CESSNA SECTION 2
MODEL 162 AIRPLANE AND SYSTEM DESCRIPTION
GARMIN G300
U.S.
PROPELLER
The airplane is equipped with a two bladed, fixed pitch, one-piece
forged aluminum alloy propeller which is anodized to retard corrosion.
The propeller is 67 inches in diameter.
FUEL SYSTEM
The airplane fuel system, Refer to Figure 2-6, consists of two vented
integral fuel tanks (one tank in each wing), fuel shutoff valve, and a fuel
strainer. The engine-mounted portion of the system consists of the
gravity-fed updraft float carburetor.
UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE
DETERMINED IN ACCORDANCE WITH ASTM
INTERNATIONAL COMPLIANCE STANDARDS.
FAILURE TO OPERATE THE AIRPLANE IN
COMPLIANCE WITH FUEL LIMITATIONS SPECIFIED IN
SECTION 3 MAY FURTHER REDUCE THE AMOUNT OF
FUEL AVAILABLE IN FLIGHT.
FUEL QUANTITY DATA IN U.S. GALLONS
FUEL DISTRIBUTION
Fuel flows by gravity from the two wing tanks to a fuel shutoff valve, the
fuel strainer, and to the carburetor. The carburetor meters fuel flow in
proportion to induction air flow and distributes to the cylinder intake
manifold.
(Continued Next Page)
FUEL
TANKS
FUEL LEVEL
(QUANTITY
EACH TANK)
TOTAL
FUEL
TOTAL
UNUSABLE
TOTAL USABLE
ALL FLIGHT
CONDITIONS
Two Full (12.73) 25.46 1.46 24.0
Figure 2-1
162PHUS-01
2-15
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