AD 2010-26-10 Airworthiness Directives; The Boeing Company Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes

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

This AD applies to The Boeing Company Model 747-200C, -200F, -400, -400D, and -400F series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2006-05-09, With Revised Service Information Initial Inspections and Related Investigative and Corrective Actions (g) For airplanes identified in Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005: At the applicable time specified in Table 1 of this AD, do an external surface high frequency eddy current (HFEC), external low frequency eddy current (LFEC), and internal LFEC inspection, as applicable, for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, and any applicable related investigative and corrective actions by doing all of the actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005; Revision 1, dated October 30, 2008; or Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. Do any applicable related investigative and corrective actions before further flight. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, may be used. Table 1—Initial Compliance Time For airplanes on which Structural Significant Items (SSIs) F-25G, F-25H, and F-25I— Inspect— (1) Have not been inspected in accordance with paragraph (i) of AD 2004-07-22 R1, Amendment 39-15326, using the HFEC method Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after April 13, 2006 (the effective date of AD 2006-05-09), whichever occurs later. (2) Have been inspected in accordance with paragraph (i) of AD 2004-07-22 R1, using the HFEC method Within 3,000 flight cycles after the most recent supplemental structural inspection document (SSID) inspection of each applicable structural significant item (as given in Boeing Document D6-35022, “SSID for Model 747 Airplanes,” Revision G, dated December 2000), or within 1,000 flight cycles after April 13, 2006, whichever occurs later. Repetitive Inspections (h) Repeat the applicable inspections required by paragraph (g) of this AD thereafter at intervals not to exceed those specified in paragraph 1.E., “Compliance,” (including the note) of Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005; Revision 1, dated October 30, 2008; or Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, may be used. New Requirements of This AD Repetitive Inspections/Investigative and Corrective Actions (i) For all airplanes: Do an external HFEC inspection of the lap joints in Sections 41, 42, and 46 for cracks, by doing all the actions, including all applicable related investigative and corrective actions, specified in the Accomplishment Instructions of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. Do the inspection at the applicable time specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010; except as required by paragraph (m) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the times specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. Accomplishment of the inspections required by this paragraph terminates the inspections required by paragraphs (g) and (h) of this AD. (j) For areas on which a lap joint repair was installed and the repair doubler is greater than or equal to 40 inches long: Do initial and repetitive internal HFEC inspections for cracks by doing all the actions, including all applicable corrective actions, specified in the Accomplishment Instructions of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, except as required by paragraph (l) of this AD. Do the inspections and corrective actions at the times specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, except as required by paragraph (m) of this AD. Terminating Action (k) Modify the applicable lap joints in Sections 41 and 42 by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, at the time specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010; except as required by paragraphs (l) and (m) of this AD. Accomplishing this modification terminates the repetitive inspections of the skin lap joints in Sections 41 and 42 required by paragraphs (i) and (j) of this AD for the length of lap joint that is modified. Exceptions to Service Bulletin Procedures (l) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, 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 (o) of this AD. (m) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Credit for Actions Done Using Previous Service Information (n) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 747-53A2499, Revision 1, dated October 30, 2008, are acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (o)(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: Nicholas Han, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6449; fax (425) 917-6590. Information may be e-mailed 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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) or other person 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. (4) AMOCs approved previously in accordance with AD 2006-05-09 are approved as alternative methods of compliance with the corresponding requirements of this AD. Material Incorporated by Reference (p) You must use Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005; or Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010; 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 747-53A2499, Revision 2, dated August 12, 2010, 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 747-53A2499, dated August 11, 2005, on April 13, 2006 (71 FR 12122, March 9, 2006). (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. (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 13, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-31992 Filed 12-27-10; 8:45 am] BILLING CODE 4910-13-P

This AD results from a structural review of affected skin lap joints for widespread fatigue damage. The Federal Aviation Administration is issuing this AD to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization of the airplane.