AD 99-11-14 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 1 through 609 inclusive; certificated in any category; having 4330M steel fuse pins installed in the outboard support of the main landing gear (MLG) beam. 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 detect and correct corrosion and cracking of the fuse pins in the outboard support of the MLG beam, which could result in the failure of a fuse pin and, consequently, lead to collapse of the MLG, accomplish the following: Detailed Visual Inspection (a) Within 4 years of service since the MLG was new, or within 18 months after the effective date of this AD, whichever occurs later, perform detailed visual inspections of the fuse pins of the MLG outboard support beam to detect corrosion or chrome plating cracks on the fuse pin, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0054, Revision 2, dated April 18, 1996, or Boeing Service Bulletin 767-57A0054, Revision 3, dated October 30, 1997. Note 2: 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 Actions (b) If any corrosion or plating crack of a fuse pin is found during any inspection required by paragraph (a) of this AD, prior to further flight, accomplish either paragraph (b)(1) or (b)(2) of this AD. (1) Install a new or serviceable 4330M steel fuse pin in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0054, Revision 2, dated April 18, 1996, or Boeing Service Bulletin 767-57A0054, Revision 3, dated October 30, 1997. Repeat the detailed visual inspections required by paragraph (a) of this AD thereafter at intervals not to exceed 48 months. Or (2) Install a newer-type 15-5PH CRES fuse pin in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0054, Revision 2, dated April 18, 1996, or Boeing Service Bulletin 767-57A0054, Revision 3, dated October 30, 1997. Accomplishment of this installation constitutes terminating action for the repetitive inspection requirements of paragraphs (a), (b)(1), and (c)(1) of this AD. (c) If no corrosion or plating crack is found on the fuse pins, prior to further flight, accomplish the requirements of either paragraph (c)(1) or (c)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767- 57A0054, Revision 2, dated April 18, 1998, or Boeing Service Bulletin 767-57A0054, Revision 3, dated October 30, 1997. (1) Install the existing 4330M steel fuse pins in accordance with the Accomplishment Instructions of the service bulletin. Repeat the detailed visual inspections required by paragraph (a) of this AD thereafter at intervals not to exceed 48 months. Or (2) Install newer-type 15-5PH CRES fuse pins in accordance with the Accomplishment Instructions of the service bulletin. Accomplishment of this installation constitutes terminating action for the repetitive inspection requirements of paragraphs (a), (b)(1), and (c)(1) of this AD. [[Page 29781]] Alternative Methods of Compliance (d) 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 3: 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 (e) Special flight permits may be issued in accordance with Secs. 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 (f) The actions shall be done in accordance with Boeing Alert Service Bulletin 767-57A0054, Revision 2, dated April 18, 1996; or Boeing Service Bulletin 767-57A0054, Revision 3, dated October 30, 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, 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. (g) This amendment becomes effective on July 8, 1999. Issued in Renton, Washington, on May 21, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-13878 Filed 6-2-99; 8:45 am] BILLING CODE 4910-13-U