SA 160
AIRCRAFTA I R C R A F T
Symphony
AIRCRAFT
7.29 FUEL SYSTEM
The fuel system of the SA 160 (See Fig. 7-9) consists of two main fuel
tanks which are installed in the wings, a feeder tank behind the seats,
a fuel shut-off valve on the center pedestal, an auxiliary fuel pump, a
gascolator, an engine driven fuel pump and a single-barrel float type
carburetor in the engine compartment. Fuel lines are made of flexible
hoses and aluminum depending upon location. The fuel system
quantities are as follow:
Fuel Quantity Data:
Total Fuel: 123 l (32.5 U.S. Gallons)
Usable Fuel: 114 l (30.2 U.S. Gallons)
Unusable Fuel: 9 l (2.3 U.S. Gallons)
(a) Fuel Distribution
In the SA 160, fuel flows from the tank to the engine by gravity.
However, an electrically operated auxiliary fuel pump is provided to
supportfuelsupplyincaseofthefailureoftheenginedrivenpump.
Fuel flows from the two wing tanks through flexible hoses and
aluminum-fuel-linestoairbleedertubesandtothefeedertank.
The feeder tank guarantees a continuous fuel supply to the engine
during a possible short-term interruption of the fuel flow from the
wing fuel tanks. This may occur during descend with high nose
downattitude when the wing tank havelittle fuel remaining since the
fuel is draw-off from the rear part of the wing fuel tanks. However
the size of the feeder tank guarantees a secure fuel supply to the
engineduringlongerdescents.
SECTION 7
DESCR. & OPERATION
7-31
Feb 25, 2005
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