Airworthiness Directive · Amendment 39-18118 · Wings
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes; certificated in any category; having any outer wing serial number 4542 and subsequent, or any manufacturing end product (MEP) replacement outer wing except 14Y series.
We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower rainbow fittings on the outer wing are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the upper and lower rainbow fittings on the outer wing to detect cracks propagating from fasteners attaching the fittings to skin panels, and related investigative and corrective actions if necessary; and replacement of the upper and lower rainbow fittings on the outer wing. We are issuing this AD to prevent fatigue cracking of the upper and lower rainbow fittings on the outer wing and skin-panel- to-fitting fastener holes, which could result in reduced structural integrity of the airplane and possible separation of the wing from the airplane.
At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do an ECSS inspection of the left and right outer wing upper and lower rainbow fitting-to-skin-panel attachments to detect cracks propagating from fasteners attaching the fittings to skin panels, and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013, except as provided by paragraph (j)(1) of this AD. Do all applicable related investigative actions before further flight. If any cracking is found during any inspection required by this paragraph, before further flight, repair the cracking, using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Repeat the inspection of the left and right outer wing upper and lower rainbow fitting-to-skin-panel attachments thereafter at intervals not to exceed 2,000 flight hours, except as provided by paragraph (l) of this AD.
(1) Before the accumulation of 30,000 total flight hours on any wing.
(2) Within 365 days or 600 flight hours, whichever occurs first, after the effective date of this AD.
At the time specified in paragraph (i) of this AD, do the actions required by paragraph (h)(1) and (h)(2) of this AD.
(1) Do a detailed inspection of the wing faying structure for damage and cracks, and do an automated bolt hole eddy current inspection on all open fastener holes in the mating structure, stiffeners, webs and angles for cracking, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013, except as provided by paragraph (j)(1) of this AD.
(i) If any damage is found during any inspection required by paragraph (h)(1) of this AD, before further flight, repair the damage, using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(ii) If any cracking is found during any inspection required by paragraph (h)(1) of this AD, before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013, except as provided by paragraphs (j)(1) and (j)(2) of this AD.
(2) Replace the left and right upper and lower rainbow fittings of the outer wing with new fittings, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013.
Note 1 to paragraph (h) of this AD: AD 2012-06-09, Amendment 39-16990 (77 FR 21404, April 10, 2012), is related to the rainbow fitting replacement. AD 2012-06-09 references the Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2010; which contains inspections for the entire Model 382B-H airframe, not just the outer wing. Since installing new rainbow fittings, as required by paragraph (g) of this AD, resets the accumulated service life on certain parts to zero, certain compliance times specified in Table 3 of this SSID would be affected by the installation of new outer wing fittings.
Note 2 to paragraph (h) of this AD: AD 2011-15-02, Amendment 39-16749 (76 FR 41647, July 15, 2011), has requirements for fuel system limitations and critical design configuration control limitations, which might include configuration or parts limitations on areas affected by accomplishment of this AD.
At the later of the times specified in paragraph (i)(1) and (i)(2) of this AD, do the actions required by paragraph (h) of this AD.
(1) Before the accumulation of 50,000 total flight hours on any wing.
(2) Within 60 days or 100 flight hours, whichever occurs first, after the effective date of this AD.
(1) Although Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
(2) Where Lockheed Martin Aeronautics Company Service Bulletin 382-57-95, including Appendix A, dated December 16, 2013, specifies to contact Lockheed for repair instructions, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
After replacement of the left and right upper and lower rainbow fittings of the outer wing with new fittings, as required by paragraph (h) of this AD, any subsequent rainbow fitting replacements must be done using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
For any wing on which the left or right upper and lower rainbow fittings of the outer wing have been replaced with new fittings as required by paragraph (h) of this AD: Before the accumulation of 30,000 flight hours after accomplishing the replacement, do the inspection required by paragraph (g) of this AD and repeat thereafter at the times specified in paragraph (g) 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.
