The design of IL-114 aircraft represents the free lift monoplane with low located wings, usual single-fin tail unit, with the three-basic chassis with a forward rack. The composite materials are widely used in the design of the aircraft. Wing – low located, straight, large lengthening, trapezoid form, caisson type. The wing is demountable and consists of the wing center section and two console parts. The wing is equipped with the means of takeoff-landing mechanism, which consists from sliding two-slot-hole flaps with the fixed baffles (deviating by 10, 20 and 40 degrees); the aileron with trimmers and service jacks, and four section brake panels (that deviate upwards at 50 degrees when chassis wheels contact with the surface of the runway). Fuselage – hermetically sealed, round section and one-deck. Fuselage consists of forward, middle and tail parts, and also APU compartment. On the deck are placed: cabin of the crew and transport cabin that includes passenger cabin, entrance hall, luggage and cargo compartments. The cabins are equipped with the necessary household, sanitary and rescue equipments.
The emergency exits, entrance and cargo doors are located in fuselage. Tail Unit – single-fin with the fixed stabilizer on fuselage. Horizontal tail unit consists of two cantilevers with the control surface of height with trimmers on each cantilever. Vertical tail unit consists of fin, control surface with trimmer and balance tab. Landing gear – removable, three-basic circuit with a forward rack. The chassis consists of single prop forward support, two main support, the system of releasing and retracting of landing gear, the control system of turning of a forward support wheels, the system of braking of the main support wheels, the system of cooling of the wheels. A forward support is controlling. On an axis of each support two wheels are established. Wheels of the main support are braking. The shock-absorbing racks of the landing gear have the telescopic type with pneumohydraulic shock-absorption. All the landing gear supports are removed in the flight direction.
Systems Wing – low located, straight, large lengthening, trapezoid form, caisson type. The wing is demountable and consists of the wing center section and two console parts. The wing is equipped with the means of takeoff-landing mechanism, which consists from sliding two-slot-hole flaps with the fixed baffles (deviating by 10, 20 and 40 degrees); the aileron with trimmers and service jacks, and four section brake panels (that deviate upwards at 50 degrees when chassis wheels contact with the surface of the runway). Fuselage – hermetically sealed, round section and one-deck. Fuselage consists of forward, middle and tail parts, and also APU compartment. On the deck are placed: cabin of the crew and transport cabin that includes passenger cabin, entrance hall, luggage and cargo compartments. The cabins are equipped with the necessary household, sanitary and rescue equipments. The emergency exits, entrance and cargo doors are located in fuselage. Tail Unit – single-fin with the fixed stabilizer on fuselage. Horizontal tail unit consists of two cantilevers with the control surface of height with trimmers on each cantilever. Vertical tail unit consists of fin, control surface with trimmer and balance tab. Landing gear – removable, three-basic circuit with a forward rack. The chassis consists of single prop forward support, two main support, the system of releasing and retracting of landing gear, the control system of turning of a forward support wheels, the system of braking of the main support wheels, the system of cooling of the wheels. A forward support is controlling. On an axis of each support two wheels are established. Wheels of the main support are braking. The shock-absorbing racks of the landing gear have the telescopic type with pneumohydraulic shock-absorption. All the landing gear supports are removed in the flight direction.

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