
2.21.2 Hot Section Module. The hot section module
(fig 2-16) consists of three subassemblies: the gas generator
turbine, the stage one nozzle assembly, and the
annular combustion liner.
2.21.3 Power Turbine Section Module. The power
turbine module (fig 2-16) includes a two stage power
turbine and exhaust frame. Mounted on the power turbine
module is the thermocouple harness, the torque
and overspeed sensor, and the Np sensor.
2.21.4 Accessory Section Module. The accessory
section module (fig 2-16) includes the top mounted accessory
gearbox and the following components: a hydromechanical
unit (HMU), a fuel boost pump, oil filter, oil
cooler, alternator, oil lube and scavenge pump, particle
separator blower, fuel filter assembly, chip detector, oil/
filter bypass sensors, oil/fuel pressure sensor, overspeed
and drain valve (ODV), and an air turbine starter.
2.22 ENGINE COOLING.
Each engine is cooled by air routed through the engine
nacelle. Airflow is provided by eductor pumping action
of the infrared suppressor. Fixed louvers on the top and
bottom of the aft portion of each nacelle and moveable
doors in the bottom center forward portion of each nacelle
accelerate convective engine cooling after shutdown.
The moveable door is shut by engine bleed-air
pressure during engine operation and is spring-loaded
to open during engine shutdown.
2.23 ENGINE AIR INDUCTION.
The engines receive air through a bellmouth shaped
nacelle inlet at the front of the engine. Air flows around
the nose gearbox fairing before entering the engine nacelle
inlet. From the inlet, air continues through canted
vanes in the swirl frame where swirling action separates
sand, dust, and other particles. Separated particles
accumulate by centrifugal force in a scroll case.
The particles are ejected overboard by a blower which
forces them through a secondary nozzle of the infrared
suppression device. Clean air, meanwhile, has passed
through a deswirl vane which straightens the airflow
and channels it into the compressor inlet.
2.24 INFRARED (IR) SUPPRESSION SYSTEM.
The IR suppression system consists of two assemblies:
the primary nozzle and three secondary nozzles. The
primary nozzle is mounted to the engine exhaust frame
and directs exhaust gases into the secondary nozzle.
The three secondary nozzles are attached and sealed to
　
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