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Beechcraft 1900

beech1900d
Beechcraft 1900D


In 1975 a decision was made to develop what was to be the model 1900. This was to be a pressurised, high density 19-seater aircraft based on the model 200 Super King Air. Using the model 200 cockpit, tail section, a longer fuselage and a new continuous spar wing was developed. A slightly unusual feature of these aircraft was the “tail-lets” attached beneath the horizontal tailplane for improved directional stability and an auxiliary horizontal tail (stabilon) on each side of the rear fuselage to extend the aft centre of gravity limits. The first of the three 1900C development aircraft flew (under SFAR part 41C) on 13 September 1982 powered with the PT-6A-65 which was up rated to the 1000-shp -65A on production aircraft. Its type certificate was achieved on 22 November 1983. Production deliveries, fitted with 52-inch by 52-inch cargo doors, began in February 1984 but were phased out in October 1991 when the SFAR part 41 C regulation expired. Some 72 “C” models had been built, followed by around 175 1900C-1 versions with their “wet wings”.

Announced by Raytheon at the US Airlines Association meeting in March 1989 was the Model 1900D, Beech’s answer to the 19-passenger, stand-up, pressurised aircraft for the commuter and regional airline operators. Power chosen was the 1600-shp PT6A-67D flat rated at 1279 shp. Wingspan and area were increased with winglets added. The fuselage was some 28.5% larger, which gives the aircraft the “high forehead” look and “stand-up head room” (of 5 ft 11 in) in the cabin. The aircraft introduced the twin ventral strakes designed to improve the directional stability and turbulence penetration. The wet wing is design fabri-cated and assembled as a one-piece unit. It is able to hold 2,517 litres in two integral fuel tanks in each wing (the main tanks hold 1621 lbs and the smaller auxiliary tank 621 lbs). The primary controls are mechanically linked and the land-ing gear is hydraulically actuated with dual main wheels and a single nose wheel. The prototype 1900D (N5584D), a converted 1900C, first flew on 1 March 1990 with FAA certification being achieved in March 1991. Production switched to the 1900D in 1991 and first deliveries began in No-vember 1991.

1900C

Engines: 2 x Pratt & Whitney Canada PT6A-65B turboprop.

1900D

Engines: 2 x Pratt & Whitney Canada PT6A-67D turboprop, 1279-shp.
Props: Hartzell four-blade composite.
Wingspan: 57 ft 10 in (17.65rn).
Wing area: 303 sq.ft (28.l5sq.m).
Length: 57 ft 10 in (17.63m).
Height: 14 ft 10 in. (4.54m).
Empty weight: 10,400 lb (4,717 kg).
MTOW: 16,950 lb (7,688 kg).
Wing loading: 54.7 lb/sq.ft (267 kg/sq.m).
Power loading: 6.62 lb/hp (3 kg/hp).
Max cruise speed 334 mph (537 kph) at 13,000 ft (3,960m).
Rate of climb: 2,625 ft/min (800m/min) at sea level.
Service ceiling: 25,000 ft (7,620m).
SE service ceiling (MTOW): 17,500-ft.
Range high cruise power 45 min res: 794 miles (1,278km) at 25,000 ft (7,620m).
Pax cap: 19.

 

 


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