Torquemeter
The torquemeter is a hydro-mechanical torque measuring device located
inside the rst stage of reduction gear housing. The torquemeter provides
an accurate indication of engine power output in foot-pounds of torque. The
difference between the torquemeter pressure and the reduction gearbox
internal pressure accurately indicates torque production. The two pressures
are routed to a pressure transducer which is electrically connected to the
G1000 which provides an accurate indication of engine torque pressure.
Starter/Generator
The starter/generator is installed on the top of the accessory gearbox at
the rear of the engine. The starter/generator is a 28 volt, 300 amp. direct
drive unit that acts as a motor for engine starting and as a generator for the
airplane electrical system. The starter/generator is cooled by an internal fan
in addition to ram air ducted from the right side of the engine cowling.
Interturbine Temperature Sensing System
The inter-turbine temperature sensing system is designed to provide the
pilot with an accurate indication of the engine operating temperatures taken
between the compressor turbine disk and power turbine stator. The system
consists of two bus bars, twin leads and eight individual chromel-alumel
thermocouple probes connected in parallel. Each probe protrudes through
a threaded boss on the power turbine stator housing into an area adjacent
to the leading edge of the power turbine vanes. The probe is secured to
the boss by means of a oating, threaded tting which is an integral part of
the thermocouple probe assembly. Shielded leads connect each bus bar
assembly to a terminal block which provides a means of connecting the
external leads to the ITT indicator on the instrument panel.
Propeller Governor
The propeller governor is located in the 12 o’clock position on the front case
of the reduction gearbox. Under normal conditions, the governor acts as
a constant speed unit and maintains the propeller speed selected at the
propeller RPM control by varying the propeller blade angle to match the
propeller load to the engine torque. The propeller governor also contains
an integral power turbine governor section. Its function is to protect the
engine against a possible power turbine overspeed condition in the event of
a propeller governor failure. If such an overspeed condition should occur, a
governing orice in the propeller governor is opened by yweights to bleed off
compressor discharge pressure through the governor and computing section
of the fuel control unit. When this occurs, compressor discharge pressure
acting on the fuel control unit bellows decreases and brings the metering
valve to a closed direction and reduces fuel ow to the ow divider.
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