2001-12-07: Fuel Flow Divider Assemblies

2001-12-07 General Electric Company: Amendment 39-12262. Docket No. 2001-NE-07-AD. Applicability This airworthiness directive (AD) is applicable to General Electric Company (GE) CT58-140-1, -140-2, and former military T58-GE-5, -8F, -10, -100, and -402 turboshaft engines, with fuel flow divider assemblies part numbers (P/N's) 4050T82G02, or 5040T77G02 having temperature control assemblies with serial numbers (SN's) with the first two digits of 95, 96, 97, 98, or 99 installed. These engines are installed on, but not limited to Agusta S.p.A. AS-6N, Boeing Vertol 107-11, Sikorsky S-61 Series and S-62 Series, and the following surplus military helicopters that have been certified in accordance with sections 21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or 21.27): Carson S-61L, Firefly UH-1F, Glacier CH-3E, Quentin HH52A, Robinson Air Crane CH-3C, CH-3E, HH-3C, and HH-3E, Sikorsky S-61A, S-61D, S-61E, S-61V, and S-61V-1, and Siller Helicopters CH-3A, and SH-3A.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 (c) 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 the unsafe 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 flow divider assembly fuel leakage, which could cause an engine fire, leading to an in-flight engine shutdown and forced landing, do the following within 120 hours time-in-service after the effective date of this AD: (a) Locate the temperature control assembly, which is mounted on the fuel flow divider assembly and do the following: (1) Read the temperature control assembly SN, located on the temperature control assembly end cap. The end cap can be identified by a one-inch hex flange and by being threaded into the fuel flow divider body. (2) If the first two digits of the SN are 95, 96, 97, 98, or 99, or if the SN cannot be determined, replace the entire fuel flow divider assembly. Further information regarding SN location on the temperature control assembly may be found in GE Alert Service Bulletin CT58 73-A0080, dated February 13, 2001. (b) After the effective date of this AD, do not install any fuel flow divider assembly P/N 4050T82G02 or 5040T77G02, that has the first two digits of the temperature control assembly SN of 95, 96, 97, 98, or 99. Alternative Methods of Compliance (c) An alternative method ofcompliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. Special Flight Permits (d) Special flight permits may be issued in accordance with sections 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 accomplished. Effective Date of this AD (e) This amendment becomes effective on July 2, 2001.