Credit
Gennady Misko · CC BY-SA 3.0 · Resized · CC BY-SA 3.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
An-24V · Length
Single source23.53 m (77 ft 2 in)[source]
Falcon 20F · Length
Single sourceConfiguration
| Specification | Antonov An-24 | Dassault Falcon 20 |
|---|---|---|
| Type | Regional airliner / military transport[source] | Business jet[source] |
| National origin | Soviet Union[source] | France[source] |
| Manufacturer | Antonov Serial Production Plant Irkutsk Aviation Plant Ulan-Ude Aviation Plant[source] | Dassault Aviation[source] |
| Designer | Antonov[source] |
17.15 m (56 ft 3 in)[source]
Cruise; An-24V · at 6,000 m (20,000 ft)
Single sourceMaximum; An-24V · at 6,000 m (20,000 ft)
Single source485 km/h (301 mph, 262 kn) at 6,000 m (20,000 ft)[source]
450 km/h (280 mph, 240 kn) at 6,000 m (20,000 ft)[source]
Cruise; Falcon 20F · at 12,200 m (40,000 ft) (econ. cruise)
Single sourceMaximum; Falcon 20F · at 7,620 m (25,000 ft) (max cruise)
Single sourceAn-24V · 2 × Ivchenko AI-24 A turboprop engines (2,550 shp) each (eshp)
Single source2 × Ivchenko AI-24 A turboprop engines, 1,900 kW (2,550 shp) each (eshp)[source]
Falcon 20F · 2 × General Electric CF700 -2D-2 turbofans thrust each
Single source2 × General Electric CF700 -2D-2 turbofans , 20 kN (4,500 lbf) thrust each[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Status | In service[source] | Out of production, in active service[source] |
|---|
| Primary users | Aeroflot (former) IrAero Utair Polar Airlines[source] | Federal Express (formerly) French Navy United States Coast Guard[source] |
|---|
| Number built | >1,367[source] | 512[source] |
|---|
| Manufactured | 1959–1976[source] | 1965–1991[source] |
|---|
| Introduction date | 1962[source] | 3 June 1965[source] |
|---|
| First flight | 29 October 1959[source] | 4 May 1963[source] |
|---|
| Developed into | Antonov An-30 Antonov An-26 Antonov An-32 Xi'an Y-7 Antonov/Taqnia An-132[source] | Dassault Falcon 10 Dassault Falcon 50[source] |
|---|
| Capacity | 50 passengers[source] | 8–14 passengers[source] |
|---|
| Aspect ratio | 11.7:1[source] | 6.4:1[source] |
|---|
| Fuel capacity | 5,550 L (1,470 US gal; 1,220 imp gal)[source] | 5,200 L (1,100 imp gal; 1,400 US gal)[source] |
|---|
| Propellers | 4-bladed AV-72 constant-speed propellers , 3.90 m (12 ft 10 in) diameter[source] | — |
|---|
| Time to altitude | 17.5 min to 6,000 m (20,000 ft) 45.2 min to 8,100 m (26,600 ft)[source] | — |
|---|
| Role | 50-seat twin turboprop regional airliner[source] | French business jet[source] |
|---|
| Source measurement | The Antonov An-24 ( Russian / Ukrainian : Антонов Ан-24 ; NATO reporting name : Coke ) is a 50-seat twin turboprop regional airliner designed in 1957 in the Soviet Union by the Antonov Design Bureau . Later variants saw other uses, such as military transport and aerial cartography . The aircraft was manufactured by the Kyiv, Irkutsk and Ulan-Ude Aviation Factories. It was license-produced in China as the early versions of the Xi'an Y-7 .[source]Antonov An-24 · Lead; only the objects and conditions stated in this passage 200 were built (9 in 1962, 191 in 1963) of this improved version, delivered directly from the Kiev factory. It seated 44 passengers and had a larger interior volume. In addition, the APU exhaust was moved to the tip of the starboard nacelle. This was the second time the designation was used.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage 400 aircraft were built in the second production version. A passenger version with seating for up to 52. Maximum takeoff weight was increased to 21 tonnes, a window was added on each side, the double slotted flaps were replaced with single slotted flaps, and the centre chord was extended to compensate for the poor performance of the flaps. Some aircraft were delivered with four additional fuel bladders in the centre wing. Production began in 1964.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage Turbojet boosted export version, similar to the An-24V but fitted with a 1,985-lb (8830 N) thrust auxiliary turbojet engine in the starboard nacelle.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage An-24PS ( Poiskovo-Spasahtel'nyy – SAR)[source]Antonov An-24 · Variants / Special mission aircraft; only the objects and conditions stated in this passage Capacity: 50 passengers[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Length: 23.53 m (77 ft 2 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Wingspan: 29.20 m (95 ft 10 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Height: 8.32 m (27 ft 4 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Wing area: 74.98 m 2 (807.1 sq ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Empty weight: 13,300 kg (29,321 lb)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Max takeoff weight: 21,000 kg (46,297 lb)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Powerplant: 2 × Ivchenko AI-24 A turboprop engines, 1,900 kW (2,550 shp) each (eshp)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Propellers: 4-bladed AV-72 constant-speed propellers , 3.90 m (12 ft 10 in) diameter[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Maximum speed: 485 km/h (301 mph, 262 kn) at 6,000 m (20,000 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Cruise speed: 450 km/h (280 mph, 240 kn) at 6,000 m (20,000 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Range: 2,400 km (1,500 mi, 1,300 nmi) with maximum fuel; 550 km (340 mi; 300 nmi) with maximum payload[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Service ceiling: 8,400 m (27,600 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Time to altitude: 17.5 min to 6,000 m (20,000 ft) 45.2 min to 8,100 m (26,600 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage | During the 1950s and 1960s, the French government, which had taken a significant interest in the re-establishment and growth of its national aviation industries in the aftermath of the Second World War , developed a detailed request for a combined liaison / trainer aircraft, to be equipped with twin-turbofan engines. Among those companies that took interest in the government request was French aircraft manufacturer Dassault Aviation . In December 1961, French aircraft designer and head of Dassault Aviation, Marcel Dassault , gave the go-ahead to proceed with work towards the production of an eight- to 10-seat executive jet /military liaison aircraft, which was initially named as the Dassault-Breguet Mystère 20 . The emerging design was of a low-wing monoplane, which drew upon the aerodynamics of the transonic Dassault Mystère IV fighter-bomber , and was equipped with a pair of rear-mounted 14.68 kN (3,300 lbf) Pratt & Whitney JT12A-8 turbojet engines.[source]Dassault Falcon 20 · Development / Origins; only the objects and conditions stated in this passage Progress between Dassault and Pan Am was rapid, moving from engineering evaluations of the type to the formation of general agreements between the two companies. In response to feedback received from Pan American, the aircraft was re-engined with a pair of General Electric CF700 engines and several dimensions were increased. Accordingly, Pan American formed an agreement with Dassault to distribute the Mystère 20 in the western hemisphere; the firm placed an initial order for 40 aircraft along with options for a further 120. On 10 July 1964, the re-engined aircraft made its first flight. On 1 January 1965, the first production aircraft performed its maiden flight; in June 1965, both French and American type certifications were awarded. On 10 June 1965, French aviator Jacqueline Auriol achieved the women's world speed record using the first Mystère 20 prototype, having flown at an average recorded speed of 859 km/h over a distance of 1000 km.[source]Dassault Falcon 20 · Development / Origins; only the objects and conditions stated in this passage In 1973, FedEx's Falcons, designation FA-20-DC, cost $1.2 million each and were modified with a 55-by-74.5-inch forward cargo door with independent power supply, higher mtow, reinforced floor, plugged windows, and bigger brakes.[source] |
|---|
| Stall speed | — | 152 km/h (94 mph, 82 kn)[source] |
|---|
| Country of origin | — | France[source]Inventory Origin column; table 1, row 54, cell 4; revision 1377423821; retrieved 2026-10-02 |
|---|
862 km/h (536 mph, 465 kn) at 7,620 m (25,000 ft) (max cruise)[source]
750 km/h (470 mph, 400 kn) at 12,200 m (40,000 ft) (econ. cruise)[source]
An improved model of the aircraft, designated the Falcon 200 , was developed, which featured more advanced jet engines and other major improvements to increase range, capacity, and comfort. The Falcon 200, along with the Falcon 20G and HU-25 models, were powered by a pair of Garrett ATF3 engines. According to the magazine Flying , the Falcon 200 variant was more comparable to the newer Falcon 50 trijet than the original Falcon 20 model.[source]Dassault Falcon 20 · Development / Further development; only the objects and conditions stated in this passage
During 2013, the FAA modified 14 CFR part 91 rules to prohibit the operation of jets weighing 75,000 pounds or less that were not Stage 3 noise compliant after 31 December 2015. The Falcon 20 was listed explicitly in Federal Register 78 FR 39576 . Any examples of the type that had not been modified, either by the installation of Stage 3 noise-compliant engines or have had hush kits installed upon noncompliant engines, were no longer permitted to fly anywhere in the contiguous 48 states after 31 December 2015. However, 14 CFR §91.883 Special flight authorizations for jet airplanes weighing 75,000 pounds or less – lists special flight authorizations that may be granted for operation after 31 December 2015.[source]Dassault Falcon 20 · Development / Further development; only the objects and conditions stated in this passage
Prototype, one built. F-WLKB, initially powered by two 14.68 kN (3,300 lbf) Pratt & Whitney JT12A-8 turbojet engines. Now stored at Musée Air et Espace Aéroport Paris – Le Bourget.[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Initial production version, with lengthened fuselage compared to first prototype and with 10–12 seats. Powered by 4,200 lbf (19 kN) CF700-2B engines.[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Falcon 20CC (s/n 073)[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Falcon 20G[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Falcon 20H[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Improved variant, powered by two 2360-kg (5,200-lb) Garrett ATF3-6A-4C turbofan engines and with more fuel. First flown on 30 April 1980.[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
United States Coast Guard version of the Falcon 20G. 41 built. Equipped with two Garrett AiResearch Garrett ATF3-6-2C turbofan engines.[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Enlarged, 30-passenger commuter airliner derivative of Falcon 20, powered by two 27.0 kN (6,070 lbf) Lycoming ALF 502 D turbofans. One prototype built, first flying on 11 May 1973. No further production of Falcon 30 or proposed 40-passenger, shorter-range Mystére 40-100 .[source]Dassault Falcon 20 · Variants; only the objects and conditions stated in this passage
Pakistan Air Force – 3 in service, including 2 DA-20s in EW , ECM , ESM roles[source]Dassault Falcon 20 · Operators / Current military operators; only the objects and conditions stated in this passage
Royal Australian Air Force – Three in service from 1967 to 1989. No. 34 Squadron RAAF[source]Dassault Falcon 20 · Operators / Former military operators; only the objects and conditions stated in this passage
Capacity: 8–14 passengers[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Length: 17.15 m (56 ft 3 in)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Wingspan: 16.30 m (53 ft 6 in)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Height: 5.32 m (17 ft 5 in)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Wing area: 41.00 m 2 (441.3 sq ft)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Empty weight: 7,530 kg (16,601 lb)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Max takeoff weight: 13,000 kg (28,660 lb)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Powerplant: 2 × General Electric CF700 -2D-2 turbofans , 20 kN (4,500 lbf) thrust each[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Maximum speed: 862 km/h (536 mph, 465 kn) at 7,620 m (25,000 ft) (max cruise)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Cruise speed: 750 km/h (470 mph, 400 kn) at 12,200 m (40,000 ft) (econ. cruise)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Stall speed: 152 km/h (94 mph, 82 kn)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Range: 3,350 km (2,080 mi, 1,810 nmi)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage
Service ceiling: 12,800 m (42,000 ft) (absolute ceiling)[source]Dassault Falcon 20 · Specifications (Falcon 20F); only the objects and conditions stated in this passage