AD 2006-25-05 Airworthiness Directives; Boeing Model 777 Airplanes

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

This AD applies to Boeing Model 777-200, -300, and -300ER series airplanes; certificated in any category; as identified in Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 2006.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections (f) At the latest of the compliance times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, as applicable: Perform a detailed inspection of the fuselage skin under the wing-to-body fairings for corrosion or missing corrosion inhibiting compound (CIC) by doing all the applicable actions specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; or Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 2006. Repeat the inspection thereafter at intervals not to exceed 1,500 days until the requirements of paragraph (h) of this AD are accomplished. (1) Before the accumulation of 1,500 days since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. (2) Within 1,500 days after accomplishing the latest zonal or surveillance inspection before the effective date of this AD that is equivalent to the detailed inspection specified in paragraph (f) of this AD. (3) Within 750 days after the effective date of this AD. Corrective Action (g) If any corrosion or missing CIC is found during any inspection required by paragraph (f) of this AD: Before further flight, do a detailed inspection to determine the full extent of the corrosion; repair before further flight by doing all the applicable actions specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; or Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 2006. Where the service bulletin specifies to contact Boeing for repair instructions: Repair before further flight, according to a method approved in accordance with the procedures specified in paragraph (i) of this AD. Optional Terminating Action (h) Accomplishing the preventive modification of the fairing areas in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; or Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 2006; terminates the repetitive inspections required by paragraph (f) of this AD. After the effective date of this AD, only Revision 1 of the service bulletin may be used for accomplishing the preventive modification. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (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. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; or Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 2006; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents 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. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-20624 Filed 12-6-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wing-to-body fairings. We are issuing this AD to detect and correct corrosion, and prevent subsequent fatigue cracks, on the fuselage skin under the forward and aft wing-to-body fairings, which could result in rapid decompression of the airplane.