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; 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de Voltige de l'Armee de l'Air at Salon de Provence, of which first (No. 22 'CJ') delivered 21 July 1995; however, both withdrawn by 1997 and sold in 2000, one to UK owner Cole Aviation.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.

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)
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