AD 2008-25-07 Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR Series 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 all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes, certificated in any category.

Comply with this AD within the compliance times specified, unless already done. Repetitive Inspections/Corrective Actions (f) For all airplanes: Except as provided by paragraph (h) of this AD, at the applicable times specified in paragraph 1.E. of Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008, inspect for cracks or fractures of the forward end attachment and the forward lower flange of the flap tracks of the trailing edge flaps, and do all applicable corrective actions, by doing all the actions specified in Parts 1 and 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008, except as provided by paragraph (i) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspection at the applicable time specified in paragraph 1.E. of Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008. Modification of Fail Safe Links of Main Carriage (g) For Groups 1, 2, and 3 airplanes: Within 24 months after the effective date of this AD, replace the fail-safe links, pins, and attachment hardware in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008. Exception to Compliance Times (h) Where Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008, specifies counting the compliance time from “* * * the date on this service bulletin,” this AD requires counting the compliance time from the effective date of this AD. Exception to Corrective Actions (i) If any fractured support fitting is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM-120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6443; fax (425) 917-6590; has the authority to approve AMOCs for this AD, if requested using 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 (k) You must use Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008; 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, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com ; Internet https://www.myboeingfleet.com . (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (4) You may also review copies of the service information 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 November 28, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-29073 Filed 12-10-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from a detailed structural analysis of the flap attach structural and fail-safe components accomplished as a result of a dynamic stability and control analysis, which could not demonstrate continued safe flight and landing of the airplane after the loss of a trailing edge flap. We are issuing this AD to detect and correct cracks or fractures of the primary structural and fail-safe load paths of the inboard and outboard trailing edge flaps, which could result in the loss of a flap during takeoff or landing, reducing flightcrew ability to maintain the safe flight and landing of the airplane.