Aircraft Description
N4352F is a 1976 Piper PA-32R-300, a single-engine reciprocating (piston) aircraft registered to Bidzy Ta Hot Aana Corp in Dillingham, AK. This aircraft holds a standard airworthiness certificate issued by the Federal Aviation Administration on August 18, 1976. The registration certificate was issued on September 30, 2004. The registration is set to expire on April 30, 2028. The aircraft is configured with 7 seats. The aircraft's Mode S transponder code is A53855 (hex), used for ADS-B identification and flight tracking. The FAA registry record for N4352F was last updated on May 5, 2023. AviatorDB monitors aircraft positions through ADS-B surveillance data and updates records as new position data is received.
The Piper M600 represents the pinnacle of single-engine turboprop aviation, combining advanced safety technology with exceptional performance capabilities. First entering production in 2016, this low-wing single-engine aircraft seats six passengers and features the revolutionary Garmin Autoland system, making it the first certified aircraft with autonomous landing capability. Powered by a 600-shaft-horsepower Pratt & Whitney Canada PT6A-42A turboprop engine, the M600 achieves a maximum operating speed of 250 knots with a range exceeding 1,000 nautical miles. The aircraft is manufactured by Piper Aircraft Corporation at their Vero Beach, Florida facility. AviatorDB tracks 48,285 Piper aircraft currently registered in the FAA database. The ICAO type designator for this aircraft model is M600.
AviatorDB has found no NTSB accident or incident reports involving N4352F. 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 21, 2016 | ANC17LA014 | MINR | Serious | The failure of the nose landing gear to extend and lock due to the failure of the alternator and reduced battery power due to the cold ambient temperature, which prohibited the electrically-driven hydraulic pump from supplying adequate hydraulic pressure to extend the nose landing gear. The cause of the left main landing gear collapse could not be determined, as there were no postaccident anomalies or malfunctions found when the landing gear was actuated following replacement of the alternator and battery. |
| Sep 22, 2001 | ANC01LA145 | Substantial | None | An unlocked landing gear mechanism during landing roll. A factor associated with the accident was an electrical system failure. |
The failure of the nose landing gear to extend and lock due to the failure of the alternator and reduced battery power due to the cold ambient temperature, which prohibited the electrically-driven hydraulic pump from supplying adequate hydraulic pressure to extend the nose landing gear. The cause of the left main landing gear collapse could not be determined, as there were no postaccident anomalies or malfunctions found when the landing gear was actuated following replacement of the alternator and battery.
An unlocked landing gear mechanism during landing roll. A factor associated with the accident was an electrical system failure.
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