2004-04-06: Fuel flow divider assemblies

2004-04-06 General Electric Company: Amendment 39-13487. Docket No. 2003-NE-66-AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 9, 2004. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT58-100-2, CT58-140-1, -140-2, and T58-GE-1, -3, -5, -8E, -8F, -10, -100, and - 402 turboshaft engines, with fuel flow divider assemblies part number (P/N) 4050T82G02 or 4067T04G02, having temperature control assemblies, P/N 5040T77G02 or 5040T87G02, with serial numbers (SNs) listed in 1.A.(3) of GE Alert Service Bulletin (ASB) No. CT58 S/B 73-A0081, Revision 2, dated August 7, 2003, installed. These engines are installed on, but not limited to, Agusta S.p.A. AS-61N, AS-61N1, Boeing Vertol 107-II, and Sikorsky S-61L, S-61N, S-61R, S-61NM, S- 62A helicopters, and the following surplus military helicopters that have been certified in accordance with Sec. 21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or 21.27): CA Department of Forestry UH-1F, Carson S-61L, Firefly UH-1F, Garlick Helicopters UH-1F, UH-1P, and TH-1F, Glacier CH-3E, Robinson Air Crane CH-3C, CH-3E, HH-3C, HH-3E, UH-1F, UH-1P, and TH-1F, Sikorsky S-61A, S-61D, and S-61V, Tamarack UH-1F, and Siller Helicopters CH-3A, and SH-3A helicopters. Unsafe Condition (d) This AD results from a report that a certain population of flow divider end caps could crack and cause large volumes of fuel leakage. We are issuing this AD to prevent fuel leakage from the fuel flow divider assembly, which could cause an engine fire, leading to an in-flight engine shutdown and forced landing. Compliance (e) You are responsible for having the actions required by this AD performed within 120 hours time-in-service after the effective date of this AD: Required Actions (f) Locate the temperature control assembly, which is mounted on the fuel flow divider assembly and do the following: (1) Read the SN ofthe temperature control assembly. The SN is located on the end cap of the temperature control assembly. The end cap has a one-inch hex flange and is threaded into the fuel flow divider body. (2) If the SN is listed in 1.A.(3) of GE ASB No. CT58 S/B 73- A0081, Revision 2, dated August 7, 2003, or if the SN cannot be determined, remove the fuel flow divider assembly from service. (g) After the effective date of this AD, do not install any fuel flow divider assembly P/N 4050T82G02 or 4067T04G02, that has a temperature control assembly with a SN listed in 1.A.(3) of GE ASB No. CT58 S/B 73-A0081, Revision 2, dated August 7, 2003. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) You must use GE ASB No. CT58 S/B 73-A0081, Revision 2, dated August 7, 2003 to identifyby SN the affected temperature control assemblies. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, e- mail GEAE.csc@ae.ge.com. You may review copies at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA 01803-5299, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Related Information (j) None.