Piper PA-28-161, Maintenance Manual

Page: 358 / 1104

PIPER AIRCRAFT, INC.
PA-28-161, WARRIOR III
MAINTENANCE MANUAL
PAGE 8
Nov 30/06
2H8
27-10-00
4. Aileron Control Cables
A. Removal (Refer to Figure 4.)
(1) For the removal of either the control cables in the fuselage or the wings, first remove the rear
seat bottom.
(2) To remove either the right or left primary control cables (14 or 15) that are located in the
fuselage, the following procedure may be used:
(a) Remove the two front seats from the airplane.
(b) Remove the tunnel cover located aft of the tee bar assembly by removing the rudder trim
control knob and trim cover attaching screws. Roll back the carpet from the tunnel and
remove the tunnel plate that is located just aft of the tee bar assembly by removing the
plate attaching screws.
NOTE: To facilitate reinstallation of control cables, mark the cable ends and attach a line
where applicable before drawing them through the fuselage or wing.
(c) Separate the primary control cable (14 or 15) at the turnbuckle (12 or 16) located under
the floor panel aft of the main spar.
(d) Remove the cable pulleys (8) attached to the lower section of the control column tee bar
assembly by removing the pulley attaching bolt (21).
(e) Move the cable guard (28) under the pulley cluster (9) located just aft of the lower portion
of the tee bar by removing the cotter pin from the exposed end of the guard and sliding it
to the left or right as required.
(f) Remove the cotter pins used as cable guards at the pulley (10) in the forward area of the
floor opening aft of the main spar.
(g) Disconnect the cable (14 or 15) from the control chain (4) at the control column tee bar
assembly by removing the cotter pin, nut, bolt and bushing (23) that connect the two
together. Secure the chains in some manner to prevent them from unwrapping from
around the sprockets.
(h) Draw the cable back through the floor tunnel.
(3) The primary control cable (13 or 17) in either wing may be removed by the following procedure:
(a) Remove the access plate to the aileron bellcrank (6) located on the underside of the wing
forward of the inboard end of the aileron.
(b) If not previously disconnected, separate the cable at the turnbuckle (12 or 16) located in
the area aft of the main spar.
(c) Disconnect the cable from the forward end of the aileron bellcrank by removing the cotter
pin, nut, washer and bolt.
(d) Draw the cable from the wing.
(4) Either balance cable (18 or 19) may be removed by the following procedure:
(a) Separate the balance cable at the turnbuckle (24) in the right side of the opening aft of the
main spar.
(b) If the left balance cable is to be removed, remove the cotter pin used as a cable guard at
the pulley (11) in the center of the opening.
(c) Remove the access plate to the aileron bellcrank (6) located on the underside of the wing
forward of the inboard end of the aileron.
(d) Disconnect the cable from the aft end of the aileron bellcrank by removing the cotter pin,
nuts washer and bolt.
(e) Draw the cable from the wing.