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.
Houston, TX
THE PURPOSE OF THE FLIGHT WAS FOR THE PILOT TO PRACTICE MANEUVERS IN PREPARATION FOR A PART 135 CHECK RIDE. THE PILOT WAS PRACTICING POWER RECOVERY AUTOROTATIONS TO A HEIGHT OF ABOUT 5 FT AG. HE REPORTED THAT ON HIS FOURTH AUTOROTATION, THE ENGINE DID NOT ACCELERATE WHEN HE ATTEMPTED THE POWER RECOVERY. SUBSEQUENTLY, THE HELICOPTER FELL THROUGH THE RECOVERY AND LANDED HARD. DURING THE INVESTIGATION, THE ENGINE FUEL CONTROL AND POWER TURBINE GOVERNOR WERE REMOVED FOR EXAMINATION. THE GOVERNOR WAS FOUND TO BE WITHIN SPECIFICATIONS. HOWEVER, AN EXAMINATION OF THE FUEL CONTROL UNIT REVEALED THE PX TRIM BLEED PART WAS OVERSIZE. THE SPECIFICATION CALLED FOR A SIZE #64 TO #68 PART, BUT A #61 PART WAS INSTALLED. ALSO, THERE WAS SOME WEAR ON THE BELLOWS. ACCORDING TO BENDIX CORP, THE OVERSIZE PART AND WEAR WOULD HAVE LEANED THE MIXTURE, BUT WOULD NOT HAVE CAUSED THE POWER LOSS.
THE PURPOSE OF THE FLIGHT WAS FOR THE PILOT TO PRACTICE MANEUVERS IN PREPARATION FOR A PART 135 CHECK RIDE. THE PILOT WAS PRACTICING POWER RECOVERY AUTOROTATIONS TO A HEIGHT OF ABOUT 5 FT AG. HE REPORTED THAT ON HIS FOURTH AUTOROTATION, THE ENGINE DID NOT ACCELERATE WHEN HE ATTEMPTED THE POWER RECOVERY. SUBSEQUENTLY, THE HELICOPTER FELL THROUGH THE RECOVERY AND LANDED HARD. DURING THE INVESTIGATION, THE ENGINE FUEL CONTROL AND POWER TURBINE GOVERNOR WERE REMOVED FOR EXAMINATION. THE GOVERNOR WAS FOUND TO BE WITHIN SPECIFICATIONS. HOWEVER, AN EXAMINATION OF THE FUEL CONTROL UNIT REVEALED THE PX TRIM BLEED PART WAS OVERSIZE. THE SPECIFICATION CALLED FOR A SIZE #64 TO #68 PART, BUT A #61 PART WAS INSTALLED. ALSO, THERE WAS SOME WEAR ON THE BELLOWS. ACCORDING TO BENDIX CORP, THE OVERSIZE PART AND WEAR WOULD HAVE LEANED THE MIXTURE, BUT WOULD NOT HAVE CAUSED THE POWER LOSS.