AD 95-10-17
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | L-1011-385-1 | Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-14 | Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-15 | Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-3 | Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes |
Unsafe Condition
Fatigue cracking of fuselage frames at the fastener hole attaching the outer flange to the WL 280.6 longeron, potentially leading to reduced structural integrity due to pressurization loads.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct either an external X-ray inspection or both an internal close visual and eddy current inspection to detect cracking or severing of fuselage frames. Perform an inspection using eddy current surface scan or magneto-optic imager on adjacent frames and external skin, or repair if necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
25 days for airplanes with 25,000 or more total landings; 120 days for those with 20,000 to 25,000 total landings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Lockheed Aeronautical Systems Company Model L-1011-385 series airplanes including L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3.
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
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.