The design of the AS.332 commenced in 1974 and the definitive prototype was preceded by a modified Puma, the AS.331, which flew in September 1977 with an uprated transmission driven by two Turbomeca Makila turboshafts. The first AS.332 flew on 13 September 1978 (the prototype designated as the AS 331) and introduced additional changes to improve payload, performance and survivability, and to reduce maintenance.

Changes included a new energy-absorbing landing gear with increased wheel base and track, a lengthened nose section, more efficient fiberglass main and tail rotors, greater fuel capacity, and revised fin and tail plane contours to improve handling. In 1980 a fourth prototype introduced a cabin stretch of 0.76m with two additional windows and up to three more passengers.

Aerospatiale SA330 Puma Article

When development of the SA.330 (then called Alouette IV) and the production of seven test aircraft (two prototypes and five pre-series machines) was authorised by the STAe in June 1963 (the War Ministry allocated 20 million francs), Turmo III free turbines of the same rating were selected in preference to the Bastan powerplant. A full-size mock-up, seen at the Paris Air Show that year, was similar to the final version apart from the shape of the nose. The evaluation aircraft were registered F-ZWWN to F-ZFWT, and the first of them made its maiden flight on 15 April 1965; all of these, plus a sixth pre-series aircraft, were flying by mid-1968, the last on 30 July 1968.

Beginning with the AS 331 prototype, this produced the AS 332A commercial pre-production models followed by the first commercial production examples designated as the AS 332C. Military pre-production models became the AS 332B followed by the initial militarized forms in the AS 332B1. The AS 332 C1 was a dedicated Search & Rescue (SAR) example equipped with six cabin stretchers and a surface search radar. The AS 332F became a militarized anti-submarine and anti-ship variant while the AS 332F1 was a base navalized Super Puma modified to contend with the rigors of the salty ocean environment.

The sixth pre-production aircraft had a different nose, which was standardized on the production aircraft. As a result of the trials programme the SA330 won the approval of the French Army, which ordered 130 (designated SA.330H).

After several trial examples were built the production of the Puma was started in 1968 powered by twin 1115kW Turbomeca Turmo IVC turboshafts and carrying sixteen combat troops at 260kph for a range of 555km. The first deliveries of fifty-four SA 330Bs to the French army took place in 1969, the type becoming operational the following year and the first of forty-eight Westland-built Pumas joining the RAF in 1971.

Thirty of the SA.330B, which is the version for the French ALAT (Army Air Corps), were built from spring 1969.

The SA.330C export version also went into production in 1969.

The SA.330 may carry a 2500kg external sling load or 20 troops and is equipped with a hoist capable of lifting a 175kg load. The SA.330 carries a crew of 2. The main rotor blades fold back for stowage, and all landing wheels retract, but protrude slightly. The fully-articulated main rotor had four extruded aluminum bladesand the anti-torque rotor five-blades.

The last pre-production Puma was modified by Westland for the RAF and after promising tests, a joint production agreement was reached (concluded on 2 April 1968) and Westland Helicopters built 48 SA 330E as the Puma HC.Mk I.

Those which are in British and French military service are powered by two 1,185 shp Turbomeca Turmo IIIC4 turboshaft engines. They can carry a wide variety of cannon, machine‑guns, and mis­siles, or be used to transport up to 20 troops or cargo.

The RAF’s SA.330E Puma HC Mk.1s built by Westland in 1970-71, were assigned to No.33 and 230 Squadrons.

The SA.330F civil version flew in September 1969 powered by 1290shp Turmo lVA engines. It was superseded by the SA.330J, introduced in 1976, and the SA.330L for military use. Both have 1580shp Turmo IVC engines and composite material main rotor blades. The SA.330J has been certified for all-weather operation and has an anti-icing system on both the rotor blades and air intakes.

The SA 330J provides for a standard crew of two on the flight deck, with a toilet and baggage compartment at the rear of the cabin. Equipped with thermal de-icing of the main rotor blades, thermal anti-icing of the tail rotor blades, special intakes and weather radar, the SA 330J, on 25 April 1978, received certification for all-weather operations, including flight in icing conditions.

Aerospatiale went on to build 686 (some sources claim 697) SA 330s (before switching production to the Super Puma in 1981) in successively improved versions for numerous export customers. These included civil operators, especially those in the oilfield support industry once the all-weather capability was available in the SA 330J and L. Between 1970 and 1984, Aerospatiale sold 126 civil models in all.

The SA330 was also assembled in Romania as the CNIAR-330, the first IAR-330H Puma flying on 22 October 1975. In 1977 a licence was granted for the Puma to be built in Romania.

Romania became the sole manufacturer of the Puma helicopter, and had completed 112 by mid-1985, mostly for military use. Romania exported a number of Puma, the military customers included Sudan, which received 12 in 1985. By 1994 IAR had built over 200 and production of the IAR-330L. Despite being a COMECON and Warsaw Pact member, Romania strove for some measure of independence from the USSR. Instead of buying popular Soviet designs, Romania bought a licence to manufacture the French Aérospatiale SA 330 Puma on 30 July 1974. The first licensed helicopter was flown on 22 October 1975 under the designation IAR-330L. Production was at the Industria Aeronautică Română plant at Ghimbav near Brașov.

At least 163 of these helicopters have been built, out of which 104 were assigned to Romania’s military, 2 were retained by the manufacturer and 57 were produced for export (Pakistan, Ivory Coast, United Arab Emirates, Sudan, Ecuador). There is also a search and rescue (SAR) version, fitted with inflatable floats for emergency landing at sea, which has been built in a small batch.

The fuselage of the SA 330 Puma is a conventional all-metal semi-monocoque structure, with the engines mounted externally on top of the fuselage shell and forward of the main rotor assembly. The rotor is driven via a main gearbox, with twin free-wheeling spur gears to combine the outputs of the two turboshaft engines to a single main drive shaft. Should both engines fail the auto-rotating main rotor continues to drive the auxiliary take-offs for the shaft-driven tail rotor, alternator, dual hydraulic pumps, and ventilation fan. The tail boom, which carries the flapping-hinge five-blade tail rotor on the starboard side and a horizontal stabiliser on the port side, is a monocoque continuation of the aft fuselage. Early main rotor blades were of light alloy construction, but those fitted since 1976 are composite units of glassfibre, carbon fibre and honeycomb construction, with anti-abrasion leading edges of stainless steel. The landing gear is of the semi-retracting tricycle type, with twin wheels on each unit, all of which are partly exposed when retracted.
The first SA 330Bs for the French army and air force, and the SA 330Es for the Royal Air Force, were powered by Turmo III C4 turboshaft engines with a take-off rating of 990kW; and the SA330C/H military export versions, first flown in September 1968, had originally 1044kW Turmo IVBs, but from the end of 1973 SA 330H aircraft were equipped with 1174kW Turmo IVC engines which include anti-icing of the engine air intakes. The first SA 330F/G civil versions had Turmo IVA engines of 1070kW as first flown on 26 September 1969 and delivered from the end of 1970; but the SA 330G acquired Turmo IVC engines from the end of 1973; and this is also installed on the SA 330J (civil) and SA 330L (military) helicopters of 1976.

Features:
A four-blade main rotor, with a fully articulated hub and integral rotor brake. Attachment of each blade to its sleeve is by two quick-disconnect pins enabling the blades to be folded back manually. The five-blade tail rotor on the starboard side of the tailboom has flapping hinges only, with mechanical shaft and gear drive. The main gearbox is on top of cabin behind engines, and has two separate inputs from the engines and five reduction stages. Drive to the tail rotor is via shaft and an intermediate angle gearbox, and a right-angle tail rotor gearbox. The hydraulically controlled rotor brake, on the main gearbox, allows the rotor to be stoped 15 seconds after engine shutdown.
Each of the moulded blades is made up of a fibreglass roving spar, a composite fibreglass and carbonfibre fabric skin, with Moltoprene/honeycomb filler. The leading-edge is covered with a stainless steel protective section. The fuselage is an all-metal semi-monocoque structure. Titanium alloy is used under the engines, which are outside the main fuselage shell. The monocoque tailboom supports the tail rotor and a horizontal stabiliser on the port side.
The Messier-Hispano-Bugatti semi-retractable tricycle type landing gear, with twin wheels on each unit retract upward hydraulically into fairings on sides of fuselage and a self-centring nose unit retracts rearward. The wheels have hydraulic differential disc brakes, controlled by foot pedals, and a lever-operated park brake.
The two Turbomeca Turmo IVC turboshaft 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 is in four flexible tanks and one auxiliary tank beneath the cargo compartment floor, with a total capacity of 1,544 litres. There is provision for an additional 1,900 litres in four auxiliary ferry tanks to be installed in the cabin. External auxiliary tanks (two of 350 litres each) can be fitted. For long-range missions one or two extra internal tanks of 215 litres each can be fitted in the cabin. Each engine is supplied by a pair of interconnected primary tanks, the lower halves of which have self-sealing walls for protection against small calibre projectiles.
Crew can be one, or two side by side on anti-crash seats on the flight deck, with a jump-seat for third crew member if required. Doors feature on each side of flight deck on later versions. An internal doorway connects the flight deck with folding seat in the doorway for an extra crew member or cargo supervisor. Dual controls standard. Accommodation in main cabin for 16 individually equipped troops (20 in the high-density version), six stretchers and six seated patients, or equivalent freight. The floor is strengthened for cargo-carrying, with lashing points. The main cabin can have jettisonable sliding door on each side or a port-side door with built-in steps and starboard-side door in VIP or airline configuration. 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 have a baggage compartment and/or toilet facilities in the rear of cabin.
Two independent hydraulic systems, each 172 bars, are supplied by self-regulating pumps driven by the main gearbox. Three-phase 200V AC electrical power is supplied by two 15 kVA 400Hz 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. 28.5V 10kW DC power is provided from the AC system by two transformer-rectifiers. A main aircraft battery is used for self-starting and emergency power in flight. De-icing of engines and engine air intakes is by warm air bled from compressor.
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.
A wide range of armament can be carried, including side-firing 20mm cannon, axial-firing 7.62mm machine guns, missiles and rockets.

The design of the AS.332 commenced in 1974 and the definitive prototype was preceded by a modified Puma, the AS.331, which flew in September 1977 with an uprated transmission driven by two Turbomeca Makila turboshafts. The first AS.332 flew on 13 September 1978 (the prototype designated as the AS 331) and introduced additional changes to improve payload, performance and survivability, and to reduce maintenance.
Changes included a new energy-absorbing landing gear with increased wheel base and track, a lengthened nose section, more efficient fiberglass main and tail rotors, greater fuel capacity, and revised fin and tail plane contours to improve handling. In 1980 a fourth prototype introduced a cabin stretch of 0.76m with two additional windows and up to three more passengers.

Production began in France in 1981, and is also undertaken by IPTN in Indonesia under license from Aérospatiale. Samco assembling 17 AS.332Ms under licence for the Republic of Singapore Air Force, and CASA planed to assemble 12 AS.332Bs for the Spanish Army in 1988/89, both joining fleets of French-built helicopters. A total of 197 military Super Pumas had been ordered by May 1987.
There are versions of the Super Puma based on short and long fuselage variants.

The short fuselage AS.332B is the standard 23-seat tactical transport military version and the short fuselage AS.332F is a naval variant. The AS.332F features a folding tail-rotor pylon, a deck-landing assistance device, additional corrosion protection, a nose mounted Omera 360 deg scan search radar, and sonar equipment. Anti-ship armament comprises two AM.39 Exocets, six AS.15TT, or a mix of one Exocet and three AS.15TT. The AS.332F can also be configured for search and rescue. The civil equivalent of the AS.332B and F is the AS.332C.
There is a stretched AS.332M 25-seat military transport.
The stretched AS.332L civil version of the AS.332M is in wide use with 34 with Bristow Helicopters, redesignated Tigers to signify equipment differences from the standard AS.332L.

Aérospatiale was devel¬oping the AS.332 Mk.II incorporating advanced rotor systems, including lengthened blades with parabolic tips, an uprated gearbox to allow increased power transmission, and upgraded avionics and equipment. Performance and manoeuvrability improvements over the standard AS.332 are significant, and uprated engines give a better hot/high capability. The first Super Puma Mk.II flew on February 6, 1987.
The 2002 build Eurocopter AS.332L2, a modified Super Puma, had the latest glass cockpit technology with a four¬ axis coupled autopilot for IFR, day/night approaches and SAR search modes. HIF, VHF/FM, UHF and homing devices make up the extra avionics, whilst an Ultraforce 11 FLIR camera is under the nose, a 30 million candela Nitesun on the lower starboard fuselage and a Skyshout system is also installed. A comprehensive set of medical equipment is carried, including a heart monitor and defibrillator.

Externally, the Super Puma shares many of its characteristics with the preceding Puma design. Its engines are mounted forward and high atop the fuselage exhausting outwards above the crew cabin. The engines power a four-bladed composite construction main rotor and five-bladed tail rotor mounted to starboard. The pilot and co-pilot are fitted into a glazed forward-mounted canopy with excellent views in all vital directions. Each pilot is afforded an automobile-style door for easy entry and exit. The fuselage sides are dominated by two large cabin doors (one door to a side) with cabin windows. The undercarriage is full retractable and features two main landing gears (single-wheeled) recessing into low-mounted fuselage side sponsons as well as a nose gear fitting two wheels recessing behind and under the cockpit floor. Like the Puma series before it, the Super Puma features an elevated empennage with a single vertical tail fin and a horizontal tailplane jutting out of the portside of the fin.

The AS 332L first flew on October 10th, 1980, appeared as a new civilian production model and sported a lengthened fuselage for an increase in its cabin space and fuel capacity as well as uprated turboshaft engines. Operations of the type were certified in 1983. The AS 332L1 was a similar model featuring an even more lengthened fuselage containing an airliner-type interior and uprated Makila 1A1 turboshaft engines and made its operational appearance in 1986. The AS 332M became a militarized version of the AS 332L model while the AS 332M1 was a similar militarized AS 332L with a lengthened fuselage.

Indonesian Aerospace (formally IPTN) has license-produced the Super Puma as the NAS 332L1 of which at least 7 were sold to Iran in a 1996 deal.

The AS 332L2 “Super Puma Mk II” was a further civilian-based transport development of the type beginning service in 1993 and featuring a long-fuselage for an extra row of seats. These Super Pumas were also given a spheriflex rotor head with EFIS flight instrumentation as well as longer main rotor blades with parabolic tips and a four-axis Automatic Flight-Control System (AFCS). The cockpit was updated to include four large multi-function LCD screens. Passenger seating is between 19 and 24 persons. A 15-passenger VIP model (Super Puma Mk II VIP) is also available complete with galley and toilet.

The AS 332L1 utilized twin Turbomeca Makila 1A1-series turboshaft engines running at 1,742 shaft horsepower each while the AS 332L2 fitted twin Turbomeca 1A2-series turboshaft engines rated at 1,819 shaft horsepower each. Top speed for the AS 332L1 was 278 kilometers-per-hour with a range of 841 kilometers and a service ceiling of 20,000 feet. Rate-of-climb was listed at 1,618 feet-per-minute. Comparatively, the AS 332L2 operated at a top speed of 278 kilometers-per-hour, a range of 831 kilometers, a service ceiling of 23,622 feet and a rate-of-climb of 1,614 feet-per-minute.

The AS 332L has seen extensive production and use during its run. These are now being replaced by the newer AS 332L2 Super Puma MK II series. Bristow Helicopters acquired no fewer than 31 custom AS 332L’s for its North Sea-based offshore oil rig work. Customizations included folding cabin seats, life rafts, jettisonable cabin doors, IFR instrumentation, de-icing equipment, baggage compartments and North Sea-related navigational aid equipment. These came under the designation of “Tiger” (sometimes called “Super Tigers”).

Following on from the Alpha XH-1 research, Denel comimssioned two Puma helicopters to develop the systems required for the Rooivalk. Puma J1 first flew in 1986 and was the primary avionics, weapons and flight control systems’ test bed. Puma J2 flew shortly afterwards, its primary task being to develop the weapons systems and integrate them with the aircraft and the other on hoard systems. Concurrently two missile tests were conducted: the first studied the effect of missile blast on the tail boom and the other studied the accuracy of the weapons and associated systems.
From the J model Pumas the Rooivalk started to take shape in the form of the initial experimental development model (XDM).
Production of the original Puma totalled over 686.

The Airbus Helicopters H215 (formerly Eurocopter AS332 Super Puma) is a four-bladed, twin-engined, medium-sized, utility helicopter developed and initially produced by French aerospace company Aérospatiale.

Gallery

Versions:

SA.330 Puma / Alouette IV
Medium-lift 20-troop military helicopter with retractable tricycle u/c and four-blade main rotor driven by two 1320shp Turbomeca Turmo III.C4 turboshafts positioned in housing above main cabin. Prot. F-ZWWN FF 14 Apr. 1965. Jointly built by Aerospatiale and Westland. Originally named Alouette IV.

SA.330B
Initial military production version; delivered to ALAT (French Army Air Corps) from 1969; two 984kW Turmo IIIC-4 turboshaft engines. First flown January 1969.

SA 330B Orchidee
Prototype for battlefield surveillance version, fitted with ESB Orchidee 360° radar and datalink system.

SA.330C Puma
Military export version; similar to SA 330B with provision for fixed or retractable undercarriage; some fitted with surveillance radar and flotation gear.

SA 330E / Puma HC.1
Westland-built version for Royal Air Force, designated HC Mk 1. Forty built.

SA.330F
First civil version with 1,070kW Turmo IVA engines. First flown 26 September 1969; French certification 12 October 1970; FAA IFR certification 23 June 1971.

SA 330G
Uprated SA.330F model for civil and military markets; two 1,174kW Turmo IVC engines; composite main rotor blades.

SA.330H
Export version of Puma SA.330G for ALAT and military customers.

SA.330J
Puma SA.330G with composite main rotor blades and higher weights introduced in 1976. Some assembled by IPTN in Indonesia.

SA.330L
Puma SA.330H with composite main rotor blades and higher weights introduced in 1976.

SA.330S Puma
Portuguese SA.330C modified by OGMA with composite main rotor and two 1700shp Turbomeca Makila I turboshafts.

SA.330Z
Puma SA.330 fitted with experimental tail fenestron. Prot F-ZWRR.

IAR.330L Puma
Puma Licence-built in Romania by IAR Brasov with 1588shp Turbomeca Turmo IV-CA turboshafts.

SA.330R / SA.331
Stretched Puma SA.330 used as development aircraft for SA.332 Super Puma with two 1755shp Turbomeca Makila turboshafts and redesigned rotor head. Also known as SA.330R. F-ZWWO First flown on 5 Sept. 1977.

Oryx
Upgraded Puma by Denel (Atlas Aviation) in South Africa. Atlas has conducted the development and production of a variant of the SA 330 Puma helicopter as the Oryx, and development of a modular weapon suite for the Puma helicopter to convert it into a gunship.

Aérospatiale SA 330 Puma
Engine: 2 x Turboméca Turmo III C4, 1302 shp
Length: 46.129 ft / 14.06 m
Height: 13.714 ft / 4.18 m
Rotor diameter: 49.213 ft / 15.0 m
MTOW: 14112.0 lb / 6400.0 kg
Max. speed: 151 kt / 280 km/h
Service ceiling: 15748 ft / 4800 m
Range: 756 nm / 1400 km
Crew: 2+20

SA 330B Puma
Rotor dia: 49 ft 2.5 in /15 m
Max cruise: 169 mph / 272 km/h

SA 330E Puma / HC.1

Engines: 2 x Turbomeca Turmo TS, 1185shp
Rotor dia: 49 ft 2.5 in / 15 m
Length: 59 ft 6.5 in / 18.15 m
Height: 16 ft 10.5 in / 5.14 m
Max TO wt: 14,770 lb / 6700 kg
Max level speed: 169 mph / 272 kph

SA330J Puma
Engines: 2 x Turbomeca Turmo IVC, 1558 shp
TBO: 2000 hrs
Main rotor: 49.5 ft
Seats: 16/22
Length: 59.8 ft
Height: 16.9 ft
Max ramp wt: 16,315 lb
Width: 5.14 m
Standard empty weight: 8358 lb
MTOW: 16,315 lb
Max landing weight: 16,315 lb
Max useful load: 7957 lb
Max sling load: 7715 lb
Disc loading: 8.5 lb/sq.ft
Power loading: 5.2 lb/hp
Max usable fuel: 2734 lb
Max rate of climb: 1200 fpm
Service ceiling: 15,750 ft
Hover in ground effect: 7545 ft
Hover out ground effect: 5580 ft
Max speed: 142 kts
Normal cruise/3000 ft: 128 kt
Fuel flow normal cruise: 1269 pph
Endurance normal cruise: 2 hr

IAR-330H

IAR-330L
Powerplant: 2 × Turboméca Turmo IVC, 1,175 kW (1,576 hp) each
Main rotor diameter: 15.00 m (49 ft 3 in)
Main rotor area: 176.7 m2 (1,902 sq ft)
Length: 18.15 m (59 ft 7 in) (overall), 14.06 m (46 ft 2 in)
Height: 5.14 m (16 ft 10 in)
Empty weight: 3,615 kg (7,970 lb)
Max takeoff weight: 7,400 kg (16,314 lb)
Never exceed speed: 294 km/h (183 mph, 159 kn)
Cruise speed: 271 km/h (168 mph, 146 kn) (max cruise)
Range: 572 km (355 mi, 309 nmi)
Service ceiling: 6,000 m (20,000 ft)
Rate of climb: 9.2 m/s (1,810 ft/min)
Crew: 1–3
Capacity: 16 fully equipped troops

AS 332 Super Puma
Engine: 2 x Turboméca Makila 1A, 1701 shp
Length: 61.45 ft / 18.73 m
Rotor diameter: 49.475 ft / 15.08 m
MTOW: 18411.8 lbs / 8350.0 kg
Range: 342 nm / 634 km
Crew: 2
Payload: 24 Pax / 2722 kg int. / 4500 kg ext.

AS.332B Super Puma
Engine: 2 x Turbomeca Makila 1A1, 1380kW
Installed pwr: 2370 kW
Rotor dia: 15.6 m
Fuselage length: 15.5 m
Height: 4.92m
No. Blades: 4
Empty wt: 4290 kg
MTOW: 9000 kg
Max internal payload: 2722kg
Max external payload: 4500kg
Max speed: 295 kph
Cruising speed: 262km/h
ROC: 530 m/min
Ceiling: 4600 m
HIGE: 2700 m
HOGE: 1600 m
Fuel cap (+aux): 2060 lt (1900 lt)
Range: 635 km
Crew: 2-3
Pax: 20

AS332C Super Puma
Engine: Turbomeca Makila, 1755 shp
TBO: 2000 hrs
Main rotor: 51.1 ft
Seats: 21
Length: 61.4 ft
Height: 16.1 ft
Max ramp weight: 18,080 lb
Max takeoff weight: 18,080 lb
Standard empty weight: 9115 lb
Max useful load: 8965 lb
Max landing weight: 18,080 lb
Max sling load: 9920 lb
Disc loading: 8.8 lb/sq.ft
Power loading: 5.2 lb/hp
Max usable fuel: 4576 lb
Max rate of climb: 1810 fpm
Service ceiling: 15,580 ft
Hover in ground effect: 9840 ft
Max speed: 160 kts
HOGE: 7545 ft
Normal cruise @ 3000 ft: 135 kt
Fuel flow @ normal cruise: 1030 pph
Endurance @ normal cruise: 4.2 hr
First built: 1979

AS.332L1 Super Puma Mk.2
Engine: 2 x Turbomeca Makila 1A1
Instant pwr: 1400 kW
Rotor dia: 15.6 m
MTOW: 8600 kg
Useful load: 4140 kg
Max cruise: 140 kts
Max range: 1216 km
HIGE: 10,170 ft
HOGE: 7545 ft
Service ceiling: 13,450 ft
Seats: 22/26

AS.332L2 Super Puma Mk.2
Engine: 2 x Turbomeca Makila 1A2
Instant pwr: 1573 kW
Rotor dia: 16.2 m
MTOW: 9150 kg
Useful load: 4490 kg
Max cruise: 150 kts
Max range: 1215 km
HIGE: 9414 ft
HOGE: 7382 ft
Seats: 22/28

Oryx Gunship
Engine: 2 x Turbomeca Turmo IV C.
Instant pwr: 1115 kW.
Rotor dia: 15 m.
MTOW: 7400 kg.
Max speed: 140 kts.
Max cruise: 136 kts.
Max range: 348 km.
HOGE: 12,000 ft.
Crew: 2.

Airbus H215
Engine type: 2 x Safran Makila 1A1 Turboshaft
Takeoff power: 1,357 kW / 1,819 shp
One engine inoperative (OEI 2 min 30s): 1,400 kW / 1,877 shp
Hover ceiling IGE: 3.250 m
Hover ceiling OGE: 2,300 m
Recommended cruise speed: 252 Km/hr
Max range with standard fuel tanks at SL: 642 km / 866 km
Max endurance with standard fuel tanks: 772 km / 1,241 km
Max endurance with standard fuel tanks: 3 hr, 19 min / 4 hr, 25 min
Max endurance with SL Aux fuel tanks: 4 hr, 02 min / 6 hr, 35 min
Rotor diameter: 15.60 m
Cabin Internal volume: 11.4 cu.m / 13.4 cu.m
Crew + passengers / troops: 1 or 2 + 17/20 – 1 or 2 +19/22
Max takeoff weight (MTOW): 8,600 kg
Max takeoff with external load: 9,350 kg
Useful load: 4,038 kg / 3,889 kg
Max External load: 4,500 kg
Standard fuel tank capacity: 1,228 kg / 1,613 kg

SA 321 Super Frelon development stemmed from the prototype – but not accepted for production – SA 3200 Frelon built to a French military specification. In a joint effort between Sud Aviation and Sikorsky, the base SA 3200 Frelon was developed into the “Super Frelon” (with Frelon translating into “Hornet”). The result was a rather large troop transport version that would go onto to be produced into three different variants.

At the end of the fifties, the French armed forces issued a specification for a heavy helicopter for troop transport and Sud-Aviation initiated the SA.3200 Frelon project. Sud-Aviation was formed on 1 March 1957 from the Sud-Ouest and Sud-Est Aviation companies. One of its first major projects was the Frelon, a large helicopter of conventional layout powered by three Turbomeca Turmo III turboshaft engines mounted above its cabin. Two are side-by-side in front of the rotor shaft and, the third behind the rotor shaft. Each engine supplied independent drive to the rotor head, thus ensuring twin-engined capability if one unit should fail. The first SE.3200 prototype flew on 10 June 1959. All fuel is carried externally in two tanks mounted to each side of the cabin.
Both the main and tail rotors are four-bladed and there is a variable-incidence tail control surface on each side of the rear fuselage. Standard equipment includes dual controls, radio and full night-flying equipment, with provision for an automatic pilot.
The Frelon cabin is ventilated and sound-proofed and measures 7m in length, with a width of 1.90m, and head-room of 1.83m. The entire tail assembly swings to the right to permit direct loading into the cabin. Normal entry is via large sliding doors on each side of the fuselage. Trials of the SA.3200 were suspended in 1963 in favour of the SA.3210 Super Frelon programme.

SA321 Super Frelon Article

The planned production version was the SA.3210 powered by three 932kW Turmo IIIC engines. Development of the Frelon lapsed in favour of the SA.3210 (now SA.321) Super Frelon.

The SA321 was designed as an improved version of the SA 3200 Frelon (hornet) with the suport of Sikorsky, who were largely responsible for the rotor system.

Fiat, in Italy, were responsible for producing the main gearbox and transmission. Prototypes were produced as land-based troop trans­port accommodating up to 30 troops, and as naval anti-submarine type forming the basis of the SA 321G initial production model.

The basic structure of the Super Frelon was no different from the original model but for the US-built rotor system with six blades folded back automatically with the extreme rear of the tailboom, the watertight boat-type hull with a rear-loading ramp, and the three turbines were located side-by-side above the fuselage and the landing gear was of the fixed tricycle type. The two prototypes were followed by two pre-production models with Turmo III turbines and other variants with civil registrations.

The first prototype of the Super Frelon (originally designated SA 3210-01 (F-ZWWE) flew on 7 December 1962, powered by three 985kW Turmo IIIG-2 engines, represented the troop transport version and (with a modified fuselage and retractable landing gear) in July 1963 set up three speed records: 341.23km/h over 3km; 350.47km/h over 15/25km (unbeaten until 1967); 334.28km/h over 100km. The second prototype, flown on 28 May 1963, was representative of the naval version, with stabilising floats on the main landing gear supports incorporating search radar, dipping sonar and other anti-submarine equipment.

The cabin of the Super Frelon in the military transport version is 7m long and can take two jeeps or two DCA 20mm cannon. For casualty evacuation it can take 15 stretcher cases with two medical attendants. The rear loading ramp is hydraulically operated and can remain open even in flight. In 1962 the tri-turbine SA 3210 Super Frelon set three international records: 211.12 mph over 3 km; 217.53 mph on 15 to 25 km dash; and 197.41 mph for 100 km.

Four pre-production aircraft followed, and the French Government ordered an initial production series of 17, designated SA (AS) 321G, in October 1965, which entered service in 1966. The first flight of the first production machine was on 30 November 1965. By mid-1967, twenty-five were in service. These are a mixture of SA.321G’s, which can carry four homing torpedoes or other antisubmarine stores, or gear for mine-sweeping, minelaying or ship towing and were equipped with two Sylphe radars, all-weather navigation systems, an automatic stabilization system; and pure-transport versions capable of airlifting up to 30 troops, 18 casualty litters or 4000kg of cargo over 200km stage lengths. Five SA.321 transports have also been supplied to the Heil Avir le Israel, and delivery of sixteen Super Frelons to the South African Air Force began in July 1967.

Carrying weapons in addition to search radar and sonar, the SA 321Gs were used to patrol the seaward approaches to the French navy’s nuclear submarine base at Brest. Some were later modified with nose-mounted radar and Exocet missiles for anti-ship attack, and the SA 321Ga was delivered for utility transport duties. In French naval service the Frelon equiped three units: 33F and 20S at St Mandrier and 32F based at Lanveoc.

The French Navy utilized the SA 321G, which was fitted in a maritime configuration with a dunking sonar system, torpedoes and other anti-submarine warfare equipment. These specialized versions would later be relegated to search and rescue roles in the navy capacity.

Only 24 SA 321Gs were built, but the production total was boosted by small-scale production of other variants, including the SA 321K assault transport for Israel (12 helicopters) and the SA 321J/ L/M transport exported to China, South Africa, and Libya. Israel re-engined eight of its Super Frelons and sold them to Argentina.

Iraq used Super Frelons, equipped with Omera radar and AM39 Exocet missiles, in anti-shipping strikes against Iran.

A commercial ‘air utility’ version, the SA.321J, was in production, eighteen were completed up to the end of September 1967. This can be used as a 27-seat passenger transport, as a freighter with a 2500kg payload, or for firefighting, flying crane or other duties; at least one is acting as a supply transport to offshore oil drilling operations. Certificated on 20 October 1967, the SA.321J is powered by Turmo IIIC5 engines. On 7 April 1967, the prototype SA.321F (F-WMHC) made its first flight. This is an enlarged passenger version with a 19.4m fuselage seating up to 37 occupants, a gross weight of 12,000kg, and large sponson-type fairings amidships which act as baggage holds. The one-off SA.321F commercial transport version, test-flown in 1968, is powered by three 1400shp Turmo IIIC3 shaft turbines. It had an air-conditioned, soundproofed cabin, a sliding door on the starboard side and a rotor head fairing. The two stub wings at the sides of the fuselage were used as baggage holds, and airline-style seating provided for 34-37 passengers.

The SA 321 has six-blade main rotor and five-blade anti-torque tail rotor, with rearward folding of all six main rotor blades of SA 321G accomplished automatically by hydraulic jacks, simultaneously with automatic folding of the tail rotor pylon. The rotor can be stopped within 40 seconds by a boosted disc-type rotor brake fitted to this shaft.

The main rotor blades of all-metal construction, with D-section main spar forming leading-edge. The tail rotor is of similar construction to main rotor. The boat-hull fuselage is of conventional metal semi-monocoque construction, with watertight compartments inside planing bottom. On the SA 321G, there is a small stabilising float attached to the rear landing gear support structure on each side. The tail section of the SA 321G folds for stowage. Small fixed stabilisers on starboard side of tail rotor pylon on all versions. The SA 321F has large external fairings on each side of the centre-fuselage which serve a similar purpose to stabilising floats and also act as baggage containers.

The landing gear is of non-retractable tricycle type, by Messier-Hispano-Bugatti, with twin magnesium alloy wheels on each unit. Hydraulic disc brakes are on the mainwheels and the nosewheel unit is steerable and self-centring. Fuel is in flexible tanks under the floor of the centre-fuselage, with a total standard capacity of 3,975 litres in SA 321G/H and 3,900 litres in SA 321Ja. Optional auxiliary fuel tankage comprises two 500 litre external tanks on all models, two 500 litre internal tanks in the SA 321G, and three 666 litre tanks in the 321H/Ja.

The military version has a crew of two on the flight deck, with dual controls and advanced all-weather equipment. The SA 321G carries three other flight crew, and has provision for 27 passengers. SA 321H transport accommodates 27-30 troops, 5,000kg of internal or external cargo, or 15 stretchers and two medical attendants.

The SA 321F has airliner seats for up to 37 passengers (34 if toilets are installed) in three-abreast rows with centre aisle, while the SA 321Ja has seating for up to 27 passengers in the personnel transport role. As a cargo transport, external loads of up to 5,000kg can be suspended from the cargo sling. Loading of internal cargo (up to 5,000kg) is via rear ramp doors, with the assistance of a Tirefor hand winch.

The ASW SA 321G operates normally in tactical formations of three or four aircraft, each helicopter carrying the full range of detection, tracking and attack equipment, including a self-contained navigation system associated with a Doppler radar, a 360° radar with transponder and display console, and dipping sonar. Four homing torpedoes can be carried in pairs on each side of the main cabin. Both the SA 321G and H can be fitted with an anti-surface vessel weapon system, consisting of two Exocet missiles and launch installation associated with an Omera-Segid Heracles ORB 31D or ORB 32 radar for target designation. Other equipment is provided for secondary duties such as towing and minesweeping. Rescue hoist of 275kg capacity standard.

Argentina received several SA 321 from Israel. Argentine versions were Israeli-owned and refitted with the General Electric GE T58 powerplants. South African versions were noted for not being the full amphibious versions of the Super Frelon type.

The triple-turbine-powered Changhe Z-8  (Zhishengji-8 / Vertical take-off aircraft 8) design work began in 1976, but was suspended from 1979 to mid-1984. Chinese equivalent of Aerospatiale Super Frelon, of which 16 supplied to PLA Navy in 1977-78. The Z-8 features a six-blade main rotor and five-blade tail rotor: boat-hull fuselage with watertight compartments inside planing bottom; stabilising float at rear each side, attached to small stub-wing; small, strut-braced fixed horizontal stabiliser on starboard side of tail rotor pylon. Search radar in nose ‘thimble’ on SAR version.

Pitch control fitting at root of each main rotor blade; drag and flapping hinges for each blade mounted on rotor head starplates; each main blade also has a hydraulic drag damper. Fully redundant flight control system, with Dong Fang KJ-8 autopilot.

Stressed skin metal fuselage, with riveted watertight compartments; gearboxes manufactured by Zhungnaii Transmission Machinery Factory.

A non-retractable tricycle undercarriage, with twin wheels and low-pressure oleo-pneumatic shock-absorber on each unit. Small tripod tailskid under rear of tailboom. Boat hull and side floats permit emergency water landings and take-offs.

Power is from three Changzhou (CLXMW) WZ6 turboshafts, each with maximum emergency rating of 1,156kW and 20% power reserve at S/L, ISA. Two engines side by side in front of main rotor shaft and one aft of shaft. Transmission rated at 3,072kW.

Standard internal fuel capacity 3,900 litres, in flexible tanks under floor of centre-fuselage. Auxiliary fuel tanks can be carried inside cabin for extended-range or self-ferry missions, increasing total capacity to 5,800 litres.

Crew of two or three on flight deck. Accommodation in main cabin for up to 27 fully armed troops, or 39 without equipment; up to 15 stretchers and a medical attendant in ambulance configuration; a BJ-212 Jeep-type vehicle and its crew; or other configurations according to mission. Entire accommodation heated, ventilated, soundproofed and vibration-proofed. Forward-opening crew door on each side of flight deck. Rearward-sliding door at front of cabin on starboard side. Hydraulically actuated rear-loading ramp/door.

First flown on 11 December 1985, a second prototype flew in October 1987. Domestic type approval was awarded on 8 April 1989 and the first Z-8 was handed over to FLA Naval Air Force for service trials on 5 August 1989. Initial production was approved and the final design approval granted on 12 November 1994.

Up to 20 were delivered to PLA Navy by the end of 1999. There was no firm evidence of production status since then, but the type was still being promoted by CATIC in 2002. The sole operating naval unit was Shipborne Helicopter Group within East Sea Fleet at Dachang (Shanghai).

Gallery

Principal versions:

SE.3210 / SA.321 Super Frelon
Larger development of SA.320 with boat hull and outrigger floats, rear loading doors, boom tail, six-blade main rotor driven by three 1320shp Turbomeca Turmo IIIC turboshafts. Prot. F-ZWWE FF 7 Dec. 1962.

SA 321B
Standard French Air Force/Army Super Frelon.

SA 321D
Standard French Navy Super Frelon.

SA 321F
Commercial airliner with streamlined external sponsons, designed to carry 34-37 passengers. The prototype was designed in accordance with US FAR Pt 29 regulations and flew for the first time on 7 April 1967. Type certification was granted by the SGAC on 27 June 1968 and by the FAA on 29 August 1968.

SA 321G
Anti-submarine helicopter able to carry 27 passen¬gers or freight in its alternative transport role. First version to enter production. The first SA 321G flew on 30 November 1965 and deliveries began in early 1966. Twenty-four built.

SA 321H
Simplified military version for air force and army service, without stabilising floats or external fairings on each side of lower fuselage. Turmo IIIE_6 engines instead of Turmo IIIC_6 in other versions. No de-icing equipment fitted.

SA 321Ja
Utility and public transport version, intended to fulfil the main roles of personnel and cargo transport. Designed to carry a maximum of 27 passengers or 11,023 lb/5,000 kg of freight. External loads of up to 5,000kg can be suspended from the cargo sling. The SA 321Ja prototype flew for the first time on 6 July 1967. A French certificate of airworthiness was granted in December 1971.

SA 321K
Israeli assault transport, later re-engined with Gen¬eral Electric T58 turboshafts

SA 321L
Develop¬ment of the SA 321K for other export markets

SA 321M
Libyan version of the SA 321L

Changhe Z-8
Standard Chinese development

Changhe Z-8A
Reported designation of upgraded version, with Turbomeca Makila 2A engines matched to Turmo gearbox. Pratt & Whitney Canada also a candidate for any re-engining programme. Two Z-8As reportedly delivered to PLA Army Aviation for evaluation in 2001, camouflaged; lack nose radome and side-mounted floats.

Changhe Z-8F
Improved and more powerful version, for which the 1,380kW P&WC PT6B-67A turhoshaft was selected in November 2002. Additional 671kW of power expected to enhance ‘hot-and-high’ performance, including increase in service ceiling to 4,700m at MTOW and increased payload capacity. Other improvements said to include new (composites) main rotor blades, with anti-icing; new avionics and mission equipment. Duties envisaged are search and rescue, general utility missions and logistics support.

Specifications

S.E.3200 Frelon
Engines: 3 x Turmo IIIB turboshaft, 750/800shp
Main rotor diameter: 15.0 m
Length, blades folded: 14.9 m
Width, blades folded: 5.2 m
Height: 4.7 m
Weight empty: 4500 kg
Max useful load: 3500 kg
Normal loaded weight: 7500 kg
Max loaded weight: 8000 kg
Max ferrying range: 1300 km

SA 321 Super Frelon
Engine: 3 x Turboméca Turmo III C 6, 1529 shp / 1156kW
Length: 63.648 ft / 19.4 m
Length with rotors: 23.03 m
Height: 21.85 ft / 6.66 m
Width: 5.2 m
Rotor diameter: 62.008 ft / 18.9 m
Max takeoff weight: 27562.5 lb / 12500.0 kg
Weight empty: 14420.7 lb / 6540.0 kg
Max. speed: 130 kt / 240 km/h
Cruising speed: 124 kt / 230 km/h
Service ceiling: 11647 ft / 3550 m
Maximum range: 583 nm / 1080 km
Range (max. weight): 351 nm / 650 km
Rate of climb: 12.0 m/s
Hovering ceiling: 2170 m
Crew: 2
Payload: 30 Pax / 4500kg
Fuel: 3975 kg

SA321G Super Frelon
Engines: 3 x Turbomeca Turmo 111C6 turboshafts, l,570-shp / 1,171-kW
Maximum speed: 154 mph (248 kph) at SL
Initial climb rate: 984 fpm (300 m/min)
Service ceiling: 10,170 ft (3,100 m)
Cruising speed: 248 km/h (154 mph)
Endurance in ASW role: 4 hr
MTOW: 28,660 lb (13,000 kg)
Empty weight: 15,130 lb (6,863 kg)
Height: 22 ft 2 in (6.76 m)
Main rotor diameter: 62 ft (18.9 m)
Main rotor disc area: 3,019.94 sq ft (280.55 sq.m)
Length overall, rotors turning: 75 ft 6.75 in (23.03 m)
Range 3500 kg (7,716 ¬lb) load: 1020 km (633 miles)
Armament: up to four homing anti¬submarine torpedoes or two AS.39 Ex¬ocet anti ship missiles.

SA321H
Engines: 3 x Turbomeca Turmo IIIE-6 turboshaft

Changhe Z-8
Engine: 3 x Changzhou WZ6, 1,156kW
Instant pwr: 1156 kW
Main rotor diameter: 18.90m
Tail rotor diameter: 4.00m
Length overall, rotors turning: 23.035m
Height overall, rotors turning: 6.66m
Width over main gear sponsons: 5.20m
Empty weight equipped: 7550kg
Max take-off weight, standard fuel: 10592kg
Max take-off weight, with auxiliary fuel: 13000kg
Max cargo payload (internal): 4000kg
Max cargo payload (external sling): 5000kg
Never-exceed speed: 315km/h
Max cruising speed: 266km/h
Econ cruising speed: 255km/h
Rate of climb: 690m/min
HIGE: 18,045 ft / 5500m
HOGE: 14,435 ft / 4400m
Service ceiling: 19,685 ft / 6000m
Max range: 880 km
Range max fuel / TOW 9000kg: 430km
Endurance max fuel: 2 h 31 min
Crew: 2
Pax: 27