Propeller; Fuel System - Cessna TR182 1979 Pilot Operating Handbook

CESSNA
MODELTR182
SECTION
7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
An inadvertent overboost of 2 to 3 inches of manifold pressure is not
considered detrimental to the engine as long as it is momentary. Imme-
diate corrective action is required when an overboost occurs.
ATTITUDE OPERATION
Although a turbocharged airplane will climb faster and higher than a
normally aspirated airplane, fuel vaporization should not be a problem
since the engine is carbureted. However, if the fuel pressure drops below
0.5
PSI; this may be an indication ofvapor. Should this occur, the auxiliary
fuel pump switch should be placed in the ON position until smooth engine
operation can be resumed.
PROPELLER
The airplane has an all-metal, two-bladed, constant-speed, governor-
regulated propeller. A setting introduced into the governor with the
propeller control establishes the propeller speed, and thus the engine
speed to be maintained. The governor then controls flow of engine oil,
boosted to high pressure by the governing pump, to or from a piston in the
propeller hub. Oil pressure acting on the piston twists the blades toward
high pitch (low RPM).When oil pressure to the piston in the propeller hub
is relieved, centrifugal force, assisted by an internal spring, twists the
blades toward low pitch (high RPM).
A control knob on the center area of the switch and control panel is
used to set the propeller and control engine RPM as desired for various
flight conditions. The knob is labeled PROPELLER, PUSH INCR RPM.
When the control knob is pushed in, blade pitch will decrease, giving a
higher RPM. Whenthe control knob is pulled out, the blade pitch increases.
thereby decreasing RPM. The propeller control knob is equipped with a
vernier feature which allows slow or fine RPM adjustments by rotating the
knob clockwise to increase RPM, and counterclockwise to decrease it. To
make rapid or large adjustments, depress the button on the end of the
control knob and reposition the control as desired.
FUEL SYSTEM
The airplane fuel system (see figure
7-6)
consists of two vented
integral fuel tanks (one in each wing), a four-position selector valve, fuel
strainer, manual primer, engine-driven fuel pump, auxiliary fuel pump,
and carburetor. Refer to figure
7-7
for fuel quantity data for the system.
Fuel flows by gravity from the two integral wing tanks to a four-
1
October 1978 7-27