History of the Flight
On 7 September 2024, a single-engine ATEC v.o.s. Zephyr 2000, registration EI-GCT, departed from a local private grass strip for a local flight. The aircraft had flown two short legs earlier that day. The accident flight, of 15 minutes duration, routed north around the Stranolar area then turned south-east towards Finn Valley Airfield, Co. Donegal, with the intention to land on Runway 03.
While on the downwind leg, immediately after the pilot reduced throttle to decelerate, the engine began to run roughly and the instrument panel vibrated. Suspecting carburettor icing, the pilot manipulated the throttle in an attempt to clear any ice. The engine continued to run roughly, and when the throttle was closed and then advanced, the engine stopped.
The pilot selected first stage of flap, pitched for best glide speed of 54 knots, turned on the auxiliary electric fuel pump, and attempted to restart the engine while turning towards the runway. The propeller was observed turning but the engine did not restart. During the final turn to align with the runway, the aircraft had lost sufficient energy. Before impact, the pilot selected full flap and pulled back on the elevator. The aircraft made ground contact as it 'pancaked' onto the airfield's boundary hedge, approximately four metres short of the runway. There was no ground scoring leading to the final position. The pilot exited unaided and uninjured. There was no fire.
Aircraft and Engine Information
The ATEC Zephyr 2000 is a low-wing ultralight aircraft with a fixed tricycle undercarriage, manufactured in 2001. It was powered by one Rotax 912-UL engine, 80 hp, driving a two-bladed ground adjustable propeller. The engine had accumulated 1,505.1 hours total time. The aircraft was operated on a Flight Permit issued by the Irish Aviation Authority (IAA), valid until 8 June 2025. The fuel system included a mechanical pump feeding two carburettors.
Post-Accident Inspection and Tests
Investigators inspected the carburettors at the site; fuel was present in both float chambers. A fuel sample was taken for laboratory analysis. The fuel system vent line was checked and found to be venting correctly and its routing compliant with the engine manufacturer's installation manual. The aircraft was recovered to a hangar, and the pilot performed an engine test start in the presence of investigators. The engine started on the first attempt and idled smoothly within expected parameters.
Injuries and Damage
No injuries were reported. The aircraft sustained substantial damage: the left wing was broken at two points, the nose landing gear, left flap and right wingtip separated, propeller blades fractured, and forward fuselage panelling showed cracks and breaks consistent with impact. No evidence of fuel spillage was found. No other damage was reported.