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  • MiG-29K/KUB
    aircraft has an arrester hook and a reinforced landing gear Its flight life and service life are also increased to 6 000 flying hours and 30 40 years correspondingly The aircraft is maintained on condition EQUIPMENT The aircraft has an open architecture avionics suite based on the MIL STD 1553B multiplexing bus enabling integration of onboard equipment and weapon systems of Russian and foreign origins at customer requests The MiG 29K aircraft is equipped with the modern weapons control system including the Zhuk ME new multifunctional radar with enhanced operational range multi channel fire capability and modern air to ground modes of operation The optical locating station and helmet mounted targeting system make the avionic suite of the aircraft functionally complete Integration of the targeting and navigational equipment on the basis of the modern computing system has resulted in much greater target acquisition range and sighting angles while the number of targets simultaneously engaged is increased to four ARMAMENT The weapons mix of the aircraft includes the RVV AE and R 73E air to air guided missiles air to surface guided weapons such as the Kh 35E and Kh 31A anti ship missiles Kh 31P anti radiation guided missiles and KAB 500Kr guided bombs Unguided weapons include the FAB 500 air bombs and rockets The aircraft is armed with the GSh 301 built in gun VARIANTS The MiG 29KUB ship borne combat trainer is designed for naval aviation pilots training and mastering flying skills monitoring their techniques of flight management navigation and combat employment as well as pilot transition to the MIG 29K aircraft In terms of its combat mission the MiG 29KUB performs the entire scope of MiG 29K assigned combat tasks The MiG 29KUB has a high degree of design commonality with the MiG 29K aircraft It is

    Original URL path: http://www.aviamarket.org/reviews/military-aircraft/410-mig-29kkub-shipborne-multirole-fighter.html (2016-02-13)
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  • Aeritalia G91
    18 1m 2 195 2sq ft ACCOMMODATION Pilot only except G91T which seats two in tandem ARMAMENT G91Y Two 30mm DEFA 532 cannon with 125 rounds per gun mounted in the forward fuselage Disposable payload of up to 1815kg 4000lb including Sidewinder AAMs bombs and rockets OPERATORS Italy HISTORY The Fiat G91 was the result of an early 1950s design contest to produce a light attack fighter for NATO member countries Eight European companies responded to the 1953 NATO requirement to yield a light strike aircraft that was not reliant upon lengthy concrete runways The winner of the competition was Fiat with its G91 which was designed by Giuseppe Gabrielli although this decision was not made until 1957 when the prototype had been evaluated against three French contenders The G91 s first flight had earlier occurred on August 9 1956 Although the single Bristol Orpheus powered G91 was selected as the clear winner of the design contest interest in the concept had waned and the aircraft did not see the widespread European NATO service envisioned for it Italy took delivery of the first production G91s armed with four 12 7mm 0 5in Colt Browning machine guns in 1958 Numerous variants followed including the G91R 1 reconnaissance variant with a suite of cameras mounted in a shortened nose The G91R 1A had improved navaids and the 1B strengthened undercarriage The G91R 3 meanwhile was similar but developed for the West German Air Force and built under licence in that country some of which were later acquired by Portugal It was equipped with a Doppler radar and twin 30mm cannon The final single seat G91R variant was the G91R 4 it was similar to the German G91 R3 but had the original R 1 armament and some minor equipment changes The G91T

    Original URL path: http://www.aviamarket.org/reviews/military-aircraft/461-aeritalia-g91.html (2016-02-13)
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  • Gulfstream G100
    are usable Additional fuel can be carried in 378 5 litre 100 US gallon 83 3 Imp gallon removable auxiliary tank in forward area of baggage compartment with baggage weight limilation imposed all usable Single pressure refuelling point in lower starboard side of fuselage aft of wing or single gravity point in upper fuselage allow refuelling of all tanks from one position Fuel sequencing automatic ACCOMMODATION Crew of two on flight deck Dual controls standard Sliding door between flight deck and cabin Standard accommodation in pressurised cabin for six persons two in forward facing seats at front and four in club layout galley port or starboard at front of cabin coat closet forward starboard lavatory at rear All six seats individually adjustable fore and aft laterally and can be swivelled or reclined all fitted with armrests and headrests Two wall mounted foldaway tables between club seat pairs Coat closet houses stereo tape deck Maximum accommodation for nine passengers New cabin interior first redesign since 1986 introduced in September 1999 has less intrusive curved cabinetry and galley units restyled headliner and sidewall panels new seats tables and lighting Forward club searing maximises recline angle and personal space for each occupant lavatory has brighter lighting more storage space for coats and carry on baggage Plug type airstair door at front on port side emergency exit over wing on each side Heated baggage compartment aft of passenger cabin with external access and service ladder Service compartment in rear fuselage houses aircraft batteries or optional APU electrical relay boxes inverters and miscellaneous equipment SYSTEMS Honeywell environmental control system using engine bleed air with normal pressure differential of 0 61 bar 8 8 lb sq in Honeywell 36 150 W APU available optionally Two independent hydraulic systems each at pressure of 207 bar 3 000 lb sq in Primary system operated by two engine driven pumps for actuation of anti skid brakes landing gear nosewheel steering spoilers lift dumpers and primary control surfaces Back up system operated by electrically driven pump provides power for emergency parking brake primary control surfaces and thrust reversers Electrical system comprises two Lucas Aerospace 300 A 30 V DC engine driven starter generators with two 1 kVA single phase solid state inverters operating in unison to supply single phase 115 V AC power at 400 Hz and 26 V AC power for aircraft instruments Two 24 V 24 Ah Ni Cd batteries for engine starting and to permit operation of essential flight instruments and emergency equipment 28 V DC external power receptacle standard Pneumatic de icing of wing leading edge slats and tailplane leading edges thermal anti icing of engine intakes Oxygen system for crew pressure demand and passengers drop down masks supplied by 2 18 m 3 77 cu ft cylinder with second cylinder of same capacity optional Two bottle Freon type engine fire extinguishing system standard AVIONICS Rockwell Collins Pro Line 4 suite standard Comms Dual VHF 422C radios RTU 4220 radio tuners TDR 94D transponders Baker B12135

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/999-gulfstream-g100.html (2016-02-13)
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  • Gulfstream G150
    weights but same range and cruising speed G200 style windscreen and cabin windows latter reduced in number from six to five Differences from G100 summarised below POWERPLANT Two 19 6 kN 4 400 lb st Honeywell TFE731 40R turbofans ACCOMMODATION Two pilots and between six and eight passengers in three choices of interior DIMENSIONS EXTERNAL Wing span 16 94 m 55 ft 7 in Length overall 17 25 m 56 ft 7 1 4 in Height overall 5 54 m 18 ft 2 in DIMENSIONS INTERNAL Cabin Length 5 41 m 17 ft 9 in Max width 1 75 m 5 ft 9 in Max height 1 75 m 5 ft 9 in Volume 13 17 m 3 465 cu ft Baggage volume main compartment 1 56 m 3 55 cu ft overhead bins 0 25 m 3 8 8 cu ft WEIGHTS AND LOADINGS Basic operating weight including two pilots 6 849 kg 15 100 lb Payload max 1 089 kg 2 400 lb with max fuel 363 kg 800 lb Max fuel weight 4 581 kg 10 100 lb Max T O weight 11 725 kg 25 850 lb Max landing weight 9 843 kg 21 700 lb

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/84-gulfstream-g150.html (2016-02-13)
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  • Gulfstream G200
    45 fully up and Fowler single slotted inboard and outboard trailing edge flaps settings 0 12 20 and 40 Ailerons and elevators can be operated manually in event of hydraulic failure STRUCTURE Generally similar to that described for G100 Sogerma France produced tail units doors access panels tailcones and wing fuselage fairings for prototypes Flight Environments cabin flame protection and sound attenuation system LANDING GEAR Hydraulically retractable tricycle type twin wheels and oleo pneumatic shock absorbers on each unit Nose unit has electrohydraulic steering 60 and retracts forward Trailing link mainwheel units retract inward and are equipped with Honeywell multidisc anti skid carbon brakes POWER PLANT Two FADEC equipped Pratt Whitney Canada PW306A turbofans each flat rated at 26 9 kN 6 040 lb st pylon mounted on sides of rear fuselage Nordam nacelles and thrust reversers Fuel in seven tanks right and left wing each 1 334 litres 352 5 US gallon 293 5 Imp gallons right and left feed each 102 litres 26 9 US gallons 22 4 Imp gallons centre 1 533 litres 405 US gallons 337 Imp gallons forward 1 011 litres 267 US gallons 222 Imp gallons and fuselage 3 115 litres 823 US gallons 685 Imp gallons Total fuel 8 532 litres 2 254 US gallons 1 877 Imp gallons of which 8 479 litres 2 240 US gallons 1 865 Imp gallons are usable ACCOMMODATION One or two pilots provision for jump seat for third crew member Standard club type seating for four to eight persons in business executive version legroom between facing seats allows enough space for full reclining and berthing large galley with room for refrigerator microwave oven coffee maker and storage Alternative 10 passenger layout has four club seats at front with a four place conference group and two on a divan to the rear plus optional lavatory and additional baggage space aft Three abreast seating for up to 18 passengers with single aisle can be provided in corporate shuttle configuration Generous baggage compartment in rear fuselage accessed by external airstair door can accommodate baggage for all 18 passengers Entire accommodation including baggage compartment is pressurised Airshow in flight cabin entertainment system optional SYSTEMS Dual hydraulic systems each 207 bar 3 000 lb sq in Electrical system comprises three including one on APU Lucas Aerospace 28 V 400 Ah engine driven starter generators two 24 V 43 Ah Ni Cd batteries and a Honeywell GTCP36 150 APU Third 24 V 27 Ah battery for back up powering of essential flight instruments and emergency systems Pneumatic system for emergency extension of landing gear actuation of wheel brakes and thrust reversers and de icing of wing leading edges Cabin pressurisation and air conditioning system differential 0 61 bar 8 8 lb sq in One optionally two oxygen bottles AVIONICS Rockwell Collins Pro Line 4 suite standard Comms Dual VHF 422C radios RTU 4220 radio tuners TDR 94D transponders Bendix King KHF 950HF and Baker B1045 F512 audio systems triple Magnastar Flightphones single

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/85-gulfstream-g200.html (2016-02-13)
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  • Alenia G222
    Can carry a 9600kg 21 165lb payload comprisinglight vehicles and artillery Two Libyan G222s equipped for VIPs ARMAMENT None OPERATORS Argentina Dubai Italy Libya Nigeria Somalia Thailand USA HISTORY The G222 s origins date back to an early 1960 s NATO requirement for a V STOL tactical transport The NATO requirement spawned a number of exotic V STOL concepts none of which were practical The Italian Air Force placed a contract with Fiat to develop its G222 V STOL concept but importantly that contract was later extended to cover a conventionally configured STOL development which laid the ground work for the definitive G222 transport The Italian Air Force placed a contract for two prototype G222s in 1968 and after a number of delays caused by external forces the first G222 made the type s first flight on July 18 1970 The two prototypes were unpressurised and powered by two lowerrated CT64 820 engines but other wise the prototype and production aircraft were similar Design features of the G222 include its goodshort field performance large double slotted flaps barrel shapedfuselage rear freight ramp and tandem main under carriage wheels with levered suspension Much of the Italian aerospace industry wasinvolved in the

    Original URL path: http://www.aviamarket.org/reviews/military-aircraft/493-alenia-g222.html (2016-02-13)
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  • Gulfstream G300 and G400
    Aerostructures Corporation LANDING GEAR Retractable tricycle type with twin wheels on each unit Main units retract inward steerable nose unit forward Mainwheel tyres size 34x9 25 16 18 ply tubeless pressure 12 07 bar 175 lb sq in Nosewheel tyres size 21x7 25 10 10 ply tubeless pressure 7 93 bar 115 lb sq in maximum steering angle 82 Dunlop air cooled carbon brakes Aircraft Braking Systems anti skid units and digital electronic brake by wire system Dowty electronic steer by wire system Turning circle about wingtip 14 43 m 47 ft 4 in about nosewheel 12 04 m 39 ft 6 in POWER PLANT TWO Rolls Royce Tay Mk 611 8 turbofans each flat rated at 61 6 kN 13 850 lb st to ISA 15 C Target type thrust reversers Fuel in two integral wing tanks with total capacity of 16 542 litres 4 370 US gallons 3 639 Imp gallons in GIV G400 and 15 141 litres 4 000 US gallons 3 331 Imp gallons in G300 Single pressure fuelling point in leading edge of starboard wing In 1999 Gulfstream considered re engining of IV SP as part of product improvement policy possibilities including Rolls Royce Deutschland BR710 and General Electric CF34 in May 2000 it placed an order for US 1 4 billion with Rolls Royce for improved Tays ACCOMMODATION Crew of two plus cabin attendant Standard seating for up to 19 passengers typically 12 to 14 in corporate configuration in pressurised and air conditioned cabin Quick Change cargo passenger version certified for up to 26 passengers announced 22 December 1993 Galley lavatory and large baggage compartment capacity 907 kg 2 000 lb at rear of cabin Integral airstair door at front of cabin on port side Baggage compartment door on port side Electrically heated wraparound windscreen Six cabin windows including two overwing emergency exits on each side SYSTEMS Cabin pressurisation system maximum differential 0 65 bar 9 45 lb sq in maintains 1 980 m 6 500 ft cabin altitude at 13 715 m 45 000 ft dual air conditioning systems Two independent hydraulic systems each 207 bar 3 000 lb sq in Maximum flow rate 83 3 litres 22 US gallons 18 3 Imp gallons min Two bootstrap type hydraulic reservoirs pressurised to 4 14 bar 60 lb sq in Honeywell GTCP36 100G APU in tail compartment flight rated to 12 500 m 41 000 ft since s n 1156 Electrical system includes two 36 kVA alternators with two solid state 30 kVA converters to provide 23 kVA 115 200 V 400 Hz AC power and 250 A of regulated 28 V DC power two 24 V 40 Ah Ni Cd storage batteries and external power socket Wing leading edges and engine inlets anti iced AVIONICS Comms Dual VHF HF transceivers transponders and cockpit audio systems cockpit voice recorder Calquest CD 400 satellite communications equipment optional Radar Digital colour weather radar Nav Dual VOR LOC GS with marker beacon receivers dual DME dual ADF

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/86-gulfstream-g300.html (2016-02-13)
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  • Gulfstream G450
    Aerial Common Sensor ACS programme with requirement for up to 38 aircraft and potential US Navy requirement for up to 20 aircraft COSTS US 33 million 2003 DESIGN FEATURES Combines wing and tail unit of G400 with a fuselage stretched by 0 30 m 1 ft 0 in cabin door repositioned G550 flight deck and nose section and Rolls Royce Tay Mk 611 8C turhofans housed in G550 type nacelles POWER PLANT Two Rolls Royce Tay Mk 611 8C turbofans each rated at 61 6 kN 13 850 lb st with FADEC Thrust reversers standard SYSTEMS Honeywell 36 150GIV APU with air start and run capability up to 11 280 m 37 000 ft Pressurisation system maintains a 1 830 m 6 000 ft cabin altitude to 12 500 m 41 000 ft AVIONICS Honeywell Primus Epic PlaneView cockpit as described for G550 with HUD and EVS standard DIMENSIONS EXTERNAL Wing span 23 72 m 77 ft 10 in Length overall 27 23 m 89 ft 4 in Height 7 67 m 25 ft 2 in DIMENSIONS INTERNAL Cabin Length 13 74 m 45 ft 1 in Max width 2 23 m 7 ft 4 in Max height 1 88 m 6 ft 2 in Volume 43 2 m 3 1 525 cu ft Baggage compartment volume 4 8 m 3 169 cu ft WEIGHTS AND LOADINGS Basic operating weight 19 504 kg 43 000 lb Payload max 2 722 kg 6 000 lb with max fuel 816 kg 1 800 lb Max fuel weight 13 381 kg 29 500 lb Max T O weight 33 520 kg 73 900 lb Max landing weight 29 937 kg 66 000 lb Max zero fuel weight 22 226 kg 49 000 lb Max wing loading 379 6 kg m 2 77 76

    Original URL path: http://www.aviamarket.org/reviews/civil-aircraft/1002-gulfstream-g450.html (2016-02-13)
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