Piper SARATOGA PA-32-301 Maintenance Manual page 221

PIPER AIRCRAFT
PA-32-301/301T
MAINTENANCE MANUAL
GENERAL.
The airplane is controlled in flight by the use of three primary control surfaces. consisting of ailerons.
stabilator and rudder. Operation of these controls is through the movement of the control column-tee bar
assembly and rudder pedals. On the forward end of each control column is a sprocket assembly. A chain is
wrapped around the sprockets to connect the right and left controls and then back to idler sprockets on the
column's tee bar. which in turn connect to the aileron primary control cables. The cables operate the aileron
bellcrank and push-pull rods. The stabilator is controlled by a cable connected to the bottom of the tee bar
assembly and to the top and bottom sides of the stabilator balance arm. Cables also connect the rudder pedals
with the rudder horn. Provisions for directional and longitudinal trim control is provided by an adjustable
trim mechanism for the stabilator and rudder. The stabilator trim is controlled by a wheel and drum mounted
on the floor tunnel between the front seats. Cables routed aft from the drum to a screw assembly mounted
above the stabilator attachment point. This screw assembly in turn moves the push rod which controls the
stabilator trim tab. The rudder trim is controlled by a knob and screw assembly attached to the rudder pedal
assembly. An interconnect system is provided which consists of a spring loaded cable located in the fuselage
tunnel which connects the aileron cable to the rudder cable. The flaps are mechanically operated on early
models and electrically operated on 1985 models.
STANDARD PROCEDURES.
The following tips may be helpful where applicable in the individual control system procedures.
1. Turnbuckles must be assembled and adjusted in a manner that each terminal end is screwed an
approximately equal distance into the barrel. During adjustment. the terminals must not be turned in a
manner which would put a permanent twist in the cable.
2. After adjustment is completed. each turnbuckle must be checked. Not more than three terminal
threads shall be visible outside the barrel. Locking clips must be installed and checked for proper installation
by trying to remove the clips using fingers only. Locking clips which have been installed and remo ed must be
scrapped and new clips used.
3. Torque all nuts in the flight control surface rigging system in accordance with AC 43.13-1A or to
torques specified within this manual text.
4. After completion of adjustment. each jam nut must be tightened securely and inspected.
5. On push rods or rod ends provided with an inspection hole. the screw must be screwed in sufficiently
far to pass the hole. This can be determined visually or feel. by inserting a piece of wire into the inspection hole.
If no inspection hole is provided. a minimum of .375 of an inch thread engagement must be maintained.
6. All cable rigging tensions given must be corrected to ambient temperature in the area where the
tension is being checked by using Chart 2702.
7. See Figure 27-1 for the proper method of adjusting rod ends to prevent possible damage and binding
of bearing surface in rod end. and all pulley guard pins installed.
TROUBLESHOOTING.
Chart 2701 lists troubles peculiar to the flight controls along with their probable causes and suggested
remedies. When troubleshooting the flight controls. additional reference may be obtained from Chapters 55
and 57 on control surface balancing if required. After the trouble has been corrected. check the entire system
for security and operation.
27-02-00
Page 27-01
1J5
Revised: August 9, 1984