With the NATO reporting name Cash, the An-28 Was designed for STOL performance with up to 19 passengers. A development of the piston-engined An-14, the first prototype flew in September 1969 and had a retractable landing gear and Isotov TVD-850 engines. Production An-28 have a non-retractable tricycle type landing gear and two 723kW Glushenkov TVD-10B turboprops. Operational in 1969, the An-28 went into production in Poland (still in production in 1999) by WSK “PZL-Mielec” as the M-28 Bryza / Skytruck.
An-28RM
Engine: 2 x turbo prop TVD-10B, 705kW Wingspan: 22.1 m / 72 ft 6 in Length: 13.0 m / 42 ft 8 in Height: 4.5 m / 14 ft 9 in Take-off weight: 5100 kg / 11244 lb Empty weight: 3000 kg / 6614 lb Max. speed: 350 km/h / 217 mph Cruise speed: 300 km/h / 186 mph Ceiling: 6000 m / 19700 ft Range w/max.fuel: 1300 km / 808 miles Range w/max.payload: 1000 km / 621 miles Crew: 1-2 Passengers: 15-26
NATO code name ‘Curl’, the Antonov An-26 is a twin-engine transport aircraft first flown in May 1969 and exhibited at the 1969 Paris Air Show. A militarised development of the An-24 airliner, the pressurised An-26 flew first in 1968 and differs from the An-24 in featuring a rear loading ramp, more powerful lvchenko turbine-engines and an auxiliary turbojet in the right engine nacelle. An improved An-26B version was announced in 1981 with an improved freight handling system.
An-26B
Approximately 1,410 An-26s and An-26Bs were built by GAZ 473 at Kiev, 1968-85, before being superseded in production by An-32. Production of the An-26 Curl twin-turboprop transport and its hot-and-high derivative, the An-32 Cline, continued in 1987. They were widely exported, serving in more than 20 countries. It was developed into the An-26 (freighter), the An-30 (survey/photo) and the An-32 (hot and high version). A derivative Y7H-500 was built by Xian Aircraft Company, in China.
The Antonov An-26 arrived in Cuba in late 1978 and early 1979. The fleet consisted of two squadrons numbered from FAR 12-20 to FAR 12-39. In the first half of the 80s, more aircraft of this type were incorporated, reaching more than 30, of which 4 became Aerocaribbean.
The remaining AN-26s begin to change their military paint scheme, known as “chipojos” to the Cubana de Aviación paint scheme but without belonging to the airline. In 1994 with the emergence of Aerogaviota, most of these aircraft were painted with the new scheme. At present (2014) only around 5 Antonov An-26 aircraft remain active.
Variants: An-26: standard version of tactical transport. An-26B: Equipped with two Ivchenko Al-24VT turboprops, of greater power. An-26BRL: Research version for frozen areas. An-26L: Track calibration version. An-26M: Air ambulance. An-26P: Fire control plane. An-26RTR: Electronic warfare and signals intelligence version. An-26ST: Special missions version manufactured for the Air Force of the German Democratic Republic. An-26Z-1: Signal intelligence aircraft (SIGINT). Y-7H: Chinese version of military transport (No license). Y-7-500: Chinese civil cargo version (Unlicensed).
Engine: 2 x turbo prop AI-24T, 2075kW and 1 x turbo-jet RU-19-300, 8.8kW Wingspan: 29.2 m / 95 ft 10 in Length: 23.8 m / 78 ft 1 in Height: 8.6 m / 28 ft 3 in Wing area: 75.0 sq.m / 807.29 sq ft Take-off weight: 24000 kg / 52911 lb Max payload: 5.500kg / 40 passengers. Max. speed: 540 km/h / 336 mph Cruise speed: 430 km/h / 267 mph Ceiling: 7500 m / 24600 ft Range w/max.fuel: 2550 km / 1585 miles Range w/max.payload: 980 km / 609 miles Crew: 5 Passengers: 38-40 Hold cap: 1765 cu.ft.
Engines: 2 × Progress AI-24VT turboprop, 2,103 kW / 2,820 hp Wingspan: 29.20 m Wing area: 74.98 m² Length: 23.80 m Height: 8.58 m Empty weight: 15,020 kg Maximum takeoff weight: 24,000 kg Load: 5,500 kg Cruise speed: 440 km / h (237 knots, 273 mph) Range: 2,550 km; 1,100 km at full load Service ceiling: 7,500 m (24,600 ft) Rate of climb: 8 m / s (1,575 ft / min) Crew: 5 (2 pilots, 1 radio operator, 1 flight engineer, 1 navigator) Capacity: 40 passengers
Development of this twin-turboprop transport was started in 1957, to replace piston-engined Li-2 and Il-14’s types on Aeroflot’s internal feederline routes. The An-24 was intended originally to carry 32 to 40 passengers, but when the first of two prototypes flew on 20 October 1959, it had been developed into a 44-seater. It was followed by a second prototype and five preproduction An-24. On the prototype, the engine nacelles extended only a little past the wing trailing-edges: production An-24 have lengthened nacelles with conical rear fairings. A ventral tail fin was also added on production models of the passenger-carrying version, which are supplemented by the An-24T and An-26 specialised freight-carrying versions of the same basic design. Flight testing was completed in September 1962 and the An-24 entered service on Aeroflot’s routes from Moscow to Voronezh and Saratov in September 1963.
Normal accommodation is for two pilots, a navigator, a steward and up to 44 passengers in four-abreast seats, mounted in pairs. The front cabin is movable to make possible alternative mixed passenger-freight payloads, all passenger seats can be removed. The cabin is 48 ft 1.5 in long, 9 ft 5 in wide and 6 ft 5 in high, with a volume of 2750 cu.ft and floor area of 439 sq.ft. In the standard version, there is a luggage compartment forward of the passenger cabin on the port side, with a freight hold on the starboard side. Entry to the cabin is via a door at the rear, on the port side, with built-in airstairs.
The An-24 is designed to operate from airfields of limited size, with paved or natural runways and can be fitted with rocket-assisted take-off units to permit operation with a full load of cargo at ambient temperatures above 30°C. Two were taken to the Antarctic in late 1969, to replace piston-engined Il-14 used previously for flights between Antarctic stations.
Deliveries of the An-24V started in 1962. The An-24RV features a small turbojet in the right engine nacelle to boost takeoff performance and up to 5 crew and 50 passengers.
Production ended in 1979 with over 1460 An-24 variants were built in Kiev, Irkutsk and Ulan Ude in the former USSR/Ukraine. An An-24 variant entered production in China as the Xian Y-7.
It was widely exported, serving in more than 20 countries. It was developed into the An-26 (freighter), the An-30 (survey/photo) and the An-32 (hot and high version).
The An-24RT variant became the basis for a developmentally improved design in the An-26 “Curl”.
An-24T Length: 77.20ft (23.53m) Wingspan: 95.80ft (29.20m) Height: 27.30ft (8.32m) Maximum Speed: 280mph (450kmh; 243kts) Maximum Range: 398miles (640km) Service Ceiling: 27,559ft (8,400m) Accommodation: 2 + 44 Engines: 2 x ZMBD Progress (Ivchenko) AI-24A turboprop engines generating 2,250eshp each.
Engine: 2 x turbo prop AI-24, 1875 kW Wingspan: 29.2 m / 95 ft 10 in Length: 23.5 m / 77 ft 1 in Height: 8.3 m / 27 ft 3 in Wing area: 72.5 sq.m / 780.38 sq ft Take-off weight: 21000 kg / 46297 lb Empty weight: 14248 kg / 31412 lb Cruise speed: 500 km/h / 311 mph Ceiling: 8400 m / 27550 ft Range w/max.fuel: 2280 km / 1417 miles Range w/max.payload: 750 km / 466 miles Crew: 2 Passengers: 44-50
Carrying the NATO reporting name Cock, the An-22 is a very large, long-range heavy transport. The An-22 was the world’s largest aircraft when first flown on 27 February 1965, powered by four Kuznetsov turboprop engines, each driving two contrarotating coaxial propellers.
A very heavy freighter for the Soviet Air Force and Aeroflot, it was given a rear loading ramp to provide access to the 26.4m cargo hold, and can carry a payload of up to 176,350 lb (80 000 kg), including Ganef and Scud-A missiles on their tracked launchers.
Entering Soviet service in 1967 all 65 production aircraft were built at the Chakalov factory in Tashkent for the VTA/Soviet Air Force Transport Service, but were available to Aeroflot for charter and so all were painted in Aeroflot colours.
In October 1967 an An-22 established 14 payload-to-height records. With a payload of 100,000kg of metal blocks it reached a height of 7,848m, thereby qualifying also for the intermediate records from 35,000kg. Max payload lifted to a height of 2,000m was 104,444.6 kg. A take-off run of just over one kilometre was reported; the flight duration was 78 minutes.
In 1972 a further series of ten records for speed with payload were set up by Marina Popovich, wife of the Soviet cosmonaut Pavel Popovich. The aircraft averaged a speed of 593.318km/h around a 2,000km closed circuit with a 50,000kg payload, qualifying also for the intermediate records from 30,000kg. In addition the aircraft averaged a speed of 608.449km/h in a flight two days later around a 1,000km circuit with the same payload. The An-22 also holds three further records for speed with payload over a 5,000km circuit, established in 1974 and 1975.
Deliveries to both the Soviet Air Force and Aeroflot were completed during 1974.
Antonov An 22 A Antei Engines: 4 x Samara / Kusnetsov NK-12MA, 14602 shp Prop diameter: 6.2 m Length: 188.025 ft / 57.31 m Height: 41.142 ft / 12.54 m Wingspan: 211.286 ft / 64.4 m Aspect ratio: 12.02 Wing area: 3713.58 sqft / 345.0 sqm Max take off weight : 496125.0 lb / 225000.0 kg Weight empty : 261793.0 lb / 118727.0 kg Max. payload weight : 132300.0 lb / 60000.0 kg Max. speed : 324 kts / 600 km/h Landing speed : 130 kts / 240 km/h Cruising speed : 313 kts / 580 km/h Take off distance : 4790 ft / 1460 m Landing distance : 3412 ft / 1040 m Wing load : 133.66 lb/sq.ft / 652.00 kg/sq.m Maximum range : 5940 nm / 11000 km Range (max. weight) : 2700 nm / 5000 km Crew : 5 Payload : Cabin for 29 Pax, freight hold volume 640cu.m
Antonov An-22M Antei (Cock) Engines: 4 x KKBM Kuznetsov NK-12MA turboprop, 14602 shp Prop diameter: 6.2 m Length: 190.03ft (57.92m) Wingspan: 211.29ft (64.40m) Aspect ratio : 12.02 Wing area : 3713.58 sqft / 345.0 sqm Height: 41.11ft (12.53m) Maximum Speed: 460mph (740kmh; 400kts) Landing speed : 130 kts / 240 km/h Cruising speed : 313 kts / 580 km/h Maximum range : 5940 nm / 11000 km Range (max. weight) : 2700 nm / 5000 km Service Ceiling: 24,606ft (7,500m) Crew : 5 Weight empty : 261793.0 lb / 118727.0 kg Maximum Take-Off Weight: 551,156lbs (250,000kg) Max. payload weight : 132300.0 lb / 60000.0 kg Payload : Cabin for 29 Pax, freight hold volume 640cu.m Take off distance : 4790 ft / 1460 m Landing distance : 3412 ft / 1040 m
The Antonov designed An 14A Ptchelka (Bee), first flown on March 15, 1958, entered service with Aeroflot as a successor to the An 2 biplane, after five and a half years of flight testing and modification. Production began both for Aeroflot and the Soviet armed forces at the Progress Plant at Arsenyev in 1965 and by the mid-1970s well over 300 aircraft had been delivered. The military version, first seen at the Domodedovo air display in 1967, appeared not to differ from the civilian passenger version externally.
The An-14A featured an increase in wing span and the introduction of 300 hp AI 14RF engines.
The An-14 was a light transport used for agricultural and air ambulance duties which eventually evolved into the 19-seat An-28, and was produced by PZL Mielec in Poland until at least 1991. It entered service with only one division of Aeroflot, in Khazakistan.
Carrying the NATO reporting name Clod, An-14 were also in service with the air forces of Bulgaria, the German Democratic Republic and Guinea.
An-14A Engine: 2 x AI-14RF, 220 kW Wingspan: 21.4 m / 70 ft 3 in Length: 11.0 m / 36 ft 1 in Height: 4.2 m / 13 ft 9 in Wing area: 43.5 sq.m / 468.23 sq ft Take-off weight: 4410 kg / 9722 lb Empty weight: 2310 kg / 5093 lb Payload: 1,323 lb (600 kg) Max. speed: 350 km/h / 217 mph Cruise speed: 106 112 mph (170.5 180 km/h) Ceiling: 5000 m / 16400 ft Range: 1550 km / 963 miles Range w/max.fuel: 780 km / 485 miles Range 1,235 lb (560 kg) payload, 1 hr res: 453 mls (730 km). Range w/max.payload: 300 km / 186 miles ROC: 1,020 fpm (5.18 m/sec) SE ROC: 300 ft/min (1.5 m/sec) Take off distance: 295 ft (90 m) fully loaded Landing distance: 361 ft (110 m). Crew: 1 Passengers: 7-9
The An-12 (NATO reporting name ‘Cub’) is a military development of the An-10 airliner. The An-12 prototype (7900101) built at Irkutsk, flew first on 16 December 1957 powered by four Kuznetsov NK-4 turboprops of 4,000 horsepower and differs from the An-10 in featuring a more upswept rear fuselage and rear loading ramp, entering service in 1959.
Fully pressurised, the An-12 has high performance yet can operate from unpaved surfaces. At least one was fitted with large skis with shallow V planing surfaces equipped with heating (to prevent sticking to ice or snow) and brakes. Nearly all have the tail turret, and under the transparent nose is a weather and mapping radar. The rear ramp door is made in left and right halves which can be folded upwards inside the fuselage, either for loading heavy freight with the aid of a built-in gantry or for the dispatch of 100 paratroops in less than one minute. The An 12 BP became the standard Soviet Air Force cargo and paratroop transport since 1960, also being exported for both military and commercial use to the air forces of India, Egypt, Indonesia, Poland, Iraq, Algeria and Bangladesh and to 70 other freight operators. Powered by four 4,000 ehp (2 985 kW) Al-20K turboprops, standard transport variants of the An-12 have been adapted for EW and ELINT duty with SovAir and SovNavAir. Variants include Cub-A and Cub-B for ELINT role and Cub-C and Cub-P with varying antenna and radomes, to perform passive and active ECM duty. With a max payload of 20,500 kg or up to 4 crew and 90 troops, series production of the An-12 in a number of variants continued until 1973. Around 1,400 were built with AI-20K engines and the type was also produced by Shaanxi Aircraft Company (or Harbin), China as the Yunshuji-8 (Y-8) redesigned transport version and derivatives.
Harbin Y-8
The first Shaanxi Y8, assembled from Russian components, flew in December 1974, the first Chinese-manufactured example following a year later.
About 200 remained in service in civil marks in 1992, including some working as aerial laboratories, with industry and with the WA (Air Force Transport Service) in Aeroflot colours, plus at least 25 An-12BK/PP/PPS “Cub-A/B/C/D” electronic warfare conversions in air forces and Naval Aviation. The An 12 was gradually superseded by the Il 76 with the Soviet forces from 1974.
Engines: 4 x Ivchenko Al-20K turboprop, 4,000 ehp (2 985 kW). Wing span 124 ft 8 in (38 m) Length 121 ft 4½ in (37 m) Height 32 ft 3 in (9.83 m) Empty weight: 61.730 lb (28.000 kg) Loaded weight: 121.475 lb (55.100 kg) Payload: 44,090 lb (20,000 kg) of freight or 100 troops. Maximum speed: 482 mph (777 km/h) Maximum cruise: 416 mph (670 km/h) Maxi¬mum rate of climb: 1970 ft (600 m)/min Service ceiling: 33,500 ft (10200 m) Range with full payload: 2,236 miles (3600 km). Armament: powered tail turret with two 23 mm NR-23 cannon.
Engine: 4 x turbo-prop AI-20, 3125 kW Take-off weight: 54000-61000 kg / 119050 – 134483 lb Empty weight: 30500 kg / 67241 lb Wingspan: 38.0 m / 124 ft 8 in Length: 37.0 m / 121 ft 5 in Height: 9.8 m / 32 ft 2 in Wing area: 121.7 sq.m / 1309.97 sq ft Max. speed: 640 km/h / 398 mph Cruise speed: 600 km/h / 373 mph Ceiling: 10000 m / 32800 ft Range: 5500 km / 3418 miles Crew: 6 Passengers: 130 Armament: 2 x 23mm machine-guns
An-12BK (Cub) Engines: 4 x ZMDB Progress (Ivchenko) AI-20M turboprop, 4,252eshp Length: 108.60ft (33.1m) Wingspan: 124.67ft (38.00m) Height: 34.55ft (10.53m) Maximum Take-Off Weight: 134,482lbs (61,000kg) Maximum Speed: 300mph (482kmh; 260kts) Maximum Range: 2,237miles (3,600km) Service Ceiling: 34,449ft (10,500m) Armament: Some with tail-mounted 2 x 23mm cannons Crew: 4 or 5
An-12BP Powerplants: – Four 2985kW (4000ehp) Ivchenko Al-20K turboprops Wing span 38.00m (124ft 8in) Length 33.10m (108ft 7in) Height 10.53m (34ft 7in) Wing area 121.7sq.m (131.0sq ft). Empty weight 28,000kg (61,728lb) MTOW 61,000kg (134,480lb). Max Landing Weight: 58,000kg 127,870lb Max Zero Fuel Weight: 48,000kg 105,790lb Structural Payload: 44,090kg 20,000lb Fuel Capacity: 21,000kg 46,295lb Max speed 777km/h (420kt) Max cruising speed 670km/h (360kt) Max initial rate of climb 1970ft/min Service ceiling 33,465ft Takeoff run MTOW 700m (2296ft) Range max fuel 5700km (3075nm) Range max payload 3600km (1940nm). Accommodation: Flightcrew of two pilots, flight engineer, navigator (in glazed nose) and radio operator, plus loadmasters. Main Deck Useable Volume: 97m3 285ft3 4in3 Cargo Area Width: 3.5m 11ft 5in Cargo Area Height: 2.6m 8ft 6in Main Cargo Door Width: 2.95m 9ft 8in Main Cargo Door Height: 2.6m 8ft 6in
Design of the An-10 airliner began in November 1955 and the prototype (named Ukraina) first flew on 4 July 1957, The An-10 was the initial version with accommodation for 84 passengers and a room at the rear. It entered service in July 1959 on routes from Simferopol to Moscow and Kiev. The An-10A developed version had a 2m longer fuselage and accommodated 100 to 130 passengers. It entered service in February 1960. An-10A also operated on skis in the far north of the Soviet Union. No An-10/10A were exported and Aeroflot withdrew the airliners in 1973 after a series of crashes. 104 were built.
Both versions had the NATO reporting name Cat. From this was derived the An 12 military and civil freighter, with redesigned rear fuselage incorporating a cargo loading and air drop ramp. The An 10, accommodating from 84 to 130 passengers, was designed as a bulk passenger carrier for remote and under developed regions of Russia.
Engine: 4 x turbo prop AI-20K, 2940 kW Take-off weight: 55000 kg / 121255 lb Empty weight: 30500 kg / 67241 lb Wingspan: 38.0 m / 124 ft 8 in Length: 37.0 m / 121 ft 5 in Height: 9.8 m / 32 ft 2 in Wing area: 120.0 sq.m / 1291.67 sq ft Max. speed: 725 km/h / 451 mph Cruise speed: 660 km/h / 410 mph Ceiling: 10000 m / 32800 ft Range w/max.fuel: 4000 km / 2486 miles Range w/max.payload: 1200 km / 746 miles Crew: 5 Passengers: 100-132
The An-8 military and civil transport aircraft was designed for the Soviet Air Force and Aeroflot. Both aircraft carried the NATO reporting name Camp. First flown in February 1955, the prototype military An-8 was exhibited at Tushino in 1956, powered by two 3,800kW Kuznetsov turboprop engines and with a cannon in a tail turret. 151 were built in several versions.
Engine: 2 x turbo-prop Kuznetsov AI-20D, 3810 kW Take-off weight: 43400 kg / 95681 lb Empty weight: 24400 kg / 53793 lb Wingspan: 37.0 m / 121 ft 5 in Length: 30.7 m / 100 ft 9 in Wing area: 117.2 sq.m / 1261.53 sq ft Max. speed: 520 km/h / 323 mph Cruise speed: 450 km/h / 280 mph Ceiling: 9600 m / 31500 ft Range w/max.fuel: 3900 km / 2423 miles Range w/max.payload: 1000 km / 621 miles Armament: 2 x 23mm machine-guns Crew: 6 Passengers: 70
The An-2ZA variant of the An-2 (design bureau designation An-4) is intended specially for high-altitude meteorological research. The An-4 has a glazed position immediately in front of the tail fin for an observer. The ZA suffix standing for Zondirovanie Atmosfery, translatable as ‘air sampling’. The An-4 is able to maintain power up to 10,000m by the ASh-62IR engine has a TK supercharger mounted on the starboard side of the cowling. The spinner of the An-2 standard model is deleted to aid engine cooling, and the original ailerons have been replaced by an unslotted variety.
Designed originally for agricultural duties two prototypes of what became the An-2 were designated SKh-1 and the first example made its first flight on August 31, 1947. The type was developed by OKB-153 (Design Bureau 153) which was later named after Oleg Antonov. The prototypes had a 630-hp Shvetsov ASh-61, and ASh-62 respectively, radial engine with the latter being selected for production aircraft. With an all metal fuselage and fabric wings aft of the main spar, the aircraft can carry a crew of 2 plus 14 passengers. NATO code name ‘Colt’ and is designated in US DoD nomenclature as the “Type 22”.
Externally, the An-2 engine – powering a four-bladed propeller – is held in the extreme forward of the fuselage with the cockpit directly aft. The cockpit is heavily glazed and observation port windows can be seen along the fuselage sides. Wings are of an unequal span single bay biplane design, all metal construction, with fabric covering. Each wing is connected via a single large vertical strut making up a single wing bay and each wing has dihedral. The wings have full length automatic leading edge slats and ailerons droop with flap actuation to provide great STOL performance. Fuselage is of all-metal stressed skin semi-monocoque construction. The fuselage tapers slightly into the empennage which has a single large, smooth-edge vertical tail fin and stabilizers mounted to either tail fin side. Tail is a braced all metal structure with fabric covering. Wing area is 770 square feet total. Ailerons, rudder, and elevators are all manually controlled with pushrods and cables. Flaps and trim electrically operated.
The landing gear is of conventional configuration (tail wheel design) with split axle, long stroke oleo shock absorbers on the main mounts and a fully castoring and self centering tail wheel. The main landing gear legs feature wheel bogies angled inwards with each leg braced at two points along the underside of the fuselage. Brakes are pneumatically operated. Normally two pilots, but may be flown single pilot when no passengers are aboard.
The compressed air system has an 8 litre (490 cu.in) air cylinder at 49 bars (711 PSI) maintained by an engine driven AK-50M compressor and AD-50 relief valve. A pressure gauge is on pilot’s left hand console. A pressure reducer supplies 10 bars (145 PSI) for the main brakes. The Air Pressure is required for the pneumatic main wheel brakes, but can be used to charge the landing gear shock absorbing oleo-pneumatic struts when dry nitrogen is not available. A fitting is also available to fill the tires from this system. The 8 litre air cylinder can also be charged from appropriate ground support equipment.
The electrical system has a 24 VDC battery with engine driven generator to maintain charge. A Voltmeter and Ammeter are on the Instrument Panel. The 28 VDC generator requires at least 900-1000 RPM to kick in. 36 Volt 3 phase 400hz AC power, supplied by two convertors, is used to power the Russian Gyroscopic compass, Artificial Horizon and ADF.
Nine fire detectors are located throughout the engine compartment. If the Fire Warning Lamp light, the CO2 system can be activated by breaking the safety seal and pushing the button. The CO2 bottle has an electrically activated pyro-technic cartridge to release the CO2 into the collector. Portable CO2 Fire Extinguishers are normally installed in the cockpit and cabin as well.
The Oil System consists of a 125 litre (33 gal) max permitted 22 gal tank, suction pump and an external oil cooler with electrically controlled shutters. They use Aeroshell 100 Oil.
Accommodations are generally made for a crew of one pilot and cabin seating can hold an additional 12 passengers.
Almost 3600 An-2 were built at Kiev, ending in mid-1960s after limited manufacture of specialised agricultural An-2M. Production was transferred to PZL Mielec, Poland.
The An-2R developed and built by WSK-PZL in Poland was a special agricultar model. Introduced in 1964, it carried a fiberglass container for 1960 litre pesticides or 1350 kg fertilisers.
China acquired licence and has built Yunshuji-5 (Y-5) versions from 1957.China has produced many versions of the An-2 beginning with the Fong Shou-2 (“Harvester-2”). This was the first An-2 built to agricultural specifications. The Nanchang Y-5 is a transport version since taken over in production by Harbin with 727 examples delivered. Nanchang Y-5II was an agricultural form seeing production number 229. Shijiazhuang Y-5A was a light passenger model based on the An-2T and produced in 114 examples. The agricultural derivative became the Shijiazhuang Y-5B based on the An-2 SKh. The PLAAF makes use of the Shijiazhuang Y-5B(T) para-drop model. The Nanchang Y-5C is an amphibious version of the Y-5A while the Nanchang Y-5D is a bomber crew trainer. The Nanchang Y-5K became a VIP passenger transport seating five.
Y-5
By 1991 over 18.000 of the different types were built in the Ukraine (5000), Poland (12000) and China (1000). In 1994 the Polish manufacturer of the An-2, Meliec, produced a version which conformed to the US FAR 23 requirements.
The Antonov An-2 has seen combat action. It was debuted during the Korean War (1950-1953) and later in the Vietnam War – the latter by the North Vietnamese. Some An-2’s were converted from their traditional crop dusting roles to become make-shift bombers in the Croatian War of Independence (1991).
Notable operators of the An-2 have included Afghanistan, China, Cuba, East Germany (and Germany proper), Egypt, Georgia, Hungary, Iraq, Laos, Lithuania, Macedonia, North Yemen, North Korea, Poland, South Korea, Romania, Russia, Serbia, Somalia, Sudan, Syria, Turkey, Ukraine, Vietnam, Yemen and Yugoslavia.
The An-3 was originally considered as a turboprop development of An-2, but was offered as a midlife upgrade of the An-2 to have a turboprop engine and other improvements (first flown 1980).
Another organization working on a “better” An-2 is SibNIA (Siberian Aeronautical Research Institute) in Novosibirsk, Russia. In this version, the An-2MS (An-2MC in Russian) and later usually referred to as the TVS-2MS), the radial engine was replaced by an 1,100 hp Honeywell TPE331-12UHR turbine, driving a five-bladed Hartzell propeller. The first An-2MS/TVS-2MS was first flown on September 5, 2011 and by 2015 well over fifteen examples had been delivered by SibNIA and Rusaviaprom JSC, all built, from existing An-2 airframes retaining the An-2 wings and tail feathers.
An-2-100
An-2 04 was modified for meteorological research by the addition of an observation cockpit in front of the fin, and a turbo-supercharger on its Ash-621R radial engine.
On 19 July 1954 it established an FAI altitude record for its class of 11,248 m (36,880 ft).
There was even a ground effect version, the An-2e WIG.
There have been various attempts to modernise the AN-2 over the years;
Antonov An-2 (Colt) Engines: 1 x Shvetsov ASh-62IR 9-cylinder supercharged radial, 1,000 horsepower. Length: 40.68ft (12.4m) Wingspan: 59.71ft (18.20m) Height: 13.45ft (4.10m) Empty Weight: 7,275lbs (3,300kg) Maximum Take-Off Weight: 12,125lbs (5,500kg) Maximum Speed: 160mph (258kmh; 139kts) Cruise: 100-110 kt. Maximum Range: 525miles (845km) Rate-of-Climb: 700ft/min (213m/min) T/O roll: 220 ft. Service Ceiling: 14,750 ft (4,500m) Accommodation: 2 + 12
Engine: Shvetsov ASz-62 IR, 1000 hp max Propeller: 4 blade AW-2 Wing Span: 59 ft 8 in / 18.18 m or 14.2 m / 46 ft 7 in Length: 41 ft 9 in / 12.74 m Height: 4.1 m / 13 ft 5 in Total Wing Area: 256.6 sq.ft Upper wing area: 156.2 sq.ft Lower wing area: 100.4 sq.ft Empty weight: 7,600 lb Max Take Off weight: 12,125 lb / 5500.0 kg Max Landing weight: 11,574 lb Max fuel: 2,000 lb / 312 USG Oil Qty: 22 Gallons Max / 13 Gallons minimum to 18 Gallons normal Useful load max fuel: 2,525 lb Useful load half fuel: 3500 lbs VNE: 162 kt VFE: 70 kt Best Glide: 65 kt Maximum Speed: 139kt / 160 mph / 258 km/h Economy Cruise: 100kt / 115 mph Minimum Speed: 49kt / 56 mph Take-Off Speed: 43kt / 50 mph (15 degrees of flap) Landing Speed: 46kt / 53mph (30 degrees of flap) Stall Speed: 35-40kt (controlled descents are possible at 25kt / 30mph) Typical SL Take-Off to 50 ft: 1600 ft Minimum SL Take-Off Run: 560 ft Typical SL Landing distance 50 ft: 1400 ft Normal Range: 485nm / 900 km with 45 min. res Max Range: 550nm / 6 hours endurance Max SL Rate of Climb: 680 fpm Time to 14,425 ft: 30 min Service ceiling: 16404 ft / 5000 m Ceiling: 14,425 ft with 1,100 lb cargo Cross wind component: 8 kt with full flaps Max wind speed for taxy: 20 kt Cargo compartment: 13.5 ft long x 5 ft wide x 5.9 ft high Cargo compartment capacity: 398.25 cu.ft Cargo door opening: 4.5 ft wide x 5 ft high Crew: 2 + 16
An-2V floatplane Wingspan: 59 ft 7.5 in Wing area: 769.6 sq.ft Max speed: 153 mph TO dist: 260-330 ft Landing dist: 195-260 ft Min water depth: 32 in Max wave height: 20 in
