2.
Block the trim cables at the first set of pulleys forward of the cable turnbuckles in the aft section of the fuselage by the method shown in Figure 27-21.
3.
Disconnect the cable at the turnbuckles in the aft section of the fuselage.
4.
Remove cable guard from pulley cluster and cable guards from pulley cluster.
5.
Remove the fin tip by removing attachment screws.
6.
Disconnect the push rod by removing the attaching hardware securing push rod to screw.
7.
Remove bolts, washers, bushings and nuts securing forward end of barrel. Remove snap ring to free aft end of barrel.
8.
Draw the trim cable from the fuselage and up the fin.
INSTALLATION OF AFT STABILATOR TRIM CONTROLS. (Refer to Figure 27-22.)
1.
Wrap the trim barrel by first laying the center of the trim cable (as measured equally from each end to the center of the cable) in the slot of the barrel. Bring the half of the cable to be used on the right side through the diagonal slot in the flange at the forward end of the barrel and wrap aft in a clockwise direction 7 wraps to the center of barrel. Bring the half of the cable to be used on the left side through the diagonal slot in the aft end of the barrel and wrap forward in a counterclockwise direction 7 wraps to the center of barrel. ( Refer to Figure 27-23 .)
2.
Block the cable by clamping between two pieces of wood laid next to the wraps to prevent unwrap-ping. Fabricate block with a notch so hardware can be installed.
3.
Lubricate the bearings and install barrel per exploded view given in Figure 27-22. Install the barrel using any combination of AN960-10, AN960-10L and AN960PD 10L washers to achieve free barrel rotation with trim cable rigged and tensioned.
4.
Rotate the cables down the fin into the fuselage through the two pulley clusters and attach the ends to the forward trim cables.
5.
Install all cable guards.
6.
Remove the blocks that are holding the forward cables tight and aft cables at the barrel.
7.
Set cable tension and check rigging and adjustment. Check safety of all turnbuckles.
8.
Install fin tip and secure with screws.
9.
Install the access panel to the aft section of the fuselage.
RIGGING AND ADJUSTMENT OF STABILATOR TRIM. (Refer to Figure 27-22.)
1.
Level the airplane. (Refer to Leveling, Chapter 8.)
2.
Check for proper stabilator trim cable tension as given in Figure 27-20. If cables were disconnected, rotate the control wheel several times to allow the cables to seat and recheck tension.
3.
Secure the stabilator in neutral position: stabilator chord line parallel with front seat tracks.
4.
To obtain correct travels, if incorrect, adjust by disconnecting the rod end and turning the end in or out as required. Travel adjustments which cannot be corrected at the rod end adjustment require the repo-sitioning of the screw in the barrel. A screw position of approximately 1.38 inches of screw exposure at the aft end of the barrel is suggested as a preliminary neutral setting from which final adjustments can be made at the rod end. (Refer to Figure 27-21.)
5.
If required, adjust the stabilator tab push rod to streamline the tab with the stabilator. This is the neu-tral position of the tab.
6.
Turn the trim control wheel to its full up and full down position alternately. Travel of the tab from its neutral position should match the travels shown in Figure 27-20.
27-30-00 Page 27-53 Issued: April 1, 1997 27-30-00 Page 27-54 Issued: April 1, 1997
Figure 27-24. Stabilator Trim Screw Adjustment 7.
Move the stabilator and trim tab to all extremes of travel and check to insure that there is no interference between the turnbuckles and pulleys.
8.
Check to insure that the stabilator up and down stops are contacted before the tee bar stops are contacted.
9.
With the stabilator held securely against either stop, determine the free play of the stabilator tab. Total free play, measured at the tab trailing edge must not exceed 0.15 of an inch.
STALL WARNING HORN AND LIFT DETECTOR.
This system consists of two detectors which are electrically connected to the flap position switch and the stall warning horn. Performed the following ground check to determine that the lift detectors are functioning properly.
The lift detectors are located on the left wing. With the master switch ON gently lift the tabs on both lift detectors; the stall warning horn should not sound. With the master switch still ON, activate the main gear squat switch to simulate inflight conditions; extend the flaps to the 10° flap position. The 0° to 10° flap positions relate only to the outboard lift sensor. Gently lift out the outboard sensor; the stall warning horn should sound. Lifting the inboard sensor should not sound the horn. With flaps positioned from 25° to 40° gently lift the inboard sensor, the horn should sound. Lifting the outboard sensor should not sound the horn. With the check completed return the flaps to the full up position, turn the master switch OFF and remove any items used to activate the squat switch.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：西门诺尔飞机维护手册 simenole PA-44-180 AMM 1(88)
