Lycoming O-235

Last updated
O-235
AVCOLycomingO-235C2CPhoto01.jpg
A Lycoming O-235-C2C engine mounted in an American Aviation AA-1 Yankee light aircraft.
TypeCertified piston aero-engine
National origin United States
Manufacturer Lycoming Engines
First run1941
Major applications Cessna 152
Piper Tomahawk
Beechcraft Skipper
Produced1942–present
Developed from Lycoming O-233
Developed into Lycoming IO-233

The Lycoming O-235 is a family of four-cylinder, air-cooled, horizontally opposed piston aircraft engines that produce 100 to 135 hp (75 to 101 kW), derived from the earlier O-233 engine. [1] [2]

Contents

Well-known designs that use versions of the O-235 included the Cessna 152, Grumman American AA-1 series, Beechcraft Model 77 Skipper, Piper Tomahawk, American Champion Citabria, Piper Clipper, and the Piper PA-22-108 Colt.

Development

The engines are all carburetor-equipped, feature dual magneto ignition and have a displacement of 233 cubic inches (3.82 L). The first O-235 model was certified on 11 February 1942. [2]

The O-235 was developed into the lighter-weight Lycoming IO-233 engine for light sport aircraft. [3]

Variants

O-235-C1
Power 115 hp (86 kW) at 2800 rpm, dry weight 246 lb (112 kg) Provision for dual pump drives, tractor and pusher installation. [2]
O-235-C1A
Power 100 hp (75 kW) at 2450 rpm, dry weight 236 lb (107 kg) Similar to O-235-C1 except ignition timing, lower rpm and power. Optional 2 position or automatic propeller governor drive. [2]
O-235-C1B
Power 115 hp (86 kW) at 2800 rpm, dry weight 245 lb (111 kg) Similar to O-235-C1 except with retarded breaker magnetos. [2]
O-235-C1C
Power 108 hp (81 kW) at 2600 rpm, dry weight 243 lb (110 kg) Similar to O-235-C1 except with Slick magnetos. [2]
O-235-C2A
Power 115 hp (86 kW) at 2800 rpm, dry weight 246 lb (112 kg) Similar to O-235-C1 except with a type 1 propeller flange. [2]
O-235-C2B
Power 115 hp (86 kW) at 2800 rpm, dry weight 247 lb (112 kg) Similar to O-235-C2A but with two S-1200 series magnetos. [2]
O-235-C2C
Power 108 hp (81 kW) at 2600 rpm, alternate rated maximum continuous power rating of 100 hp at 2400 rpm, dry weight 244 lb (111 kg) Similar to O-235-C2B except with Slick magnetos and shielded ignition harness. [2]
O-235-E1
Power 115 hp (86 kW) at 2800 rpm, dry weight 250 lb (113 kg) Similar to O-235-C1 except crankcase and crankshaft supply pressurized oil to a constant speed propeller. Accessory case changed to accommodate a standard propeller governor drive. [2]
O-235-E1B
Power 115 hp (86 kW) at 2800 rpm, dry weight 249 lb (113 kg) Similar to O-235-E1 except for S4LN-200 series retarded breaker magnetos. [2]
O-235-E2A
Power 115 hp (86 kW) at 2800 rpm, dry weight 250 lb (113 kg) Similar to O-235-E1 except Type 1 propeller flange. [2]
O-235-E2B
Power 115 hp (86 kW) at 2800 rpm, dry weight 251 lb (114 kg) Similar to O-235-E2A except incorporates S-1200 series magnetos. [2]
O-235-F1
Power 125 hp (93 kW) at 2800 rpm, dry weight 250 lb (113 kg) Similar to O-235-C1 except compression ratio, fuel grade and rating. [2]
O-235-F1B
Power 125 hp (93 kW) at 2800 rpm, dry weight 249 lb (113 kg) Similar to O-235-F1 except retarded breaker magnetos. [2]
O-235-F2A
Power 125 hp (93 kW) at 2800 rpm, dry weight 250 lb (113 kg) Similar to O-235-F1 except a Type 1 propeller flange. [2]
O-235-F2B
Power 125 hp (93 kW) at 2800 rpm, dry weight 251 lb (114 kg) Similar to O-235-F2A but with S-1200 series magnetos. [2]
O-235-G1
Power 125 hp (93 kW) at 2800 rpm, dry weight 253 lb (115 kg) Similar to O-235-F1 except provisions for using constant speed propeller. [2]
O-235-G1B
Power 125 hp (93 kW) at 2800 rpm, dry weight 252 lb (114 kg) Similar to O-235-G1 except has retarded breaker magnetos. [2]
O-235-G2A
Power 125 hp (93 kW) at 2800 rpm, dry weight 253 lb (115 kg) Similar to O-235-G1 except a Type 1 propeller flange. [2]
O-235-G2B
Power 125 hp (93 kW) at 2800 rpm, dry weight 254 lb (115 kg) Similar to O-235-G2A except S-1200 series magnetos. [2]
O-235-H2C
Power 108 hp (81 kW) at 2600 rpm, alternate rated maximum continuous power rating of 100 hp at 2400 rpm, dry weight 243 lb (110 kg) Similar to O-235-C2C except Type 1 dynafocal mounting. [2]
O-235-J2A
Power 125 hp (93 kW) at 2800 rpm, dry weight 252 lb (114 kg) Similar to O-235-J2B except magnetos. [2]
O-235-J2B
Power 125 hp (93 kW) at 2800 rpm, dry weight 253 lb (115 kg) Similar to O-235-F2B except Type 1 dynafocal mounting. [2]
O-235-K2A
Power 118 hp (88 kW) at 2800 rpm, dry weight 252 lb (114 kg) Similar to O-235-F2A except ignition timing, lower power and reduced compression ratio. [2]
O-235-K2B
Power 118 hp (88 kW) at 2800 rpm, dry weight 253 lb (115 kg) Similar to O-235-F2B except ignition timing, lower power and reduced compression ratio. [2]
O-235-K2C
Power 115 hp (86 kW) at 2700 rpm, dry weight 248 lb (112 kg) Similar to O-235-K2A except Slick magnetos. [2]
O-235-L2A
Power 118 hp (88 kW) at 2800 rpm, alternate ratings of 115 hp (86 kW) at 2700 rpm, 112 hp (84 kW) at 2600 rpm, 110 hp (82 kW) at 2550 rpm and 105 hp (78 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-J2A except ignition timing, lower power and reduced compression ratio. [2]
O-235-L2C
Power 115 hp (86 kW) at 2700 rpm, alternate ratings of 115 hp (86 kW) at 2700 rpm, 112 hp (84 kW) at 2600 rpm, 110 hp (82 kW) at 2550 rpm and 105 hp (78 kW) at 2400 rpm, dry weight 249 lb (113 kg) Similar to O-235-L2A except Slick magnetos and lower maximum continuous rating. [2]
O-235-M1
Power 118 hp (88 kW) at 2800 rpm, alternate ratings of 115 hp (86 kW) at 2700 rpm, 112 hp (84 kW) at 2600 rpm, 110 hp (82 kW) at 2550 rpm and 105 hp (78 kW) at 2400 rpm, dry weight 255 lb (116 kg) Similar to -L2A except provision for controllable propeller and has AS-127 Type 2 propeller flange. [2]
O-235-M2C
Power 118 hp (88 kW) at 2800 rpm, alternate ratings of 115 hp (86 kW) at 2700 rpm, 112 hp (84 kW) at 2600 rpm, 110 hp (82 kW) at 2550 rpm and 105 hp (78 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-M1 except Slick 4200 series magnetos and Type 1 propeller flange. [2]
O-235-M3C
Power 118 hp (88 kW) at 2800 rpm, alternate ratings of 115 hp (86 kW) at 2700 rpm, 112 hp (84 kW) at 2600 rpm, 110 hp (82 kW) at 2550 rpm and 105 hp (78 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-M1 except Slick 4200 series magnetos. [2]
O-235-N2A
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-L2A except reduced compression ratio and reduced power ratings. [2]
O-235-N2C
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 249 lb (113 kg) Similar to O-235-L2C except reduced compression ratio and reduced power ratings. [2]
O-235-P1
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 255 lb (116 kg) Similar to O-235-M1 except reduced compression ratio and reduced power ratings. [2]
O-235-P2A
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 255 lb (116 kg) Similar to O-235-P1 except a Type 1 propeller flange. [2]
O-235-P2C
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-M2 except reduced compression ratio and reduced power ratings. [2]
O-235-P3C
Power 116 hp (87 kW) at 2800 rpm, alternate ratings of 113 hp (84 kW) at 2700 rpm, 110 hp (82 kW) at 2600 rpm, 108 hp (81 kW) at 2550 rpm and 103 hp (77 kW) at 2400 rpm, dry weight 252 lb (114 kg) Similar to O-235-M3C except reduced compression ratio and reduced power ratings. [2]

Applications

Specifications (O-235-C series)

Data fromOperator's Manual, Textron Lycoming Aircraft Engines. [1]

General characteristics

Components

Performance

See also

Comparable engines

Related lists

Related Research Articles

Lycoming XR-7755

The Lycoming XR-7755 was the largest piston aircraft engine ever built in the United States, with 36 cylinders totaling about 7,750 in³ (127 L) of displacement and a power output of 5,000 horsepower (3,700 kilowatts). It was originally intended to be used in the "European bomber" that eventually emerged as the Convair B-36. Only two examples were built before the project was terminated in 1946.

Lycoming O-320

The Lycoming O-320 is a large family of naturally aspirated, air-cooled, four-cylinder, direct-drive engines produced by Lycoming Engines. They are commonly used on light aircraft such as the Cessna 172 and Piper Cherokee. Different variants are rated for 150 or 160 horsepower. As implied by the engine's name, its cylinders are arranged in horizontally opposed configuration and a displacement of 320 cubic inches (5.24 L).

Lycoming O-540 Family of flat-six piston aircraft engines

The Lycoming O-540 is a family of air-cooled six-cylinder, horizontally opposed fixed-wing aircraft and helicopter engines of 541.5 cubic inch displacement, manufactured by Lycoming Engines. The engine is a six-cylinder version of the four-cylinder Lycoming O-360.

The Lycoming O-290 is a dual ignition, four-cylinder, air-cooled, horizontally opposed aircraft engine. It was first run in 1939, and entered production three years later.

Continental A40

The Continental A40 engine is a carbureted four-cylinder, horizontally opposed, air-cooled aircraft engine that was developed especially for use in light aircraft by Continental Motors. It was produced between 1931 and 1941.

Continental O-240

The Continental O-240 engine is a four-cylinder, horizontally opposed, air-cooled aircraft engine that was developed in the late 1960s for use in light aircraft by Continental Motors, Inc. The first O-240 was certified on 7 July 1971.

Lycoming O-145

The Lycoming O-145 is a family of small, low-horsepower, four-cylinder, air-cooled engines. It was Lycoming Engines' first horizontally opposed aircraft engine and was produced from 1938 until the late 1940s. The family includes the reduction-geared GO-145. The O-145 received its Approved Type Certificate on 13 Jun 1938.

Continental IO-360

The Continental IO-360 is a family of fuel-injected air-cooled, horizontally opposed six-cylinder aircraft engines manufactured by Continental Motors in the United States of America, now part of AVIC International since 2010.

Continental O-470

The Continental O-470 engine is a family of carbureted and fuel-injected six-cylinder, horizontally opposed, air-cooled aircraft engines that was developed especially for use in light aircraft by Continental Motors. Engines designated "IO" are fuel-injected.

Continental IO-550

The Continental IO-550 engine is a large family of fuel injected six-cylinder, horizontally opposed, air-cooled aircraft engines that were developed for use in light aircraft by Teledyne Continental Motors. The first IO-550 was delivered in 1983 and the type remains in production.

Lycoming IO-580

The Lycoming IO-580 engine is a horizontally opposed, six-cylinder aircraft engine featuring three cylinders per side, manufactured by Lycoming Engines.

Lycoming IO-390

The Lycoming IO-390 engine is a horizontally opposed, four-cylinder aircraft engine, manufactured by Lycoming Engines.

Lycoming TIO-541

The Lycoming TIO-541 engine is a turbocharged, fuel-injected, horizontally opposed, six-cylinder aircraft engine featuring three cylinders per side, manufactured by Lycoming Engines.

Lycoming IO-233

The Lycoming IO-233 is a non-certified four-cylinder, air-cooled, horizontally opposed piston aircraft engine that produces between 100 hp (75 kW) and 116 hp (87 kW).

The Lycoming O-340 is a family of four-cylinder horizontally opposed, carburetor-equipped aircraft engines, that was manufactured by Lycoming Engines in the mid-1950s.

Packard X-2775 Experimental aircraft engine

The Packard X-2775 was an American experimental liquid-cooled aircraft engine. The engine was constructed as a single crankcase with four banks of six cylinders in what is close to an X-configuration. The engine was an upright 60 degree vee-12 and an inverted 60 degree vee-12 sharing a common crankcase. Although technically incorrect, the engine has been characterized as two Packard 1A-1500 V-12 engines coupled with a mutual crankcase.

Superior Air Parts Vantage

The Superior Air Parts Vantage is a type certified piston aircraft engine developed by Superior Air Parts of Coppell, Texas, United States and based upon the non-certified Superior Air Parts XP-360. The design is officially designated the Superior Air Parts O-360 and IO-360. Vantage is a marketing name.

Lycoming DEL-120

The DEL-120 is an aircraft diesel engine with propeller speed reduction unit produced by Lycoming Engines. Using automotive technology and initially powering unmanned aircraft. DEL-120 is a non-certified engine and is meant for military use only, there is no civil application of this engine.

The Extra NG is a two-seat German aerobatic monoplane designed by Walter Extra and built by Extra Aerobatic Aircraft.

References

  1. 1 2 Textron Lycoming: Operator's Manual, Textron Lycoming Aircraft Engines, Series O-235 & O-290, 4th Edition January 1988, Pages 2-1 & 2-4, Stock # 60297-9, Textron Lycoming.
  2. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 Federal Aviation Administration (December 2003). "TYPE CERTIFICATE DATA SHEET NO. E-223" (PDF). Retrieved 2008-11-30.
  3. Lycoming Engines (July 2008). "Lycoming Engines Launches the IO-233-LSA". Archived from the original on 2010-11-26. Retrieved 2009-04-03.