SECTION
7
CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL
208B
(675
SHP)
ENGINE
(Continued)
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.
ENGINE CONTROLS
The engine is operated by four separate controls consisting of a power
lever, emergency power lever, propeller control lever, and a fuel
condition lever. The power and fuel condition levers are engine controls
while the propeller control lever controls propeller speed and
feathering.
POWER LEVER
The power lever is connected through linkage to a cam assembly
mounted in front of the fuel control unit at the rear of the engine. The
power lever controls engine power through the full range from
maximum takeoff power back through idle to full reverse. The lever also
selects propeller pitch when in the BETA range. The power lever has
MAX, IDLE, and BETA and REVERSE range positions. The range from
MAX position through IDLE enables the pilot to select the desired
power output from the engine. The BETA range enables the pilot to
control propeller blade pitch from idle thrust back through a zero or
no-
thrust condition to maximum reverse thrust.
CAUTION
THE PROPELLER REVERSING LINKAGE CAN BE
DAMAGED IF THE POWER LEVER IS MOVED AFT OF
THE
IDLE
POSITION WHEN THE PROPELLER IS
FEATHERED.
(Continued Next Page)
Revision
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