2002-16-25: Fuel pumps

2002-16-25 Turbomeca S.A.: Amendment 39-12864. Docket No. 2001-NE- 10-AD. Applicability This airworthiness directive (AD) is applicable to Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C turboshaft engines. These engines are installed on, but not limited to Sikorsky S76, Eurocopter France "Ecureuil" AS 350 B3, and Eurocopter France "Dauphin" AS 365 N3 helicopters. Note 1: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if theunsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance Compliance with this AD is required as indicated, unless already done. To prevent fuel leakage, which may cause engine fires that could lead to an in-flight engine shutdown, damage to the helicopter, and forced landing, do the following: Inspections and Actions (a) For the fuel metering high pressure/low pressure (HP/LP) pump assemblies listed by serial number (SN) in Appendix 1 of Turbomeca Service Bulletin (SB) No. 292 73 2803, dated July 2, 1999, do the following: (1) After the last flight of each day, within five minutes of engine shutdown, perform a visual inspection of the floor of the helicopter engine bay for fuel leaks. (2) If evidence of a fuel leak is observed, inspect the fuel metering HP/LP pump assembly for leakage and if leakage is observed, replace with a serviceable pump assembly before further flight. (3) Ifvisual inspection of the floor of the helicopter engine bay for fuel leaks reveals no leaks, do either of the following: (i) Continue repetitive visual inspections of the floor of the helicopter engine bay for fuel leaks in accordance with paragraph (a)(1) of this AD, and perform repetitive visual inspections of the fuel metering HP/LP pump assembly for fuel leaks at intervals not to exceed 50 hours of operation. If evidence of fuel leaking is observed, replace the pump assembly with a serviceable pump assembly before further flight, in accordance with Turbomeca SB No. 292 73 2803, dated July 2, 1999; or (ii) Remove the pump assembly and inspect to determine if pump body material wall thickness is below the minimum material thickness, in accordance with Section 2 of Turbomeca SB No. 292 73 2803, dated July 2, 1999. If pump body material wall thickness is at or above the minimum material thickness, mark the pump assembly by adding a letter "x" to the end of the SN. (b) Replace the fuel metering HP/LP pump assembly if listed by SN in Appendix 1 of Turbomeca Service Bulletin (SB) No. 292 73 2803, dated July 2, 1999, with a serviceable pump assembly by December 31, 2006. Definition (c) For the purposes of this AD, a serviceable pump assembly is a fuel metering HP/LP pump assembly not listed by SN in Appendix 1 of Turbomeca SB No. 292 73 2803, dated July 2, 1999, or a fuel metering HP/LP pump assembly listed by SN in Appendix 1 whose pump body material wall thickness has been determined by inspection to be at or above the minimum material thickness, and marked in accordance with paragraph (a)(3)(ii) of this AD. Terminating Action (d) Replacement, or verification of correct wall thickness of a fuel metering HP/LP pump assembly that is listed in Appendix 1 of Turbomeca SB No. 292 73 2803, dated July 2, 1999, with a serviceable pump assembly as defined in paragraph (c) of this AD, is considered terminating action for the inspection requirements specified in paragraph (a) of this AD. Alternative Methods of Compliance (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Special Flight Permits (f) Special flight permits may be issued in accordance with 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be done. Documents That Have Been Incorporated by Reference (g) The inspections and removals must be done in accordance with Turbomeca SB No. 292 73 2803, dated July 2, 1999. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 64 40 00; fax (33) 05 59 64 60 80. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. Note 3: The subject of this AD is addressed in Direction Generale de L'Aviation Civile (DGAC) Airworthiness Directive AD 99- 285(A), dated July 13, 1999. Effective Date (h) This amendment becomes effective on September 26, 2002.