Overall Trends
Total, fatal, and serious accidents in the selected range.
Search investigations, review source evidence, monitor watched reports, and trace long-term patterns from one calm, data-first workspace.
Fast key and full-text search with live filters, watches, and precise metadata.
Use quotes for exact phrase matches (for example "fuel selector valve").
Track fatal and non-fatal accident patterns across Part 91, Part 135, and Part 121 operations.
Major cases, deep-report coverage, and investigation media across decades of NTSB history.
Move quickly by aircraft, airport, operator, and time with indexes built for research, not wandering.
NTSB Reports is an independent research and search tool for public aviation accident and incident records. It brings NTSB aviation reports, structured fields, docket files, extracted figures, photos, videos, and update history into one searchable interface.
The goal is practical safety education: make it faster to find relevant investigations, compare similar events, review factual records, and understand the evidence behind probable-cause and preliminary reports.
The investigative work and source records belong to the National Transportation Safety Board and the published investigation record. This site is not affiliated with or endorsed by the NTSB.
Watkins Glen, NY
DURING A CERTIFICATION TEST FLIGHT INVOLVING A SERIES OF DESCENTS AT LOW ROTOR RPM AND LOW AIRSPEEDS, THE ENGINE OF THE PROTOTYPE HELICOPTER LOST POWER. AN AUTOROTATION WAS INITIATED AND THE AIRCRAFT IMPACTED THE GROUND IN A TAIL LOW CONDITION, CAUSING DAMAGE TO THE TAIL ROTOR AND MAIN ROTOR. THE AIRCRAFT WAS BEING OPERATED AT A HIGH GROSS WEIGHT AND AFT CENTER OF GRAVITY TO MEET CERTIFICATION CRITERIA. THE RIGGING BETWEEN THE THROTTLE AND FUEL CONTROL UNIT WAS EXAMINED AND FOUND TO BE IMPROPERLY SET, CAUSING THE PREVENTION OF CONTINUOUS ENGINE POWER THROUGHOUT THE FLIGHT TEST PROFILE.
FUEL STARVATION AS A RESULT OF IMPROPER RIGGING OF THE FUEL CONTROL UNIT.
DURING A CERTIFICATION TEST FLIGHT INVOLVING A SERIES OF DESCENTS AT LOW ROTOR RPM AND LOW AIRSPEEDS, THE ENGINE OF THE PROTOTYPE HELICOPTER LOST POWER. AN AUTOROTATION WAS INITIATED AND THE AIRCRAFT IMPACTED THE GROUND IN A TAIL LOW CONDITION, CAUSING DAMAGE TO THE TAIL ROTOR AND MAIN ROTOR. THE AIRCRAFT WAS BEING OPERATED AT A HIGH GROSS WEIGHT AND AFT CENTER OF GRAVITY TO MEET CERTIFICATION CRITERIA. THE RIGGING BETWEEN THE THROTTLE AND FUEL CONTROL UNIT WAS EXAMINED AND FOUND TO BE IMPROPERLY SET, CAUSING THE PREVENTION OF CONTINUOUS ENGINE POWER THROUGHOUT THE FLIGHT TEST PROFILE.