- Effective
- October 15, 1980
- Models
- 205A-1, 212
- Registered aircraft
- 118 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-3931
- Docket
- 76-SW-28
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 | 20 KB | 977127ca…b8b2277 | FAA DRS (API key needed) |
On this page
The airworthiness directive
80-21-05 BELL: Amendment 39-3931. Applies to Model 205A-1 and 212 helicopters equipped with fixed float landing gears. (Airworthiness Docket No. 76-SW-28)
Compliance required within 50 hours' time in service after the effective date of this Ad unless already accomplished.
To preclude possible fatigue cracks from occurring in the landing gear cross tubes under the riveted saddle fittings, install forward and aft cross tube assemblies, P/N 205-050-114-23 and -25 respectively or higher dash numbers that have clamp-on saddle fittings.
Float kit installation, P/N 205-706-050-101, uses cross tubes having clamp-on saddle fittings.
(Bell Helicopter Textron Alert Service Bulletin Nos. 212-80-18 and 205-80-13 also pertain to this subject.)
This amendment becomes effective October 15, 1980.
Affected TCDS · 2
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 118
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1968 | 5 |
|---|---|
| 1969 | 3 |
| 1970 | 2 |
| 1971 | 3 |
| 1972 | 5 |
| 1973 | 7 |
| 1974 | 11 |
| 1975 | 9 |
| 1976 | 5 |
| 1977 | 5 |
| 1978 | 3 |
| 1979 | 14 |
| 1980 | 12 |
| 1981 | 4 |
| 1982 | 4 |
| 1984 | 1 |
| 1991 | 1 |
| 1993 | 2 |
| 1995 | 1 |
21 with no year recorded