2008-02-19: High pressure (HP) turbine rotor assemblies

2008-02-19 Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.): Amendment 39-15349. Docket No. FAA- 2007-27891; Directorate Identifier 2007-NE-14-AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 6, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. (Honeywell) TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, - 20R, -20AR, -20BR, -40, -40AR, -40R, and -60 series turbofan engines with certain high pressure (HP) turbine rotor discs part numbers and serial numbers. These engines are installed on, but not limited to, the following airplanes: Avions Marcel Dassault Mystere-Falcon 10 and 50 Series Cessna Model 650; Citations III, VI, and VII Dassault-Aviation 20, 50, 50EX, 900, MF900, and 900EX (900DX) Series Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra, Astra SPX, Gulfstream 100 Series Israel Aircraft Industries (IAI) 1124 Series (Westwind 1124) Learjet 31, 35, 36, 45 (or Learjet 40), and 55 Series Lockheed-Georgia 3329-25 Series (731 Jetstar, Jetstar II) Raytheon Corporate Jets (formerly British Aerospace) Hawker 800 and 850 Series Sabreliner NA-265-65 (Sabreliner 65) Unsafe Condition (d) This AD results from the manufacturer's report that some HP turbine rotor discs received improperly machined radii in the root of the forward and aft curvic teeth during manufacture. We are issuing this AD to prevent uncontained failure of the HP turbine rotor assembly, which could result in damage to the airplane. 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. TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, and -5R Series Turbofan Engines (f) For TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, - 5BR, and -5R series turbofan engines,remove HP turbine rotor assemblies from service containing HP turbine rotor discs, part number (P/N) 3075772-1, having any serial number (SN) in Table 1 of Honeywell Service Bulletin (SB) No. TFE731-72-3720, dated July 5, 2006. Use the following drawdown schedule: (1) For HP turbine discs with 4,200 cycles-since-new (CSN) or more on the effective date of this AD, remove HP turbine rotor assemblies within 100 cycles-in-service (CIS) after the effective date of this AD. (2) For HP turbine discs with fewer than 4,200 CSN on the effective date of this AD, remove HP turbine rotor assemblies at the next access to the HP turbine rotor discs, but not to exceed 4,300 CSN. TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, and -60 Series Turbofan Engines (g) For TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, and -60 series turbofan engines, remove HP turbine rotor assemblies from service containing HP turbine rotor discs, P/N 3060841-1, having any SN in Table 1 of Honeywell Alert SB No. TFE731-A72-5185, dated July 5, 2006. Use the following drawdown schedule: (1) For HP turbine discs with 3,200 CSN or more on the effective date of this AD, remove HP turbine rotor assemblies within 100 CIS after the effective date of this AD. (2) For HP turbine discs with fewer than 3,200 CSN on the effective date of this AD, remove HP turbine rotor assemblies at the next access to the turbine rotor discs, but not to exceed 3,300 CSN. For All Engines (h) HP turbine rotor discs removed per paragraphs (f) and (g) of this AD must pass a curvic root radius inspection performed by Honeywell Engines, Systems and Services, Phoenix, Arizona, Certificate Repair Station No. ZN3R030M, before the discs are eligible for reinstallation in an engine. (i) For the purposes of this AD, access to the HP turbine rotor discs is defined as the removal of the HP turbine rotor assembly from the engine. Alternative Methods of Compliance (j) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) Contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: joseph.costa@faa.gov; telephone: (562) 627-5246; fax: (562) 627- 5210, for more information about this AD. (l) For more information regarding the engine manufacturer's accomplishment instructions or material information, refer to Honeywell Alert SB No. TFE731-A72-5185, dated July 5, 2006, and SB No. TFE731-72-3720, dated July 5, 2006. (m) Also, for technical support regarding the curvic root dimensional inspection criteria, contact the Technical Operations Center: telephone: (800) 601-3099 (U.S.) or (602) 365-3099 (International) and press option 9; e-mail: AeroTechSupport@Honeywell.com; or fax: (602) 365-3343. Material Incorporated by Reference (n) You must use Table 1 of Honeywell Alert Service Bulletin No. TFE731-A72-5185, dated July 5, 2006, or Table 1 of Honeywell Service Bulletin No. TFE731-72-3720, dated July 5, 2006, as applicable, to determine SN applicability of HP turbine rotor discs requiring removal by this AD. The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell Technical Publications and Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation), (602) 365-5535 (Commercial Aviation), fax: (602) 365-5577 (General Aviation and Commercial Aviation) for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr- locations.html.