1 fatality

25 May 2008: Nolan RV-4 (N6290F) — Kermeth Shane Owens — Tolani Lake, AZ

Tolani Lake, AZ, United States

On 25 May 2008, a Nolan RV-4 (registration N6290F) operated by Kermeth Shane Owens was involved in an aviation accident near Tolani Lake, AZ. One person was killed. Investigators recorded the probable cause as: An in-flight collision with terrain for undetermined reasons. This summary draws on records from NTSB.

SourcesNTSBPrimary reportUpdated 1778583330Data APIEditorial standards

On May 25, 2008, an amateur-built Nolan RV-4 (N6290F) impacted terrain near Tolani Lake, Arizona, killing the sole occupant pilot. The flight was from Payson, AZ, to Blanding, UT. No preimpact mechanical malfunctions were found.

History of Flight

On May 25, 2008, at approximately 0730 mountain standard time, an amateur-built Nolan RV-4 airplane, registration N6290F, was substantially damaged when it struck terrain near Tolani Lake, Arizona. The cross-country flight was operated under Title 14 Code of Federal Regulations Part 91 without a filed flight plan. Visual meteorological conditions prevailed. The private pilot, the sole occupant, was killed. The flight departed from Payson Airport, Payson, Arizona, around 0630, destined for Blanding, Utah. An Alert Notification was issued by the Federal Aviation Administration after the pilot's family reported the airplane overdue. The wreckage was located around 1200 by local cattle ranchers in an open sandy area.

Personnel Information

The 40-year-old pilot held a private pilot certificate with single-engine land and multi-engine land ratings. He was issued a third-class airman medical certificate on March 16, 2006, with no limitations. According to the pilot's logbook, as of the last entry on January 8, 2008, he had logged 257.4 total flight hours. Federal Aviation Administration records revealed that the pilot was involved in a previous accident in October 2006. During a subsequent reexamination, he failed to demonstrate proficiency on the ground portion. His private pilot certificate was suspended on April 4, 2008, and remained under suspension at the time of the accident.

Aircraft Information

The two-seat, low-wing, fixed-gear amateur-built airplane, serial number 002, was manufactured in 1998. It was powered by a Lycoming O-320-E2D engine rated at 150 horsepower, equipped with a fixed-pitch propeller. Airframe logbook records indicated the airframe and propeller underwent a conditional inspection on November 12, 2007, at a tach time of 446.1 hours. The engine logbook showed the most recent 100-hour inspection on the same date and tach time. The tachometer was observed at the accident site but damage prevented determining the current readings.

Meteorological Information

The automated surface observation system at Winslow Airport, Winslow, Arizona, about 29 miles south-southeast of the accident site, reported at 0756: wind from 120 degrees at 5 knots, visibility 10 statute miles, clear sky, temperature 11°C, dew point 3°C, and altimeter setting 29.95 inches of mercury.

Wreckage and Impact Information

Examination by an FAA inspector revealed the airplane impacted an open, flat sandy area. The first identified point of contact with terrain was consistent with the left wing. From that point to the main wreckage was approximately 34 feet. The left wing, left horizontal stabilizer, and left elevator were crushed upward. All primary flight controls were located at the accident site. Evidence of fuel was observed, and the ground was saturated with a liquid consistent with aviation 100 low-lead fuel about one inch below the surface within the fine sand. The wreckage was recovered to a secure location for further examination.

Medical and Pathological Information

The Coconino County Medical Examiner performed an autopsy on the pilot on May 29, 2008, determining the cause of death as "Multiple Blunt Force Injuries." The FAA's Civil Aeromedical Institute conducted toxicology tests, which were negative for carbon monoxide, cyanide, volatiles, and drugs.

Tests and Research

Examination of the recovered airframe and flight control system components revealed no evidence of preimpact mechanical malfunction. Examination of the engine showed the propeller remained attached to the crankshaft flange; one blade was straight and undamaged but cut by recovery personnel, while the opposing blade exhibited torsional twisting, trailing edge "S" bending, and chordwise striations across the cambered surface. Examination of recovered engine and system components revealed no evidence of preimpact mechanical malfunction.