N224MS is a 2025 Sonex SONEX B. It is a fixed-wing single-engine aircraft with 2 seats. The registration is active, with the registrant based in Venice, FL. Its experimental airworthiness certificate was issued in Jul 2025. It has been registered to its current owner since May 2025. This page also carries 1 NTSB event.
- 1 year old
- Only 8 Sonex SONEX B here
2025
That's everything on file so far — TailWiki checks the FAA registry daily and adds new entries as N224MS's record changes.
On October 15, 2015, about 1810 eastern daylight time, a Comp Air Inc. (Plambeck) CA8 experimental airplane, N224MS, was substantially damaged while landing at Ray Community Airport (57D), Ray, Michigan. The private pilot had minor injuries. Visual meteorological conditions prevailed at the time of the accident. The business flight was being conducted under the provisions of 14 Code of Federal Regulations Part 91 without a flight plan. The cross country flight departed Anniston Regional Airport (KANB), Anniston, Alabama, about 1315 central daylight time and was en route to 57D.
The pilot stated that while on a left downwind in the airport traffic pattern for runway 27, he extended 10 degrees of flaps. He completed a left base and extended full flaps while on a short final. Shortly after extending full flaps the left wing dropped. The pilot attempted to correct the left wing drop with right aileron and rudder; however, the airplane did not respond. The pilot elected to go around and increased engine power. The airplane pitched up and the left turn steepened. The pilot subsequently reduced engine power and with the resulting descent prepared for an impact with the ground. The airplane struck the ground short of the runway and the left wing separated from the fuselage. The pilot reported that the engine continued to run for about 15 minutes following the accident.
A Federal Aviation Administration inspector who responded to the accident established that the flight controls were free and correct and the flaps were completely extended. Further review and examination of the trim system revealed that the right aileron trim and left rudder trim were in positions consistent with a right turn and a left yaw. The examination of the airframe, flight controls, engine, and remaining systems revealed no mechanical anomalies that would have precluded normal operation prior to the accident.
The inspector interviewed a flight instructor who witnessed the accident. This witness reported that the airplane appeared to be in a cross controlled attitude or a skid while on final approach to the airport. The witness confirmed that it sounded as though there were several power changes during the final approach.
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