Airworthiness Directive · Amendment 39-14620 · Honeywell International Inc. 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
Honeywell International Inc. 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
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 § 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27).
The FAA is superseding an existing airworthiness directive (AD) for AlliedSignal, Inc. T5317A-1 turboshaft engines. That AD currently requires repetitive engine fuel pump pressure tests of certain fuel control regulator assemblies to determine if both fuel pumps in the fuel control regulator assemblies are producing fuel pressure. That AD also requires replacing the fuel control regulator assembly, if necessary. This AD requires initial and repetitive visual and dimensional inspections of fuel control regulator assembly main and secondary drive shaft and pump gear splines, installed in certain fuel control regulator assemblies. This AD also expands the engine applicability, and includes certain engines installed on helicopters certified under Sec. 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). 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.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
