THE NEW PIPER AIRCRAFT, INC.
PA-32-301FT / 301XTC
MAINTENANCE MANUAL
PAGE 1
Jun 1/03
3C7
28-00-00
GENERAL
1. Description
The fuel system consists of two interconnected tanks in each wing, having a combined capacity of 53.5
U.S. gallons per wing, for a total capacity of 107.0 U.S. gallons. The inboard tank is an integral part of the
wing surface. Fuel flow is indicated on the gauge located in the instrument panel. A fuel quantity dual
gauge is also located in the instrument panel, and indicates the amount of fuel remaining in each wing
system as transmitted by the electric fuel quantity sending units located in the wing tanks. An exterior
sight gauge is installed in the inboard tank of each wing so fuel quantities can be checked on the ground
during the preflight of the airplane.
Fuel is drawn through a finger screen located in the inboard fuel tank and routed to a three position fuel
selector valve and filter unit which is located aft of the main spar. The valve has OFF, LEFT and RIGHT
positions which are remotely selected by means of a torque tube operated by a handle located in the
pedestal. The handle has a spring loaded detent to prevent accidental selection to the OFF
position. From the selector valve the fuel goes to the electric fuel pump which is also mounted aft of the
main spar and then goes forward to the engine driven fuel pump which forces the fuel through the
injector unit into the engine.
Refer to Figure1 for layout and relationship of the fuel system and components.
2. Troubleshooting
Electrical and mechanical troubles of the system are found in Chart 1. When troubleshooting, check from
the power supply to the items affected. If no problem is found by this method, the trouble probably exists
inside individual pieces of equipment, which may then be removed from the airplane and replaced with
an identical unit or units, tested and known to be good.
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