Aviation Crash Map

Bruce R Prouse M24 ORION PLUS N590DM

22 May 2022 · Cape Girardeau, Missouri, United States · Fatal

Summary

On 22 May 2022 at about 13:03 local time, a Bruce R Prouse M24 ORION PLUS registered N590DM was involved in an accident near Cape Girardeau, Missouri, United States. One person was on board and one died. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

The record

Date
at 13:03
Classification
Accident
Location
Cape Girardeau, Missouri, United States
Nearest airport
Cape Girardeau Regional Airpor (CGI)
Coordinates
37.2280, -89.5848
Aircraft
Bruce R Prouse M24 ORION PLUS
Registration
N590DM
Category
Gyrocraft
Year built
2022
Engines
1
Operator
Not recorded
Operating rule
Part 91: General Aviation
Purpose of flight
Personal
Phase of flight
Not recorded
Route
Unknown → Sioux Falls
Aircraft damage
Substantial
Weather
VMC
Light
Day
NTSB number
WPR22FA184

People

1 person died.

On board Died Serious Minor Uninjured
1 1 0 0 0

Probable cause

The pilot’s failure to maintain controlled flight, which resulted in a hard left roll, excessive blade flapping and a subsequent in-flight separation of the right horizontal stabilizer.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

The pilot was ferrying a gyroplane from Gulf Shores, Alabama, to his home in South Dakota. He made an overnight stopover in Cape Girardeau, Missouri, as part of his planned route of flight. The following morning he requested progressive taxi instructions from air traffic control to the assigned departure runway. After he taxied to the runway he departed to the northwest, consistent with what he told the controller. However, shortly into his climb, he reported to the controller that he wanted to return to the airport and the controller cleared him to land on his departure runway. The gyroplane flew the airport traffic pattern back to the runway to land; however, during the downwind leg the gyroplane rapidly descended to the ground following a loud crack that was heard by a witness at the airport. Postaccident examination of the gyroplane revealed no preimpact mechanical anomalies or malfunctions with the airframe or engine that could have precluded normal operation. Data retrieved from an onboard recording system suggests that the engine performance was unremarkable and consistent with the throttle movements throughout the final moments of the flight. Paint transfer marks on the rotor blades suggested that the main rotor contacted the horizontal stabilizer right winglet in the final moments of the accident flight, which was likely the source of the “crack” sound heard by the witness. The postaccident examination revealed evidence of severe blade flapping from a partial bend of the teetering stop of one of the main rotor blades and rotor contact with the horizontal stabilizer, which is typically due to a several-second low g or zero rotor load condition that slows the autorotation speed of the rotor. This condition was likely the result of the 270° hard left roll before the gyroplane rapidly descended and impacted the ground. Without the ability to maintain a load on the rotor in the full roll over, the rotor would have slowed and began severe flapping. The investigation was unable to determine the reason for such a severe control input (hard left roll) based on the available evidence. The evidence does indicate distress in the pilot’s voice and that he had opened his door at some point during the flight. There was no damage to the door latches and the door was found at the same distance from the main wreckage as the right horizontal stabilizer (about 170 ft). As a door annunciation would have informed the pilot if the door was not properly latched on takeoff, it is likely that this occurred in flight, and was possibly intentional if the pilot anticipated a hard landing. The accident was the result of the pilot’s failure to maintain controlled flight, which resulted in a hard left roll, excessive blade flapping, and a subsequent inflight separation of the right horizontal stabilizer.

Quoted verbatim from the NTSB record.

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