Fuel System - Piper Cherokee Arrow II PA-28R-200 1973 Pilots Operating Manual

FUEL SYSTEM

in each wing containing twenty-five ( 2 5 ) 1J.S. gallons, giving a total of 48 usable gallons. 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 easy 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 take-off, switching tanks and during landing.
The fuel tank selector, which allows the pilot t o control the flow of fuel t o the engine, is
located on the left side wall below the instrument panel. It has three positions:
TANK and RIGHT TANK, The arrow on the handle of the selector points t o the tank which is
supplying fuel t o 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 comer. The
fuel strainer also incorporates a quick drain which is located in the left front corner o f the
The fuel tanks are vented individually by
the wing at the rear outboard corner of'each fuel rank. The vent should be checked periodically
t o 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 t o the
left of the switch panel.
AIRPLANE AND SYSTEMS
ISSUED: JULY 13,197 3
vent tube which protrudes below the bottom of
Fuel Selector
ARROW
OFF, LEFT