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Lycoming IO-720 The Lycoming O-360 is a family of four-cylinder , direct-drive, horizontally opposed , air-cooled , piston aircraft engines . Engines in the O-360 series produce between 145 and 225 hp (110 and 170 kW), with the basic O-360 producing 180 hp (130 kW).
Same as the IO-360-A1B6 but it is equipped with an inverted oil system kit for aerobatic flight. [4] AEIO-360-A1C 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1C but it is equipped with an inverted oil system kit for aerobatic flight. [4] AEIO-360-A1D
Lycoming IO-360 A1B6 200 hp ... Data fromLA4-200 Airplane Flight Manual. ... Service ceiling: 14,700 ft (4,500 m) See also
The type certification for the P.68 Victor, a twin piston engine, high wing monoplane with fixed tricycle landing gear was applied for on 22 January 1969. [2] The Partenavia P.68 was designed as a six-seat light transport and trainer powered by two 200 hp (149 kW) Lycoming IO-360 engines, it made its first flight on 25 May 1970 at Naples. [1]
S.205 F/R-18: Avco Lycoming O-360 S.205 F/R-20: Avco Lycoming IO-360-A1A S.205 F/R-22: Franklin 6A-350C1 S.206 6-seat version, never realized S.208 5-seat version with a 260 hp engine and a retractable undercarriage S.208M military version for the Italian Air Force S.208AG agricultural version, also used as an aviation-ambulance. S.210 twin ...
The prototype of the Robin HR100 was the prototype DR253 Regent which was rebuilt with metal wings and powered by a 180 hp (134 kW) Lycoming O-360 engine. It first flew on 3 April 1969 as the Robin HR100/180. The HR100 is a low-wing cantilever monoplane with a conventional cantilever tail unit and a fixed tricycle landing gear.
The G-200's acceptable installed power range is 150 to 220 hp (112 to 164 kW) and the standard engine used is the 200 hp (149 kW) Lycoming IO-360 powerplant. [2] [4] The G-200 has an empty weight of 750 lb (340 kg) and a gross weight of 1,150 lb (520 kg), giving a useful load of 400 lb (180 kg).
This aircraft featured a constant-speed propeller and retractable landing gear and was powered by a 180 hp (130 kW) Lycoming IO-360-B1E engine. A 200 hp (150 kW) version powered by a Lycoming IO-360-C1C was offered as an option beginning in 1969 and designated the PA-28R-200; the 180 hp (130 kW) model was dropped after 1971. [17]