SECTION 7 CESSNA
AIRPLANE & SYSTEMS DESCRIPTION MODEL 182T
FUEL SYSTEM
The airplane fuel system (see 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 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 aircraft integral
tanks. One drain is added to properly drain the 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.
NOTE
Unusable fuel is at a minimum due to the design of the fuel
system. However, with 1/4 tank or less, prolonged
uncoordinated flight such as slips or skids can uncover the
fuel tank outlets, causing fuel starvation and engine
stoppage. Therefore, with low fuel reserves, do not allow the
airplane to remain in uncoordinated flight for periods in
excess of one minute.
7-26 Apr 30/01
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