| AD Number | 71-12-01 | Status | Active |
| Effective Date | June 08, 1971 | Issue Date | May 21, 1971 |
| Docket Number | Unknown | Amendment | 39-1220 |
| 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-23 PA-23-160 PA-23-250 (Navy UO-1) |
71-12-01 PIPER AIRCRAFT: Amdt. 39-1220. Applies to all PA-23 and PA-23-160 type aircraft serial numbers 23-1 and up and PA-23-250 aircraft serial numbers 27-1 through 27- 140 inclusive.
Compliance required as indicated unless already accomplished.
To prevent failure of the engine controls support bracket in the cockpit pedestal, accomplish the following:
1. Within 15 hours' time in service for airplanes with 2000 hours' or more total time and 50 hours' time in service with less than 2000 hours' total time after the effective date of this AD, visually inspect P/N 17892-00 engine control cable support bracket for cracks, distortion and security of attachment. Any part found cracked or distorted must be replaced prior to further flight.
2. The inspection described in paragraph (1) above must be accomplished at intervals of 100 hours' time in service until an improved bracket, Piper P/N 16975-00 or an equivalent part approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, is installed. Upon installation of the improved part, the above repetitive inspections are no longer required.
3. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD. (Piper Aircraft Corp. Service Bulletin No. 335 pertains to this subject.)
This amendment is effective June 8, 1971.