MAVERICK LEADER

TYPE: Light business jet.

PROGRAMME: Launched at EAA Convention at Oshkosh, Wisconsin, July 1997; then known as Twinjet 1200; construction of proof-of-concept prototype, undertaken by Maverick Air of Pueblo, Colorado started September 1999; first flight (N750TJ) 4 August 1999; designated TJ-1500 Twinjet 1500; public debut at EAA AirVenture, Oshkosh, August 2000. Became Maverick Leader in 2002. Prototype destroyed in fatal crach 24 January 2003. FAA/JAA certification planned for 2004.
Production undertaken by Tbilaviamsheni in Georgia, where initial two aircraft were nearing completion in late 2003.

COSTS: Unit cost US$1.25 million; estimated operating cost US$170 per hour or 55 cents per mile (both 2003).

DESIGN FEATURES: Designed using advanced CAD and three-dimensional modelling techniques; design goals include comfort and performance of a traditional business jet in a light piston twin configuration and good short-field performance; unswept, mid-mounted, constant-chord wing with tip tanks; T tail; engines pod-mounted on rear fuselage shoulders.

FLYING CONTROLS: Conventional and manual. Electrically-actuated flaps, approximately two-thirds span; speedbrakes in upper wing; dual (stick) controls; electric trim.

STRUCTURE: Composites, employing prepreg glass/carbon fibre and nomex.

LANDING GEAR: Retractable tricycle type with single wheel on each unit; main units retract inwards; nosewheel, forwards; Cleveland brakes.

POWER PLANT: Two 4.89 kN (1,100 lb st) Williams International FJ33-4 turbofans with FADEC, pod-mounted on rear fuselage. Fuel contained in two integral wing tanks and single fuselage tank, combined capacity 1,249 litres (330 US gallons; 275 Imp gallons).

ACCOMMODATION: Five persons in pressurised cabin; single upward-opening gullwing door on port side; baggage compartments in nose and to rear of cabin. Leather interior standard.

SYSTEMS: Pressurisation system, maximum differential 0.39 bar (5.6 lb/sq in) maintains 3,050 m (10,000 ft) cabin altitude to 9,150 m (30,000 ft). Split-bus electrical system supplied by two 24 V batteries and two alternators. Airframe anti-icing and oil-heated engine inlets standard.

AVIONICS: Integrated all-glass flight deck.

DIMENSIONS, EXTERNAL:

  • Wing span: standard: 10.13 m (33 ft 3 in)
    • with tip tanks: 10.52 m (34 ft 6 in)
  • Wing aspect ratio: 7.6
  • Length overall: 8.69 m (28 ft 6 in)
  • Height overall: 2.74 m (9 ft 0 in)

DIMENSIONS, INTERNAL:

  • Cabin: Length: 2.64 m (8 ft 8 in)
    • Max width: 1.32 m (4 ft 4 in)
    • Max height: 1.09 m (3 ft 7 in)
  • Baggage volume: 0.42 m³ (15.0 cu ft)

AREAS:

  • Wings, gross: 13.43 m² (144.6 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: 1,315 kg (2,900 lb)
  • Max baggage weight: 91 kg (200 lb)
  • Max T-O weight: 2,630 kg (5,800 lb)
  • Max wing loading: 195.8 kg/m² (40.11 lb/sq ft)
  • Max power loading: 394 kg/kN (3.87 lb/lb st)

PERFORMANCE (estimated):

  • Never-exceed speed (VNE) and max level speed: 391 kt (724 km/h; 450 mph)
  • Max cruising speed: 350 kt (648 km/h; 403 mph)
  • Econ cruising speed: 330 kt (611 km/h; 380 mph)
  • Stalling speed, flaps down: 78 kt (145 km/h; 90 mph)
  • Max rate of climb at S/L: 914 m (3,000 ft)/min
  • Rate of climb at S/L, OEI: 305 m (1,000 ft)/min
  • Max certified altitude: 9,450 m (31,000 ft)
  • Service ceiling, OEI: 6,095 m (20,000 ft)
  • T-O run: 610 m (2,000 ft)
  • Landing run: 607 m (1,990 ft)
  • Range with max internal fuel: 1,500 n miles (2,775 km; 1,726 miles)
    • with tip tanks: 1,700 n miles (3,148 km; 1,956 miles)