Jean, NV, USA
N6064C
Commander 114
The pilot departed on a personal cross-country flight in night visual meteorological conditions. While approaching and maneuvering to land at the destination airport, the airplane made a right turn consistent with a right base turn to the destination runway. As the airplane began the base-to-final turn, just before entering a small cloud, it entered a steep, nosedown spin. Subsequently, the airplane impacted terrain and a postimpact fire ensued. The airplane damage and ground scars at the accident site were consistent with a near wings-level attitude at the time of impact. Postaccident examination of the airplane and engine revealed no preimpact anomalies or malfunctions that would have precluded normal operation. It is likely that, while maneuvering to avoid the cloud, the pilot failed to maintain the proper airspeed, which resulted in the airplane entering an accelerated stall.
HISTORY OF FLIGHTOn September 5, 2018, about 2145 Pacific daylight time, a Commander Aircraft Company AC-114TC, N6064C, was destroyed when it was involved in an accident near Jean, Nevada. The private pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. A review of the Nevada’s Department of Transportation, traffic camera video, showed the accident airplane flying west of and parallel to Interstate 15. The airplane turned to a course consistent with a right base turn to runway 20R at Jean Airport (0L7). The airplane then began another right turn and about halfway through the turn and just before entering a small cloud, the airplane entered a steep nose-down descent and spin then impacted the ground. A post impact fire ensued that consumed most of the airplane. AIRCRAFT INFORMATIONThe airframe and engine maintenance logbooks were not located during the investigation. AIRPORT INFORMATIONThe airframe and engine maintenance logbooks were not located during the investigation. WRECKAGE AND IMPACT INFORMATIONThe airplane impacted desert terrain populated with light vegetation about 1 mile north of 0L7. The site was surveyed by the National Transportation Safety Board (NTSB) drone support team. The debris field was determined to be about 280 ft in length. The first point of impact was a large disturbance in the ground which was consistent with the front of the airplane and wings impacting terrain at a near wings level attitude. The area of disturb dirt measured about 10 ft lengthwise, 28 ft wide, and 2 ft in depth at the middle portion and 6 inches in depth where the wings impacted terrain. Several parts of the airplane’s fuselage and wings were located within the disturbance. Parts of the left-wing tip were observed on the left edge of the ground disturbance. A burnt fan pattern was observed on the desert sand forward of each wing, consistent with fuel being sprayed out during impact and then being ignited. All major structural components and primary flight controls of the airplane were located at the accident site. The main wreckage consisted of the fuselage, engine, wings, and empennage. The fuselage was mostly consumed by the postimpact fire. The engine remained attached to the fuselage. The front of the aircraft and cabin area were destroyed during the impact sequence and the postimpact fire. The empennage was folded under the left wing and remained partially attached to the fuselage; the tail cone had separated. The airplane was identified by the registration plate located in the aft fuselage. The leading edges of the wings displayed compression and impact damage. The vertical stabilizer was almost entirely consumed by the fire. The rudder remained attached to the vertical stabilizer. The elevators remained attached to the empennage, and the elevator trim was observed near the neutral position. Flight control continuity was established from the ailerons to the cockpit controls. Flight control continuity was also established to the rudder and elevator despite observed overload separations of flight control cables. Both the left and right wings remained attached to the fuselage. Both ailerons and flaps were attached. The right aileron remained partially attached only by the outboard connection. The engine displayed impact and thermal damage. The three-bladed propeller remained attached and one blade was bent aft near the hub. Another blade was intact and was bent and curled near the tip. The third blade was intact and exhibited gouging, torsional twisting, and chordwise striations across the cambered surface and trailing edge. The landing gear was observed in the extended position. Additionally, impact marks and damage on the main landing gear assembly were consistent with the gear in the extended position. The cockpit area sustained substantial thermal damage and no instrumentation was readable. The fuel selector handle was not observed. The examination of the airframe and engine revealed no evidence of mechanical malfunctions or failures that would have precluded normal operation. ADDITIONAL INFORMATIONAccident Environment A right traffic pattern to land on runway 20R at 0L7 would place the base turn in a relative position close to where the accident site was located. Over a two-day period following the accident, several airplanes landing to the south at 07L were observed flying directly over the accident site, while on the base leg turn to land on runway 20R. MEDICAL AND PATHOLOGICAL INFORMATIONThe Clark County Coroner/Medical Examiner Office, Las Vegas, Nevada, conducted an autopsy on the pilot. The medical examiner determined that the cause of death was “multiple blunt force injuries.” The FAA's Forensic Sciences Laboratory performed toxicological testing on the pilot. Testing was negative for drugs and volatiles, except for ethanol detected in the brain and muscle specimens. Some or all of the ethanol may be from sources other than consumption.
The pilot failed to maintain adequate speed while maneuvering at a low attitude during night and entered an aerodynamic stall and subsequent spin.
Source: NTSB Aviation Accident Database
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