Fatal Gyrocopter Crash Near Wellton, Arizona (N618TC)

Accident Overview and Flight History On December 23, 2012, at approximately 1427 mountain standard time, a Charland Vortex gyrocopter, registration N618TC, sustained substantial damage after impacting terrain near a private airport in Wellton, Arizona. The aircraft was registered to and operated by the pilot under Title 14 Code of Federal Regulations Part 91. The local personal flight departed the private airport around 1400, and no flight plan was filed. Visual meteorological conditions prevailed at the time of the accident. The sole occupant, a private pilot, was fatally injured. A witness, who was also a gyrocopter pilot and personally knew the accident pilot, reported that they were flying in the traffic pattern together in separate gyrocopters. The two pilots were performing touch-and-go landings with left turns at approximately 400 feet above ground level while maintaining radio contact. The witness noted that the accident pilot had replaced the oil sump before the flight that day. During the touch-and-go maneuvers, the witness observed normal and unremarkable performance from the accident gyrocopter. The witness had landed and was attempting another takeoff when he noticed the wreckage of the accident gyrocopter to his left. He aborted his takeoff and proceeded to the crash site to render assistance. A second witness near the airport reported seeing and hearing the gyrocopters flying around the airport. He observed a gyrocopter at approximately 100 feet above the ground, descending and hitting the ground hard, nose first. He estimated the descent angle to be about 45 degrees. Upon arriving at the accident site, this witness observed fuel leaking from the gyrocopter. ## Personnel Information The pilot, age 64, held a private pilot certificate with single engine, glider, and sport ratings. He was issued a third-class airman medical certificate on April 27, 2007, with no limitations stated. On his most recent medical certificate application, the pilot reported 80 total flight hours and 4 hours in the last six months. According to the pilot's logbook, he had accumulated 126 total flight hours. The total time logged in the accident gyrocopter was 13.3 hours. ## Aircraft Information The single-seat gyrocopter, serial number 020, was manufactured in 2007. It was powered by a Rotax type 582 engine, serial number 4656450, rated at 65 horsepower. The gyrocopter was equipped with a warp drive and a three-blade, fixed-pitch propeller. ## Meteorological Information Recorded data from the Yuma Marine Corp Air Station automated weather observation station, located about 39 miles south of the accident site, showed conditions at 1355 as wind from WNW at 5.8 knots, visibility 10 statute miles, clear sky, temperature 64.9 degrees Fahrenheit, dew point 33.1 degrees Fahrenheit, and an altimeter setting of 30.07 inches of Mercury. Using the reported weather conditions and field elevation, the calculated density altitude was about 844 feet. ## Wreckage and Impact Information The National Transportation Safety Board (NTSB) investigator-in-charge examined the accident site and found that the gyrocopter impacted terrain about 40 feet west of runway 16 at coordinates 32:39.528N and 114:00.433W, at an elevation of 443 feet. All major structural components were located within an 85-foot-long debris path, which consisted mostly of broken propeller blade portions. The first identified point of contact (FIPC) was a small area of disturbed dirt about 6 feet from the main wreckage, containing portions of the nose gear assembly and nose cone assembly. The gyrocopter came to rest inverted on a heading of about 090 degrees magnetic, approximately 6 feet from the FIPC. The rotor blades, empennage, and engine remained partially attached to the main fuselage. No thermal damage was observed, but the main structure and engine mounts sustained impact damage. Several separations were observed in the upper main structure. Examination of the airframe and flight control system components revealed no evidence of anomalies that would have precluded normal operation. The engine examination showed remnants of the three-bladed constant speed propeller attached to the crankshaft flange. The propeller had impact damage, and all three composite blades were separated about mid-span. One propeller blade exhibited splitting from delamination and was bent about 90 degrees at mid-span, while the other blades broke in numerous portions. The engine was rotated by hand through the propeller hub assembly, establishing rotational continuity throughout the engine and valve train. Compression and suction were obtained on all cylinders. The oil reservoir was intact and about half full. The engine exhaust system had impact damage but remained attached to all cylinders. The engine examination did not reveal any anomalies that would have precluded normal operation. ## Medical and Pathological Information The Yuma County Regional Medical Center conducted an autopsy on the pilot on December 25, 2012. The medical examiner determined the cause of death was blunt force trauma. The FAA's Civil Aeromedical Institute (CAMI) in Oklahoma City, Oklahoma, performed toxicology tests on the pilot. According to CAMI's report, tests for carbon monoxide, cyanide, volatiles, and drugs yielded negative findings. ## Tests and Research Investigators examined the wreckage at the facilities of Air Transport in Phoenix, Arizona, on February 22, 2013. A complete report of the airframe and engine examination is in the public docket. The post-accident examination revealed no evidence of mechanical anomalies or failures that would have precluded normal operation.