AD 2006-01-07 Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP Series Airplanes

Models named: 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, 747SP series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes, certificated in any category; without a stretched upper deck or stretched upper deck modification; as identified in Boeing Special Attention Service Bulletin 747-53-2502, dated April 21, 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. Repetitive Inspections and Corrective Actions (f) At the applicable time in paragraph (f)(1) or (f)(2) of this AD: Do detailed and high-frequency eddy current inspections for cracking of each affected tension tie and of the surrounding structure. If any cracking is found: Before further flight, do all applicable corrective and related investigative actions. Do all actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2502, dated April 21, 2005. Where the special attention service bulletin specifies to contact Boeing for repair instructions: Before further flight, repair the area using a method approved in accordance with paragraph (g) of this AD. (1) For airplanes identified in the special attention service bulletin as Groups 1, 3, and 6 airplanes: Do the first inspections before the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later; and repeat the inspections thereafter at intervals not to exceed 4,000 flight cycles. (2) For airplanes identified in the special attention service bulletin as Group 2, 4, and 5 airplanes: Do the first inspections before the accumulation of 17,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later; and repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. Alternative Methods of Compliance (AMOCs) (g)(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) 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. (4) Certain actions required by paragraph (f) of this AD are AMOCs for certain requirements in the ADs identified in paragraphs (g)(4)(i), (g)(4)(ii), and (g)(4)(iii) of this AD. All provisions of the referenced ADs, including applicable post-modification inspection thresholds, remain fully applicable and must be complied with. (i) Repairs of the aft tension tie channels done in accordance with this AD are AMOCs for the repair requirements of paragraph A. of AD 84-19-01, amendment 39-4913, and paragraphs (a)(2) and (b)(2) of AD 94-13-06, amendment 39-8946. (ii) The inspection requirements of this AD are AMOCs for the post-modification inspection requirements of paragraph B. of AD 84-19-01, and paragraph (b) of AD 94-13-06. (iii) The inspection requirements of this AD are AMOCs for the inspections of structural significant item (SSI) F-19A of Boeing Supplemental Structural Inspection Document D6-35022, Revision G, dated December 2000, as required by paragraphs (c) and (d) of AD 2004-07-22, amendment 39-13566. Material Incorporated by Reference (h) You must use Boeing Special Attention Service Bulletin 747-53-2502, dated April 21, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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 December 30, 2005. Linda Navarro, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-183 Filed 1-11-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a crack in the tension tie at the body station 820 frame connection, and cracks found on the Boeing 747SR fatigue-test airplane in both the tension ties and frames at the tension tie to frame connections at body stations 800, 820, and 840. We are issuing this AD to find and fix cracks in the tension ties, which could lead to cracks in the skin and body frame and result in rapid in-flight depressurization of the airplane.