AD 2001-08-23 Airworthiness Directives; Boeing Model 767-200 Series Airplanes

Model series airplanes, as listed in Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To find and fix cracking of the outboard pitch load fittings of the wing front spar, which could lead to loss of the upper link load path and result in separation of the strut and engine from the airplane, accomplish the following: Initial and Repetitive Inspections (a) Within 30 days after the effective date of this AD, perform a high frequency eddy current (HFEC) inspection for cracking of the outboard pitch load fitting of the wing front spar, on the left and right sides of the airplane, according to Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000. If no cracking is found, repeat the inspection at least every 3,000 flight cycles or 18 months, whichever occurs first, until paragraph (c) of this AD is done. Note 2: Inspections done prior to the effective date of this AD, in accordance with Boeing Service Bulletin 767-57A0070, dated March 2, 2000, as revised by Information Notice 767-57A0070 IN 01, dated March 23, 2000, are considered acceptable for compliance with paragraph (a) of this AD. Corrective Action (b) If any cracking is found during any inspection per paragraph (a) of this AD, prior to further flight, do paragraph (b)(1) or (b)(2) of this AD. (1) Rework the cracked outboard pitch load fitting according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings. For a rework method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. (2) Replace the cracked outboard pitch load fitting with a new, improved fitting (including removing the existing fittings, performing an HFEC inspection for damage of fastener holes, repairing damaged fastener holes—if necessary, and installing new fittings of improved design), according to Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000. Such replacement terminates the repetitive inspections required by paragraph (a) of this AD for the replaced fitting. Note 3: Boeing Service Bulletin 767-57A0070, Revision 1, refers to Boeing Service Bulletin 767-57-0053 as an additional source of service information for accomplishment of the replacement of the outboard pitch load fitting on Model 767-200 series airplanes. Optional Terminating Action (c) Replacement of the outboard pitch load fitting of the wing front spar with a new, improved fitting, according to Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000, terminates the repetitive inspections required by paragraph (a) of this AD for the replaced fitting. Spares (d) As of the effective date of this AD, no one may install on any airplane an outboard pitch load fitting that has a part number listed in the “Existing Part Number” column of Paragraph 2.E. of Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000. Alternative Methods of Compliance (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (g) Except as provided by paragraph (b)(1) of this AD, the actions shall be done in accordance with Boeing Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (h) This amendment becomes effective on May 14, 2001. Issued in Renton, Washington, on April 18, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-10176 Filed 4-26-01; 8:45 am] BILLING CODE 4910-13-P