Ilyushin Il-103

"Il-103" redirects here. For the road, see Illinois Route 103.

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.^[1] It was the first Russian aircraft to achieve Federal Aviation Administration certification in 1998, it is for sale in the United States.^[2]

Il-103
Il-103 at MAKS, Zhukovskiy, 1999.
Role	Training aircraft
National origin	Soviet Union / Russia
Manufacturer	Ilyushin
Designer	Genrikh Novozhilov
First flight	17 May 1994
Introduction	1996
Status	In service
Primary user	see Operators
Produced	1994–present
Number built	66

Operational history

Reviewers Dave Unwin and Marino Boric described the design in a 2015 review as "very robust, safe and comfortable. It was designed for everyday operation on poor runways and with the ability to cope with every variation of the harsh Russian climate."^[2]

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.^[3]

Operators

Current

 Laos

• Lao People's Liberation Army Air Force:^[4] three delivered with 21 ordered

Peru

• Peruvian Army: Five operated out six delivered.

Somaliland ^{[5][better source needed]}

• Somaliland Armed Forces : Four purchased for civilian aviation and military purposes

Specifications (Il-103)

Data from ^[6][7][8]

General characteristics

• Crew: 1
• Capacity: 4 pax ( max payload: 270 kg (600 lb))
• Length: 8 m (26 ft 3 in)
• Wingspan: 10.56 m (34 ft 8 in)
• Height: 3.135 m (10 ft 3 in)
• Wing area: 14.71 m² (158.3 sq ft)
• Aspect ratio: 7.6
• Empty weight: 900 kg (1,984 lb)
• Max takeoff weight: 1,310 kg (2,888 lb)
• Fuel capacity: 150 kg (330 lb) / 200 L (53 US gal; 44 imp gal) in two wing tanks
• Powerplant: 1 × Teledyne Continental IO-360-ES2B 6-cyl. air-cooled horizontally-opposed piston engine, 157 kW (211 hp)
• Propellers: 2-bladed Hartzell BHC-C2YF-1BF/F8459A-8R

Performance

• Maximum speed: 220 km/h (140 mph, 120 kn)
• Cruise speed: 180 km/h (110 mph, 97 kn)
• Stall speed: 117 km/h (73 mph, 63 kn) flaps up; 111 km/h (69 mph; 60 kn) 10° flaps
• Never exceed speed: 340 km/h (210 mph, 180 kn)
• Range: 800 km (500 mi, 430 nmi) (at cruising speed, pilot and 270 kg (600 lb) payload with 30 min fuel reserve)
• Service ceiling: 3,000 m (9,840 ft) (maximum certified altitude)
• g limits: Utility: =4.4 / -1.8; Aerobatic: +6 / -3
• Rate of climb: 3.167 m/s (623.4 ft/min)
• Wing loading: 89.1 kg/m² (18.2 lb/sq ft)
• Power/mass: 8.37 kg/kW (13.75 lb/hp)

See also

Aircraft of comparable role, configuration, and era

• Cessna 172
• Piper Cherokee
• Beechcraft Musketeer
• Socata TB-10