AD 2008-26-07 Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series Airplanes

This AD applies to all McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71, DC-8-72, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes; certificated in any category.

Comply with this AD within the compliance times specified, unless already done. Repetitive Inspections and Corrective Actions (f) At the times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008 (“the service bulletin”), except as provided by paragraph (g) of this AD: Do the applicable inspections for fatigue cracking of the lower skin and stringers at stations Xw=408 and Xw=−408, and do all applicable corrective actions, by accomplishing all applicable actions specified in the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Do all corrective actions before further flight, in accordance with the service bulletin. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E. of the service bulletin. (g) Where Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008 (“the service bulletin”), specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (h) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, ATTN: Dara Albouyeh, Aerospace Engineer, Airframe Branch, ANM-120L, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5222; fax (562) 627-5210; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) 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 Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (4) Accomplishing the requirements of this AD is an acceptable AMOC with the requirements of paragraph (b) of AD 93-01-15, amendment 39-8469, for those areas of principal structural element 57.08.037/038. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, 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 Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024); telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com ; Internet https://www.myboeingfleet.com . (3) You may review copies of the service information that is incorporated by reference 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 or 425-227-1152. (4) You may also review copies of the service information 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 December 12, 2008. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-30265 Filed 12-23-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks in the skins and stringers at the end fasteners common to the stringer end fittings at stations Xw=408 and Xw=−408 wing splice joints. We are issuing this AD to detect and correct fatigue cracking in the skins and stringers at the end fasteners common to the stringer end fittings at certain station and wing splice joints, which could result in wing structure that might not sustain limit load, and consequent loss of structural integrity of the wing.