TYPE: Aerobatic two-seat sportplane/kitbuilt.
PROGRAMME: Prototype CR100 (F-PDYN) first flew 27 August 1992; third aircraft (F-PAFC) was designated CR100D); first five CR100s flew total of 600 hours of aerobatics in first year of operations. Available factorybuilt or as a kit.
CURRENT VERSIONS: CR100: Baseline version. Prototype (FWASP).
CR100T: Tricycle landing gear version, first flown December 2000. Description applies to CR100, except where otherwise stated.
CR110: Uprated version with 149 kW (200 hp) Textron Lycoming engine.
CR120: High-agility version. First flight (F-PPCR) September 1996; second aircraft (F-PTCR) flying by 1998. Engine as CR110, but airframe all carbon fibre; longer span ailerons (2.70 m; 8 ft 10¼ in), no flaps, shorter wing span (7.77 m; 25 ft 6 in), 270°/s rate of roll at 140 kt (260 km/h; 162 mph) compared with CR100's 195°/s,149 kW (200 hp) Textron Lycoming AEIO-360 engine driving MTV-12-B-C/C-183-17e two-blade propeller, 85 litres (22.4 US gallons; 18.7 Imp gallons) aerobatic fuel in starboard wingroot and 105 litres (27.7 US gallons; 23.1 Imp gallons) in port wingroot, tyre pressure 2.00 bar (29.0 lb/sq in). Aircraft are registered under CR100 designation.
CUSTOMERS: Two CR100s ordered March 1995 by l'Equipe de Voltige de l'Armee de l'Air at Salon de Provence, of which first (No. 22 'CJ') delivered 21 July 1995; however, both withdrawn by 1997 and sold in 2000, one to UK owner Cole Aviation. Total of at least 37 CR100/110/120kits sold; of these, 16 had been registered by early 2002.
COSTS: €76,200 as a kit without engine; about €137,200 assembled, with engine and instruments (2005).
DESIGN FEATURES: Single-engined low-wing monoplane of conventional layout. Aerofoil section NACA 21015/12 modified; dihedral 0°.
FLYING CONTROLS: Conventional and manual. Elevator tab for pitch trim. Ground-adjustable tab on ailerons on rudder. Plain flaps.
STRUCTURE: Wood and fabric, but including carbon fibre main wing spar.
LANDING GEAR: Tailwheel type; fixed. Oleo-pneumatic shockabsorption. Speed fairings on mainwheel legs. Disc brakes. Mainwheel tyre size 380x150; pressure 2.30 bar (33.0 lb/sq in).
POWER PLANT: One 134 kW (180 hp) Textron Lycoming AEIO-360-B2F flat-four engine, driving either Evra fixedpitch or MT variable-pitch propeller. Compatible with alternative engines of 119kW (160 hp) and above. Fixed-pitch or constant-speed propellers can be fitted. Fuel capacity for aerobatics 85 litres (22.4 US gallons; 18.7Imp gallons), of which 82 litres (21.7 US gallons; 18.0 Imp gallons) are usable; max fuel capacity 160 litres(42.3 US gallons; 35.2 Imp gallons). Oil capacity 7.6 litres(2.0 US gallons; 1.7 Imp gallons).
ACCOMMODATION: Two seats, side by side, with dual controls. Fixed windscreen and rearward-sliding canopy.
SYSTEMS: Electrical system: 12 V 30 Ah battery.
AVIONICS: Customer specified.
| DIMENSIONS, EXTERNAL: | |
| Wing span | 8.50 m (27 ft 10½ in) |
| Wing aspect ratio | 6.8 |
| Length overall | 7.50 m (24 ft 7¼ in) |
| Tailplane span | 2.80 m (9 ft 2¼ in) |
| Wheel track | 2.37 m (7 ft 9¼ in) |
| Propeller diameter | 1.90 m (6 ft 3 in) |
| AREAS: | |
| Wings, gross | 10.65 m² ( l 14.6 sq ft) |
| Ailerons (total) | 1.215 m² (13.08 sq ft) |
| Trailing-edge flaps (total) | 1.21 m² (13.02 sq ft) |
| Vertical tail surfaces (total) | 1.71 m² (18.40 sq ft) |
| Horizontal tail surfaces (total) | 2.20 m² (23.68 sq ft) |
| WEIGHTS AND LOADINGS: | |
| Weight empty | 550 kg (1,213 lb) |
| Max T-O weight: Aerobatic | 760 kg (1,676 lb) |
| - Normal | 850 kg (1,873 lb) |
| Max wing loading: Aerobatic | 71.5 kg/m² (14.64 lb/sq ft) |
| - Normal | 80.0 kg/m² (16.38 lb/sq ft) |
| Max power loading: Aerobatic | 5.66 kg/kW (9.31 Ibmp) |
| - Normal | 6.34 kg/kW (10.41 lb/hp) |
| PERFORMANCE: | |
| Never-exceed speed (VNE) | 205 kt (379 km/h; 235 mph) |
| Max level speed | 165 kt (305 km/h; 190 mph) |
| Max cruising speed | 151 kt (280 km/h; 174 mph) |
| Manoeuvring speed (VA) | 140 kt (260 km/h; 161 mph) |
| Max rate of climb at S/L | 480 kt (1,575 ft)/min |
| T-O run | 153 m (500 ft) |
| T-O to 15 m (50 ft) | 351 m (1,150 ft) |
| Range: normal fuel | 302 n miles (560 km; 348 miles) |
| - max fuel | 604 n miles (1,120 km; 696 miles) |
| g limits | +8/-6 |
