AD 2005-10-17 Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes

Models named: 777-200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 777-200 and -300 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 777-57A0040, Revision 2, dated February 24, 2005.

Required as indicated, unless accomplished previously. To prevent fatigue cracks in the lower t-chord at the bolt holes common to the paddle fittings that could result in fractures of one or more of the t-chord segments, which could lead to detachment of the lower wing panel and consequent loss of the wing, accomplish the following: Modification of the Lower Paddle Fitting Bolt Holes/Fastener Replacement (a) At the later of the times specified in paragraphs (a)(1) and (a)(2) of this AD, modify the bolt holes of the lower side of the body splice t-chord common to the paddle fittings of the lower wing panel (includes performing a high frequency eddy current inspection of the fastener hole for cracks, repairing the hole if necessary, and replacing the fasteners with new inconel bolts) by accomplishing all of the actions specified in “Part 2—Preventative Modification” of the Work Instructions of Boeing Service Bulletin 777-57A0040, Revision 2, dated February 24, 2005, except as provided by paragraph (b) of this AD. Any applicable repair must be accomplished before further flight. (1) At the time specified in Figure 1 of the service bulletin. Where the service bulletin refers to compliance times as flight hours and flight cycles, this AD refers to the compliance times as total flight hours and total flight cycles. (2) Within 1,500 days or 8,000 flight cycles after the effective date of this AD, whichever is first. (b) If any crack is found during the modification required by paragraph (a) of this AD, and the service bulletin specifies to contact Boeing for additional instructions: Before further flight, repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing 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. Actions Accomplished According to Previous Issue of Service Bulletin (c) Actions accomplished before the effective date of this AD according to Boeing Service Bulletin 777-57A0040, Revision 1, dated July 10, 2003, are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (d) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Service Bulletin 777-57A0040, Revision 2, dated February 24, 2005. 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 the service information, go to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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. Effective Date (f) This amendment becomes effective on June 23, 2005. Issued in Renton, Washington, on May 9, 2005. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-9875 Filed 5-18-05; 8:45 am] BILLING CODE 4910-13-P