| AD Number | 81-24-01 | Status | Active |
| Effective Date | November 19, 1981 | Issue Date | November 03, 1981 |
| Docket Number | Unknown | Amendment | 39-4262 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | --- - _EMPTY_ |
| Citation | This information is not available. | ||
| Manufacturer(s) | Piper Aircraft Inc. |
| Model(s) | PA-36-285 PA-36-300 PA-36-375 |
81-24-01 PIPER: Amendment 39-4262. Applies to Piper airplane Models PA-36-285 and PA-36-300, S/N 36-7360001 thru 36-8160001, 36-8160003, 36-8160004 and 36-8160009 and PA-36-375, S/N 36-7802001 thru 36-8102004, certificated in all categories.
To prevent failure of the rudder control system, and seat and harness cable assemblies, accomplish the following inspection or an approved equivalent.
(a) Within the next 15 hours in service after the effective date of this AD, inspect for cracks, using a dye penetrant method,
(1) Two Rudder Control Shackles, Piper P/N 486 566 (MS 20115-5), and
(2) Two MS 20115-5 shackles on seat and harness cable assemblies, Piper P/N 98193-10 and 98193-9, respectively.
(b) Replace all shackles found cracked prior to further flight with new shackles Piper P/N 486 566 or equivalent which have been previously inspected for cracks in accordance with paragraph (a).
(c) Equivalent inspections or parts must be approved by the Chief,Engineering and Manufacturing Branch, FAA, Eastern Region.
(d) Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector.
This amendment is effective November 19, 1981.