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Wednesday, 12 December 2012

The Raytheon 390 Premier I






Type  

Light corporate jet

History  

The Model 390 Premier I is the first all new product of the Raytheon Aircraft Beech/Hawker combine to fly, and is an all new entry level corporate jet designed to compete head on with Cessna's highly successful CitationJet/CJ1 series.

Design work on the Premier I began in early 1994 under the designation PD-374. Development go-ahead was authorised in early 1995, and initial details of the new jet were released in mid 1995. Raytheon publicly launched the Premier I at the NBAA (National Business Aircraft Association) convention in Las Vegas in September 1995, where a full size cabin mockup was on display.

Construction of the first Premier I began in late 1996 and rollout was on August 19 1998. Four Premier Is were used in the flight test program with the first flying on December 22 1998. Certification was achieved in early 2001.

The Premier I was designed using CATIA computer aided design. Features include its composite carbonfibre/epoxy honeycomb fuselage, swept metal construction wings, T-tail and two WilliamsRolls FJ-44 turbofans.

The composite fuselage is an important feature for a number of reasons. Firstly, advanced production techniques (using computer controlled automated machines) means a Premier I fuselage can be constructed in just one day, whereas a conventional airframe would require one to two weeks to complete. The composite construction also allows greater (approx 13%) internal cabin space compared with a conventional construction fuselage of the same external dimensions.

The Premier I is certificated for single pilot operations. The flightdeck features the new Collins Pro Line 21 EFIS avionics suite with two 20 x 25cm (8 x 10in) flat panel LCDs.

Raytheon intends that the Premier I will form the basis of a new family of business jets.


Country of origin  

United States of America

Powerplants  

Two 10.2kN (2300lb) WilliamsRolls FJ442A turbofans.

Performance  

Max cruising speed 854km/h (461kt). Max certificated operating altitude 41,000ft. Takeoff length at MTOW at S/L less than 915m (3000ft). Max range at long range cruising speed with IFR reserves 2780km (1500nm). Time to climb to 37,000ft at max takeoff weight at SL 15min.

Weights  

Basic operating 3626kg (7996lb). Max takeoff 5670kg (12,500lb) Payload with full fuel and one pilot 429kg (946lb).

Dimensions  

Wing span 13.56m (44ft 6in), length 13.81m (45ft 4in), height 4.66m (15ft 4in).

Capacity  

One or two pilots on flightdeck (will be certificated for single pilot). Main cabin seats six in standard configuration with four seats in a club arrangement and two seats behind them. Toilet in rear fuselage. Baggage compartments in nose and tail.

Production  

More than 300 orders held at late 2001. First deliveries planned for second half of 2001. Planned production of 50 per year.







Er Neha Godbole B.E (Computer Science), PGDM (PM & HRD) 
Executive HR 
www.AeroSoftCorp.com  
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www.AeroSoft.co.in 
www.AeroSoftseo.com 
http://ernehagodbole.blogspot.com 


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