2003-16-10: Compressor turbine and power turbine blades

2003-16-10 Pratt & Whitney Canada: Amendment 39-13263. Docket No. 2003-NE-25-AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 29, 2003. Affected ADs (b) None. Applicability (c) This AD is applicable to Pratt & Whitney Canada (PWC) PW206A and PW206E turboshaft engines. These engines are installed on, but not limited to MD Helicopters Inc. Model MD-900 helicopters. Unsafe Condition (d) This AD is prompted by reports of engine shutdowns and emergency landings due to severe vibration and drops in engine torque, and an increase in internal engine temperature, triggering in-flight engine fire warnings. We are issuing this AD to prevent turbine blade axial shift, leading to high levels of vibration, loss of engine torque, in-flight engine shutdown, and possible uncontained engine failure. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Sequence of Borescope Inspections (f) Perform an initial sequence of borescope inspections of compressor turbine blades and power turbine blades for blade axial shift within the turbine disks. Use paragraph 3. of Accomplishment Instructions of PWC Alert Service Bulletin (ASB) No. PW200-72- A28242, Revision 1, dated October 2, 2002, for the borescope inspection. Do the inspections at the following times: (1) Within 25 flight hours accumulated or 30 days after the effective date of this AD, whichever occurs earlier. (2) After 30 flight hours, but before 50 flight hours accumulated since inspection of paragraph (f)(1) of this AD. (3) After 80 flight hours, but before 100 flight hours accumulated since inspection of paragraph (f)(1) of this AD. (4) After 180 flight hours, but before 200 flight hours accumulated since inspection of paragraph (f)(1) of this AD. Repetitive Borescope Inspections (g) Thereafter, perform repetitive borescope inspections at intervals of not less than 280 nor more than 300 flight hours since- last-inspection. Use paragraph 3. of Accomplishment Instructions of PWC ASB No. PW200-72-A28242, Revision 1, dated October 2, 2002, for the borescope inspections. Disposition (h) If any blade shift is found, remove engine from service before further flight and perform rivet and rotor air seal replacements, as specified in paragraphs (j)(1) and (j)(2) of this AD, to return the engine to service. (i) If blade shift is suspected, confirm the blade shift with the appropriate engine manufacturer service representative before further flight. Remove engine from service if shift is confirmed, and perform rivet and rotor air seal replacements, as specified in paragraphs (j)(1) and (j)(2) of this AD, to return the engine to service. Terminating Action (j) At the next engine shop visit for any reason, or at the next engine overhaul, whichever occurs first, but before December 31, 2009, do the following: (1) Replace the compressor turbine blade retaining rivets, the No. 3 bearing rotor air seal, and the No. 4 bearing front rotor air seal. Use paragraph 3. Accomplishment Instructions of Service Bulletin (SB) No. PW200-72-28069, Revision 5, dated February 10, 2003. (2) Replace the power turbine blade retaining rivets. Use paragraph 3. Accomplishment Instructions of SB No. PW200-72-28239, Revision 2, dated February 10, 2003. Previous Credit (k) Previous credit is allowed for terminating action in paragraph (j)(1) and (j)(2) of this AD that was done in accordance with Accomplishment Instructions of SB No. PW200-72-28069, Revision 4, dated December 27, 2000, and Accomplishment Instructions of SB No. PW200-72-28239, dated September 5, 2002, or Revision 1, dated December 5, 2002, before the effective date of this AD. (l) Completing the actions in paragraphs (j)(1) and (j)(2) of this AD terminates all inspection requirements of this AD. Alternative Methods of Compliance (AMOCs) (m) You must request AMOCs as specified in 14 CFR part 39.19. All AMOCs must be approved by the Manager, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299. Material Incorporated by Reference (n) You must use the following Pratt & Whitney Canada Service Bulletins and Alert Service Bulletin to perform the inspections and replacement actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Pratt & Whitney Canada, 1000 Marie- Victorin, Longueuil, Quebec, Canada J4G1A1. You may review copies at Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-NE-25-AD, 12 New England Executive Park, Burlington, MA 01803-5299; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. Table 1 follows: Table 1.--Incorporation by Reference Service bulletin Page No.(s) Revision Date PW200-72-A28242 Total Pages--7 PW200-72-28069 Total Pages--17 PW200-72-28239 Total Pages--20 All All All 1 5 2 October 2, 2002 February 10, 2003 February 10, 2003 Related Information (o) Transport Canada issued airworthiness directive CF-2003-06, dated February 4, 2003, which pertains to the subject of this AD, in order to assure the airworthiness of these PWC PW206A and PW206E turboshaft engines in Canada.