Airworthiness Directive · Amendment 39-18126 · Wings
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
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 superseding Airworthiness Directive (AD) 2011-09-03 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This new AD requires reduced intervals for inspections of the upper rainbow fittings. This AD was prompted by analysis of in-service cracking, which has shown that a reduction in the inspection intervals is necessary for the upper rainbow fittings. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing.
This paragraph restates the requirements of paragraph (g) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Except as required by paragraph (m) of this AD, 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; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (m) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated July 11, 2013, for accomplishing the actions specified in this paragraph.
(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 May 26, 2011, (the effective date of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)), whichever occurs first.
This paragraph restates the requirements of paragraph (h) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a new exception. Except as required by paragraph (n) of this AD, 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 this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (n) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only.
This paragraph restates the requirements of paragraph (i) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Before the accumulation of 30,000 flight hours on the rainbow fitting, or within 600 flight hours after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)), whichever occurs later: Replace the rainbow fitting with a new 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; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. Replace the rainbow fitting thereafter at intervals not to exceed 30,000 flight hours. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph.
This paragraph restates the requirements of paragraph (j) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a new exception. For upper and lower rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD: Except as required by paragraph (o) 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. Doing the requirements of paragraph (o) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only.
This paragraph restates the requirements of paragraph (k) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information and revised references to inspection paragraphs. If, during any inspection required by paragraph (g), (h), (m), or (n) of this AD, any crack is detected in the rainbow fitting, before further flight, replace the rainbow fitting with a new 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; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph.
This paragraph restates the requirements of paragraph (l) of AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with revised service information. Where Lockheed Service Bulletin 382-57-82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009; or Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013; 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.
At the applicable compliance time specified in paragraphs (m)(1) and (m)(2) of this AD, do eddy current inspections to detect cracking of the center wing upper rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of this paragraph terminates the requirements of paragraph (g) of this AD for that upper rainbow fitting only. Repeat the inspection thereafter at the interval required by paragraph (n) of this AD.
(1) For upper rainbow fittings that have accumulated less than 10,000 total flight hours as of the effective date of this AD, the compliance time is at the later of the times in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight hours.
(ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first.
(2) For upper rainbow fittings that have accumulated 10,000 total flight hours or more, but less than 15,000 total flight hours as of the effective date of this AD, the compliance time is the earlier of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first.
(ii) Before the accumulation of 15,000 total flight hours on the rainbow fitting.
For upper rainbow fittings on which the requirements of paragraph (g), (h), or (m) of this AD were done, do the next inspection at the earlier of the times required in paragraphs (n)(1) and (n)(2) of this AD. Thereafter, repeat the inspection required by paragraph (m) of this AD at intervals not to exceed 2,500 flight hours until the upper rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing an inspection required by this paragraph terminates the requirements of paragraph (h) of this AD for the affected upper rainbow fitting only.
(1) Within 3,600 flight hours since the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest.
(2) At the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Within 2,500 flight hours after the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest.
(ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first.
For upper rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD, do the inspection required by paragraph (m) of this AD at the earlier of the compliance times required in paragraph (o)(1) and (o)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 2,500 flight hours. Doing the inspections required by this paragraph terminates the requirements of paragraph (j) of this AD for the affected upper rainbow fitting only.
(1) At the later of the times in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD. (i) Within 10,000 total flight hours on the upper rainbow fitting.
(ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first.
(2) Within 15,000 total flight hours on the upper rainbow fitting.
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.
