AD 2006-10-08 Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes

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

This AD applies to Boeing Model 767-200, -300, and -300F series airplanes; certificated in any category; identified in Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004.

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 2002-01-15 Initial Inspection (f) For airplanes having line numbers 1 through 819 inclusive, on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Within 90 days after February 14, 2002 (the effective date of AD 2002-01-15), or within 36 months after date of manufacture of the airplane, whichever is later, do detailed inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies ( e.g. , lubrication passage blocked, fractured bearing, loose or damaged joint); per Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004. After the effective date of this AD, only Revision 2 of the service bulletin may be used. Repetitive Inspections/Corrective Action With New Compliance Times (g) For airplanes having line numbers 1 through 819 inclusive, on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Do the actions required by paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable, at the time specified, per the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004. After the effective date of this AD, only Revision 2 of the service bulletin may be used. (1) If the lubrication passage is not blocked and no fractured bearing or loose or damaged joint is found, do paragraph (h) of this AD. (2) If the lubrication passage is blocked and no fractured bearing or loose or damaged joint is found, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 60 days, and within 24 months after the most recent inspection required by paragraph (a) or (b)(1) of AD 2002-01-15, or paragraph (f) of this AD, as applicable, do the actions required by paragraph (g)(3) of this AD. (3) If any fractured bearing or loose or damaged joint is found, before further flight, do the corrective action (including removal of the link assembly, inspection for damage, and replacement with a new assembly if damaged), as specified in Part 2 of the Accomplishment Instructions of the service bulletin. New Requirements of This AD (h) For airplanes having line numbers 1 through 819 inclusive, on which the lubrication passage has not been found blocked and no fractured bearing or loose or damaged joint has been found, and on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Within 24 months after the most recent inspection in accordance with paragraph (a) or (b)(1) of AD 2002-01-15, or paragraph (f) of this AD, as applicable, remove the link assembly, perform a detailed inspection of the link assembly for damage, and reinstall the undamaged link or replace it with a new link assembly that has been inspected and found to be free of damage or other discrepancy, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004. Detailed Inspection of Bearing Ball and Outer Race (i) For all airplanes: Remove the link assembly, and perform a detailed inspection for cracking of the bearing ball, and for severe wear of the outer race of the bearing, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004. Do this action at the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. Then, repeat this action at intervals not to exceed 72 months. If any cracking or severe wear is found during any inspection required by this paragraph: Before further flight, do the corrective action in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004, or do paragraph (j) of this AD. (1) For airplanes identified in the service bulletin as being in Group 1: Within 72 months after doing Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004, or within 18 months after the effective date of this AD, whichever is later. (2) For airplanes identified in the service bulletin as being in Group 2: Within 72 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness; or within 18 months after the effective date of this AD; whichever is later. Optional Terminating Action (j) For all airplanes: Replacing the existing link assemblies of the trailing edge flaps with new, improved or modified assemblies that contain new bearings, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27-0196, dated April 21, 2005, ends the repetitive removal/inspections required by paragraph (g), (h), and (i) of this AD, as applicable. Actions Accomplished Previously (k) Inspections and corrective actions done before the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 1, dated June 6, 2002, are acceptable for compliance with the corresponding actions required by this AD. No Reporting Requirement (l) Although Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004, specifies to submit certain information to the manufacturer, this AD does not require that action. Alternative Methods of Compliance (AMOCs) (m)(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 14 CFR 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) AMOCs approved previously according to AD 2002-01-15 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (n) You must use Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating action, you must use Boeing Service Bulletin 767-27-0196, dated April 21, 2005. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004; and Boeing Service Bulletin 767-27-0196, dated April 21, 2005; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On February 14, 2002 (67 FR 4328, January 30, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000. (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 May 4, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-4423 Filed 5-12-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from additional reports indicating fractured bearings of the link assembly joint in the inboard and outboard flaps of the trailing edge. We are issuing this AD to prevent failure of the bearings in the link assembly joint, which could result in separation of the inboard or outboard flap and consequent loss of control of the airplane.