4-3. WING GROUP.
— NOTE —
The major subassemblies of the wing may be removed individually or the wing may
be removed as a unit. To remove a wing, a fuselage supporting cradle is required.
4-4. WING TIP.
4-5. REMOVAL OF WING TIP
a. Remove the screws holding the wing tip to the wing, being careful not to damage the wing or fiberglass
wing tip.
b. Pull the wing tip off far enough to disconnect the position light wire assembly. The ground lead may be
disconnected at the point of connection on the wing rib, and the positive lead may be disconnected at the wire
terminal or unscrewed from the light assembly.
c. Inspect the fiberglass wing tip to ensure that it is free of cracks, severe nicks and minor damage. If repair
is required, refer to Paragraph 4-51.
4-6. INSTALLATION OF WING TIP.
a. Place the wing tip in a position that the navigation light leads may be connected. Connect the ground lead
to the wing rib by use of a screw and nut, and the positive lead to the position light by connecting the wire
terminals or screwing the connectors together. Insulate the wire terminals and be certain that the ground lead is
free of dirt and film to insure a good connection.
b. Insert the wing tip into position and install the screws around the tip. Use caution to refrain from
damaging the fiberglass tip or wing. Check the operation of the position light.
4-7. AILERON.
4-8. REMOVAL OF AILERON. (Refer to Figure 4-1.)
a. Disconnect the aileron control rod at the middle of the aileron by removing the nut, washers and bolt from
the rod end bearing. To simplify installation note location of the washers.
b. Remove the attaching screws, with nuts, from the three hinges within the aileron, and remove the aileron
by moving it aft
4-9. INSTALLATION OF AILERON. (Refer to Figure 4-1.)
a. Move the aileron into place and install attaching screws and nuts. Ensure that the aileron is free to move
with no interference.
b. Attach the aileron control rod with bolt, washers and nut, dividing the washers so that the aileron is free to
rotate from stop to stop without the control rod binding or rubbing on the opening in the aft spar. Be certain that
the rod end bearing has no side play when tightening the bolt and that the rod does not contact the side of the
bracket.
c. Actuate the aileron controls to insure freedom of movement.
PIPER AIRCRAFT
PA-28-161 CADET
AIRPLANE MAINTENANCE MANUAL
1E9
STRUCTURES
Issued: FEBRUARY. 28, 1989
