Hawker Beechcraft 390 Premier

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Hawker Beechcraft 390 Premier
Hawker Beechcraft 390 Premier 1
Type: Business jet
Design country:

United StatesUnited States United States

Manufacturer:

Hawker Beechcraft

First flight:

December 22, 1998

Commissioning:

2001

Production time:

since 2001

Number of pieces:

> 260

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) and light aluminum , which is used on the wings. The structure of the surface of the rudder fin , which consists of graphite layers, is an exception . The turbofan engines of the type Williams Rolls-Royce FJ44-2A disposed at the upper rear, the wing assembly is to be designated as low-wing aircraft. The fuselage has a round cross-section with a lowering on the inside to provide additional headroom. Today the manufacturer is Textron Aviation from Wichita in Kansas .

history

In 1994 Raytheon began developing a light business jet that was intended to compete with Cessna's Citation range . The rollout took place on August 19, 1998 and the first flight took place on December 22, 1998. The FAA approved after the testing of four machines on March 23, 2001. More than 260 machines (as of the end of 2008) have been delivered so far, including machines of the further development Premier 1A which was approved on September 22, 2005. In addition to improvements to various systems, this also included a new cabin design. The successor model Premier 2 with more powerful Williams FJ44 -3AP 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 was to come onto the market as the Hawker 200 and enter service at the end of 2012. However, after Hawker Beechcraft went bankrupt in 2012, production of jet-powered business aircraft was discontinued and development of the Hawker 200 was discontinued. Support for business jets that have already been delivered will be continued by the successor company, Beechcraft Corporation .

Certification

The Raytheon 390 Premier 1 is FAR 23 and FAR 36 approved.

ICAO designation

The ICAO - 4 letter code for the Raytheon 390 Premier 1 is PRM1. This code is entered in an ICAO flight plan, for example.

technology

Avionics

The Premier IA is equipped with the fully integrated Collins Pro Line 21 ™ avionics (glass cockpit). All relevant data (such as electronic Jeppesen maps, weather information, etc.) are shown to the pilot on three screens.

Engines

Hawker Beechcraft 390 Premier 1A at ILA 2012.

The above mentioned engines with a take-off rating of 2300 lbs. Thrust (the same values ​​apply to the highest continuous thrust and highest climb thrust) are approved according to the Williams - Rolls FJ44-2A maintenance manual for the use of commercial aviation kerosene of the types Jet A, Jet A-1 and JP-8. As an exception, ASTM D910 AVGAS 100 LL jet fuel may be used to a limited extent between two major periodic inspections (maximum 5000 USG).

landing gear

The aircraft is equipped with a retractable, three-part landing gear. The main landing gear uses an air-oil strut and is retracted inward into the central wing structure. The tires are H22 × 8.25-10, twelve-layer, tubeless. The front landing gear has an air-oil damper and is pulled forward (seen in the direction of flight) into the fuselage. The front tire is 18 × 4.4, six-ply, tubeless. The Premier 1 has a wheelbase of 17 ft. 5 in. (5.31 meters) with a track width of 9 ft. 3 in. (2.82 meters). Each main landing gear has brakes equipped with an anti-lock device with independently operating supplies and a hydraulic backup. In an emergency, the landing gear is extended by a free fall system and a hydraulic backup.

Flight control

The aircraft is approved for single pilot operation, but has double controls for the captain and copilot. A three-axis trim system influences the trim around the roll, yaw and pitch axes. The spoilers are electronically controlled and driven hydraulically. The spoilers offer braking, lift destruction and roll support functions. The single slotted Fowler flaps are electrically controlled and driven.

Hydrofoil

  • Wing area 246.79 square feet = 22.26 square meters
  • Wingspan see below, external dimensions
  • mean aerodynamic wing depth = 5 feet and 6.24 inches (1.68 meters)
  • Aspect ratio = 8,604: 1
  • positive V position = 2.5 °
  • Sweep: leading edge of the wing 22.82 ° / trailing edge of the wing 10.97 °

Outer wing flaps

  • Outer wing flap area 2 * 10.94 square feet (2 * 0.98 m²)
  • Outboard flap span: 9 feet 0 inches (2.74 meters)
  • Possible deflection angles: retracted, 10, 20, extended

Inner wing flaps

  • Inner wing flap area 2 * 7.00 square feet (2 * 0.63 m²)
  • Inner wing flap span: 4 feet 10 inches (1.47 meters)
  • possible deflection angles: see outer wing flaps!

Roll trim device

  • Roll Trim Wing Area: 2 * 0.31 square feet (2 * 0.028 m²)
  • Roll Trim Wingspan: 1 foot 6.48 inches (0.47 meters)
  • Max. Deflection angle d. Roll trim wings: 20 ° up… 20 ° down

Fuel system

The fuel system consists of a (independent) right and left subsystem with devices for the transfer of aviation fuel from one tank to the other. Each subsystem contains a “wet” integral wing tank with the option of tank filling, tank emptying and tank filling quantity measurement as well as a fuel feed system for the associated engine. Two pumps with electric reserve pumps belong to the engines. The fuel transfer capability of the Premier 1 is generated by the gear pump, which can run in two directions. The most important fuel quantities are listed as follows:

Type of fuel quantity Gravity filling Single point filling
Total capacity 552.8 USGal = 3704 lbs. 541.8 USGal = 3631 lbs.
Usable amount of fuel 539.0 USGal = 3611 lbs. 528 USGal = 3538 lbs.
non-drainable amount of fuel 1.86 USGal = 12.5 lbs. 2.46 USGal = 16.5 lbs.
Unusable amount of fuel 15.7 USGal = 105.2 lbs. 16.3 USGal = 109.2 lbs.

Hydraulic system

Each engine drives a hydraulic pump that generates 3000 psi (207 bar) pressure. This pressure is used by the landing gear, spoiler system and the anti-lock braking system.

Arrangement of the interior

The interior of the aircraft is divided into two sectors: cockpit and cabin. The cockpit contains a pilot seat and a copilot seat, instruments and control boards as well as other equipment (e.g. oxygen masks). The passenger cabin contains seats in various configurations, a toilet, a luggage rack, a main entrance door, an emergency door and equipment for passenger comfort such as a kind of coat rack, map table, etc.

Dimensions, areas, general data

External dimensions
The aircraft is 46 feet, corresponding to 14.02 meters, and has a wingspan of 44 feet and 6.0 inches, corresponding to 13.56 meters, and the height is up to 15 feet and 3.6 inches (4.66 meters) measured at normal tire inflation and immersion depth of the shock absorbers.
Hull dimensions
Length with cockpit = 18 ft. 6.7 in. (5.66 meters)
Length without cockpit = 12 ft. 9.6 in. (3.90 meters)
Width = 5 ft. 6.4 in. (1.69 in.) Meter)
height = 5 ft. 5.1 in. (1.65 meters)
Internal volumes
approximately 429 cubic feet (12.87 m³)
cockpit: 97.9 cubic feet
cabin: 331.5 cubic feet

Technical specifications

All specifications mentioned in this article refer to serial number RB-2 and following.

Parameter Data
crew 1-2
Passengers 6th
length 14.02 m
span 13.56 m
height 4.67 m
Wing area 22.26 m²
Wing extension 8.604
payload 635 kg at Premier IA
Empty mass 3824 kg
Max. Takeoff mass 5670 kg
Cruising speed ? km / h (861 km / h for Premier II)
Top speed 841 km / h
Service ceiling 12,497 m or 41,000 ft (13,700 m for Premier II)
Range 2519 km with maximum fuel and 45 minutes reserve (2778 km for Premier II)
Engines two Williams-Rolls FJ44-2A with 10.23 kN thrust each

Web links

Commons : Beechcraft Premier  - collection of pictures, videos and audio files

Individual evidence

  1. ↑ FliegerRevue November 2008, p. 67, data sheet Premier 1
  2. ↑ Deagel: Data Sheet