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At a glance
Measured figures
Il-103 · Length
Single source8 m (26 ft 3 in)[source]
Length
Single sourceConfiguration
| Specification | Ilyushin Il-103 | Thai Aviation Industries RTAF-6 |
|---|---|---|
| Type | Training aircraft[source] | Trainer aircraft[source] |
| National origin | Soviet Union / Russia[source] | Thailand[source] |
| Manufacturer | Ilyushin[source] | Thai Aviation Industry[source] |
| Designer | Genrikh Novozhilov[source] |
8.35 m (27.39 ft)[source]
Il-103 · 1 × Teledyne Continental IO-360-ES2B 6-cyl. air-cooled horizontally-opposed piston engine
Single source1 × Teledyne Continental IO-360-ES2B 6-cyl. air-cooled horizontally-opposed piston engine, 157 kW (211 hp)[source]
1 × Allison 250 -B17-D turboprop
Single source1 × Allison 250 -B17-D turboprop , 313 kW (420 hp)[source]
Il-103 · Wing area
Single source14.71 m 2 (158.3 sq ft)[source]
Il-103 · 623.4 ft/min
Single source3.167 m/s (623.4 ft/min)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Status | In service[source] | In service, in production[source] |
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| Primary user | see Operators[source] | Royal Thai Air Force[source] |
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| Number built | 66[source] | 3 (2017), 25 reported built[source] |
|---|
| Manufactured | 1994–present[source] | 2014–present[source] |
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| Introduction date | 1996[source] | 2014[source] |
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| First flight | 17 May 1994[source] | 14 June 2012[source] |
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| Capacity | 4 pax ( max payload: 270 kg (600 lb))[source] | — |
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| Aspect ratio | 7.6[source] | — |
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| Fuel capacity | 150 kg (330 lb) / 200 L (53 US gal; 44 imp gal) in two wing tanks[source] | — |
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| Propellers | 2-bladed Hartzell BHC-C2YF-1BF/F8459A-8R[source] | — |
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| Stall speed | 117 km/h (73 mph, 63 kn) flaps up; 111 km/h (69 mph; 60 kn) 10° flaps[source] | — |
|---|
| Never exceed speed | 340 km/h (210 mph, 180 kn)[source] | — |
|---|
| g limits | Utility: =4.4 / -1.8; Aerobatic: +6 / -3[source] | — |
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| Wing loading | 89.1 kg/m 2 (18.2 lb/sq ft)[source] | — |
|---|
| Power/mass | 8.37 kg/kW (13.75 lb/hp)[source] | — |
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| Role | single-engine, low-wing training aircraft[source] | — |
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| Source measurement | The Ilyushin Il-103 is a single-engine, low-wing training aircraft developed by the Ilyushin Design Bureau that started in 1990 in the Soviet Union . The aircraft is now produced in Russia . It was the first Russian aircraft to achieve Federal Aviation Administration certification in 1998, it is for sale in the United States .[source]Ilyushin Il-103 · Lead; only the objects and conditions stated in this passage Russia’s United Aircraft Corporation reached an agreement with Aviation Engineering Zrt of Pécs, Hungary, to develop and licence produce a modernised version of the Ilyushin Il-103 in Hungary in March 2021.[source]Ilyushin Il-103 · Operational history / Hungary; only the objects and conditions stated in this passage Capacity: 4 pax ( max payload: 270 kg (600 lb))[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Length: 8 m (26 ft 3 in)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Wingspan: 10.56 m (34 ft 8 in)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Height: 3.135 m (10 ft 3 in)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Wing area: 14.71 m 2 (158.3 sq ft)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Empty weight: 900 kg (1,984 lb)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Max takeoff weight: 1,310 kg (2,888 lb)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Fuel capacity: 150 kg (330 lb) / 200 L (53 US gal; 44 imp gal) in two wing tanks[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Powerplant: 1 × Teledyne Continental IO-360-ES2B 6-cyl. air-cooled horizontally-opposed piston engine, 157 kW (211 hp)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Maximum speed: 220 km/h (140 mph, 120 kn)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Cruise speed: 180 km/h (110 mph, 97 kn)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Stall speed: 117 km/h (73 mph, 63 kn) flaps up; 111 km/h (69 mph; 60 kn) 10° flaps[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Never exceed speed : 340 km/h (210 mph, 180 kn)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Range: 800 km (500 mi, 430 nmi) (at cruising speed, pilot and 270 kg (600 lb) payload with 30 min fuel reserve)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Service ceiling: 3,000 m (9,840 ft) (maximum certified altitude)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage Rate of climb: 3.167 m/s (623.4 ft/min)[source]Ilyushin Il-103 · Specifications (Il-103); only the objects and conditions stated in this passage | — |
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| Developed from | — | SIAI-Marchetti SF.260[source] |
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| Hardpoints | — | 4 with a capacity of up to 68 kg (150 lb) on inner, 100 lb (45 kg) on outer[source] |
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