TYPE: Aerobatic, two-seat sportplane/kitbuilt.

PROGRAMME: Prototype CR100 (F-PDYN) first flew 27August 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; longerspan ailerons (2.70 m; 8 ft 101/4 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; 23.1Imp 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de Voltige de l'Armee de l'Air at Salon de Provence, of which first (No. 22 'CJ') delivered 21 July 1995; however, both withdrawn by 1997 and sold in 2000, one to UK owner Cole Aviation.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 (Information for 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.

Wing span 8.50 m (27 ft 101/2 in)
Wing aspect ratio 6.8
Length overall 7.50 m (24 ft 71/4in)
Tailplane span 2.80 m (9 ft 21/4in)
Wheel track 2.37 m (7 ft 91/4in)
Propeller diameter 1.90 m (6 ft 3 in)
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)
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)
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