AD 2000-10-51 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 (L/N) 1 through 230 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 (g) 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 and correct cracking or fracturing of the tension bolts on the side load underwing fittings on the strut, which would eventually result in loss of the strut, accomplish the following: One-Time Inspection (a) At the applicable time specified in paragraph (a)(1) or (a)(2) of this AD, perform a one-time inspection of the tension bolts in the side load underwing fittings on both struts to determine whether tension bolts made of H-11 steel are installed, in accordance with Boeing Alert Service Bulletin 767-57A0074, dated May 17, 2000, or Revision 1, dated May 18, 2000. If the inspection shows conclusively that no H-11 steel bolt is installed, no further action is required by this AD. (1) For airplanes having L/N 1 through 162 inclusive: Inspect within 5 days after the effective date of this AD. (2) For airplanes having L/N 163 through 230 inclusive: Inspect within 10 days after the effective date of this AD. Repetitive Inspections (b) If any H-11 steel bolt is found during the inspection required by paragraph (a) of this AD, or if the type of bolt cannot be determined: Prior to further flight, perform an ultrasonic inspection to detect cracking or fracturing of the tension bolts in the side load underwing fittings on both struts, in accordance with Boeing Alert Service Bulletin 767-57A0074, dated May 17, 2000, or Revision 1, dated May 18, 2000. Repeat the inspection thereafter at intervals not to exceed 500 flight hours or 300 flight cycles, whichever occurs later. Replacement (c) If any cracked or fractured bolt is found during any inspection required by paragraph (b) of this AD, prior to further flight, replace both tension bolts in the affected side load underwing fitting with new, improved bolts, in accordance with Boeing Alert Service Bulletin 767-57A0074, dated May 17, 2000, or Revision 1, dated May 18, 2000. Additional Inspection Requirements (d) If both tension bolts in one side load underwing fitting are found cracked or fractured during any inspection required by paragraph (b) of this AD, prior to further flight, perform inspections to detect discrepancies of adjacent structure in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. For an inspection method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Reporting Requirement (e) For airplanes having L/N 163 through 230 inclusive on which an H-11 bolt is found installed, or on which the type of bolt cannot be determined during the inspection required by paragraph (a) of this AD: Within 48 hours after performing the inspection required by paragraph (b) of this AD, submit a report of findings to the Manager, Seattle ACO, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (425) 227-1181. The report must include the type of bolt found and the airplane serial number. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) 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. Optional Terminating Action (f) Replacement of all H-11 steel tension bolts in the side load underwing fittings on both struts with new, improved bolts, in accordance with Boeing Alert Service Bulletin 767-57A0074, dated May 17, 2000, or Revision 1, dated May 18, 2000, constitutes terminating action for this AD. Alternative Methods of Compliance (g) 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 2: 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 (h) 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 (i) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 767-57A0074, dated May 17, 2000, or Boeing Alert Service Bulletin 767-57A0074, Revision 1, dated May 18, 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 (j) This amendment becomes effective on June 19, 2000, to all persons except those persons to whom it was made immediately effective by emergency AD 2000-10-51, issued on May 18, 2000, which contained the requirements of this amendment. Issued in Renton, Washington, on June 1, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-14314 Filed 6-12-00; 8:45 am] BILLING CODE 4910-13-U