Aircraft description

 The aircraft was developed in mid-sixties. It is equipped with RU-19A300 auxiliary power plant of 800 kgf-thrust mounted in the RH turboprop nacelle. This engine improves the aircraft takeoff performance. Àn-24 "Ñoke" is configured as a cantilever monoplane with high-mounted wing equipped with extended-span Fouler flaps. The double-slotted flaps are externally fitted at the engine nacelle and single-slotted flaps are installed at the root wing. The tail unit has a traditional design, in a serial aircraft it is completed with a ventral fin (from the seventies both An-24B and An-24RV are equipped with two anti-spin ventral fins); the fuselage is of a semi-monocoque type. The hydraulically-retractable three-strut landing gear has double wheels at each strut, steerable and rotatable nose wheels, providing the pressure inside tires to be adjusted on the ground. An-24B aircraft is equipped with AI-24 2nd series engines; and An-24RV aircraft is equipped with AI-24T engines with variable pitch propeller. The performed tests and aircraft operation later on revealed that it is featured with a good stability and easy controllability, capable to continue one engine inoperative takeoff. The landing gear construction and mechanical design ensures its extension by gravity or by ram air even if any system fails. The aircraft is provided with reliable wing and tail unit anti-icing systems.
An-24 aircraft is a metal-made monoplane with high-mounted wings. It is fitted with in-flight retractable three-strut landing gear with a nose wheel. The main landing gear struts are installed in the engines' nacelles and are retracted against ram air into special under-engine compartments. The nose wheel is installed at the fuselage front end and is retracted into compartment under the cockpit. The nose strut is a pedal-controlled unit that significantly improves the aircraft mobility on the ground. The landing gear wheels with low-pressure tires allow landing soaked unpaved aerodromes.
The adhesive bonded joints were for the first time applied for An-24 in the practice of world aircraft construction. More than 67% of rivet joints were replaced with adhesive-bonded joints that resulted in the increased structure fatigue, considerable labor performance saving and production cost reduction.
The aircraft wing consists of centre-section, two middle sections and two cantilever sections. The wing middle sections are fitted with double-slotted flaps, while the centre-section is fitted with single-slotted flaps. Each aileron root is fitted with a trimmer and balance tab. The centre-section chamber incorporates four soft fuel tanks; the middle section chambers are made as pressurized fuel integral tanks. The aircraft is equipped with two AI-24 jet-prop engines.
 
The aircraft is equipped with communication aids and all facilities required for day and night flights in adverse meteorological conditions any season of the year. The aircraft altitude equipment produces and maintains the pressure and air temperature to the extent required for the crew and passengers normal vital activity when flying at high altitudes. In icing conditions the wing leading edge, tail unit and engines’ air intakes cowlings are heated with hot air taken off the engine compressors. The propellers, cockpit windshields, pitots, batteries containers are provided with electrical heating. If required, An-24 can be easily converted either to a cargo-passenger or cargo version.
An-24 aircraft stands among the best world examples of aircrafts for its reliability and operating life. An-24 airframe time between overhauls is 6000 flight hours and total depreciation overhaul period makes up 30000 flight hours. The engine TBO is 3000 hours.
The aircraft is developed by Antonov ASTC [Aeronautical Scientific & Technical Complex].