AD 2006-20-02 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 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; as identified in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005.

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 96-23-02 Actions for Groups 1 Through 10, and 17 Through 36, as Specified in Boeing Alert Service Bulletin 747-53A2409, Revision 5 (f) For airplanes identified as Groups 1 through 10 inclusive, and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005: Do the inspections in paragraph (f)(1) of this AD; and do the corrective action in paragraph (f)(2) of this AD as applicable. Except as provided by paragraph (i) of this AD, do all actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996; or Revision 5, dated August 18, 2005. After the effective date of this AD, only Revision 5 of the service bulletin may be used. (1) At the applicable time in Figures 1, 2, 18, and 20 of Revision 5 of the service bulletin, do initial and repetitive inspections of Areas 1 and 4, as applicable, to detect disbonding, corrosion, and cracking of the skin; except any inspection using Method 1 or 2 must not be accomplished before the latest of the following, as applicable: Before the accumulation of 2,000 total flight cycles; 2,000 flight cycles since modification to the stretched upper deck (SUD) configuration; or 2,000 flight cycles since skin panel replacement in accordance with AD 90-26-10, amendment 39-6836. If inspection Method 1 or 2 is used and no disbonded doubler is found, no further action is required by this AD. (2) If any corrosion or cracking is found during any inspection required by paragraph (f)(1) of this AD: Before further flight, except as provided by paragraph (i) of this AD, repair and do any applicable related investigative actions in accordance with the Accomplishment Instructions of Revision 5 of the service bulletin. New Requirements of This AD Actions for Groups 11 Through 16 as Specified in Boeing Alert Service Bulletin 747-53A2409, Revision 5 (Airplanes Added to the Applicability of This AD) (g) For airplanes identified as Groups 11 through 16 inclusive in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005: Do the inspections in paragraph (g)(1) of this AD; and do the corrective action in paragraph (g)(2) of this AD as applicable. Except as provided by paragraph (i) of this AD, do all actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005. (1) At the applicable time in Figures 18 and 20 of the service bulletin, do initial inspections of Area 4 and repetitive inspections, as applicable, to detect disbonding, corrosion, and cracking of the skin, as applicable; except any inspection using Method 2 must not be accomplished before the latest of the following, as applicable: Before the accumulation of 2,000 total flight cycles; 2,000 flight cycles since modification to the SUD configuration; or 2,000 flight cycles since skin panel replacement in accordance with AD 90-26-10. If inspection Method 2 is used and no disbonded doubler is found, no further action is required by this AD. (2) If any corrosion, disbonding, or cracking is found during any inspection required by paragraph (g)(1) of this AD, before further flight: Repair and do any applicable related investigative actions in accordance with the Accomplishment Instructions of the service bulletin. Actions for Airplanes With Alodine-Coated Rivets for Groups 1 Through 10, and 17 Through 36 as Specified in Boeing Alert Service Bulletin 747-53A2409, Revision 5 (h) For airplanes identified as Groups 1 through 10 inclusive, and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005: Do the inspections in paragraph (h)(1) of this AD; and do the corrective action in paragraph (h)(2) of this AD if necessary. Except as provided by paragraph (i) of this AD, do all actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005. (1) At the applicable time in Figures 21 and 22 of the service bulletin: Do initial and repetitive inspections of Areas 1 and 4, as applicable, to detect cracking of the skin. (2) If any cracking is found during any inspection required by paragraph (h)(1) of this AD, before further flight: Repair in accordance with the Accomplishment Instructions of the service bulletin. Exceptions (i) Do all actions in accordance with the applicable service bulletin except as provided by paragraphs (i)(1), (i)(2), (i)(3), (i)(4), and (i)(5) of this AD. (1) For the action in paragraph (f)(1) of this AD: Where Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996; and Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005; specify a compliance time after the issuance of any revision of the service bulletin, this paragraph requires compliance before the specified compliance time after November 27, 1996 (the effective date of AD 96-23-02). (2) For the actions in paragraphs (g)(1) and (h)(1) of this AD: Where Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005, specifies a compliance time after the issuance or receipt of any revision of the service bulletin, this paragraph requires compliance before the specified compliance time after the effective date of this AD. (3) For any repair or any inspection where Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005, specifies to contact the manufacturer for further instructions: Before further flight, repair or inspect using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (4) If corrosion is found during any inspection required by this AD, before further flight: Repair in accordance with an FAA-approved method. (5) Where Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005, specifies that it is not necessary to count flight cycles at 2.0 psi or less cabin differential pressure, this AD does not allow for that adjustment factor. Credit for Actions Accomplished Previously (j) Actions done before the effective date of this AD in accordance with the service bulletins specified in Table 1 of this AD are acceptable for compliance with the corresponding requirements of paragraphs (f) and (g) of this AD. Table 1.—Credit Service Bulletins Service bulletin Revision level Date Boeing Service Bulletin 747-53A2409 1 May 29, 1997. Boeing Service Bulletin 747-53A2409 2 August 6, 1998. Boeing Service Bulletin 747-53A2409 3 October 22, 1998. Boeing Service Bulletin 747-53A2409 4 February 17, 2000. Alternative Methods of Compliance (AMOCs) (k)(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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 96-23-02, are approved as AMOCs for the corresponding provisions of paragraph (f) of this AD, except AMOCs for terminating action based upon inspection results using a sliding probe low frequency eddy current (LFEC), sliding probe high frequency eddy current (HFEC), or mid frequency surface eddy current (MFEC) inspection methods; and provided that any alternative method for future inspections did not incorporate a sliding probe LFEC, sliding probe HFEC, or MFEC inspection methods. (4) 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 Alert Service Bulletin 747-53A2409, dated September 26, 1996; or Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On November 27, 1996 (61 FR 57994, November 12, 1996), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 14, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-8227 Filed 9-27-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of cracking discovered in a skin lap joint that was previously inspected using the eddy current method. We are issuing this AD to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.