Search

17th of September 1997

Updated: Apr 10

The successor of the Antonov An-24 made its first flight on this day in 1997. The Antonov An-140.

The 52 seat passenger aircraft is produced in both the Ukrain and Iram (as IrAn-140). An identical-looking aeroplane is also built in Russia entirely with Russian components.

The standard powerplant for the aircraft is the motor-Sich AI-30 series 1 turboprop, a license-built version Klimov TV3-117VMA-SBM1 turboprop, providing 2465 hp. As an optional Power source, the P&W Canada PW127A in combination with Hamilton Sundstrand propellers is offered.

The An-140 has gone through several developments stages, resulting in 5 different variants of the An-140, an overview;


Three perspective view of the An-140

  • An-140T (Tactical airlift) Based on the An-140-100 turboprop airliner. It features a rear access ramp for loading and unloading of troops and/or material;

  • An-140S This subversion of the An-140T, it basically is an An-140T with a larger ramp. The An-140T and An-140S were intended to replace the Russian Air Force fleet of An-24 and An-26 aircraft. Due to political reasons, this project was abandoned in favour of the Ilyushin Il-112.

  • An-140TK A convertible cargo-passenger version for the civil market

  • An-140 VIP A 30 seat VIP version with a cabin divided into two or three zones, The three zones are; - An exclusive lounge with 4 seats, audio en video. - Business-class - economy class

  • An-140-100 The baseline model differs from the prototype by having a greater wingspan. Subversion are available for any special mission.

  • HESA IrAn-140 Iranian built version of the An-140, assembled from a kit supplied by Antonov.

Specifications for the An-140: General characteristics

  • Crew: 2

  • Capacity: 52 pax / 6,000 kg (13,228 lb) max payload

  • Length: 22.605 m (74 ft 2 in)

  • Wingspan: 24.505 m (80 ft 5 in)

  • Height: 8.225 m (27 ft 0 in)

  • Wing area: 51 m2 (550 sq ft)

  • Empty weight: 12,810 kg (28,241 lb)

  • Max takeoff weight: 19,150 kg (42,219 lb)

  • Maximum zero fuel weight: 17,800 kg (39,242 lb)

  • Maximum landing weight: 19,100 kg (42,108 lb)

  • Fuel capacity: 4,370 kg (9,634 lb)

  • Powerplant: 2 × Motor-Sich AI-30 series 1 turboprop engines, 1,838 kW (2,465 hp) each (licence-built Klimov TV3-117VMA-SBM1)

  • Alternate engines: 2x Pratt & Whitney Canada PW127A turboprops driving Hamilton Sundstrand 247F propellers

  • Propellers: 6-bladed Aerosila SV-14, 3.6 m (11 ft 10 in) diameter constant-speed fully feathering reversible propellers

Performance

  • Cruise speed: 575 km/h (357 mph, 310 kn) at 7,200–7,500 m (23,622–24,606 ft) max

  • Economical cruise speed: 520 km/h (320 mph; 280 kn) at 7,200–7,500 m (23,622–24,606 ft)

  • Range: - 900 km (560 mi, 490 nmi) with 6,000 kg (13,228 lb) payload at econ. cruise - 2,100 km (1,300 mi; 1,100 nmi) with 52 pax - 3,700 km (2,300 mi; 2,000 nmi) with 33 pax

  • Service ceiling: 7,600 m (24,900 ft)

  • Rate of climb: 6.83 m/s (1,344 ft/min)

  • Balanced field length: 1,350 m (4,429 ft)

7 views0 comments

Recent Posts

See All