TYPE: Two-seat jet sportplane.
PROGRAMME: Announced early 2001, at which time initial wind tunnel testing was being undertaken; this finished 28 February 2001. Construction of full-scale, non-flying mockup being undertaken during mid-2001. A second series of wind tunnel tests was scheduled for late 2001 and 2002, followed by a maiden flight during the first half of 2004. One non-conforming and two conforming prototypes to fly 1,400-hour test programme. Certification to FAR Pt 23 Amdt 52 (Aerobatic) intended late 2004 with deliveries in early 2005.
All data are provisional.
CURRENT VERSIONS: ATG-1A: Initial design. Mid-wing configuration and separate windscreen. Replaced by ATG-1B.
ATG-1B: Mockup unveiled 12 July 2002 and shown at NBAA Convention, Olrando, Florida, in September 2002. Low wing with leading-edge 'dog-tooth' and two-piece canopy.
Javelin HDI (Homeland Defense Interceptor): Single-seat version armed with wingtip-mounted AIM-9 Sidewinder or air-to-air Stinger missiles, was announced in early 2002, Quoted maximum speed of M1.6.
Javelin AJT (Advanced Jet Trainer): Two-seat version equipped with ejection seats and head-up displays to complement Javelin HDI.
UCAV: Unmanned combat version announced in July 2002.
CUSTOMERS: Production forecasts rainge from 711 to 1,638 units (2002 estimate). Deposits (US$25,000 each) taken on 26 aircraft by July 2002. By August 2003, the company had three distributorships and held letters of intent for 151 aircraft.
COSTS: US$2.20 million (2003) including type rating course will rise to US$2.50 million once distributor network becomes active. Development costs estimated at US$120 million up to certification. HDI version provisionally costed at US$4.5 million.
DESIGN FEATURES: Extensive use of aluminium provides optimum strength to weight ratio.
FLYING CONTROLS: Conventional and manual. Flaps. Electrically trimmed slab-type stabiliser and twin 15° outward-canted vertical stabilisers.
STRUCTURE: Fuselage of modular aluminium structure with swept cantilevered aluminium wing with leading edge root extensions. Quarter-chord sweep: wings 33° 10'; tailplane 37° 0'; fins 41° 0'. Sweptback tail; two aft body strakes.
LANDING GEAR: Hydraulically operated retractable tricycle type with oleo-pneumatic trailing-link struts. Anti-skid brakes.
POWER PLANT: Two Williams FJ33-4 turbofan engines, each 6.7 kN (1,500 lb st). Fuel capacity 946 litres (250 US gallons; 208 Imp gallons).
ACCOMMODATION: Pilot and passenger in tandem. Dual controls. Max cabin pressure differential 0.48 bar (7.0 lb/sq in). Air conditioning standard. Production aircraft will have side hinged canopies with integral explosive cords.
SYSTEMS: Combination of de-icing/anti-icing systems is planned; electro-expulsive de-icing for wings, bleed air heat for engine inlets, electric de-icing for windscreen and electric anti-icing for probes.
AVIONICS: Full IFR capability with dual EFIS displays. Options include head-up display and airborne video camera systems.
Comms: VHF/UHF radios; Mode S transponder.
Radar: Colour weather radar.
Flight: E-TCAS, TAWS and GPS integrated FMS with waypoint map.
Instrumentation: Three-axis autopilot.