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]
UH-1H · with rotors
Configuration
| Specification | Bell 412 | Bell UH-1 Iroquois |
|---|---|---|
| Type | Multipurpose utility helicopter[source] | Utility helicopter[source] |
| National origin | United States / Canada[source] | United States[source] |
| Manufacturer | Bell Helicopter[source] | Bell Helicopter[source] |
| Primary users | Japan Ground Self Defence Force See Operators for others[source] | United States Army (historical) Japan Ground Self-Defense Force Canadian Army See Operators section for others |
57 ft 9 + 5 ⁄ 8 in (17.618 m) with rotors[source]
UH-1H · over skids
Single source9 ft 6 + 1 ⁄ 2 in (2.908 m) (over skids)[source]
Cruise; Bell 412EP · Cruise speed
Single sourceMaximum; Bell 412EP · Maximum speed
Single source140 kn (160 mph, 260 km/h)[source]
122 kn (140 mph, 226 km/h)[source]
Cruise; UH-1H · (at 5,700 ft (1,700 m) at maximum takeoff weight)
Single sourceMaximum; UH-1H · at maximum takeoff weight; also Vne at this weight
Single sourceBell 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]
UH-1H · 1 × Lycoming T53-L-13 turboshaft , 1,400 shp ( ) (limited to 1,100 shp (
Single sourceUH-1H · ) by transmission
Single source1 × Lycoming T53-L-13 turboshaft , 1,400 shp (1,000 kW) (limited to 1,100 shp (820 kW) by transmission)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Number built | 1,300+[source] | >16,000[source] |
|---|
| Manufactured | 1979–present[source] | 1956–1987[source] |
|---|
| Introduction date | 1981 ( 1981 )[source] | 1959[source] |
|---|
| First flight | August 1979 ( 1979-08 )[source] | 20 October 1956 (XH-40)[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] | 3,880 pounds (1,760 kg) including 11–14 troops, 6 stretchers and attendant, or equivalent 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] | 1,809.56 sq ft (168.114 m 2 )[source] |
|---|
| Power/mass | 0.2663 hp/lb (0.4378 kW/kg)[source] | 0.1159 hp/lb (0.1905 kW/kg)[source] |
|---|
| Status | — | In service[source] |
|---|
| Variants | — | Bell UH-1N Twin Huey Bell 204/205 Bell 212 Bell 214 Bell 412 Bell CH-146 Griffon Bell UH-1Y Venom[source] |
|---|
| Developed into | — | Bell 214ST Bell 533[source] |
|---|
| Disk loading | — | 5.25 lb/sq ft (25.6 kg/m 2 )[source] |
|---|
Maximum take-off; UH-1H · Max takeoff weight
Single source