AD 98-10-14
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | L-1011-385-1 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-14 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-15 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-3 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
Unsafe Condition
Fatigue cracking of the rear spar caps, web, skin, and certain fastener holes could lead to rear spar rupture, extensive wing damage, and fuel spillage.
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Required Actions
Perform initial inspections and follow-on actions per Lockheed L-1011 Service Bulletin 093-57-203, Revision 6, including repetitive X-ray, eddy current surface scan, bolt hole eddy current, ultrasonic, and low frequency eddy current ring probe inspections. Repeat inspections at intervals specified in Table I of Revision 6 of the service bulletin.
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Compliance Time
Within 6 months after May 15, 1996, or at the times specified in Table I of Revision 4 of the service bulletin, whichever occurs later. After the AD's effective date (June 19, 1998), subsequent inspections must follow Table 1 of Revision 6.
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Affected Aircraft
Lockheed Model L-1011-385-1, L-1011-385-3, L-1011-385-1-14, and L-1011-385-1-15 series airplanes, certificated in any category.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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