| AD Number | 62-14-03 | Status | Active |
| Effective Date | June 26, 1962 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Schweizer Aircraft Corporation |
| Model(s) | 269A |
62-14-03 HUGHES: Amdt. 455 Part 507 Federal Register June 21, 1962. Applies to Model 269A helicopter Serial Numbers 0011 to 0059 Inclusive.
Compliance required as indicated.
(a) To prevent failure of the tail rotor blade, within the next 10 hours' time in service after the effective date of this AD, and each day thereafter, conduct a visual inspection of the tip of the Hughes P/N 269A6124 tail rotor blade for separation of the rib and the blade skin. This will appear as a crack in the bond line between the blade tip rib and the blade skin.
(b) If no separation is detected, the tail rotor blades may continue to be used in service for the remainder of their service life subject to the inspection specified in paragraph (a).
(c) If separation is detected, remove the tail rotor assembly and replace prior to further flight with an assembly incorporating tail rotor blades P/N 269A6124 Change E or later. After installation of P/N 269A6124 Change E or later, the normal inspection procedures may be followed.
(Hughes Tool Company, Aircraft Division, Hughes-O-Gram to operators dated May 2, 1962, covers the same subject.)
This directive effective June 26, 1962.