AD 2010-01-02 Airworthiness Directives; The Boeing Company Model 747-100B SUD, -200B, -300, -400, and -400D Series Airplanes

Models named: 747-100B SUD, -200B, -300, -400, -400D series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to The Boeing Company Model 747-100B SUD, -200B, -300, -400, and -400D series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2005-15-08 Inspection for Certain Airplanes Subject to AD 2005-15-08 With New Service Bulletin (g) For airplanes identified in Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003, except airplanes identified in paragraph (j) of this AD, do a detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, in accordance with Part 1 of the Accomplishment Instructions in Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. Do the inspections at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles until the requirements of paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. After the effective date of this AD, use only Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. (1) For airplanes with 19,000 total flight cycles or less as of August 30, 2005 (the effective date of AD 2005-15-08): Prior to the accumulation of 8,000 total flight cycles, or within 2,000 flight cycles after August 30, 2005, whichever is later, not to exceed 20,000 total flight cycles. (2) For airplanes with more than 19,000 total flight cycles as of August 30, 2005: Within 1,000 flight cycles after August 30, 2005. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” New Requirements of This AD Inspection: Variable Number RS699 (h) For Model 747 airplane variable number RS699, do a detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, in accordance with Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009, at the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Before the accumulation of 8,000 total flight cycles. (2) Within 2,000 flight cycles after the effective date of this AD. (i) For Model 747 airplane variable number RS699, repeat the inspection specified in paragraph (h) of this AD thereafter at intervals not to exceed 3,000 flight cycles until the actions specified in paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. Inspection: Group 4 Airplanes (j) For Group 4 airplanes as identified in Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009, do a detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, within 1,000 flight cycles after the effective date of this AD. Do the actions in accordance with Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles until the actions specified in paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. Repair (k) If cracking is found during any inspection required by this AD: Before further flight, repair the affected stringer in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. After the effective date of this AD, use only Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. Accomplishing the repair terminates the repetitive inspections required by this AD for that repaired stringer location only. Optional Terminating Action (l) Installing new frame clips and new doublers, and repairing as applicable, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009; terminates the repetitive inspections required by this AD for that modified stringer only. After the effective date of this AD, use only Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle 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, Seattle Aircraft Certification Office (ACO), FAA, 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. (4) AMOCs approved previously in accordance with AD 2005-15-08, are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (n) You must use Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003; and Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009; 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 Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2484, dated June 26, 2003, on August 30, 2005 (70 FR 43020, July 26, 2005). (3) 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 . (4) 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. (5) 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 December 17, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-30970 Filed 1-19-10; 8:45 am] BILLING CODE 4910-13-P

This AD results from findings of cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations. We are issuing this AD to detect and correct fatigue cracking in the specified fuselage stringers, which, if left undetected, could result in fuselage skin cracking that reduces the structural integrity of the skin panel, and consequent rapid depressurization of the airplane.