AD 2004-09-14 Airworthiness Directives; Boeing Model 767 Series Airplanes Powered by General Electric or Pratt & Whitney Engines

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

Model 767 series airplanes, as listed in Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002; certificated in any category.

Required as indicated, unless accomplished previously. To prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine, accomplish the following: Requirements of AD 2001-07-05 Repetitive Inspections (a) Except as provided by paragraph (b) of this AD, before the accumulation of 10,000 total flight cycles, or within 600 flight cycles after May 15, 2001 (the effective date of AD 2001-07-05, amendment 39-12170 (66 FR 18523, April 10, 2001), whichever occurs later: Accomplish the inspections required by paragraph (a)(1) or (a)(2) of this AD, as applicable. (1) Perform a detailed inspection of the four aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut to detect cracking, in accordance with Part 1, “Detailed Inspection,” of the Accomplishment Instructions of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000. If no cracking is detected, repeat the inspection thereafter at the applicable intervals specified in Table 1, “Reinspection Intervals for Part 1—Detailed Inspection” included in Figure 1 of the service bulletin. Note 1: For the purposes of this AD, a detailed 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.” (2) Perform a high frequency eddy current inspection of the four aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut to detect discrepancies (cracking, incorrect fastener hole diameter), in accordance with Part 2, “High Frequency Eddy Current (HFEC) Inspection,” of the Accomplishment Instructions of the service bulletin. Accomplish the requirements specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable; and repeat the inspection thereafter at the applicable intervals specified in Table 2, “Reinspection Intervals for Part 2—HFEC Inspection” included in Figure 1 of the service bulletin. (i) If no cracking is detected and the fastener hole diameter is less than or equal to 0.5322 inch, before further flight, rework the hole in accordance with Part 3 of the Accomplishment Instructions of the service bulletin. (ii) If no cracking is detected and the fastener hole diameter is greater than 0.5322 inch, before further flight, accomplish the requirements specified in either paragraph (c)(1) or (c)(2) of this AD. (b) For airplanes on which the two aft-most fasteners have been inspected in accordance with Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000, prior to May 15, 2001: Perform the initial inspection of the four aft-most fasteners in accordance with paragraph (a) of this AD before the accumulation of 10,000 total flight cycles, or within 1,500 flight cycles after May 15, 2001, whichever occurs later. Corrective Actions (c) If any cracking is detected after accomplishment of any inspection required by paragraph (a) of this AD, before further flight, accomplish the requirements specified in either paragraph (c)(1) or (c)(2) of this AD. (1) Accomplish the terminating action specified in Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000; or Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002. Accomplishment of this paragraph terminates the requirements of this AD. (2) Replace the midspar fitting of the strut with a serviceable part, or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Repeat the applicable inspection thereafter at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. (d) If any discrepancies (cracking, incorrect fastener hole diameter) are detected during any inspection required by paragraph (a) of this AD, for which the service bulletin specifies that the manufacturer may be contacted for disposition of those repair conditions: Before further flight, accomplish the corrective actions (including fastener hole rework and/or midspar fitting replacement) in accordance with a method approved by the Manager, Seattle ACO; or in accordance with 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 method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. New Requirements of This AD Additional Inspections (e) Prior to the accumulation of 10,000 total flight cycles, or within 600 flight cycles after the effective date of this AD, whichever occurs later: Perform the inspections specified in paragraph (a)(1) or (a)(2) of this AD, as applicable, on all eight aft-most fastener holes or the four forward fastener holes in the group of eight aft-most fastener holes not inspected per paragraph (a)(1), (a)(2), or (b) of this AD. The inspection must be done per the Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002. Accomplishment of the applicable inspection on all eight aft-most fastener holes constitutes terminating action for the repetitive inspection requirements of paragraphs (a)(1), (a)(2), and (b) of this AD. (f) If no cracking or discrepancy is detected during any detailed inspection required by paragraph (e) of this AD, repeat the inspections of all eight aft-most fastener holes thereafter at the applicable intervals specified in Table 1 of this AD. (g) If no cracking or discrepancy is detected during any HFEC inspection required by paragraph (e) of this AD: Perform the follow-on actions specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable, per the Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002; and repeat the inspections of all eight aft-most fastener holes thereafter at the applicable intervals specified in Table 1 of this AD. Table 1.—Repetitive Inspection Intervals for All Eight Aft-Most Fastener Holes If— Repetitive intervals— (1) All eight aft-most fastener holes were inspected per paragraph (e) of this AD: At the applicable intervals specified in Table 1, “Reinspection Intervals for Part 1—Detailed Inspection,” or Table 2, “Reinspection Intervals for Part 2—HFEC Inspection,” as applicable. Both tables are included in Figure 1 of the service bulletin. (2) Only the four forward fastener holes in the group of eighnt aft-most fastener holes were inspected per paragraph (e) of this AD: At the next scheduled repetitive inspection required by paragraph (a)(1) or (a)(2) of this AD, as applicable. Thereafter at the applicable intervals specified in Table 1, “Reinspection Intervals for Part 1—Detailed Inspection,” or Table 2, “Reinspection Intervals for Part 2—HFEC Inspection,” as applicable. Both tables are included in Figure 1 of the service bulletin. Corrective Actions (h) If any cracking or discrepancy is detected during any inspection required by paragraphs (e), (f), or (g) of this AD, before further flight: Accomplish the corrective actions described in paragraph (c) of this AD, per the Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002, except as provided in paragraph (d) of this AD. Service Bulletin Revisions (i) Accomplishment of the terminating action in paragraph (c)(1) of this AD, per the original release of Boeing Service Bulletin 767-54A0101, dated September 23, 1999; or Revision 2 of Boeing Service Bulletin 767-54A0101, dated January 10, 2002; is acceptable for compliance with the requirements of this AD. As of the effective date of this AD, only Revision 3 of Boeing Service Bulletin 767-54A0101, dated September 5, 2002, may be used for accomplishment of the terminating action in paragraph (c)(1) of this AD. Inspections Accomplished Per Previous Issue of Service Bulletin (j) Inspections required by paragraphs (a) and (b) of this AD that are accomplished before the effective date of this AD per Revision 2 of Boeing Service Bulletin 767-54A0101, dated January 10, 2002; or Revision 3 of Boeing Service Bulletin 767-54A0101, dated September 5, 2002; are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (k) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (l) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000; and Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002; as applicable. (1) The incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002, is approved by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000, was approved previously by the Director of the Federal Register as of May 15, 2001 (66 FR 18523, April 10, 2001). (3) Copies may be obtained from Boeing Commercial Airplanes, 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Effective Date (m) This amendment becomes effective on June 9, 2004. Issued in Renton, Washington, on April 22, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-9761 Filed 5-4-04; 8:45 am] BILLING CODE 4910-13-P