AD 2006-24-04 Airworthiness Directives; Boeing Model 767 Airplanes

Models named: 767-200, -300, -300F, -400ER series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category.

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) Before the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever is later: Do the detailed and high frequency eddy current (HFEC) inspections for cracking as specified in Parts 1, 2, 3, and 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006; and do all corrective actions before further flight; by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006, except as provided by paragraph (g) of this AD. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles. Accomplishing the corrective action for the inspections specified in Part 1, 2, 3, or 4 of the service bulletin, as applicable, terminates the repetitive inspections for that area only. Exception to Service Bulletin (g) If any cracking is found in the skin or in any structure other than the forward outer chord or horizontal inner chord, during any inspection required by this AD, and Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006, specifies 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. Optional Terminating Action (h) If no cracking is found during the most recent detailed and HFEC inspections for a specified area as required by paragraph (f) of this AD: Modification of a specified area according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, terminates the repetitive inspections required by paragraph (f) of this AD for that area only. For a forward outer chord, one approved method is accomplishment of the actions in Steps 4.A through 4.C and 4.G through 4.P of Repair 9, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 Structural Repair Manual (SRM), Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable. For a horizontal inner chord, one approved method is accomplishment of the actions in Steps 4.A, 4.B, and 4.F through 4.P of Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable. Credit for Previously Accomplished Repairs (i) Repair of a forward outer chord done before the effective date of this AD in accordance with Repair 9, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable; is acceptable for compliance with the requirements of paragraph (f) of this AD for that area only. Repair of a horizontal inner chord before the effective date of this AD in accordance with Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable; is acceptable for compliance with the requirements of paragraph (f) of this AD for that area only. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle 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. Material Incorporated by Reference (k) You must use Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006, 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 November 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-19797 Filed 11-24-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from fatigue cracks found in the forward outer chord and horizontal inner chord at station (STA) 1809.5. We are issuing this AD to detect and correct cracking in the bulkhead structure at STA 1809.5, which could result in failure of the bulkhead structure for carrying the flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane.