SECTION 7 CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL 182T NAV
Ill
PROPELLER (Continued)
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. When the 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 (refer to Figure 7-6) consists of two vented
integral fuel tanks (one tank in each wing), two fuel manifolds (one
in each aft doorpost), a dual stack, four-position selector valve, an
electrically-driven auxiliary fuel pump, and a fuel strainer. The
engine-mounted portion of the system consists of the engine-driven
fuel pump, a
fuellair control unit, fuel flow transducer, a fuel
distribution valve (flow divider) and fuel injection nozzles.
The fuel system also incorporates a fuel return system that returns
fuel from the top of the fuel servo back to each integral wing tank.
The system includes a flexible fuel hose assembly between the
servo and the firewall. Aluminum fuel lines return the fuel to the top
portion of the selector valve and then to the aircraft integral tanks.
One drain is added to properly drain the return system.
(Continued Next Page)
7-38 U.S.
To Next Page
Loading...
Need help?
General
