SECTION 7 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III
GFC 700 AFCS
U.S.
FUEL SYSTEM (Continued)
FUEL RETURN SYSTEM
A fuel return system was incorporated to improve engine operation
during extended idle operation in hot weather environments. The major
components of the system include an orifice fitting located in the top of
the fuel servo, a dual stack fuel selector and a drain valve assembly.
The system is designed to return fuel/vapor back to the main fuel tanks
at approximately 7 GPH. The dual stack fuel selector ensures that fuel/
vapor returns only to the fuel tank that is selected as the feed tank. For
example, if the fuel selector is positioned to use fuel from the left fuel
tank, the fuel return system is returning fuel/vapor to the left fuel tank
only.
FUEL VENTING
Fuel system venting is essential to system operation. Complete
blockage of the fuel venting system will result in decreasing fuel flow
and eventual engine stoppage. The fuel venting system consists of an
interconnecting vent line between the fuel tanks and check valve
equipped overboard vents in each fuel tank. The overboard vents
protrude from the bottom surface of the wings behind the wing struts,
slightly below the upper attach points of the struts. The fuel filler caps
are vacuum vented; the fuel filler cap vents will open and allow air to
enter the fuel tanks in case the overboard vents become blocked.
REDUCED TANK CAPACITY
The airplane may be serviced to a reduced capacity to permit heavier
cabin loadings. This is accomplished by filling each tank to the bottom
edge of the fuel filler indicator tab, thus giving a reduced fuel load of
32.0 gallons usable in each tank or to the line of holes located inside
the filler indicator tab, thus giving a reduced fuel load of 37.0 gallons
usable in each tank.
(Continued Next Page)
T182TPHBUS-01
7-54
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