AD 2008-05-03 Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, 747SP, and 747SR Series Airplanes Powered by General Electric (GE) CF6-45/50 and Pratt & Whitney (P&W) JT9D-70, JT9D-3 or JT9D-7 Series Engines

This AD applies to Model 747-100, -100B, -100B SUD,—200B,—200C, -200F, -300, 747SP, and 747SR series airplanes; certificated in any category; powered by General Electric (GE) CF6-45/50 and Pratt & Whitney (P&W) JT9D-70, JT9D-3, or JT9D-7 series engines; as identified in Boeing Alert Service Bulletin 747-54A2202, 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. Compliance Times (f) Do all applicable actions specified in paragraphs (g), (h), and (i) of this AD at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006, except that where paragraph 1.E. of the service bulletin specifies starting the compliance time from “* * * the release date of Revision 1 of this service bulletin,” this AD requires starting the compliance time from the effective date of this AD. Initial and Repetitive Inspections/Corrective Actions (g) For all airplanes: Perform detailed and high frequency eddy current inspections for cracks and broken fasteners of the rear engine mount bulkhead of the inboard and outboard nacelle struts, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006. Repeat the applicable inspection and actions thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of the service bulletin. Accomplishing the applicable repair (Repair 1, 2, 3, or 4, or repair per the Boeing 747 Structural Repair Manual, Section 54-11-03 or 54-12-03) terminates the requirements in this paragraph for that nacelle strut only. Modification (h) For Groups 1, 2, and 5 airplanes: Do the applicable modification (Repair 2, 3, or 4) of the rear engine mount bulkhead of the inboard and outboard nacelle struts, and all the applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006. Accomplishing this modification terminates the requirements in paragraph (g) of this AD for that nacelle strut only. Post-Modification Inspection/Corrective Actions (i) For Groups 1, 2, and 5 airplanes on which the applicable corrective actions (Repair 1, 2, 3, or 4) required by paragraph (g) of this AD have been accomplished; or the applicable modification (Repair 2, 3, or 4) required by paragraph (h) of this AD has been accomplished: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006, or within 6 months after the effective date of this AD, whichever occurs later, perform detailed and high frequency eddy current inspections for cracks and broken fasteners of the rear engine mount bulkhead of the inboard and outboard nacelle struts, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006. Repeat the applicable inspections and actions thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of the service bulletin. Exception to Service Bulletin (j) If any crack or any broken fastener is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006, specifies to contact Boeing for appropriate action: Before further flight, repair the discrepancy using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Alternative Methods of Compliance (AMOCs) (k)(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) 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, 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 (l) You must use Boeing Alert Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006, 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, P.O. Box 3707, Seattle, Washington 98124-2207. (3) You may review copies of the service information incorporated by reference 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 . Issued in Renton, Washington, on February 20, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-3749 Filed 3-3-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of web and frame cracks and sheared attachment fasteners on the inboard and outboard nacelle strut. We are issuing this AD to detect and correct cracks and broken fasteners of the inboard and outboard nacelle struts, which could result in possible loss of the rear engine mount bulkhead load path and consequent separation of the engine from the airplane.