Airworthiness Directive · Amendment 39-15976 · Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines
Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines
This AD applies to Honeywell International Inc. T5313B, T5317A, T5317A-1, T5317B, and T5317BCV turboshaft engines with combustion chamber housing (CCH), part numbers (P/Ns) 1-130-610-05, 1-130-610-12, and 1-130-610-17, installed. These engines are installed on, but not limited to, Bell 205 and 210 Series and Kaman K-1200 helicopters.
The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc., T5313 and T5317 series turboshaft engines. This AD requires initial and repetitive visual inspections and initial and repetitive ultrasonic inspections of combustion chamber housings (CCHs) for cracks. This AD results from eight instances of cracks in CCHs. Two of the instances resulted in an engine shutdown during flight. We are issuing this AD to detect cracks in the CCH, which could result in rupture of the CCH, leading to loss of engine power and damage to the helicopter.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
For CCH, P/N 1-130-610-05 and 1-130-610-12, within 50 hours time-in-service (TIS) after the effective date of this AD, inspect the area between points A and B around the entire housing circumference in Figure 1 of this AD for weld repairs and cracks.
(1) If you find any cracks, replace the CCH before further flight. Honeywell International Inc. Alert Service Bulletin (ASB) T53-A0142, Revision 1, dated September 14, 2006, contains additional guidance on replacing the CCH.
(2) If you find any weld repairs, replace the CCH within 100 hours TIS after the visual inspection. Honeywell International Inc. ASB T53-A0142, Revision 1, dated September 14, 2006, contains additional guidance on replacing the CCH.
For CCH, P/N 1-130-610-05 and 1-130-610-12, inspect the area between points A and B around the entire housing circumference in Figure 1 of this AD for cracks within every 50 hours time-since-last inspection. Honeywell International Inc. Standard Practices Manual 70-20-02, SP 1302, contains additional guidance on visual inspection.
(h) If you find any cracks, replace the CCH before further flight. Honeywell International Inc. ASB T53-A0142, Revision 1, dated September 14, 2006, contains additional guidance on replacing the CCH.
(i) Perform an ultrasonic inspection on the CCH. Use Honeywell International Inc. Service Bulletin (SB) No. T53-0144, Revision 4, dated March 31, 2008, section 3. Accomplishment Instructions and the SB Appendix to perform the ultrasonic inspection at the following compliance times.
(1) For CCH, P/N 1-130-610-05 and 1-130-610-12, within 500 hours TIS or next hot section inspection, whichever occurs first after the effective date of this AD, but not to exceed 6 months after the effective date of this AD.
(2) For CCH, P/N 1-130-610-17, perform at the first overhaul, but do not exceed 5,000 hours or 11,000 cycles, after the effective date of this AD, whichever occurs first.
Repeat the ultrasonic inspection on the CCH using Honeywell International Inc. SB No. T53-0144, Revision 4, dated March 31, 2008, section 3. Accomplishment Instructions and the SB Appendix at the following compliance times:
(1) Within every 1,200 flights, defined as the cumulative number of landings, since the last inspection; or
(2) Within every 200 flights, if the last inspection had ultrasonic findings as defined in paragraph 3.A.(2) or paragraph 3.A.(3) of Honeywell International Inc. SB No. T53-0144, Revision 4, dated March 31, 2008.
Installation of a CCH P/N 1-130-610-19 or 1-130-610R16, or an FAA approved equivalent part, terminates the inspection requirements 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.
