Piper PA-34-200T Seneca II, Руководство по обслуживанию

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PIPER SENECA II SERVICE MANUAL
V - SURFACE CONTROLS 01/01/09
1H8
g. To adjust the trim travel right, perform the following:
1. Add shim washers at the aft end of the shaft to reduce the trim travel.
2. Remove shim washers at the aft end of the shaft to increase the trim travel.
h. Check the trim and servo travels by swinging the rudder full left with full right trim and full right
rudder with full left trim.
i. Check all travels with specifications given in Table V-I.
j. Determine the free play of the rudder tab with the rudder securely held against either stop. Total
free travel measured at the tab trailing edge must not exceed 0.06 inch. If this tolerance is exceeded,
check the travel control arm assembly for wear at the center bolt and the bolt attaching the rudder
trim rod to the control arm. Replace the arm assembly and associated hardware if there is any
noticeable wear or elongation of the holes. Check the rudder trim barrel end play in the mounting
bracket. Total allowable play is .006 to .008 inches. Use 62833-18 laminated shim stock washer as
required to achieve the correct end play.
5-35. WING FLAP CONTROLS. (See Figure 5-13.)
5-35a. FLAP HANDLE CONTROL CABLE ATTACHMENT BOLT 100 HOUR INSPECTION.
1. Remove royalite flap handle and trim wheel cover.
2. Remove flap handle mounting bracket attachment bolts and raise handle and bracket assembly to
allow access to the flap control cable attachment bolt.
3. Remove and inspect cable attachment bolt for possible wear. If an AN23-10 bolt is installed or if
wear is detected, replace existing bolt with a new Clevis Bolt (AN23-11) P/N 400-673.
4. Re-install hardware ensuring a bushing (P/N 63900-174) is in the flap handle lever bolt hole. If bolt
hole has not previously been enlarged to accommodate the bushing refer to Detail A, Figure 5-13.
5-36. REMOVAL OF WING FLAP CONTROLS. (Refer to Figure 5-13.)
a. The flap torque tube assembly may be removed by the following procedure:
1. Remove the access plate located between the underside of the aft section of each wing and the
fuselage by removing attaching screws.
2. Remove the floor panel located aft of the main spar by removing the center seats, seat belt
attachments and the screws securing the panel. Lift the panel and remove from airplane.
3. Disconnect the left and right flap control tubes (rods) (13) at the flaps by removing the
nuts, washers and bolts (2) or at the torque tube cranks (arms) (17) by removing the bolts
and washers (16) from the inner side of each crank. It will be necessary to remove bolt (16)
through a hole in the side skin of the fuselage located over the torque tube with the flap handle
moved to its 40 degree position.
4. With the flap handle (30), fully extend the flaps and disconnect the flap tension spring (23) at
the spar or the aft end of the control cable (24) as desired.
5. Grasp the flap handle (30); release the plunger (31) and allow the flap to return to the retracted
position. Use caution as forward pressure will be on the handle with the tension spring (23)
disconnected.
6. Disconnect the flap return spring (18) at the spar or return chain (11) as desired.
7. Disconnect the control cable from the chain (20) by removing cotter pin, nut, and clevis bolt (21).
8. Remove the tube support bearing blocks (3) by removing the block attachment bolts (7).