CEN25LA031

The pilot stated that he increased engine power to lift off and initiated a pedal turn toward the adjacent taxiway. He recalled that the helicopter made a “violent lurch” to the right, so he lowered the collective abruptly but that did not seem to make any difference. He did not remember anything further. Airport surveillance video footage captured the helicopter lift off and translate a short distance to the right. The right skid appeared to contact the ground again, and the helicopter immediately began rotating to the right. This was accompanied by dramatic pitch oscillations. The aft portion of the tailboom impacted the paved ramp surface, and the tailboom and empennage separated. Rotation of the helicopter continued until it collided with a nearby parked airplane. The helicopter sustained damage to both main rotor blades, the tailboom, tail rotor assembly, and the empennage. An examination helicopter did not reveal any preimpact anomalies consistent with an inability to maintain control of the helicopter. A review of the surveillance video indicated that the helicopter began a dynamic rollover when the right skid dragged on the ground immediately after lifting off. Based on the response of the helicopter, the pilot likely increased collective pitch to increase height but did not provide sufficient left anti-torque pedal input to counter the increased torque. The pilot was unable to regain control of the helicopter before it impacted the ground.

On October 27, 2024, about 0830 central daylight time, a Robinson Helicopter R-22 Beta, N7521Z, was substantially damaged when it was involved in an accident at the Pearland Regional Airport (LVJ), Pearland, Texas. The pilot sustained minor injuries. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot stated that he increased engine power to about 18 inches of manifold pressure to lift off and he started a pedal turn toward the adjacent taxiway. He recalled the helicopter made a “violent lurch” to the right and he lowered the collective abruptly but that did not seem to make any difference. The pilot did not remember anything further. Airport surveillance video footage showed the helicopter lift off and translate a short distance to the right. The right skid appeared to contact the ground again, and the helicopter immediately began rotating to the right. This was accompanied by pitch oscillations. The aft portion of the tailboom impacted the paved ramp surface, and the tailboom and empennage separated. Rotation of the helicopter continued until it collided with a nearby parked airplane. The helicopter sustained damage to both main rotor blades, the tailboom, tail rotor assembly, and the empennage. An examination of the helicopter confirmed flight control continuity from the cyclic and collective cockpit controls to the main rotor. Tail rotor control continuity was confirmed from the cockpit anti-torque pedals to the tailboom separation. Damage to the tail rotor control system aft of the tailboom separation was consistent with the impact damage. The examination did not reveal any preimpact anomalies consistent with an inability to maintain control of the helicopter.