2006-11-16: Fuel control regulator assemblies

2006-11-16 Honeywell International Inc. (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming): Amendment 39-14620. Docket No. 98-ANE-72-AD. Effective Date (a) This AD becomes effective July 5, 2006. Affected ADs (b) This AD supersedes AD 98-22-11. Applicability (c) This AD applies to Honeywell International Inc., (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming) T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B series turboshaft engines and Lycoming former military T53-L-11B, T53-L-11D, T53-L-13B, T53-L-13B/D, and T53-L-703 series turboshaft engines using Goodrich Pump & Engine Control Systems, Inc. (GPECS) (formerly Chandler Evans Control Systems) engine fuel control regulator assembly models TA-2S, TA-2G, TA-2F, TA-7, or TA-10. (d) The T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B turboshaft engines are installed on, but not limited to, Bell 204, 205, and Kaman K-1200 helicopters. Lycoming T53-L-11B, T53-L-11D, T53-L-13B, T53-L-13B/D, and T53-L-703 series turboshaft engines are installed on, but not limited to, Bell AH-1 and UH-1 helicopters certified under Sec. 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). Unsafe Condition (e) This AD results from several reports of loss of fuel flow from the engine fuel control regulator assembly due to failure of both main and secondary drive shaft and pump gear splines. We are issuing this AD to prevent in-flight engine failure and forced autorotation landing. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Visual and Dimensional Inspection (g) Within 150 flight hours after the effective date of this AD, do the following: (1) Remove the fuel control regulator assembly from the engine and perform an initial visual and dimensional inspection of the fuel control regulator assembly main and secondary drive shaft and pump gear splines for wear. (2) Use paragraphs 2.A. through 2.D.(7) and 2.E. through 2.F.(2) of the Accomplishment Instructions of Goodrich Pump & Engine Control Systems, Inc. (TA series) Service Bulletin (SB) No. 73-42, Revision 1, dated August 12, 2004 to do the inspection. (3) Do not install any engine fuel control regulator assembly that fails inspection. Repetitive Visual and Dimensional Inspections (h) Thereafter, within every 1,250 flight hours since-last- inspection, perform repetitive visual and dimensional inspections of the fuel control regulator assembly main and secondary drive shaft and pump gear splines for wear, as specified in paragraphs (g)(1) through (g)(3) of this AD. Alternative Methods of Compliance (i) The Manager, Los Angeles Aircraft 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. Related Information (j) Honeywell International Inc. Service Bulletin No. T53-0138, Revision 1, dated May 5, 2005, also pertains to the subject of this AD. Material Incorporated by Reference (k) You must use Goodrich Pump & Engine Control Systems, Inc. (TA series) Service Bulletin (SB) No. 73-42, Revision 1, dated August 12, 2004, to perform the inspections required by this AD. 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 Goodrich Pumps & Engine Control Systems, P.O. Box 3306519, West Hartford, CT 06133, fax (860) 231-2718. You can review a copy at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 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.