- Effective
- July 8, 1974
- Published
- July 5, 1974
- Issued
- June 21, 1974
- Model
- PA-36-285
- Registered aircraft
- 40 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-1885
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed November 21, 2025.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 21 KB | 4e542c07…9025251 | FAA DRS (API key needed) |
On this page
The airworthiness directive
74-14-06 PIPER: Amendment 39-1885. Applies to all Model PA-36-285 airplanes, S/N 36-7360001 through 36-7460016 certificated in all categories.
Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished.
To preclude the possibility of having bolts installed in the wing spar carry through assembly which could be subject to deformation, accomplish the following:
(a) Remove a total of four AN 4C-11A bolts and corresponding nuts and washers from the spar center section carry through left and right end vertical stiffeners.
(b) Enlarge these four holes to 5/16" + .005 - .001 diameter. If the maximum hole size above does not eliminate evidence of elongation or wear, damaged parts should be replaced or further repaired in a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
(c) Install an AN5-11A bolt, AN960-516L washer under bolt head, MS20365-524C nut and anAN960-516 washer under nut in each of the four holes. Torque to 100-140 inch pounds.
Piper Service Bulletin No. 425 pertains to this same subject.
This amendment becomes effective July 8, 1974.
Registered aircraft · 40
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1973 | 4 |
|---|---|
| 1974 | 1 |
| 1975 | 22 |
| 1976 | 8 |
5 with no year recorded