N7521Z

Substantial
Minor

ROBINSON HELICOPTER R22 BETAS/N: 3810

Accident Details

Date
Sunday, October 27, 2024
NTSB Number
CEN25LA031
Location
Pearland, TX
Event ID
20241028195385
Coordinates
29.521278, -95.242139
Aircraft Damage
Substantial
Highest Injury
Minor
Fatalities
0
Serious Injuries
0
Minor Injuries
1
Uninjured
0
Total Aboard
1

Probable Cause and Findings

The pilot’s failure to maintain control of the helicopter during lift off.

Aircraft Information

Registration
Make
ROBINSON HELICOPTER
Serial Number
3810
Engine Type
Reciprocating
Year Built
2005
Model / ICAO
R22 BETAR22
Aircraft Type
Rotorcraft
No. of Engines
1
Seats
2
FAA Model
R22 BETA

Registered Owner (Current)

Name
VERACITY AVIATION LLC
Address
395 BEECHCRAFT LN
City
SEGUIN
State / Zip Code
TX 78155-2510
Country
United States

Analysis

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.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CEN25LA031