Airworthiness Directive · Amendment 39-16665 · Wings
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G Airplanes
Superseded. A later AD replaced this one: AD 2015-06-08. Comply with the one in force.
This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all Model 382, 382B, 382E, 382F, and 382G airplanes. This AD requires repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacements of rainbow fittings, which would extend the repetitive interval for the next inspection. 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. We are 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.
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.
(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.
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.
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.
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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
