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)4х16000kgf
Maximum takeoff weight250tons
Maximum flight altitude13 100m
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 Engine model PS-90A 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 with maximum fuel reserve, km 13 500 Takeoff distance, m 2 340 Landing distance, m 860 Number of seats
Crew, persons 3 Passengers, persons One-class design - 300
Two-class design - 263
Three-class design - 237
Calendar operating life, years 25 Number of flights 10 000 Number of flight hours, hr. 70 000