GENERAL.
The fuel system components covered in this section consist of the fuel tanks, selector valves, filter screens,
fuel pumps and quantity transmitter units. Instructions are given for remedying difficulties which may arise in
the normal operation of the fuel system. The instructions are organized so the mechanic can refer to: Removal,
Repair, Installation and Adjustment of each part of the system.
Maintenance for fuel injection may be found in Chapter 73.
DESCRIPTION.
PA-28RT-201 (Refer to Figure 28-1.)
The fuel system was designed with simplicity in mind. It incorporates two fuel tanks, one in each wing
containing 38.5 U.S. gallons, giving a total capacity of 77 gallons, of which 72 gallons are useable. The tanks
are attached to the leading edge of the wing with screws and are an integral part of the wing structure. This
allows for removal for service. An auxiliary electric fuel pump is provided in case of a failure of the engine
driven pump. A rocker type switch for controlling the electric pump is located on the switch panel above the
throttle quadrant. The electric pump should be on for takeoff, switching tanks and during landing.
The fuel tank selector, which allows the pilot to control the flow of fuel to the engine, is located on the left
side wall below the instrument panel. If has three positions: OFF, LEFT TANK and RIGHT TANK. The arrow
on the handle of the selector points to the tank which is supplying fuel to the engine. The valve also
incorporates a safety latch which prevents inadvertently selecting the “OFF” position.
Each tank has an individual quick drain located at the bottom inboard rear corner. The fuel strainer also
incorporates a quick drain which is located in the left front corner of the firewall. The quick drain protrudes
from the cowling to allow easy draining of the fuel strainer. All three drains should be drained before every
flight and checked for contamination.
The fuel tanks are vented individually by a vent tube which protrudes below the bottom of the wing at the
rear outboard corner of each fuel tank. The vent should be checked periodically to ascertain that the vent is not
obstructed and allows free passage of air.
Fuel quantity and pressure are indicated on gauges located in the instrument cluster to the left of the switch
panel.
PA-28RT-201T (Refer to Figure 28-2.)
The fuel system was designed with simplicity in mind. It incorporates two fuel tanks, one in each wing
containing 38.5 U.S. gallons, giving a total capacity of 77 gallons, of which 72 gallons are useable. The tanks
are attached to the leading edge of the wing with screws and are an integral part of the wing structure. This
allows for removal for service. The tanks are vented individually by a vent tube which protrudes below the
bottom of the wing at the rear inboard corner of each tank. The vents should be checked periodically to
ascertain that the vent is not obstructed and will allow free passage of air.
Each fuel tank has an individual quick drain located at the bottom inboard rear corner. The fuel strainer
also incorporates a quick drain, which is located on the left lower portion of the firewall. The quick drain
protrudes through the cowling to allow easy draining of the fuel strainer.
28-00-01
Page 28-01
December 1, 1978
2A20
PIPER AIRCRAFT
PA-28RT-201 / 201T
MAINTENANCE MANUAL
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