- Effective
- May 30, 1974
- Model
- G-1159
- Data sheet
- TCDSA12EA
- Registered aircraft
- 14 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-1851
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 May 30, 2024.
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 | 19 KB | acb69c33…4823318 | FAA DRS (API key needed) |
On this page
The airworthiness directive
74-12-04 R2 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 1851 Applies to Grumman G-1159 airplanes certificated in all categories.
Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished.
To prevent operation of the pitch trim at a greater rate when an additional signal in the opposite direction is selected, modify the Automatic Flight Control System junction box in accordance with Grumman American Aviation Corporation, Aircraft Service Change 143, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
This amendment becomes effective May 30, 1974.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 14
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1967 | 1 |
|---|---|
| 1968 | 2 |
| 1971 | 1 |
| 1974 | 1 |
| 1976 | 1 |
| 1977 | 1 |
7 with no year recorded