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PIPER NAVAJO SERVICE MANUAL
5-3. TROUBLESHOOTING. Troubles peculiar to the control system are listed in Table V-II at the back of
this section, along with their probable causes and suggested remedies.
5-4. STANDARD
SERVICE PROCEDURES. The following tips may be helpful in the removal.
installation and servicing of the various assemblies:
a.
It is recommended, though not always necessary, to level and place the airplane on jacks during
rigging and adjustment of controls.
b.
Remove turnbuckle barrels from cable ends before withdrawing cables through structures.
c.
Tie a cord to the cable end before drawing cable through structures to facilitate reinstallation of
cables.
d.
Turnbuckle stations are given at neutral position.
e.
When referring to marking cable end, etc., before disconnecting, a felt marker may be used.
f.
When turnbuckles have been set to correct cable tension, no more than three threads should be
exposed from either end of the turnbuckle barrel. Do not lubricate turnbuckles.
g.
Cable tension should be taken with the appropriate surface control in its neutral position and
tension specified corrected to ambient temperature in the area where tension is being checked. (Refer to Table
V-I.)
NOTE
Whenever the elevator control system of the airplane is serviced. a
friction check of the system must be accomplished in accordance
with instructions given in Section IV. Elevator Control System
Friction Measurement.
h.
Ascertain that all cable guard pins are installed in their proper location and are not interfering with
control cable travel.
i.
When installing rod end jam nuts refer to Figure 5-la for proper installation method.
j.
Clip-type locking devices are used at all turnbuckle locations. After completing all adjustments.
install a new clip-type locking device at each terminal. These locking clips must not be reused. (When special
locking clips are not available. the use of safety wire per the latest revision of AC43-13-1A is acceptable.)
k.
If push rods or rod end bearings have an inspection hole, the threaded portion should extend past
the inspection hole. If there is no inspection hole. there should be a minimum of
3/8
thread engagement.
1.
Verify that all control systems function properly and control surfaces travel in their proper direction
In coordination with the control wheel and rudder pedal movements.
5-4a. CONTROL COLUMN ASSEMBLY.
5-5. REMOVAL OF CONTROL COLUMN ASSEMBLY. (Refer to Figure 5-1.)
a.
To remove either control wheel (43) with tube (27 or 44), proceed as follows:
1.
Mark the control tube (27 or 44), ring (26) and collar (21) in relation to location around the
roller fitting (23). Note the installation position of link assemblies (30) for reinstallation. If link assemblies
are not installed in the same position, control friction may increase.
2.
Cut safety wire (24) from the cap bolts (25) which secure the control tube (27 or 44) and
ring (26) to the roller fitting (23). Remove bolts from the fitting.
3.
Slide the control tube from the roller fitting and ring, and draw the tube from the
instrument panel: Do not allow the square tube (31) assembly to fall.
Revised: 3/2/84
SURFACE CONTROLS
112
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