AD 2009-19-05 Airworthiness Directives; Boeing Model 747 Airplanes

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

This AD applies to Boeing Model 747 airplanes, certificated in any category, as specified in paragraph (c)(1) or (c)(2) of this AD, as applicable. (1) Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes, as identified in Boeing Alert Service Bulletin 747-53A2732, dated August 28, 2008. (2) Boeing Model 747-400, 747-400D, and 747-400F series airplanes, as identified in Boeing Alert Service Bulletin 747-53A2753, dated August 28, 2008.

Comply with this AD within the compliance times specified, unless already done. Repetitive Inspections and Corrective Actions (g) At the applicable compliance time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2732 or 747-53A2753, both dated August 28, 2008, as applicable, do the detailed inspection for cracking of the fuselage frames in section 41, and do all applicable corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2732 or 747-53A2753, both dated August 28, 2008, as applicable; except as provided by paragraphs (h) and (i) of this AD. Repeat the inspection at intervals not to exceed those specified in paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2732 or 747-53A2753, both dated August 28, 2008, as applicable. If any crack is found, do all corrective actions before further flight. Note 1: As specified in Boeing Alert Service Bulletins 747-53A2732 and 747-53A2753, both dated August 28, 2008, an optional special detailed inspection behind the P14 and P15 electrical terminal panels using the borescope may be done. (h) Where Boeing Alert Service Bulletins 747-53A2732 and 747-53A2753, both dated August 28, 2008, recommend an initial inspection threshold relative to the date on Boeing Alert Service Bulletins 747-53A2732 and 747-53A2753, both dated August 28, 2008; this AD requires the initial inspection threshold relative to the effective date of this AD. (i) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletins 747-53A2732 and 747-53A2753, both dated August 28, 2008, specify to contact Boeing for appropriate action: Before further flight, repair the cracking 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 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to 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. 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), as appropriate, 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 (k) You must use Boeing Alert Service Bulletin 747-53A2732 dated August 28, 2008; or Boeing Alert Service Bulletin 747-53A2753, dated August 28, 2008; as applicable; 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 September 1, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-21922 Filed 9-21-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracking in fuselage frames made of 2024 aluminum alloy that were installed during previous modification of the frames in section 41 and during production. We are issuing this AD to detect and correct frame cracks, which could result in cracking of the adjacent fuselage skin and consequent rapid decompression of the airplane.