Ilyushin Il-12 — Founding Document Set
Two primary-source Soviet civil aviation documents from the Научно-Исследовательский Институт ГВФ (Scientific Research Institute of the Civil Air Fleet), covering the airframe structure and electrical power systems of the Ilyushin Il-12 — the classic post-war Soviet twin-engine transport that bridged the gap between wartime utility aviation and the modern Soviet civil fleet.
This is the opening entry of the Il-12 Collection, which will grow as additional primary-source documents are located and processed.
Document 1 — Airframe Manual
Title: Самолет Ил-12 — Планер (Aircraft Il-12 — Airframe)
Publisher: Редакционно-Издательский Отдел Аэрофлота (Aeroflot Editorial Division), Moscow
Date: 1947
Language: Russian
Institute: НИИ ГВФ (Scientific Research Institute of Civil Air Fleet)
The foundational structural reference for the Il-12 airframe, covering the aircraft's all-metal construction, fuselage, wing assembly, empennage, and landing gear. Documents the original design as issued for Aeroflot operational and training use in the immediate post-war period.
Document 2 — Electrical Systems Defect Prevention Bulletin
Title: Летная Эксплуатация и Предупреждение Дефектов Самолета Ил-12, Выпуск 3
(Flight Operation and Defect Prevention of the Il-12 Aircraft, Issue 3: Electrical Power Source Operating Characteristics)
Publisher: Aeroflot Editorial Division, Moscow
Date: 1948
Language: Russian
Library stamp: НИИ ГВФ, Inv. No. 833, Ref. 056-082.05 / П-56
Issue 3 of the operational defect-prevention series for the Il-12, focused specifically on the electrical power sources — generators, batteries, and distribution systems. Issued to Aeroflot technical and flight personnel to prevent in-service electrical failures through correct operating procedures and early defect recognition.
Aircraft Technical Overview — Ilyushin Il-12
Powerplant — Shvetsov ASh-82FN
- Type: 14-cylinder, two-row, air-cooled radial
- Takeoff output: 1,380 kW (1,850 hp) per engine
- Fuel capacity: 4,170 litres across wing tanks
- Fuel consumption at cruise: approx. 560–600 litres/hour
Performance Data
| Parameter | Figure |
|---|---|
| Maximum Speed (at 2,500 m) | 407 km/h (220 kt / 253 mph) |
| Maximum Speed (Sea Level) | 365 km/h |
| Cruising Speed (standard) | 320 km/h (173 kt) |
| Fuel-efficient cruise | 285–295 km/h |
| Single-engine cruise | 210 km/h (at 16,100 kg AUW) |
| Service Ceiling (twin-engine) | 6,500–6,700 m (21,300–21,980 ft) |
| Single-engine ceiling | 3,000 m (9,840 ft) |
| Time to 5,000 m | 15 minutes |
| Range (16 pax, min payload) | 3,000 km |
| Range (27 pax + baggage) | 2,000 km |
| Range (32 pax, max capacity) | 1,250–1,500 km |
| Takeoff run | 360–520 m |
| Landing run | 450 m |
Weight Data
- Maximum Takeoff Weight (MTOW): 17,250 kg (38,030 lbs)
- Modified MTOW (international operators, e.g. ČSA): 16,100 kg
- Empty weight: approx. 11,045 kg (24,350 lbs)
- Bare structure weight: approx. 9,000 kg
Handling & Stability Notes
- Early prototypes exhibited poor lateral stability — corrected via aerodynamic steering and dorsal stabilizers (Il-12B variants)
- Tail-tipping risk when unloaded — temporary ventral tail strut used during loading operations on early models
- Engineering bulletins issued for de-icing system updates and nosewheel enlargement for improved runway stability
- Superseded by the Ilyushin Il-14 in the mid-1950s, which brought structural wing enhancements and improved single-engine safety profiles
This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorized distributor.
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