AD 2011-08-06 Airworthiness Directives; Honeywell International Inc. LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines

This AD applies to Honeywell International LTS101-600A-2, -3, -3A, LTS101-700D-2, LTS101-650B-1, LTS101-650C-3, LTS101-650C-3A, LTS101-750B-1, LTS101-750B-2, LTS101-750C-1, and LTS101-850B-2 turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop engines with power turbine rotor, part number (P/N) 4-141-290-01, -02, -03, -05, -06, -11, -12, -13, -14, or -16, installed. These engines are installed on, but not limited to, Eurocopter AS350 and BK117 series and Bell 222 series helicopters; and Page Thrush, Air Tractor AT-302, and Pacific Aero 08-600, Piaggio P166 DL3, and Riley International R421 airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) For engines with power turbine rotors, P/Ns 4-141-290-11, -12, -13, and -14, marked with “ORI T41881,” on the aft hub in the vicinity of the P/N, no further action is required. Removing Power Turbine Rotors From LTS101-600A-2, -3, -3A, and LTS101-700D-2 Turboshaft Engines and LTP101-600A-1A and LTP101-700A-1A Turboprop Engines (g) For LTS101-600A-2, -3, -3A, and LTS101-700D-2 turboshaft engines and LTP101-600A-1A and LTP101-700A-1A turboprop engines, remove power turbine rotors, P/Ns 4-141-290-01, -02, -03, -05, -06, -11, -12, -13, -14, or -16, using the cycles specified in Table 1 of this AD: Table 1—Drawdown Cycles for LTS101-600A-2, -3, -3A, and LTS101-700D-2 Turboshaft Engines and LTP101-600A-1A and LTP101-700A-1A Turboprop Engines If power turbine rotor time on the effective date of this AD is . . . Then remove the power turbine rotor from the engine . . . (1) Fewer than 5,000 cycles-since-new (CSN) Between 5,000 and 5,500 CSN. (2) 5,000 to 7,899 CSN Within 500 cycles-in-service (CIS) after the effective date of this AD or before exceeding 8,000 CSN, whichever occurs first. (3) 7,900 to 9,999 CSN Within 100 CIS after the effective date of this AD or before exceeding 10,050 CSN, whichever occurs first. (4) 10,000 or more CSN Within 50 CIS after the effective date of this AD. Removing Power Turbine Rotors From LTS101-650B-1, -650C-3,—650C-3A, -750B-1, -2, -750C-1, and -850B-2 Engines (h) Remove power turbine rotors, P/Ns 4-141-290-01, -02 -03, -05, -06, -11, -12, -13, -14, or -16, using the cycles specified in Table 2 of this AD: Table 2—Drawdown Cycles for LTS101-650B-1, -650C-3,-650C-3A, -750B-1, -2, -750C-1, and -850B-2 Engines If power turbine rotor time on the effective date of this AD is . . . Then remove the power turbine rotor from the engine . . . (1) Fewer than 5,500 CSN Between 5,000 and 7,200 CSN. (2) 5,500 to 7,999 CSN Within 1,700 CIS after the effective date of this AD or before exceeding 8,950 CSN, whichever occurs first. (3) 8,000 to 9,999 CSN Within 950 CIS after the effective date of this AD or before exceeding 10,400 CSN, whichever occurs first. (4) 10,000 or more CSN Within 400 CIS after the effective date of this AD. Alternative Methods of

This AD results from reports of fatigue cracks in the airfoil of the power turbine blade. We are issuing this AD to prevent fracture of the power turbine blade airfoil, which could result in sudden loss of engine power and prevent continued safe flight or safe landing.