g. Cable tensions should be taken with the appropriate control surface in its neutral position.
h. After completion of each adjustment, check the turnbuckles to be sure not more than three terminal threads
are visible outside the barrel. Install the locking clips, and check for proper installation by trying to remove the
clips using fingers only. Both locking clips may be installed in opposite holes. Locking clips which have been
installed and removed must be scrapped and not reused.
i. When push rods or rod ends are provided with an inspection hole, the screw must be screwed in far enough
to pass the inspection hole. This can be determined visually or by feel, inserting a piece of wire into the
inspection hole. If no hole is provided, there must be a minimum of .375 of an inch thread engagement.
j. After completion of adjustments, each jam nut must be tightened securely.
— NOTE —
Cable rigging tensions specified must be corrected to ambient temperature in the
area where the tension is being checked, using Table V-II.
k. Torque all nuts in the flight control surface rigging system (including nose wheel steering) in accordance
with Table II-II, Recommended Torques, unless specific torques are given in text.
5-4. CONTROL COLUMN ASSEMBLY.
5-5. REMOVAL OF CONTROL COLUMN ASSEMBLY. (Refer to Figure 5-1.)
a. To remove either control wheel (1) with its tube (2), the following procedure may be used:
assembly (5) by removing the nut, washer and bolt (3). Pull the tube from the flexible joint.
2. If removing the left control tube, slide the stop (6) from the tube.
3. Should wires from the various Autopilot systems be installed in the control tube, disconnect them at the
quick disconnect terminals behind the instrument panel. Draw the wires back into the tube and out through the
forward end of the tube.
4. Remove the control wheel assembly from the instrument panel.
b. The tee bar (5) with assembled parts may be removed from the airplane by the following procedure:
1. Remove the access panel to the aft section of the fuselage.
2. Relieve the cable tension from the stabilator control cables (11) at one of the stabilator cable turnbuckles
in the aft section of the fuselage.
connects the chains at the top of the tee bar (5).
4. Disconnect the control chains from the control cables where the chains and cables join, by removing the
cotter pins, nuts, bolts and bushings.
5. Remove the tunnel cover 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.
each side of the floor tunnel, and lifting it up and out through the right side of the cabin.
PIPER AIRCRAFT
PA-28-161 CADET
AIRPLANE MAINTENANCE MANUAL
Issued: FEBRUARY 28, 1989
S U R FACE CONTROL
1F23
