ANC24LA013

A sudden stoppage of the tail rotor for unknown reasons, which resulted in the tortional overload failure of the tail rotor driveshaft.

The pilot stated that he was flying the helicopter solo with the doors removed while scouting potential locations for an aerial photography flight scheduled for later that day. During cruise flight, he heard a loud “boom” and felt a slight airframe vibration. He subsequently lost tail rotor thrust and performed an autorotation to an area of snow-covered, mountainous terrain. Examination revealed the tail rotor driveshaft was fractured between the forward and aft flex plates. Further examination of the tail rotor driveshaft revealed the fractures were consistent with ductile tension overload. There was no evidence of pre-existing cracks or other damage to the fracture surfaces. The tail rotor blades were not damaged during the accident sequence, and there were no mechanical anomalies found with the tail rotor gearbox assembly. The torsional twisting of the fractured surfaces of the tail rotor driveshaft is consistent with a sudden binding of the tail rotor gearbox, or a rapid deceleration of the tail rotor blades. There was no damage evident to the tail rotor assembly from a bird strike or impact with a hard object. Although, if a small rag or towel was overlooked during the preflight inspection and it had blown out of the helicopter during the doors-off flight, it likely would have been struck by the tail rotor, resulting in the rapid deceleration of the tail rotor blades, with little to no detectable damage. Thus, the reason for the torsional fracture of the tail rotor driveshaft could not be determined.

On February 11, 2024, about 1130 Alaska standard time, a Robinson Helicopter R44 II, N74868, was substantially damaged when it was involved in an accident near Glacier View, Alaska. The pilot was not injured. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 business flight. According to the pilot, while in cruise flight with both aft doors removed, about 700 ft above an area of snow-covered glacial terrain, he heard a loud “boom” noise and felt a slight airframe vibration. The pilot stated that he subsequently lost tail rotor thrust and that he then performed an autorotation to an area of snow-covered, mountainous terrain. A postaccident inspection, after the helicopter was recovered, revealed that the tail rotor driveshaft was fractured between the forward and aft flex plates, which resulted in substantial damage to the tail rotor driveshaft system.  The fractured pieces of the tail rotor driveshaft were sent to the NTSB Materials Laboratory for further examination. The examination revealed the fractures were consistent with ductile torsion overload. There was no evidence of pre-existing cracks or other damage to the driveshaft surfaces. The tail rotor blades were not damaged. Figure 1. View of the tail rotor driveshaft fracture surfaces The tail rotor gearbox assembly was removed from the accident helicopter and no anomalies were discovered. The pilot stated that he did not have a passenger, but that he did have the doors off in preparation for a passenger/photographer later that day. He also stated that during his preflight inspection, he checked for loose items that could blow out and strike the tail rotor. The pilot did not submit the National Transportation Safety Board Pilot/Operator Aircraft Accident/Incident Report Form 6120.1.