Airworthiness directives › 2008-09-20
AD 2008-09-20 Airworthiness Directives; Boeing Model 747-200F, 747-300, 747-400, and 747-400D Series Airplanes
Models named: 747-200F, 747-300, 747-400, 747-400D series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Boeing Model 747-200F, 747-300, 747-400, and 747-400D series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747-53A2685, Revision 1, dated March 13, 2008.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection and Applicable Related Investigative and Corrective Actions (f) At the applicable compliance time and repeat intervals listed in Tables 1 and 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2685, Revision 1, dated March 13, 2008; except where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD: Do the inspection and applicable related investigative and corrective actions by accomplishing all the applicable actions specified in the Accomplishment Instructions of the service bulletin, except as provided by paragraph (g) of this AD. Repair of Cracks (g) If any crack is found during any inspection required by this AD, and Boeing Service Bulletin 747-53A2685, Revision 1, dated March 13, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Credit for Actions Done Using the Previous Service Information (h) Actions accomplished before the effective date of this AD in accordance with Boeing Alert Service Bulletin 747-53A2685, dated May 31, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD. 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) 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. Material Incorporated by Reference (j) You must use Boeing Service Bulletin 747-53A2685, Revision 1, dated March 13, 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, 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 April 23, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-9894 Filed 5-7-08; 8:45 am] BILLING CODE 4910-13-P
Unsafe condition
This AD results from two reports of cracks found in the exterior skin and internal doubler adjacent to the shear clip at the stub frame to auxiliary sill joint at stringer 30 (left and right sides), body station (BS) 488. In addition, on one of the airplanes, seven fasteners were missing from the shear clip on the left side of the airplane. The cause of the missing fasteners has been attributed to a manufacturing process error. We are issuing this AD to ensure fasteners in the shear clip of the stub frame to auxiliary sill joints (left and right sides) are installed. Missing fasteners could result in cracks in the adjacent exterior skin and internal doubler, which can propagate and result in loss of structural integrity and sudden in-flight decompression of the airplane.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1