|HKS 700E mounted on a Flightstar II|
|Type||Twin cylinder four-stroke aircraft engine|
The HKS 700E is a twin-cylinder, horizontally opposed, four stroke, carburetted aircraft engine, designed for use on ultralight aircraft, powered parachutes and ultralight trikes. The engine is manufactured by HKS, a Japanese company noted for its automotive racing engines.
The HKS 700E has dual capacitor discharge ignition, dual carburetors and electric start. The engine is mainly air-cooled, but with oil-cooled cylinder heads. The OHV pushrod engine has four valves per cylinder, and nickel-ceramic coated cylinder bores. Lubrication is dry sump, with a trochoid pump.
The reduction drive is a choice of two integral gearboxes: the A-type gearbox has a 2.58:1 ratio and can accommodate propellers of up to 4,000 kg/cm2 inertial load; the B-type gearbox has a 3.47:1 ratio and can accommodate propellers of up to 6,000 kg/cm2.
Producing 60 hp (45 kW) at 6,200 rpm for three minutes for take-off and 56 hp (42 kW) at 5,800 rpm continuously, the 700E was designed as a fuel efficient four stroke alternative to the high fuel consumption two stroke engines, such as the Rotax 582.
HKS 700E engines from serial number 101105 and above meet ASTM standard 2339-05, which governs the design and manufacture of reciprocating engines for light-sport aircraft. Compliance with the ASTM standard means the aircraft is applicable for use on special or experimental light-sport aircraft (S-LSA or E-LSA).
The company's owner's manual disclaimer states:
WARNING! This is a non-certified aircraft engine, the possibility of engine failure exists at all times. Do not operate this engine over densely populated areas. Do not operate this engine over terrain where a safe, power off landing cannot be performed. The operating and maintenance instructions supplied with this engine must be followed at all times. Flying any aircraft involves the risk of injury or death, building and maintaining your own aircraft requires great personal responsibility.
- Initial version, normally aspirated and producing 60 hp (45 kW) at 6200 rpm for three minutes for take-off and 56 hp (42 kW) at 5800 rpm continuously.
- Turbocharged version with a 62.5 mm (2.5 in) stroke and a compression ratio of 8.8:1, that produces 80 hp (60 kW) at 5300 rpm for three minutes for take-off and 77 hp (57 kW) at 4900 rpm continuously. The engine's dry weight is 57.5 kg (127 lb) equipped with electrical system, electric starter, fuel injectors, gearbox, exhaust system and turbocharger. The initial time between overhauls is recommended as 500 hours, but this is expected to rise with operational experience.
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- Type: Two cylinder, four-stroke aircraft engine
- Bore: 85 mm (3.3 in)
- Stroke: 60 mm (2.4 in)
- Displacement: 680 cc (41.49 cu in)
- Dry weight: 55 kg (121 lb) equipped with electrical system, electric starter, carburetors, gearbox, exhaust system, oil tank and cooler
- Valvetrain: two intake and two exhaust valves per cylinder
- Fuel type: unleaded auto fuel
- Oil system: dry sump with a trochoid pump
- Cooling system: free air cylinders, with oil-cooled cylinder heads
- Reduction gear: A-type gearbox with 2.58:1 ratio, limit of 4,000kg/cm2 inertial load. The B-type gearbox with 3.47:1 ratio, limit of 6,000kg/cm2 inertial load
- Power output: 60 hp (45 kW) at 6200 rpm for three minutes for take-off and 56 hp (42 kW) at 5800 rpm continuous
- Compression ratio: 11.3:1
- Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page G-9 Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
- HKS (n.d.). "HKS Aviation". Archived from the original on 1999-10-13. Retrieved 2009-12-25.
- HKS (2011). "HKS 700E Specifications". Retrieved 27 February 2014.
- HKS Engines Compliance Statement July,2006
- HKS Aviation Co. (2011). "HKS 700T four stroke turbo power". Retrieved 3 January 2012.
- HKS Aviation Co. (2011). "HKS 700T Specifications". Retrieved 3 January 2012.
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