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AD/T53/22 - Engine Fuel Pump Spline Failure
AlliedSignal (Lycoming) Turbine Engines AlliedSignal (Lycoming) Turbine Engines - T53 Series
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AlliedSignal (Lycoming) Turbine Engines - T53 Series
| AD/T53/22 | Engine Fuel Pump Spline Failure | 8/2006 |
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| Applicability: | 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 militaryT53-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 modelsTA-2S, TA-2G, TA-2F, TA-7, or TA-10.Note 1: 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, andT53-L-703 series turboshaft engines are installed on, but not limited to, Bell AH-1 and UH-1 helicopters. |
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| Requirement: | 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 in accordance with 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 12 August 2004 or later FAA approved revision.2. 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 requirement 1 of this AD.3. Do not install any engine fuel control regulator assembly that fails inspection.Note 2: FAA AD 2006-11-16 Amdt 39-14620 dated 23 May 2006 refers. |
| Compliance: | 1. Within 150 flight hours after the effective date of this AD, unless previously accomplished.2. Repetitively every 1,250 flight hours since-last- inspection.3. From the effective date of this AD. |
| This Airworthiness Directive becomes effective on 3 August 2006. |
| Background: | 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. The actions detailed in this AD are intended to prevent in-flight engine failure and forced autorotation landing. |
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