- Effective
- May 8, 1970
- Models
- S-61A, S-61D, S-61E, S-61L, S-61N, S-61NM, S-61R, S-61V
- Registered aircraft
- 54 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-980
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.
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On this page
The airworthiness directive
70-09-03 SIKORSKY: Amdt. 39-980. Applies to S-61 Type Helicopters.
To prevent failure of P/N S6135-66649 and S6137-66704 series tail gear box pitch beams accomplish the following:
(a) Within the next 10 days or 25 hours in service, whichever occurs first after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 90 days or 240 hours in service, whichever occurs first, from the last inspection perform the inspections of the bore area of the pitch beam in accordance with Sikorsky Service Bulletin No. 61B35-7 dated 12 February 1970 or later revisions or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. If a crack is found, remove the pitch beam from service prior to further flight.
This amendment is effective May 8, 1970.
Affected TCDS · 2
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 54
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1960 | 1 |
|---|---|
| 1961 | 2 |
| 1962 | 1 |
| 1963 | 4 |
| 1964 | 2 |
| 1966 | 2 |
| 1968 | 3 |
| 1969 | 2 |
| 1970 | 1 |
| 1971 | 2 |
| 1972 | 1 |
| 1973 | 1 |
| 1974 | 4 |
| 1975 | 2 |
| 1976 | 2 |
| 1977 | 6 |
| 1978 | 3 |
| 1979 | 1 |
| 1980 | 4 |
| 1985 | 1 |
9 with no year recorded