The advent of the Mi-6 gave the Soviet Union the very useful ability to move and place large, bulky or heavy loads with precision. Limitations of the Mi-6 in the flying crane role included a weight to payload ratio and the inability of the crew to easily see the load and its intended final position. A Council of Ministers directive of 20 February 1958 tasked OKB-329 (OKB Mil) with the development of a dedicated flying crane helicopter for carrying bulky loads unable to be carried in the hold of a Mi-6.

The Mil OKB's response drew heavily on the Mi-6, utilising the dynamic components and 4,100 kW (5,500 hp) Soloviev D-25V turboshaft engines, on a slim fuselage sitting on four tall strut braced undercarriage legs, with a wide track allowing the helicopter to taxi over loads, or for mobile loads to be moved underneath. The fuselage can carry 28 passengers inside the cabin as well as 3 t (6,600 lb) of cargo loaded through a side door in the aft fuselage, by an integral boom and winch. Underslung loads can be attached directly to the fuselage by hydraulically operated clamps, or carried on a 8.5 m × 3.6 m (28 ft × 12 ft) pallet lifted by the winch and braced by cables and/or struts to the undercarriage legs. The external sling system of the Mi-6, with a capacity of 8 t (18,000 lb) could also be fitted under the centre fuselage.

The first prototype V-10 emerged with canted main undercarriage legs with single wheels on all four legs, as well as a retractable emergency escape chute extending below the cockpit and external auxiliary fuel tanks either side of the centre fuselage. As development progressed the main undercarriage legs were replaced with vertical units carrying twin wheels, twin nose undercarriage wheels after a period retaining the single wheels, an Auxiliary power unit (APU) installed behind the cockpit on the starboard side and emergency escape slide cables for use when the pallet is carried.

The limitations of the Mi-10 in the slung load mission soon became obvious, chiefly, the loss of payload due to the heavy and complicated undercarriage, and more importantly the almost complete lack of oversight of the slung load, despite the inclusion of a CCTV (closed circuit television) system intended for observation of slung loads.

Foregoing the requirement to carry palleted or podded cargoes, Mil redesigned the Mi-10 with a much shorter, fixed, four-leg undercarriage and replaced the extendible escape chute with a gondola fitted with flying controls for a pilot to fly the aircraft during slung load operations. The remainder of the aircraft is essentially identical with the long-legged version. Seventeen of the new flying crane were produced as the Mi-10K, including two conversions from Mi-10s from 23 March 1974 to 1977.

For details of the world records held between the 10 variants of the Mi-10, click here.

Short legged Mi-10K

The Mil Mi-17 (NATO reporting name: Hip) is a Soviet designed Russian military helicopter family in production at two factories in Kazan and Ulan-Ude. It is known as the Mi-8M series in Russian service. The helicopter is mostly used as medium twin-turbine transport helicopter, as well as an armed gunship version.

Developed from the basic Mi-8 airframe, the Mi-17 was fitted with the larger Klimov TV3-117MT engines, rotors, and transmission developed for the Mi-14, along with fuselage improvements for heavier loads. Optional engines for "hot and high" conditions are the 1545 kW (2070 shp) Isotov TV3-117VM. Recent exports to China and Venezuela for use in high mountains have the new Klimov VK-2500 version of the Klimov TV3-117 engine with FADEC control.

The designation Mi-17 is for export; Russian armed forces call it Mi-8MT. The Mi-17 can be recognized because it has the tail rotor on the port side instead of the starboard side, and dust shields in front of the engine intakes. Engine cowls are shorter than on the TV2-powered Mi-8, not extending as far over the cockpit, and an opening for a bleed air valve outlet is present forward of the exhaust.

Actual model numbers vary by builder, engine type, and other options. As an example, the sixteen new Ulan-Ude-built machines delivered to the Czech Air Force in 2005 with -VM model engines were designated as Mi-171Sh, a development of the Mi-8AMTSh. Modifications include a new large door on the right side, improved Czech-built APU, and Kevlar armor plates around the cockpit area and engines. Eight have a loading ramp in place of the usual clamshell doors and can load a vehicle up to the size of an SUV.

In May 2008 licensed production of the Mi-17 started in China, with production being led by Mil Moscow Helicopter Plant JSC and the Sichuan Lantian Helicopter Company Limited in Chengdu, Sichuan province. The plant built 20 helicopters in 2008, using Russian Ulan-Ude-supplied kits; production is expected to reach 80 helicopters per year eventually. The variants to be built by Lantian will include the Mi-171, Mi-17V-5, and Mi-17V7.

Over 12,000 had been built by 2007.

For operational history and variants, click here.

The Mi-2 was produced exclusively in Poland, in the WSK "PZL-Świdnik" factory in Świdnik.

The first production helicopter in the Soviet Union was the Mil Mi-1, modelled along the lines of the S-51 and Bristol Sycamore and flown by Mikhail Mil's bureau in September 1948. During the 1950s it became evident, and confirmed by American and French development, that helicopters could be greatly improved with turbine engines. S. P. Isotov developed the GTD-350 engine and Mil used two of these in the far superior Mi-2.

The twin shaft-turbine engines used in the Mi-2 develop 40% more power than the Mi-1's piston engines, for barely half the engine weight, with the result that the payload was more than doubled. The Mi-2 fuselage was extensively altered from its predecessor, with the engines mounted overhead. However, the external dimensions remained similar.

For more details, including the 27 variants and versions, click here.

The Mil Mi-34 (NATO reporting name: Hermit) is a light helicopter designed by the Mil Moscow Helicopter Plant in either a two or four seat configuration for utility and training. It was first flown on 17 November 1986 and introduced at the Paris Air Show in 1987. The Mi-34 entered production in 1993, and is capable of performing aerobatic manoeuvres, including rolls and loops.

Variants

Mi-34S – four seat production model powered by a 239 kW (325 hp) Vedeneyev (VOKBM) M-14V-26V nine-cylinder, air-cooled, radial engine mounted sideways in the fuselage, and equipped with modern avionics. A few aircraft were purchased by the Moscow police.
Mi-34S2 "Sapsan" – turbine version of the Mi-34. It will be able to accommodate up to 4 passengers and the first deliveries are planned by the end of 2011. It will be powered by Turbomeca Arrius-2F[1]
Mi-34L – proposed version powered by a 261 kW (350 hp) Textron Lycoming TIO-540J piston engine. None built.
Mi-34P Patrulnyi (English: patrol) – Police patrol version for Moscow Mayor Office.
Mi-34A – Luxury version, intended to be powered by an Allison 250-C20R turboshaft engine. None built.
Mi-34M1 and Mi-34M2 – Proposed twin-turbine, six-passenger versions.
Mi-34UT – trainer with dual control.
Mi-34V or Mi-34VAZ or Mi-234 – proposed version powered by two VAZ-4265 rotary piston engines.
Mi-44 – proposed development with TV-O-100 engine and refined aerodynamics. A mockup was built in 1987.

The Mil Mi-38 is a transport helicopter designed by Mil Moscow Helicopter Plant and being developed by Kazan Helicopters. Originally intended as a replacement for the Mil Mi-8 and the Mi-17, it is being marketed in both military and civil versions. It flew for the first time on 22 December 2003 and was certified on 30 December 2015.

The Mi-38's development was carried out by Kazan Helicopters since early 1980s and a mockup was first shown during the 1989 Paris Air Show. After the dissolution of the Soviet Union in 1991, Kazan Helicopters went into collaboration with Eurocopter that was to adapt the Mi-38 for international market. In September 1994, Euromil JSC was established and funding of the programme began a month later. Sextant and Pratt & Whitney Canada were also to participate in the programme as suppliers of Mi-38's avionics and powerplant equipment. Initially, the helicopter was to be first flight tested in 1999, but only on 18 August 1999 a contract was signed for completion of the first demonstrator. In 2001, testing of Mi-38's rotor blades was carried out on a Mi-17 helicopter. The first Mi-38 demonstrator (PT-1) performed its maiden flight above the Kazan Helicopters plant on 22 December 2003.

The second prototype (OP-2), powered by Pratt & Whitney Canada PW127/TS engines, made its first flight on 2 December 2010. The prototype is also equipped with the IBKO-38 or IBKV-38 aviation complex, developed by Transas Aviation, which implements a concept of a glass cockpit for the Mi-38. The same month, OP-2 performed its first long-haul flight from Kazan to Moscow, which covers more than 800 km.

Number built:   10 (4 test and 6 serial)

For further details of the 3rd and 4th prototypes, plus variants, click here.

The Mil Mi-8 (Russian: Ми-8, NATO reporting name: Hip) is a medium twin-turbine helicopter, originally designed by the Soviet Union, and now produced by Russia.

In addition to its most common role as a transport helicopter, the Mi-8 is also used as an airborne command post, armed gunship, and reconnaissance platform. Along with the related, more powerful Mil Mi-17, the Mi-8 is among the world's most-produced helicopters, used by over 50 countries. As of 2015, when combined the two helicopters are the third most common operational military aircraft in the world.

Mikhail Mil originally approached the Soviet government with a proposal to design an all-new two-engined turbine helicopter after the success of the Mil Mi-4 and the emergence and effectiveness of turbines used in the Mil Mi-6; but the military argued against a new helicopter, as they were content with the current Mil Mi-4. To counter this, Mikhail Mil proposed that the new helicopter was more of an update to new turbine engines rather than an entirely new helicopter; this persuaded the council of ministers to proceed with production. Due to the position of the engine, this enabled Mikhail Mil to justify redesigning the entire front half of the aircraft around the single engine (designed by Oleksandr Ivchenko at OKB-478 in Zaporizhzhia, Ukraine, originally for fixed wing aircraft as all other soviet turbines had been up to that point).

The prototype, which was named V-8, was designed in 1958 and based on the Mil Mi-4 with a larger cabin. Powered by an AI-24 2,010 kW (2,700 shp) Soloviev turboshaft engine, the single engined V-8 prototype had its maiden flight in June 1961 and was first shown on Soviet Aviation Day parade (Tushino Air Parade) in July 1961.

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

Specifications below are for the Mi8MT variant.

The Mil V-12 (NATO reporting name: Homer), given the project number Izdeliye 65 ("Item 65"), is the largest helicopter ever built. The designation "Mi-12" would have been the name for the production helicopter and was not applied to the V-12 prototypes.

Design studies for a giant helicopter were started at the Mil OKB in 1959, receiving official sanction in 1961 by the GKAT (Gosudarstvenny Komitet po Aviatsionnoy Tekhnike - State Committee on Aircraft Technology) instructing Mil to develop a helicopter capable of lifting 20 to 25 t (44,000 to 55,000 lb). The GKAT directive was followed by a more detailed specification for the V-12 with hold dimensions similar to the Antonov An-22, intended to lift major items of combat materiel as well as 8K67, 8K75 and 8K82 inter-continental ballistic missiles (ICBM).

Design limitations forced Mil to adopt a twin rotor system but design studies of a tandem layout, similar to the Boeing CH-47 Chinook, revealed major problems. The single rotor layouts also studied proved to be non-viable, leading to the transverse layout chosen for the finished article.

The transverse rotor system of the V-12, which eliminates the need for a tail rotor, consists of two Mil Mi-6 transmission systems complete with rotors mounted at the tips of the approximately 30 m (98 ft) span inverse tapered wings. Although the first use by Mil, the transverse system had been used by several of the early helicopters, including the Focke-Wulf Fw 61, Focke-Achgelis Fa 223 Drache and Kamov Ka-22 Vintokryl convertiplane.

The large fuselage accommodated the 28.15×4.4×4.4 m (92.4×14.4×14.4 ft) cabin and crew section in the extreme nose, housing a pilot, co-pilot, flight engineer and electrical engineer in the lower cockpit, with the navigator and radio operator in the upper cockpit.

At the aft end of the fuselage access to the cabin is gained by large clamshell doors and a drop down cargo ramp with inbuilt retractable support jacks. Doors in the fuselage also give access to the cargo hold: two on the starboard side and three on the port side. Above the rear fuselage is a very large fin and rudder, with a moderately sized tailplane with dihedral fitted with end-plate fins (not fitted for the first flight).

Records achieved.

For further details on the V-12 (Mi-12), click here.

The MH2000 is Japan's first indigenous helicopter with Mitsubishi Heavy Industries (MHI) having sole responsibility for developing and manufacturing the fuselage and engines.

In the development of the MH2000, MHI aimed for safety, economy and low noise levels. The program was launched in 1995 to fulfill a variety of missions, include passenger and business transport, law enforcement, search and rescue and emergency medical services.

The first of four developmental aircraft first flew on 29 July 1996, the second flying later that year and the remaining two used for ground testing. The MH2000 has its engine module and dynamic system positioned behind the cabin section to minimize sound levels in the passenger compartment. Power is provided by a pair of Mitsubishi MG5-100 turboshaft engines. 

The first production model was delivered on October 1, 2000 to Excel air service in Japan. The loss of one prototype due to tail rotor blade separation led to suspension of type certificate and redesign of tail rotor. Delivered craft were modified with the new rotor and all further craft will be delivered with the new tail rotor.

Low levels of interest in the aircraft forced Mitsubishi to halt sales of MH2000 in September 2004.

By 2015 Mosquito Aviation was out of business and the design was being produced by Innovator Technologies of Rockyview, Alberta, Canada. By 2019 the design was being produced by Composite FX of Trenton, Florida.

The XE is a development of the Mosquito Air, with a cockpit fairing and a more sophisticated exhaust system, plus a rotor diameter increased by 40 cm (15.7 in) to support the higher gross weight. The aircraft was designed to comply with the US Experimental - Amateur-built and European microlight aircraft rules. It features a single main rotor and tail rotor, a single-seat enclosed cockpit with a windshield, skid landing gear and a two-cylinder, air-cooled, two stroke 64 hp (48 kW) MZ 202 engine.

The aircraft fuselage is made from composites and metal tubing. Its two-bladed rotor has a diameter of 5.95 m (19.5 ft) and a chord of 17 cm (6.7 in). The aircraft has a typical empty weight of 135 kg (298 lb) and a gross weight of 280 kg (617 lb), giving a useful load of 145 kg (320 lb). With full fuel of 45 litres (9.9 imp gal; 12 US gal) the payload for the pilot and baggage is 112 kg (247 lb).

Variants

AIR

(2002) Open aluminum frame with tripod landing gear[3]

XE

(2004)

XEL

XE with floats. Meets United States FAA FAR 103 Ultralight Vehicles rules for 254 lb (115 kg) and under for ultralight aircraft.[4]

XE285

85 hp (63 kW) Inntec 800 2 cylinder 2 cycle

XE3 - Discontinued

85 hp (63 kW) CRE MZ 301 3 cylinder 2 cycle

XET

90 hp (67 kW) Solar T62-2A1 turbine

The Niki Lightning is a fully enclosed two-seater tricycle autogyro of composite construction, designed and built by Niki Rotor Aviation in Bulgaria. It was introduced in 2009.

The Lightning's cockpit pod accommodates a pilot and passenger in tandem. The main rotor is two-bladed, with a pre-rotator. Unconventionally the tail boom is mounted though the centre of the propeller shaft. The boom may be unbolted and removed to aid access to the engine and prop.

There is a choice of two very compact D-Motor engines (both liquid-cooled horizontally-opposed side-valve four-strokes): either the 95 hp (71 kW) 4-cylinder LF26 or the 130 hp (97 kW) 6-cylinder LF39. The engine is sited behind the cockpit, driving a 3- or 4-bladed ground-adjustable pusher propeller which is coaxial with the tail boom. The D-Motor engines are direct-drive units redlined at 3,000 rpm. The engines are sited beneath the thrust line of the propeller; instead of using a gearbox, the Lightning uses a multi-belt-drive reduction system of about 3:2 ratio, resulting in an efficient propeller speed of up to 2,000 rpm. This arrangement avoids the necessity of a tailboom beneath the propeller, giving a smoother empenage and reducing drag. Beneath the tail-fin a spring-steel tailskid is fitted, to inhibit propeller strikes.

Consuming some 15 L (4.0 US gal; 3.3 imp gal) of avgas per hour, the autogyro has an endurance of 4 hours, with 30 minutes reserve. Its cruise speed of 81 kn (150 km/h; 93 mph) gives the autogyro a range of over 320 nmi (590 km; 370 mi). It has a take-off roll of 70 m (230 ft), and a landing roll of 20 m (66 ft). The Lightning may be flown with its side doors removed.

An alternative engine for the Niki Lightning is the Rotax 914UL (but the normal Rotax gearbox would be dispensed with in favour of the drive belts).

The Omega BS-12 was a utility helicopter with high ground clearance designed to carry loads behind the cabin at, or near, the center of gravity.

Bernard Sznycer, designer of the Sznycer SG-VI, the first helicopter certified in Canada, set up the Omega Aircraft Corporation, based at New Bedford, Massachusetts in December 1953, with himself as President and Chief Designer of the company. Omega's first design was a twin-engined flying crane / utility helicopter, intended to be inexpensive to produce and relatively cheap to operate.

The helicopter was of conventional layout, with a single four-bladed lift rotor and a two bladed anti-torque rotor. Its fuselage was of pod-and-boom layout, with a small enclosed crew cabin forward connected to an uncovered steel tube tail boom. Cargo, either a slung load or in a pre-loaded pod, could be carried between the crew cabin and the undercarriage mainwheels, while it was planned to also provide a pod to carry passengers. It was powered by twin piston engines mounted horizontally on either side of the main gearbox.

The first example made its maiden flight on December 29, 1956. The type was certified by the Federal Aviation Administration in April 1961. Omega planned to build an initial batch of 25 BS-12-D-1s, which were priced at $77,500, with production gradually building up from one per month. Although Omega received orders for several BS-12s following certification, shortages of funds stopped production, and Omega entered into bankruptcy in July 1962. Omega was purchased by the Aeronautical Research and Development Corporation of Boston, Massachusetts, with the intention of putting the BS-12 into production as the ADRC/Omega RD-400.

Not to be confused with Piasecki H-16 Transporter.

The Piasecki 16H was a series of compound helicopters produced in the 1960s. The first version of the Pathfinder, the -1 version, first flew in 1962. The similar but larger Pathfinder II, the 16H-1A, was completed in 1965.

Variants

Model 16H-1 Pathfinder
one PWC PT6B-2 with one 405 shp turboshaft engine
Model 16H-1A Pathfinder II   Specifications below
larger version with one 1,250 shp (930 kW) T58-GE-8
Model 16H-1C Pathfinder III
proposed conversion of the 16H-1A with one 1,500 shp (1,100 kW) T58-GE-5 
Model 16H-3J
nine-seat development, not built.

The Piasecki H-21 Workhorse/Shawnee is an American helicopter, the fourth of a line of tandem rotor helicopters designed and built by Piasecki Helicopter (later Boeing Vertol). Commonly called "the flying banana", it was a multi-mission helicopter, capable of being fitted with wheels, skis or floats.

The H-21 was originally developed by Piasecki as an Arctic rescue helicopter. The H-21 had cold-weather features permitting operation at temperatures as low as −65 °F (−54 °C) and could be routinely maintained in severe cold weather environments.

Piasecki Helicopter designed and successfully sold to the United States Navy a series of tandem rotor helicopters, starting with the HRP-1 of 1944. The HRP-1 was nicknamed the "flying banana" because of the upward angle of the aft fuselage, which ensured that the large rotors could not strike the fuselage in any flight attitude. The name was later applied to other Piasecki helicopters of similar design, including the H-21.

In 1949, Piasecki proposed the YH-21 Workhorse, which was an improved, all-metal derivative of the HRP-1, to the United States Air Force (USAF). Using two tandem, fully articulated three-bladed counter-rotating rotors, the H-21 was powered by one nine-cylinder Curtis-Wright R-1820-103 Cyclone supercharged 1,150 hp (858 kW) air-cooled radial engine.

After the first flight of the YH-21 on 11 April 1952, the USAF ordered 32 H-21A SAR models and 163 of the more powerful H-21B assault transport variant.[2] The H-21B was equipped with an uprated version of the Wright 103 engine, developing 1,425 shaft horsepower (1,063 kW) and featured rotor blades extended by 6 inches (152 mm). With its improved capabilities, the H-21B could carry 22 fully equipped infantrymen or 12 stretchers, plus space for two medical attendants, as a medevac helicopter. With its Arctic winter capabilities, the H-21A and H-21B were put into service by the USAF and the Royal Canadian Air Force (RCAF) to maintain and service Distant Early Warning Line (DEW) radar installations stretching from the Aleutian Islands and Alaska across the Canadian Arctic to Greenland and Iceland.

In 1952, some H-21As were evaluated by USMC helicopter squadron HMX-1 for air assault.[3] In 1957, an H-21B was loaned to the United States Marine Corps (USMC) to evaluate the helicopter as an airborne tug to tow disabled landing ships and amphibious landing vehicles to the beach. During the evaluation, the H-21B towed an LST at 5 kn (9.3 km/h; 5.8 mph) and a simulated tracked amphibious vehicle from the water to the beach.[4] The uprated 1425 hp Wright engine used in the H-21B was also used in subsequent variants sold to both the U.S. Army (as the H-21C Shawnee) and the military forces of several other nations. In 1962, the H-21 was renamed the CH-21 in U.S. Army service.

In 1959 Vertol Aircraft, the new name for Piasecki Helicopters, came up with a concept for heavy lift over short distances where between two and six H-21Bs would be linked by beams to lift heavy loads. It was considered to be unsafe, because if one helicopter had mechanical problems during the lift it could unbalance the structure and cause all helicopters to crash.

For operational history and details of the 18 variants, click here.

The Piasecki HRP Rescuer (also called Harp) is a United States tandem-rotor transport or rescue helicopter designed by Frank Piasecki and built by Piasecki Helicopter. The Piasecki PV-3 was adopted as the HRP-1 Rescuer by the United States Navy, United States Marine Corps, and United States Coast Guard. An improved PV-17 variant was later produced as the HRP-2. As one of the first transport helicopters in military service, the HRP-1 was capable of carrying two crewmen and 8–10 passengers or 2,000 lb. (907 kg) of cargo.

It was first flown in early 1945, entered service in 1947.

The prototype helicopter (designated PV-3 by Piasecki, though commonly known to test personnel as "The Dogship") first flew at Morton, Pennsylvania in 7 March 1945 following a development contract from the United States Navy in February 1944. The "Dogship" was a novel tandem-rotor helicopter with a fixed tricycle landing gear, powered by a 600 hp (447 kW) Pratt & Whitney R-1340-AN-1 engine. To ensure that the rotors did not hit each other, the rear end of the fuselage curved upwards so the rear rotor was higher than the forward rotor. The fuselage was constructed of ordinary mild steel tubing, filled out with wooden ribs, and covered with doped fabric.

Following a series of mechanical incidents with the prototype, including stripped transmission gears, it was determined that use of common automotive parts in the helicopter transmission were inadequate to the severe loads imposed by flight; subsequent prototypes built after the war used stronger components. Two prototypes designated XHRP-1 were constructed; one was used as a static test aircraft and the other was used for development flying.

The helicopter got the nicknames " Harp" and "flying banana", a name also carried on by its successor.

Number built    28

Variants

PV-3
Prototype tandem-rotor helicopter powered by a Wright R-975 piston engine, one built.
XHRP-1
Military designation for two further PV-3s, one for static testing and one for flight trials.
HRP-1
Production variant, 20 built including three HRP-1Gs.
HRP-1G
Three United States Navy HRP-1s for the United States Coast Guard.
HRP-2
Metal skinned variant, five built.

The Piasecki HUP Retriever or H-25 Army Mule, later UH-25, is a compact single radial engine, twin overlapping tandem rotor utility helicopter developed by the Piasecki Helicopter Corporation of Morton, Pennsylvania. Designed to a United States Navy specification, the helicopter was produced from 1949 to 1954, and was also used by the United States Army and foreign navies. The HUP/H-25 was the first helicopter to be produced with an autopilot and also the first to perform a loop.

The design was a product of a competition by the U.S. Navy in 1945 for a compact utility/rescue helicopter to operate from ships including aircraft carriers, battleships, and cruisers. Either 2 or 3 prototypes—designated PV-14 by the factory and XHJP-1 by the Navy—were built and subjected to a side-by-side flight evaluation against the 3 prototypes of the Sikorsky XHJS-1; however, the XHJS was fundamentally a scaled-up version of the Sikorsky H-5, and the increased weight and size magnified the design's problems with maintaining proper weight and balance under varying loading conditions. The Piasecki won the competition, and with the introduction of the aircraft configuration letter "U" for Utility in the 1950s, the aircraft was ordered for production as the HUP-1.

The design featured two three-bladed, 35-foot-diameter (11 m) rotors in tandem in which blades could be folded for storage; the relatively small rotor diameter allowed the aircraft to use aircraft carrier elevators with its blades fully extended. The tandem overlapping rotor configuration was a development by Piasecki and was used in future helicopter designs by the company and successors including the H-21, HRB-1/CH-46, and CH-47. The original HUP-1 was powered by a single Continental R-975-34 radial engine, with a take-off rating of 525 hp (391 kW), while later versions used the uprated R-975-42 or R-975-46A with 550 hp (410 kW). To aid search and rescue (SAR) operations, the aircraft was equipped with an overhead winch capable of lifting 400 lb (181 kg), which could lower a rescue sling through an electrically-operated door available after the copilot's seat was folded forward.

During a flight demonstration of its capability to withstand high g-force, the type became the first helicopter to perform a loop, albeit unintentionally.

For operational history and details of the 9 variabts, click here.

The PZL Kania (Polish Kite, also marketed as Kitty Hawk) is a follow-up design to the Mil Mi-2 helicopter, developed in Poland by PZL-Świdnik.

In 1964, an agreement was signed between Poland and the Soviet Union assigning production of the Mil Mi-2 twin-engined light helicopter exclusively to the WSK PZL-Świdnik factory at Świdnik, Poland.

Work on a significantly redesigned version of the Mi-2 started in 1977. PZL decided to develop, in conjunction with the American aero-engine company Allison, a re-engined version for export for western markets, the Kania or Kitty Hawk.[1] The changes include a modified fuselage with more pointed nose, new engines (Allison Model 250-C20B turboshaft engines) each rated at 313 kW (420 hp), new composite rotors blades, and new western avionics. The first prototype, utilizing a modified Mi-2 airframe, was flown on 3 June 1979. Two prototypes were made and two pre-series machines. Tests conducted during the early 1980s led to certification according to FAR-29, in February 1986.

The prototype SP-SSC took part in the 5th Helicopter World Championships in Castle Ashby in 1986. Production started that year in limited quantity, in the PZL Świdnik factory. The helicopter was intended to be a replacement of the Mi-2, more economical, comfortable and offering better performance, and it compared quite favourably with Western counterparts. It did not become popular, however, partly due to problems with certification and a weak promotion in Western countries, and reluctance to spend convertible currency for imported parts in Eastern Bloc countries in the 1980s. Only 19 were built until 2006, including prototypes. It isn't currently offered by PZL-Świdnik.

The main user is the Polish Border Guard, with 7 helicopters (not concurrently). The Polish Police used two helicopters. Three Polish Kanias were employed in air service in Sierra Leone in 1987–1990. In 2007, Świdnik offered 6 armed Kanias for Philippine Air Force, but lost in competition (finally, after cancelling a procedure, PZL W-3 Sokół was chosen).

Variants

Passenger Standard

Seats for pilot and 9 passengers, individual vents and lighting.

Passenger Executive

Seats for pilot and 5 passengers, luxury finishing, silenced cockpit, individual vents, lighting and audio system.

Cargo

Ability to carry 800 kg (1,764 lb) external loads as a flying crane or to carry up to 1,200 kg (2,646 lb) of load in the cabin.

Medevac / Air ambulance

Equipment and space for up to 4 stretchers or less with paramedic crew on board.

Agricultural

Ability to carry up to 1,000 kg (2,205 lb) of chemicals or agro loads (grains, seeds etc.) and ability to carry on one of following aerial application methods: LV spraying, ULV spraying, dustring and spreading (not built in series, only tested).

Spitfire Taurus II or Super Kania

American version of the PZL Kania, with redesigned fuselage and single 550 shp (410 kW) Allison Model 250-C28 engine, with a big central air inlet, that was to be built under licence in the United States by Spitfire Helicopters but only a mock-up was built.

Following a protracted development, the PZL SW-4 Puszczyk entered service in 2002, the primary operator of the type has been the Polish Armed Forces. The SW-4 was further developed by PZL-Świdnik and corporate parent AgustaWestland into an optionally piloted vehicle, the SW-4 Solo. From 2016 onwards, the type has been marketed to civil operators as the AW009, while the SW-4 designation shall be continue to be used for the military market.

The SW-4 is powered by a single 335 kW (450 shp) (283 kW/380 shp max continuous rated) Rolls-Royce Model 250C20R/2 turboshaft engine, which drives the rotorcraft's three-blade main rotor and two-blade tail rotor. An alternative engine is provided in the form of the 460 kW (615 shp) Pratt & Whitney Canada PW200/9 turboshaft engine. The main rotor is fully articulated and the rotor blades on both the main and tail rotors are composed of composite materials. The SW-4 uses hydraulic flight controls, the rotorcraft has been promoted as possessing excellent flight controls, and can be flown in both day and night visual flight rules conditions.

For more details of the evelopment, design and operational history of the SW-4, click here.

The PZL W-3 Sokół (English: "Falcon") is a medium-size, twin-engine, multipurpose helicopter developed and manufactured by Polish helicopter company PZL-Świdnik (now AgustaWestland Świdnik). It was the first helicopter entirely designed and produced in Poland.

During 1973, work commenced upon what would become the W-3 Sokół at PZL Świdnik; design work was performed by an in-house team led by aeronautical engineer Stanisław Kamiński. A major influence on the design was the perceived demands from both military and civilian aviation across the Soviet Union, which was envisioned to serve as the major operator of the type. On 16 November 1979, the Sokół conducted its maiden flight. Following an intensive test programme, type certificated for the helicopter was received from aviation authorities in Poland, Russia, the United States and Germany.

During May 1993, certification of the Sokol to Federal Aviation Administration (FAA) FAR Part 29 standards was granted; it was followed by the receipt of German certification during December of that year. During 1985, low rate production of the Sokół commenced. In June 1996, the 100th Sokół was completed by the company.

During 1973, work commenced upon what would become the W-3 Sokół at PZL Świdnik; design work was performed by an in-house team led by aeronautical engineer Stanisław Kamiński. A major influence on the design was the perceived demands from both military and civilian aviation across the Soviet Union, which was envisioned to serve as the major operator of the type. On 16 November 1979, the Sokół conducted its maiden flight. Following an intensive test programme, type certificated for the helicopter was received from aviation authorities in Poland, Russia, the United States and Germany.

During May 1993, certification of the Sokol to Federal Aviation Administration (FAA) FAR Part 29 standards was granted; it was followed by the receipt of German certification during December of that year. During 1985, low rate production of the Sokół commenced. In June 1996, the 100th Sokół was completed by the company.

The Sokół has been offered in a number of diverse variants and is capable of performing a typical range of helicopter missions, including passenger transport, VIP, cargo, EMS, medevac, firefighting and search and rescue. When used in maritime environments, the rotorcraft is typically outfitted with floats, a transponder, a global positioning system navigation system, night-vision equipment, and a Lucas winch.

For more information on the development of the Sokol, including the aborted Huzar attack helicopter variant, the operational history and the many variants and proposals, click here.

The Revolution Mini-500 is a 1990s American single-seat light helicopter, designed and built by Revolution Helicopter Corporation as a kit for homebuilding.

Revolution Helicopter went out of business in November 1999 and kits are no longer available.

The Mini-500 was designed as a light helicopter that resembles a scaled-down Hughes 500, powered by a Rotax 582 64 hp (48 kW) two-stroke engine.

The Mini-500 design was initially based upon Augusto Cicaré's control system design as incorporated in his CH-6 prototype helicopter, but company president Dennis Fetters and Cicaré were unable to agree on licensing terms. Fetters instead elected to design and patent a "newly improved control system".

The Mini-500 has a tubular steel fuselage with a foam and glass-fibre structure cabin. It has a two-bladed semi-rigid rotor and a conventional two-blade tail rotor. The first Mini-500 flew in 1992 and the company delivered the first production factory-assembled helicopter in July 1994. Production of kits ceased in 1999 and the company claimed that more than 500 had been sold.

For more information on the Mini-500, click here.

The two-seat R22 was designed in 1973 by Frank Robinson and has been in production since 1979.

The R22 is a light, two-place, single reciprocating-engined helicopter with a semi-rigid two-bladed main rotor and a two-bladed tail rotor. The main rotor has a teetering hinge and two coning hinges. The tail rotor has only a teetering hinge.

The normal production variant has skid landing gear. The Mariner version — which is no longer manufactured — provided floats. Wheeled gear is not available.

The basic structure is welded chromoly steel tubing. The forward fuselage is made of fiberglass and aluminum with a Plexiglas canopy. The tailcone and vertical and horizontal stabilizers are aluminum. It has an enclosed cabin with side-by-side seating for a pilot and passenger. The doors may be removed for flight, as is often done for photographic flights, interior cooling in high temperatures, or a 10.4 lb weight saving.

A check of the Australian Aircraft Register shows there are more than 500 R22's registered in Austratlia.

For more details including variants, click here.

Helicopter mustering by R22.

Based on the company's two-seat Robinson R22, the R44 features hydraulically assisted flight controls. It was first flown on 31 March 1990 and received FAA certification in December 1992, with the first delivery in February 1993.

The R44 has been the world's best-selling general aviation (GA) helicopter every year since 1999. It is the most-produced GA aircraft of the 21st century, with 5,805 deliveries from 2000–2017.

The R44 is a single-engined helicopter with a semi-rigid two-bladed main rotor, a two-bladed tail rotor and a skid landing gear. It has an enclosed cabin with two rows of side-by-side seating for a pilot and three passengers. Tail rotor direction of rotation on the R44 is reversed compared to the R22 for improved yaw control authority. On the R44 the advancing blade is on the bottom.

The R44 was developed into the R66 with the fitting of a turbine engine.

For details of development and accident history, click here.

The Robinson R66 is a helicopter designed and built by Robinson Helicopter Company. It has five seats, a separate cargo compartment and is powered by a Rolls-Royce RR300 turboshaft engine. The R66 is slightly faster and smoother than the Robinson R44 from which it is derived. The R66 received both type and production certificates from the U.S. Federal Aviation Administration (FAA) on October 25, 2010.

Announced in 2007, the R66 was designed to be the company's first turbine-powered product and to extend its product range to compete with larger helicopters manufactured by Bell Helicopter and Eurocopter. Most of the R66 design is based on the earlier piston-engine R44.

Robinson started taking orders for the R66 in February, 2010. It went into preliminary production in 2010, and full production in 2011. The existing two-seat R22 and four-seat R44 continued in production. A four-seat police version of the R66 has entered production with a forward looking infrared (FLIR) camera system, searchlight, and external public address (PA) system as standard equipment.

In 2012, Robinson delivered 191 R66s while Robinson's competitors in the light single turbine sector delivered only 40 units between them. About 70 percent of the R66 production is exported. In 2014, the production rate slowed to about two R66s per week for a total of 101 for the year. In 2015, Robinson produced three R66s per week. RHC has contracted with Rolls-Royce to supply 100 RR300 turbines per year for 10 years.

The company delivered the 1,000th R66 in August 2020.

The R66 is a single-engined helicopter with two-bladed main and tail rotors, and a fixed skid landing gear. The R66 is constructed from advanced composites, aluminum alloy (sheet), and chromoly steel. Like the R44, the R66 has both electromechanical instruments and optional digital glass cockpit.

The R66 is the first Robinson helicopter with a cargo hold; the hold carries up to 300 pounds (140 kg).

The RR300 engine is more compact and lighter than the Lycoming O-540 six-cylinder piston engine that powers the R44—the R66 has a lower empty weight than the R44. The RR300 has a simplified single-stage centrifugal compressor which makes it less expensive and is expected to result in lower maintenance costs.

For more information on development and design, click here.

The RAF 2000 was a development of the single seat RAF 1000 and was designed primarily by Bernard J Haseloh. The aircraft kits were manufactured by Rotary Air Force Inc of Canada until April 2007 when the marketing and manufacturing rights were transferred to UMRTC Eben Mocke located in Upington, South Africa.

As a result of test flying in the UK the RAF 2000 has been documented as being subject to Power Push Over (PPO), whereby the thrust line is above the aircraft's vertical centre of gravity. This results in a power application causing a nose-down pitching moment and increases the risk of tail to main rotor contact.

VARIANTS

RAF 2000 GTX SE

Equipped with a 130 hp (97 kW) Subaru flat four carburetted engine

RAF 2000 GTX SE FI

Equipped with the same engine but it is fuel injected thus making it a little more economical

RAF 2000 GTX SE FI 2.5

Equipped with a more powerful 165 hp (123 kW) Subaru fuel injected engine.

The RotorWay A600 Talon is an American helicopter, designed and produced by RotorWay International of Chandler, Arizona. The aircraft is supplied as a kit for amateur construction.

By April 2017 the company seemed to have dropped the name Talon, referring to the aircraft just as the A600.

The A600 Talon is a development of the RotorWay Exec and externally resembles the earlier design. The A600 incorporates a different structure, a shaft-driven tail rotor, taller and longer landing skids and a new in-house developed turbocharged powerplant.

The A600 features a single main rotor, a two-seats in side-by-side configuration enclosed cockpit with a windshield, skid-type landing gear and a turbocharged four-stroke, 147 hp (110 kW) RotorWay RI 600S engine that drives the 25 ft (7.6 m) diameter two-bladed rotor and conventional 50.25 in (127.6 cm) diameter two-bladed tail rotor. The aircraft has an empty weight of 965 lb (438 kg) and a gross weight of 1,500 lb (680 kg), giving a useful load of 535 lb (243 kg). With full fuel of 17 U.S. gallons (64 L; 14 imp gal) the payload is 433 lb (196 kg).

The aircraft is capable of an in ground effect hover at 6,000 ft (1,829 m) and an out of ground effect hover at 4,000 ft (1,219 m).

By February 2013 seven examples had been registered in the United States with the Federal Aviation Administration, one with the Civil Aviation Authority in the United Kingdom and one with Transport Canada.