Summary
On October 14, 2011, a Hughes 269A (N10375) was involved in an incident near Fort Worth, TX. All 2 people aboard were uninjured. The aircraft sustained substantial damage.
The National Transportation Safety Board determined the probable cause of this incident to be: The inadvertent entry into ground resonance after a hovering autorotation.
After practicing some flight and landing maneuvers, the certified flight instructor and pilot receiving instruction decided to practice some hovering autorotations on a taxiway. With the skids on the ground for approximately 20 seconds after completing a hovering autorotation and the engine at 2,000 RPM, the helicopter began to vibrate and violently shake. The vibrations and shaking continued to increase and lasted approximately 15 to 30 seconds. After the shaking stopped, the certified flight instructor shutdown the helicopter. Postaccident examination of the helicopter revealed the tail rotor and gearbox separated, and the fuselage was bent and deformed. No preimpact mechanical malfunctions or failures with the helicopter were noted that would have precluded normal operation.
This incident is documented in NTSB report CEN12CA031. AviatorDB cross-references NTSB investigation data with FAA registry records to provide comprehensive safety information for aircraft N10375.
Accident Details
Probable Cause and Findings
The inadvertent entry into ground resonance after a hovering autorotation.
Aircraft Information
Registered Owner (Current)
Analysis
After practicing some flight and landing maneuvers, the certified flight instructor and pilot receiving instruction decided to practice some hovering autorotations on a taxiway. With the skids on the ground for approximately 20 seconds after completing a hovering autorotation and the engine at 2,000 RPM, the helicopter began to vibrate and violently shake. The vibrations and shaking continued to increase and lasted approximately 15 to 30 seconds. After the shaking stopped, the certified flight instructor shutdown the helicopter. Postaccident examination of the helicopter revealed the tail rotor and gearbox separated, and the fuselage was bent and deformed. No preimpact mechanical malfunctions or failures with the helicopter were noted that would have precluded normal operation.
Data Source
Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CEN12CA031