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Voltige de l'Armee de l'Air at Salon de Provence, of which first (No. 22 'CJ') delivered 21 July 1995; however, both withdrawn by 1997 and sold in 2000, one to UK owner Cole Aviation.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