2012-07-09: P3 air pipe (first section) and the RH rear half-wall

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 2009-14-11, Amendment 39-15961 (74 FR 34221, July 15, 2009), and adding the following new AD: 2012-07-09 Turbomeca S.A: Amendment 39-17015; Docket No. FAA-2009- 0330; Directorate Identifier 2008-NE-43-AD. (a) Effective Date This airworthiness directive (AD) is effective May 24, 2012. (b) Affected ADs This AD supersedes AD 2009-14-11, Amendment 39-15961 (74 FR 34221, July 15, 2009). (c) Applicability This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines with right-hand (RH) rear half-wall, part number (P/N) 0319 99 824 0, installed.(d) Unsafe Condition The P3 air pipe (first section) and the RH rear half-wall could rub each other. Rubbing [[Page 23382]] between the pipe and the RH rear half-wall may lead to rupture of the P3 air pipe (first section), which could cause an uncommanded power loss to flight idle. We are issuing this AD to prevent an uncommanded power loss to flight idle, which could result in an emergency autorotation landing or accident. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For installed engines, within 100 engine hours (EH) after the effective date of this AD: (i) Inspect the clearance between the P3 air pipe (first section) and the RH rear half-wall for sufficient clearance (0.5 mm or more). (ii) Use paragraph 2.B.(1) of Turbomeca Mandatory Service Bulletin (MSB) No. 319 75 4810, Version B, dated January 25, 2011 to do the inspection. (2) Thereafter, repeat the inspections in paragraphs (e)(1)(i) through (e)(1)(ii) of this AD as follows: (i) At every installation of a RH rear half-wall P/N 0 319 99 824 0 on an installed engine, and (ii) After every installation or reinstallation of an engine with a RH rear half-wall P/N 0 319 99 824 0 installed. (3) If the P3 air pipe (first section) or the RH rear half-wall P/N 0 319 99 824 0 is found damaged, then before further flight, replace the damaged part(s) with parts eligible for installation. (4) If the P3 air pipe (first section) and the RH rear half-wall P/N 0 319 99 824 0 are found contacting each other but are not damaged, replace the RH rear half-wall with a RH rear half-wall eligible for installation. (5) If both the P3 air pipe (first section) and the RH rear half-wall are found not damaged during the inspections specified in paragraph (e)(1) or (e)(2) of this AD, and the clearance between them is less than 0.5 mm, but they are not contacting each other, then repeat the inspection in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD within every 100 EH. (6) Installation of RH rear half-wall, P/N 0 319 99 008 0, is terminating action to the inspections required by paragraphs (e)(1), (e)(2), and (e)(5) of this AD. (7) Once a RH rear half-wall, P/N 0 319 99 008 0, is installed on an engine, do not install a RH rear half-wall, P/N 0 319 99 824 0, on that engine. (f) Definition For the purpose of this AD, parts eligible for installation is defined as: (1) An undamaged P3 air pipe (first section). (2) An undamaged RH rear half-wall P/N 0 319 99 824 0. (3) A new design RH rear half-wall P/N 0 319 99 008 0. (g) Credit for Previous Action An inspection performed on an installed engine before the effective date of this AD using Turbomeca MSB No. 319 75 4810, Version A, dated May 14, 2008, satisfies the inspection requirement in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve alternative methods of compliance for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (i) Related Information (1) For more information about this AD, contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7758; fax: 781-238-7199; email: mark.riley@faa.gov. (2) European Aviation Safety Agency AD 2011-0182R1, dated February 3, 2012, pertains to the subject of this AD. (3) For service information identified in this AD, contact. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (j) Material Incorporated by Reference You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information. (1) Turbomeca Mandatory Service Bulletin No. 319 75 4810, Version A, dated May 14, 2008, approved for IBR August 19, 2009 (74 FR 34221, July 15, 2009). (2) Turbomeca Mandatory Service Bulletin No. 319 75 4810, Version B, dated January 25, 2011, approved for IBR May 24, 2012. (3) For service information identified in this AD, contact Turbomeca, 40220 Tarnos, France; telephone 33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5 59 74 45 15. (4) You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (5) You may also review copies of the service information that is incorporated by reference 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.