Credit
Sardaka · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
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At a glance
Measured figures
Bell 412EP · including rotors
Single source56 ft 1 in (17.09 m) including rotors[source]
Mi-26 · Length
Single sourceConfiguration
| Specification | Bell 412 | Mil Mi-26 |
|---|---|---|
| Type | Multipurpose utility helicopter[source] | Heavy lift transport helicopter[source] |
| National origin | United States / Canada[source] | Soviet Union / Russia[source] |
| Manufacturer | Bell Helicopter[source] | Rostvertol[source] |
| Primary users | Japan Ground Self Defence Force See Operators for others[source] | Russian Aerospace Forces Algerian Air Force Utair Russian Ministry of Emergency Situations |
40.025 m (131 ft 4 in)[source]
Bell 412EP · Range
Single source529 nmi (609 mi, 980 km)[source]
Bell 412EP · 1 × Pratt & Whitney Canada PT6T-3D Twin-Pac or PT6T-3DF Twin-Pac coupled turboshaft engine - each, 1,250 shp (
Single source1 × Pratt & Whitney Canada PT6T-3D Twin-Pac or PT6T-3DF Twin-Pac coupled turboshaft engine - each, 1,250 shp (930 kW)[source]
Mi-26 · 2 × ZMKB Progress D-136 turboshaft engines each
Single source2 × ZMKB Progress D-136 turboshaft engines, 8,500 kW (11,400 hp) each[source]
Bell 412EP · 1,350 ft/min (
Single source1,350 ft/min (6.9 m/s)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Number built | 1,300+[source] | Over 300 as of 2026[source] |
|---|
| Manufactured | 1979–present[source] | 1980–present[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 1983[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 14 December 1977[source] |
|---|
| Developed from | Bell 212[source] | — |
|---|
| Variant | Bell CH-146 Griffon[source] | — |
|---|
| Capacity | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] | **90 troops or 60 stretchers 20,000 kg (44,000 lb) cargo[source] |
|---|
| Fuselage length | 43 ft (13 m)[source] | — |
|---|
| Blade sections | root: Boeing VR-7; tip: Wortmann FX 71-H-080[source] | — |
|---|
| Main rotor area | 1,662 sq ft (154.4 m 2 )[source] | 804.25 m 2 (8,656.9 sq ft)[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | — |
|---|
| Designer | — | Mil Moscow Helicopter Plant[source] |
|---|
| Status | — | In service[source] |
|---|
| Fuel capacity | — | 12,000 L (3,200 US gal; 2,600 imp gal)[source] |
|---|
| Blade section | — | root: TsAGI 12%; tip: TsAGI 9%[source] |
|---|
Maximum take-off; Mi-26 · Max takeoff weight
Single source