SECTION 7 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III
GFC 700 AFCS
U.S.
FUEL SYSTEM
The airplane fuel system (Refer to Figure 7-7) 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 fuel/air 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 airplane’s integral tanks. One drain is
added to properly drain the fuel return system.
UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE
DETERMINED IN ACCORDANCE WITH FEDERAL
AVIATION REGULATIONS. FAILURE TO OPERATE THE
AIRPLANE IN COMPLIANCE WITH FUEL LIMITATIONS
SPECIFIED IN SECTION 2 MAY FURTHER REDUCE THE
AMOUNT OF FUEL AVAILABLE IN FLIGHT.
(Continued Next Page)
T182TPHBUS-01
7-48
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