Airworthiness Directive · Amendment 39-17981 · Wings
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
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.
We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. This AD was prompted by reports of cracked rib cap castellations. This AD requires repetitive inspections for castellation and skin clips cracked or damaged between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar; repetitive inspections for cracking, damage, or failure of the pylon back-up torque box structure; repetitive inspections for cracking or damage of the wing box external areas at the drag brace aft wing fitting; repetitive inspections of the outer surface of the wing upper and lower skins for cracks or damage along the rib attachment at the fastener holes and between the two rows of attachment; and corrective actions if necessary. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
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.
(1) For airplanes that have not accomplished the inspections described in Lockheed Martin Service Bulletin 093-57-207 prior to the effective date of this AD: At the later of the compliance times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Before the accumulation of 15,000 total flight cycles or 27,000 total flight hours, whichever occurs first.
(ii) Within 1,800 flight cycles or 3,600 flight hours, whichever occurs first, after the effective date of this AD.
(2) For airplanes that have accomplished the inspections described in Lockheed Martin Service Bulletin 093-57-207 prior to the effective date of this AD: Within 3,600 flight cycles or 7,200 flight hours, whichever occurs first, after the completion of the most recent inspections, except as specified in paragraph (h)(3) of this AD.
(3) For rib caps that have been modified as described in Lockheed Martin Service Bulletin 093-57-207: Before the accumulation of 15,000 total flight cycles or 27,000 total flight hours, whichever occurs first, for that rib cap only.
If any cracking, damage, or failure is found during any inspection required by paragraph (g) of this AD: Before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Lockheed Martin Service Bulletin 093-57-207, Revision 5, dated November 14, 2008, except where this service bulletin specifies that all other damaged structural items should be repaired using the best shop practices, following procedures in Structural Repair Manual 57-12-00, this AD requires repairing the damage before further flight, in accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
Submit a report of positive findings of the inspection for cracking, damage, or failure required by this AD to the Manager, Atlanta ACO, at the applicable time specified in paragraph (j)(1) or (j)(2) of this AD. The report must include the inspection results, a description of the discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
