SECTION 7 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III
GFC 700 AFCS
U.S.
FUEL SYSTEM
The airplane fuel system, refer to Figure 7-6, consists of two vented
integral fuel tanks (one tank in each wing), three-position selector
valve, fuel reservoir tank, electrically-driven auxiliary fuel pump, fuel
shutoff valve, 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.
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.
FUEL QUANTITY DATA IN U.S. GALLONS
(Continued Next Page)
FUEL
TANKS
FUEL LEVEL
(QUANTITY
EACH TANK)
TOTAL
FUEL
TOTAL
UNUSABLE
TOTAL USABLE
ALL FLIGHT
CONDITIONS
Two Full (28.0) 56.0 3.0 53.0
Two Reduced (19.0) 38.0 3.0 35.0
Figure 7-5
172SPHBUS-02
7-38
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