The AN-74 airplane is designed on the basis of the AN-72 “transport worker” for transportation in the Arctic. The aircraft developer is Kiev ASTC. Antonov. The model was commissioned on July 3, 1991; since then, it has been used by airlines in more than twenty countries of the world. There are civilian and military modifications, which, in turn, are divided into cargo, cargo-passenger, passenger, special, military transport and patrol.
Brief description and purpose of the aircraft
The AN-74 is a cantilever all-metal monoplane with a high-winged low sweep and a T-shaped single-fin plumage. The power plant of the aircraft includes two turbofan-ventilated bypass engines D-36 series 1-A, which are cantilever-mounted on the center section in such a way that their jet streams blow the upper surface of the wing, creating additional lift.
The aircraft is designed for use in the most extreme climatic conditions in the operating temperature range from -60 to +45 degrees Celsius, at high mountains, but its main purpose is to carry out activities in the Arctic, Antarctic and adjacent regions.
An-74 is intended for conducting visual ice reconnaissance, escorting ships, transporting goods and passengers, searching for schools of fish, performing special work in organizing drifting research stations and providing research projects in the central Arctic basin.
The aircraft meets the requirements of the airworthiness standards of the aircraft and the additional airworthiness requirements of the AN-74 aircraft, which take into account its design and operational features, which together with the above standards form the “Certification Airworthiness Basis”. Approved by the Executive Committee of the USSR SNLG on 05/17/1991 and introduced by the Presidium of the Council of the USSR NLG on July 3, 1991.
Minimum crew - 5 people:
Allowed flights without airborne radar along the routes of MGA, where communication is provided in the MF-range. The maximum number of passengers is 10 people (in the cargo and passenger version).
An-74: engine performance
Mounted engine D-36 series 1A. Turbojet unit D-36 ser. 1A is made with an axial compressor according to the three-shaft design, an annular combustion chamber, an intermediate casing, a five-stage turbine and separate unregulated output nozzles of the inner and outer contours. Installation weight (dry) - 1.1 tons.
Motor data by mode:
The time of continuous operation of the D-36 on take-off mode is no more than 5 minutes. on the mode of terrestrial gas - no more than 30 minutes. on the nominal and cruising modes - without limitation within the resource of a particular aircraft.
Auxiliary gas turbine engine
The TA-12 engine of the auxiliary power unit (APU) is a single-shaft gas turbine with the extraction of compressed air and electrical energy of alternating current with an available power of 40 kVA. The unit is installed in the unpressurized compartment of the right fairing of the landing gear of the aircraft and is intended for:
- air launch of D-36 sustainer engines on the ground at altitudes up to 3,600 m and in flight at altitudes up to 6,000 m;
- compressed air feeding the air conditioning system of the aircraft on the ground at altitudes up to 3600 m
- supply of the aircraft network with AC power on the ground at altitudes up to 3,600 m and in flight in case of failure of the main power sources up to 9000 m.
The TA-12 engine consists of a reducer, a four-stage axial compressor, a counter-current annular combustion chamber, a three-stage axial turbine.
The following fuels are used for refueling AN-74: PT, TC-1 and T-1 without anti-crystallization liquids. It is allowed to mix the specified brands of fuel in any proportions and apply them with Sigbol additives, I, I-M, TGF, TGF-M fluids and their analogues. It is allowed to use fuel of foreign brands and with additives that meet accepted standards.
Takeoff and landing performance
The list shows the main parameters of the AN-74, technical characteristics by weight and flight speed:
- Maximum take-off weight - 34,800 kg.
- Maximum landing weight when landing on snowy and unpaved runways – 30 000 kg on the ice of the runway – 33 000 kg.
- Maximum commercial load – 7 500 kg.
- The maximum mass of fuel refueled is 13 210-13 700 kg.
- Flight speed: D36-1A – 500 km/h, D36-2A – 700 km/h.
The chassis of the aircraft is executed according to the three-support scheme, consists of the front and two main supports. The main support consists of two racks, each of which is equipped with a KT192A brake wheel, with 1050 × 390 tires. Non-brake wheels K327 with tires 720 × 310 are installed on the front landing gear of the aircraft.
The hydraulic system consists of two main systems: left and right (plus one backup). The main source of pressure in each hydraulic system is the hydraulic pump NP72MV variable flow with a drive from the corresponding engine. The supply of one pump with a discharge pressure of up to 145 Kg / cm 2 (14.5 MPa) is at least 27 l / min. Working fluid - AMG-10. As a backup power source serves electrically driven pump station NS-14, connected to the left hydraulic system.
- A complete resource of the aircraft (to the cancellation) is 40 000 flight hours or 20 000 landings, or 20 years of operation.
- The initial assigned resource of the airframe, chassis and mechanical elements of the control system and configuration changes is 10,000 flight hours, 5,000 flights.
- The initial assigned resource of the D-36 Series 1A engine is 1000 flight hours.
- The initial assigned resource vgtd TA-12 is 1,000 flight hours or 2,500 starts.
To ensure emergency escape of the crew and passengers in the event of an emergency landing of the aircraft on land or water, the aircraft is equipped with emergency exits, as well as outside the fuselage, additional exit points are provided.
The aircraft has the following rescue equipment (ASO): ropes, ax, first-aid kits, light signs with the words “Exit”, emergency lighting system, signaling and communication means, radio stations - one P-861 and two P-855UM.
For flights over deserts, arctic or tropical areas there are places for equipment with livelihoods that meet the conditions of the area. When forced to land on the water, the AN-74 will retain a floating and stable position for the time required for emergency evacuation of passengers and crew members.
When flying over bodies of water, the following ASO is additionally established:
a) when the flight duration is less than 30 minutes from the coast - life jackets by the number of transported passengers and crew members and one demonstration vest;
b) when the flight duration is over 30 minutes from the coast - inflatable life rafts.
Family AN-74 TK-300
Models of this family are distinguished by the location of power units under the wings (and not above, as in the basic version), high efficiency and recycled cabin in the passenger version. Initially, it was conceived as a modernization of the 1991 model, but the number of innovations was so significant that the TK-300 can be considered an independent aircraft of the Antonov family. The first model was produced in 2001, and to date, several units are in operation.
Antonov Corporation sells various modifications of the AN-74. The price of the aircraft starts from 15 million dollars. For example, the internal troops of Kazakhstan in 2013 purchased the An-74TK-200 for $ 28 million. The transporter is specially designed for humanitarian and tactical peacekeeping missions, the aircraft is capable of landing on short takeoff and landing bands.