The Aermacchi MB-339 is a military jet trainer and light attack aircraft designed and manufactured by Italian aviation company Aermacchi.

The MB-339 was developed during the 1970s in response to an Italian Air Force requirement that sought a replacement for the service's existing fleet of Aermacchi MB-326s. Its design was derived from that of the MB-326, rather than a new design, and thus the two aircraft share considerable similarities in terms of their design. Aermacchi had found that the MB-339 was capable of satisfying all of the specified requirements while being the most affordable option available. The maiden flight of the MB-339 took place on 12 August 1976; the first production aircraft were delivered two years later.

Roughly half of all MB-339s entered service with the Italian Air Force, while the remainder have been sold to various export customers. As well as being used for training, the type is also flown by the Frecce Tricolori aerobatic display team. The type has been used in combat by both the Eritrean Air Force during the Eritrean–Ethiopian War of 1998–2000 and the Argentine Naval Aviation during the Falklands War of 1982. In both conflicts, the MB-339 was typically flown as an attack aircraft. In Italian service, the aircraft is intended to be replaced by the newer Aermacchi M-345.

The Aermacchi MB-339 is a military jet trainer and light attack aircraft, featuring a conventional configuration, tricycle undercarriage and all-metal construction. It has many similarities with the design of the MB-326, sharing the majority of its airframe with the older aircraft. According to aviation periodical Air International, the most significant revision of the MB-339 was a redesigned forward fuselage, which raised the instructor's seat to allow visibility over and past the student pilot's head. In typical operations, the aircraft is flown by a crew of two, who are seated in a tandem configuration; during training missions, the student is seated in the forward position while the observing instructor is placed directly behind and somewhat above them. The cockpit is pressurised and is covered by a jettisonable canopy which works in conjunction with the twin Martin-Baker-built ejection seats.

The MB-339 possesses a low, un-swept wing complete with tip tanks; the air intakes for the single turbojet engine is located within the wing roots. This wing is identical to that used on the older MB-326K model. The powerplant used for the aircraft's initial versions was the Rolls-Royce Viper 632-43 turbojet engine, which was capable of producing a maximum thrust of 4,000 lbf (17.8 kN); this is the same model as installed upon the older MB-326K model. Later models, such as the MB-339C, are furnished with the more powerful Viper 680 engine, which can generate up to 4,300 lbf (19.57 kN) of thrust. For improved aerodynamics, the MB-339 features an enlarged tailfin over its predecessor.

While some models of the MB-339 are primarily intended for training operations, other are instead principally equipped to perform light fighter and fighter-bomber roles. Combat-orientated aircraft are typically outfitted with more advanced avionics, such as improved inertial guidance systems, digital nav/attack computers, a MIL-STD-1553B databus, and hands-on throttle-and-stick (HOTAS)-compatible flight controls. Furthermore, various defensive systems, such as a radio jammer, radar warning receiver (RWR), electronic countermeasures (ECM), along with larger wingtip tanks, would typically be adopted. The MB-339K carries a pair of 30mm DEFA cannon while a total of six underwing hard points can accommodate up to 1,815 kilograms (4,000 lb) of external stores.[2] It has been qualified to be armed with various munitions, such as the Sidewinder and R.550 Magic air-to-air missiles, the AGM-65 Maverick air-to-surface missile, various laser-guided bombs and rockets, as well as the Marte Mk.2 anti-ship missile. According to Forecast International, Aermacchi had at one point considered making provisions for the installation of an additional two pod-mounted 30mm cannon.

For deails of operational histoy and numerous variants, click here.

The Aérospatiale Gazelle (company designations SA 340, SA 341 and SA 342) is a French five-seat helicopter, commonly used for light transport, scouting and light attack duties. It is powered by a single Turbomeca Astazou turbine engine and was the first helicopter to feature a fenestron tail instead of a conventional tail rotor. It was designed by Sud Aviation, later Aérospatiale, and manufactured in France and the United Kingdom through a joint production agreement with Westland Aircraft. Further manufacturing under license was performed by SOKO in Yugoslavia. and the Arab British Helicopter Company (ABHCO) in Egypt.

Since being introduced to service in 1973, the Gazelle has been procured and operated by a number of export customers. It has also participated in numerous conflicts around the world, including by Syria during the 1982 Lebanon War, by Rwanda during the Rwandan Civil War in the 1990s, and by numerous participants on both sides of the 1991 Gulf War. In French service, the Gazelle has been supplemented as an attack helicopter by the larger Eurocopter Tiger, but remains in use primarily as a scout helicopter.

Originally developed as a replacement to Aérospatiale's Alouette helicopter, some aspects of the Gazelle such as its purpose and layout were based on the previous model. The Gazelle featured several important innovations. It was the first helicopter with a fenestron or fantail; this is a shrouded multi-blade anti-torque device housed in the vertical surface of the Gazelle's tail, where it replaces a conventional tail rotor.

The fenestron, while requiring a small increase in power at slow speeds, has advantages such as being considerably less vulnerable to damage, safer for people working around the helicopter and with low power requirements at cruising speeds, and has been described as "far more suitable for high-speed flight". The fenestron is likely to have been one of the key advances that allowed the Gazelle to become the world's fastest helicopter in its class.

The main rotor system was originally based upon the rigid rotor technology developed by Messerschmitt-Bölkow-Blohm for the MBB Bo 105; however, due to control problems experienced while at high speeds upon prototype aircraft, the rigid rotor was replaced with a semi-articulated one on production aircraft. The difficulties experienced with the early design of the main rotor was one of the factors contributing to the lengthy development time of the Gazelle. The individual rotor blades were made from composite materials, primarily fiberglass, and had been designed for an extremely long operational lifespan; composite rotor blades would become common on later helicopters. The main rotor maintains a constant speed in normal flight, and is described as having a "wide range of tolerance" for autorotation.

For more details of development, design, operational history and variants, click here.

The Aérospatiale (formerly Sud Aviation) SA 321 Super Frelon ("Super Hornet") is a three-engined heavy transport helicopter produced by aerospace manufacturer Sud Aviation (later Aérospatiale) of France. It held the distinction of being the most powerful helicopter to be built in Europe at one point, as well as being the world's fastest helicopter.

The Super Frelon was a more powerful development of the original SE.3200 Frelon, which had failed to enter production. On 7 December 1962, the first prototype conducted the type's maiden flight. On 23 July 1963, a modified Super Frelon flew a record-breaking flight, setting the new FAI absolute helicopter world speed record with a recorded speed of 217.7 mph (350.4 km/h). Both civilian and military versions of the Super Frelon were produced; the type was predominantly sold to military customers. In 1981, Aerospatiale, Sud Aviation's successor company, chose to terminate production due to a lack of orders.

The Super Frelon was most heavily used by naval air arms, such as the French Navy and the People's Liberation Army Naval Air Force. On 30 April 2010, the type was retired by the French Navy, having been replaced by a pair of Eurocopter EC225 helicopters as a stopgap measure pending the availability of the NHIndustries NH90 helicopter. The Super Frelon was in use for an extended period within China, where it was manufactured under license and sold by the Harbin Aircraft Industry Group as the Harbin Z-8. A modernised derivative of the Z-8, marketed as the Avicopter AC313, performed its first flight on 18 March 2010.

For details of development, design, operational history and variants, click here.

The Aérospatiale SA 330 Puma is a four-bladed, twin-engined medium transport/utility helicopter. The Puma was originally built by Sud Aviation of France, and continued to be made by Aérospatiale. It was also license-built in Romania as the IAR 330; two unlicensed derivatives, the Denel Rooivalk and Atlas Oryx, were made in South Africa. The Puma was a commercial success and was quickly developed into more advanced models such as the AS332 Super Puma and AS532 Cougar, manufactured by Eurocopter since the early 1990s. These descendants of the Puma remain in production in the 21st century.

The Puma has seen combat in a range of theatres by a number of different operators; significant operations include the Gulf War, the South African Border War, the Portuguese Colonial War, the Yugoslav Wars, the Lebanese Civil War, the Iraq War, and the Falklands War. The type also saw popular use in the civilian field and has been operated by a number of civil operators.

The SA 330 Puma is a twin-engine helicopter intended for personnel transport and logistic support duties. As a troop carrier, up to 16 soldiers can be seated on foldable seats; in a casualty evacuation configuration, the cabin can hold six litters and four additional personnel; the Puma can also perform cargo transport duties, using alternatively an external sling or the internal cabin, with a maximum weight of 2500 kg. Civilian Pumas feature a variety of passenger cabin layouts, including those intended for VIP services. In a search and rescue capacity, a hoist is commonly installed, often mounted on the starboard fuselage.

A pair of roof-mounted Turbomeca Turmo turboshaft engines power the Puma's four-blade main rotor. The helicopter's rotors are driven at a speed of roughly 265 rpm via a five reduction stage transmission. The design of the transmission featured several unique and uncommon innovations for the time, such as single-part manufacturing of the rotor shaft and the anti-vibration measures integrated into the main gearbox and main rotor blades. The Puma also featured an automatic blade inspection system, which guarded against and alerted crews to fatigue cracking in the rotor blades. There are two hydraulic systems on board, these operate entirely independent of one another, one system powers only the aircraft's flight controls while the other serves the autopilot, undercarriage, rotor brake, and the flight controls.

In flight, the Puma was designed to be capable of high speeds, exhibit great maneuverability, and have good hot-and-high performance; the engines have an intentionally high level of reserve power to enable a Puma to effectively fly at maximum weight with only one functioning engine and proceed with its mission if circumstances require. The cockpit has conventional dual controls for a pilot and copilot, a third seat is provided in the cockpit for a reserve crew member or commander. The Puma features a SFIM-Newmark Type 127 electro-hydraulic autopilot; the autopilot is capable of roll and pitch stabilization, the load hook operator can also enter corrective adjustments of the helicopter's position from his station through the autopilot.

For development  and operational history details, and the 21 vants, click here.

The AgustaWestland AW101 is a medium-lift helicopter in military and civil use. First flown in 1987, it was developed by a joint venture between Westland Helicopters in the United Kingdom and Agusta in Italy in response to national requirements for a modern naval utility helicopter. Several operators, including the armed forces of Britain, Denmark, and Portugal, use the name Merlin for their AW101 aircraft. It is manufactured at factories in Yeovil, England, and Vergiate, Italy. Licensed assembly work has also taken place in Japan and the United States.

Prior to 2007, the aircraft had been marketed under the designation EH101. The original designation was EHI 01, from the name given to the Anglo-Italian joint venture – European Helicopter Industries – but a transcription error changed this to EH101. In 2000, Westland Helicopters and Agusta merged to form AgustaWestland, leading to the type's current designation.

The AW101 entered into service in 1999 and has since replaced several older helicopter types, such as the Sikorsky SH-3 Sea King, performing roles such as medium-sized transport, anti-submarine warfare, search and rescue, and ship-based utility operations. The Royal Canadian Air Force (RCAF) operates the CH-149 Cormorant variant for air-sea rescue. Another variant, the Lockheed Martin VH-71 Kestrel, was produced to serve in the United States presidential transport fleet before the program was cancelled and the aircraft sold off to Canada for parts. Civil operators use the AW101 for passenger and VIP transportation. The type has been deployed to active combat theatres, such as in support of coalition forces during the Iraq War and the War in Afghanistan.

The AW101 Merlin follows a conventional design layout, but makes use of advanced technologies, such as the design of the rotor blades, avionics systems, and extensive use of composite materials. The fuselage structure is modular and comprises an aluminium–lithium alloy, designed to be both light and damage-resistant. The AW101 is designed for operating in extreme weather conditions; it is fitted with a de-icing system and rated to operate in temperatures ranging between −45 and +50 °C. The aircraft's control systems allow the AW101 to maintain a stable hover in 74 km/h (40 kn) crosswinds.

An active vibration control system, known as the active control of structural response system, reduces airframe vibration by up to 80%, increasing crew comfort and minimising buildup of stress on the airframe. The cockpit is fitted with armoured seats for the crew, and can withstand an impact velocity of over 10 m/s. Dual flight controls are provided, though the AW101 can be flown by a single person. The pilots' instrument displays include six full-colour high-definition screens and an optional mission display; a digital map or forward looking infrared (FLIR) display can also be installed.

For much more information on the development, operational history and 31 variants, click here.

The AgustaWestland AW149 is a medium-lift multi-role military helicopter developed by AgustaWestland, now Leonardo, launched in 2006 and had its first flight in 2009. By 2014 it had received military flight certification, and it went on to enter production going into military service with Egypt and Thailand. It is also planned for Poland with a new PZL-Swidnik production line there that opened in 2024, and North Macedonia has a pending order. The aircraft the only contender for the British NMH procurement program in the 2020s.

The AW149 began life as an all-new, military design. [1] It was unveiled at the 2006 Farnborough Air Show, with a larger fuselage and more powerful engines compared to the AW139, resulting in a greater cargo volume and payload carrying ability. On 13 November 2009, the first prototype conducted its first flight from AgustaWestland's Vergiate manufacturing facility in northern Italy. On 26 February 2011, the second prototype, the first with production model engines, made its first flight from Vergiate.

On 20 June 2011 AgustaWestland announced the AW189, a civilian development of the AW149, for service in 2013.

For operational history and operators, click here.

The AIDC F-CK-1 Ching-Kuo (Chinese: 經國號戰機; pinyin: Jīngguó Hào Zhànjī), commonly known as the Indigenous Defense Fighter (IDF), is a multirole combat aircraft named after Chiang Ching-kuo, the late President of the Republic of China. The aircraft made its first flight in 1989. It entered service with Republic of China Air Force (Taiwan) in 1992. All 130 production aircraft were manufactured by 1999.

Taiwan initiated the IDF program when the United States refused to sell them F-20 Tigershark and F-16 Fighting Falcon jet fighters following diplomatic pressure from China. Taiwan therefore decided to develop an advanced indigenous jet fighter. The Aerospace Industrial Development Corporation (AIDC), based in Taichung, Taiwan, designed and built the IDF jet fighter.

Number built    137 (6 Prototypes and 131 serials)

For extensive details of the background, design process, and variants, click here.

The A330 MRTT has a maximum fuel capacity of 111,000 kg (245,000 lb) without the use of additional fuel tanks, which leaves space for the carriage of 45,000 kg (99,000 lb) of additional cargo. The A330 MRTT's wing has common structure with the four-engine A340-200/-300 with reinforced mounting locations and provision for fuel piping for the A340's outboard engines. The A330 MRTT's wing therefore requires little modification for use of these hardpoints for the wing refuelling pods.

The A330 MRTT cabin can be modified to carry up to 380 passengers in a single class configuration, allowing a complete range of configurations from maximised troop transport to complex customisation suitable for VIP and guest missions. Available configurations include 300 passengers in a single class and 266 passengers in two classes. The A330 MRTT can also be configured to perform Medical Evacuation (Medevac) missions; up to 130 standard stretchers can be carried. The main deck cargo configuration allows carriage of standard commercial containers and pallets, military, ISO and NATO pallets (including seats) and containers, and military equipment and other large items which are loaded through a cargo door. Like the A330-200, the A330 MRTT includes two lower deck cargo compartments (forward and aft) and a bulk area capability. The cargo hold has been modified to be able to transport up to 8 military pallets in addition to civilian Unit Load Device (ULD).

RAAF MRTT

The KC-30A MRTT is fitted with two forms of air-to-air refuelling systems: an Advanced Refuelling Boom System mounted on the tail of the aircraft; and a pair of all-electric refuelling pods under each wing.

These systems are controlled by an Air Refuelling Operator in the cockpit, who can view refuelling on 2D and 3D screens.

The KC-30A can carry a fuel load of more than 100 tonnes, and transfer part of that load to compatible aircraft, including:

• F/A-18A/B Hornets;
  
• F/A-18F Super Hornets;
  
• E/A-18G Growlers;
  
• E-7A Wedgetails;
  
• C-17A Globemaster III; and
  
• Other KC-30As.
  

It is also compatible with refuelling P-8A Poseidon surveillance aircraft, F-35A Lightning II, and foreign aircraft such as the F-16C Fighting Falcon and B-1B Lancer.

The KC-30A MRTT can remain 1800 km from its home base, with 50 tonnes of fuel available to offload for up to four hours.

For more information, click here and here.

It was designed by Airbus Military (now Airbus Defence and Space) as a tactical airlifter with strategic capabilities to replace older transport aircraft, such as the Transall C-160 and the Lockheed C-130 Hercules. The A400M is positioned, in terms of size, between the C-130 and the C-17; it can carry heavier loads than the C-130 and is able to use rough landing strips. Along with the transport role, the A400M can perform aerial refuelling and medical evacuation when fitted with appropriate equipment.

The A400M's maiden flight, originally planned for 2008, took place on 11 December 2009 from Seville, Spain. Between 2009 and 2010, the A400M faced cancellation as a result of development programme delays and cost overruns; however, the customer nations chose to maintain their support for the project. A total of 174 A400M aircraft had been ordered by eight nations by July 2011. In March 2013, the A400M received European Aviation Safety Agency (EASA) certification. The first aircraft was delivered to the French Air Force in August 2013.

For a great deal more information on the A400M Atlas, click here.

MRH90 Taipan is the Australian designation for the NH Industries (Airbus Helicopters) NH90.

The MRH90 is in the 10-tonne helicopter class and is capable of carrying two pilots, two loadmasters and 18 combat troops up to 900km at speeds of up to 300km/h. Being a true multi-role machine, the MRH90 can undertake troop transport, search and rescue, special operations and counter-terrorism missions.

The helicopter is a single main rotor helicopter of the 10-tonne class, powered by two engines. The engines installed on the MRH90 are the RTM 322-01/9 supplied by Rolls Royce / Turbomeca. The helicopter has a full composite, crashworthy fuselage with a constant cross-section centre fuselage and significant crashworthy capabilities (based on MIL-STD-1290A) giving protection up to 10m/s (landing gear extended) and 7m/s (landing gear retracted) up to 11-tonnes helicopter weight. The forward fuselage contains the cockpit with two crashworthy seats for pilot and co-pilot and a foldable crashworthy jump seat for an additional crew member.

The centre fuselage offers a spacious, unobstructed cabin with a sliding door on each side and a rear ramp. The cabin allows the installation of 20 crashworthy troop seats or, alternatively, up to 12 stretchers. The flight control system (FCS) of the MRH90 is based on a redundant fly-by-wire (FBW) system with no mechanical back-up. It provides the MRH90 with enhanced manoeuvrability and keeps the crew workload acceptable at any time during the mission.

The Commonwealth of Australia ordered 46 MRH90s from Airbus in Australia Pacific .

For more details of the development, models and other user nations, click here.

The Aermacchi M-346 Master is a family of military twin-engine transonic advanced jet trainers and light combat aircraft. Originally co-developed with Yakovlev as the Yak/AEM-130, the partnership was dissolved in 2000 and then Alenia Aermacchi proceeded to separately develop the M-346 Master, while Yakolev continued work on the Yakovlev Yak-130. The first flight of the M-346 was performed in 2004. The type is currently operated by the air forces of Italy, Israel, Singapore, Greece, Turkmenistan and Poland. Since 2016 the manufacturer became Leonardo-Finmeccanica as Alenia Aermacchi merged into the new Finmeccanica, finally rebranded as Leonardo in 2017.

The M-346 is designed for the main role of lead-in fighter trainer, in which aircraft's performance and capabilities are used to deliver pilot training for the latest generation of combat fighter aircraft. Powered by a pair of Honeywell F124 turbofan dry engines, designed to reduce acquisition and operating costs, it is capable of transonic flight without using an afterburner; Alenia Aermacchi has claimed that the M-346's flight performance to be "second only to afterburner-equipped aircraft". During the design process, the twin concepts of "design-to-cost" and "design-to-maintain" were adhered to, reducing acquisition and operational costs; the per flying hour costs of the M346 are reportedly one-tenth of those of the Eurofighter Typhoon. Outside of the training role, the M-346 was designed from the onset to accommodate additional operational capabilities, including combat missions such as close air support and air policing duties.

The combat capable M-346FA can perform ground attack, homeland defence and air policing missions and reconnaissance. Various munitions and stores can be carried, including IRIS-T or AIM-9 Sidewinder air-to-air missiles, various air-to-surface missiles, anti-ship missiles, free-fall and laser-guided bombs and rockets, a 12.7 mm gun pod, reconnaissance and targeting pods, and electronic warfare pods; weapon aiming is performed using the Helmet Mounted Display and the multifunction displays. All main systems are duplicated, and the flight system reconfigurable, to increase survivability and functionality in the event of battle damage being sustained.[28] The aircraft has a maximum range of 1,375 nautical miles when outfitted with a maximum of three external fuel tanks, this can be extended via in-flight refuelling via a removable refuelling probe.

For more details of the design and operational history of the M-346, click here.

Variants

M-346
Designation for the basic type.
T-346A
Italian military designation from 2012 for the M-346.
M-346LCA (Light Combat Aircraft)
Armed variant offered to Poland as a replacement for aging Su-22. Designation no longer in use.
M-346FT (Fighter Trainer)
Multirole variant capable of switching between training and combat operations. New features include a new tactical datalink system and different armament capability, but do not include physical changes to the hardware.
M-346FA (Fighter Attack)
Multirole variant capable of air-to-air and air-to-surface combat with a 3 tonne payload spread over 7 hardpoints, advanced Grifo-M346 radar radar, countermeasures and stealth features including engine intake grids and radar-absorbing coatings on the canopy and wing leading edge. It is being marketed as a light attack aircraft also suitable for aggressor and companion training purposes. The aircraft was revealed on June 18, 2017, in a static display at that year's Paris Air Show. The aircraft is being marketed for export to South American and East Asian countries, and is claimed to be able to carry out operational missions at far lower costs than those of front-line fighters.

T-100
Designation used for the United States Air Force's T-X program.

It is an advanced derivative of Alenia Aeronautica's earlier G.222 (C-27A Spartan in U.S. service), equipped with the engines and various other systems also used on the larger Lockheed Martin C-130J Super Hercules. In addition to the standard transport configuration, specialized variants of the C-27J have been developed for maritime patrol, search and rescue, C3 ISR (command, control, communications, intelligence, surveillance and reconnaissance), fire support and electronic warfare and ground-attack missions.

The C-27J has been ordered by the military air units of Australia, Bulgaria, Chad, Italy, Greece, Kenya, Lithuania, Mexico, Morocco, Peru, Romania, Slovakia, and Zambia (on order).

In 1995, Alenia and Lockheed Martin began discussions to improve Alenia's G.222 using C-130J's glass cockpit and a more powerful version of the G.222's T64G engine and four-blade propellers. In 1996, a program began on an improved G.222, named C-27J; it used a U.S. military type designation based on the G.222's C-27A designation. In 1997, Alenia and Lockheed Martin formed Lockheed Martin Alenia Tactical Transport Systems (LMATTS) to develop the C-27J. The design changed to use the C-130J Super Hercules's Rolls-Royce AE 2100 engine and six-blade propeller. Other changes include a fully digital MIL-STD-1553 systems and avionics architecture, and an updated cargo compartment for increased commonality. The C-27J has a 35% increase in range and a 15% faster cruise speed than the G.222.

In December 2011, the Royal Australian Air Force (RAAF) issued a Foreign Military Sales request for 10 C-27Js valued at US$950m to replace its retired DHC-4 Caribou fleet. Australia had opted for the C-27J over the rival EADS CASA C-295 following an RAAF evaluation, which had noted the C-27J's wider and taller cabin being compatible with the Australian Army's general purpose G-Wagon vehicle, and palletized goods. In December 2013, the first Australian C-27J performed its maiden flight. In December 2014, the RAAF began maintenance training on the type; delivery of the first two of the ten C-27Js on order was also formally accepted that month.

For more details about the Spartan, click here.

he AMX International AMX is a ground-attack aircraft jointly developed by Brazil and Italy. The AMX is designated A-11 Ghibli by the Italian Air Force and A-1 by the Brazilian Air Force. The Italian name, "Ghibli", is taken from the hot dry wind of the Libyan desert.

During the early 1970s, Italian manufacturer Aermacchi conducted a design study on a prospective light ground attack aircraft, which was given the designation of MB-340. During early 1977, the Italian Air Force issued a requirement for 187 new-build strike fighters, which were to replace its existing Aeritalia G.91 in the close air support. During 1980, the Brazilian government announced that they intended to participate in the program in order to provide a replacement for the Aermacchi MB-326. As a result of a memorandum between Italy and Brazil for the type's joint development in 1981, AMX International, an Italian-Brazilian joint venture, was formed to develop, manufacture, and market the aircraft.

The AMX is a conventional shoulder-winged monoplane. It is composed primarily of aluminium and manufactured using traditional construction methods, however elements such as the tail fin and elevators use carbon fibre composite materials. For its size, a large proportion of the AMX's internal space is allocated to avionics and onboard computer systems, both the navigation and attack systems are computerized. For accessability and ease of maintenance, all avionics are installed directly in bays beneath the cockpit in a manner in which they can be worked upon at ground level without the use of support platforms.

Drawing on experience from the Panavia Tornado, the AMX is equipped with a hybrid flight control system; a fly-by-wire control system is employed to operate flight control surfaces such as the spoilers, rudder and variable incidence tailplane, while the ailerons and elevators are actuated via a dual-redundant hydraulic system. Manual reversion is provided for the ailerons, elevator and rudder to allow the aircraft to be flown even in the event of complete hydraulic failure; either control system can act independent of one another. The wing is fitted with both leading edge slats and trailing edge flaps and overwing spoilers ahead of the flaps. The spoilers can function as airbrakes and to negate lift; improving take-off and landing performance as well as manoeuvrability during flight.

A single Rolls-Royce Spey turbofan engine serves as the AMX's powerplant. During the aircraft's development, the Spey was heavier and less modern than some of the available alternatives, but it was considered to be reliable, relatively cheap and was free of export restrictions that would be imposed by using American engines. The Spey engine also enabled for the use of a simplified round-lipped inlet design. The rear fuselage is detachable in order to gain access to the engine. Separate consortia in both Brazil and Italy manufactured the Spey for the AMX. Unusual for a strike aircraft of the era, no attempt was made to develop the aircraft to fly at supersonic speeds.

For more details of development, design, operational history, variants and operators, click here.

The Antonov An-178 (Ukrainian: Антонов Ан-178) is a short-range medium-airlift military transport aircraft designed by the Ukrainian Antonov company and based on the Antonov An-158 (An-148-200). It was announced on 5 February 2010, rolled out on 16 April 2015 and the maiden flight was on 7 May 2015.

The An-178 is proposed to replace outdated aircraft like the An-12, An-26 and An-32. The aircraft will have an avionics suite similar to the An-148, and will use Progress D-436-148FM engines.

The An-178 is a potential competitor for the Embraer KC-390 from Brazil. The company plans to build more than 200 of the aircraft.

An-178 is a high-wing transport aircraft with moderately swept wing, winglets and a T-tail. The airframe is made of aluminium alloys and composite materials. The fuselage is semi-monocoque with a circular cross-section. The retractable landing gear consists of two main wheel bogies and a dual nose wheel. The flight control system is dual duplex fly-by-wire system, consisting of two parts: FCS-A and FCS-B, each of which is responsible for two control channels. The flight control surfaces include ailerons near the wing tips, four control spoilers, six lift-dump/speed-brake spoilers, rudder and elevators, with an emergency mechanical cable back-up system. The powerplant consists of two Progress D-436-148FM turbofan engines, mounted on pylons under the wings and an auxiliary power unit.[citation needed] It can shift 18 tonnes over 1,000 km, or 10 tonnes over 4,000 km.

The aircraft was derived from the 99-seat An-158 regional airliner and was fitted with the commonized F1 fuselage nose section with the identical flight deck, wing panels, empennage and most of the onboard systems.[9] The fuselage however was newly created with an enlarged diameter that had grown from 3.35 m to 3.9 m, which has resulted in an enlarged cargo hold - the cargo cabin cross section increased to 2.75 m by 2.75 m.[9] Aside from the wing structure, outer panels (including winglets), front fuselage nose, cockpit and nose landing gear which come from the An-158, there is an extra pair of tandem main-wheels on each side.[10] The aircraft made its Western debut at the 2015 Paris Air Show.

There are reports that future production-standard aircraft will have a longer wingspan while retaining the organic wing panels of the An-158. Its maximal takeoff weight would increase to an estimated 56 tons. Later production variants would need turbofan engines with a thrust of about 9,500 kgf to have the characteristics required. The planned engine may be the new-generation in-development Ivchenko-Progress AI-28 turbofan. The decision was made to fit the An-178 prototype with less powerful D-436-148FM engines in the interim. The D-436-148FM is a derivative of the production-standard D-436-148 with an upgraded fan, which boosted the takeoff thrust to 7,800 kgf and at emergency power rating to 8,580 kgf.

Powered by four turboprop engines each driving a pair of contra-rotating propellers, the design was the first wide-body transport aircraft and remains the world's largest turboprop-powered aircraft to date. The An-22 first appeared publicly outside the Soviet Union at the 1965 Paris Air Show. Thereafter, the model saw extensive use in major military and humanitarian airlifts for the Soviet Union, and is still in service with the Russian Air Force.

In the late 1950s, the Soviet Union required a large military transport aircraft to supplement the Antonov An-8 and An-12s then entering service. Originally known as the An-20, the model is a conventional multi-engined high-wing design. In the early 1960s, the Antonov bureau produced a wooden mock up at its Kyiv, Ukraine, workshops of what was designated the Model 100. The prototype, now designated the An-22, was rolled out on 18 August 1964 and first flew on 27 February 1965. The prototype was given the name Antaeus (sometimes misspelled Antheus) and, after four-months of test flying, was displayed at the 1965 Paris Air Show. All aircraft were built at the Tashkent State Aircraft Factory and the first military delivery was made to the Air Transport Wing at Ivanovo Airbase in 1969.

The aircraft was designed as a strategic airlifter, designed specifically to expand the Soviet Airborne Troops' capability to land with their then-new BMD-1 armoured vehicles. The An-22 cargo hold can accommodate four BMD-1s compared to only one in the An-12.

It has the capability to takeoff from austere, unpaved, and short airstrips, allowing airborne troops to perform air-landing operations. This is achieved by four pairs of contra-rotating propellers, similar to those on the Tupolev Tu-114. The propellers and exhaust from the engines produce a slipstream over the wings and large double-slotted flaps. The landing gear is ruggedized for rough airstrips. In early versions tire pressures could be adjusted in flight for optimum landing performance. That feature was removed in later models. A total of 69 units were built.

For more information on the development, operational history and variants, click here.

The Antonov An-26 (NATO reporting name: Curl) is a twin-engined turboprop civilian and military transport aircraft, designed and produced in the Soviet Union from 1969 to 1986.

While the An-24T tactical transport had proved successful in supporting Soviet troops in austere locations, its ventral loading hatch restricted the handling of cargo, and in particular vehicles, and made it less effective than hoped in parachuting men and supplies. As a result, interest in a version with a retractable cargo ramp increased, and the Antonov design bureau decided in 1966 to begin development on the new An-26 derivative, in advance of an official order. The cargo ramp was based on that designed and allowed the cargo deck to be sealed and pressurised in flight. When loading cargo, it could either be lowered to allow vehicles to be driven in, or slid beneath the aircraft's fuselage, so that cargo could be loaded straight in off a truck bed. In March 1968, the OKB received official permission to begin development.[4] Particular attention was given to the military mission, and the majority of early An-26 production was delivered to the VTA (voyenno-transportnaya aviatsiya).

Using the majority of the An-24 airframe, with its high-set cantilevered wings, twin turboprops and stalky main undercarriage, the An-26 included military equipment, such as tip-up paratroop canvas seats, an overhead traveling hoist, bulged observation windows and parachute static line attachment cables. The An-26 made its public debut at the 27th Paris Air Show at Le Bourget where the second prototype, CCCP-26184 (c/n00202), was shown in the static aircraft park.

The An-26 is also manufactured without a license agreement in China by the Xian Aircraft factory as the Y-14, later changed to be included in the Xian Y7 series.

For operational history and details of the 40 variants (including non-Russian), click here.

The photo above and third photo below are An-26's operated by the Ukranian Air Force.

The Antonov An-70 (Ukrainian: Антонов Ан-70) is a four-engine medium-range transport aircraft, and the first aircraft to take flight powered only by propfan engines. It was developed in the late 1980s by the Antonov Design Bureau to replace the obsolete An-12 military transport aircraft. The maiden flight of the first prototype took place in December 1994 in Kyiv, now independent Ukraine. Within months the prototype had suffered a mid-air collision. A second airframe was produced to allow the flight-test programme to proceed. Both prototypes were produced by the Kyiv Aircraft Production Plant.

Following the dissolution of the Soviet Union in the early 1990s, the programme became a joint development between Russia and Ukraine. The former compounded the issue of a reduced market with its intermittent commitment to the project. Repeated attempts to start production have had limited success. Western European countries, including Germany, at one stage assessed the aircraft for procurement, but many later decided against it.

The An-70 is a monoplane with a high-mounted wing design that features four distinctive propfan engines. Designed by the Progress Design Bureau, each of the D-27 engines is rated at 13,800 shp (which can be uprated to 16,000 shp), which is used to drive the SV-27 contra-rotating scimitar propellers designed by Aerosila; eight on the front propeller and six on the aft propeller. The propfan engines deliver slipstream to the supercritical wings that feature double-slotted trailing edges to provide high lift coefficients at low speeds.  The modernisation of the aircraft during 2010–12 saw upgrades to the engines, including the incorporation of FADEC, and the further separation of the two propellers.  The aircraft's cruise speed is 750 km/h (405 kt) at an operational altitude of 8,600 to 9,600 m (28,200 to 31,500 ft); Antonov claimed in 1997 that the aircraft had a design maximum speed of 850 km/h (460 kt, or Mach 0.8), which would have compared favourably with Mach 0.77 of the larger turbofan-powered C-17.  According to DASA's evaluation, the propfan engines were 10 percent more efficient than conventional turboprops.

Similar to many aircraft designs of the Soviet Union, the An-70 was designed as an airlifter that could operate from unprepared fields. In short take-off and landing (STOL) configuration, the aircraft could lift off from a 600 m (2,000 ft) dirt strip with 25 tonnes (55,000 lb) of cargo and fly for 3,000 km (1,900 mi). Alternatively, it could fly the same distance with 35 t (77,000 lb) of cargo if it took off from a 1,800 m (5,900 ft) paved runway. For a payload-heavy mission, the An-70 can haul 47 t (104,000 lb) of cargo for a range of 1,500 km (930 mi), but if range was essential, the aircraft can carry a load of 17 t (37,000 lb) over 8,000 km (5,000 mi). In exceptional circumstances, the An-70 subjected to lower-g take-offs, can airlift a 47-tonne (104,000 lb) T-80U main battle tank and fly it for 3,000 km (1,900 mi).  The fully pressurised internal cabin measures 4 m (13 ft) wide and 4.1 m (13 ft) high, and has a length of 18.6 m (61 ft) from the front to the ramp; with the ramp included, the total cabin length is 22.4 m (73 ft).  In comparison, the turbofan-powered Il-76 has a lower cross-sectional cargo area, but exceeds the An-70 in payload capability and ramp length.  The An-70's cargo hold is serviced by four electrical hoists that facilitate autonomous cargo loading. A central floor can be rapidly installed for the accommodation of 300 soldiers or 200 injured personnel over two decks.

For more details of the development, design and variants, click here.

The Atlas Cheetah is a South African fighter aircraft designed and produced by the aviation company Atlas Aircraft Corporation (later Denel Aeronautics). It was developed at the behest of, and principally operated by, the South African Air Force (SAAF).

The Cheetah was developed amid the Border War of the 1980s as a major upgrade of the French-built Dassault Mirage III fleet operated by the SAAF. The programme integrated technology from the Israeli-built IAI Kfir, which had been derived from the Mirage 5/IAI Nesher. The upgrade programme, which was known as Project Cushion, produced three variants; the two-seat Cheetah D, the single-seat Cheetah E, and the single-seat Cheetah C. All three models were inducted into the SAAF, functioning for a time as the service's most capable fighter and strike aircraft. A single Cheetah R, intended for aerial reconnaissance, was built as a prototype, but this variant never entered service.

During 1992, the Cheetah E model was withdrawn from SAAF service; both the Cheetah Cs and Cheetah Ds were retired during April 2008, having been being replaced by the Swedish-built Saab Gripen. Since its retirement by the SAAF, a limited number have still operated in South Africa as flight test aircraft. Some have been exported, such as to the Ecuadorian Air Force (EAF) as a source of spare parts. The privately owned company Draken International intends to use the Cheetah as an adversarial aircraft for combat training services in the United States.

Variants

Cheetah C  (Specifications below)

The Cheetah C was the final development in the Cheetah series and was the only fighter aircraft in service with the SAAF until replaced by the Swedish-built Saab JAS 39 Gripen during 2008. In addition to the upgrades described above, the Cheetah C incorporated more sophisticated avionics and navigation suite and an improved pulse-doppler multi-mode radar (ELTA). The aircraft was also fitted with a data link and updated versions of the helmet-mounted sight, HUD and improved HOTAS controls.

Other improvements included the fitting of a single-piece wrap-around windshield in place of the previous three-piece version, a revised in-flight refuelling probe with less external piping, new undercarriage and suspension, the deletion of the wing fences, an Atar 9K50 engine and a new nose to incorporate the more sophisticated electronics and radar.

Like the Cheetah D, the Cheetah C was capable of delivering precision-guided munitions (PGMs), ranging from laser-guided bombs (LGBs), to GPS-guided weapons and TV-guided bombs. It also had the capability of using stand-off air-to-ground weapons such as the MUPSOW and TORGOS. In addition, it was able to carry a wide range of air-to-air weapons including the V4 R-Darter radar-guided missile and the A-Darter infrared (IR)-guided missile.

Cheetah D

The Cheetah D was the sole two-seater variant, and was predominantly used as a trainer for pilots converting to the Cheetah C. It also had a secondary attack capability, including the ability to deliver PGMs. Under Project Recipient, 10 Cheetah Ds were re-engined with the Atar 09K50C-11, replacing their original Atar 09C engines. After the engine modification, the remaining aircraft received an avionics upgrade to bring them to the same standard as the Cheetah C. The original three piece front windshield was also replaced with a one-piece wraparound version.

Cheetah D No.845 was based at the Test Flight and Development Centre (TFDC) as a systems testing aircraft and used in the development of the Denel Dynamics MUPSOW stand-off weapon. Denel used two Cheetah Ds for testing (844 and 847). The former was Denel's standard systems testing aircraft, while the latter was used in the evaluation of the SMR-95 engine, a development of the Soviet-built Klimov RD-33. The performance increase offered by the Russian engine was impressive, but a combination of budget cuts and problems with the aircraft's centre of gravity contributed to the program's termination.

Cheetah E

The single-seater Cheetah E was developed as an interim fighter for use in the period before the Cheetah Cs became operational. It was fitted with a comparatively simple avionics suite and radar and retained the Atar 9C-3 engine. Its typical mission was as a standby interceptor, whereby a minimum of two aircraft armed with two V3B (later V3C) missiles, would be on permanent alert status in case of an attack from the north.

All aircraft were placed into storage with the final example (No.842) painted in a non-standard camouflage scheme and used for systems testing. No.842 is currently with the SAAF Museum, and is stored at AFB Swartkop. In 2003, Chile purchased five of the mothballed aircraft (Numbers 819, 820, 827, 832 and 833) and indicated its desire to purchase seven more aircraft (numbers 822, 823, 825, 828, 829, 831 and 834) subject to the agreement of a suitable purchase price. The Chilean Air Force (FACh) used the Cheetah E airframes as a source of spares for its similar ENAER Pantera aircraft until these planes were retired in late 2006.

Cheetah R

The Cheetah R was a feasibility study into an extension of the Cheetah upgrade programme to include a specialist reconnaissance model. An Atar 9K50-engined Mirage IIIR2Z, (855), was chosen as the airframe for the upgrade. In addition to the airframe refurbishment, 855 received a new nose design and the same radar as used in the Cheetah E, the twin DEFA 30mm cannons were removed and it was the only Cheetah type to not receive an in-flight refuelling probe. The SAAF decided not to proceed with the Cheetah R programme and 855 was assigned to the Atlas Advanced Combat Wing (ACW) where it was used as a testing and development aircraft. It was decided that rather than developing a dedicated reconnaissance airframe, that the Vinten Vicon 18 Series 610 reconnaissance pod would be used on the Cheetah C variant to provide reconnaissance capabilities

It was operated by the Royal Air Force (RAF) from 1956 until 1984. Aircraft manufacturer A.V. Roe and Company (Avro) designed the Vulcan in response to Specification B.35/46. Of the three V bombers produced, the Vulcan was considered the most technically advanced and hence the riskiest option. Several reduced-scale aircraft, designated Avro 707, were produced to test and refine the delta wing design principles.

The Vulcan B.1 was first delivered to the RAF in 1956; deliveries of the improved Vulcan B.2 started in 1960. The B.2 featured more powerful engines, a larger wing, an improved electrical system, electronic countermeasures (ECM) and many were modified to accept the Blue Steel missile. As a part of the V-force, the Vulcan was the backbone of the United Kingdom's airborne nuclear deterrent during much of the Cold War. Although the Vulcan was typically armed with nuclear weapons, it was capable of conventional bombing missions, a capability which was used in Operation Black Buck during the Falklands War between the United Kingdom and Argentina in 1982.

The Vulcan had no defensive weaponry, initially relying upon high-speed high-altitude flight to evade interception. Electronic countermeasures were employed by the B.1 (designated B.1A) and B.2 from circa 1960. A change to low-level tactics was made in the mid-1960s. In the mid-1970s nine Vulcans were adapted for maritime radar reconnaissance operations, redesignated as B.2 (MRR). In the final years of service six Vulcans were converted to the K.2 tanker configuration for aerial refuelling.

After retirement by the RAF, one example, B.2 XH558, named The Spirit of Great Britain, was restored for use in display flights and air shows, whilst two other B.2s, XL426 and XM655, have been kept in taxiable condition for ground runs and demonstrations. B.2 XH558 flew for the last time in October 2015, before also being kept in taxiable condition.

A total of 134 production Vulcans were assembled at Woodford Aerodrome, 45 to the B.1 design and 89 were B.2 models, the last being delivered to the RAF in January 1965.

For details of the development, design, operational history and variants, click here.

The Hawk was first flown at Dunsfold, Surrey, in 1974 as the Hawker Siddeley Hawk, and subsequently produced by its successor companies, British Aerospace and BAE Systems, respectively. It has been used in a training capacity and as a low-cost combat aircraft.

Operators of the Hawk include the Royal Air Force (notably the Red Arrows display team) and a considerable number of foreign military operators. The Hawk is still in production in the UK and under licence in India by Hindustan Aeronautics Limited (HAL) with over 900 Hawks sold to 18 operators around the world.

The Royal Australian Air Force ordered 33 Hawk 127 Lead-in Fighters (LIFs) in June 1997, 12 of which were produced in the UK and 21 in Australia. The Hawk 127 lead-in fighter prepares qualified RAAF pilots for conversion to F/A-18A and F/A-18B Hornets and F/A-18F Super Hornets.

For history and development of the Hawk, click here.

For details of the Hawk 127 in Australian service, click here.

The Beechcraft T-6 Texan II is a single-engine turboprop aircraft built by the Raytheon Aircraft Company (Textron Aviation since 2014). A trainer aircraft based on the Pilatus PC-9, the T-6 has replaced the United States Air Force's Cessna T-37B Tweet and the United States Navy's T-34C Turbo Mentor.

The T-6A is used by the United States Air Force for basic pilot training and Combat Systems Officer (CSO) training, the United States Navy and United States Marine Corps for primary Naval Aviator training and primary and intermediate Naval Flight Officer (NFO) training, and by the Royal Canadian Air Force (CT-156 Harvard II designation), Greek Air Force, Israeli Air Force (with the "Efroni" nickname), and Iraqi Air Force for basic flight training. The T-6B is the primary trainer for U.S. student naval aviators (SNAs). The T-6C is used for training by the Mexican Air Force, Royal Air Force, Royal Moroccan Air Force, and the Royal New Zealand Air Force.

The Model 3000/T-6 is a low-wing cantilever monoplane with enclosed tandem seating for two. It is powered by single Pratt & Whitney Canada PT6A-68 turboprop engine in tractor configuration with an aluminum, 97-inch (8.1 ft; 2.5 m), four-blade, constant-speed, variable pitch, non-reversing, feathering propeller assembly and has retractable tricycle landing gear. The aircraft is fitted with Martin-Baker Mark 16 ejection seats and a canopy fracturing system.

The T-6 is a development of the Pilatus PC-9, modified by Beechcraft to enter the Joint Primary Aircraft Training System (JPATS) competition in the 1990s.[1] A similar arrangement between Pilatus and British Aerospace had also been in place for a Royal Air Force competition in the 1980s, although that competition selected the Short Tucano. The aircraft was designated under the 1962 United States Tri-Service aircraft designation system and named for the decades-earlier T-6 Texan.

The JPATS competition-winning design was based on a commercial off-the-shelf Pilatus PC-9, with minor modifications. Additional requirements and conflicts between the Air Force and the Navy resulted in delays, cost increases (from initial estimates of $3.9 to roughly $6 million per aircraft) and an aircraft that is 22% or 1,100 pounds (500 kg) heavier than the Pilatus.

On 9 April 2007, the U.S. Department of Defense released their Selected Acquisition Reports, which reported that the T-6 JPATS program was one of only eight programs cited for Congressional notification for 25–50% cost overrun over initial estimates, which is referred to as a "Nunn-McCurdy Breach" after the Nunn-McCurdy Amendment. It is unusual for a program so far into full-rate production to experience significant enough cost overruns to trigger this congressional notification.

For operational history and 9 variants, click here.

The Bell HSL (Model 61) was an American 1950s anti-submarine warfare (ASW) helicopter built by Bell Helicopter for the US Navy. The prototype first flew in 1953, but the type became obsolete during development and was found unsatisfactory upon entering service in 1957, resulting in the cancellation of the production contract; many of the 50 production aircraft were delivered directly into storage. The last HSL was retired in 1960. It was the only tandem rotor type designed by Bell.

The prototype Bell Model 61 first flew on 3 March 1953; it had been designed to meet a United States Navy requirement for an anti-submarine warfare helicopter. In June 1950, the Model 61 was announced as the winner of the competition, and three XHSL-1 evaluation aircraft were ordered. The Model 61 had a rectangular-section fuselage structure and four-leg, six-wheel landing gear.[citation needed] It was powered by a Pratt & Whitney R-2800 radial engine mounted in the aft fuselage. Crew included two pilots and two sonar operators. The main rotors were at either end of the fuselage tube, linked by a transmission. The front rotor shaft was slightly ahead of pilots in the front cockpit.

Because of the urgency of the requirement, low-rate production was ordered almost immediately after Bell received a contract for three XHSL-1s. The Navy eventually contracted for at least 160 production aircraft, including 18 intended for the British Royal Navy. Bureau Numbers were assigned for a total of 234. Because of development problems that resulted in poor schedule performance to the contract, only 50 were built. Although all were delivered, after service test and acceptance only a handful were used, for the development of airborne mine sweeping. The rest were delivered directly into storage and were subsequently struck off.

Variants

XHSL-1
two experimental flight test and one static test article
HSL-1
production version, 50 built.
Bell Model 61
Company designation for the HSL
Bell D-116
A proposed civil variant of the Model 61, not proceeded with.
Bell D-216
A proposed variant of the HSL, not proceeded with.
Bell D-238
A proposed variant of the HSL, not proceeded with.

The Bell P-59 Airacomet was a single-seat, twin jet-engine fighter aircraft that was designed and built by Bell Aircraft during World War II, the first produced in the United States. As the British were further along in jet engine development, they donated an engine for the United States to copy in 1941 that became the basis for the General Electric jet used by the P-59 a year later. Because the plane was underpowered, the United States Army Air Forces (USAAF) was not impressed by its performance and canceled half of the original order for 100 fighters, using the completed aircraft as trainers. The USAAF would instead go on to select the Lockheed P-80 Shooting Star as its first operational jet fighter. Although no P-59s entered combat, the aircraft paved the way for later generations of U.S. turbojet-powered aircraft.

Major General Henry H. "Hap" Arnold became aware of the UK's jet program when he attended a taxiing demonstration of the Gloster E.28/39 in April 1941. The subject had been mentioned, but not in-depth, as part of the Tizard Mission the previous year. He requested and was given, the plans for the aircraft's powerplant, the Power Jets W.1, which he took back to the U.S. He also arranged for an example of the engine, the Whittle W.1X turbojet, to be flown to the U.S. on 1 October in a Consolidated B-24 Liberator, along with drawings for the more powerful W.2B/23 engine and a small team of Power Jets engineers. On 4 September, he offered the U.S. company General Electric a contract to produce an American version of the engine, which subsequently became the General Electric I-A. On the following day, he approached Lawrence Dale Bell, head of Bell Aircraft Corporation, to build a fighter to utilize it. Bell agreed and set to work on producing three prototypes. As a disinformation tactic, the USAAF gave the project the designation P-59A, to suggest it was a development of the unrelated Bell XP-59 fighter project which had been canceled. The design was finalized on 9 January 1942, and construction began. In March, long before the prototypes were completed, an order for 13 YP-59A pre-production aircraft was added to the contract.

The P-59A had an oval cross-section, all-metal stressed skin semi-monocoque fuselage that housed a single pressurized cockpit. The mid-mounted, straight wing had two spars plus a false spar in the inner panel. The electrically-powered tricycle landing gear was attached to the center spar. The pair of General Electric J31 turbojets were positioned under the wing roots in streamlined nacelles. The armament was located in the nose of the aircraft; two of the three XP-59As and most of the YP-59As had a pair of 37-millimeter (1.5 in) M10 autocannon. Later aircraft, including the production models, had one M10 autocannon and three 0.5-inch (12.7 mm) AN/M2 Browning heavy machine guns. 

The crated prototype had been built on the second floor of a disused Pierce-Arrow factory, but its components were too big to fit through any elevator and required a hole to be broken in the brick outer wall to remove the first XP-59A. It was shipped to Muroc Army Air Field (today, Edwards Air Force Base) in California on 12 September 1942 by train for flight testing. The aircraft first became airborne during high-speed taxiing tests on 1 October with Bell test pilot Robert Stanley at the controls, although the first official flight was made by Colonel Laurence Craigie the next day. While being handled on the ground, the aircraft was fitted with a dummy propeller to disguise its true nature. When heavy rains flooded Rogers Dry Lake at Muroc in March 1943, the second prototype was towed 35 mi (56 km) to Hawes Field, an auxiliary airfield of Victorville Army Airfield, later George Air Force Base, over a public road. After one flight on 11 March, security concerns caused the jet to be transferred to nearby Harper Lake where it remained until 7 April.

Number built: 66

For more details of development, operational history and variants, click here.

The first member of the prolific Huey family, it was developed by Bell Helicopter to meet a 1952 US Army requirement for a medical evacuation and utility helicopter, and first flew in 1956. The UH-1 was the first turbine-powered helicopter produced for the United States military, and more than 16,000 have been built since 1960.

The Iroquois was originally designated HU-1, hence the Huey nickname, which has remained in common use, despite the official redesignation to UH-1 in 1962. The UH-1 first saw service in combat operations during the Vietnam War, with around 7,000 helicopters deployed. The Bell 204 and 205 are Iroquois versions developed for the civil market.

The UH-1 has a metal fuselage of semi-monocoque construction with tubular landing skids and two rotor blades on the main rotor. Early UH-1 models featured a single Lycoming T53 turboshaft engine in versions with power ratings from 700 shp (522 kW) to 1,400 shp (1,040 kW). Later UH-1 and related models featured twin engines and four-blade rotors.

The Royal Australian Air Force employed the UH-1H until 1989. Iroquois helicopters of No. 9 Squadron RAAF were deployed to South Vietnam in mid 1966 in support of the 1st Australian Task Force. In this role they were armed with single M60 doorguns. In 1969 four of No. 9 Squadron's helicopters were converted to gunships (known as 'Bushrangers'), armed with two fixed forward firing M134 7.62 mm minigun (one each side) and a 7-round rocket pod on each side. Aircrew were armed with twin M60 flexible mounts in each door. UH-1 helicopters were used in many roles including troop transport, medevac and Bushranger gunships for armed support.

For more etails of the development, design, operational history and multiple variants, click here.

The specifications below are for the UH-1D variant.