Aircraft Description
N9892 is a 1974 Grumman G-164A, a single-engine reciprocating (piston) aircraft registered to Redditt Air Service INC in Cleveland, MS. This aircraft holds a restricted airworthiness certificate issued by the Federal Aviation Administration on September 10, 1990. The registration certificate was issued on August 1, 2017. The registration is set to expire on August 31, 2027. Powered by a P&w PT6A SERIES engine producing 500 horsepower, N9892 is. The aircraft's Mode S transponder code is ADCF31 (hex), used for ADS-B identification and flight tracking. The FAA registry record for N9892 was last updated on March 10, 2023. AviatorDB monitors aircraft positions through ADS-B surveillance data and updates records as new position data is received.
Grumman Aircraft (later Northrop Grumman) was a major American aircraft manufacturer known for naval fighters in World War II and the Apollo Lunar Module. In general aviation, the Grumman American AA-5 and Tiger series remain popular sport aircraft. AviatorDB tracks 473 Grumman aircraft currently registered in the FAA database, including the G-164A model.
AviatorDB has found no NTSB accident or incident reports involving N9892. 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 |
|---|---|---|---|---|
| Jul 22, 2023 | CEN23LA317 | Substantial | None | A partial loss of engine power due to the failure of two compressor turbine blades as a result of the engine operating near or above the engine’s operating limits for an undetermined amount of time beyond the recommended engine’s TBO limit, which led to material creep and overload failure. |
| Jul 28, 2008 | CHI08CA217 | Substantial | None | The oil filler cap not reinstalled by the pilot prior to the aerial application flight and the total loss of engine oil during an aerial application. Additional causes were the low altitude of the operation and the unsuitable terrain encountered by the pilot during the forced landing. |
A partial loss of engine power due to the failure of two compressor turbine blades as a result of the engine operating near or above the engine’s operating limits for an undetermined amount of time beyond the recommended engine’s TBO limit, which led to material creep and overload failure.
The oil filler cap not reinstalled by the pilot prior to the aerial application flight and the total loss of engine oil during an aerial application. Additional causes were the low altitude of the operation and the unsuitable terrain encountered by the pilot during the forced landing.
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