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]
R44 Raven II · Length
Configuration
| Specification | Bell 412 | Robinson R44 |
|---|---|---|
| Crew | one-two pilots[source] | 1/2 (There are 4 seats including the pilot, so there can be pilot and co-pilot, with two passengers, or alternately a single pilot with 3 passenger spots)[source] |
| Type | Multipurpose utility helicopter[source] | Light utility and trainer helicopter[source] |
| National origin | United States / Canada[source] | — |
| Manufacturer | Bell Helicopter[source] | Robinson Helicopter Company[source] |
38 ft 3 in (11.66 m)[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]
R44 Raven II · 1 × Lycoming IO-540-AE1A5 6-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Lycoming IO-540-AE1A5 6-cylinder air-cooled horizontally-opposed piston engine, 245 hp (183 kW)[source]
Bell 412EP · Service ceiling
Single source20,000 ft (6,100 m)[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] | — |
|---|
| Number built | 1,300+[source] | 6,866+ (through 2023)[source] |
|---|
| Manufactured | 1979–present[source] | 1990–present[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 1993[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 31 March 1990[source] |
|---|
| Developed from | Bell 212[source] | Robinson R22[source] |
|---|
| Variant | Bell CH-146 Griffon[source] | — |
|---|
| Capacity | up to 13 passengers, maximum external load of almost 6,614 lb (3,000 kg)[source] | 3/2 / 748 lb (339 kg)[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] | 855.4 sq ft (79.47 m 2 )[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | — |
|---|
| Designer | — | Frank D. Robinson[source] |
|---|
| Status | — | In production[source] |
|---|
| Developed into | — | Robinson R66[source] |
|---|
| Fuel capacity | — | Fuel: 100 octane low lead (100LL) fuel or 100/130 octane[source] |
|---|
| Airfoil | — | NACA 63-015[source] |
|---|
| Main tank capacity | — | 31.6 US gal (26 imp gal; 120 L)[source] |
|---|
| Main tank usable fuel | — | 30.6 US gal (25 imp gal; 116 L)[source] |
|---|
| Auxiliary tank capacity | — | 18.5 US gal (15 imp gal; 70 L)[source] |
|---|
| Auxiliary tank usable fuel | — | 18.3 US gal (15 imp gal; 69 L)[source] |
|---|
| Fuel consumption | — | 15 gallons per hour (12 imp gal/h; 57 L/h)[source] |
|---|
| Altitude restrictions | — | 14,000 ft (4,300 m) density altitude or 9,000 ft (2,700 m) above ground level in order to be able to reach ground within 5 minutes in case of fire[source] |
|---|
| Country of origin | — | United States[source]Inventory Origin column; table 6, row 11, cell 3; revision 1376110979; retrieved 2026-09-30 |
|---|