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Beechcraft 100 King Air / U-21F

 

 

beech100kingair
B100 King Air


The 100 series was introduced in 1969 when initial deliveries were made in August 1969, and employed the 680-shp Pratt & Whitney turboprop. All have full-feathering, reversible propellers. It differed from the earlier King Airs in reduced wing span, a lengthened fuselage to provide accommodation for a maximum of 15 persons, increased elevator and rudder areas, twin-wheel main landing gear, and more powerful engines. The new wing was generally similar to that developed for the Model 99 Airliner. Their pressurized, three-compartment interior can be maintained at sea level atniosphere pressure to flight levels as high as 10,500 feet.


In October 1971 Beech began deliveries of the improved King Air A100, this variant incorporating detail improvements, and the first five were supplied to the US Army under the designation U-21F, 70-15908/15912. Examples have been procured by the Spanish air force, and a Universal Aircraft Com/Nav Evaluation (UNACE) configured version, for the rapid inspection and calibration of air navigation systems, has been supplied to countries that include Algeria, Belgium, Canada, Indonesia, Malaysia, Mexico, and the USA. Beech also produces specially modified camera-equipped versions of the King Air for aerial survey, and examples are in service in this role in Canada, Chile, France, Jamaica, Saudi Arabia, Thailand, and the USA.


The higher capacity versions are the A100 and B100, with the latter being the first King Air to be outfitted with Garrett turboprops. In parallel with A100 production since late 1975, Beech has produced a complementary King Air B100 offering higher performance. It differs by the installation of 533kW Garrett TPE331-6-252B turboprop engines, and of equipment directly associated with the engine installation. Beech has mated two Garrett AiResearch TPE 331-6-252B 840-shp derated to 715 shp turboprop engines to the A100 airframe. Beech made the move to assure that they would have two sources of engines considering the interruption in deliveries that was caused when United Aircraft of Canada, Ltd. (now known as Pratt & Whitney of Canada) struck for 19 months in 1974 and 1975. The derated TPE 331 turboprop engines affect the pilot's procedures and the aircraft's performance more than the handling qualities. The B100's powerplant thrust line was raised somewhat, to counter the longitudinally destabilizing influence of five percent more horsepower. Because the derated Garrett powerplants are capable of producing 840 shp, their performance in the B100 on hot days and at altitude surpasses that of the MA-28s used on the A100. Thus, the B100 is 16 knots faster than the A100 at 10,000 feet and 27 knots faster at FL 200 (262 knots compared with 235 knots at maximum cruise power). Range for both 100s at maximum cruise power with maximum payload on board and 45 minutes' reserve is slightly more than 1,200 nm.


Production of the King Air 100 ended in 1983.

A100
Engines: 2 x Pratt & Whitney PT6A-28 free-turbine, 680 shp / 507kW.
Wingspan: 14.0 m / 45 ft 11 in
Length: 12.17 m / 39 ft 11 in
Height: 4.7 m / 15 ft 5 in
Gross Wt. 11,568 lbs.
Empty wt: 6754 lb.
Equipped useful load: 4564 lb.
Payload max fuel: 1415 lb.
Wing loading: 40.8 lb/sq.ft.
Pwr loading: 8.46 lb/hp.
Fuel capacity 470 USG/3149 lb.
Ceiling 24,850 ft.
Range max fuel/cruise: 933nm/3.7hr.
Range max fuel /range: 1319nm/6.3hr.
Max cruise: 248 kt.
Max range cruise: 211 kt.
Vmc: 85 kt. Stall: 75-89 kt.
1.3 Vso: 98 kt.
Takeoff distance (50’) 2681 ft.
Landing distance (50’) 2109 ft.
ROC: 1963 fpm.
SE ROC: 452 fpm @ 119 kt.
SE ceiling: 9,300 ft.
Certified Service Ceiling: 24,850 ft.
Seats: 8 to 15.
Pressurisation: 4.6 psi.
8000ft cabin alt: 21,000ft.

BE-B100 King Air

First built: 1976.
Engines: 2 x Garrett TPE 331-6-252B, 715 shp.
Props: Hartzell 4-blade, 90-in.
Seats: 8/15.
Length: 39.9 ft.
Height: 15.4 ft.
Wingspan: 45.9 ft.
Wing area: 280 sq.ft.
Wing aspect ratio: 7.5.
Maximum ramp weight: 11,875 lbs.
Maximum takeoff weight: 11,800 lbs.
Standard empty weight: 7082 lbs.
Maximum useful load: 4793 lbs.
Zero-fuel weight: 9600 lbs.
Maximum landing weight: 11,210 lbs.
Wing loading: 42.2 lbs/sq.ft.
Power loading: 8.3 lbs/hp.
Maximum usable fuel: 3149 lbs.
Best rate of climb: 2139.
Service ceiling: 28,138 ft.
Max pressurisation differential: 4.6 psi.
8000 ft cabin alt @: 21,200 ft.
Maximum single-engine rate of climb: 501 fpm @ 129 kts.
Single-engine climb gradient: 233 ft/nm.
Single-engine ceiling: 12,120 ft.
Maximum speed: 265 kts.
Normal cruise @ 21,000ft: 262 kts.
Fuel flow @ normal cruise: 540 pph.
Endurance at normal cruise: 5.3 hrs:
Stalling speed clean: 93 kts.
Stalling speed gear/flaps down: 83 kts.
Turbulent-air penetration speed: 170 kts.

 

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