AD 2000-12-17 Airworthiness Directives; Boeing Model 767 Series Airplanes

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

Model 767 series airplanes, line numbers 1 through 663 inclusive, 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 (h) 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 detect fatigue cracks in the pitch load fittings of the wing front spar, which could result in reduced structural integrity of the strut, accomplish the following: (a) Accomplish the requirements of either paragraph (b) or (c) of this AD at the later of the times specified in paragraphs (a)(1) and (a)(2) of this AD. (1) Prior to the initial inspection threshold specified in Figure 1, Table 1.1 of Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. (2) Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever occurs first. Note 2: Inspections and repairs accomplished prior to the effective date of this AD in accordance with Boeing Service Bulletin 767-57-0053, dated June 27, 1996; or Revision 1, dated October 31, 1996; are considered acceptable for compliance with the applicable action specified in this amendment. Option 1: Ultrasonic and Eddy Current Inspections (b) Perform ultrasonic and eddy current inspections to detect cracks of the pitch load fittings of the wing front spar, in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. (1) If no crack is detected, repeat the inspections thereafter at the interval specified in Table 1.2 of Figure 1 of the service bulletin. (2) If any crack is detected, prior to further flight, remove the upper link and the pitch load fitting bushings, and accomplish both paragraphs (b)(2)(i) and (b)(2)(ii) of this AD. (i) Perform a detailed visual inspection of the inner and outer face pad-up areas of the pitch load fittings to detect damage or corrosion and to determine if the pad-up areas are parallel, in accordance with the service bulletin. Except as provided by paragraph (f) of this AD, if any damage, corrosion, or non-parallelism is detected, prior to further flight, rework the inner or outer face of the pitch load fitting where damage or corrosion was detected, and make pad-up areas parallel, as applicable, in accordance with the service bulletin. (ii) Accomplish paragraph (d) of this AD. Note 3: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Option 2: High Frequency Eddy Current and Detailed Visual Inspections (c) Remove the upper link and accomplish the requirements of paragraphs (c)(1) and (c)(2) of this AD, in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. (1) Perform a high frequency eddy current inspection or a dye penetrant inspection to detect cracking of the pitch load fittings of the wing front spar. (2) Perform a detailed visual inspection of the inner and outer face pad-up areas of the pitch load fittings to detect damage or corrosion and to determine if the pad-up areas are parallel. Except as provided by paragraph (f) of this AD, if any damage, corrosion, or non-parallelism is detected, prior to further flight, rework the inner or outer face of the pitch load fitting where damage or corrosion was detected, and make pad-up areas parallel, as applicable, in accordance with the service bulletin. Rework (d) For airplanes on which any cracking is detected during any inspection required by paragraph (b) of this AD, or on which the requirements of paragraph (c) of this AD have been accomplished: Prior to further flight, accomplish paragraph (d)(1) or (d)(2) of this AD, as applicable, in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999; and accomplish paragraph (e) of this AD. (1) For airplanes inspected in accordance with paragraph (c) of this AD and on which no cracking was detected: Make an insurance cut of the pitch load fitting lug. (2) For airplanes on which any cracking was detected during any inspection required by paragraph (b) or (c) of this AD: Except as provided by paragraph (f) of this AD, rework the lugs of the pitch load fittings of the wing front spar. Bushing Installation (e) For airplanes on which the requirements specified in paragraph (d) of this AD have been accomplished: Prior to further flight, install new bushings in the pitch load fittings of the wing front spar as specified in paragraph (e)(1) or (e)(2) of this AD, in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. (1) Option 1: Install new bushings using the high interference fit method, and repeat the inspections required by paragraph (b) or (c) of this AD at the intervals specified in Table 1.3 of Figure 1. of the service bulletin. (2) Option 2: Install new bushings using the FORCEMATE method, and repeat the inspections required by paragraph (b) or (c) of this AD at the interval specified in Table 1.4 of Figure 1. of the service bulletin. Repair (f) If any damage is detected that is outside the limits specified in Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999, and the service bulletin specifies to contact Boeing for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate; or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, as required by this paragraph, the approval letter must specifically reference this AD. Optional Terminating Action (g) Accomplishment of the actions specified in paragraphs (g)(1) and (g)(2) of this AD constitutes terminating action for the actions required by this AD. (1) Modify the nacelle strut and wing structure in accordance with Boeing Service Bulletin 767-54-0080, dated October 7, 1999 (for Model 767 series airplanes powered by Pratt & Whitney engines); Boeing Service Bulletin 767-54-0081, dated July 29, 1999 (for Model 767 series airplanes powered by General Electric engines); or Boeing Service Bulletin 767-54-0082, dated October 28, 1999 (for Model 767 series airplanes powered by Rolls-Royce engines); as applicable. (2) Accomplish the lug bore inspections and insurance cut of the pitch load fitting in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. Note 4: The FAA is considering separate rulemaking actions to mandate accomplishment of Boeing Service Bulletins 767-54-0080, 767-54-0081, and 767-54-0082. Actions described in Boeing Service Bulletin 767-57-0053, Revision 2 (or previous issues of that service bulletin), as required by this AD will be specified as an integral part of the actions required to accomplish these service bulletins. Alternative Methods of Compliance (h) 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 5: 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 (i) Special flight permits may be issued in accordance with §§ 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 (j) Except as provided in paragraphs (f) and (g)(1) of this AD, the actions shall be done in accordance with Boeing Service Bulletin 767-57-0053, Revision 2, dated September 23, 1999. 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 (k) This amendment becomes effective on July 24, 2000. Issued in Renton, Washington, on June 9, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-15183 Filed 6-16-00; 8:45 am] BILLING CODE 4910-13-U