Ilyushin Il-114 / Il-114-300 — Flight Operations & Engine Technical Manual Archive

Primary-Source Documentation | Ilyushin Design Bureau & Klimov

This Living Collection brings together the complete primary-source flight operations and engine technical documentation for the Ilyushin Il-114 regional turboprop and its fully modernized, newly certified variant, the Il-114-300. Developed by the Ilyushin Aviation Complex (ИАК) and powered by the Klimov TV7-117 turboprop family, the Il-114 represents the definitive Soviet and post-Soviet approach to short-haul regional aviation — engineered for unpaved strips, arctic conditions, and high-frequency domestic routes.

Aircraft Overview

The Il-114 is a low-wing, twin-turboprop regional transport designed for routes up to 1,500 km with 60–68 passengers. Its high-efficiency wing (aspect ratio 11.0) and fixed dihedral configuration deliver strong lateral stability and low fuel burn. The tricycle landing gear with telescopic shock absorption enables operations from unpaved and arctic ice strips — a defining operational requirement for Russian regional aviation.

The Il-114-300 modernization introduces the TV7-117ST-01 engine (2,900 shp, FADEC-controlled), six-blade Aerosila AV112-114 composite propellers, the TsPNK-114M2 dual-redundant flight-navigation suite (ICAO Cat. II autopilot), and a reduced takeoff run of just 730 m. Russian Federal Air Transport Agency type certification for serial production has been granted.

Collection Manifest — 5 Documents

Note: TV7-117S manuals carry the original «НЕ ЭТАЛОН» (Non-Master Copy) archival stamp — a standard Soviet-era distribution marking.

Key Technical Data

Propulsion — TV7-117 Family

• TV7-117S (baseline): 2,500 shp — documented in this collection's engine manuals
• TV7-117ST-01 (Il-114-300): 3,100 shp takeoff power | FADEC: BARK-65SM digital core (Auto-Thrust, Reverse Thrust, Surge Protection) | Six-blade Aerosila AV112-114 composite propellers — high-chord, low-noise profile | Up to 4,000 kg thrust | Compressor: 5-stage axial + 1-stage centrifugal
• Fuel flow: 500–550 kg/h | Efficiency: 20.8 g/passenger·km
• APU: Aerosila TA-14-114 (tailcone-mounted, unassisted ground start)
• Thermal operating envelope: −60°C to +45°C (certified)
• Test validation: 3,000+ flight hours across 400+ test flights

Systems Engineering Highlights

• Hydraulics: Dual independent circuits at 207 bar (3,000 psi) — flaps, landing gear, airbrakes, nosewheel steering
• Pressurization: Dual-redundant ECS using engine bleed air, max differential 0.44 bar (6.4 psi)
• Anti-Icing: Electrical pulse-wave system (wings/tail leading edges), electrothermal (propellers/windscreens), hot air (engine intakes)
• Electrical: 115/220V 400Hz AC via 40 kW alternators per engine + 24V DC backup
• Flight Navigation: TsPNK-114M2 dual-redundant suite, ICAO Cat. II autopilot; glass cockpit simulator with 60° × 180° direct-projection visual system
• Arctic Certification: Full system performance validated at −45°C (Yakutsk / Magan field trials)
• LRU Support: AOG spare parts delivery target: 72 hours

Permitted Uses

Historical research · Flight simulation · Museum and restoration reference · Aviation education · Scale modelling · Engineering study

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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