Credit
John Davies · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
CH-146 Griffon · Length
Single sourceCH-146 · Length
Single sourceConfiguration
| Specification | Bell CH-146 Griffon | Mil Mi-10 |
|---|---|---|
| Type | Utility helicopter[source] | Aerial crane[source] |
| National origin | United States / Canada[source] | Russia[source] |
| Manufacturer | Bell Helicopter[source] | Mil Moscow Helicopter Plant[source] |
| Status | In service[source] | Active as of 2014 (Mi-10K) |
56 ft 1 in (17.09 m)[source]
17.1 m[source]CH-146 Griffon
17.1 m[source]CH-146 Griffon
17.1 m[source]CH-146 Griffon
Mi-10 · fuselage only
Single sourceMi-10 · overall length, rotors turning
Single source32.86 m (107 ft 10 in) (fuselage only), 41.89 m (137 ft 5 in) (overall length, rotors turning)[source]
Gross; CH-146 Griffon · Gross weight · Maximum gross weight
Single sourceMaximum take-off; CH-146 · Max takeoff weight
Single source11,900 lb (5,398 kg)[source]
5,400 kg[source]CH-146 Griffon · Maximum gross weight
Empty; Mi-10 · Empty weight
Single sourceEmpty; Mi-10 · Mi-10K
Single sourceCH-146 · pilot, co-pilot, and flight engineer
Single source3 (pilot, co-pilot, and flight engineer)[source]
Mi-10 · pilot, copilot and flight engineer, navigator/radio operator and optional technician
Single source3 (pilot, copilot and flight engineer, navigator/radio operator and optional technician)[source]
Cruise; CH-146 · Cruise speed
Single sourceMaximum; CH-146 Griffon · Maximum speed
Single sourceMaximum; CH-146 · Maximum speed
Single source140 kn (160 mph, 260 km/h)[source]
118 kn (136 mph, 219 km/h)[source]
260 km/h[source]CH-146 Griffon
260 km/h[source]CH-146 Griffon
260 km/h[source]CH-146 Griffon
Cruise; Mi-10 · Cruise speed
Single sourceMaximum; Mi-10 · Maximum speed
Single sourceCH-146 · 1 × Pratt & Whitney Canada PT6T-3D Twin-Pac coupled turboshaft engine, 1,250 shp (
Single source1 × Pratt & Whitney Canada PT6T-3D Twin-Pac coupled turboshaft engine, 1,250 shp (930 kW)[source]
Mi-10 · 2 × Soloviev D-25V turboshaft each
Single source2 × Soloviev D-25V turboshaft, 4,100 kW (5,500 hp) each[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Primary user | Royal Canadian Air Force[source] | — |
|---|
| Number built | 100 (85 in service)[source] | 55[source] |
|---|
| Manufactured | 1992–1997[source] | 1964–69[source] |
|---|
| Introduction date | 1995[source] | 1963[source] |
|---|
| First flight | 1992[source] | 15 June 1960[source] |
|---|
| Developed from | Bell 412[source] | Mil Mi-6[source] |
|---|
| Capacity | 10 troops or 6 stretchers (some sources state maximum 8 passengers)[source] | 28 passengers or 3 t (3,000 kg; 6,600 lb) internally up to 15 t (15,000 kg; 33,000 lb) payload on platform or 8 t (8,000 kg; 18,000 lb) max slung payload[source] |
|---|
| Main rotor area | 1,662 sq ft (154.4 m 2 )[source] | 962 m 2 (10,350 sq ft)[source] |
|---|
| Blade sections | - root Boeing VR-7; tip Wortmann FX 71-H-080[source] | — |
|---|
| Ground clearance under fuselage | — | 3.75 m (12 ft 4 in)[source] |
|---|
| Hovering ceiling out of ground effect | — | 3,000 m (9,840 ft)[source] |
|---|
| Service ceiling | — | 3000 м[source] |
|---|
Gross; Mi-10 · Gross weight
Single sourceGross; Mi-10 · Mi-10K
Single sourceMaximum take-off; Mi-10 · Max takeoff weight
Single sourceMaximum take-off; Mi-10 · Mi-10K
Single source