Section II. EMERGENCY EQUIPMENT
The equipment covered in this section includes
all emergency equipment, except that which forms part
of a complete system. For example, landing gear
system, etc. Chapter 9 describes the operation of
emergency exits and location of all emergency
2-13. HAND-OPERATED FIRE EXTINGUISHER.
Avoid repeated or prolonged exposure to
trifluoromethane (CF3Br) or decomposition
products. The liquid shall not be allowed
to come into contact with the skin, as it
may cause frostbite or low temperature
burns because of its very low boiling point.
One hand-operated fire extinguisher is mounted
below the pilot's seat and a second extinguisher is
located in the left cabin sidewall, aft of the cabin door.
They are of the monobromotrifluoromethane (CF3Br)
type. Each extinguisher is charged to a pressure of
150 to 170 psi and emits a forceful stream. Use an
extinguisher with care within the limited area of the
cabin to avoid severe splashing.
described in Section III.
Section III. ENGINES AND RELATED SYSTEMS
Two PT6A-42 turboprop engines, rated at 850
SHP each, power the aircraft. Refer to Figure 2-10.
controlled, reversible, constant-speed, four-blade, full-
feathering propeller. The engines are reverse-flow
free turbines, and each employs a three-stage axial
compressor and a single-stage centrifugal compressor
in combination, driven by the gas generator turbine.
The gas generator turbine and the two power turbines
are in line and have opposite rotations. The power
turbines are connected through planetary reduction
gearing to a flanged propeller shaft. The oil tank, filler
cap and dipstick are an integral part of the engine.
The engine anti-ice system (ice vanes)
should be on (extended) for all ground
operations to minimize ingestion of ground
debris. Turn off engine anti-ice (retract ice
vanes) to maintain engine temperatures
The ram air supply enters the lower portion of
the nacelle and is drawn in through the aft protective
screens. The air is then routed into the compressor.
After the air is compressed, it is forced into the annular
combustion chamber and mixed with fuel that is
sprayed in through 14 nozzles mounted around the
gas generator case. A capacitance discharge ignition
unit and two spark igniter plugs are used to start
combustion. After combustion, the exhaust passes
through the compressor turbine and two stages of
power turbines, then is routed through two exhaust
ports near the front of the engine. A pneumatic fuel
control system schedules fuel flow to maintain power
set by the gas generator POWER lever. The
accessory drive at the aft end of the engine provides
power to drive the fuel pumps, fuel control, oil pump,
generator, and the tachometer generator. The
reduction gearbox forward of the power turbine
provides gearing for the propeller and drives the
2-15. ENGINE COMPARTMENT COOLING.
The forward engine compartment, including the
accessory section, is cooled by air that enters around
the exhaust stack cutouts and through the gap
between the propeller spinner and forward cowling,
and exhausts through louvers in the upper forward and