WPR13LA112

Factual narrative

On February 2, 2013, about 1400 Pacific standard time, a Cessna 305A, N342FS, experienced a runway excursion at Camarillo Airport, Camarillo, California. The pilot/owner was operating the airplane under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The commercial pilot and a pilot-rated passenger were not injured; the airplane sustained substantial damage. The local personal flight departed Camarillo at 1300. Visual meteorological (VMC) conditions prevailed, and no flight plan had been filed.The pilot reported that the preflight detected no anomalies with the airplane. The departure and local area flight had been uneventful. The three-point landing was normal in minimal wind. Immediately upon touchdown, the pilot felt an extreme tail wheel vibration, and the airplane abruptly made a sharp left turn. The airplane veered off the runway, and the right main landing gear collapsed. The right wing, right aileron, right landing gear box, horizontal stabilizer, and right elevator sustained substantial damage. The pilot noted that post flight inspection revealed that the right rudder cable had broken. Examination by a Federal Aviation Administration inspector revealed that the rudder control cables for the front and back seats, which extend from the rudder pedals to the rudder control horn, had separated about 14 inches from the rudder pedals. This was in the vicinity of the collapsed right main gear attachment point. No observations were made that could account for the tail wheel vibration on touchdown. The National Transportation Safety Board Materials Laboratory examined the rudder control cables. The specialist conducting the examination determined that both cable fractures were consistent with overstress; no evidence of preexisting defects, such as corrosion or fatigue, was found. The pilot reported that, following an uneventful flight, the three-point landing was normal in minimal wind. Immediately upon touchdown, the pilot felt an extreme tailwheel vibration, and the airplane abruptly made a sharp left turn. The airplane then veered off the runway, and the right main landing gear collapsed. Postaccident examination revealed that the right rudder control cables, which extend from the rudder pedals at both the front and rear seats to the rudder control horn, had separated from the rudder pedals. No evidence of preexisting defects, such as corrosion or fatigue, was found; the rudder cables likely fractured due to overstress during the accident sequence and did not cause the loss of directional control. Postaccident examination of the airplane revealed no mechanical malfunctions or failures that would have precluded normal operation. The reason for the tailwheel vibration on touchdown and the subsequent loss of control could not be determined. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

FAA avdata. C = Cause, F = Factor.

• C Not determined-Not determined-(general)-(general)-Unknown/Not determined - C
• — Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Directional control-Not specified