What happened
On February 19, 2016, a Hughes 269C helicopter was conducting a proficiency check to extend the pilot's type rating. The flight began in Bamberg, where the two occupants performed practice autorotations near a model aircraft field. Following these maneuvers, the crew proceeded to the Ebern-Sendelbach landing field for a specific training exercise: an autorotation from cruise flight without touchdown, approaching runway 14.
After successfully completing the initial maneuver, the crew performed a steep takeoff from runway 32. While climbing at approximately 150 feet above ground level, the aircraft reached a speed of about 45 knots. During the climb, the examiner simulated an engine failure by reducing the throttle. In response, the pilot initiated an autorotation. While the rotor RPM remained within the green arc and airspeed stabilized above 50 knots, the descent rate was noted to be steeper than usual, appearing nearly vertical. During the attempt to flare and cushion the landing, the helicopter continued to sink and made a hard impact with the ground at approximately 12:00 PM.
Both occupants were able to exit the destroyed aircraft independently. They sustained two minor injuries and were able to alert emergency services.
The investigation
The BFU investigation examined the flight sequence, the aircraft's condition, and the environmental factors. The investigation confirmed that the helicopter, a 2000-model Hughes 269C, was operating at a weight of approximately 850 kg. The investigators analyzed the flight path and the physical evidence at the crash site, which included skid marks on the grass runway and the final resting position of the aircraft on its side.
Technical examination of the wreckage showed no evidence of mechanical failure or engine malfunction prior to the simulated failure. The investigation also reviewed the flight manual performance limits, noting that at the aircraft's weight, the calculated distance from the start of the maneuver to ground contact would be approximately 902 meters.
Findings
- The aircraft was performing a simulated engine failure maneuver as part of a proficiency check.
- The descent rate during the autorotation was significantly steeper than normal, described by the examiner as nearly vertical.
- The high rate of descent prevented a successful flare and cushioning of the landing, leading to a hard impact.
- There were no pre-existing technical issues with the engine or the helicopter's systems prior to the simulated failure.