Support Aircrafts (Rotary
Wing) |
Bell Helicopter Textron Inc. model 214 ST Type: Tactical transport helicopter Origin: USA Similar aircraft: Bell 205 Rotor system: Rotor drive: Fuselage: Tail unit: Landing gear: Accommodation: Provision for up to eighteen passengers. Powerplant: Two 1,625 shp (1,212 kW) General Electric CT7-2 turboshafts. Systems: Avionics and equipment: Dimensions, external Main rotor diameter: 15.85 m (52' 0") Tail rotor diameter: Tail rotor blade chord: Distance between rotor centers: Length, rotors turning: 18.95 m (62' 2.05") Length of fuselage pod: Height: 4.84 m (15' 10.5") Width over skids: Dimensions, internal Cabin, length: Cabin, max width: Cabin, height: Cabin volume: Areas Main rotor disc: Tail rotor disc: Weights and loadings Weight, empty, equipped: Fuel: Typical mission weights Max T-O weight: 7,938 kg (17,500 lb) Max disc loading: Performance Never exceed speed: 256 kph (159 mph) Max cruising speed: Stalling speed: Max rate of climb at S/L: Service ceiling: Hovering ceiling IGE: Hovering ceiling OGE: Operational radius: Range: 805 km (500 mi) Endurance: Weapon systems: AFP weapon systems: None Back to top Bell Helicopter Textron Inc. model 412SP/EP Type: Tactical transport helicopter Origin: USA Similar aircraft: Rotor system: Four-blade composite main rotor. Rotor drive: Fuselage: Tail unit: Landing gear: Accommodation: Flight deck of two, with provision for up to fifteen passengers. Powerplant: One 1,800 shp (1,342 kW), flat-rated to 1,308 shp (975 kW) Pratt & Whitney Canada PT6T-3B-E Turbo Twin Pac turboshafts. Systems: Avionics and equipment: [Bell 412 EP] Dual digital, automatic flight control system. Dimensions, external Main rotor diameter: 14.02 m (46') Tail rotor diameter: Tail rotor blade chord: Distance between rotor centers: Length: 12.7 m (41' 9") Length, rotors turning: 17.07 m (56') Length of fuselage pod: Height: 4.57 m (15') Width over skids: Dimensions, internal Cabin, length: Cabin, max width: Cabin, height: Cabin volume: Areas Main rotor disc: 154.39 m² (1,661 ft²) Tail rotor disc: Weights and loadings Weight, empty, equipped: 3,066 kg (6,759 lb) Fuel: Typical mission weights Max T-O weight: 5,397 kg (11,900 lb) Max T-O weight with external load: Max disc loading: Performance Never exceed speed at S/L: 241 kph (140 knts; 150 mph) Max cruising speed: 230 kph (124 knts; 143 mph) Stalling speed: Rate of climb: Service ceiling: 4,330 m (14,200') Hovering ceiling IGE: Hovering ceiling OGE: Operational radius: Max range: 420 km (227 nm; 261 mi) Endurance: Weapon systems: AFP weapon systems: None Back to top Aerospatiale SA.330L 'Puma' Type: Twin-turbine all-weather, day and night, medium transport helicopter Origin: France Similar aircraft: Super Frelon, HH-3E Jolly Green Giant, SH-3 Sea King, CH-53 Sea Stallion, Mi-8 Hip, UH-60 Black Hawk Rotor system: Four-blade main rotor, driven by a gearbox, which combines the output from the engines to the main drive shaft. Rotor drive: Fuselage: Conventional, all-metal semi-monocoque structure. Tail unit: Tailboom of monocoque construction, with a five-blade tail rotor attached to the starboard tailboom with a horizontal stabilizer to port. Landing gear: Semi-retractable tricycle type with two wheels on each unit. Accommodation: Flight deck of three, with provision for up to sixteen passengers or six litters. Powerplant: Two 1,575 shp (1,175 kW) Turbomeca Turmo IVC turboshafts, mounted on top of the fuselage, forward of the main rotor assembly. Systems: Avionics and equipment: Dimensions, external Main rotor diameter: 15.00 m (49' 2.6") Tail rotor diameter: 3.05 m (9' 11 ½") Tail rotor blade chord: Distance between rotor centers: Length, rotors turning: 18.15 m (59' 6.6") Length of fuselage pod: Height: 5.14 m (16' 10.4") Wheel track: Wheel base: Dimensions, internal Cabin, length: Cabin, max width: Cabin, height: Cabin volume: Areas Main rotor disc: 177.0 m² (1,905.3 ft²) Tail rotor disc: Weights and loadings Weight, empty, equipped: 3,615 kg (7,970 lb) Fuel: Typical mission weights Max T-O weight: 7,400 kg (16,314 lb) Max T-O weight with external load: 7,500 kg (16,535 lb) Max disc loading: Performance Never exceed speed: 258 kph (139 knts; 177 mph) Max cruising speed: 258 kph (138 knts; 160 mph) Stalling speed: Rate of climb: 552 m/min (1,810 ft/min) Service ceiling: 4,800 m (15,750') Hovering ceiling IGE: Hovering ceiling OGE: Operational radius: Range, without reserves: 570 km (310 nm; 360 mi) Endurance: Weapon systems: Generally none, but can include 7.62 mm forward firing machine-guns, 20-mm side-firing cannon, missiles and rocket launchers. AFP weapon systems: None Back to top Sikorsky S-70C 'Blackhawk' Type: Twin-turbine utility helicopter Origin: USA Similar aircraft: S-76 Seahawk Rotor system: Four-blade main rotor. Sikorsky SC-1095 blade section, with thickness-chord ratio of 9.5%. Middle section has leading-edge droop and trailing edge tab to overcome vortex impingement from preceding blade in cruising flight. Blade twist 18°. Blade tips swept back 20°. Each blade consist of hollow oval titanium spar, Nomex honeycomb core, graphite trailing-edge and root, covered with glassfiber/epoxy, with glass fiber leading-edge counterweight, titanium leading-edge sheath and Kevlar tip. Blades are tolerant to 23 mm gunfire damage, and are pressurized and equipped with gauges providing fail-safe confirmation of blade structural integrity. Electrically heated de-icing mat in leading-edge of each blade of both main and tail rotors. Forged titanium one-piece rotor head with C/R Industries elastomeric bearings which require no lubrication, reducing rotor head maintenance by 60%. Bifilar self-tuning vibration absorber on rotor head. Manual blade folding. Canting of tail rotor (20° to port) increases vertical lift and allows greater CG travel. 'Cross beam' of four-blade tail rotor of composite materials, eliminating all rotor head bearings. Rotor drive: Conventional transmission system with both turbines driving through freewheeling units to main gearbox. This is of modular construction to simplify maintenance. Transmission can operate for 30 min following total oil loss. Intermediate and tail rotor gearboxes oil lubricated. Main rotor shaft can be lowered for storage or air transport. Fuselage: Conventional semi-monocoque light alloy structure, designed to retain 85% of its passengers and a flight deck space in a vertical crash at 11.5 m/sec (38 fps), a lateral crash at 12.2 m/sec (40 fps). It can also withstand a combined force of 20g forward and 10g downward. Composite materials including glassfiber and Kevlar are used for the cockpit, doors, canopy, fairings and engine cowlings. Glassfiber Nomex floors. Tail unit: Pylon structure with port-canted tail rotor mounted on starboard side. Tail pylon design permits normal forward flight and roll-on landing if tail rotor is destroyed. Large variable incidence tailplane has a control system which senses airspeed, collective lever position, pitch attitude rate, and lateral acceleration. Tailplane is set at about +34° incidence in the hover, and -6° for autorotation. Tailplane moved by dual electric actuators, with manual backup. Tailboom folds (to starboard) immediately forward of tail pylon for transport and storage. Landing gear: Non-retractable tailwheel type with single wheel on each unit. Energy absorbing main gear with a tailwheel which gives protection for the tail rotor in taxiing over rough terrain or during a high-flare landing. Axle assembly and main gear oleo shock absorbers by General Mechatronics. Mainwheel tire size 26 x 10.00-11, pressure 8.96-9.65 bars (130-140 psi); tailwheel tire size 15 x 6.00-6, pressure 6.21-6.55 bars (90-95 psi). Accommodation: Flight deck of two, with provision for 12 passengers in standard cabin configuration and up to 19 passengers in high density layout. Forward hinged doors on each side of flight deck for access to cockpit area. External cargo hook, having a 3,630 kg (8,000 lb) lift capacity, enables the S-70C to transport a 105 mm howitzer, its crew of five and 50 rounds of ammunition. Cabin mounted rescue hoist of 272 kg (600 lb) capacity and aero-medical evacuation kit optional. Large rearward sliding door on each side of the fuselage for rapid entry and exit. Powerplant: Two 1,625 shp (1,212 kW) General Electric CT7-2C or 1,723 shp (1,285 kW) CT7-2D turboshafts. Combined transmission rating (continuous) 3,130 shp (2,334 kW). Maximum fuel capacity 1,370 liters (362 US gallons; 301 Imp gallons). Systems: Solar 90 hp (67 kW) T-62T-40-1 APU. Garret engine start system. An optional winterization kit provide a second hydraulic accumulator, maintaining engine start capability at low ambient temperatures; Bendix 30/40kVA and 20/30kVA electrical power generators; 17Ah nickel-cadmium battery. Engine fire extinguishing system. Rotor blade de-icing system optional. Avionics and equipment: Com equipment comprises E-systems AN/ARC-186 VHF-FM, GTE Sylvania AN/ARC-115 VHF-AM, Magnavox AN/ARC-164 UHF-AM, Collins AN/ARC-186(V) VHF-AM/FM, Bendix AN/APX-100 IFF transponder, Magnavox TSEC/KT-28 voice security set, and intercom. Nav equipment comprises Emerson AN/ARN-89 ADF, Bendix AN/ARN-123(V)1 VOR/marker/beacon/glidescope receiver, Sperry AN/ASN-43 gyrocompass, Singer Kearfott AN/ASN-128 Doppler and Honeywell AN/APN-209(V)2 radar altimeter. Hamilton Standard AFCS with digital three-axis autopilot. Dimensions, external Main rotor diameter: 16.36 m (53' 8") Main rotor blade chord: 0.53 m (1' 8 ¾") Tail rotor diameter: 3.35 m (11' 0") Tail rotor blade chord: Distance between rotor centers: Length overall, rotors turning: 19.76 m (64' 10") Length, rotors and tail pylon folded: 12.60 m (41' 4") Length of fuselage: 15.26 m (50' 0 ¾") Fuselage max width: 2.36 m (7' 9") Fuselage max depth: 1.75 m (5' 9") Height overall, tail rotor turning: 5.13 m (16' 10") Height to top of rotor head: 3.76 m (12' 4") Height in air transportable configuration: 2.67 m (8' 9") Tailplane span: 4.38 m (14' 4 ½") Wheel track: 2.705 m (8' 10 ½") Wheel base: 8.83 m (28' 11 ¾") Tail rotor ground clearance: 1.98 m (6' 6") Cabin door height: 1.37 m (4' 6") Cabin door width: 1.75 m (5' 9") Dimensions, internal Cabin, length: 3.84 m (12' 7") Cabin, max width: 2.34 m (7' 8") Cabin, height: 1.37 m (4' 6") Cabin floor area: 8.18 m² (88 ft²) Cabin volume: 10.96 m³ (387 ft³) Baggage compartment volume: 0.52 m³ (18.5 ft³) Areas Main rotor blades, each: 4.34 m² (46.7 ft²) Tail rotor blades, each: 0.41 m² (4.45 ft²) Main rotor disc: 210.05 m² (2,261 ft²) Tail rotor disc: 8.83 m² (95.0 ft²) Tailplane: 4.18 m² (45.0 ft²) Vertical stabilizer: 3.0 m² (32.3 ft²) Weights and loadings Weight, empty: 4,607 kg (10,158 lb) Max external load: 3,630 kg (8,000 lb) Fuel: Typical mission weights Max T-O weight: 9,185 kg (20,250 lb) Max disc loading: Performance (ISA, at max T-O weight) Never exceed speed: 361 kph (195 knts; 224 mph) Max level speed at S/L): 290 kph (157 knts; 180 mph) Max cruising speed: Cruising speed at S/L: 268 kph (145 knts; 167 mph) Stalling speed: Max rate of climb at S/L: 615 m/min (2,020 ft/min) Service ceiling: 4,360 m (14,300') Service ceiling, one engine out: 1,095 m (3,600') Hovering ceiling IGE: Hovering ceiling OGE: 1,204 m (3,950') Operational radius: Range at 250 kph (135 knts; 155 mph) at 915 m (3,000'), with max standard fuel, 30 min reserves: 473 km (255 nm; 294 mi) Range with max fuel, no reserves: 550 km (297 nm; 342 mi) Endurance: 3 hrs Weapon systems: Provision for one or two side-firing machine-guns in forward area of the cabin; Hellfire missiles, rockets; mine dispensers and other stores on ESSS; infra-red jamming flares and Tracor XM130 chaff dispenser. AFP weapon systems: None Back to top Last modified on 7/09/06  |
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