B1900D information page

(Information taken from Jane's All The World's Aircraft 1998-99)

TYPE: Twin-turboprop regional transport.

PROGRAMME: Original Beech 1900 first flew on 3 September 1982; three prototypes followed by 74 1900Cs and 174 wet-wing 1900C-1s by 1991. Current 1900D announced at US Regional Airlines Association meeting 1989; development of 1900C (1991-92 Jane's); prototype (converted from 1900C-1 N5584B) first flight 1 March 1990; certification to FAR Pt 23 Amendment 34 received March 1991; full certification with supplements received, and deliveries (to Mesa Airlines) began, November 1991; contract signed February 1997 with Xian Aircraft Company of People's Republic of China for supply to Raytheon of 800 metal-bonded subassemblies for 1900D, to be delivered between 1997 and 2001; 500th Model 1900 delivered in March 1997. Beech also offers special mission versions for signals intelligence, maritime patrol and similar duties.

CUSTOMERS: Total 65 delivered in 1995, 69 in 1996 and 42 in 1997. Recent customers include Impulse Airlines of Sydney, Australia, which took delivery of one aircraft (the 500th production Model 1900) in March 1997, Regional Airlines of Morocco, which received four aircraft in March and April 1997 and Proteus Airlines of France, which ordered 10 for delivery between December 1997 and third quarter of 1998. Mesa Airlines ordered 40 in November 1994, in addition to 78 previously ordered, for delivery during 1996-97. Total of 300 1900Ds delivered by March 1998.

COSTS: US$4.775 million (1996).

DESIGN FEATURES: Flat floor with stand-up headroom; cabin volume increased by 28.5 per cent compared to 1900C; winglets add better hot and high performance; tailplane and fin swept; each tailplane carries small fin (tailet) on underside near tip; auxiliary horizontal fixed tail surface (stabilon) each side of rear fuselage improve centre of gravity range; twin ventral strakes improve directional stability and turbulence penetration; small horizontal vortex generator on fuselage ahead of wingroots. Wing aerofoil NACA 23018 (modified) at root, 23012 (modified) at tip; dihedral 6º; incidence 3º 29' at root, -1º 4' at tip; no sweepback at quarter-chord.

FLYING CONTROLS: Mechanical, with automatic cable tensioner in aileron circuit; trim tabs in elevators, rudder and port aileron; primary and secondary controls routed separately to improve protection from possible engine-failure damage; single-slotted trailing-edge flaps in two sections on each wing.

STRUCTURE: Wing has continuous main spar with fail-safe structure riveted and bonded; fuselage pressurised and mainly bonded.

LANDING GEAR: Hydraulically retractable tricycle type; main units retract forward and nose unit rearward; Beech oleo-pneumatic shock-absorber in each unit. Twin Goodyear wheels on each main unit, size 6.50 × 10, with Goodyear tyres size 22 × 6.75-10 (tubeless 10 ply rating), pressure 6.69 bars (97 lb/sq in); Goodyear steerable nosewheel size 6.50 × 8, with Goodyear tyres size 19 × 6.75-8 (tubeless 10 ply rating), pressure 4.14 bars (60 lb/sq in). Multiple-disc hydraulic brakes. Optional Beech Hydro-Aire anti-skid units, power steering and brake de-icing. Ground turning radius based on wingtip clearance 12.55 m (41 ft 2 in).

POWER PLANT: Two Pratt & Whitney Canada PT6A-67D turboprops, each flat rated at 954 kW (1,279 shp) and driving a Hartzell four-blade constant-speed fully feathering reversible-pitch composites propeller. Wet wing fuel storage with a total capacity of 2,528 litres (668 US gallons; 556 Imp gallons), of which 2,519 litres (665 US gallons; 554 Imp gallons) usable. Refuelling point in each wing leading-edge, inboard of engine nacelle. Oil capacity (total) 29.5 litres (7.8 US gallons; 6.5 Imp gallons).

ACCOMMODATION: Crew of one (FAR Pt 91) or two (FAR Pt 135) on flight deck, with standard accommodation in cabin of commuter version for 19 passengers in single airline-standard seats on each side of centre aisle. Forward carry-on baggage lockers, underseat baggage stowage, rear baggage compartment. Forward door, incorporating airstairs, on port side. Upward-hinged rear cargo door, also on port side. Three emergency exits over wing (two starboard, one port). Accommodation air conditioned, heated, ventilated and pressurised. Executive and corporate shuttle options seat between 10 and 18 passengers with options for forward and rear compartments, combination lavatory/passenger seat and two beverage bars at cabin compartment division. Club, double club and triple club seating optional. Customised interiors to customer's choice.

SYSTEMS: Bleed air cabin heating and pressurisation, maximum differential 0.35 bar (5.1 lb/sq in). Air cycle and vapour cycle air conditioning. Hydraulic system, pressure 207 bars (3,000 lb/sq in), for landing gear actuation. Electrical system includes two 300 A engine-driven starter/generators and one 34 Ah Ni/Cd battery. Constant flow oxygen system of 4,420 litre (156 cu ft) capacity standard. Engine inlet screen anti-ice protection, exhaust heated engine inlet lips, fuel vent heating, electric propeller and windscreen de-icing systems standard. Brake de-icing optional. Pneumatic de-icing boots on wings, tailplane, tailets and stabilons.

AVIONICS: Comms: Collins Pro Line II digital technology radios; cabin briefer; cockpit voice recorder. Flight: Dual flight directors; GPWS; provision for TCAS1. Loran optional. Instrumentation: Collins EFIS-84 four-tube EFIS. Primary display consists of multicolour CRT panels, remote display processor unit and system control units; CRT displays provide conventional electronic attitude director indicator (EADI) and electronic horizontal situation indicator (EHSI) functions.


Height (m): 4.72
Length (m): 17.63
Max Level Speed (kts): 272
Max Range (nm): 1476
Max Rate Of Climb (m/min): 800
Max T-O Weight (kg): 7688
Max Wing Load (kg/m2): 266.9
Service Ceiling (ft): 25000
Wing Span (m): 17.67


Wing span over winglets 17.67 m (57 ft 11¾ in)
Wing chord: At root 2.18 m (7 ft 1¾ in)
    At tip 0.91 m (3 ft 0 in)
Wing aspect ratio 10.9
Length overall 17.63 m (57 ft 10 in)
Height overall 4.72 m (15 ft 6 in)
Tailplane span 5.63 m (18 ft 5¾ in)
Wheel track 5.23 m (17 ft 2 in)
Wheelbase 7.25 m (23 ft 9½ in)
Propeller diameter 2.78 m (9 ft 1½ in)
Propeller ground clearance 0.35 m (1 ft 1¾ in)
Distance between propeller centres 5.23 m (17 ft 2 in)
Passenger door: Height 1.63 m (5 ft 4{1/4} in)
    Width 0.64 m (2 ft 1{1/4} in)
Cargo door: Height 1.45 m (4 ft 9 in)
    Width 1.32 m (4 ft 4 in)
Emergency exits (each): Height 0.80 m (2 ft 7½ in)
    Width 0.51 m (1 ft 8 in)


Cabin (incl flight deck and rear baggage compartment):
    Length 12.03 m (39 ft 5½ in)
    Max width 1.37 m (4 ft 6 in)
    Max height 1.80 m (5 ft 10¾ in)
    Floor area 15.3 m2 (165 sq ft)
    Pressurised volume 26.0 m3 (918 cu ft)
Volume of passenger cabin 18.1 m3 (640 cu ft)
Baggage volume, cabin: Forward 0.34 m3 (12.0 cu ft)
    Underseat 0.91 m3 (32.0 cu ft)
    Rear 5.0 m3 (175 cu ft)


Wings, gross 28.80 m2 (310.0 sq ft)
Ailerons (total) 1.67 m2 (18.00 sq ft)
Trailing-edge flaps (total) 4.17 m2 (44.90 sq ft)
Fin 4.86 m2 (52.30 sq ft)
Rudder (incl tab) 1.40 m2 (15.10 sq ft)
Tailets (total) 0.63 m2 (6.80 sq ft)
Tailplane 6.32 m2 (68.00 sq ft)
Elevator (incl tab) 1.79 m2 (19.30 sq ft)
Stabilons (total) 1.44 m2 (15.50 sq ft)


Weight empty (typical) 4,831 kg (10,650 lb)
Max fuel (usable) 2,022 kg (4,458 lb)
Max baggage 939 kg (2,070 lb)
Max ramp weight 7,738 kg (17,060 lb)
Max T-O weight 7,688 kg (16,950 lb)
Max landing weight 7,530 kg (16,600 lb)
Max zero-fuel weight 6,804 kg (15,000 lb)
Max wing loading 266.9 kg/m2 (54.68 lb/sq ft)
Max power loading 4.03 kg/kW (6.63 lb/shp)

PERFORMANCE (at max T-O weight except where indicated):

Max cruising speed at AUW of 6,804 kg (15,000 lb):
    at 2,440 m (8,000 ft) 272 kt (504 km/h; 313 mph)
    at 4,875 m (16,000 ft) 283 kt (524 km/h; 326 mph)
    at 7,620 m (25,000 ft) 274 kt (507 km/h; 315 mph)
Unstick speed, T-O flap setting 105 kt (195 km/h; 121 mph) IAS
Approach speed at max landing weight 117 kt (217 km/h; 135 mph)
Stalling speed at max T-O weight:
    Wheels and flaps up 101 kt (187 km/h; 116 mph)
    Wheels down, T-O flap setting 90 kt (167 km/h; 104 mph)
Stalling speed at max landing weight, wheels and flaps down 84 kt (156 km/h; 97 mph)
Max rate of climb at S/L 800 m (2,625 ft)/min
Rate of climb at S/L, OEI 192 m (630 ft)/min
Service ceiling 10,058 m (33,000 ft)
Service ceiling, OEI 5,181 m (17,000 ft)
T-O field length, T-O flap setting 1,140 m (3,740 ft)
Landing from 15 m (50 ft) at max landing weight 844 m (2,770 ft)
Range with 10 passengers, at long-range cruise power, with allowances for starting, taxi, T-O, climb and descent, with reserves (45 min hold at 1,525 m; 5,000 ft) 1,476 n miles (2,733 km; 1,698 miles)