• Performance

    General Data

    Il-96-300 is a wide-bodiedlong-haul passenger aircraft. Its aerodynamic configuration, design and systems use the newest solutions, ensuring high safety and economic efficiency in operations.The Il-96-300 complies with all international ecologicalrequirements and thus can be operated in all regions of the world. The aircraft is admitted for operation from high-altitude aerodromes and can land at airfields of ICAO categories IIIA and IIIB.

    The Il-96-300 can admit up to 300 passengers onboard. The airliner crew consists of just 3 people.This is possible due to the use of modern systems and a glass cockpit. In terms of reliability, safety and cost effectiveness, the Il-96-300 is equal to its foreign counterparts.

    The aircraft is equipped with PS-90A engines complying with ICAO requirements, as regards noise and emissions.

    The aircraft with its PS-90A engines and their sound-absorbing structures of the 2nd generation (ZPK-2) complies with ICAO requirements of Appendix 16, Chapter 4, as regards noise emissions.

    Modern materials used in its design allow for reducing the plane’s weight while ensuring required rigidness and durability. A large-diameter fuselage gives passengers a new level of comfort during long flights. The new wing ensures reliable and safe flight within the entire operational range of speeds.

    Aircraft operation “on condition”helps reducing time spent on maintenance, which is of utmost importance for modern traffic-intensive airlines.

    First flight took place on September 28, 1988. Test pilot was S.G. Blizniuk.

    Type Certificate No. 22-96-300 AR by IAC was granted in December 1992.

    Passenger transportation commenced in July 1993.

    • Top thrust (SI system, H=0)
    • Maximum takeoff weight
    • Maximum flight altitude
      13 100m
    Another figure

    Main technical characteristics

    Dimensional characteristics
    Length, m 55,345
    Height, m 17,55
    Wingspan, m 60,105
    Wing area, sq. m. 350
    Fuselage midsection, m 6,08
    Power plant parameters
    Number x engine type 4 x turbojet engine
    Top thrust (SI system, H=0), kgf 16 000
    Compliance with ICAO standards Appendix 16, Chapter 4
    Weight parameters
    Maximum takeoff weight, tons 250
    Maximum payload, tons 40
    Fuel tank capacity, l 150 000
    Aircraft performance
    Cruising speed, km/h 850–870
    Flight altitude, m 9 100–13 100
    Flying range with maximum load, km 9 800
    Flying range maximum , km 14 000
    Takeoff distance, m 2 380
    Landing distance, m 860
    Number of seats
    Crew, persons 3
    Passengers, persons One-class design - 300
    Two-class design - 263
    Three-class design - 237
    Specified life
    Calendar operating life, years 25
    Number of flights 10 000
    Number of flight hours, hr. 70 000
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