Credit
Sardaka · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
FORCETALLY
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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-10 · fuselage only
Configuration
| Specification | Bell 412 | Mil Mi-10 |
|---|---|---|
| Type | Multipurpose utility helicopter[source] | Aerial crane[source] |
| National origin | United States / Canada[source] | Russia[source] |
| Manufacturer | Bell Helicopter[source] | Mil Moscow Helicopter Plant[source] |
| Primary users | Japan Ground Self Defence Force See Operators for others[source] | — |
Mi-10 · overall length, rotors turning
Single source32.86 m (107 ft 10 in) (fuselage only), 41.89 m (137 ft 5 in) (overall length, rotors turning)[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-10 · 2 × Soloviev D-25V turboshaft each
Single source2 × Soloviev D-25V turboshaft, 4,100 kW (5,500 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] |
55[source] |
| Manufactured | 1979–present[source] | 1964–69[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 1963[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 15 June 1960[source] |
|---|
| Developed from | Bell 212[source] | Mil Mi-6[source] |
|---|
| Variant | Bell CH-146 Griffon[source] | — |
|---|
| Capacity | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] | 28 passengers or 3 t (3,000 kg; 6,600 lb) internally up to 15 t (15,000 kg; 33,000 lb) payload on platform or 8 t (8,000 kg; 18,000 lb) max slung payload[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] | 962 m 2 (10,350 sq ft)[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | — |
|---|
| Status | — | Active as of 2014 (Mi-10K)[source] |
|---|
| Ground clearance under fuselage | — | 3.75 m (12 ft 4 in)[source] |
|---|
| Hovering ceiling out of ground effect | — | 3,000 m (9,840 ft)[source] |
|---|
Gross; Mi-10 · Gross weight
Single sourceGross; Mi-10 · Mi-10K
Single sourceMaximum take-off; Mi-10 · Max takeoff weight
Single sourceMaximum take-off; Mi-10 · Mi-10K
Single source