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]
Length
Single sourceConfiguration
| Specification | Bell 412 | HAL Rudra |
|---|---|---|
| Crew | one-two pilots[source] | Two pilots[source] |
| Type | Multipurpose utility helicopter[source] | Armed helicopter[source] |
| National origin | United States / Canada[source] | India[source] |
| Manufacturer | Bell Helicopter[source] | Hindustan Aeronautics Limited[source] |
15.87 m (52 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]
2 × HAL/Turbomeca Shakti -1H turboshaft (1,432 shp) each
Single source2 × HAL/Turbomeca Shakti -1H turboshaft , 1,068 kW (1,432 shp) each[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] | Indian Army Indian Air Force[source] |
|---|
| Number built | 1,300+[source] | 91[source] |
|---|
| Manufactured | 1979–present[source] | 2007–present[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 2012[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 16 August 2007[source] |
|---|
| Developed from | Bell 212[source] | HAL Dhruv[source] |
|---|
| Variant | Bell CH-146 Griffon[source] | — |
|---|
| Capacity | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] | 12 passengers (14 passengers in high density seating)[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] | 136.85 m 2 (1,473.0 sq ft)[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | — |
|---|
| Designer | — | Rotary Wing Research and Design Centre[source] |
|---|
| Status | — | In service[source] |
|---|
| Fuel capacity | — | 1,055 kg (2,326 lb)[source] |
|---|
| Never exceed speed | — | 292 km/h (182 mph, 157 kn)[source] |
|---|
| Disk loading | — | 40.19 kg/m 2 (8.23 lb/sq ft)[source] |
|---|
| Reported operators | — |
|
|---|
5,800 kg (12,787 lb)[source]
245 km/h (153 mph, 132 kn)[source]