AD 97-08-51 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, 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 (e) 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 separation of the outboard trailing edge flap from the airplane due to failed bolts of the attach fitting, accomplish the following: (a) Perform an inspection to check the bolt torque, bolt length, and type of all bolts of both hinge fittings on the left-and right- hand outboard trailing edge flaps, in accordance with Boeing Alert Service Bulletin 767-27A0151, Revision 1, dated April 2, 1997. Perform these inspections at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. (1) For airplanes that have accumulated 15,000 total flight cycles or more, or 37,500 total flight hours or more, as of the effective date of this AD: Perform the inspections within 15 days after the effective date of this AD. (2) For all other airplanes: Perform the inspections at the later of the times specified [[Page 24017]] in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) Prior to the accumulation of 10,000 total flight cycles, or 25,000 total flight hours, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (b) If any bolt of the hinge fittings of the left-and right-hand outboard trailing edge flaps is below the torque check threshold specified in Boeing Alert Service Bulletin 767-27A0151, Revision 1, dated April 2, 1997: Prior to further flight, accomplish the action specified in paragraph (b)(1) or (b)(2) of this AD in accordance with the alert service bulletin. (1) Perform a dye penetrant inspection of all the bolts of the hinge fitting to detect any cracking or discrepancy. (i) If no cracking or discrepancy is detected, reinstall the bolt using new nuts and washers. (ii) If any cracking or discrepancy is detected, replace the cracked or discrepant bolt with a new or serviceable bolt. (2) Replace all of the bolts of both hinge fittings with new or serviceable bolts. (c) If the length or type of any bolt of the hinge fittings of the left-and right-hand outboard trailing edge flaps is outside the specifications of Boeing Alert Service Bulletin 767-27A0151, Revision 1, dated April 2, 1997: Prior to further flight, replace the bolt with a new or serviceable bolt in accordance with the alert service bulletin. (d) Within 10 days after accomplishing the actions required by this AD, submit a report describing any cracking, damage, or any torque check of any bolt of either hinge fitting that was below the threshold of the torque check specified by this AD, to the Manager, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (206) 227-1181. 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. (e) 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, Transport Airplane Directorate. 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. (f) Special flight permits may be issued in accordance with 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. (g) The actions shall be done in accordance with Boeing Alert Service Bulletin 767-27A0151, Revision 1, dated April 2, 1997. 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, ransport 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. (h) This amendment becomes effective on May 7, 1997, to all persons except those persons to whom it was made immediately effective by telegraphic AD T97-08-51, issued on April 2, 1997, which contained the requirements of this amendment. Issued in Renton, Washington, on April 25, 1997. Neil D. Schalekamp, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-11334 Filed 5-1-97; 8:45 am] BILLING CODE 4910-13-U