| AD Number | 67-18-03 | Status | Active |
| Effective Date | March 12, 1973 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1601 |
| 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 |
67-18-03 LOCKHEED: Amendment 39-423 as amended by Amendment 39-1601. Applies to Model 382 and 382B series airplanes, serial numbers 3946 and 4101 through 4196.
Compliance as indicated.
(a) For airplanes with 2350 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection.
(b) For airplanes with less than 2350 hours' total time in service on the effective date of the AD comply with Paragraph (c) before the accumulation of 2400 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection.
(c) Inspect all eight affected engine mount truss assemblies in accordance with the tooling and inspection instructions given in Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, Section 1f and 2a through 2e, respectively, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
(1) Cracked parts shall be replaced with new parts having the same part number, or with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision. Replacement truss assemblies shall be installed according to the replacement instructions given in Section 2h through 2aa in the above Service Bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region.
(2) Replacement of cracked trusses shall be accomplished before further flight, except that one flight may be made for the purpose of obtaining the necessary replacements in accordance with the provisions of FAR 21.197.
(d) When a particular truss assembly is replaced with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153dated December 1, 1966, or later FAA approved revision, the repetitive inspection of that truss as required by this AD may be discontinued.
Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966, covers this same subject.
Amendment 39-423 became effective June 25, 1967.
This Amendment 39-1601 becomes effective March 12, 1973.