Incident Details
On June 29, 2021, at 1347 eastern daylight time, a Bell 206B helicopter (registration N134VG) was substantially damaged during an accident at Griffiss International Airport in Rome, New York. The pilot and two pilot-rated passengers sustained minor injuries. The flight was conducted under Title 14 Code of Federal Regulations Part 91 as an instructional flight for an initial Part 135 competency check ride. On board were two Federal Aviation Administration (FAA) aviation safety inspectors: one in the left front seat conducting the check ride and another in the left rear seat providing oversight.
Maneuver and Sequence
According to the pilot, after performing maneuvers, the flight returned to the airport for a straight-in autorotation with a powered recovery to runway 33. He briefed the inspectors, executed clearing turns and landing checks, and entered the autorotation at 1,500 feet mean sea level. He reduced collective and throttle to idle, maintaining 65 knots. Before the flare, he advanced the throttle to full open and noted rotor RPM in the green arc. When he raised the collective for recovery, the low rotor warning activated, the engine lost partial power, and the helicopter landed hard on the runway and rolled onto its left side.
The front-seat FAA inspector stated that as the pilot reduced collective, he observed a needle split on the tachometer, concluding throttle reduction. He did not notice yaw. The descent was smooth, but at recovery initiation, he noted the helicopter was slightly high (above 100 feet AGL). He checked the throttle by attempting to rotate it—it did not move. As the low rotor horn sounded, he glanced at the tachometer but could not see it; upon looking back, the helicopter impacted the ground. After the helicopter came to rest with the engine running, he rotated the right-side throttle to idle, requiring multiple attempts, then to off.
The rear-seat inspector stated that the maneuver was initiated properly, but the deceleration was too high and aggressive. He heard the low rotor warning continue and tried to check RPM before impact.
Examination Findings
Post-accident examination revealed substantial damage to the fuselage above the windscreen and left horizontal stabilizer. Drive continuity was established in the main transmission and tail rotor system. Main rotor blades exhibited detached tips, trim tab separations, and fragmenting. The throttle functioned correctly in all positions when manipulated by hand, with proper corresponding fuel control unit pointer positions. The fuel valve switch was on, the shutoff valve was full open, fuel appeared clear, and the fuel filter was unobstructed. Control continuity was confirmed.
Engine and transmission chip detectors, fuel and oil filters were debris-free. A borescope examination showed metal splatter in the combustion chamber, consistent with ingestion of metallic fragments during combustion. No pre-accident engine anomalies were found.
Maintenance History
The most recent 100-hour inspection occurred on April 19, 2021, about 60 flight hours before the accident. Subsequent maintenance included replacement of the turbine outlet temperature indicator (May 14, 2021) and fuel cell replacement (June 4, 2021) with drain valve replacement (June 11, 2021).
FAA Guidance
The FAA Helicopter Flying Handbook notes that the straight-in autorotation with powered recovery requires precise coordination of throttle and collective to avoid loss of rotor RPM. Common errors include failure to coordinate throttle and collective properly and late engine power engagement.