Flight Controls; General Information; Description And Operation; Standard Practices Andprocedures - Piper PA-32R-301 SARATOGA SP Maintenance Manual

FLIGHT CONTROLS

A. General Information

(1) Description and Operation.

The airplane is controlled in flight by the use of three primary control surfaces: ailerons, stabilator
and rudder. The controls are operated by 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 sprock-
ets on the column's tee bar, which connect to the aileron primary control cables. The cables oper-
ate the aileron bellcrank and push-pull rods. The stabilator is controlled by a cable connected to
the bottom of the tee bar assembly and operates an aft fuselage bellcrank which controls a push
rod connected to the balance arm of the stabilator. 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. The flaps are mechanically operated
on early models and electrically operated on 1985 and later models.
(2) Standard Practices and Procedures
The following tips may be helpful in the removal, installation, and rigging of individual control
system assemblies.
(a) Turnbuckles must be assembled and adjusted in a manner that each terminal end is screwed
into the barrel an approximately equal distance. During adjustment, the terminals must not be
turned in a manner which would put a permanent twist in the cable.
(b) 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 removed must be scrapped and new clips used.
(c) Torque all nuts in the flight control surface rigging system in accordance with AC 43.13-1A
or to torques specified within this manual.
(d) After completion of adjustment, each jam nut must be tightened securely and inspected.
(e) On push rods or rod ends provided with an inspection hole, screws must be screwed in
sufficiently far to pass the hole. This can be determined visually or, by feel, by inserting a
piece of wire into the inspection hole. If no inspection hole is provided, a minimum of 0.375
of an inch thread engagement must be maintained.
(f) All cable rigging tensions given must be corrected to ambient temperature in the area where
the tension is being checked. Refer to Chart 1.
(g) See Figure 1 for proper method of adjusting rod ends to prevent possible damage and binding
of bearing surface in rod end.
(h) All pulley guard pins should be properly installed.
PIPER AIRCRAFT
PA-32R-301/301T
MAINTENANCE MANUAL
2A23
27-00-00
Page 27-1
Reissued: July 1, 1993