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  • FAKEL ENGINEERING DESIGN BUREAU NAMED AFTER ACADEMICIAN GRUSHIN
    SA 5 SA 8 SA 10 and SA 15 were adopted by armed forces in 60 countries and still remain in service Today Fakel is a large scientific research center able to design develop and manufacture missiles with a wide range of performances Fakel has unique hightech experimental complexes and production bases which makes it able to produce and to test different military and civil goods Fakel can develop high

    Original URL path: http://www.aviamarket.org/directory/f/267-fakel-engineering-design-bureau-named-after-academician-grushin.html (2016-02-13)
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  • Dassault Falcon 900
    max takeoff 20 640kg 45 500lb DIMENSIONS Wing span 19 33m 63ft 5in length 20 21m 66ft 4in height 7 55m 24ft 9in Wing area 49 0m2 527 4sq ft ACCOMMODATION Flightcrew of two Main passenger cabin accommodation for between eight or 15 passengers or as many as 18 in a high density configuration OPERATORS Algeria Australia France Gabon Japan Malaysia Nigeria South Africa Spain Syria United Arab Emirates HISTORY Of the more than 150 transcontinental Falcon 900s built so far a significant number are operated as military VIP transports Dassault announced it was developing a new intercontinental range large size business jet based on its Falcon 50 trijet at the 1983 Paris Airshow Development culminated in the prototype Spirit of Lafayette flying for the first time on September 21 1984 A second prototype flew on August 30 1985 and this aircraft demonstrated the type s long range potential by flying nonstop from Paris to Little Rock Arkansas in the USA for a demonstration tour While of similar overall configuration to the Falcon 50 the Falcon 900 features an all new widebody fuselage which can seat three passengers abreast and is also considerably longer and wider The main commonality with the Falcon 50 is the wing which despite being originally designed for a considerably lighter aircraft was adapted almost directly unchanged and incidentally also appears on the new Falcon 2000 twin Design of the Falcon 900 made extensive use of computer aided design while the aircraft s structure incorporates a high degree of composite material From 1991 the standard production model was the Falcon 900B which differs from the earlier 900 in having more powerful engines increased range and the ability to operate from unprepared strips and Category II visibility approach clearance A further improved development is the 900EX with

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/457-dassault-falcon-900.html (2016-02-13)
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  • Dassault Falcon 2000
    25 October 2001 two aircraft F WMEX and c n 02 F W66A Completed 568 hours of flight testing in 242 flights culminating in JAA and FAA certification on 25 March 2003 first three green production airframes delivered to Little Rock completion centre in January 2003 with first customer deliveries of outfitted aircraft expected in the second quarter of2003 Pro Line avionics EASy flight deck available from second quarter of 2004 Falcon 2000EX manufactured in parallel with Falcon 2000 New features include two Pratt Whitney Canada PW308C turbofans with FADEC each rated at 31 1 kN 7 000 lb st for take off at ISA 15 C Nordam advanced single pivot ASP thrust reversers revised fuel system with 2 045 kg 4 508 lb increase in usable fuel capacity to 9 414 litres 2 487 US gallons 2 071 Imp gallons strengthened main landing gear with heavy duty braking system and Falcon 900EX nose landing gear and new bleed air system The first 40 Falcon 2000EXs will retain the current Collins Pro Line 4 avionics suite but aircraft delivered from March 2004 will be equipped with Dassault EASy flight deck with four tube flat panel displays based on those of the Honeywell Primus Epic modular avionics system and designated Falcon 2000EX EASy first flight with EASy cockpit F WXEY 29 January 2003 CUSTOMERS The 206th Falcon 2000 was delivered to the USA for outfitting on 10 December 2003 Production totalled 20 in 1997 15 in 1998 34 in 1999 26 in 2000 35 in 2001 35 in 2002 and three in the first three months of 2003 Falcon 2000 No 159 N259QS delivered to Executive Jet on 11 September 2001 was also 1 500th Falcon Mystere business jet produced by Dassault Total of 72 Falcon 2000s and 28 Falcon 2000EXs plus 25 Falcon 2000EXs on option ordered by Executive NetJets and NetJets Middle East fractional ownership programmes in Europe Middle East and USA of which 38 were in operation by October 2002 Royal Australian Air Force ordered three in 2000 to replace five leased Falcon 900 s Total market estimated at more than 300 in 10 years COSTS Basic price 2000 US 20 6 million 2001 2000EX US 24 million 2000 DESIGN FEATURES Same fuselage cross section as Falcon 900 but 1 98 m 6 ft 6 in shorter Falcon 900 wing with modified leading edge and no inboard slats sweepback at quarter chord 24 50 to 29 STRUCTURE Largely as for Falcon 900 Rear tuselage including engine pods and pylons by Alenia and Piaggio thrust reversers by Dee Howard Agreement reached in early 2002 for production of fuselage components of 2000EX by Chengdu Aircraft of China New horizontal tail surface featuring cast titanium central box with resin transfer moulding composite spars and carbon fibre skin panels resulting in a 13 6 kg 30 lb reduction in weight certified by the DGAC in December 1999 and introduced as standard from December 2000 deliveries LANDING GEAR Retractable tricycle type mainwheels retract

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/191-dassault-falcon-2000.html (2016-02-13)
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  • FANTASY AIR
    at Pisek 1995 initial product launched as Cora in Legato and Allegro versions By mid 2000 was standardising on variants of Allegro Contact Details Address Kollarova 511 CZ 397 01 Pisek Czech Republic Tel 420 3 82 21 02 46 Fax 420 3 82 21 29 62 and 21 44 57 A B C D E F G H I J K L M N O P Q R S

    Original URL path: http://www.aviamarket.org/directory/f/1327-fantasy-air.html (2016-02-13)
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  • MIG-19
    of 30KhGSA steel Aluminum skins were machined w a max thickness of 19 in 4 8 mm Hydraulically boosted ailerons and hydraulically actuated w pneumatic emergency back up Fowler type flaps which could be used at their 12 o setting for maneuvering in combat at speeds up to 495 mph 797 km h on dual tracks were of conventional aluminum construction Each flap had an area of 18 5 ft 2 1 72 m 2 and their extension angles were 15 for takeoff and 25 for landing Two ailerons ea have an area of 8 40 ft 2 78 m 2 Left aileron was equipped w trim tab Aileron travel range was 20 o up or 20 o down Trim tab travel range was 10 o up or 10 o down Wing had single large fence w height of 12 57 in 320 mm on each side Original aircraft built w conventional elevators but these quickly were discarded in production and replaced w slab type stabilators w anti flutter mass balances faired onto tips These stabilators provided pitch control only Vertical tail assembly was conventional w single piece rudder Leading edge sweep angle of vertical fin was 56 o 37 Vertical fin thickness chord ratio was 8 Total vertical tail surface area including rudder was 44 9 ft 2 4 17 m 2 Rudder travel range was 25 o to either side The stabilators had a movable surface area of 59 2 ft 2 5 5 m 2 and a total area including fixed root segment of 83 73 ft 2 7 78 m 2 Stabilator thickness chord ratio was 7 and sweepback angle was 55 o Total stabilator span was 14 ft 4 in 4 46 m Stabilator actuation was via a BU 14MS ram and an ARU 2A automatic load adjuster for pilot artificial feel and stick inputs With advent of MiG 19S all control surfaces had an APS 4 electromechanical backup in the event of total hydraulic system failure MiG 19S also equipped w additional ventral airbrake and wing spoilers interfaced w the ailerons for increased roll control throughout envelope Landing Gear Conventional tricycle arrangement w free castoring nose gear Differential braking accommodated steering requirements until advent of MiG 19PF which introduced steerable nose gear Main gear retracted inward toward fuselage centerline and were stored in wells aft of main spar Nose gear retracted forward into well built into space between tunnel bifurcation Landing gear retraction and extension were hydraulically actuated w pneumatic emergency back up Lever type suspension utilized on all three units Main gear tire size was 25 9 in x 8 6 in 660 mm x 220 mm and nose gear tire size was 19 7 in x 7 in 500 mm x 180 mm Main gear inflation pressure was 129 lb in 2 883 kPa The wheel track was 13 ft 4 in 4 15 m and wheel base was 14 ft 2 in 4 398 m Brakes were pneumatically actuated A ventrally

    Original URL path: http://www.aviamarket.org/reviews/military-aircraft/1062-mig-19.html (2016-02-13)
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  • Gippsland GA200 Fatman
    and manual cable actuated Single slotted trailing edge wing flaps can be deployed to tighten turning radius during agricultural operations T O setting 15 maximum 38 Interconnect system applies bias to elevator trim spring when flaps extended to avoid pitch trim changes Fixed tab on rudder STRUCTURE Fuselage of welded SAE 4130 chromoly steel tube with removable metal side and top panels wings braced by overwing inverted V strut of aluminium each side and wire braced tail surfaces conventional all metal but wing spars constructed from sheet metal to expedite repairs wingtips detachable Rear fuselage and tail surfaces are fabric covered LANDING GEAR Non retractable with 6 in diameter Cleveland P N 40 84A mainwheels mounted on tubular steel side Vs wire cutter on leading tube of landing gear legs rubber cord shock absorption with hydraulic dampers and Cleveland heavy duty hydraulic disc brakes Mainwheel tyres size 8 50x6 6 ply Scott 3200 steerable castoring tailwheel size 5 00 5 4 ply mounted on multileaf flat springs POWER PLANT One 224 kW 300 hp Textron Lycoming IO 540 K1A5 flat six engine driving a Hartzell HCC2YR 1BF F8475R constant speed two blade metal propeller AEIO 580 installation under test in 2003 offering additional 22 kW 30 hp Fuel in integral tank in each wing combined usable capacity 200 litres 52 8 US gallons 44 0 Imp gallons plus small 14 litre 3 7 US gallon 3 1 Imp gallon header tank in upper front fuselage Oil capacity 11 4 litres 3 0 US gallons 2 5 Imp gallons ACCOMMODATION Two energy absorbing seats side by side smaller right hand seat for loader driver dual controls and second set of rudder pedals for right hand seat in Agtrainer Four point 25 g restraint hamess es Cockpit doors open upward each with bulged window to improve shoulder room and outward view Pressurisation system minimises dust and chemical ingress SYSTEMS 14 V 95 A automotive alternator and automotive or R 35 aviation battery for electrical power 50 A circuit breaker switch serves as master switch AVIONICS Instrumentation Basic VFR instruments and VHF torn only EQUIPMENT One 1 050 litre 277 US gallon 231 Imp gallon capacily hopper in forward fuselage approximately 76 litres 20 0 US gallons 16 7 Imp gallons less in Agtrainer with minimum load dump time of five seconds Multirole door hopper outlet eliminating need to change nulla when changing between solids and liquids can also be used for fire bombing or laying of fire retardants Spreader vanes can be added to increase swath width Cable cutters on landing gear legs and windscreen 100 W landing light in each wingtip 28 V night working lights system two retractable underwing 600 W lights powered by separate 28 V 55 A alternator also available DIMENSIONS EXTERNAL Wing span standard version 11 985 m 39 ft 3 3 4 in Wing chord constant 1 60 m 5 ft 3 in Wing aspect ratio 7 3 Laiglh overall flying attitude 7 48 m 24

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/447-gippsland-ga200-fatman.html (2016-02-13)
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  • FED SCIENTIFIC PRODUCTION CORPORATION
    used on engines of varios type and versions and work successfully on aircraft of well known type such as Su MiG An Tu YaK IL Mi Ka They have high level of operation life reliability manufacturing quality small dimensions and weight which allowed using them on all types of airplanes and helicopters manufactured in CIS and operated in more then 60 countries The new MS based ISO 9002 quality system

    Original URL path: http://www.aviamarket.org/directory/f/200-fed-scientific-production-corporation.html (2016-02-13)
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  • MYASISHCHEV DESIGN BUREAU
    in Design of aircraft of any classes development of multistage space systems development of airships and heli aerostats aircraft conversion and tests experimental investigations on air platforms design and experimental test bed development of aircraft and space vehicles systems and accessories flight tests of vehicles for safe landing of people and cargoes Development of automated equipment for light industry development of high efficient devices and mechanisms of different application Contact

    Original URL path: http://www.aviamarket.org/directory/m/256-myasishchev-design-bureau.html (2016-02-13)
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