The Kari-Keen 90 Sioux coupe was designed by Swen Swanson and is a two-seat side by side high-wing monoplane with conventional landing gear. The wing is fully cantilevered, with skylights built in. The fuel tank sits above the pilot’s head and is part of the leading edge. Ole Fahlin built all the propellers and test flew the aircraft.
Production of the Sioux coupe began in 1929. The first model, the Kari-Keen 60 Sioux Coup, featured a 60 hp (45 kW) Veile M-5 engine. 22 aircraft were built without a type certificate.
Coupe 90-A
In 1930, six more model 90s were built with a type certificate. The price was US$3,365 in 1930.
In 1931, the Sioux Aircraft Corporation bought the company assets, changing the name of the Kari-Keen 90 into the Sioux Coupe 90.
1931 Kari-Keen Coupe built by Sioux Aircraft Corp
One 1930 Coupe 60 (ATC 2-81), powered by a 65hp Velie M-5 engine, was carried over from Kari-Keen inventory to Sioux Aircraft Corporation.
With the re-organization of Kari-Keen Aircraft Co, the 1931 Sioux Coupe 90 was a slight variation of the Kari-Keen 90. Designed by Swen Swanson and redesign by Gazley & LaSha, the one built, NC10544, sold for $3,355. Originally powered by a 90hp Brownback Tiger, it was later re-powered with a 110hp Warner Scarab.
The Sioux Coupe 90-B Junior (ATC 414) built in 1931, NC10721, sold for $3,500. Originally powered by a 90hp Warner engine, there are reports that a 90hp Lambert was also installed at one time.
The Sioux Coupe 90-C Senior (ATC 2-356) NC10735 was built in 1931.
Production of the Sioux coupe ended on 1 August 1933.
Niilo and Valto Karhumäki started in autumn 1924 the construction of an airplane at their home. The work also involved Emil Kankaanpää and Hope Hovinen. The machine was given the name Bear 1.
The brothers built in the 1920s of four aircraft: Bear 1 Bear 2 Bear 3 and Tern. Construction was initially something of a hobby, but soon expanded into a versatile aviation business.
The Veljekset Karhumäki O/Y company had been formed in 1924 and concerned itself with licence manufacturing. During 1946-1947 the company designed and built the Karhu 48B a high-wing strut-braced four-seat monoplane in collaboration with Valtion. The development team included Uuno Karhumäki, Matti Hahka and August Puukko from Karhumäki and Torolf Eklund, Johannes Joensuu, Oiva Lounivuo, Toivo Mäntysalo, Karl Konrad Wessman, Paavo Paitula, Olavi Raitio and Aaretti Nieminen from Valtion, Nieminen being appointed team leader.
WINGS: High-wing rigidly braced monoplane. Wing braced by steel-tube V-struts. Two-spar wooden structure covered with fabric. Flaps and ailerons with welded steel-tube frames and fabric covering.
FUSELAGE: Welded steel-tube structure covered with fabric.
LANDING GEAR: Tail wheel type with interchangeable wheels and skis. Faired side vees, incorporating springing, and two half axles hinged at centreline of underside of fuselage. Steerable tail wheel. The landing gear could be replaced by twin all-metal single-step floats of Karhumäki design and construction, with a rudder on port float.
POWER PLANT: One 190 hp Lycoming O-435A six-cylinder horizontally-opposed air-cooled engine driving an Acromatic 220 variable-pitch airscrew.
ACCOMMODATION: Enclosed cabin seating four, two single seats in front with removable dual controls and a full-width seat aft. Entrance door on each side. Two baggage compartments. Cabin heating and ventilation. Radio fitted as standard.
Two prototypes were completed, the first, registered OH-VKK and named Nalle, was flown for the first time by Uuno Karhumäki (the youngest of the Karhumäki brothers) on July 20, 1948. The second, which flew later that year, was registered OH-VKL and named Tavi. Planned production did not materialize by the import of cheap military surplus aircraft, and subsequently both aircraft were used by Karhumäki.
Karhumäki Karku 48B (OH-VKL c/n 6) “Tavi”
OH-VKL eventually had its wing modified and was redesignated Karhu 48B, it was reregistered OH-KUA in 1961 when it was sold to O. Marjamäki in Vilppula. After being deregistered in 1973, the aircraft eventually ended up at the Suomen Ilmailumuseo (Finnish Aviation Museum), restored by Karair in 1988 into the original livery and registration.
Landplane Span: 37 ft 10 in (11.54 m) Length: 25 ft 9 in (7.85 m) Wing area: 186.25 sq.ft (17.31 sq.m) Weight empty: 1,789 lb (813 kg) Weight loaded: 2,882 lb (1,310 kg) Max speed: 142 mph (229 kmh) Cruising speed: 116 mph (186 kmh) Landing speed: 48 mph (78 kmh) Service ceiling: 15,745 ft (4,800 m) Cruising range: 435 mls (700 km)
Seaplane Span: 37 ft 10 in (11.54 m) Length: 26 ft 6.5 in (8.10 m) Wing area: 186.25 sq.ft (17.31 sq.m) Weight empty: 1,991 lb (905 kg) Weight loaded: 3,080 lb (1,400 kg) Max speed: 126 mph (203 kmh) Cruising speed: 109 mph (176 kmh) Alighting speed: 52 mph (83 kmh) Service ceiling: 13,780 ft (4,200 m) Cruising range: 404 mls (650 km).
Karhu 48B Engine: 1 × Avco Lycoming O-435A 6-cyl. air-cooled horizontally-opposed piston engine, 140 kW (190 hp) Propeller: 2-bladed Aeromatic 220 variable-pitch Length: 7.85 m (25 ft 9 in) (landplane) Wingspan: 11.54 m (37 ft 10 in) Wing area: 17.31 sq.m (186.3 sq ft) Max takeoff weight: 1,310 kg (2,888 lb) Maximum speed: 229 km/h (142 mph; 124 kn) Cruising speed: 186 km/h (116 mph; 100 kn) Range: 700 km (435 mi; 378 nmi) Service ceiling: 4,800 m (15,748 ft) Crew: 1 Capacity: 3 passengers
In 1994 the development of the all-metal UL aircraft KP-2U SOVA was started. Three prototypes were built: two for the test flights and one for the strength tests. The first test flight of the SOVA was done in May 1996. In September 1997 the aircraft obtained the type certificate by the UL-2 regulations from the Air Amateur Association of the Czech republic. In June 1977, KAPPA77 a.s. was founded and the KP-2U entered serial production. After the KAPPA 77 a.s. was declared bankruptcy on 16 February 2005, the company Jihlavan airplanes, s.r.o. was founded on 2 March 2005 with the main objective – to proceed in the production of the ultralight aircraft KP 2U SOVA. On 1 April 2005, the Jihlavan airplanes, s.r.o. became the holder of the manufacture rights, intellectual properties, etc. of the KP-2U. Over 160 airplanes of the Kappa KP-2U versions were built. After Jihlavan took over the production of the aircraft it was renamed as the Rapid KP-2U.
The Kappa KP-2UR Sova is a side-by-side two-seat low-wing ultralight aeroplane, featuring variable-pitch three blade composite prop, retractable trailing link tricycle undercarriage and fowler flaps. The all-metal aircraft is delivered in airworthy condition, with electro-retractable landing gear with hydraulic brakes, mechanically controlled Fowler flaps, removable wings with winglets, dual control and an elevator with electro-controlled trim tab. Both fabric-covered seats are adjustable, with four-point safety belts. 2009 Price: 49000 EURO
KP 2U
The KP 2V SOVA structure is entirely riveted dural tube. The side by side two seater is equipped with retractable undercarriage and Fowler flaps with a GAW 1 profile.
The Ka-226 as a derivative of the Ka-26, has gas turbine engines, installation of new, aerodynamically more perfect, rotors, arrangement of new on-board avionics package and provision for comfortable conditions for the pilot and passengers. The Ka-226 has a coaxial rotor scheme with two three-blade rotors of 13-m diameter. The polymeric composite blade with advanced aerodynamic profile is semi-rigidly attached to the hub by a torsion bar. The helicopter features modular design (detachable transport-passenger cabin) and four-leg non-retractable landing gear. The helicopter is equipped with up-to-date on-board equipment package and complies with the national aviation standards, as well as FAR requirements, categories A and B. The Ka-226 was announced at the 1990 Helicopter Association International convention, Dallas, USA, and developed originally for the Russian TsENTROSPAS disaster relief ministry, which provided significant funding. First flown (RA-00199), at Lyubertsy, on 3 September 1997, the “official” first flight was on the following day. The prototype flew four sorties by 31 December 1997, and began AP-29 certification testing on 28 March 2001. State ground testing of Ka-226 second prototype was completed at Strela’s Orenburg plant on 6 March 2000. KAPP built two prototypes, of which the first was rolled out at Kumertau on 29 May 1998. The first production aircraft from KAPP was due to have flown in the first quarter of 2002 but remained under construction in mid-2002. Planned certification in third quarter of 2002 was not achieved, being reportedly “seriously delayed”. The prototype was destroyed in ground resonance incident in November 2002.
Named Sergei in 1999, honouring politician Sergei Shoigu, the programme was also guided by Sukhoi General Designer, Sergei Mikheev. By mid-2000, Moscow regional government had provided Rb 12 million in development funding and was beginning disbursements under second programme valued at Rb4 million. Initial deliveries due in first half of 2000, but not effected. Prototypes built jointly by Kamov, Strela, KAPP and Ufa Motors, with final assembly by KAPP and Strela for production aircraft.
Strela scheduled to have delivered five preproduction helicopters to Kamov at Lyubertsy by mid-2000; these for MChS Rossii but not supplied until 2003, when one exhibited at MAKS ’03. KAPP designated second production plant; first batch of five under construction by 2001. Motor-Sich of Zaporozhye, Ukraine, negotiated with Kamov in June 2000 to build Ka-226s powered by indigenous ZMKB AI-450 engine; agreement on AI-450 installation signed 15 August 2001. On 19 October 2001, however, Motor Sich announced it would source all Ka-226 components with Ukrainian industry, if decision to proceed were taken. Programme launch was reportedly imminent in late 2002. MoU on use of Turbomeca Arrius 2G signed in August 2001 with NPO Saturn and French manufacturer; collaboration agreement followed on 16 April 2002, with intention of certifying Arrius Ka-226 in September 2004 after trials of three prototypes. Orders by January 2002 totalled 66: Gazprom 50, Moscow City 10, TsENTROSPAS five and Bashkiriya one. Identified requirements include up to 20 for City of Moscow for patrol and medevac; some 250 for MChS Rossii/TsENTROSPAS disaster relief organisation; and up to 75 for Gazprom in gasfield support role. Firm order for 25 reportedly received from TsENTROSPAS by 1997, but quantity had reduced to 10 by 1999; by mid-2000 this quoted as five firm (to be first five production aircraft) and further 15 to be ordered by 2002; manufacture by Strela which had completed first two (including one in medevac configuration) by early 2002. Bashkiriyan local government ordered one Ka-226-50 in September 2001; this accepted 28 December 2001 (when still not cleared for flight) and due for trials at Zhukovsky before service entry. Funds for 22 of initial Gazprom order for 50 had been transferred by 2001, this initial batch, built by Strela, to have been received by 2005 (although formal signing of order for 50 was undertaken at Moscow Salon in August 2001). Moscow city government signed US$1.5 million order for 10 in December 2001, delivery over two years, but later announcement indicated that funds had not been earmarked; Moscow’s helicopters to be built by KAPP. City allocated initial Rb33 million in 2002 and intends to receive three helicopters in 2003, four in 2004 and final three in 2005. Ka-226 was beaten by Kazan Ansat in competition to supply new training helicopter to Russian armed forces, announced September 2001, although small number of Ka-226s required by Russian Navy. To 1999, development cost was Rb108 million. Featuring interchangeable mission pods. Refinements of the Ka-26/126 include a new rotor system with hingeless hubs and glass fibre/carbon fibre blades, changes to the shape of the nose, twin tailfins and rudders. Payload modules include an agricultural systems with a hopper capacity of 1,000 litres.
The Ka-226 features contrarotating coaxial three-blade rotors, a hinge rotor head with ‘rake’-type blade attachment, the Ka-26 blades of the initial series were to be succeeded by GFRP and CFRP blades with twin-contour spar, load-carrying rear section and electrothermal anti-icing. A rotor brake WAS standard, and non-folding blades. There was a three-stage gearbox with planetary gear trains, of alloy steel and aluminium casting, flange mounted with four load-carrying bolts. Accessories included cooling fan, hydraulic pump and AC generator. The engine input was 6,000 rpm. The flying controls were mechanical with irreversible hydraulic actuators. An automatic rotor constant-speed control, with a conventional four-channel control (longitudinal, lateral, cyclic and differential pitch). The two endplate fins and rudders are toed inward 15 degrees, with a non-controllable horizontal stabiliser. Airframe materials are primarily aluminium alloys, steel alloys and composite sandwich panels of GFRP with honeycomb filler. Rotor blade overhaul interval 2,000 hours; total life 6,000 hours, but to be extended by increments to 18,000 hours. The landing gear is a non-retractable four-wheel type. Main units, at rear, are carried by stub-wings. All four units embody oleo-pneumatic shock-absorber, the forward wheels have no brakes. The rear wheels have pneumatic brakes. Mainwheel tyres size 595 x 185 mm, pressure 2.5 bars + 1.0; forward wheel tyres size 300 x 125 mm, pressure 3.43 bars. Skis optional. Provision for large inflatable pontoons, across front of aircraft forward of front wheels and under each mainwheel. Forward units of castoring type, without brakes. Rear wheels have pneumatic brakes.
Two 335kW Rolls-Royce 250- C20R/2 turboshafts are side by side aft of rotor mast, with individual driveshafts to the rotor gearbox. Two 335kW Rolls-Royce 250-C20B engines were in the prototypes. The transmission rating is 626kW. Alternatively, two Progress (ZMKB) AI-450 turboshafts, each 331kW or two Turbomeca Arrius 2G (500 kW) or Klimov VK-800 turboshafts (588kW) may be fitted. Standard fuel capacity is 770 litres, in tanks above and forward of the payload module area. Provision for two external tanks, on sides of fuselage, has a total capacity of 320 litres.
The fully enclosed cabin has a rearward-sliding door each side, and normal operation is by a single pilot. A second seat and dual controls are optional. The cabin is ventilated, and warmed and demisted by air from a combustion heater, which also heats the passenger cabin when fitted. An air filter is fitted on the nose of the agricultural version. Space aft of cabin, between main landing gear legs and under transmission, can accommodate a variety of interchangeable payloads. A cargo/passenger pod accommodates four or six persons on folding sidewall seats, with provision for a seventh passenger beside pilot. Two clamshell doors are at the rear of the pod, with emergency exit each side and a hatch in the floor. An ambulance pod accommodates two stretcher patients, two seated casualties and a medical attendant. For agricultural work, a chemical hopper (capacity 1,000 litres) and dust spreader or spraybars are fitted in this position, on the aircraft’s CG. Flight deck pressurisation protects crew against chemical ingress. The aircraft can also be operated with either an open platform for hauling freight or hook for slinging loads at the end of a cable or in a cargo net. A single hydraulic system, with manual override, is for control actuators. The main electrical system is 27V 3kW DC, with a back-up 40Ah battery. A secondary system is 36/115V AC with two static inverters, and a 115/200V AC system with 16kVA generator (6kVA to power agricultural equipment and rotor anti-icing). Electrothermal rotor blade de-icing; hot air engine air intake anti-icing; alcohol windscreen anti-icing; electrically heated pitot. Pneumatic system for mainwheel brakes, tyre inflation, agricultural equipment control, pressure 39 to 49 bars.
The cost in 2000 for the Ka-226A was US$1.5 million.
The Ka-226-50 is an “improved” version.
Engine: 2 x Allison 250-C20B. Instant pwr: 313 kW. Rotor dia: 13 m. Fuselage length: 8.1m Height: 4.15m MTOW: 3400 kg Payload: 1300 kg Useful load: 1448 kg Max speed: 111 kts Max cruise: 104 kts Max range: 602 km HIGE: 6623 ft HOGE: 4197 ft Rate of climb: 11.7m/s Endurance: 4.6h Service ceiling: 16,557 ft Crew: 1 Pax: 7
Development began 1984 with an early mockup with two small turboshafts above the cabin. A single TVO-100 turboshaft was subsequently adopted. In 1985 a Romanian-Russian agreement of co-operation for manufacturing a utility helicopter derived from the Ka-26 was signed. In 1986 the ICA Brasov factory started development and manufacturing preparation. A ground test vehicle was completed early in 1986. The first flight of the prototype (SSSR-01963) was on 19 October 1988. The first Romanian aircraft was flown on 22 December 1988 and, with a second, was delivered to the USSR for testing.Serial production was started with 15 completed. The first of four Soviet-built preproduction Ka-126s first flew on 19 October 1988. A proposed Ka-128, differing only in a 722shp Turbomeca Arriel 1D1 turboshaft power plant and addition of an intermediate gearbox was abandoned.
Featuring contrarotating coaxial three-blade rotors, a hinge rotor head with ‘rake’-type blade attachment, the Ka-26 blades of the initial series were to be succeeded by GFRP and CFRP blades with twin-contour spar, load-carrying rear section and electrothermal anti-icing. A rotor brake WAS standard, and non-folding blades. There was a three-stage gearbox with planetary gear trains, of alloy steel and aluminium casting, flange mounted with four load-carrying bolts. Accessories included cooling fan, hydraulic pump and AC generator. The engine input was 6,000 rpm. The flying controls were mechanical with irreversible hydraulic actuators. An automatic rotor constant-speed control, with a conventional four-channel control (longitudinal, lateral, cyclic and differential pitch). The two endplate fins and rudders are toed inward 15 degrees, with a non-controllable horizontal stabiliser. Airframe materials are primarily aluminium alloys, steel alloys and composite sandwich panels of GFRP with honeycomb filler. The landing gear is a non-retractable four-wheel type. Main units, at rear, are carried by stub-wings. All four units embody oleo-pneumatic shock-absorber, the forward wheels of castoring type, self-centring, with no brakes. The rear wheels have pneumatic brakes. Mainwheel tyres size 595 x 185 mm, pressure 2.45 bars; forward wheel tyres size 300 x 125 mm, pressure 3.43 bars. Skis optional. Provision for large inflatable pontoons, across front of aircraft forward of front wheels and under each mainwheel. One 522kW Mars (Omsk) TV-O-100 turboshaft is installed centrally in a streamline fairing above the cabin. Electronic-hydraulic automatic two-channel control system, with manual control in case of electronic governor failure, is installed. A front driveshaft has a plate coupling to the gearbox. Fuel is in two forward and one aft tank, with a total capacity of 800 litres. There is provision for two external tanks, on sides of fuselage, total capacity 320 litres. A single-point main tank refuelling is on the port side of aft tank. The fully enclosed cabin has a rearward-sliding door each side, and normal operation is by a single pilot. A second seat and dual controls are optional. The cabin is ventilated, and warmed and demisted by air from a combustion heater, which also heats the passenger cabin when fitted. An air filter is fitted on the nose of the agricultural version. Space aft of cabin, between main landing gear legs and under transmission, can accommodate a variety of interchangeable payloads. A cargo/passenger pod accommodates four or six persons on folding sidewall seats, with provision for a seventh passenger beside pilot. Two clamshell doors are at the rear of the pod, with emergency exit each side and a hatch in the floor. An ambulance pod accommodates two stretcher patients, two seated casualties and a medical attendant. For agricultural work, a chemical hopper (capacity 1,000 litres) and dust spreader or spraybars are fitted in this position, on the aircraft’s CG. The aircraft can also be operated with either an open platform for hauling freight or hook for slinging loads at the end of a cable or in a cargo net. A single hydraulic system, with manual override, is for control actuators. The main electrical system is 27V 3kW DC, with a back-up 40Ah battery. A secondary system is 36/115V AC with two static inverters, and a 115/200V AC system with 16kVA generator (6kVA to power agricultural equipment and rotor anti-icing). Electrothermal rotor blade de-icing; hot air engine air intake anti-icing; alcohol windscreen anti-icing; electrically heated pitot. Pneumatic system for mainwheel brakes, tyre inflation, agricultural equipment control, pressure 39 to 49 bars. After 1989 the project was cancelled.
Ka-126
Engine: 1 x Koptchencko TV-O-100. nstant pwr: 537 kW. Rotor dia: 13 m. MTOW: 4250 kg. Payload: 1000 kg. Useful load: 1335 kg. Max speed: 97 kts. Max cruise: 86 kts. Max range: 713 km. HIGE: 3180 ft. HOGE: 262 ft. Service ceiling: 12,623 ft. Crew: 1. Pax: 7.
The Ka-115 is a light multi-purpose helicopter equipped with landing skids. It is powered by Pratt & Whitney/Klimov PW 206K/2 engine (Canada/Russia production), and features a large five-door cabin with large windows. In terms of payload-to-weight ratio the helicopter is comparable to its world counterparts. The cabin is fitted with heating and ventilation systems. High rotor system efficiency, absence of power losses for the tail rotor drive, combined with smooth aerodynamic shape of the airframe and economic engine give the helicopter fuel flow characteristic of less than 0.5kg per km at a cruise speed of 230km/h. A de-icing system of the rotor blades, engine inlet particle separator and air conditioning system make the helicopter capable of operating in any climatic region within a 50 degree temperature range. The helicopter complies with international standards on reliability, safety and comfortable conditions for pilot and passengers.
Ka-115 Engines: 1 x PW/K 206D turboshaft, 477kW Rotor diameter: 9.5m Fuselage length: 9.2m Height: 3.6m Width: 2.0m Max take-off weight: 1850kg Max speed: 250km/h Cruising speed: 230km/h Rate of climb: 11.5m/s Service ceiling: 5200m Range: 780km Payload: 700-900kg Crew: 1 Passengers: 5
Ka-115 Engine: 1 x P&W/Klimov PW206K/2. Instant pwr: 410 kW. Rotor dia: 9.5 m. MTOW: 1850 kg. Payload: 600 kg. Useful load: 878 kg. Max speed: 135 kts. Max cruise: 124 kts. Max range: 780 km. HIGE: 10,164 ft. HOGE: 7541 ft. Service ceiling: 17,049 ft. Crew: 1. Pax: 4/5.
Funded under the Russian programme for development of civil aviation for 2000, construction of the prototype Ka-62 (then known as V-62) began early 1990, but apparently was abandoned. One Ka-60 military version and two Ka-62s were intended to undertake flight trials, although the second of the basic type was completed as a Ka-60U, delaying the debut of the civil version. In April 2001, The Turkish Ministry of Public Health was discussing a contract for six Ka-62s, with a total value of US$31.5 million. The Russian government’s 2002-10 aviation plan included Rb62 million to develop the Ka-62 and Rb51 million to launch production at UUAP and, possibly, RSK “MiG” (LAPIK).
The Ka-62 was developed on the basis of the Ka-60 army helicopter and is intended for carrying passengers and cargo in the transport cabin, and transportation of bulky cargo on external sling. It has a single main rotor with a multi-blade tail rotor in the tail ring. The rotor blades and 60% of the airframe weight are made of polymeric composite materials. The airframe features perfect aerodynamic outlines, large transport-passenger cabin and retractable three-leg landing gear. The power plant is made of modular-design developed by Rybinsk Motor Design Bureau, headed by Mr. A. Novikov, Designer General. The civil derivative has large door openings on both fuselage sides of the cabin. The helicopter is equipped with anti-icing and fire-fighting systems. The Ka-62 is equipped with standard avionics suite of a basic transport version for VFR conditions, or for IFR flying, using the satellite navigational equipment. The export version of the helicopter is supplied with western engines and avionics of the customer’s option.
Originated as a military transport, all main systems and components are duplicated, with main and secondaries routed on opposite sides of airframe. The transmission is resistant to 12.7mm bullets and main blades to 23mm shells. The gearboxes have a run-dry capacity. The main rotor blades have sweptback tips. Yaw control is by 11-blade fan-in-fin. Landing gear is retractable tricycle tailwheel. Composites account for 60%, by weight, of the structure, including blades of main rotor, fuselage sides, doors, floor and roof, tailboom, fin, vertical stabilisers, and fan blades of carbon-reinforced Kevlar.
Retractable reverse tricycle type; Single KT-217 mainwheels retract inward and upward into the bottom of the fuselage and twin rear wheels retract forward into the tailboom. Shock absorbers are in each unit. An option is inflatable pontoons for emergency use on water. The basic Ka-62 has two RKBM Rybinsk RD-600V turboshafts, each 956kW max continuous, 1,140kW emergency rating. Fuel tanks are under the floor, with a 1,450 litres capacity. General Electric T700/ CT7-2D1 engines are offered as an alternative to the RD-600V. The crew of one or two, side by side, have an optional bulkhead divider between the flight deck and the cabin. The cabin holds up to 14 passengers in four rows. A forward-hinged door is on each side of the flight deck, and a large forward-sliding door and small rearward-hinged door are on each side of the cabin. There is a baggage hold to the rear of the cabin. The interior is heated and air conditioned. A thermoelectric de-icing system is optional. An Ivchenko AI-9V APU was originally proposed, but a replacement Aerosila TA-14 was under development.
Ka-62 Passengers: 16 Engines: 2 x Rybinsk RD-600 turboshaft, 955kW Main rotor diameter: 13.5m Fuselage length: 13.25m Height: 4.1m Max take-off weight: 6250kg Empty weight: 3730kg Max speed: 162 kts Cruising speed: 140 kts Rate of climb: 11.7m/s HIGE: 9508 ft. HOGE: 6885 ft. Service ceiling: 5000m / 16,885 ft. Range: 720km Payload: 2000-2500kg Crew: 1-2 Pax: 14
