| AD Number | 70-09-03 | Status | Active |
| Effective Date | May 08, 1970 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-980 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Sikorsky Aircraft Corporation |
| Model(s) | S-61A S-61D S-61E S-61L S-61N S-61NM S-61R S-61V |
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.