Credit
Ronnie Robertson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
EC175 · rotors running
Single source18.06 m (59 ft 3 in) rotors running[source]
Bell 412EP · including rotors
Configuration
| Specification | Airbus Helicopters H175 | Bell 412 |
|---|---|---|
| Type | Medium utility helicopter[source] | Multipurpose utility helicopter[source] |
| National origin | Multinational[source] | United States / Canada[source] |
| Manufacturer | Eurocopter Airbus Helicopters Aviation Industry Corporation of China[source] | Bell Helicopter[source] |
| Status | In service[source] | — |
56 ft 1 in (17.09 m) including rotors[source]
Empty; EC175 · Empty weight
Single sourceGross; EC175 · Gross weight
Single sourceMaximum take-off; EC175 · Max takeoff weight
Single source4,603 kg (10,148 lb)[source]
7,500 kg (16,535 lb)[source]
7,800 kg (17,196 lb)[source]
Empty; Bell 412EP · Empty weight
Single sourceMaximum take-off; Bell 412EP · Max takeoff weight
Single sourceEC175 · 2 × Pratt & Whitney Canada PT6C-67E turboshaft engines with dual channel FADEC each for take-off
Single source2 × Pratt & Whitney Canada PT6C-67E turboshaft engines with dual channel FADEC, 1,324 kW (1,776 hp) each for take-off[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]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured | 2009–present[source] | 1979–present[source] |
|---|
| Introduction date | H175 : December 2014[source] | 1981 ( 1981 )[source] |
|---|
| First flight | H175: 17 December 2009 AC352: 20 December 2016[source] | August 1979 ( 1979-08 )[source] |
|---|
| Capacity | 12-18 pax[source] up to 18 passengers[source] | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] |
|---|
| Fuel capacity | 2,710 L (720 US gal; 600 imp gal) / 2,136 kg (4,709 lb)[source] | — |
|---|
| Main rotor area | 172 m 2 (1,850 sq ft)[source] | 1,662 sq ft (154.4 m 2 )[source] |
|---|
| Primary users | — | Japan Ground Self Defence Force See Operators for others[source] |
|---|
| Number built | — | 1,300+[source] |
|---|
| Developed from | — | Bell 212[source] |
|---|
| Variant | — | Bell CH-146 Griffon[source] |
|---|
| Fuselage length | — | 43 ft (13 m)[source] |
|---|
| Blade sections | — | root: Boeing VR-7; tip: Wortmann FX 71-H-080[source] |
|---|
| Power/mass | — | 0.2663 hp/lb (0.4378 kW/kg)[source] |
|---|
| Reported operators |
| — |
|---|