20001022018899A

(-23) After takeoff the heli turned downwind toward its destination. Two to three minutes after takeoff, the pilot heard three loud banging noises and felt vibrations. The pilot entered autorotation and turned into the wind to land. The subsequent landing was hard and the heli had some forward motion when it landed. The heli rotated forward on the curved part of the skids and then rotated back onto it's main skids causing a down-force on the tailboom which resulted in structural damage at the fuselage attach point. Onlythe tailboom received damage. Upon inspection of the engine it was noted that the compressor would not rotate. The engine was sent to the manufacturerfor further investigaion. There were several chip lights that occurred on days prior to the accident but the operator could not determine the cause. The engine was recently overhauled and assembled by the operator. (.4)on October 22, 2000, at 0807 hours hawaiian standard time, an aerospatiale AS350BA, N12NT, was substantially damaged during an autorotative emergency landing following loss of engine power about 1 mile west-southwest of the waimea-kohala airport at Kamuela, Hawaii. The commercial certificated pi ot, the sole occupant, received serious injuries. Visual meteorological conditions prevailed for the positioning flight that was operated by mauna kea helicopters, under 14 CFR part 91. The helicopter was departing from the airport at the time of the engine failure, destined for a nearby resort hotel. No flight plan was filed. The autorotation was performed to an upsloping area of dirt and rocks. Inspection of the engine after the accident revealed that the engine compressor was seized. The engine was overhauled 61 hours prior to the accident. The engine is comprised of five modules. Module 1 is overhauled on-condition and was not serviced at the overhaul. Turbomeca engine corporation of grand prairie, Texas, overhauled modules 2 and 3, and acro aerospace, inc., of richmond, bc, Canada, overhauled modules 4 and 5. The five modules were assembled together and installed in the helicopter by the operator. The engine was examined by safety board investigators at the facilities of turbomeca engine corporation on December 7, 2000. The rotating assembly (compressor and turbine) of the gas generator section (N1, modules 1, 2 and 3) of the engine was seized and the power turbine assembly and output gearbox (N2, modules 4 and 5) was free to rotate. When modules 2 and 3 were separated, the compressor and accessory case (modules 1 and 2) rotated freely and the combustion section and turbine (module 3) remained seized. Module 3 was difficult to disassemble due to damage at the rear bearing area. Further examination revealed the turbine rear support bearing (bearing, turbomeca part number 9609000153) was backed out of the bearing support housing (cage, part number 0292502630). Ordinarily the bearing is retained in the housing by a circlip (part number 9560119360), however, no evidence of presence of the circlip was found. The circlip retaining groove in the support housing was visibly undamaged. An additional party to the investigation was Mr. Joe braz of acro aerospace, inc, richmond, bc, Canada. The wreckage was released to the owner on December 22, 2000.