TYPE: Light utility twin-prop transport.

PROGRAMME: Design started November 1972; ptototype construction began January 1977; prototype (N44KE) built on production tooling; first flight 13 January 1984; structural testing began 1990; certification to FAR Pt 23 (Normal category) for day, night, VFR and IFR conditions gained 20 October 1992. Production began December 1993; second aircraft completed July 1994 but held in abeyance, pending acquisition of larger production premises. Second Angel eventually registered in August 2002 to Kansair Inc as N442KB, having been displayed at AirVenture, Oshkosh, in previous month. Third (N442KC) nearing completion in late 2003.

DESIGN FEATURES: Designed partly, but not exclusively, for missionary aviation; other commercial uses include air taxi, air ambulance, air observation/patrol, fishery/pipeline/border inspection, tracking, mining/oil/rubber/forestry operations, ranching and firefighting control. Design goals include STOL capability, operation from soft and rough fields, easy repair in field, and easy loading of bulky cargo.
Vortex generators on wing outboard panels for enhanced lift; small wing endplates. Crashworthiness built and tested in key structures; seats dynamically tested to absorb 20 g vertically and 26 g horizontally; cabin structure includes areas of double-wall and tested for overturn impact survivability. Extra-large propeller spinners assist airflow around rear fuselage.
Wing section NACA 23018-23010 with modified leading-edge; sweepback 15° 36' at leading-edge, 11° at quarter-chord; dihedral 5° 24'; incidence 3° at root; -0° 22' at tip.

FLYING CONTROLS: Manual. Actuation by cables. Almost full-span, hydraulically actuated semi-Fowler flaps deflecting to maximum 37°. Lateral control initiated by small ailerons at wingtips known as trimmerons (first 3 to 5° of bank), further bank being induced by spoilers in form of 11 small plates immediately forward of flaps on each wing; elevators and rudder, both with horn balanced and trim tabs (one in each side of elevator).

STRUCTURE: Riveted aluminium alloy and welded 4130/4340 steel tube; wing has built-up capstrip spars and 19 die-formed ribs each side; broad-chord fin and rudder with large dorsal fin; CFRP spinners; GFRP/epoxy in some areas.

LANDING GEAR: Retractable tricycle type. Electrohydraulic retraction, mainwheels inward into wingroots (on wheel doors), nosewheel rearward. Emergency extension by gravity. Cleveland wheels; McCreary mainwheel tyres size 8.50-10 (pressure 2.41 bar; 35 lb/sq in), McCreary or Goodyear nosewheel tyre size 8.50-6 (pressure 1.03 bar; 15 lb/sq in). Hydraulic Cleveland disc brakes. Min ground turning radius 5.11 m (16 ft 9 in) due to fully-castoring nosewheel.

POWER PLANT: Two 224 kW (300 hp) Textron Lycoming IO-540-M1C5 flat-six engines, each driving a Hartzell HC-E3YR-2ATLF/FLC7468 three-blade, constant-speed (hydraulic), feathering pusher propeller. Two wing fuel tanks, gravity flow cross-fed, with total capacity 849 litres (224 US gallons; 187 Imp gallons). Refuelling point in top of each wing. Oil capacity 22.7 litres (6.0 US gallons; 5.0 Imp gallons).

ACCOMMODATION: Accommodation for two pilots and four passengers, rearmost facing sideways, others on three individual seats. Seats can be removed for carrying cargo, including four 208 litre (55 US gallon; 45.8 Imp gallon) drums. Four large windows and one smaller circular window on each side of cabin. Horizontally divided clamshell door on port side at front of cabin with folding step in lower element; emergency exit on starboard side. Heating and window air vents standard. Compartment for baggage at rear of fuselage, with door on port side.

SYSTEMS: Hydraulic system, with electric pump, for landing gear and flap actuation. Electrical system with two alternators includes 12 V DC battery in nose.

AVIONICS: IFR. Bendix/King and Garmin avionics, including twin com/nav transceivers, glideslope, ADF, transponder, ELT and GPS Weather radar, Loran C and HF com optional.