| AD Number | 75-17-04 | Status | Active |
| Effective Date | April 21, 1978 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-3185 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Lockheed Martin Corporation |
| Model(s) | 382 382B 382E 382F 382G |
75-17-04 LOCKHEED: Amendment 39-2300 as amended by Amendment 39-3185. Applies to all Model 382 series airplanes, serial numbers 3946 and 4101 through 4751, certificated in all categories.
Compliance required within the next 325 hours' time in service on airplanes which have accumulated 10,000 or more flight hours and thereafter at each "C" check inspection.
(a) To detect cracks in the main frames, inspect the frames in accordance with Lockheed Service Bulletin A382-189, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region.
(b) In the event a crack or cracks are found, before further flight, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320.
(c) The inspection required by the A.D. may be discontinued on those airplanes which have been repaired in accordance with Lockheed Service Bulletin A382-189, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region.
Amendment 39-2300 became effective August 8, 1975.
This Amendment 39-3185 becomes effective April 21, 1978.