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Decommissioned PAF Aircrafts (Rotary Wing)

SA.330L | H-13 | Hughes 300 | S-58T | H-19A | S-62B/HH-52A | Ships

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Sud Aviation/ 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
Design Features:
Four-blade main rotor, with a fully articulated hub and integral rotor brake. Attachment of each blade to its sleeve by two quick-disconnect pins enables blades to be folded back quickly by manual methods. The five-blade tail rotor has flapping hinges only, and is located on the starboard side of the tailboom. Mechanical shaft and gear drive. Main gearbox on top of cabin behind engines, has two separate inputs from the engines and five reduction stages. Drive to the tail rotor is via shafting and an intermediate angle gearbox, terminating at a right-angle tail rotor gearbox. The hydraulically controlled rotor brake, installed on the main gearbox, permits stopping of the rotor 15 seconds after engine shutdown.
Structure:
Each of the moulded blades is made up of a glass fiber roving spar, a composite glass fiber and carbonfiber fabric skin, with Moltoprene/honeycomb filler. The leading-edge is covered with a stainless steel protective section. The fuselage is a conventional all-metal semi-monocoque structure. Local use of titanium alloy under engine installation, which is outside the main fuselage shell. Monocoque tailboom supports the tail rotor on the starboard side and a horizontal stabilizer on the port side. Optional blade de-icing system, with heating mat protected by titanium shielding on leading-edge of each main and tail rotor blade.
Landing gear:
Messier-Hispano-Bugatti semi-retractable tricycle type, with twin wheels on each unit. Main units retract upward hydraulically into fairings on sides of fuselage; self-centring nose unit retracts rearward. Hydraulic differential disc brakes, controlled by foot pedals. Lever-operated parking brake. Emergency pop-out flotation units can be mounted on rear landing gear fairings and forward fuselage.
Accommodation:
Crew of one or two side by side on anti-crash seats on flight deck, with jump-seat for third crew member if required. Door on each side of flight deck on later versions. Internal doorway connects flight deck with folding seat in doorway for an extra crew member or cargo supervisor. Dual controls standard. Accommodation in main cabin for 16 individually equipped troops, six stretchers and six seated patients, or equivalent freight. The number of troops can be increased to 20 in the high-density version. Strengthened floor for cargo-carrying, with lashing points. Jettisonable sliding door on each side of main cabin; or port-side door with built-in steps and starboard-side door in VIP or airline configurations. A hatch in the floor below the centreline of the main rotor is provided for carrying loads of up to 3,200kg on an internally mounted cargo sling. A fixed or retractable rescue hoist (capacity 275kg) can be mounted externally on the starboard side of the fuselage. The cabin can be equipped in 8/9/12-seat VIP, 17-seat commuter or 20-seat high-density layouts, with baggage compartment and/or toilet facilities in the rear of cabin.
Powerplant:
Two Turbomeca Turmo IVC turboshaft engines, each with maximum rating of 1,575 shp (1,175 kW) and fitted with intake anti-icing. Engines are mounted side by side above cabin forward of the main rotor assembly and separated by a firewall. They are coupled to the main rotor transmission box, with shaft drive to the tail rotor, and form a completely independent system from the fuel tanks up to the main gearbox inputs. Fuel in four flexible tanks and one auxiliary tank beneath cargo compartment floor, with total capacity of 1,544 liters. Provision for additional 1,900 liters in four auxiliary ferry tanks installed in cabin. External auxiliary tanks (two each 350 liters capacity) can be fitted. For long-range missions (mainly offshore) one or two special internal tanks each 215 liters can be fitted in the cabin. Each engine is supplied normally by a pair of interconnected primary tanks, the lower halves of which have self-sealing walls for protection against small calibre projectiles.
Systems:
Two independent hydraulic systems, each 172 bars, supplied by self-regulating pumps driven by the main gearbox. Three-phase 200 V AC electrical power supplied by two 15 kVA 400 Hz alternators driven by the port side intermediate shaft from the main gearbox and available on the ground under the same conditions as the hydraulic ancillary systems. 28.5 V 10 kW DC power provided from the AC system by two transformer-rectifiers. Main aircraft battery used for self-starting and emergency power in flight. De-icing of engines and engine air intakes by warm air bled from compressor. Anti-snow shield for Winter operations.
Avionics and equipment:
Optional communications equipment includes VHF, UHF, tactical HF and HF/SSB radio installations and intercom system. Navigational equipment includes radio compass, radio altimeter, VLF Omega, Decca navigator and flight log, Doppler, and VOR/ILS with glide path. Autopilot, with provision for coupling to self-contained navigation and microwave landing systems. Full IFR instrumentation available optionally. The search and rescue version has nose-mounted Bendix RDR 1400 or RCA Primus 40 or 50 search radar, Doppler, and Decca self-contained navigation system, including navigation computer, polar indicator, roller-map display, hover indicator, route mileage indicator and groundspeed and drift indicator.
Dimensions, external
Main rotor diameter:
15.00 m (49' 2.6")
Tail rotor diameter:
3.05 m (9' 11 ")
Tail rotor blade chord:
Distance between rotor centers:
Length, rotors turning:
18.15 m (59' 6.6")
Length of fuselage pod:
14.1 m (46' 1")
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 m (1,905.3 ft)
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:
Payload:
3,200 kg (7055 lb)
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, hull mounted 20-mm side-firing cannon; free flight rocket launchers; AT-3 'Sagger' wire guided ATGM; 100 kg (220 lb) freefall bombs; A-93 AAMs.
AFP weapon systems:
None

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Bell H-13 'Sioux'
Type:
Origin:
USA
Similar aircraft:
Rotor system:
Rotor drive:
Fuselage:
Tail unit:
Landing gear:
Accommodation:
Powerplant:
Systems:
Avionics and equipment:
Dimensions, external
Main rotor diameter:
Tail rotor diameter:
Length, rotors turning:
Height:
Areas
Main rotor disc:
Tail rotor disc:
Weights and loadings
Weight, empty, equipped:
Typical mission weights
Max T-O weight:
Performance
Never exceed speed:
Max cruising speed:
Stalling speed:
Max rate of climb at S/L:
Service ceiling:
Hovering ceiling IGE:
Hovering ceiling OGE:
Operational radius:
Range:
Weapon systems:
Program:

Hughes Tool Company/Schweizer Aircraft Corporation 300
Type:
Light Utility Helicopter
Origin:
USA
Similar aircraft:
Robinson R22
Rotor system:
Fully articulated, counter-clockwise rotating, three-blade main rotor, and a two-blade tail rotor. Main rotor rpm, 471.
Rotor drive:
Fuselage:
Conventional pod and boom design.
Tail unit:
Landing gear:
Skid type landing gear, with damped shock absorbers.
Accommodation:
Normally seats two but is capable of seating a third passenger between the two main seats if the middle collective control stick is removed and a seat cushion is put in its place.
Powerplant:
One 190 shp (141 kW) Textron-Lycoming HIO-360-D1A four-cylinder, fuel injected piston engine. Fuel capacity 121 liters (32 US gallons).
Systems:
Flight controls are directly linked to the control surfaces of the helicopter. No hydraulics. Generally have two sets of controls with the right-hand side controls of the cockpit removable.
Avionics and equipment:
Dimensions, external
Main rotor diameter:
8.18 m (26.83')
Tail rotor diameter:
1.3 m (4.25')
Length, overall:
9.4 m (30.83')
Height, overall:
2.65 m (8.72')
Fuselage length:
6.76 m (22.19')
Landing gear tread width:
1.99 m (6.54')
Areas
Main rotor disc:
52.49 m (565 ft)
Tail rotor disc:
Weights and loadings
Weight, empty:
499 kg (1,100 lb)
Typical mission weights
Max T-O weight:
Gross weight:
930 kg (2,050 lb)
Payload:
431 kg (950 lb)
Max Fuel weight:
87 kg (192 lb)
Performance
Max speed at S/L:
176 kph (95 knts; 109 mph)
Cruising speed:
159 kph (86 knts; 99 mph)
Stalling speed:
Max rate of climb at S/L:
Service ceiling:
Hovering ceiling IGE:
3,300 m (10,800')
Hovering ceiling OGE:
2,600 m (8,600')
Max endurance:
3.8 hrs (5.5 hrs with auxilliary tanks)
Operational radius:
Range:
587 km (365 mi)
Weapon systems:
Program:

Sikorsky/California Helicopters S-58T/ US Army designation UH-34D 'Choctaw'
Type:
Medium transport helicopter
Origin:
USA
Similar aircraft:
Rotor system:
Four-blade all-metal main and tail rotors. Blades of main rotor interchangeable. Tail rotor has servo control. Main and tail rotor brakes.
Rotor drive:
Fuselage:
Semi-monocoque structure.
Tail unit:
Landing gear:
Conventional three-wheel undercarriage, with tailwheel at extreme rear of fuselage. Air-oil shock-absorber struts. Mainwheels have rotating struts to reduce drag and weight. Tailwheel is fully castoring and self-centring, with an anti-swivelling lock. Mainwheel tires 11.00 x 12. Tailwheel tire 6.00 x 6. Toe-operated mainwheel brakes. Track 3.66 m. Wheelbase 8.75 m.
Accommodation:
Pilot's compartment above main cabin seats two side by side with dual controls and one loadmaster. Cabin normally seats 12 passengers. Up to eight stretchers can be carried or 2,495 kg (5,500 lb) payload . Sliding windows of pilot's compartment removable in an emergency. Cabin and cockpit air conditioned and soundproofed.
Powerplant:
One Wright R-1820-84 radial air-cooled engine, rated at 1,136kW for take-off (S-58C) or 1,342kW Pratt & Whitney PT6T-3 Twin-Pac comprising two PT6 turboshaft engines side by side with combining gearbox. Engine is mounted behind large clamshell doors in nose of fuselage to allow complete accessibility from ground level. Fuel capacity is from 750 liters to 1,164 liters depending on model.
Systems:
Avionics and equipment:
Dimensions, external
Main rotor diameter:
17.1 m (56')
Tail rotor diameter:
Length, overall:
14.2 m (46' 6")
Height:
4.4 m (14' 3 ")
Width:
3.6 m (12')
Areas
Main rotor disc:
Tail rotor disc:
Weights and loadings
Weight, empty, equipped:
3,402 kg (7,500 lb)
Typical mission weights
Max T-O weight:
Performance
Never exceed speed:
212 kph (117 knts; 132 mph)
Max cruising speed:
204 kph (110 knts; 127 mph)
Stalling speed:
Rate of climb:
390 m/sec (1,275 ft/min)
Service ceiling:
3,658 m (12,000')
Hovering ceiling IGE:
3,170 m (10,400')
Hovering ceiling OGE:
1,980 m (6,500')
Operational radius:
Range:
482 km (260 nm; 300 mph)
Weapon systems:
Generally none but can carry 7.62 mm machine-gun pods or rocket pods.
Program:

Sikorsky H-19A 'Chickasaw'
Type:
Origin:
USA
Similar aircraft:
Rotor system:
Rotor drive:
Fuselage:
Tail unit:
Landing gear:
Accommodation:
Powerplant:
Systems:
Avionics and equipment:
Dimensions, external
Main rotor diameter:
Tail rotor diameter:
Length, rotors turning:
Height:
Areas
Main rotor disc:
Tail rotor disc:
Weights and loadings
Weight, empty, equipped:
Typical mission weights
Max T-O weight:
Performance
Never exceed speed:
Max cruising speed:
Stalling speed:
Max rate of climb at S/L:
Service ceiling:
Hovering ceiling IGE:
Hovering ceiling OGE:
Operational radius:
Range:
Weapon systems:
Program:

Sikorsky S-62B/HH-52A
Type:
VIP Transport Helicopter
Origin:
USA
Similar aircraft:
Rotor system:
Rotor drive:
Fuselage:
Tail unit:
Landing gear:
Accommodation:
Powerplant:
Systems:
Avionics and equipment:
Dimensions, external
Main rotor diameter:
Tail rotor diameter:
Length, rotors turning:
Height:
Areas
Main rotor disc:
Tail rotor disc:
Weights and loadings
Weight, empty, equipped:
Typical mission weights
Max T-O weight:
Performance
Never exceed speed:
Max cruising speed:
Stalling speed:
Max rate of climb at S/L:
Service ceiling:
Hovering ceiling IGE:
Hovering ceiling OGE:
Operational radius:
Range:
Weapon systems:
Program:



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Last modified on 7/30/06

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