Israel Defence Force name: Tsofit (Thrush)
Swedish Air Force designation: Tp 101

TYPE: Utility turboprop twin.

PROGRAMME: Design of Super King Air 200 began October 1970; 'Super' prefix deleted from all 200, 300 and 350 series King Airs in 1996; first flight (c/n BB1) 27 October 1972; certified to FAR Pt 23 plus icing requirements of FAR Pt 25, 14 December 1973; design of B200 (prototype c/n BB343) began March 1980; production started May 1980; FAA certification 13 February 1981; on sale March 1981.

CURRENT VERSIONS: King Air B200: Baseline version.
Detailed description applies to B200.
King Air B200C: As B200 but with 1.32 x 1.32 m (4 ft 4 in x 4 ft 4 in) cargo door. Two, identified as military C-12R/AP, ordered by US Army on behalf of Greece, January 2000; special missions fit includes cameras for geophysical survey, removable for VIP transport; delivered mid-2002.
King Air B200T: Standard provision for removable tip tanks, adding total 401 litres (106 US gallons; 88.25 Imp gallons), making total 2,460 litres (650 US gallons; 541 Imp gallons). Span without tip tanks 16.92 m (55 ft 6 in). Total 38 built up to 1993. Four ordered by US Army Missile Command in October 1998 for delivery by June 2000; however, these appear to be part of batch of five for Israel Defence Force, also completed in June 2000 and increasing production total to 43. Further three built in 2002 for undisclosed customer; total 46, all converted on production line from B200s.
King Air B200CT: Combines tip tanks and cargo door as standard. Four built by 1983 for Chile (one) and Peru (Navy, three). All converted on production line from King Air 200. Israel Defence Force/Air Force ordered five, of which first was delivered on 4 September 2002, with deliveries completed in June 2003. All B200T/CTs converted on production line from King Air 200s.
Maritime patrol B200T: Production discontinued.
Beech 200 HISAR: Radar surveillance platform. Launched 1997; based on Beech 200T airframe; demonstrator (N4277E) undertook 16-country tour in 1997-98. First international sale to Traffic 2000 of Germany, November 1997, for North Sea environmental monitoring. Ventral radome for Hughes Integrated Synthetic Aperture Radar (HISAR) suitable for border surveillance, remote sensing, pollution monitoring, EEZ patrol and agricultural monitoring. Equipment operator's console in cabin.
C/RC/UC-12: Military versions; described separately.
King Air 300LW: Production discontinued.
King Air 350: Described separately.

CUSTOMERS: Deliveries by 30 September 2003 totalled 1,878 for commercial and private orders, plus 397 military versions to US armed forces and foreign customers. Total of 23 King Air B200s delivered in 1994, 28 in 1995, 33 in 1996, 45 in 1997, 45 in 1998, 55 in 1999, 59 in 2000, 46 in 2001, 26 in 2002, and 17 in the first nine months of 2003.
French Institut Géographique National has three B200Ts fitted with twin Wild RC-10 Superaviogon camera installations and Doppler navigation; maximum endurance 10 hours 20 minutes; high flotation landing gear; special French certification for maximum T-O weight 6,350 kg (14,000 lb) and maximum landing weight 6,123 kg (13,500 lb). Egyptian government acquired one King Air 200 in 1978 for water, uranium and other natural resources exploration over Sinai and Egyptian deserts as follow-up to satellite surveys; fitted with remote sensing gear, specialised avionics and special cameras. Navaid checking versions supplied to Taiwan government (one) and Malaysian government (two). Other special missions aircraft delivered to Taiwan Ministry of Interior May 1979; Royal Hong Kong Auxiliary Air Force (later Government Air Service) (two) 1986 and 1987; four King Air 200s operated by Swedish Air Force since 1988 as Tp 101.
King Air B200 selected by UK Serco Group plc for Royal Air Force Cranwell Multi-Activity (MAC) and Multi-Engine Pilot Training Interim Solution (replacing BAe Jetstreams); first two (of seven) delivered 12 December 2003, with remainder scheduled for delivery by March 2004.

COSTS: B200 US$3.839 million; B200C US$4.814 million (all 2001).

DESIGN FEATURES: Generally as for earlier versions. Wing aerofoil NACA 23018 to 23016.5 over inner wing, 23012 at tip; dihedral 6°; incidence 3° 48' at root, -1° 7' at tip; swept vertical and horizontal tail.

FLYING CONTROLS: Conventional and manual. Trim tabs in port aileron and both elevators; anti-servo tab in rudder; single-slotted trailing-edge flaps; fixed tailplane.

STRUCTURE: Two-spar light alloy wing; safe-life semi-monocoque fuselage.

LANDING GEAR: Hydraulically retractable tricycle type, with twin wheels on each main unit. Single wheel on steerable nose unit, with shimmy damper. Main units retract forward, nosewheel rearward. Beech oleo-pneumatic shock-absorbers. Goodrich mainwheels and tyres size 18x5.5 (10 ply) tubeless, pressure 7.25 bar (105 lb/sq in). Oversize and/or 10 ply mainwheel tyres optional. Goodrich nosewheel size 6.50x10 (8 ply) tubeless, with tyre size 22x6.75-10, pressure 3.93 bar (57 lb/sq in). Goodrich hydraulic multiple-disc brakes. Parking brake.

POWER PLANT: Two 634 kW (850 shp) Pratt & Whitney Canada PT6A-42 turboprops, each driving a Hartzell four-blade, constant-speed, reversible-pitch, metal propeller with autofeathering and synchrophasing. Bladder fuel cells in each wing, with main system capacity of 1,461 litres (386 US gallons; 321.5 Imp gallons) and auxiliary system capacity of 598 litres (158 US gallons; 131.5 Imp gallons). Total usable fuel capacity 2,059 litres (544 US gallons; 453 Imp gallons). Two refuelling points in upper surface of each wing. Wingtip tanks optional, providing an additional 401 litres (106 US gallons; 88.3 Imp gallons) and raising maximum usable capacity to 2,460 litres (650 US gallons; 541 Imp gallons). Oil capacity 29.5 litres (7.8 US gallons; 6.5 Imp gallons).

ACCOMMODATION: Pilot only, or crew of two side by side, on flight deck, with full dual controls and instruments as standard. Seven cabin seats standard, each equipped with seat belts and inertia reel shoulder harness; optional seats in baggage compartment raise passenger capacity to nine. Partition with sliding door between cabin and flight deck, and partition at rear of cabin. Door at rear of cabin on port side, with integral airstair. Large cargo door optional. Inward-opening emergency exit on starboard side over wing. Lavatory and stowage for baggage in rear fuselage. Maintenance access door in rear fuselage; radio compartment access doors in nose. Cabin is air conditioned and pressurised, with electric heat panels to warm cabin before engine starting.

SYSTEMS: Cabin pressurisation by engine bleed air, with a maximum differential of 0.44 bar (6.5 lb/sq in). Cabin air conditioner of 32,000 BTU capacity. Auxiliary electric cabin heating. Oxygen system for flight deck, and 623 litre (22 cu ft) oxygen system for cabin, with automatic drop-down face masks; 2,182 litre (77 cu ft) system optional. Dual vacuum system for instruments. Hydraulic system for landing gear retraction and extension, pressurised to 171 to 191 bar (2,475 to 2,775 lb/sq in). Separate hydraulic system for brakes. Electrical system has two 300 A 28 V starter/generators and a 24 V 34 Ah air-cooled Ni/Cd battery with failure detector. AC power provided by dual 300 VA inverters. Engine fire detection system standard; engine fire extinguishing system optional. Pneumatic de-icing of wings and tailplane standard. Anti-icing of engine air intakes by hot air from engine exhaust, electrothermal anti-icing for propellers.

AVIONICS: Standard Rockwell Collins Pro Line II package. Pro Line 21 available as option from 2003.
Comms: Cockpit-to-cabin paging standard. Bendix/King KHF 950 transceiver, Fairchild A-100A cockpit voice recorder standard, Wulfsberg Flitefone optional.
Radar: Rockwell Collins WXR-270 colour weather radar standard, WXR-840 or WXR-850 turbulence detecting radar optional.
Flight: Collins APS-65H autopilot/flight director, Universal UNS-1D and UNS-1K navigation management systems, with GPS optional.
Instrumentation: Rockwell Collins EFIS-84/B-14, pilot's ALT-80A encoding altimeter; dual maximum allowable airspeed indicators, and flight director standard. Options include Rockwell Collins three-tube EFIS-85B with MFD.

EQUIPMENT: Standard/optional equipment generally as for King Air C90B except fluorescent cabin lighting, one-place couch with storage drawers, flushing chemical toilet, cabin electric heating, cockpit/cabin partition with sliding doors, and airstair door with hydraulic snubber and courtesy light, standard. FAR Pt 135 operational configuration includes cockpit fire extinguisher and 2.2 m³ (77 cu ft) oxygen bottle with cockpit oxygen pressure indicator as standard. A range of optional cabin seating and cabinetry configurations is available, including quick-removable fold-up seats.