Spécifications techniques
Technical data
Dimensions & Performance
| Dimensions | ||
| Length | 19 ft 7 1/2" | 5.98 m |
| Height | 8 ft 2" | 2.48 m |
| Wing span | 28 ft 5" | 8.65 m |
| Cabin width | 46 1/2" | 1.18 m |
| Baggage compartment volume | 10.1 cu.ft | 285 l |
| Weight & Quantities | ||
| Useful load | 640 lb | 292 kg |
| Max take-off weight | 1320 lb | 600 kg |
| Empty weight (standard a/c) | 680 lb | 308 kg |
| Empty weight (equipped a/c) | 747 lb | 339 kg |
| Max. baggage | 55 lb | 25 kg |
| Design load factors | +6 / -3 g | +6 / - 3 g |
| Operation load factors | +4 / -2 g | +4 / - 2 g |
| Wing tank capacity | 31.7 USgal | 120 l |
| Flight performance | Rotax 912 ULS 100 HP | |
| Never exceed speed | 146 KIAS | 270 km/h |
| Maximum level speed | 115 KCAS | 214 km/h |
| Cruise at 75% engine power | 110 KCAS | 204 km/h |
| Stall speed VS1 | 45 KCAS | 83 km/h |
| Stall speed VS0 (full flaps) | 40 KCAS | 74 km/h |
| Rate of climb | 1 020 ft / min | 7.5 m/s |
| Service ceiling | 15 500 ft | 4 720 m |
| Take-off run (concrete RWY) | 620 ft | 190 m |
| Landing run (concrete RWY) | 590 ft | 180 m |
| Range | 700 nm | 1 300 km |
| Under ISA conditions. All information can change without prior notice. | ||
Range diagram
Power plant
| Engine | Bombardier Rotax 912 ULS | |
| Number of cylinders | 4 | |
| Maximum power | 100 hp | |
| TBO | 2000 hrs | |
| Fuel consumption | 4.0 US gal / hr | 15 l / hr |
| Unleaded automotive gasoline RON95 / AKI91 / ASTM D4814 or AVGAS 100LL | ||
| Propeller | Fixed, on-glound or in-flight adjustable | |