AD 67-11-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Models 188A and 188C Series Airplanes |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Models 188A and 188C Series Airplanes |
Unsafe Condition
Cracking of the fuselage main frame forgings, part numbers 801030-3, -4, 801031-1, and -2, at areas above and below the floor line.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect fuselage main frame forgings for cracks above and below the floor line using specified methods; rework intercostals and floor support structures per Lockheed drawings or service bulletins; repair or replace cracked forgings before further flight with approved methods, including special or complete repairs, new forgings, or new design replacements. Implement recurring inspections and rework within specified time intervals.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated in the AD, with specific intervals based on time in service: inspections within 60/350 hours post-effective date or prior to reaching 10,060/15,350 hours, rework within 2,000/4,000 hours post-effective date or prior to 12,000/19,000 hours, and subsequent inspections/rework at intervals not exceeding 1,000/4,000 hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Lockheed Models 188A and 188C Series airplanes with fuselage main frame forgings part numbers 801030-1 through -4 and 801031-1 through -2.
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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