Piper Cherokee LANCE, Service Manual

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PIPER CHEROKEE SIX / LANCE SERVICE MANUAL
VIII - FUEL SYSTEM 07/15/06
2I20
SECTION VIII
FUEL SYSTEM
NOTE: Through a model change all future PA-32-300 aircraft, S/N’s 32-7940001 and up , will have
incorporated the same fuel system as the PA-32R-300.
8-1. DESCRIPTION. (PA-32-260 and 300 to S/N 7840222).
The fuel system consists of two aluminum tanks contained in the inboard leading edge section of the
wings plus two fiberglass tanks, one located in each wing tip. The main tanks have a maximum capacity
of 25 U. S. gallons each while the tip tanks hold a maximum capacity of 17 U.S. gallons each.
Fuel is taken from each tank through a screen located in the tank outlet fitting and onto a combination
fuel selector valve and strainer located under the floor panel under the middle seats. The fuel selector
valve is controlled remotely by a selector lever located on the sloping face of the control tunnel. The
strainer portion of the valve is operated by a lever located on the right front side of the spar cover under
the forward end of the right middle seat. From the selector valve, fuel is drawn through the electric fuel
pump(s) located in the area under the middle seats, through the engine driven pump and onto the
carburetor or injector.
Four electric fuel quantity gauges are mounted in the instrument cluster located on the right side of the
instrument panel. Each gauge is connected to a sender unit installed in the fuel tanks.
Refer to Figures 8-1 or 8-2 for the layout and relationship of the fuel system and components.
8-2. DESCRIPTION (PA-32R-300). The fuel system consists of two interconnected aluminum tanks in each
wing, having a combined capacity of 49 U.S. gallons, for a total capacity of 98 U.S. gallons. These tanks
form an integral part of the wing surface when installed. Fuel flow is indicated on the gauge located in
the instrument panel. A fuel quantity gauge for each wing system is also located in the instrument panel,
and indicates the amount of fuel remaining 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 Figure 8-3 for layout and relationship of the fuel system and components.
8-3. TROUBLESHOOTING. Troubles peculiar to the instruments and related areas of the fuel system are
listed in Section IX along with their probable causes and suggested remedies. Electrical and mechanical
troubles of the system are found in Table VIII-III at the back of this section. When troubleshooting,
check from the power supply to the items affected. If no trouble is found by this method, the trouble
probably exists inside individual pieces of equipment; they may then be removed from the airplane and
an identical unit or units, tested and known to be good, installed in their place.