AD 2005-15-14

To prevent stress corrosion cracking in the forward tang of the upper inboard spar cap of the wing, which could result in structural damage to adjacent components of the wing and consequent reduced structural integrity of the airplane, accomplish the following:

(a) Within 48 months after the effective date of this AD, except as provided by paragraphs (b) and (c) of this AD, perform a one-time eddy current conductivity test of the upper inboard spar cap of the wing to determine the type of material, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC8-57-072 R03, Revision 03, dated October 2, 1995. Although the Accomplishment Instructions of the service bulletin specify that it is necessary to remove the wing leading edge to perform this test, this AD does not require removing the wing leading edge to access the upper inboard spar cap. The conductivity test can be accomplished through the access panels on the lower surface of the wing leading edge, through the main fuel tank, or through the fuselage at station 680, as applicable.

(1) If the test reveals that the upper inboard spar cap is made from 7075-T73 material (as defined in the service bulletin): No further action is required by this paragraph.

(2) If the test reveals that the upper inboard spar cap is made from 7079-T6 material: Within 48 months after the effective date of this AD, except as provided by paragraph (c) of this AD, accomplish the modification specified in the service bulletin, in accordance with the Accomplishment Instructions of the service bulletin. The procedures specified in the service bulletin include determining the condition that applies, trimming the forward tang of the upper inboard spar cap, installing a spar cap angle doubler and stiffener clips, installing wing upper surface doublers, and trimming the front spar stiffeners, as applicable.

(b) For airplanes in Group 2 as defined by McDonnell Douglas Service Bulletin DC8-57-072 R03, Revision 03, dated October 2, 1995: In lieu of accomplishing the one-time eddy current conductivity test to determine the material of the upper inboard spar cap of the wing required by paragraph (a) of this AD, accomplishing the modification in paragraph (a)(2) of this AD within the compliance time specified in that paragraph is acceptable for compliance with this AD.

(c) For airplanes in Group 3 as defined by McDonnell Douglas Service Bulletin DC8-57-072 R03, Revision 03, dated October 2, 1995: The actions specified by paragraph (a) of this AD are not required until the actions specified in McDonnell Douglas DC-8 Service Bulletin 57-30 are accomplished. If the actions specified in McDonnell Douglas DC-8 Service Bulletin 57-30 have not been accomplished before the effective date of the AD, the actions required by paragraph (a) of this AD must be accomplished concurrent with McDonnell Douglas DC-8 Service Bulletin 57-30 (if McDonnell Douglas DC-8 Service Bulletin 57-30 is accomplished), or within 48 months after the effective date of this AD, whichever is later. If the actions specified in McDonnell Douglas DC-8 Service Bulletin 57-30 have been accomplished before the effective date of the AD, the actions required by paragraph (a) of this AD must be accomplished within 48 months after the effective date of this AD.

(d) Accomplishment of the action(s) required by this AD constitutes compliance with the inspections required by paragraph A. of AD 90-16-05, amendment 39-6614, as it pertains to McDonnell Douglas DC-8 Service Bulletin 57-72, Revision 2, dated July 16, 1971; and McDonnell Douglas DC-8 Service Bulletin 57-34, Revision 3, dated December 29, 1970. Accomplishment of the actions required by this AD does not terminate the remaining requirements of AD 90-16-05 as it applies to other service bulletins; operators are required to continue to inspect and/or modify in accordance with the other service bulletins listed in that AD.

(e)(1) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOC) for this AD.

(2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make such findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(f) Unless otherwise specified in this AD, the actions must be done in accordance with McDonnell Douglas Service Bulletin DC8-57-072 R03, Revision 03, dated October 2, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.