AD 2001-24-01 Airworthiness Directives; Boeing Model 767 Series Airplanes Powered by Pratt & Whitney Model PW4000 Series Engines

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 821, equipped with Pratt & Whitney PW4000 series engines; 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 (f) 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 prevent the potential for dual wire faults from grounded, separated, or shorted wires, which could result in inadvertent takeoff thrust overboost, in-flight loss of thrust, or engine shutdown, accomplish the following: Detailed Visual Inspection (a) Prior to the accumulation of 10,000 hours' time-in-service or within 180 days after the effective date of this AD, whichever occurs later: Do a one-time detailed visual inspection of the wire bundles located in the aft section of the strut forward fairing panel of both engine struts to detect chafing damage, per Boeing Service Bulletin 767-73A0049, Revision 3, dated December 20, 2000, or Revision 4, dated April 5, 2001. If any chafing damage of any wire bundle is found, do the actions required by paragraphs (a)(1) and (a)(2) of this AD at the times specified in those paragraphs. Note 2: Inspections accomplished prior to the effective date of this AD per Boeing Service Bulletin 767-73A0049, Revision 2, dated April 27, 2000, or per Boeing Standard Wiring Practices Manual D6-73A0049, Subject 20-10-13 or 20-30-12, are considered acceptable for compliance with the applicable action specified in 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.” Corrective Action (1) Before further flight, repair the wire bundle per the service bulletin, except as provided by paragraph (a)(2) of this AD. (2) Replace all spliced wires with new wires per the service bulletin, concurrently with accomplishment of the terminating action required by paragraph (b) of this AD. Terminating Action (b) Within 6,000 flight hours or 18 months after the effective date of this AD, whichever occurs later, do the actions specified in paragraphs (b)(1) and (b)(2) of this AD per the Accomplishment Instructions of Boeing Service Bulletin 767-73-0051, dated December 20, 2000. (1) Do a detailed visual inspection of the wire bundles to detect chafing damage; if any damaged wires are found, replace the wires that require a splice repair with new wires concurrently with accomplishment of the terminating action specified in paragraph (b)(2) of this AD. (2) Replace the existing support bracket of the wire bundle with a new bridge bracket, support bracket, and wire bundle clamps. Accomplishment of this replacement terminates the requirements of this AD. (c) Any of the Type 2 tapes listed in Boeing Standard Wiring Practices Manual D6-54446, Subject 20-00-11, dated May 1, 2000, are acceptable alternatives to the TFE-2X Teflon wrap specified in Figure 1 of Boeing Service Bulletin 767-73A0049, Revision 3, dated December 20, 2000, or Revision 4, dated April 5, 2001. Report Inspection Results (d) Within 10 days after accomplishing the actions required by paragraph (a) or (b) of this AD: Report inspection results, as described in Boeing Service Bulletin 767-73A0049, Revision 3, dated December 20, 2000, or Revision 4, dated April 5, 2001, to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMP) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ) and have been assigned OMB Control Number 2120-0056. Spares (e) As of the effective date of this AD, no person shall install on any airplane any support bracket located in the aft section of the strut forward fairing panel of either engine strut, as identified in the “Existing Part Number” column of Paragraph 2.E. of Boeing Service Bulletin 767-73-0051, dated December 20, 2000. Alternative Methods of Compliance (f) 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 Aircraft Certification Office (ACO), FAA. 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 Permit (g) Special flight permits may be issued per 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 (h) Except as provided by paragraph (c) of this AD, the actions shall be done in accordance with Boeing Service Bulletin 767-73A0049, Revision 3, dated December 20, 2000, or Boeing Service Bulletin 767-73A0049, Revision 4, dated April 5, 2001; and Boeing Service Bulletin 767-73-0051, dated December 20, 2000; as applicable. 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 Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 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 (i) This amendment becomes effective on January 4, 2002. Issued in Renton, Washington, on November 16, 2001. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-29323 Filed 11-29-01; 8:45 am] BILLING CODE 4910-13-U