Il-114-300

  • Performance

    General Data

    The Il-114-300 airliner is designed for local routes. It is an upgraded version of the turboprop Il-114. The aircraft will be manufactured at Russian aircraft production facilities.

    The flight crew consists of pilot-in-command and co-pilot. For successful performance of the flight crew the Il-114-300 is fitted with digital flight-navigation suite ensuring take-off and landing under weather conditions which conform to ICAO category II standard. All flight-navigation information and data on aircraft systems performance is delivered to five color LCD displays.

    Usage of the TV7-117SM engines as power plant increases the flight range with maximum passenger load up to 1900 km as compared to the Il-114.

    Modern passenger cabin ensures comfortable flight within the whole altitude range.

    The systems are configured in such a way that failure of one system does not influence the performance of others. The systems have required level of redundancy and employ well-proven materials.

    Execution of modern technological achievements in maintaining necessary aerodynamic and weight efficiency of the aircraft and power unit give the Il-114-300 high fuel efficiency.

    Aircraft landing gear allows it to land on unprepared aerodromes with concrete or dirt runways which contributes to expansion of the Il-114-300 usage in different regions.

    Besides, the aircraft is designed for independent operation at non-equipped airports. The Il-114-300 has integral passenger airstairs. Access to all structural elements and units, inspection of which is required by maintenance program, is quick and easy.

    For the Il-114-300 there was adopted a condition-based operation system without overhauls, which allows maintenance of necessary flight worthiness with minimal operational costs within design life of 30,000 flight hours or 30,000 flights and service life of 30 years.

    • Maximum shaft power (SI, Н=0), horsepower
      2х2 650
    • Maximum takeoff weight
      23,5tons
    • Flight altitude
      7 600m
    Another figure

    Estimated  technical characteristics

    Dimensional characteristics
    Length, m 26,877
    Height, m 9,324
    Wingspan, m 30
    Wing area, sq. m. 81,9
    Fuselage diameter, m 2,86
    Power plant parameters
    Number x engine type 2 x turbo-propeller engine
    Engine model TV7-117SM
    Maximum shaft power (SI, Н=0), horsepower 2 650
    Propeller diameter, m 3,6
    Compliance with ICAO standards Appendix 16, Chapter 4
    Weight parameters
    Maximum takeoff weight, tons 23,5
    Maximum payload, tons 6,5
    Fuel tank capacity, l 8 780
    Aircraft performance
    Cruising speed, km/h up to 500
    Flight altitude, m up to 7 600
    Flight range with maximum number of passengers, km 1 900
    Flight range with maximum fuel reserve (w/o payload), km 5 200
    Takeoff distance, m 1 600
    Landing distance, m 550
    Number of seats
    Crew, persons 2
    Passengers, persons 64
    Specified life
    Calendar operating life, years 30
    Number of flights 30 000
    Number of flight hours, hr. 30 000

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