AD 96-19-01

96-19-01 Allison: Amendment 39-9749. Docket 95-ANE-72. Applicability: Allison Model 250-B15G,-B17F, -B17F/1, -B17F/2, -C20, -C20B, -C20F, -C20J, -C20S, -C20W, -R, -C20R/1, -C20R/2, -C20R/4, -C28B, -C28C, -C30, -C30P, -C30M, and -C30G turbine engines, with Superior Air Parts, Inc. Parts Manufacture Approval (PMA) bearings, Part Number (P/N) A6871505 and P/N A23007152, installed. These engines are installed on but not limited to the following aircraft: Aerospace Technologies of Australia PTY Ltd. N-22 and N-24; Agusta S.p.A A109 series, SF600 series; Beech Aircraft Corp. A36 and T34 (Tradewind Turbines conversion); Bell Helicopter Textron Model 47 (Soloy Conversion), OH58 series, 206 series, 230, 430; Cessna 206 and 207 (Soloy Conversions); Enstrom Helicopter Corp. TH28, 480; Eurocopter Deutschland GmbH BO105 series; Eurocopter France AS355 series; Flugzeugwerke Altenrheim AG (FFA) AS202 series; Hiller Aviation UH12 series (Soloy Conversions); Maule Aerospace Technology Corp. MX-7 series; McDonnell Douglas Helicopter Co. OH6 series, 500 series, MD500 series, MD520N series, MD530 series; Partenavia Costruzioni Aeronautiche S.p.A P68 series; Pilatus Britten-Norman Ltd. BN-2T; and Sikorsky Aircraft Division S76 series. Note: This airworthiness directive (AD) applies to each engine 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 engines 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.Compliance: Required as indicated, unless accomplished previously. To prevent bearing failure due to bearing separator instability, which can result in subsequent turbine and engine failure, accomplish the following: (a) For engines with No. 5 bearings, Superior P/N A6871505, installed, accomplish the following: (1) Within 20 days after the effective date of this AD, perform an initial visual inspection of all engine filters for metal particles in accordance with Superior Turbine Service Bulletin (SB) No. T95-SB001, Revision A, dated September 29, 1995. If any engine filter contains metal particles that exceed the return to service criteria described in that SB, prior to further flight, remove the No. 5 bearing, Superior P/N A6871505, and replace with a serviceable No. 5 bearing, Allison P/N 6871505. (2) Thereafter, for engines with No. 5 bearing, Superior P/N A6871505, installed, perform visual inspections of all engine filters for metal particles in accordance withSuperior Turbine SB No. T95-SB002, dated September 29, 1995, and, if necessary, replace with serviceable parts, at intervals not to exceed the following: (i) For engines with 300 hours or less TIS since overhaul, or TSN if never overhauled, perform inspections at intervals not to exceed 25 hours TIS since last inspection. (ii) For engines with more than 300 hours TIS since new or overhaul, whichever is lesser, perform inspections at intervals not to exceed 100 hours TIS since last inspection. (b) For engines with No. 8 bearings, Superior P/N A23007152, installed, accomplish the following: (1) Within 20 days after the effective date of this AD, perform an initial visual inspection of all engine filters for metal particles in accordance with Superior Turbine SB No. T95-SB002, Revision A, dated September 29, 1995. If any engine filter contains metal particles that exceed the return to service criteria described in that SB, prior to further flight, remove the No. 8 bearing, Superior P/N A23007152, and replace with a serviceable No. 8 bearing, Allison P/N 23031478. (2) Thereafter, for engines with No. 8 bearing, Superior P/N A23007152, installed, perform visual inspections of all engine filters for metal particles in accordance with Superior Turbine SB No. T95-SB002, dated September 29, 1995, and, if necessary, replace with serviceable parts, at intervals not to exceed the following: (i) For engines with 300 hours or less TIS since overhaul, or TSN if never overhauled, perform inspections at intervals not to exceed 25 hours TIS since last inspection. (ii) For engines with more than 300 hours TIS since new or overhaul, whichever is lesser, perform inspections at intervals not to exceed 100 hours TIS since last inspection. (c) At the next engine overhaul, or repair or maintenance when disassembly permits replacement of the bearing, after the effective date of this AD, whichever occurs first, remove the No. 5 bearing, Superior P/N A6871505, and replace with a serviceable No. 5 bearing, Allison P/N 6871505; and remove the No. 8 bearing, Superior P/N A23007152, and replace with a serviceable No. 8 bearing, Allison P/N 23031478. (d) Installation of serviceable bearings in accordance with paragraph (c) of this AD, constitutes terminating action to the inspection requirements of this AD. (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, Special Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Special Certification Office. Note: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Special Certification Office. (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 aircraft to a location where the requirements of this AD can be accomplished. (g) The actions required by this AD shall be done in accordance with the following Superior Turbine service documents:

Document No. Pages Revision Date SB No. T95-SB001 1-2 A September 29, 1995 Total pages: 2.

SB No. T95-SB002 1-2 A September 29, 1995 Total pages: 2.

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 Superior Air Parts, Inc., 14280 Gillis Rd., Dallas, TX 75244-3792; telephone (800) 487-4884, fax (214) 490-8471. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on September 26, 1996.