• Performance

    General Data

    The Il-114 turboprop airliner is designed for local routes.

    The flight crew consists of pilot-in-command and co-pilot. For successful performance of the flight crew all flight data display devices and warning systems of the Il-114, as well as aircraft system controls, are combined in the single information and control system with delivery of data to digital displays, situated on pilots’ instrument panel.

    Flight-navigation suite of the aircraft allows operation of the Il-114 during day and night, in visual and instrument weather conditions, in storm, and ensures take-off and landing in ICAO standard II weather conditions.

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

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

    The Il-114 made its maiden flight from the aerodrome of Gromov Flight Research Institute on 29 March 1990. The aircraft was flown by crew under the command of test-pilot V. Belousov.
    • Maximum shaft power (МСА, H=0)
    • Maximum takeoff weight
    • Maximum flight altitude
      7 600m
    Another figure

    Main technical characteristics

    Dimensional characteristics
    Length, m 26,877
    Height, m 9,324
    Wingspan, m 30
    Wing area, sq. m. 81,9
    Fuselage midsection, m 2,86
    Power plant parameters
    Number x engine type 2 x turbo-propeller engine
    Maximum shaft power (МСА, H=0), kgf. 2 500
    Propeller diameter, m 3,6
    Compliance with ICAO standards Appendix 16, Chapter 3
    Weight parameters
    Maximum takeoff weight, tons 23,5
    Maximum payload, tons 6,5
    Fuel tank capacity, l 8 360
    Aircraft performance
    Cruising speed, km/h up to 500
    Flight altitude, m up to 7 600
    Flying range with maximum number of passengers, km 1 000
    Flying range with maximum fuel reserve, km 4 800
    Takeoff distance, m 1380
    Landing distance, m 550
    Number of seats
    Crew, persons 2
    Passengers, persons 64
    Specified life
    Calendar operating life, years 30
    Number of flights 12 000
    Number of flight hours, hr. 18 000
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