AD 2011-09-03 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G Airplanes

Models named: 382, 382B, 382E, 382F, 382G. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial Inspections (g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do eddy current inspections to detect cracking of the center wing upper and lower rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A and B, dated May 20, 2009. If any crack is found during the inspections required by paragraph (g) of this AD, before further flight, do the actions required by paragraph (k) of this AD. (1) Before the accumulation of 15,000 total flight hours on the rainbow fitting. (2) Within 365 days or 600 flight hours on the rainbow fitting after the effective date of this AD, whichever occurs first. Repetitive Inspection Schedule (h) Repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 3,600 flight hours on the center wing, until the rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by paragraph (h) of this AD, before further flight, do the actions required by paragraph (k) of this AD. Rainbow Fitting Replacements (i) Before the accumulation of 30,000 flight hours on the rainbow fitting, or within 600 flight hours after the effective date of this AD, whichever occurs later: Replace the rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, including Appendix C, dated May 20, 2009, except as required by paragraph (l) of this AD. Replace the rainbow fitting thereafter at intervals not to exceed 30,000 flight hours. Post-Replacement Repetitive Inspections (j) For upper and lower rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD: Do the eddy current inspections specified in paragraph (g) of this AD within 15,000 flight hours after doing the replacement and repeat the eddy current inspections specified in paragraph (h) of this AD thereafter at intervals not to exceed 3,600 flight hours until the rainbow fittings are replaced in accordance with paragraph (i) or (k) of this AD. Replacement, Related Investigative Actions, and Corrective Actions (k) If, during any inspection required by paragraph (g) or (h) of this AD, any crack is detected in the rainbow fitting, before further flight, replace the rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with Paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, including Appendix C, dated May 20, 2009, except as provided by paragraph (l) of this AD. Exceptions to Service Bulletin (l) Where Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009, specifies to contact the manufacturer for disposition of certain repair conditions or does not specify corrective actions if certain conditions are found, this AD requires repairing those conditions using 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. Credit for Actions Accomplished in Accordance With Previous Service Information (m) Actions accomplished before the effective date of this AD in accordance with Lockheed Service Bulletin 382-57-82, Revision 3, including Appendixes A, B, and C, dated April 25, 2008, are acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (n)(1) The Manager, Atlanta ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Carl Gray, Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; telephone (404) 474-5554; fax (404 474-5606. (2) Before using any approved AMOC, notify your appropriate principal inspector, the manager of the local flight standards district office/certificate holding district office. Material Incorporated by Reference (o) You must use Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-5445; e-mail ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on April 12, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-9285 Filed 4-20-11; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of fatigue cracking of the wing upper and lower rainbow fittings during durability testing and on in-service airplanes. Analysis of in-service cracking has shown that these rainbow fittings are susceptible to multiple site fatigue damage. The Federal Aviation Administration is issuing this AD to detect and correct such fatigue cracks, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing.