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PIPER CHEROKEE WARRIOR SERVICE MANUAL
4-15a. INSTALLATION OF STALL STRIPS: (Refer to Figure 4-3.) PA-28-161,Warrior II airplanes, s/n's
28-8016363 through 28-28-8616057, 2816001 through 2816093, 2816095, and 2816096 may require that stall
strips be added to the leading edge of both wings. Refer to the latest revision of Piper Service Bulletin No. 916
and kit No.765 399 for further information.
a. Locate the stall strip (Piper p/n 35802-3) at wing station (WS) 106.19, which is located at the lead-
ing edge skin splice outboard of the fuel tank.
b. Hold the stall strip in place with duct tape.
c. Spot the stall strip's two mounting holes on wing.
d. Remove stall strip. Drill two 0.144 inch (#27) diameter holes in wing skin at marked positions.
e. Attach stall strip with two NAS 1738B4-3 (Piper p/n 522 883) blind rivets.
f. Make appropriate entry in aircraft log or permanent maintenance records.
4-16.
EMPENNAGE GROUP
4-17.
STABILATOR
4-18.
REMOVAL OF STABILATOR. (Refer to Figure 4-5.)
Before entering the aft portion of the fuselage, attach a stand
to the tail skid for support; and with the use of a heavy pad,
protect the inside of the fuselage. Be certain to distribute
weight on top of the bulkheads so as not to damage the fuse -
lage skin.
Should it be necessary to move the rudder to its extreme left or
right for clearance, do so with the use of the rudder pedals or
tow bar.
a. Remove the screws from around the upper and lower tail cone fairing assembly and remove the
fairings separately.
b. Block the trim cable at the barrel of the trim screw assembly to prevent the cable from unwrap-
ping.
c. Remove the access panel to the aft section of the fuselage located at the back wall of the baggage
compartment.
d. Install cable blocks, as illustrated in Figure 4-4, on the stabilator trim control cable at the first set
of pulleys forward of the cable turnbuckles to prevent the forward cable from unwrapping.
e. Disconnect the trim cables at the turnbuckles within the aft section of the fuselage.
f. Relieve tension from the stabilator control cables by loosening one of the cable turnbuckles in the
aft section of the fuselage.
g. Disconnect the stabilator control cables from the stabilator balance arm by removing cotter pins,
nuts, washers, bushings and clevis bolts.
h. Disconnect the trim assembly from the aft bulkhead of the fuselage by removing the attaching
nuts, washers and bolts of the horizontal and diagonal support brackets.
i.
Move the trim assembly up through the tail cone fairing cutout in the stabilator and remove, with
cable, from the airplane.
j.
Remove the stabilator by disconnecting and removing attaching nuts, washers and bolts at the
hinge points.
Revised: February 28, 1995
CAUTION
CAUTION
1E17
Island Enterprises
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