Piper CHEROKEE WARRIOR PA-28-151 1995 Maintenance Manual page 188

PIPER CHEROKEE WARRIOR SERVICE MANUAL
b. Before attaching the assembly to the mounting channel, ascertain that the clips (11) are installed so
the safety wire (12) will be on top. Also, that the threaded bushing (4) is installed on the assembly shaft (15)
with the welded attachment bushing forward or toward the housing.
c. Attach the housing lug to the arm provided on the rudder pedal torque tube and secure with bolt,
washer and nut (7). Tighten the nut only finger tight and safety with cotter pin.
d. Clamp the rudder pedals in neutral and position the threaded bushing in the mounting channel (8).
Turn the control shaft until the holes in the bushing and channel align and then install the clevis pin and cotter
pin (5). Should two thru holes be located in the aft end of the mounting channel, the pin must be installed
through the hole that will give equal travel and hit rudder stops before bottoming out of the trim assembly.
e. With the rudder pedals neutral and no pressure fore and aft on the clevis pin, install the assembly
cover (1) so that the indicator washer (13) and the neutral mark on the cover align.
f. Install the trim cover, secure with screws, and install the trim control knob.
5-36. RIGGING AND ADJUSTMENT OF RUDDER TRIM CONTROLS. No adjustments are necessary
other than those required during installation of the assembly in the airplane as given in Paragraph 5-35.
5-37. WING FLAP CONTROLS.
5-38. REMOVAL OF WING FLAP CONTROLS. (Refer to Figure 5-21.)
a. Remove the flap torque tube assembly by the following procedure:
1. Remove the access plate located between the underside of the aft section of each wing and the
fuselage by removing attaching screws.
2. Remove the two front seats and the bottom half of the rear seat or floor panel, whichever
applies.
3. Disconnect the left and right flap control tubes (rods) (4) at the flaps by removing the nuts,
washers and bolts (2) or at the torque tube cranks (arms) (11) by removing the bolts (12) and washers from the
inner side of each crank. It will be necessary to remove bolt through a hole in the side skin of the fuselage
located over the torque tube with the flap handle moved to its 40 degree position.
4. Using the flap handle (29), fully extend the flaps and disconnect the flap tension spring (22) at
the spar or the aft end of the control cable (23), as desired.
5. Grasp the flap handle, release the plunger (33) and allow the flap to return to the retracted
position. Use caution as forward pressure will be on the handle with the tension spring disconnected.
6. Disconnect the flap return spring (32) at the spar or return chain (30) as desired.
7. Disconnect the control cable from the chain (20) by removing cotter pin, nut and clevis bolt
(21).
8. Remove the tube support blocks (16 and 31) by removing the block attaching bolts (15).
9. Remove the nuts, washers and bolts (10) securing the right and left cranks (11) and stop fit-
tings (13) on the torque tube.
10. From between each wing and the fuselage, remove the cranks from the torque tube.
11. Disconnect one bearing block (7) from its mounting brackets (6) by removing nuts, washers
and bolts (5).
12. Slide the tube from the bearing block still attached to its brackets, raise the end and lift it from
the floor opening.
b. Remove the flap control cable (23) by the following procedure:
1. Remove the seats floor panel. Remove the seats.
2 . Disconnect the flap tension spring (22) from the cable, if not previously disconnected, by
e x t e n ding the flaps to relieve spring tension.
3 . Retract the flap. Use caution as forward pressure will be on the handle with the spring
d i sc o nn e c ted.
Revised: February 28, 1995
1H20
Island Enterprises
SURFACE CONTROLS