AD 64-08-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Aeronautics Company | 1649A-98 | LOCKHEED Model 1649A Series Aircraft |
Unsafe Condition
Cracks in the wing upper milled skin panel (second plank aft of the front spar) aft of Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to skin lap joints.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect for cracks using ultrasonic shear wave inspection technique (within 350 hours' time in service after effective date, then every 5,500 hours). Visually inspect for cracks (within 1,400 hours' time in service after effective date, then every 1,050 hours). Repair cracks per Lockheed Report 11885 or FAA-approved equivalent before further flight. Ferrying allowed under Section 1.76 of CAR Part 1 pending repair.
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Compliance Time
Within 350 hours' time in service after May 11, 1964, and within each 5,500 hours' time in service thereafter for ultrasonic inspections; within 1,400 hours' time in service after May 11, 1964, and thereafter at intervals not exceeding 1,050 hours' time in service for visual inspections.
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Affected Aircraft
Lockheed Model 1649A Series Aircraft (all serial numbers)
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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