Airworthiness Directive · Amendment 39-11770 · Boeing Model 767 Series Airplanes
Boeing Model 767 Series Airplanes
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.
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-10-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 767 series airplanes by individual notices. This AD requires a one-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary. This action is prompted by a report that two fractured bolts and one cracked bolt were found in the side load underwing fittings. The actions specified by this AD are intended 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.
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:
(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.
(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.
(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.
(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.
(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.
(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.
