Airworthiness directives › 2014-20-08
AD 2014-20-08 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Models named: L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, L-1011-385-3. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes, certificated in any category, as identified in Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
For Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes, serial numbers 1189 and subsequent: At the applicable compliance time specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, do the inspections specified in paragraphs (g)(1) through (g)(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 3,600 flight cycles or 7,200 flight hours, whichever occurs first. (1) Do a detailed inspection for castellation and skin clips cracked or damaged (including cracks, loose or missing fasteners, oversized and missed drilled fastener holes, corrosion, dents, scratches and other signs of distress) between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar, in accordance with the Accomplishment Instructions of Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008. (2) Do a general visual inspection for cracking or damage (including cracks, loose or missing fasteners, oversized and missed drilled fastener holes, corrosion, dents, scratches and other signs of distress) of the pylon back-up torque box structure, in accordance with the Accomplishment Instructions of Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008. (3) Do a general visual inspection for cracking, damage (including cracks, loose or missing fasteners, oversized and missed drilled fastener holes, corrosion, dents, scratches and other signs of distress), or failure of the wing box external areas at the drag brace aft wing fitting, in accordance with the Accomplishment Instructions of Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008. (4) Do a general visual inspection for cracking or damage (including cracks, loose or missing fasteners, oversized and missed drilled fastener holes, corrosion, dents, scratches and other signs of distress) of the outer surface of the wing upper and lower skins for cracks along the rib attachment at the fastener holes and between the two rows of attachments, in accordance with the Accomplishment Instructions of Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008.
Unsafe condition
This AD was prompted by reports of cracked rib cap castellations. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1