|Engines||4*4000hp NK-4||4*4000hp AI-20K|
|Loaded weight (max.)||55000kg||54000kg|
|Wing Load (kg/m2)||?||444|
|Power load (kg/hp)||?||3.38|
|Cruise Speed||?km/h||630 to 680km/h|
|Economy Speed at 8000m||?km/h||660 to 670km/h|
|Landing Roll||?m||500m to 650m|
|Takeoff Roll||?m||700m to 800m|
|Range (max. payload)||?km||1220km +1hreserve|
|Range (8440kg payload)||?km||4075km no reserve|
|Cabin size LxWxH||222m3||?m3|
|Passengers||75 to 84||100|
Right after the first flight of the An-8 (1955) new design started, following Aeroflot (and military) demand for four-engine transport. There was an idea keep the civil An-10 as a reserve for military: if necessary civil aircraft could be converted into military just by 'snapping on' different tail section. Project did not took a while to finish, and on March 7, 1957 Ya.I.Varennikov and V.P.Vasin performed the maiden flight of the An-10. Prototype was named 'Ukraina' but this name was abandoned soon.
An-10 got a new circular fuselage (4.1m diameter) pressurized monocoque instead of slab-sided An-8, increased flaps area and a lower tail with small bumper. The first two prototypes had 4000hp NK-4, replaced in series by its more economical 'clone' AI-20K. New engines were installed in revised cowlings with moved forward deeper air intakes. Propellers - 4.5m diameter four-blade reverse-pitch AV-68. Engines and accessories were mounted as self-contained units and easily replaced.
Wing contains twenty-two center section bag fuel tanks. Trailing edge is equipped with double-slotted hydraulically operated flaps. Wing, tailplane, fin, engine intakes and propellers are equipped with thermoelectric de-icing system. All controls are manually operated with electrically operated servo-tabs.
Stability problems resulted in 2.5 years delay of the service operations. Tail unit of An-10 evolved from single fin to configuration with small endplate fins, replaced later by splayed-out twin ventral fin. Finally problem was cured by giving a negative dihedral to the wing sections beyond the engines.
Landing gear are similar to An-8, with main four-wheel bogies with hydraulic brakes and non-braking steerable twin nosewheel. For Arctic operations skis may be fitted. The undercarriage fairings contain auxiliary power unit and cabin pressurization equipment.
An-10 crew consists of two pilots, navigator (in glazed bomber-style nose), engineer and radio operator. Normal passenger load is 85.
An-10 prototype was first demonstrated at Vnukovo Airshow in July 1957. It had accommodation for 84 passengers and playroom for children in the rear. In later modification the playroom was replaced by a small 6-passenger cabin. In May 1959 aircraft entered Aeroflot service, initially on cargo routes in Siberia, which was the typical test for any new Russian transport aircraft. Thus proved, they entered commercial service on the Simferopol-Moscow and Simferopol-Kiev routes in July 1959.
Second production version An-10A won the gold medal at the Expo-58 exhibition in Brussels. Service of the An-10A started on February 10, 1960 on the Moscow-Rostov route. It also was used to fly a Christmas trees from Moscow to Washington for Kennedy's family. It can accommodate 100 passengers (in stretched by 2m fuselage). High-density 110-passenger version was introduced in 1968 on Moldavian and Ukrainian routes.
Aircraft of the An-10 family were withdrawn from service abruptly after a fatal crash on May 18, 1972, when nobody of 102 passengers and six crewmembers survived.
At least 112 built until production ceased in 1960.
|May 1960||?||2000km with 15000kgpayload, speed 723km/h|
|June 1960||?||900km with ?kgpayload, speed 760km/h|
|? 1960||?||Demonstrated flight on single engine (outer!), carrying load of 100 passengers|
|April 29 1961||A.Mitronin, V.Terskii||500km with ?kgpayload, speed 730.616km/h|
|An-10A first production version||An-10B larger version for 130 passengers||
|Modified August 17, 1999||Back to|