Event WPR13LA063

Factual narrative

On December 2, 2012, at 1430 mountain standard time, an experimental exhibition AeroTek Pitts S-1T, N49309, experienced a flight control malfunction during the landing flare. The airplane landed hard on runway 28L, and departed the runway surface at the Billings Logan International Airport (BIL), Billings, Montana. After departing the runway surface, the airplane nosed over resulting in substantial damage to the tail section and the top wing. The pilot operated the airplane under the provisions of 14 Code of Federal Regulations Part 91 as a personal flight; he was not injured. Visual meteorological conditions prevailed for the local area flight, and no flight plan had been filed. The pilot stated that he had taken a 40-minute flight, with no problems encountered, and returned to land at his home airport. Upon touchdown, he was not able to maintain control of the airplane, and as it moved to the left edge of the runway, he added power to abort the landing. The airplane became airborne, and he was cleared to land again on runway 28L. The airplane touched down, and the pilot again was not able to gain control of the airplane. As the airplane moved to the right edge of the runway, the pilot realized he would not be able to abort the landing. The airplane departed the runway surface, something caught in the dirt, and the airplane nosed over. The pilot reported that the weld that attached the tail wheel tube to the fuselage had separated. A Federal Aviation Administration (FAA) inspector responded to the accident site. During an inspection of the airplane, he noted a broken tail wheel support bracket, which allowed the tail wheel assembly to freely move left and right without corresponding rudder input. The pilot reported to him that the support bracket failure was found when the airplane was still inverted. After completing a personal flight, the pilot was returning to his home airport. He stated that on the first landing attempt, he was not able to maintain directional control of the airplane during the landing roll, and he aborted the landing. On the second landing attempt, he again was not able to maintain directional control and subsequently realized that there was not enough remaining runway for him to successfully abort the landing. The airplane departed the runway surface and nosed over, coming to rest inverted. Postaccident examination of the airplane revealed that the weld that attached the tailwheel tube to the fuselage had separated. This would have allowed for the tailwheel assembly to freely move left and right without corresponding rudder input, and thus the pilot would not be able to maintain directional control during the landing roll. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

Hierarchical cause / factor breakdown from the FAA bulk avdata database. Each finding tagged C (Cause) or F (Factor).

• C Aircraft-Aircraft structures-Fuselage-Gear attach fittings (on fus)-Failure - C
• C Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Directional control-Attain/maintain not possible - C