AD 2010-02-08 Airworthiness Directives; Turbomeca Turmo IV A and IV C Turboshaft Engines

This AD applies to Turbomeca Turmo IV A and IV C turboshaft engines that have incorporated Turbomeca Modification TU 233. These engines are installed on, but not limited to, Eurocopter SA 330F, G, or J PUMA helicopters. Reason (d) During a maintenance inspection before the first flight of the day, an oil leak was found on an engine deck. A circumferential crack on the intermediate bearing return flexible pipe union (pipe part number 9 560 17 606 0) was identified as the origin of the leak. A similar oil pipe union crack was then reported at the same location on another engine, on the same pipe part number. This pipe part number was approved as Modification TU 233 in 2008. Although such cracks have been detected and did not lead to an in-service event, the possibility exists that some additional cracks could occur and may not be detected before the potential complete rupture of the union. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent a helicopter engine in-flight shutdown resulting in an emergency auto-rotation landing or accident.

Unless already done, do the following actions. (1) Before the next flight after the effective date of this AD, and thereafter daily after the last flight of the day until further notice, visually inspect for absence of oil leakage or seepage from both unions of the intermediate bearing return flexible pipes, part number 9 560 17 606 0. (2) If any oil leakage or seepage is found, disassemble the pipe and visually inspect the unions. (3) If no crack is found, re-install the pipe. (4) If any crack is found, remove the pipe from service and replace it. (5) The actions required by paragraph (e)(1) of this AD may be performed by the owner/operator holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 and 91.417(a)(2)(v). FAA AD Differences (f) None. Alternative Methods of Compliance (AMOCs) (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI Airworthiness Directive 2009-0261-E, dated December 18, 2009, and Turbomeca Alert Mandatory Service Bulletin No. A249 72 0809, Version A, dated December 15, 2009, for related information. Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, or go to: http://www.turbomeca-support.com, for a copy of this service information. (i) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (j) None. Issued in Burlington, Massachusetts, on January 12, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010-758 Filed 1-15-10; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Before the next flight after the effective date of this AD, and thereafter daily after the last flight of the day until further notice, visually inspect for absence of oil leakage or seepage from both unions of the intermediate bearing return flexible pipes, part number 9 560 17 606 0. (2) If any oil leakage or seepage is found, disassemble the pipe and visually inspect the unions. (3) If no crack is found, re-install the pipe. (4) If any crack is found, remove the pipe from service and replace it. (5) The actions required by paragraph (e)(1) of this AD may be performed by the owner/operator holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 and 91.417(a)(2)(v). FAA AD Differences (f) None. Alternative Methods of Compliance (AMOCs) (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI Airworthiness Directive 2009-0261-E, dated December 18, 2009, and Turbomeca Alert Mandatory Service Bulletin No. A249 72 0809, Version A, dated December 15, 2009, for related information. Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, or go to: http://www.turbomeca-support.com, for a copy of this service information. (i) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (j) None. Issued in Burlington, Massachusetts, on January 12, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010-758 Filed 1-15-10; 8:45 am] BILLING CODE 4910-13-P