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Beechcraft Premier I
From Wikipedia, the free encyclopedia
| Premier I | |
|---|---|
| Type | Civil utility aircraft |
| Manufacturer | Raytheon/Hawker Beechcraft |
| Maiden flight | December 22, 1998 |
| Status | Active |
| Number built | >150 |
The Beechcraft Premier I is a light jet aircraft.
Contents |
The Premier 1A is constructed with high-strength composite, carbon fiber/epoxy honeycomb fuselage, completely produced by computer-controlled, automated machines. Despite being under the 5700kg range meaning the Premier 1/1A can be certified as a light aircraft for operation by a single pilot, it sports a medium jet sized cabin in terms of cross section. The powerplants are Williams International FJ44-2A engines that are built on themes of simplicity, low fuel consumption, and high-altitude thrust performance. Collins Pro Line 21 avionics are featured with total system integration and instrument placement designed to make single-pilot operation easy, simple and safe.
First Flight was on December 22, 1998 flown by Charlie Volk and Warren Gould.
On March 23, 2001, the FAA issued type certification for the Beechcraft Premier I.
On September 22, 2005, the Premier IA was certified.
With the introduction of the Premier IA business jet program, Raytheon Aircraft has established itself as the world leader in composite technology for general aviation aircraft. The fuselage is designed on computer using CATIA (Computer-Aided Three-Dimensional InterActive Application). The data is then programmed into the fiber placement machine. This process between Engineering and Manufacturing ensures the final product is precisely constructed and conforms to quality specifications.
The fuselage is fabricated on special tooling utilizing a $6 million automated fiber placement machine, the Cincinnati “Viper” System. The machine fabricates the fuselage in two pieces: the forward fuselage (the cabin and nose section) and the aft fuselage (the non-pressurized section supporting the tail, engines and most of the electrical and air systems as well as the main baggage compartment).
The “Viper” machine is controlled by “Acraplace” software that translates the CATIA electronic solid models representing the fuselage composite shell designs into precise three-dimensional instructions. This enables the machine to place every strip of carbon fiber “prepreg” (pre-impregnated with resin) in exact position as designed to achieve maximum strength with minimum weight.
The fiber placement machine is able to produce the entire pressure vessel in about 1 week, which is considerably faster and more efficient than the traditional hand-lay-up process. Composites have a positive effect on operating costs. The carbon fiber fuselage is highly resistant to fatigue and corrosion and has no life limit. Minor damage is considerably easier and less costly to repair.
General characteristics
- Crew: 1-2
- Capacity: 6-7 passengers (depending on crew compliment)
- Length: 46 ft 0 in (14.02 m)
- Wingspan: 44 ft 6 in (13.56m)
- Height: 15 ft 4 in (4.67 m)
- Empty weight: 8,430lb (3,824 kg)
- Max takeoff weight: 12,500 lb (5,670 kg)
Performance
- Maximum speed: 519 mph (451 knots, 835 km/h, Mach 0.81) at FL 330
- Range: 1,360 nm (2,519 km) with maximum fuel and 45 minute reserve
- Service ceiling: 41,000 ft (12,497 m)
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