2002-21-15: Second stage turbine stator inner seal support

2002-21-15 Honeywell International Inc.: Amendment 39-12922. Docket No. 99-NE-53-AD. Applicability: This airworthiness directive (AD) is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division, Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A series turboprop and TSE331-3U series turboshaft engines with second stage turbine stator assemblies, part numbers (P/N's) 894528-1, -2, -3, -5, -6, -10, and -11. These engines are installed on, but not limited to Ayres S-2R series; Beech 18 and 45 series and model JRB-6, 3N, 3NM, 3TM, and B100 airplanes; Construcciones Aeronauticas, S.A. (CASA) C-212; De Havilland DH104 series 7AXC (Dove); Dornier 228 series; Fairchild SA226 series (Swearingen Merlin and Metro series); Grumman American G-164 series; Mitsubishi MU-2 and MU-2B series; Pilatus PC-6 series (Fairchild Porter and Peacemaker); Prop-Jets, Inc. Model 400; Rockwell Commander S2-R; Schweizer G-164 series; Shorts Brothers and Harland, Ltd. SC7 (Skyvan); and Twin Commander 680 and 690 series (Jetprop Commander) airplanes; and Sikorsky S-55 series (Helitec Corp. S55T) helicopters. Note 1: This 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 (c) 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: Compliance with this AD is required as indicated, unless already done. To reduce fatigue damage of the second stage turbine stator inner seal support, rotating knife seal, and the first and second stage turbine wheels which may result in an uncontained rotor failure and damage to the aircraft, do the following: (a) Replace second stage turbine stator assemblies, P/N's 894528-1, -2, -3, -5, -6, -10, and -11, with a new or reworked second stage turbine stator assembly at the next removal of the second stage turbine stator assembly from the engine or at the next turbine section inspection, but do not exceed 3,100 engine operating hours since last turbine section inspection. Information for replacing second stage turbine stator assemblies is available in Honeywell International Inc. Alert Service Bulletin (ASB) TPE331- A72-2082 dated May 16, 2001. Information for reworking second stage turbine stator assemblies is available in Honeywell International Inc. SB TPE331-72-2085RWK dated May 16, 2001.(b) After the effective date of this AD, do not install any second stage turbine stator assembly P/N's 894528-1, -2, -3, -5, -6, -10, and -11. Alternative Methods of Compliance (c) 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, Los Angles Aircraft Certification Office (LAACO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, LAACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the LAACO. Special Flight Permits (d) 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 aircraft to a location where the requirements of this AD can be done. Effective Date (e) This amendment becomes effective on November 26, 2002.