Piper PA-34-200T Seneca II Service Manual Download

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PIPER SENECA II SERVICE MANUAL

01/01/09

V - SURFACE CONTROLS

1F21

SECTION V

SURFACE CONTROLS

5-1. INTRODUCTION.

This section explains the removal, installation, and rigging and adjustment procedures for the control
surfaces of the various structural components. For the removal and installation of the structural surfaces
of the airplane, refer to Section IV. The assemblies need not be removed in order of paragraph since each
paragraph describes the individual removal and installation of the various assemblies. The following tips
may be helpful in the removal and installation of the various assemblies:

It is recommended, though not always necessary, to level and place the airplane on jacks during
rigging and adjustment, especially when using a bubble protractor or level.

Remove the turnbuckle barrels from cable ends before withdrawing the cable through the structures.

Tie a cord to the cable end before drawing cable through structures to facilitate reinstallation of
cable.

When turnbuckles have been set to correct tension, no more than three threads should be exposed
from either end of the turnbuckle barrel. Locking clips, after installation, should be checked for
security by trying to remove the clips using fingers only. Both locking clips may be inserted in the
same hole of the turnbuckle barrel, or they may be installed in opposite holes. After being removed,
locking clips should be discarded, not reused.

Assemble and adjust a turnbuckle so that each terminal is screwed on approximately equal distance
into the barrel. During adjustment, do not turn the terminals in such a manner as to put a permanent
twist in the cables.

When installing rod end jam nuts refer to Figure 5-1a for proper installation method. After adjusting
a jam nut, ensure that it is securely tightened and thoroughly inspected.

If the push rod or rod end has an inspection hole, the screw should be screwed in far enough to pass
the hole. This can be determined visually or by feel, inserting a piece of wire into this inspection
hole. If there is no inspection hole, there should be a minimum of 3/8 inch thread engagement.

NOTE: Cable rigging tensions specified in this section should be corrected to ambient temperature

in the area where the tension is being checked using Table V-II.

5-2. DESCRIPTION.

The Seneca II is controlled in flight by the use of three standard 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 at the balance arm of the stabilator. Cables also connect the
rudder pedals with the rudder sector. Provisions for directional and longitudinal trim are provided by
adjustable trim mechanisms for the stabilator and rudder. Both the stabilator and rudder trim are
controlled by individual wheel and drum assemblies mounted on the floor tunnel between the front seats.
Cables routed aft from the drums to the tail cone operate the particular screw assembly which in turn
moves the stabilator or rudder trim tab.

Piper PA-34-200T Seneca II, Service Manual

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