Mil Mi 8 MTV, Mil Mi 17
The Mi-8AMT or Mi-17 is a Soviet/Russian made Helicopter produced out of factories in Kazan Plant and Ulan-Ude Plant. The Mi-8MTV series are the ones in Russian service domestically whereas the export version of same is called Mi-17. It is a medium twin-turbine transport helicopter.
Developed upon the basic Mi-8 airframe, the Mi-17 are fitted with the larger Klimov TV3-117MT engines, rotors, and transmission.
These are multipurpose helicopter specifically designed for improved capabilities at higher altitudes and in hot weather conditions.
The Mi-17 is identifiable from the Mi-8 by the additional air filters on the turbine air intakes, as well as required by the more powerful TB-3-117A turboshaft engines it is fitted with.
The Mi-17 can climb at the rate of 8m/s. The maximum speed of the helicopter is 250km/h and with a cruise speed of 225km/h. The range of the helicopter is 465km and the service ceiling is 6,000m. The aircraft weighs around 7,489kg and its maximum take-off weight is 13,000kg.
Our product range being Mil Mi-8, Mi-8MT, Mi-8MTV-1 (Mi-17-1V), Mi-8AMT and Mi-171
Mi-17 (NATO Hip-H)
Improved version of the Mi-8, powered by two Klimov TV3-117MT turboshaft engines. Basic production version.
Mi-17-1
Export version of Mi-8AMT
Mi-17-1M
High altitude operations version, powered by two Klimov TV3-117VM turboshaft engines.
Mi-17-1V
Military transport, helicopter gunship version, powered by two Klimov TV3-117VM turboshaft engines. Export version of the Mi-8MTV-1
General characteristics
- Crew: 3 (two pilots and one engineer)
- Capacity: 24 troops / 12 stretchers / 4,000 kg (8,818 lb) cargo internally / 5,000 kg (11,023 lb) externally slung.
- Length: 18.465 m (60 ft 7 in)
- Height: 5.65 m (18 ft 6 in)
- Empty weight: 7,489 kg (16,510 lb)
- weight: 11,100 kg (24,471 lb)
- Max takeoff weight: 13,000 kg (28,660 lb) normal, 13,500 kg (29,762 lb) with under-slung load
- Powerplant: 2 × Klimov VK-2500PS-03 turboshaft engines, 1,800 kW (2,400 hp) each for take-off
2,000 kW (2,700 hp) emergency rating
- Main rotor diameter: 21.25 m (69 ft 9 in)
- Main rotor area: 354.7 m2 (3,818 sq ft)
- Blade section:NACA 23012
Performance
- Maximum speed: 280 km/h (170 mph, 150 kn)
- Cruise speed: 260 km/h (160 mph, 140 kn)
- Range: 800 km (500 mi, 430 nmi)
- Service ceiling: 6,000 m (20,000 ft)
- Hover ceiling OGE: 4,000 m (13,123 ft)
- Rate of climb: 8 m/s (1,600 ft/min)
Chinook CH 47
This medium to heavy lift double rotor aircraft has the capability of offering advantageous vertical lift and transportation of 9,000 lbs of cargo, with the versatility to transport several passengers, manage heavy cargo lifts, firefighting, search and rescue (SAR), among other services
Firefighting - helicopter is equipped with firefighting water bucket and rescue hoist system.
Rescue and First Aid - helicopter is equipped with rescue hoist and 3 Litters.
VIP - helicopter is equipped for VIP transportation with VIP furniture including one sofa, chairs, table, lavatory, kitchen, accessories, 8 cameras and 4 monitors.
Ambulance - helicopter is equipped for transportation of sick/ injured persons from accident sites to nearest hospital or from hospital to another hospital.
General characteristics
- Crew: three (pilot, copilot, flight engineer or loadmaster)
- Capacity: 33–55 troops or 24 litters and 3 attendants or
- Payload: 24,000 lb (10,886 kg)
- Length: 98 ft 10 in (30.1 m)
- Fuselage length: 52 ft (15.85 m)
- Fuselage width: 12 ft 5 in (3.78 m)
- Rotor diameter: 60 ft (18.3 m
- Height: 18 ft 11 in (5.7 m)
- Disc area: 5,600 ft2 (520 m2)
- Empty weight: 24,578 lb (11,148 kg
- Max. takeoff weight: 50,000 lb (22,680 kg)
- Powerplant:2 × Lycoming T55-GA-714A turboshaft, 4,733 shp (3,529 kW) each
Performance
- Maximum speed: 170 knots (196 mph, 315 km/h)
- Cruise speed: 160 kt (184 mph, 296 km/h)
- Range: 400 nmi (450 mi, 741 km)
- Combat radius: 200 nmi (230 mi, 370 km)
- Ferry range: 1,216 nmi (1,400 mi, 2,252 km)
- Service ceiling: 20,000 ft (6100 m)
- Rate of climb: 1,522 ft/min (7.73 m/s)
- Disc loading: 9.5 lb/ft2 (47 kg/m2)
- Power/mass: 0.28 hp/lb (460 W/kg)
Sikorsky UH 60 (Black Hawk)
The Sikorsky UH-60 Black Hawk is a four-blade, twin-engine, medium-lift utility helicopter manufactured by Sikorsky Aircraft. The UH-60 features four-blade main and tail rotors, and is powered by two General Electric T700 turboshaft engines. The main rotor is fully articulated and has elastomeric bearings in the rotor head. The tail rotor is canted and features a rigid crossbeam.
General characteristics
- Crew: 2 pilots (flight crew) with 2 crew chiefs/gunners
- Capacity: 2,640 lb (1,200 kg) of cargo internally, including 11 troops or 6 stretchers, or 9,000 lb (4,100 kg) (UH-60L) of cargo externally
- Length: 64 ft 10 in (19.76 m)
- Fuselage length: 50 ft 1 in (15.27 m)
- Fuselage width: 7 ft 9 in (2.36 m))
- Rotor diameter: 53 ft 8 in (16.36 m)
- Height: 16 ft 10 in (5.13 m)
- Disc area: 2,260 ft2 (210 m2)
- Empty weight: 10,624 lb (4,819 kg)
- Max. takeoff weight: 23,500 lb (10,660 kg)
- Rotational speed: Engine 20,900 RPM, main rotor 258 RPM (gear ratio 81:1)[176]
- Powerplant: 2 × General Electric T700-GE-701C turboshaft, 1,890 hp (1,410 kW) each
Performance
- Never exceed speed: 193 knots (222 mph; 357 km/h)
- Maximum speed: 159 kn (183 mph; 294 km/h)
- Cruise speed: 150 kn (170 mph; 280 km/h)
- Combat radius: 368 mi (320 nmi; 592 km)
- Ferry range: 1,380 mi (1,200 nmi; 2,220 km) with ESSS stub wings and external tanks
- Service ceiling: 19,000 ft (5,790 m)
- Rate of climb: 1,315 ft/min[177] (4.5 m/s)
- Disc loading: 7.19 lb/ft2 (35.4 kg/m2)
- Power/mass: 0.192 hp/lb (158 W/kg)
Sikrosky S 61 (Sea Hawk)
Sikorsky S-61L and S-61N are civilian version. They are two of the most widely used airliner and oil rig support helicopters built
General characteristics
- Crew: two pilots
- Capacity: up to 30 passengers
- Length: 58 ft 11 in (17.96 m)
- Rotor diameter: 62 ft (18.9 m
- Height: 17 ft 6 in (5.32 m)
- Disc area: 3,019 ft2 (280.6 m2)
- Empty weight: 12,336 lb (5,595 kg)
- Loaded weight: 16,164 lb (7,332 kg
- Max. takeoff weight: 19,000 lb (8,620 kg)
- Powerplant: 2 × General Electric CT58-140 turboshafts, 1,500 shp (1,120 kW) each
Performance
- Maximum speed: 166 mph (267 km/h)
- Cruise speed: 120 kn (222 km/h)
- Range: 450 NM (833 km)
- Service ceiling: 12,500 ft (3,810 m)
- Rate of climb: 1,310–2,220 ft/min (400–670 m/min)
Airbus Helicopters H215 (formerly Eurocopter AS332 Super Puma
The Airbus Helicopters H215 (formerly Eurocopter AS332 Super Puma) is a four-bladed, twin-engine, medium-size utility helicopter developed and marketed originally by Aérospatiale, later by Eurocopter and currently by Airbus Helicopters
General characteristics
- Crew: 2
- Capacity: 24 passengers plus attendant / 4,490 kg (9,899 lb)
- Length: 16.79 m (55 ft 1 in) fuselage, 18.7 m (61 ft) rotor turning
- Height: 4.97 m (16 ft 4 in)
- Empty weight: 4,660 kg (10,274 lb)
- Max takeoff weight: 9,150 kg (20,172 lb)
- Powerplant: 2 × Turbomeca Makila 1A2 turboshaft, 1,376 kW (1,845 hp) each
- Main rotor diameter:16.2 m (53 ft 2 in)
- Main rotor area: 206.12 m2 (2,218.7 sq ft)
- Blade section: root: NACA 13112; tip: NACA 13106
Performance
- Cruise speed: 277 km/h (172 mph, 150 kn) max, 247 km/h (153 mph; 133 kn) econ.
- Never exceed speed: 327 km/h (203 mph, 177 kn)
- Range: 851 km (529 mi, 460 nmi)
- Service ceiling: 5,180 m (16,990 ft)
- Rate of climb: 7.4 m/s (1,460 ft/min)
MBB/Kawasaki BK 117 B2
The Messerschmitt-Bölkow-Blohm (MBB)/Kawasaki Heavy Industries BK 117 is a twin-engined medium utility–transport helicopter. It performs many different roles, such as twin-engine redundancy, sizable clamshell-shaped rear-facing double doors, and a relatively spacious cabin; one mission to which it was deemed to be particularly suitable was the emergency medical services (EMS). The airframe is composed of riveted metal, making minimal use of composite materials, and machined to a high standard; in order to free up internal space, both the engines and transmission are positioned above the main cabin. Considerable efforts were made to reduce the weight of the aircraft were possible albeit without compromising the aircraft's structural integrity.[4] The cabin could be outfitted with various interiors in order to suit its purpose, or to incorporate greater comfort levels, which included measures to dampen both noise and vibration.
General characteristics
- Crew: 1
- Capacity: up to 10 passengers
- Length: 9.91 m (32 ft 6 in) (fuselage length)
- Height: 3.85 m (12 ft 8 in) (rotors turning)
- Empty weight: 1,727 kg (3,807 lb)
- Max takeoff weight: 3,350 kg (7,385 lb)
- Fuel capacity:697 L (183 US Gallons, 153 Imp Gallons) internal fuel
- Powerplant:2 × HONEYWELL LTS101-850B-2 (780 shp) each
- Main rotor diameter: 11.00 m (36 ft 1 in)
- Main rotor area: 95.03 m2 (1,022.9 sq ft)
Performance
- Maximum speed: 250 km/h (160 mph, 130 kn) at sea level
- Never exceed speed: 278 km/h (173 mph, 150 kn)
- Range:541 km (336 mi, 292 nmi)
- Service ceiling: 4,575 m (15,010 ft) (max certified altitude)
- Hover Ceiling: 3,565 m (11,700 ft) (in ground effect)
- Rate of climb: 11.00 m/s (2,165 ft/min)
