No fatalities

27 Oct 2024: ROBINSON HELICOPTER R22 BETA (N7521Z) — Veracity Aviation — Pearland, TX

Pearland, TX, United States

On 27 Oct 2024, a ROBINSON HELICOPTER R22 BETA (registration N7521Z) operated by Veracity Aviation was involved in an aviation accident near Pearland, TX. No fatalities were reported. Investigators recorded the probable cause as: The pilot’s failure to maintain control of the helicopter during lift off. This summary draws on records from NTSB; 12 related events involving the same aircraft type or operator are linked below.

SourcesNTSBPrimary reportUpdated 1778583330Data APIEditorial standards

On October 27, 2024, a Robinson R-22 Beta (N7521Z) sustained substantial damage after a loss of control during takeoff at Pearland Regional Airport, Texas. The pilot received minor injuries.

Accident Details

On October 27, 2024, at approximately 0830 central daylight time, a Robinson Helicopter R-22 Beta, registration N7521Z, was substantially damaged during an accident at Pearland Regional Airport (LVJ) in Pearland, Texas. The pilot, who was the sole occupant, sustained minor injuries. The flight was being conducted as a personal flight under Title 14 Code of Federal Regulations Part 91.

Pilot Account

The pilot reported that he increased engine power to about 18 inches of manifold pressure to lift off and initiated a pedal turn toward the adjacent taxiway. He recalled the helicopter experiencing a “violent lurch” to the right. In response, he lowered the collective abruptly, but that action did not seem to have any effect. The pilot did not remember any further events.

Video Evidence

Airport surveillance video footage captured the sequence of events. After liftoff, the helicopter translated a short distance to the right. The right skid appeared to contact the ground again, at which point the helicopter immediately began rotating to the right. This rotation was accompanied by pitch oscillations. The aft portion of the tailboom then struck the paved ramp surface, causing the tailboom and empennage to separate. The helicopter continued rotating until it collided with a nearby parked airplane.

Damage and Examination

The helicopter sustained damage to both main rotor blades, the tailboom, tail rotor assembly, and the empennage. A postaccident examination confirmed flight control continuity from the cyclic and collective cockpit controls to the main rotor. Tail rotor control continuity was verified from the cockpit anti-torque pedals to the point of tailboom separation. Damage to the tail rotor control system aft of the separation was consistent with impact forces. The examination found no preimpact anomalies that would have prevented maintaining control of the helicopter.

Probable Cause

No probable cause was stated in the source.

Contributing factors

PilotPerformance/control parameters — Not attained/maintained