Sale of Ilyushin Il-76. The Ilyushin Il-76 (NATO reporting name: Candid) is a multi-purpose four-engine turbofan strategic airlifter designed by the Ilyushin design bureau. It was first planned as a commercial freighter in 1967, as a replacement for the Antonov An-12. It was designed for delivering heavy machinery to remote, poorly served areas of the USSR. Military versions of the Il-76 have seen widespread use in Europe, Asia and Africa, including use as an airborne refueling tanker or as a command center. The Il-76 has seen extensive service as a commercial freighter for ramp-delivered cargo, especially for outsized or heavy items unable to be otherwise carried. It has also been used as emergency response transport for civilian evacuations as well as for humanitarian/disaster relief aid around the world. Because of its ability to operate from unpaved runways, it has been useful in undeveloped areas. Specialized models have also been produced for aerial fire-fighting and zero-G training.
Two aircrafts available YOM 2000/2001 AFTT 22897/21654 Cycles, Engines1 11,453/21,045, Engines2 26,182/26,586, JAR-OPS, Four Tube EFIS, Dual Collins FMS-4200’s, Dual Collins GPS-4000’s, EGPWS, TCAS II w/change7, Digital FDR, L3 CVR, CAT III-A Certified, 50 Pax Seats + 2 Flight Attendants Seats, Two Crew , Two Galleys, Fuel – 14,405 lbs, Max Cargo – 3,500 lbs, Max T/O – 51,000 lbs, Max Landing – 44,700 lbs, Basic Empty – 30,000
The Gulfstream III which built at Savannah, Georgia in the United States and what designed as to improved variant of the Grumman Gulfstream II. Design Studies were Performed by Grumman Aircraft Corporation in collaboration with Gulfstream American Corporation. Design of the Gulfstream III started with on effort to synthesize a Completely new wing Employing NASA supercritical airfoil sections and winglets. Optimization studies considering weight, drag, fuel volume, cost, and performance Indicated That a substantial portion of the new wing benefit Could be secured with modifications to the existing wing. As a result, the new wing concept which canceled and work began on design modifications That would retain the Gulfstream II wing box structure and trailing edge surfaces. The inboard wing which extended in chord and recontoured, to reduce the aircraft's high-speed drag. The wing span which Increased by six feet and five-foot winglets were added. In addition, the fuselage lengthened by at what additional two-foot section aft of the main door and the radome which extended and re-contoured. A new curved windscreen what Incorporated, changes made to the cockpit instruments were and autopilot and the maximum take-off weight Increased what. The aircraft received type approval from the American Federal Aviation Administration at September 1980th
The Mi-171 helicopter is being produced by the Ulan-Ude Aviation Plant (UUAP), part of Russian Helicopters. It is a transport variant of the Mi-171 helicopter. More than 120 helicopters have been delivered to customers in the Middle East, south-east Asia, Africa and eastern Europe. Mi-171 helicopters are designed for a wide range of tasks: carrying passengers and cargo, transportation of bulky cargo on the external load, search and rescue operations, injured evacuation. The multifunctional cargo cabin has a length of 5.34m, width of 2.34m and a height of 1.8m. It provides enough internal space to carry 4,000kg of payload. The helicopter can transport up to 4,000kg of cargo externally under sling. The main cabin features internal winch facilities, while the floor has tie-down rings for cargo transport. Either side of the fuselage is provided with a pod for an external fuel tank.The Mi-171Sh is powered by two Klimov TV3-117VM turboshaft engines mounted on top of the fuselage. Each engine is rated at 1,641kW. The helicopter can be optionally fitted with two VK-2500 turboshaft engines, each rated at 2,700hp. The Mi-171Sh can fly at a maximum altitude of 6,000m. The maximum speed of the helicopter is 250km/h. The range (without auxiliary fuel tanks) is 580km. The helicopter has a maximum take-off weight of 13,000kg.
The benchmark A320 Family’s largest member – the A321 – offers airline customers the best seat-mile costs of any single-aisle aircraft and seating capacities comparable to that of a widebody jetliner. This aircraft has a stretched fuselage with an overall length of 44.51 metres, along with an extended operating range of up to 3,000 nautical miles while carrying a maximum passenger payload. Like each member in Airbus’ A320 Family of jetliners, the A321 offers the lowest fuel burn, emissions and noise footprint in its class. The twin-engine A321 can be powered by either of two engine options: the CFM International CFM56 or International Aero Engines’ V2500. With a range of up to 4,000nm /7,400km., the A321 is capable of flying longer routes, for example transatlantic flights from Europe to U.S east coast. The A321 typically accommodates 185 passengers in a two-class configuration (16 in business class and 169 in economy) – while offering unbeatable economics in high-density seating (with up to 220 passengers) for charter and low-cost operators.
YAK-42D is one of the most reliable aircrafts made in CIS and is equipped with navigation systems of the new generation. You will find a world of comfort and coziness on board YAK-42 D VIP. The aircraft has a large comfortable passenger cabin that is much wider than cabins of many foreign aircrafts.YAK-42 D VIP is a functional, comfortable and nice passenger liner, working in which is as efficient as working in your own office, and rest is homy. The aircraft design meets the latest requirements to the corporate aircraft design. The comfortable interior of YAK-42 D VIP provides all conditions for passengers to use the flight time as efficient as possible. The aircraft is certified for international flights. The noise level complies with ICAO standards. The aircraft has flight and navigation, instrumental, radio, passenger and other equipment according to the Standard Specification. Complex off-site maintenance of the aircraft will subsequently allow to carry out all aircraft airworthiness procedures on-site. This Aircraft is available for sale. Price - $ 10,7 M
Multi-purpose Mil-8AMT russian helicopter, the upgraded modification of Mil-8 helicopter, is intended for the solving of a wide range of missions, i.e. transportations of passengers and freights, transportations of bulky freights on the external sling, carrying out of search and rescue operations, evacuations of injured. The helicopter can be equipped with additional fuel tanks to extend flight range. In passenger version the helicopter can be equipped with cushioned seats for transportation of 22 passengers in comfortable conditions.
The 737-300 is the first of the three member second generation CFM56 powered 737 family, which also comprises the stretched 737-400 and shortened 737-500. The success of the second generation Boeing 737 family pushed sales of the mark to over 3000, a record for a commercial jetliner. Boeing announced it was developing the 737-300 in March 1981. This new variant started off as a simple stretch over the 737-200 but Boeing decided to adopt the CFM International CFM56 high bypass turbofan (jointly developed by General Electric and SNECMA) to reduce fuel consumption and comply with the then proposed International Civil Aviation Organisation Stage 3 noise limits. Despite the all new engines and the 2.64m (104in) fuselage stretch, the 737-300 retains 80% airframe spares commonality and shares the same ground handling equipment with the 737-200. A number of aerodynamic improvements were incorporated to further improve efficiency including modified leading edge slats and a new dorsal fin extending from the tail. Another feature was the flattened, oval shaped engine nacelles, while the nosewheel leg was extended to increase ground clearance for the new engines. Other internal changes include materials and systems improvements first developed for the 757 and 767 programs, including an early generation EFIS flightdeck (with four colour CRT screens). The 737-300 flew for the first time on February 24 1984, while first deliveries were from November 1984. Since that time well over 1000 737-300s have been sold and it forms the backbone of many airlines' short haul fleets.
The Airbus A320 family consists of short- to medium-range, narrow-body, commercial passenger jet airliners manufactured by Airbus. The family includes the A318, A319, A320, and the ACJ business jet. After the introduction of the A320neo, it is also named A320ceo (current engine option). Final assembly of the family in Europe takes place in Toulouse, France, and Hamburg, Germany. Since 2009, a plant in Tianjin in the People's Republic of China has also started producing aircraft for Chinese airlines. In April 2013, Airbus has started construction work on a new production facility for the 319, 320, variants in Mobile, Alabama. The aircraft family can accommodate up to 220 passengers and has a range of 3,100 to 12,000 km (1,700 to 6,500 nmi), depending on model.
The Yak-42 is a low-winged monoplane of all metal construction, with a design lifespan of 30,000 one-hour flights. It has a pressurised fuselage of circular section, with the cabin designed to carry 120 passengers in six abreast layout (or 100 passengers for local services with greater space allocated to carry-on luggage and coat stowage). The aircraft is flown by a flight crew of two pilots sitting side-by-side in a flight deck forward of the cabin. Access is via two airstairs, one in the underside of the rear fuselage, like that of the Yak-40, and one forward of the cabin on the port side. Two holds are located under the cabin, carrying baggage, cargo and mail. The wing layout underwent considerable revision during the design process, with the first prototype being built with a wing sweep of 11 degrees and the second prototype with a sweep of 23 degrees. After evaluation, the greater sweep of the second prototype was chosen for production. Early aircraft had a clean wing leading edge with no control surfaces, and plain trailing edge flaps. This changed in later aircraft, which were fitted with leading edge slats, with the trailing edge slats slotted. Two engines were mounted in pods on either side of the rear fuselage, with the third embedded inside the rear fuselage, fed with air via an "S-duct" air inlet. An auxiliary power unit (APU) is also fitted in the rear fuselage. No thrust reversers are fitted. The aircraft has a T-tail, with both the vertical fin and the horizontal surfaces swept.