Piper cherokee WARRIOR Pilots Operating Manual page 15

CHEROKEE WARRIOR
Manually controlled flaps are provided on the PA-28-151. The flapsare balanced forlight
operating forces and spring loaded to return to the retracted (up) position. A control handle,
which is located between the two front seats on the control console, extends the flaps by the
use of a control cable. To extend the flaps, the handle is pulled up to the desired flap setting of
lO, 25 or 40 degrees. To retract, depress the button on the end of the handle and lower the
control. When extending or retracting flaps, there is a pitch change in the airplane. This pitch
change can be conected either by stabilator trim or increased control wheel force. When the
flaps are in the retracted (up) position the right flap, provided with an over-center lock
mechanism, acts as a step.
NOTE
The right flap will support a load only in the fully retracted (up)
position. When the flap is to be used as a step, make sure the
flaps are in the retracted (up) position.
FUEL SYSTEM
Fuel is stored in two twenty-five gallon (24 gallons usable) fuel tanks, giving the airplane a
total capacity of fifty U.S. gallons (48 gallons usable). The tanks are secured to the leading edge
of each wing with screws and nut plates. This allows easy removal for service or inspection.
On serial numbers 7415001 through 7515449 each fuel tank has two outlets, one forward
and one aft, to ensure an even fuel flow. Fuel is pumped from the tanks through the forward
and aft tank outlets to fuel manifolds in the inboard section of either wing. Each manifold is a
small collector with an inlet hose from each of the tank outlets, and an outlet hose to the fuel
selector valve. On serial numbers 7615001 and up there is only one outlet on each tank and no
fuel manifolds are used.
The fuel tank selector control is located on the left side panel forward of the pilot's seat.
The button on the selector cover must be depressed and held while the handle is moved to the
OFF position. The button releases automatically when the handle is moved back to the ON
position.
An auxiliary electric fuel pump is provided in case of the failure of the engine driven
pump. The electric pump should be ON for all takeoffs and landings and when switching tanks.
The fuel pump switch is located in the switch panel above the throttle quadrant.
'l'lrc
fuel druins shotrltl bc o;rcnctl daily prior to first flight to chcck fr>r watcr or sedimcnt.
h,aclr tank has an individual drain at the bottom, inboard rear corner, and each fuel manifold
(on early models only) is equipped with a drain. The outlets are located on the underside of the
wings.
A gascolator, located on the lower left front of the fire wall, has a drain which is accessible
from outside the nose section. The gascolator should also be drained before the first flight of
the day. (See the Handling and Servicing Section for the complete fuel draining procedure.)
Fuel quantity and fuel pressure gauges are mounted in a gauge cluster located on the left
side of the instrument panel to the right of the control wheel.
An optional engine priming system is available to facilitate starting. The primer pump is
located to the immediate left of the throttle quadrant.
AIRPLANE AND SYSTEII{S
REVISED: JULY 14,1975
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