CESSNA SECTION 7
MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION
GARMIN G1000
U.S.
ENGINE (Continued)
The compressor and power turbines are located in the approximate
center of the engine with their shafts extending in opposite directions.
The exhaust gas from the power turbine is directed through an exhaust
plenum to the atmosphere via a single exhaust port on the right side of
the engine.
The engine is flat rated at 867 shaft horsepower (2397 foot-pounds
torque at 1900 RPM. The speed of the gas generator (compressor)
turbine (N
g
) is 37,468 RPM at 100% N
g
. Maximum permissible speed
of the gas generator is 38,900 RPM which equals 103.7% N
g
. The
power turbine speed is 33,000 RPM at a propeller shaft speed of 1900
RPM.
All engine-driven accessories, with the exception of the propeller
tachometer-generator and the propeller governors, are mounted on the
accessory gearbox located at the rear of the engine. These are driven
by the compressor turbine with a coupling shaft which extends the drive
through a conical tube in the oil tank center section.
The engine oil supply is contained in an integral tank which forms part
of the compressor inlet case. The tank has a drain and fill capacity of
9.5 U.S. quarts and is provided with a dipstick and drain plug.
The power turbine drives the propeller through a two-stage planetary
reduction gearbox located on the front of the engine. The gearbox
embodies an integral torquemeter device which is instrumented to
proved an accurate indication of the engine power output.
208BPHCUS-00 7-47
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