N3659YCessna 210C · 1963

On July 15, 2022, about 1815 eastern daylight time, a Cessna 210C, N3659Y, was destroyed when it was involved in an accident near Shelby, Michigan. The private pilot and one passenger were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The flight departed from runway 9 at Oceana County Airport (C04), Shelby, Michigan, with a destination of Warsaw Municipal Airport (ASW), Warsaw, Indiana. Two witnesses, who were both commercial pilots, were at the airport and observed the airplane depart. One witness reported that the ceiling at the time of takeoff was no higher than 100 ft, and the other witness reported that the airplane entered instrument meteorological conditions as it crossed a road about 1,300 ft past the departure end of the runway. Both witnesses reported that the visibility was poor and it was raining at the time.

Another witness, who owned the land were the airplane impacted the ground, was inside his home at the time. He heard a “big roar outside.” He got up to look, thinking it was a tractor-trailer going by his house. He then heard a “big bang,” looked outside his picture window, and saw smoke or dust. He realized that an airplane had crashed adjacent to his house in the woods and the big roar was the engine running and it was “revving up.” The entire sequence lasted about 30 seconds.

No recorded radar or automatic dependent surveillance-broadcast (ADS-B) data was recorded for the accident flight.

The pilot’s widow was asked if her husband showed any sense of urgency in commencing the flight in instrument weather conditions. She stated that their son was driving in a demolition derby race in Warsaw and her husband had missed his previous races and did not want to miss this race.

At the time of the accident, a low-pressure system was located in Iowa associated with a cold front and stationary front that stretched from Nebraska through southern Iowa and Illinois and eastward through Kentucky. Also, a mid-level trough was located above the accident site. Troughs and fronts can act as lifting mechanisms to help produce clouds and precipitation if sufficient moisture is present.

In addition to the Fremont, Michigan Municipal Airport (FFX) weather detailed in this report, C04 weather was provided to investigators by the airport manager. No ceiling information was available for C04; however, at 1815:03, the Automated Weather Observing System recorded wind from 130° at 5 knots, visibility 2 miles, temperature 17° C, relative humidity 98%, and an altimeter setting of 30.09 inches of mercury.

National Weather Service forecast information for the area surrounding the accident site included instrument meteorological conditions that were expected to persist beyond 2300. A search of the Leidos and ForeFlight systems revealed that the accident pilot did not request weather information from these providers before the flight.

The wreckage was located in a wooded area about 1.5 nautical miles southeast of C04. There was no fire. The wreckage was highly fragmented. The measured descent angle through the broken tree limbs was about 50°. All structural components of the airplane were accounted for within the wreckage path. Smooth, angular cuts, consistent with propeller blade contact, were found on several tree branches scattered throughout the wreckage path.

The right wing struck a large-diameter tree and was impact-separated from the fuselage. The right wing was located about 30 ft west of the fuselage. The right flap and a portion of the outboard right aileron were separated from the crushed wing structure. The nose of the aircraft impacted soft, sandy soil and the propeller was embedded about 4 ft deep into the ground.

The left wing was also impact-separated and was located about 40 ft east of the fuselage. The left wing was fractured into multiple pieces. The majority of the left flap and the left aileron remained attached to a section of the aft spar.

The empennage sustained significant compression damage and remained attached to the crushed fuselage. The left and right horizontal stabilizer and both elevators remained attached. The vertical stabilizer and rudder sustained tree impact damage at approximately mid-span. An approximate 3-ft section of the top of the rudder, with the balance weight attached, was found adjacent to the empennage.

Control cable continuity within the flight control system was not established due to the general fragmentation of the wreckage and multiple impact-related cable separations. The hydraulic flap actuators indicated the flaps were in the fully retracted positions.

The fuel tanks were fragmented, and pieces of rubber bladder were observed throughout the accident site; no residual fuel was observed.

The instrument panel was fractured into multiple pieces. The directional gyro, attitude indictor, and turn coordinator were found near the impact crater. The gyro instruments were disassembled by investigators. All three gyros exhibited minor scoring, indicative of rotation at the time of impact. The airspeed indicator was separated and recovered from the impact crater. The needle was bent aft and captured in place near 230 knots indicated airspeed.

Engine compression and valve train continuity could not be established due to impact damage. The magnetos were found loose on top of the engine. Both magnetos sustained impact damage and spark was not produced. The top spark plugs were removed and exhibited normal color and wear when compared to a Champion inspection chart. The engine accessories, including the engine-driven hydraulic pump, fuel pump, vacuum pump, and alternator, were impact-separated from the engine. The fuel pump drive coupling and vacuum pump coupling were found intact. The fuel control inlet screen and fuel manifold screen were clean and free of obstructions. Fuel was observed inside the manifold during disassembly. The oil filter paper element was clean.

The propeller assembly was found in the impact crater. One propeller blade was separated from the hub. It was twisted, bent aft, and exhibited polishing and chordwise scratches on the cambered side. The second propeller blade remained attached to the hub. It was bent aft approximately 90 degrees at mid-span. Chordwise scratches were observed on the face of the second blade near the propeller hub, consistent with rotation at the time of bending and impact with the engine cowling.

According to Medical Examiner’s autopsy report from the Western Michigan University School of Medicine, Kalamazoo, Michigan, the cause of death of the pilot was multiple severe injuries and the manner of death was accident. Testing for ethanol and drugs was negative.