2007-01-04: Lower union of the flexible fuel pipe

2007-01-04 Turbomeca: Amendment 39-14875. Docket No. FAA-2006-26128; Directorate Identifier 2006-NE-34-AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 25, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Artouste III B and III B1 turboshaft engines fitted with a fuel pipe, part number 0 202 12 800 0. These engines are installed on SA 315 B LAMA and SA 316 B Alouette III helicopters. Reason (d) European Aviation Safety Agency, (EASA), Airworthiness Directive No. 2006-0154, dated June 1, 2006, states: 3 cases of cracking due to exfoliation corrosion on the unions of fuel pipes P/N 0 202 12 800 0, connecting the Fuel Control Unit to the start electrovalve, were reported. These cases of cracking, if they had not previously been detected, could have caused a loss of integrity of the union conveying fuel under pressure. A fuel leakage could then have happened and would have led to an uncommanded loss of power and to a fire hazard. This AD requires the fuel pipe to be inspected for cracking. FAA AD Differences (e) None. Actions and Compliance (f) At the next maintenance action on the engine or airframe, but no later than 30 days after the effective date of this AD, unless already done, do the following action. (1) Inspect for cracks in the lower union of the flexible fuel pipe between the electric fuel cock and the start valve. (2) Use the instructions contained in paragraph 2 of Turbomeca Mandatory Service Bulletin No. A218 73 0803, dated May 2, 2006, to do the inspection. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056. Related Information (h) Refer to the EASA Airworthiness Directive 2006-0154, dated June 1, 2006, and Turbomeca Mandatory Service Bulletin A218 73 0803, dated May 2, 2006, for related information. (i) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238- 7175; fax (781) 238-7199, for more information about this AD. Material Incorporated by Reference (j) You must use Turbomeca Mandatory Service Bulletin No. A218 73 0803, dated May 2, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax (33) 05 59 74 45 15. (3) You may review copies 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.