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]
K-MAX · rotors running
Single sourceConfiguration
| Specification | Bell 412 | Kaman K-MAX |
|---|---|---|
| Type | Multipurpose utility helicopter[source] | Medium lift helicopter[source] |
| National origin | United States / Canada[source] | — |
| Manufacturer | Bell Helicopter[source] | Kaman Aircraft[source] |
| Primary users | Japan Ground Self Defence Force See Operators for others[source] | — |
| Number built | 1,300+[source] |
52 ft (16 m) rotors running[source]
K-MAX · with rotors running
Single source51 ft 5 in (15.67 m) with rotors running[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]
K-MAX · 1 × Honeywell T5317A-1 turboshaft engine, 1,350 shp ( ) flat rated for take-off up to ~29,000 ft (8,839 m) to increase transmission life
Single source1 × Honeywell T5317A-1 turboshaft engine, 1,350 shp (1,010 kW) flat rated for take-off up to ~29,000 ft (8,839 m) to increase transmission life[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Manufactured | 1979–present[source] | 1991–2003, 2015–2023[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | — |
|---|
| First flight | August 1979 ( 1979-08 )[source] | December 23, 1991[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] | 6,000 lb (2,722 kg) external load at ISA +15 °C (59.0 °F) at sea level 5,663 lb (2,569 kg) external load at ISA +15 °C (59.0 °F) at 5,000 ft (1,524 m) 5,163 lb (2,342 kg) external load at ISA +15 °C (59.0 °F) at 10,000 ft (3,048 m) 5,013 lb (2,274 kg) external load at ISA +15 °C (59.0 °F) at 12,100 ft (3,688 m) 4,313 lb (1,956 kg) external load at ISA +15 °C (59.0 °F) at 15,000 ft (4,572 m)[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] | 3,669 sq ft (340.9 m 2 )[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | 0.1045 hp/lb (0.1718 kW/kg)[source] |
|---|
| Status | — | Production ended, in service[source] |
|---|
| Fuel capacity | — | 1,541 lb (699 kg) / 228.5 US gal (190 imp gal; 865 L)[source] |
|---|
| Length of fuselage | — | 41 ft 9 in (12.73 m)[source] |
|---|
| Blade section | — | - root: NACA 23012 ; tip: NACA 23011[source] |
|---|
| Never exceed speed | — | 100 kn (120 mph, 190 km/h) clean[source] |
|---|
| Hover ceiling IGE | — | 26,300 ft (8,016 m) at 6,000 lb (2,722 kg) AUW, ISA[source] |
|---|
| Disk loading | — | 3.52 lb/sq ft (17.2 kg/m 2 )[source] |
|---|
| Fuel consumption | — | 85 gal/h (71 imp gal/h; 322 L/h)[source] |
|---|