Piper Cherokee Six - Page 464

PIPER CHEROKEE SIX SERVICE MANUAL
SECTION VIII
FUEL SYSTEM
NOTE
Through a model change all future PA-32-300 aircraft, Serial
Numbers 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.
Revised: 9/18/78
FUEL
SYSTEM
2120