AD 2009-09-03R1 Airworthiness Directives; Turboméca S.A. Arriel 2B and 2B1 Turboshaft Engines

This AD applies to Turboméca S.A. ARRIEL 2B and 2B1 turboshaft engines that don't incorporate modification TU166. These engines are installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters. Reason (d) This AD results from: Since issuance of AD 2007-0109, Turboméca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or an accident.

Unless already done, do the following actions: Initial Inspection (1) Perform an initial high-pressure (HP) turbine borescope inspection according to Turboméca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, Version B, dated September 21, 2009, or earlier version as follows: (i) For engines with fewer than 500 hours and 450 cycles since new or since the last HP turbine borescope inspection, inspect before reaching 600 hours or 500 cycles whichever occurs first. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) For the remaining engines, inspect within the next 100 hours. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. Repetitive Inspections (2) Perform repetitive HP turbine borescope inspections according to Turboméca S.A. MSB No. 292 72 2825, Version B, dated September 21, 2009 or earlier version: (i) Within 600 hours or 500 cycles from the previous inspection, whichever occurs first, if the rearward displacement of the turbine blades was less than 0.2 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) Within 100 hours of the previous inspection if the rearward displacement of the turbine blades was between 0.2 mm and 0.5 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. Optional Terminating Action (f) Incorporating modification TU166 terminates the repetitive inspection requirements of paragraphs (e)(2)(i) and (e)(2)(ii) of this AD. FAA AD Differences (g) For clarification, we restructured the actions and compliance wording of this AD. (h) We deleted the Turboméca reporting requirement from the AD. (i) Although EASA Airworthiness Directive 2007-0109R1, dated November 9, 2009, applies to the ARRIEL 2B1A engine, this AD does not apply to that model because it has no U.S. type certificate. Alternative Methods of Compliance (AMOCs) (j) 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 (k) Refer to EASA Airworthiness Directive 2007-0109R1, dated November 9, 2009, and Turboméca S.A. MSB No. 292 72 2825, Version B, dated September 21, 2009, or earlier version, for related information. (l) Contact Richard Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7136; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (m) You must use Turboméca S.A. Mandatory Service Bulletin No. 292 72 2825, Version B, dated September 21, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register previously approved the incorporation by reference of Turboméca S.A. Mandatory Service Bulletin No. 292 72 2825, dated April 5, 2007, on June 1, 2009 (74 FR 18981, April 27, 2009). (2) For service information identified in this AD, contact Turboméca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. (3) 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. Issued in Burlington, Massachusetts, on September 17, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010-23833 Filed 9-24-10; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions: Initial Inspection (1) Perform an initial high-pressure (HP) turbine borescope inspection according to Turboméca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, Version B, dated September 21, 2009, or earlier version as follows: (i) For engines with fewer than 500 hours and 450 cycles since new or since the last HP turbine borescope inspection, inspect before reaching 600 hours or 500 cycles whichever occurs first. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) For the remaining engines, inspect within the next 100 hours. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. Repetitive Inspections (2) Perform repetitive HP turbine borescope inspections according to Turboméca S.A. MSB No. 292 72 2825, Version B, dated September 21, 2009 or earlier version: (i) Within 600 hours or 500 cycles from the previous inspection, whichever occurs first, if the rearward displacement of the turbine blades was less than 0.2 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) Within 100 hours of the previous inspection if the rearward displacement of the turbine blades was between 0.2 mm and 0.5 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. Optional Terminating Action (f) Incorporating modification TU166 terminates the repetitive inspection requirements of paragraphs (e)(2)(i) and (e)(2)(ii) of this AD. FAA AD Differences (g) For clarification, we restructured the actions and compliance wording of this AD. (h) We deleted the Turboméca reporting requirement from the AD. (i) Although EASA Airworthiness Directive 2007-0109R1, dated November 9, 2009, applies to the ARRIEL 2B1A engine, this AD does not apply to that model because it has no U.S. type certificate. Alternative Methods of Compliance (AMOCs) (j) 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 (k) Refer to EASA Airworthiness Directive 2007-0109R1, dated November 9, 2009, and Turboméca S.A. MSB No. 292 72 2825, Version B, dated September 21, 2009, or earlier version, for related information. (l) Contact Richard Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7136; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (m) You must use Turboméca S.A. Mandatory Service Bulletin No. 292 72 2825, Version B, dated September 21, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register previously approved the incorporation by reference of Turboméca S.A. Mandatory Service Bulletin No. 292 72 2825, dated April 5, 2007, on June 1, 2009 (74 FR 18981, April 27, 2009). (2) For service information identified in this AD, contact Turboméca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. (3) 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. Issued in Burlington, Massachusetts, on September 17, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010-23833 Filed 9-24-10; 8:45 am] BILLING CODE 4910-13-P