| AD Number | 67-21-02 | Status | Active |
| Effective Date | August 13, 1967 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-443 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Pilatus Aircraft Limited |
| Model(s) | PC-6 PC-6-H1 PC-6-H2 PC-6/350 PC-6/350-H1 PC-6/350-H2 PC-6/A PC-6/A-H1 PC-6/A-H2 PC-6/B-H2 PC-6/B1-H2 PC-6/C-H2 |
67-21-02 PILATUS: Amdt. No. 39-443, Part 39, Federal Register July 14, 1967. Applies to all Models PC-6 Airplanes, Serial Numbers to 620.
Compliance required as indicated.
To detect cracks of the elevator attachment bracket, Part No. 6300.11, accomplish the following:
(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the elevator attachment, P/N 6300.11, for cracks between the welded seams.
(b) If cracks are detected during the inspection required by paragraph (a), before further flight either replace the defective part with a new or used uncracked part of the same part number or modify the part in accordance with Pilatus Service Bulletin No. 67 or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent.
(c) The repetitiveinspections required by paragraph (a) of this AD may be discontinued after the elevator attachment bracket is modified in accordance with Pilatus Service Bulletin No. 67 or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent.
This amendment effective August 13, 1967.