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)2х2500kgf
Maximum takeoff weight23,5tons
Maximum flight altitude7 600m
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 Engine
TV7-117S 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