| AD Number | 66-05-03 | Status | Active |
| Effective Date | February 19, 1966 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-182 |
| 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) | 188A 188C |
66-05-03 LOCKHEED: Amdt. 39-182 Part 39 Federal Register January 19, 1966. Applies to Models 188A and 188C Series Airplanes.
Compliance required as indicated, unless already accomplished.
To detect fatigue cracks emanating from the barrel-nut access holes of the outer wing front cap fittings at the Wing Station 65 joint, accomplish the following:
(a) Inspect lower cap fittings, P/N's 807352-1 and -2, by visual means, for cracks emanating from the barrel-nut access holes within the next 1,100 hours' time in service after the effective date of this AD.
(b) Inspect lower and upper cap fittings, P/N's 807352-1 and -2 and P/N's 807354-1 and -2, by dye penetrant method or an FAA-approved equivalent, for cracks emanating from the barrel-nut access holes and by visual means for burrs at the forward edge of the access holes within the next 3,000 hours' time in service after compliance with (a).
(c) Replace any cracked fittings found during the inspections required by (a)or (b) before further flight, with new deburred fittings of the same part number, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made.
(d) Deburr uncracked fittings on which burrs have been found during the inspection required by (b), before further flight, in accordance with Lockheed Service Bulletin 88/SB-633B, Section 2.D.(4) or later FAA-approved revision, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made.
This directive effective February 19, 1966.