Synopsis
After takeoff, the engine of G-CJZU suffered a partial power loss that became more significant as the aircraft reached 300 ft above airfield level. The aircraft had little natural stall warning and was not fitted with an artificial stall warning device. A safe flying speed was not maintained, and the aircraft departed from controlled flight at a height from which recovery was not possible. It descended steeply and struck the ground nose first. The accident was not survivable.
Examination of the engine did not reveal any faults that could have caused or contributed to the power loss. The aircraft had sufficient fuel for the flight. Insufficient fuel supply from the tanks could have caused the power reduction, but impact and fire damage prevented assessment of the fuel system condition. A fault in the ignition system was also possible, but post-impact fire damage precluded full assessment. Weather conditions were conducive to carburettor ice formation during taxi, and carburettor ice could have caused the power loss after takeoff.
History of the Flight
G-CJZU had been advertised for sale. The passenger contacted the pilot to express interest and was invited to view the aircraft and experience a flight. After spending time with the aircraft, the pilot and passenger taxied for takeoff on Runway 32 at 1529 hrs. Power checks were completed, and takeoff began at 1533 hrs. After becoming airborne, the aircraft made a 20° right turn to avoid overflying East Lavant, as required by noise abatement procedures. Witnesses observed the aircraft appearing low and slow, struggling to climb.
CCTV footage showed the aircraft level or descending shortly after the turn, with a decrease in pitch attitude lasting about seven seconds before pitch increased again. Approximately 30 seconds later, the aircraft began a gentle left turn that quickly became unstable, with increasing bank angle and nose drop. The aircraft disappeared behind trees with a nose-low, high-bank attitude. It struck the ground at 1536 hrs, having turned almost 180° to face the aerodrome. Both occupants were fatally injured.
Accident Site and Wreckage
The wreckage was located in the corner of a field adjacent to a line of trees, confined to a small area. The aircraft was severely damaged and had been subject to an intense post-impact fire. The ground around the wreckage was fire-damaged and wet from foam applied by the Airfield Fire Service. The aircraft struck the ground nose first; the engine was partially lodged in clay-type soil and required a hydraulic lift for extraction. Splintered propeller parts were found, but no propeller witness marks were observed. The left wing had witness marks from ground contact. Cockpit control positions could not be determined due to impact forces and fire damage.
Recorded and Witness Information
Electronic devices recovered were damaged by fire and yielded no data. CCTV analysis showed the aircraft pass over the runway intersection at about 150 ft, level off for six seconds, then climb to about 300 ft over 26 seconds (average climb rate 350 ft/min). It then descended and rolled left into a steep dive. Witnesses described a cough from the engine followed by silence, then a sharp left bank with nose drop, and a thump upon impact followed by fire.
Aircraft Description
The Rogers Sky Prince is based on the Jodel D150 Mascaret, a two-seat low-wing tailwheel touring airplane of wood and fabric construction. G-CJZU was built in Spain in 2009, imported to the UK in 2017, and sold to the current owners in 2019. It was significantly heavier than a standard D150, with approximately 20% greater empty weight. The aircraft had wing fuel tanks and a large fuselage tank; normal practice was to leave the fuselage tank empty. The cockpit had brake pedals only on the left side. The fuel selector was mounted on the floor between the left seat pilot's legs and was reported to be difficult to reach, requiring the pilot to slip shoulder straps. The mixture control and carburettor heat control were similar in shape and size, differentiated only by knob color.
Examination
The main structure was severely fire-damaged. Steel control lines showed no loss of integrity, but control surfaces were destroyed. Electrical wiring suffered heat damage. The fuel system was fragmented; the electric fuel pump was in place but inlet and outlet pipes had separated. No fuel sample could be obtained. The main fuel selector valve was relatively undamaged. The engine was relatively intact but the carburettor was almost completely sheared off; the propeller hub remained attached with fragmented blades.