What happened
On April 2, 2005, a Tecnam P 92 ECHO, registration PH-2V6, was performing an overland flight at Lelystad Airport. The aircraft, a Micro Light Aeroplane (MLA), was operated by the owner, who was conducting his first flight as the new owner of the aircraft, accompanied by one passenger. The flight proceeded normally until the final approach to runway 05, which was in use under wind conditions of approximately 10 to 15 knots from 100 degrees.
During the approach, with flaps fully extended and a speed of roughly 90 km/h, the pilot noticed the aircraft was flying too low near the RDW Test Center dike and applied additional power. Shortly after passing the dike, the aircraft drifted to the left. The pilot attempted to correct this movement using the ailerons and rudder, but was unsuccessful. The aircraft struck the grass runway forcefully, making contact first with the left wheel, followed by the nose wheel and the right wheel. The propeller subsequently struck the ground and broke off. The aircraft came to a halt approximately 2mm after the initial impact. There were no injuries to the occupants, though the aircraft sustained significant damage to the engine, engine mount, and left wing.
The investigation
Because the aircraft is classified as an MLA and does not meet international airworthiness certification standards, the Dutch Safety Board (OVV) conducted a limited investigation based on data provided by the pilot and the National Police.
The investigation focused on the aircraft's weight and wind conditions. While the crosswind component of approximately 10 knots was within the pilot's stated limit of 15 knots, the investigation revealed a significant weight discrepancy. No weight calculation had been performed by the pilot prior to departure. Based on provided data, the estimated takeoff weight was approximately 502 kg, which exceeded the maximum allowable weight of 450 kg by roughly 11%. By the time of landing, the estimated weight was approximately 489 kg, still exceeding the limit by 39 kg.
Findings
- The aircraft was operating significantly above its maximum allowable weight during both takeoff and landing.
- The aircraft's airspeed likely dropped below the stall speed during the final approach, leading to an aerodynamic stall.
- While the overweight condition increased the stall speed, the investigation determined this increase was too minor to be the primary cause of the loss of control.