Lycoming O-435: Difference between revisions
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Revision as of 23:51, 27 February 2014
| O-435 | |
|---|---|
| |
| A Lycoming TVO-435 from a Bell 47G | |
| Type | Piston aircraft engine |
| Manufacturer | Lycoming Engines |
| First run | c.1942 |
| Major applications | Bell 47 |
| Developed from | Lycoming O-290 |
The Lycoming O-435 is a six-cylinder, horizontally opposed fixed-wing aircraft and helicopter engine made by Lycoming Engines. The engine is a six-cylinder version of the four-cylinder Lycoming O-290.
Design and development
The powerplant is a horizontally opposed Lycoming six-cylinder design. It is a direct-drive or geared, air-cooled, and normally aspirated engine. The cylinders have steel barrels with aluminum heads, and the valves are operated by hydraulic lifters. The crankshaft is supported in an aluminum-alloy split case by four main bearings and one ball-thrust bearing, and lubricating oil is supplied from a 12 quart wet sump. The camshaft rides in journals that do not employ bearing inserts. The accessory housing supports two magnetos, a starter, a generator, and a dual tach drive. A spare mounting pad is included for a vacuum pump.
Variants
All engines have an additional prefix preceding the 435 to indicate the specific configuration of the engine. There are also numerous engine suffixes, denoting different accessories such as different manufacturers' carburetors, or different magnetos.
- O-435-A
- O-435-C
- O-435-D
- GO-435
- GO-435-B
Applications
- Aircraft
- Other
- M22 Locust - tank
Specifications (O-435-D)
Data from Jane's.[1]
General characteristics
- Type: Six-cylinder horizontally-opposed gasoline piston engine
- Bore: 4.875 in (123.7 mm)
- Stroke: 3.875 in (98.4 mm)
- Displacement: 434 cu in (7.1 L)
- Width: 33.5 in (824 cm)
- Height: 43.5 in (1,105 cm)
- Dry weight: 433 lb (196.6 kg)
Components
- Valvetrain: Overhead valve, one inlet and one exhaust valve per cylinder
- Fuel system: Marvel-Schebler carburetor
- Fuel type: 100 octane gasoline
- Oil system: Pressure pump type
- Cooling system: Air-cooled by fan
- Reduction gear: Direct-drive
Performance
- Power output: 212 hp (158 Kw)at 3,000 rpm at sea level
- Compression ratio: 7.5:1
See also
Related development
Comparable engines
Related lists
References
- Notes
- ^ Bridgman 1994, p. 78d.
- Bibliography
- Bridgman, Leonard. Jane's All the World's Aircraft 1945-46. Hammersmith, London: HarperCollinsPublishers (1994 reprint). ISBN 000 470831-8
External links
