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-4A · Length
Single sourceConfiguration
| Specification | Bell 412 | Mil Mi-4 |
|---|---|---|
| Crew | one-two pilots[source] | 1 or 2[source] |
| Type | Multipurpose utility helicopter[source] | Transport helicopter[source] |
| National origin | United States / Canada[source] | Soviet Union[source] |
| Manufacturer | Bell Helicopter[source] | Mil Moscow Helicopter Plant[source] |
16.8 m (55 ft 1 in)[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-4A · 1 × Shvetsov ASh-82V 14-cylinder air-cooled radial piston engine
Single source1 × Shvetsov ASh-82V 14-cylinder air-cooled radial piston engine, 1,250 kW (1,680 hp)[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.
| Primary users | Japan Ground Self Defence Force See Operators for others[source] | Soviet Air Force Indian Air Force Polish Air Force Royal Afghan Air Force[source] |
|---|
| Number built | 1,300+[source] | over 4,000 including Z-5s[source] |
|---|
| Manufactured | 1979–present[source] | 1951–1979[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 1953[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 3 June 1952[source] |
|---|
| Developed from | Bell 212[source] | — |
|---|
| Variant | Bell CH-146 Griffon[source] | Harbin Z-5[source] |
|---|
| Capacity | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] | 16 troops or up to 1,600 kg (3,527 lb) of 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] | 346.4 m 2 (3,729 sq ft)[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | 0.21 kW/kg (0.13 hp/lb)[source] |
|---|
| Status | — | Limited Service; North Korean Air Force[source] |
|---|
| Disk loading | — | 41 kg/m 2 (8.4 lb/sq ft)[source] |
|---|
| Country of origin | — | Soviet Union[source] |
|---|
Maximum take-off; Mi-4A · Max takeoff weight
Single source