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SOLOY TURBINE PAC
SECTION 7
POHS CESSNA U/TU 206G
AIRPLANE & SYSTEMS
DESCRIPTION
7-14
F.A.A. Approved
October 4, 2005
PROPELLER CONTROL
The vernier propeller control in the cockpit is connected to the
propeller governor mounted on the Soloy propeller reduction
gearbox. The propeller control controls propeller governor
settings from the maximum RPM position (1810 RPM) to a
minimum flight position (1450 RPM) to full feather.
FUEL CUTOFF CONTROL
The fuel cutoff control in the cockpit is connected to the fuel
control unit. The cockpit control has two positions only, RUN (IN)
and CUTOFF (OUT).
ENGINE INSTRUMENTS
Engine instrumentation consists of the engine torque indicator,
propeller RPM indicator (N
P
), turbine outlet temperature (TOT)
indicator, N
1
percent RPM indicator, engine oil pressure, engine oil
temperature indicator, transmission oil pressure indicator and fuel
flow/temperature indicator. The indicators are placarded as to their
operational parameters.
ENGINE TORQUE INDICATOR
The power train portion of the engine gearbox consists of two
stages of helical gearing. These gears are such that a forward
axial thrust is produced on the torquemeter shaft during normal
operation. This axial thrust is transmitted to the sliding cylinder
counterbalanced by oil from the lubrication system. The cylinder
oil pressure is quoted to an external connection for use with a
torque indicator that is calibrated in PSI of torque.
PROPELLER RPM INDICATOR (N
P
)
The propeller RPM indicator (N
P
) is a tachometer which indicates
the propeller speed in revolutions per minute. The power turbine
speed (N
2
) can also be determined with the indicator where 18.1
N
P
RPM is equal to 1% N
2
speed.
TOT INDICATOR
The turbine outlet temperature gauge displays the air temperature
in the gas producer turbine outlet.
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