2005-25-03: Point "D" splice fitting

2005-25-03 Boeing: Amendment 39-14396. Docket No. FAA-2005-23176; Directorate Identifier 2005-NM-220-AD. \n\nEffective Date \n\n\t(a) This AD becomes effective December 21, 2005. \n\nAffected ADs \n\n\t(b) None. \n\nApplicability \n\n\t(c) This AD applies to Boeing Model 737-600, -700, -700C, and - 800 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin (ASB) 737-53A1222, Revision 2, dated October 20, 2005. \n\nUnsafe Condition \n\n\t(d) This AD results from full-scale fuselage fatigue testing on the splice fitting that failed prior to the design objective on Boeing Model 737-800 series airplanes, and a report of a cracked splice fitting on an operational airplane. We are issuing this AD to prevent cracking of the existing fitting that may result in cracking through the skin and consequent decompression of the flight cabin. \n\nCompliance \n\n\t(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\nReplacing the Splice Fittings \n\n\t(f) Replace the splice fittings with new splice fittings in accordance with the Accomplishment Instructions of Boeing ASB 737- 53A1222, Revision 2, dated October 20, 2005, at the times specified in paragraph (f)(1) or (f)(2) of this AD, as applicable. Before further flight, do any related investigative actions by accomplishing all the applicable actions specified in the Accomplishment Instructions. \n\n\t(1) For airplanes that have accumulated less than 13,500 total flight cycles as of the effective date of this AD: Replace prior to the accumulation of 13,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. \n\n\t(2) For airplanes that have accumulated 13,500 or more total flight cycles as of the effective date of this AD: Replace at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. \n\n\t(i) Prior the accumulation of 18,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs first. \n\n\t(ii) Within 90 days after the effective date of this AD. \n\nCorrective Actions \n\n\t(g) If any cracking is found during any inspection required by this AD, prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or with a method approved in accordance with the procedures specified in paragraph (i) of this AD. \n\nAcceptable Method of Compliance \n\n\t(h) Replacing the splice fitting before the effective date of this AD in accordance with Boeing Service Bulletin 737-53-1222, dated June 6, 2002; or Boeing ASB 737-53A1222, Revision 1, dated January 30, 2003, is acceptable for compliance with the requirements of paragraph (f) of this AD. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(i)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD,if requested in accordance with the procedures found in 14 CFR 39.19. \n\n\t(2) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. \n\n\t(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, Seattle ACO, to make those 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. \n\nMaterial Incorporated by Reference \n\n\t(j) You must use Boeing Alert Service Bulletin 737-53A1222, Revision 2, dated October 20, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Directorof the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at 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 .