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M-101T Gzhel |
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M-101T Gzhel aircraft is designed by Myasishchev Design Bureau and is being series produced at Aircraft Building Plant Sokol in Nizhni Novgorod.
By now 5 prototypes and 5 preproduction prototypes are manufactured, the preparation for series production of 50 aircraft is completed, 9 series aircraft are being assembled.
When developing the aircraft extended investigations of aerodynamic models and bench tests of the aircraft systems and accessories were carried out, at present static strength tests of the airframe are being completed. Flight certification tests are in full swing. Within operational testing of 5 aircraft of a preproduction batch with commercial transportation of cargoes to different airports of Russia including the regions of permanent frost, more than 500 flights were carried out. Over the period since November, 1999 till March, 2000 one of Gzhel aircraft carried out the demonstration flight from Nizhni Novgorod to Arabia than to Africa and returned back having flown 26300 km. It landed at 26 aerodromes in 18 countries, crossed the equator, got to Zaire and Burundi. Within this demonstration flight all aircraft systems were operating normally both in flat and mountain (up to 2400 m) regions. Direct operating costs for 1 flight hour (all expenses excluding overhead charges, profit and taxes) amount 200 dollars per hour. MDB and Aircraft Building Plant "Sokol" (Nizhni Novgorod) are implementing the certification procedure and marketing of the aircraft, and they are ready to enter into negotiations with customers on sale terms with the delivery of series aircraft in early 2000 on getting AP-23 type certificate.
Speed and range performance will be improved at the developed modifications of the aircraft. The concept of Gzhel aircraft design provides for its operation as:
Specified life of the aircraft: 15 years (20000 flight hours) with execution of check and recovery works in 6000 flight hours that will provide the aircraft stable operation within its service life up to the retirement. Calendar life of the engine: 20 years with the overhaul life 3000 hours. The number of repairs is unlimited. The aircraft is designed for conditions of autonomous operation, its structure and accessories provide its operation within 50 flight hours outside the base aerodrome. The aircraft outstanding features include the presence of the presurized cabin ensuring comfortable flight conditions at altitudes up to 7600 m and the aircraft capability to take off and land at unpaved aerodromes having limited dimensions. The structure of the pressurized cabin and the large entrance door ensure the rapid conversion of the aircraft into different versions. Performance and service characteristics of the aircraft comply with AP-23 airworthiness requirements for light civil aircraft. The aircraft is designed according to the standard aerodynamic configuration, and is a single engine , all metal , long-wing monoplane with a cantilever tapered wing. The aircraft is equipped with the two-shaft turboprop engine M-601F Walter, being a modification of L410 aircraft engine that has been operated in Russia for years, having low noise, five-blade feathering , reversible propeller V510 of Avia -Hamilton Standard company. The engine and the propeller are certified in Czech, USA and Russia. The engine starting is carried out from an airborne battery (or a ground power supply) using the starter-generator. At temperature below -20° C the engine starting is performed with heating from a ground supply. The range of operating temperatures is from -50° C up to +50° C. The in-flight start is provided due to the engine windmilling. Low level of community noise produced by the propeller and the engine enables the aircraft operation in the day and night time from aerodromes located in the vicinity of populated areas. The aircraft fuselage is an all metal semi-monocoque with the pressurized cabin which volume is 7,53 m3 . On the portside there is a crew door and a cargo/passenger door (1,15 x1,23 m). There is a cargo bay with a cargo safety net. In the cabin floor there are rails that enable to locate seats or tie-down fittings in any place in the cabin. At customers option the cabin may be equipped with a toilet and other household appliances. The aircraft wing is of torsion-box type with ailerons and double slotted rotational flaps with deflectors. The aircraft tailplane has one-piece structure with the elevator where a trimmer -reverse balancing tab is located. On the vertical stabilizer there is a rudder with a trimmer. The aircraft fuel system consists of two wing tanks of torsion-box type and two feed semi-tanks with electrical pumps. Fuel specification: T-1, TS-1, RT according to GOST 10227-86. The aircraft landing gear , is retractable in flight, tricycle, with the forward castoring strut, with the shimmy damper. The aircraft turn on the ground is carried by using the separate braking of the main struts. The landing gear provides the aircraft operation from unpaved airfields with the ground strength not less 0,6 MPa (6 kgf/cm2) covered with the grass 70 mm high or with fresh snow up to 80 mm high. The aircraft control system is mechanic, tubular-cable operated. The aircraft is controlled by a control wheel pedal system. Deflection of all trim tabs is performed by electric mechanisms. The flaps are controlled by a rod and bell crank system with a hydraulic drive. The aircraft is equipped with the dual control system with two work stations for pilots. At customers option an automatic control system is completed on the base of Bendix-King equipment may be installed. The aircraft hydraulic system actuates the landing gear and flaps, and consists of the primary and reserve systems. The air conditioning system maintains the barometric altitude in the cabin, that is not above 2400 m, air temperature 17-25° C, performs air ventilation with air flow not less 24 kg/h for one person. The aircraft anti-icing system protects the leading edges of the wing, tailplane, vertical stabilizer (pneumatic system), intake lips and the propeller leading edges, pitot static tubes and the windscreen "vision area" (electric heating systems). Flight control and navigation equipment may be completed in three versions: to carry out flights according to instrument flight rules (IFR) with two pilots; to carry out flights according to IFR with one pilot and to carry out flights according to visual flights rules with one pilot. Satellite navigation system KLN-89B, stormscope WX-900, navigation-communication system KX-165 and other equipment of Bendix King are installed on the aircraft and enable air navigation in the day and night time in VFR and IFR conditions. The autopilot is optional. Radio-communication equipment provides the crew radio-telephone communication with ground control services and other aircraft, and consists of two VHF radio stations. The emergency escape VHF radio stations may be included in complete set of the equipment. The oxygen system - is separate, for the crew and passengers. Fire-extinguishing system includes the warning equipment with sensors and fireproof bulkheads. Power generating system consists of:
Training of pilots and ground crews is carried out by MDB, the aircraft operation support within the whole service life will be carried out in maintenance centres in CIS territory involving the existing aircraft enterprises. |
| CONTACT: |
Russia, 140180, Moscow region, Zhukovsky-2, P.B. 270 Phone: (095) 556-77-76 Fax: (095) 728-41-30 E-mail: mdb@mail.sitek.ru |
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