Casualties unknown

Emergency Landing in a Field Following Engine Power Loss on Ouessant (F-GGXZ)

FR

On May 23, 2010, a Robin DR400-180 (registration F-GGXZ) was involved in an aviation accident near FR. This summary draws on records from the French Bureau d'Enquêtes et d'Analyses (BEA).

Sourcesthe French Bureau d'Enquêtes et d'Analyses (BEA)Primary reportUpdated 2026-09-13Data APIEditorial standards

A Robin DR400-180 (F-GGXZ) made an emergency landing in a field near Ouessant on May 23, 2010, after losing engine power during the final approach. The aircraft sustained damage to the nose gear and propeller, while the pilot and passenger were unharmed.

Incident Overview

On May 23, 2010, at approximately 11:00 local time, a private Robin DR400-180 with registration F-GGXZ experienced a loss of engine power while on final approach to runway 06 at Ouessant. The aircraft was operating under general aviation rules and carried one pilot and one passenger. Following the power loss, the pilot executed an emergency landing in a field located approximately 850 meters south of the runway.

Flight Details and Immediate Actions

The flight originated from Brest-Bretagne with a planned cruise altitude of 1,500 feet. During the downwind leg, the pilot performed standard pre-landing checks, including activating the electric fuel pump, extending the carburetor heat, deploying flaps, and switching the fuel selector from the left tank to the main tank. The engine was running at 1,600 rpm to maintain a speed of 150 km/h.

Approximately thirty seconds later, the pilot noticed brief engine misfires. In response, he advanced the throttle fully. While the engine RPM initially increased, power was suddenly lost. Realizing a runway landing was impossible, the pilot diverted to a nearby field. During the rollout, the nose landing gear broke, and the engine cowling and one propeller blade were damaged.

Investigation Findings

The pilot held a PPL(A) license with 380 total flight hours. Pre-flight checks had revealed no anomalies. Meteorological data indicated temperatures between 15 and 20 °C with a dew point of 11 °C, conditions conducive to carburetor icing, especially given the reduced power setting during the approach.

Examinations of the engine, propeller, and fuel system revealed no technical failures. The damage to the propeller indicated low or zero power at the time of impact. A post-repair test flight using the remaining fuel was completed without issue. The investigation could not definitively determine the cause of the power loss. While carburetor icing was a possibility due to environmental conditions, it could not be formally established. Additionally, a potential error in positioning the fuel selector between the 'closed' and 'main' positions, which are adjacent on the control panel, could not be ruled out.