TYPE: Side-by-side kitbuilt.
PROGRAMME: First flight (HB 207RG OE-CHC) 14 March 1995. Second prototype (HB 207 OE-CAA) made public debut, unmarked and then unflown, at Aero '97 at Friedrichshafen April 1997. Certified to JAR-VLA.
CURRENT VERSIONS: HB 207: Fixed landing gear version.
HB 207RG: Retractable landing gear version. Empty weight 498 kg (1,098 lb), MTOW 750 kg (1,653 lb); cruising speed at 75 per cent power 140 kt (259 km/h; 161 mph); service ceiling 4,570 m (15,000 ft); T-O run 340 m (1,115 ft), or 440 m (1,445 ft) to 15 m (50 ft); range 809 n miles (1,500 km;932 miles).
CUSTOMERS: Total 70 sold in Austria, Brazil, Czech Republic, France, Germany, Sweden, Switzerland, United Kingdom and USA by April 2001; 65 completed by late 2002.
COSTS: Standard aircraft fast-build kit, no engine, propeller or avionics €22,500 (2003).
DESIGN FEATURES: Quoted build time 1,000 hours. Constant chord low wings with raked tips; slightly sweptback fin and rudder; one-piece elevator aft of vertical tail. Airframe features derigging and rigging guide points for road transport or storage.
FLYING CONTROLS: Conventional and manual. Ailerons and elevator actuated by pushrods; rudder by cables. Large central trim tab in elevator. Manual (optionally electric) operation for flaps.
STRUCTURE: Mainly metal primary structure with GFRP skin; moving surfaces have Ceconite covering.
LANDING GEAR: HB 207RG has retractable tricycle type, with size 4.00-4 tyre on each unit. Main units have brakes and rubber-in-compression shock-absorption and retract inward; nosewheel retracts rearward. HB 207 has fixed tricycle type with streamlined fairings and spats on each unit.
POWER PLANT: Standard engine is an 80.9 kW (108.5 hp) VW-Porsche HB 2400 G/2 flat-four based on that of Porsche 911 sports car; alternatives include 59.6 kW (79.9 hp) Rotax 912A, 73.5 kW (98.6 hp) Rotax 912S and 84.5 kW (113.3 hp) Rotax 914, or Limbach or Textron Lycoming engines up to 74.6 kW (100 hp). Geared drive to choice of propellers: two-blade wooden fixed-pitch, three-blade adjustable- or variable-pitch, or (as on prototypes) five-blade adjustable- or variable-pitch. Fuel tank in each wing, combined capacity 100 litres (26.4 US gallons; 22.0 Imp gallons).
ACCOMMODATION: Rearward-sliding fully transparent canopy.
SYSTEMS: Electrical system; 200 A 15 Ah (optionally 20 Ah) battery; 14 V 75 A alternator.
AVIONICS: Comms: Honeywell 760-channel KX 155 transceiver, KT 76A transponder and ELT optional.
Flight: Honeywell KX 125 VOR with KI 208 indicator optional.
Instrumentation: VFR flight and engine transmission instrumentation standard.
