TYPE: Business turboprop.

PROGRAMME: Development started early 2001. Prototype (D-ETPG), then unflown and previously unannounced, exhibited at Paris Air Show from 16 to 24 June 2001.
Design freeze completed in 2002 following incorporation of changes based on feedback from potential customers. First flight 12 December 2002, with JAR-23 certification expected a year later and FAA approval in first quarter 2004.

CUSTOMERS: Potential market for 20 to 40 per year, for military and civilian markets. Interest reported from several air forces by early 2002.

COSTS: Unpressurised version US$1 million (2002).

DESIGN FEATURES: Generally similar to G 115/120 series.

FLYING CONTROLS: Conventional and manual. Trim tab on port elevator and each aileron; horn-balanced rudder. Dual controls (sticks) standard.

STRUCTURE: Entirely GFRP. Structural service life (aerobatic) 15,000 flight hours.

LANDING GEAR: Retractable tricycle type with trailing-link suspension on main units. Main legs retract inwards into wing root area, nosewheel rearwards.

POWER PLANT: One 336 kW (450 shp) Rolls-Royce 250-B17F turboprop driving an MT-Propeller MTV-5 five-blade, constant-speed (hydraulic) propeller.

ACCOMMODATION: Four persons in individual seats. Separate upward-opening gullwing-type door for each seat, with circular 'porthole' window at rear of cabin on each side. Baggage door at rear of cabin on port side. Air-conditioning standard, pressurisation will be offered as an option.

AVIONICS: Honeywell EFIS 40 two-screen EFIS as core system, with Litef Lasergyro AHRS and provision for TCAS, weather radar and Stormscope.