Aircraft Description
N286M is a Kaman K-600, a single-engine turbo-prop aircraft registered to Olympic Jet INC in Olympia, WA. The registration certificate was issued on November 18, 2005. The registration is set to expire on October 31, 2028. The aircraft is configured with 2 seats. The aircraft's Mode S transponder code is A2E558 (hex), used for ADS-B identification and flight tracking. The FAA registry record for N286M was last updated on June 16, 2023. AviatorDB monitors aircraft positions through ADS-B surveillance data and updates records as new position data is received.
Kaman is an aircraft manufacturer with aircraft registered in the FAA database tracked by AviatorDB. AviatorDB tracks 9 Kaman aircraft currently registered in the FAA database, including the K-600 model.
AviatorDB has found no NTSB accident or incident reports involving N286M. AviatorDB cross-references all FAA registration data with NTSB accident and incident reports, providing a comprehensive safety overview for every registered aircraft in the United States.
Registered Owner
Powerplant & Avionics
NTSB Accident History (2)
| Date | NTSB # | Damage | Highest Injury | Probable Cause |
|---|---|---|---|---|
| Nov 20, 2003 | SEA04LA019 | Substantial | Fatal | The total failure of the helicopter's right main rotor shaft while in an ascending hover due to the propagation of a fatigue crack that initiated in a corrosion pit on the surface of a slot in the wall of the subject shaft. Factors include accumulation of corrosion on the surface of the shaft. |
| May 21, 2002 | SEA02IA096 | Unknown | None | The reverse installation of the RPM compensator assembly control box bolts resulting in the threaded end of the bolt impinging on a clevis and jamming the collective during climb. A contributing factor was the lack of adequate documentation provided by the technical order instruction for installation of the compensator. |
The total failure of the helicopter's right main rotor shaft while in an ascending hover due to the propagation of a fatigue crack that initiated in a corrosion pit on the surface of a slot in the wall of the subject shaft. Factors include accumulation of corrosion on the surface of the shaft.
The reverse installation of the RPM compensator assembly control box bolts resulting in the threaded end of the bolt impinging on a clevis and jamming the collective during climb. A contributing factor was the lack of adequate documentation provided by the technical order instruction for installation of the compensator.
Additional Details
Data Source
Data provided by the US Federal Aviation Administration. View on FAA.gov
Last updated: 2026-05-01 01:32:20 UTC