Beechcraft Premier I
The Hawker Beechcraft 390 Premier (formerly Raytheon 390 Premier 1) is a twin-engine business jet with a maximum take-off mass of 5700 kg. It consists mainly of carbon fiber reinforced epoxy resin ( honeycomb structure ) as well as lightweight aluminum, which is to use the wings. An exception, the structure of the surface of the vertical stabilizer, which consists of graphite layers. The turbofan - engine " Williams - Rolls FJ44 -2A Inc. " with an oil capacity of 3.8 quarts 2 * (2 * 3.6 liter ) are arranged at the upper tail, the wing assembly can be described as low-wing monoplane. The hull has to make a round cross section with reduction inside available extra headroom. Manufacturer is now Hawker Beechcraft of Wichita, Kansas. All specifications given in this article refer to series number RB -2 and following.
- 5.1 Specifications
History
In 1994, Raytheon began with the development of a light business jets was intended as competition pattern to Cessna Citation series. The roll-out took place on 19 August 1998 and the first flight took place on 22 December 1998. The approval of the FAA performed according to the testing of four machines on March 23, 2001. More than 260 machines (as of end of 2008) have been delivered, including the development of machines Premier 1A which was approved on 22 September 2005. Alongside improvements to various systems This also included a new cabin design. The follow pattern 2 Premier Williams FJ44 - 3AP with more powerful engines with 26.8 kN thrust and winglets has been announced for 2010. This should have a higher speed, range and payload. The Premier II is to come as a Hawker 200 on the market and go into service in late 2012.
Certification
The Raytheon 390 Premier 1 is approved in accordance with FAR 23 and FAR 36.
ICAO - the name
The ICAO - 4 letter code for the Raytheon 390 Premier 1 is PRM1. This code is entered, for example, in an ICAO flight plan.
Technology
Avionics
The Premier IA is equipped with the fully integrated Collins Pro Line 21 ™ avionics (glass cockpit). On three screens the pilots all the relevant data ( such as electronic Jeppesen maps, weather, etc.) are displayed.
Engines
The designated above engines with a takeoff rating of 2300 lbs. Thrust (same values apply to maximum continuous thrust and highest climb thrust ) are, according to Williams - Rolls FJ44 -2A Maintenance Manual for the use of commercial flight of the varieties kerosene Jet A, Jet A -1 and JP -8 approved. Between two major recurring inspections exceptionally aviation gasoline AVGAS ASTM D910 100 LL may ( most 5000 USGal. ) Can be used is limited.
Landing gear
The aircraft is equipped with a retractable, three-piece landing gear. The main landing gear uses an air-oil strut and is retracted inwardly into the central wing structure. The tires are of size H22 x 8.25 to 10, zwölflagig, tubeless. The front suspension features an air-oil damper, and is ( as seen in the direction of flight) pulled forward into the fuselage. The front tire is the size of 18 x 4.4, six layers, tubeless. The Premier 1 has a wheel base of 17 ft. 5 in. ( 5.31 meters) with a track width of 9 ft. 3 in. (2.82 meters). Each main landing gear was provided with an anti-lock braking device with independently operating supplies and a hydraulic backup. In an emergency, the landing gear is extended by a free-fall system and also a hydraulic backup.
Flight control
The aircraft is certified for single pilot operation (single pilot), but has dual controls for pilot and copilot. A three-axis Trimsystem affects the trim around the roll, yaw and pitch axis. The spoilers are electronically controlled and hydraulically driven. The spoiler offer both a brake, buoyancy destruction and Roll Support. The easy- slotted Fowler flaps are electrically controlled and driven.
Hydrofoil
- Wing area 246.79 square feet = 22.26 square meters
- Wingspan see below, outer dimensions
- Mean aerodynamic chord = 5 feet and 6.24 inches ( 1.68 meters )
- Aspect ratio = 8.604:1
- Positive V - position = 2.5 °
- Sweep of the wing leading edge 22.82 ° / 10.97 ° trailing edge
Outer wing flaps
- Outer wing flap surface 2 * 10.94 square feet (2 * 0.98 m²)
- Outer wing flaps span: 9 feet 0 inches ( 2.74 meters)
- Possible deflection angle: retracted, 10, 20, extended
Inboard wing flaps
- Inboard wing flap surface 2 * 7.00 square feet (2 * 0.63 m²)
- Inboard wing flaps Wingspan: 4 feet 10 inches (1.47 meters)
- Possible deflection angle: see outer wing flaps!
Roll trimmer
- Rolltrimmungs - Wing area: 2 * 0.31 square feet (2 * 0.028 m²)
- Rolltrimmungs - Wingspan: 1 foot 6.48 inches ( 0.47 meters)
- Max. Deflection angle d Rolltrimmungs - Wing: 20 ° up 20 ° down ...
Fuel system
The fuel system consists of a (each independent ) right and left sub-system with devices for the transfer of aviation fuel from one into the other tank. Each subsystem contains a "wet " integral wing tank with the ability to tank filling, emptying tanks and tank capacity measurement, and a fuel supply system for the associated engine. Two pumps with electric stand-by pumps are one of the engines. By executable in two directions gear pump, fuel transfer capability of the Premier 1 is generated. The main quantities of fuel are set up as follows:
Hydraulic system
Each engine drives a hydraulic pump which generates 3000 PSI pressure. This pressure is used by landing gear system as well as the spoiler anti-lock brake system.
Arrangement of the interior
The interior of the aircraft is divided into two sectors: the cockpit and cabin. The cockpit includes a pilot and a copilot, instruments and control boards and other equipment (eg oxygen masks). The passenger cabin includes seats in various configurations, a toilet, a luggage rack, a main entrance door, an emergency door and equipment for passenger comfort as a kind of cloak cloakroom, card table, etc.