Ka-62
36Pages

^ HELICOPTERS technical data 3.6 Power supply system 14 4.2 Helicopter equipment control system 17 4.4 Radio communication equipment 18 4.5 Onboard equipment suite 19 6. Painting scheme variants 24 7. Helicopter application variants 25 10. Service life of helicopter and components 34 ©JSC “Russian Helicopters” 3

The information provided here is not a technical or commercial proposal, has general nature and may vary depending on the sale conditions. By publishing this technical information, JSC “Russian Helicopters” makes no official statements and gives no express or implied warranty, including but not limited to any warranties of merchantability or fitness for a particular customer purpose, as well as any warranty regarding the information set forth in this document related to the described products and services. Correspondingly, JSC "Russian Helicopters” is not liable for damage of any kind or...

The new Ka-62 medium-class utility helicopter embodies the latest achievements in the world's aviation industry. Ka-62 complies with Russian and international airworthiness requirements (AP-29, CS-29, JAR-OPS3), rules of offshore operations, international standards in reliability, service life, flight safety, comfort conditions, maintenance and serviceability. Wide range of helicopter missions • transportation of passengers, including in the conditions of enhanced comfort; • internal and external cargo transportation; • patrolling and environmental monitoring; • search and rescue; •...

2. Retractable tailwheel landing gear 5. Spacious luggage compartment 6. Fan-in-fin multiblade rotor 8. Five-blade main rotor 9. Ardiden 3G turbo shaft engines 10. Shock absorbing seats

2. Flight performanceFlight performance (metric) WEIGHT AND DIMENSION PARAMETERS Normal take-off weight, kg 6,500 Main rotor with 4th-gen blade profiles 5 blades Fan-in fin tail rotor 12 blades ENGINES (2 xArdiden3G equipped with dual channel Full Authority Digital Engine Control (FADEC) ^ Take-off rating (5 min), kW Maximum continuous rating (unlimited), kW Power with OEI (2.5 min), kW Continuous power with OEI, kW Continuous take-off power (30 min), kW normal take-off weight maximum take-off weight Service ceiling, m Hovering ceiling (OGE), m VNE, km/h Cargo capacity at the external...

WEIGHT AND DIMENSION PARAMETERS MTOW, lb Normal take-off weight, lb Main rotor with 4th-gen blade profiles Fan-in fin tail rotor ENGINES (2x Ardiden 3G equipped with dual channel Full Authority Digital Engine Control (FADEC) Maximum continuous rating (unlimited), hp Continuous power with OEI, hp Continuous take-off power (30 min), hp normal take-off weight maximum take-off weight Cargo capacity at the external sling, lb Cruise speed at max continuous rating, knots Flight range (Vecon, standard fuel, no reserve), nm Ferry range (standard fuel plus auxiliary fuel tanks 60 I, no reserve), nm...

The helicopter fuselage has a semi-monocoque design. The outer fuselage contours are formed by large-sized polymeric composite material panels. 60% of the fuselage structure is made of polymeric composite materials. Panels are mounted on metal elements of framework in the form of frames and diaphragms interlinked by longitudinal strength elements. Components which bear high concentrated loads are made of titanium alloy. For corrosion resistance, all parts of the airframe are protected by coating systems individually selected for each type of material and approved by VIAM (All-Russian...

technical data 3.2 Ka-62 helicopter. Main dimensions

The helicopter features a tail-wheel retractable landing gear absorbing impact energy during helicopter landing and taxiing on unpaved, concrete and special runways with a soil density not less than 4 kg/cm2. The landing gear consists of two main struts and one tail strut that can partially retract into the fairings in flight for the reduction of aerodynamic resistance. The main LG wheels are fitted with brakes. The LG design ensures increased shock absorbing capability during a crash landing. 3.3 Engines The helicopter power plant consists of two new-gen Ardiden 3G turboshaft engines by...

technical data 3.5 Fuel system The helicopter is fitted with crashworthy fuel system by SAFRAN AEROSYSTEMS. The fuel system is designed and successfully tested as per the AP-29/CS-29/FAR-29 requirements. To increase flight range, the luggage compartment can fit an additional crashworthy fuel tank with capacity up to 200 liters. In ferry configuration two more auxiliary tanks can be installed in the transportation cabin (option). The system comprises the following key elements: • seven fuel tanks divided in two independent fuel sub-systems; • system of gravity fueling (pressure fueling as an...

3.6 Power supply system The main power supply system provides direct current. Main sources of DC: • two starter-generators with a capacity of 8.5 kW installed on the engines with GCUs. Provide engine startup and connect to corresponding buses of central distribution devices; • two storage batteries with a capacity of 40 Ah installed in two battery compartments located under the nose fairing. Storage batteries' capacity is enough to power Cat-1 consumers for at least 30-min flight in case of power generating system failure; • switch and security blocks of General Helicopter Equipment...

technical data 4. Avionics suite 4.1 Instruments Crew cockpit accommodates: instrument panel, overhead panel, central console. The instrument panel consists of left, central and right parts. The controls, displays and alarms that the crew uses in flight are located on the instrument panel, the overhead panel and the central console. Some of the controls are on the collective pitch control stick and on the cyclic pitch control stick. The left and right parts of the instrument panel have multifunctional displays (MFDs) for output of flight control and navigation data to the pilot. The central...