Casualties unknown

2021-06-12: EUROCOPTER EC 120 B (HB-ZCA) — Lausanne "La Blécherette" Aéroport (LSGL), VD, CH

Lausanne "La Blécherette" Aéroport (LSGL), VD, CH

On June 12, 2021, an EUROCOPTER EC 120 B (registration HB-ZCA) was involved in an aviation accident near Lausanne "La Blécherette" Aéroport (LSGL), VD, CH. Investigators recorded the probable cause as: Loss of yaw control near the ground. This summary draws on records from the Swiss Transportation Safety Investigation Board (STSB / SUST).

Sourcesthe Swiss Transportation Safety Investigation Board (STSB / SUST)Primary reportUpdated 1785034239Data APIEditorial standards
Aircraft registered HB-ZCA
Aircraft registered HB-ZCA. Photo: Martin Abegglen from Bern, Switzerland / CC BY-SA 2.0, via Wikimedia Commons

On 12 June 2021, a Eurocopter EC120B helicopter experienced a loss of yaw control during a left turn after landing approach, leading to a hard landing. The pilot and four passengers were uninjured, but the landing gear was severely damaged.

Accident Overview

On 12 June 2021 at 11:39 local time, a Eurocopter EC120B helicopter (registration HB-ZCA) operated by Heli-Lausanne SA departed from Lausanne-La Blécherette aerodrome (LSGL) with five persons on board, including two children, for a pleasure flight towards Montreux and the Dents du Midi. The flight returned to the same airport.

Accident Sequence

Upon return, the helicopter approached for runway 18 and after a stabilized approach, the pilot initiated a left turn out of ground effect to reach the departure hangar tarmac. During this turn, the pilot was unable to stop the maneuver, and the helicopter performed several uncontrolled left rotations about the yaw axis before making a hard landing on the grass at the edge of the runway.

Aircraft and Damage

The helicopter came to rest in the grass with the right landing gear collapsed. The transversal structure of the landing gear was severely deformed on the right side, causing a significant tilt but without allowing the main rotor blades to contact the ground. No other visible damage was reported, and the pilot stated that the aircraft had no pre-existing defects.

Analysis and Conclusions

According to the investigation, the loss of yaw control resulted from inappropriate pedal input at the moment of stopping the turn, relative to the power demanded. The pilot's eventual reduction of power by lowering the collective prevented more serious damage. The manufacturer had issued an information notice (IN 3539-I-003) for this helicopter model equipped with a Fenestron tail rotor, noting that larger pedal displacements are required compared to a conventional tail rotor when transitioning from cruise to hover flight.

The accident was attributed to a loss of yaw control near the ground.

Probable cause

Loss of yaw control near the ground.

Investigation report by the Swiss Transportation Safety Investigation Board (STSB / SUST). Original record: https://www.sust.admin.ch/inhalte/AV-berichte/SumB_HB-ZCA.pdf. This page is a structured re-presentation; facts and quotes are in the Swiss Transportation Safety Investigation Board (STSB), Switzerland.