AD 2009-12-08 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 all 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.

Comply with this AD within the compliance times specified, unless already done. Inspection/Related Investigative and Corrective Actions (g) Except as provided by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2703, Revision 1, dated September 16, 2008, do a surface high frequency eddy current (HFEC) inspection for cracks in the left- and right-side Stringer 11 longeron exposed surfaces and edges between Station 2598 and 2607 adjacent to the horizontal stabilizer pivot bulkhead; and do all applicable related investigative and corrective actions before further flight, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2703, Revision 1, dated September 16, 2008, except as provided by paragraph (i) of this AD. Exception to Compliance Times (h) Where Boeing Service Bulletin 747-53A2703, Revision 1, dated September 16, 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 crack is found during any inspection required by this AD, and Boeing Service Bulletin 747-53A2703, Revision 1, dated September 16, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Actions Accomplished According to Previous Issue of Service Bulletin (j) Inspections, related investigative actions, and corrective actions accomplished before the effective date of this AD according to Boeing Alert Service Bulletin 747-53A2703, dated February 14, 2008, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; fax (425) 917-6590 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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 Service Bulletin 747-53A2703, Revision 1, dated September 16, 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 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 that is incorporated by reference 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 June 2, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-13406 Filed 6-10-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a crack found in the right-side Stringer 11 longeron horizontal flange, adjacent to the horizontal stabilizer pivot bulkhead, during a routine maintenance inspection. We are issuing this AD to detect and correct fatigue cracking of the longeron, which can propagate and cause damage to the adjacent horizontal stabilizer pivot bulkhead. This damage could result in loss of structural integrity and consequent inability of the bulkhead to carry flight loads, which could adversely affect controllability of the airplane.