AD 2005-19-09 Airworthiness Directives; Boeing Model 747 Airplanes

Models named: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Service Bulletin 747-54A2218, Revision 1, dated February 24, 2005.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections and Other Specified Actions (f) At the times specified in Figure 1 of Boeing Service Bulletin 747-54A2218, Revision 1, dated February 24, 2005, except as provided by paragraph (g) of this AD: Do the various inspections and other specified actions in the figure to detect discrepancies of the DSBs, underwing midspar fittings, and associated parts, by doing all of the actions specified in Parts 1, 2, and 4; and the applicable corrective actions specified in Parts 3, 5, 6, and 7; of the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Repeat the inspections and other specified actions thereafter at the intervals specified in Figure 1 of the service bulletin. Accomplishment of any terminating action specified in Figure 1 of the service bulletin terminates the inspections and other specified actions for the affected strut. (g) Where Boeing Service Bulletin 747-54A2218, Revision 1, dated February 24, 2005, recommends an initial compliance threshold of “within 24 months after the original issue date on this service bulletin” for Parts 1 and 4 of the service bulletin, and of “within 72 months after the original issue date on this service bulletin” for Part 2 of the service bulletin, this AD requires an initial compliance threshold of “within 24 months after the effective date of this AD” for Parts 1 and 4 of the service bulletin and of “within 72 months after the effective date of this AD” for Part 2 of the service bulletin. Corrective Actions (h) If any damage or crack is found during any inspection or corrective action required by this AD, before further flight, repair in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-54A2218, Revision 1, dated February 24, 2005; except, where the service bulletin specifies to contact Boeing, before further flight, repair according to 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 (i) Inspections and other specified and corrective actions accomplished before the effective date of this AD in accordance with Boeing Alert Service Bulletin 747-54A2218, dated June 17, 2004, are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (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, 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 (k) You must use Boeing Service Bulletin 747-54A2218, Revision 1, dated February 24, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC. To review copies of the service information, go 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 . Issued in Renton, Washington, on September 8, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-18313 Filed 9-15-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of corroded, migrated, and rotated bearings for the dual side braces (DSB) in the inboard and outboard struts, a report of a fractured retainer for the eccentric bushing for one of the side links of a DSB, and reports of wear and damage to the underwing midspar fitting on the outboard strut. We are issuing this AD to prevent the loss of a DSB or underwing midspar fitting load path, which could result in the transfer of loads and motion to other areas of a strut, and possible separation of a strut and engine from the airplane during flight.