AD/PA-24/33 Amdt 3 - Stabilator Torque Tube Bearing Block Attachment Fitting
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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Piper PA-24 (Comanche) Series Aeroplanes
AD/PA-24/33
Amdt 3
Stabilator Torque Tube Bearing Block Attachment Fitting
10/94
Applicability: Model Serial Numbers
PA24-180, PA24-250, and PA24-260 24-1 through 24-5047 PA24-400 26-2 through 26-148
Requirement: 1. Inspect the stabilator torque tube bearing support fittings for looseness by accomplishing the following:
Remove the tailcone and rear aft fuselage access door.
b. Grasp the stabilator tip and exert a fore and aft force and then an up and down force.
c. If looseness is found during the inspection specified above, incorporate Piper Part No. 760 835 (Hi-Shear Rivet Replacement Kit) on the affected fitting.
d. Reinstall the tailcone and right rear aft fuselage access door.
2. Reinspect all stabilator torque tube bearing support fittings on which Piper Kit Part No 760 835 has not been incorporated; in accordance with Requirement 1 of this Directive.
Note 1: Incorporating Piper Kit Part No. 760 835 on all four stabilator torque tube bearing support fittings constitutes terminating action for the inspection requirements of this Directive.
Note 2: FAA AD 94-13-10 Amdt 39-8951 and Piper SB 411A refer.
Compliance: 1. Within 100 hours time in service after 15 September 1994, unless Piper Kit Part No. 760 835 is incorporated on all four stabilator torque tube bearing support fittings.
- At intervals not to exceed 100 hours time in service, until Piper Kit Part No. 760 835 is incorporated on all four stabilator torque tube bearing support fittings.
The compliance of the previous issue of this Directive was “at intervals not exceeding 300 hours time in service”.
This amendment is effective from 15 September 1994.
Background: Incidents of looseness of the stabilator torque tube bearing support fittings prompted the issue of this Directive. The actions specified are intended to prevent the loss of pitch control because of looseness of the fittings. Amendment 3 is issued to align this Directive with the issue of a new FAA AD which specifies reinspection and terminating action criteria.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES