History of Flight
On June 1, 2008, at approximately 0816 mountain standard time, an amateur-built Van Heeswyk Lightning experimental airplane, registration N62JV, was substantially damaged when it impacted terrain while maneuvering near Marana, Arizona. The airplane was operated by the pilot under 14 CFR Part 91. The private pilot, the sole occupant, was killed. Visual meteorological conditions prevailed; no flight plan was filed. The flight originated from Ryan Field Airport, Tucson, Arizona, about 0559.
Witnesses near the accident site observed the airplane overfly a private airstrip at about 100 feet above ground level to the northwest. As it passed over the end of the airstrip, they saw the propeller assembly separate, followed by the engine revving up. The airplane then made a teardrop turn toward the airstrip, leveled on a southeasterly heading about mid-length, continued over the runway, then banked left and descended into terrain.
Pilot and Aircraft Information
The 62-year-old pilot held a private pilot certificate with an airplane single-engine land rating and a repairman experimental aircraft builders certificate. A third-class medical certificate was issued June 30, 2003, with the limitation "must wear corrective lenses for near and distant vision." According to logbook entries through May 19, 2008, he had 640.5 total flight hours, including 9.8 hours in the accident make/model. He had logged 5.3 hours in the previous 90 days and 2.2 hours in the previous 30 days.
The two-seat, low-wing, fixed-gear experimental airplane, serial number 7, was built by the owner/pilot. It was powered by a Jabaru 3300 engine rated at 120 horsepower, with a Sensenich EX-Pitch Composite propeller. According to FAA records, the airplane was registered to the pilot on November 8, 2007. The airframe logbooks show initial inspection and special airworthiness certificate on December 24, 2007, and most recent maintenance on May 4, 2008, at a total airframe time of 6 hours.
The Jabaru J ALL Constructors Manual (January 30, 2008) specifies installation instructions for the propeller flange extension, requiring Loctite 620 threadlocker and clean threads. Family members reported finding Permatex Medium Strength Threadlocker Blue in the pilot's toolbox.
Wreckage and Impact
The airplane came to rest upright in an open desert field near residential homes. The fuselage was partially separated aft of the cabin. The debris path was within a 30-foot circumference. Two undamaged bushes were noted near the right wing. All primary flight controls were located at the site. The propeller assembly and extension were found about 0.62 miles northwest of the accident site.
Medical and Pathological Information
An autopsy conducted by the Pima County Medical Examiner on June 2, 2008, determined the cause of death as blunt impact. Toxicology tests by CAMI found unspecified amounts of Alfuzosin and Metoprolol in blood and liver specimens; carbon monoxide, cyanide, volatiles, and other drugs were tested.
Tests and Research
On June 5, 2008, the airframe and engine were examined at Air Transport, Phoenix, Arizona. Flight control continuity was established with no mechanical anomalies. The engine remained attached but the propeller assembly and flange extension had separated from the crankshaft. The crankshaft, flange extension, and bolts were sent to the NTSB Materials Laboratory.
Examination showed that four of the six propeller flange extension attachment bolts were fractured at the threads where they intersected the forward face of the crankshaft. The fracture surfaces exhibited fatigue cracking and overstress. One bolt had a multifaceted fracture with multiple origins; its hardness was within specification. A light green material consistent with thread locking compound was observed between bolt and crankshaft threads.
Heavy fretting damage was found on the aft side of the propeller flange extension where it contacted the crankshaft forward face. Wear matching bolt thread patterns was observed in the attachment bolt holes. The flange extension surfaces were partially covered with silver paint that was flaking and easily removed. No paint was present on the mating surfaces to the crankshaft or propeller, but paint was found on the forward side of the extension in the bolt area including the washer contact area.