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Lycoming O-320

From PlaneSpottingWorld, for aviation fans everywhere

The Lycoming O-320 is a large family of 92 different normally-aspirated, air-cooled, four-cylinder, direct-drive engines commonly used on light aircraft such as the Cessna 172 and Piper Cherokee. Different variants are rated for 150 or 160 horsepower (112 or 119 kilowatts). 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 / 319.75cuin).[1]

Design and development

The O-320 family of engines includes the carbureted O-320, the fuel injected IO-320, the inverted mount, fuel injected AIO-320 and the aerobatic, fuel injected AEIO-320 series. The LIO-320 is a series of two models identical to the same model IO-320, but with the crankshaft rotating in the opposite direction for use on twin-engined aircraft to eliminate the critical engine.[2][3]

The first O-320, the A1A was FAA certified on 28 July 1953 to CAR 13 effective 5 March 1952. The first IO-320 was certified on 10 April 1961, with the AIO-320 following on 23 June 1969 and the first aerobatic AEIO-320 on 12 April 1974. The LIO-320s were both certified on 28 August 1969.[2][3]

The O-320 family of engines externally resembles the Lycoming O-235 and O-290 family from which they were derived. The O-320 shares the same Template:Convert stroke as the smaller engines, but produces more power with the bore increased to Template:Convert. The design uses hydraulic tappets and incorporates the provisions for a hydraulically-controlled propeller installation as well. The controllable pitch propeller models use a different crankshaft from those intended for fixed pitch propellers.[4]

The O-320 uses a conventional wet sump system for lubrication. The main bearings, connecting rods, camshaft bearings, tappets and pushrods are all pressure lubricated, while the piston pins, cylinder walls and gears are all lubricated by spray. The oil system is pressurized by an accessory-drive mounted oil pump. The engine uses a remotely mounted oil cooler, connected to the engine by flexible hoses.[4]

The carburetted O-320, but not the fuel-injected versions, have available an STC that allows the use of automotive fuel as a replacement for more expensive avgas.[5]

The factory retail price of the O-320 varies by model. In December 2008 the retail price of an O-320-B1A was USD$36,728[6]

Variants

O-320 series

0-320-A1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Provisions for a controllable pitch propeller and 25-degree spark advance.[4]
0-320-A1B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with straight riser in oil sump and -32 carburetor.[4]
0-320-A2A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with fixed pitch propeller.[4]
0-320-A2B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A2A but with straight riser in oil sump and -32 carburetor.[4]
0-320-A2C
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A2B but with retard breaker magnetos.[4]
0-320-A2D
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E3D but with conical mounts.[4]
0-320-A3A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with 7/16" prop bolts.[4]
0-320-A3B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A3A but with straight riser in oil sump and -32 carburetor.[4]
0-320-A3C
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A3B but with retard breaker magnetos.[4]
0-320-B1A
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as A1A but with high compression pistons.[4]
0-320-B1B
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B1A but with straight riser in oil sump and -32 carburetor.[4]
0-320-B2A
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B1A but with fixed pitch propeller provisions.[4]
0-320-B2B
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B2A but with straight riser in oil sump and -32 carburetor.[4]
File:Robinson R22 engine detail.jpg
An O-320-B2C mounted in a Robinson R-22 helicopter
0-320-B2C
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B2B but with retard breaker magnetos.[4]
0-320-B2D
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as D1D but with conical engine mounts and no propeller governor.[2]
0-320-B2E
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as B2B except the carburetor is in the same location as the O-320-D models.[2]
0-320-B3A
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B1A but with 7/16 inch propeller bolts.[4]
0-320-B3B
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B1A but with 7/16 inch propellor bolts, a straight riser in oil sump, and -32 carburetor.[4]
O-320-B3C
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B3B but with retard breaker magnetos.[4]
0-320-C1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B1A.[4]
0-320-C1B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B1B.[4]
0-320-C2A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2A.[4]
0-320-C2B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2B.[4]
0-320-C2C
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2C.[4]
0-320-C3A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B3A.[4]
0-320-C3B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B3B.[4]
0-320-C3C
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B3C.[4]
0-320-D1A
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B3B but with Type 1 dynafocal mounts.[4]
0-320-D1B
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D1A but with retard breaker magnetos.[4]
0-320-D1C
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D2C but with provisions for a controllable propeller,[4]
0-320-D1D
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the D1A but with Slick instead of Bendix magnetos and a horizontal carburetor and induction housing.[2] This model was used in the Gulfstream American GA-7 Cougar twin.
0-320-D1F
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1F except with high compression pistons.[4]
File:Lycoming O-320-D2A engine A.JPG
A brand new Lycoming O-320-D2A engine with baffles already mounted
0-320-D2A
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D1A but with fixed pitch propeller provisions and 3/8 inch attaching bolts.[4] Used in the Symphony SA-160.
0-320-D2B
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D2A but retard breaker magnetos.[4]
0-320-D2C
Template:Convert at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D2A except -1200 series magnetos.[4]
0-320-D2F
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2F except with high compression pistons.[4]
0-320-D2G
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the D2A except with Slick instead of Bendix magnetos and 7/16 inch instead of 3/8 inch propeller flange bolts..[2]
0-320-D2H
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the D2G except with a O-320-B sump and intake pipes and with provisions for AC type fuel pump.[2]
0-320-D2J
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1.Similar to the D2G but with two Slick impulse coupling magnetos and the propeller governor pad, fuel pump and governor pads on the accessory housing all not machined.[2] Used in the Cessna 172P.
0-320-D3G
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the D2G but with 3/8 inch propeller attaching bolts.[2]
0-320-E1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A3B but with Type 1 dynafocal mounts.[4]
0-320-E1B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1A but with retard breaker magnetos.[4]
0-320-E1C
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1B.[4]
0-320-E1F
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1C but with propeller governor drive on the left front of the crankcase.[4]
0-320-E1J
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the E1F but with Slick magnetos.[2]
0-320-E2A
Template:Convert at 2700 rpm, or Template:Convert at 2450 rpm Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1A but with fixed pitch propeller, 3/8 inch attaching bolts and an alternate power rating of Template:Convert.[4]
0-320-E2B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but with retard breaker magnetos.[4]
0-320-E2C
Template:Convert at 2700 rpm, or Template:Convert at 2450 rpm Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but -1200 series mags and an alternate power rating of Template:Convert.[4]
0-320-E2D
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Similar to E2A but with Slick disposable magnetos and 0-235 front.[4] Used in the Cessna 172 I to M models.
0-320-E2F
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1F but with fixed pitch prop provisions.[4]
0-320-E2G
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2D but with 0-320-A sump and intake pipes.[4]
0-320-E2H
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2D but with S4LN-20 and -21 magnetos.[4]
0-320-E3D
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2D but with 3/8 inch propeller flange bolts.[4]
0-320-E3H
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E3D but with S4LN-20 and -21 magnetos.[4]
0-320-H1AD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Integral accessory section crankcase, front mounted fuel pump external mounted oil pump and D4RN-2O21 impulse coupling dual magneto.[2]
0-320-H1BD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as H1AD but with a D4RN-2200 retard breaker dual magneto.[2]
0-320-H2AD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as H1AD but with provisions for a fixed pitch propeller.[2] This was the troublesome engine that was installed on the Cessna 172N.[7]
0-320-H2BD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as the H2AD but with a D4RN-2200 retard breaker dual magneto.[2]
0-320-H3AD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as the H2AD but with 3/8 inch propeller flange bolts, in place of instead of 7/16 inch.[2]
0-320-H3BD
Template:Convert at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as H3AD but with a D4RN-2200 retard breaker dual magneto.[2]

IO-320 series

I0-320-A1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Base model with a Bendix RSA -5AD1 fuel injection system.[3]
I0-320-A2A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with provisions for fixed pitch propeller.[3]
I0-320-B1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1A but with the fuel injector offset toward the engine's fore and aft centerline.[3]
I0-320-B1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1A but with an AN fuel pump drive.[3]
I0-320-B1C
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the B1A but with an adapter for mounting the fuel injector straight to the rear.[3]
I0-320-B1D
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the B1C but with S-1200 series high altitude magnetos.[3]
I0-320-B1E
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the D1C except with a horizontal fuel injector.[3]
I0-320-B2A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the BIA but with provision for a fixed pitch propeller.[3]
I0-320-C1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the B1B except it has features making it suitable for adding a turbo-supercharger via a Supplemental Type Certificate This engine has internal piston cooling oil nozzles.[3]
I0-320-C1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the C1A but with a horizontal rear mounted fuel injector.[3]
I0-320-D1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the B1D but with Type 1 dynafocal mounts, S4LN-1227 and S4LN-1209 magnetos and the fuel injector mounted vertically under the oil sump.[3]
I0-320-D1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the D1A but with the propeller governor drive on the left front of crankcase instead of on the accessory housing.[3]
I0-320-D1C
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the D1B but with Slick Magnetos.[3]
I0-320-E1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but with provision for a controllable pitch propeller.[3]
I0-320-E1B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1A but with Slick 4050 and 4051 magnetos.[3]
I0-320-E2A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A2A but with Scintilla S4LN-20 and S4LN-21 magnetos, straight conical mounts, and the fuel injector mounted under the oil sump.[3]
I0-320-E2B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but with Slick 4050 and 4051 magnetos.[3]
I0-320-F1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the C1A except with a Type 1 (30°) dynafocal mount attachment instead of Type 2 (18°) mount attachment.[3]

LIO-320 series

LI0-320-B1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as B1A except with counter-clockwise engine rotation and reverse rotation of accessories. It uses a modified starter ring gear, crankshaft, cam shaft, accessory housing and oil pump body. This engine is usually paired with an IO-320-B1A on a twin engined aircraft.[3]
LI0-320-C1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as C1A except with the same changes as the LIO-320-B1A. It has provisions for adding a turbo-supercharger. This engine is usually paired with an IO-320-C1A on a twin engined aircraft.[3]

AIO-320 series

AI0-320-A1A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the IO-320-B1D but this model permits installation and operation of the engine in the inverted position. The differences include a front mounted propeller governor, two dry oil sumps, dual external oil scavenge pumps, an oil tank, three options for the position of the fuel injector and a Type 1 dynafocal mount.[3]
AI0-320-A1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1A but with one impulse coupling magneto.[3]
AI0-320-A2A
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1A but with provision for a fixed pitch propeller.[3]
AI0-320-A2B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1A but has one impulse coupling magneto and a fixed pitch propeller.[3]
AI0-320-B1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the A1B but with a front-mounted fuel injector.[3]
AI0-320-C1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the B1B but with the fuel injector vertically mounted on bottom of the oil sump in the front position.[3]

AEIO-320 series

AEI0-320-D1B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the IO-320-D1B but with an inverted oil system kit to allow aerobatic flight.[3]
AEI0-320-D2B
Template:Convert at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1. Same as the AEIO-320-D1A but without provisions for a propeller governor.[3]
AEI0-320-E1A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the IO-320-E1A but with an inverted oil system kit to allow aerobatic flight.[3]
AEI0-320-E1B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the IO-320-E1B but with an inverted oil system kit to allow aerobatic flight.[3]
AEI0-320-E2A
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the IO-320-E2A but with an inverted oil system kit to allow aerobatic flight.[3]
AEI0-320-E2B
Template:Convert at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the IO-320-E2B but with an inverted oil system kit to allow aerobatic flight.[3]

Applications

Template:Expand list

File:Thorp T-18 amateur-built C-GEMP 02.JPG
The Lycoming O-320 is a common engine used by amateur-builders in the Thorp T-18.

Specifications (O-320-A1A)

Template:Pistonspecs

See also

References

Notes

  1. ↑ Gunston 1989, p.98.
  2. ↑ 2.00 2.01 2.02 2.03 2.04 2.05 2.06 2.07 2.08 2.09 2.10 2.11 2.12 2.13 2.14 2.15 Federal Aviation Administration (September 2005). TYPE CERTIFICATE DATA SHEET NO. E-274 Revision 20. Retrieved on 2009-01-15.
  3. ↑ 3.00 3.01 3.02 3.03 3.04 3.05 3.06 3.07 3.08 3.09 3.10 3.11 3.12 3.13 3.14 3.15 3.16 3.17 3.18 3.19 3.20 3.21 3.22 3.23 3.24 3.25 3.26 3.27 3.28 3.29 3.30 3.31 3.32 3.33 Federal Aviation Administration (December 2003). TYPE CERTIFICATE DATA SHEET NO. 1E12 Revision 9. Retrieved on 2009-01-16.
  4. ↑ 4.00 4.01 4.02 4.03 4.04 4.05 4.06 4.07 4.08 4.09 4.10 4.11 4.12 4.13 4.14 4.15 4.16 4.17 4.18 4.19 4.20 4.21 4.22 4.23 4.24 4.25 4.26 4.27 4.28 4.29 4.30 4.31 4.32 4.33 4.34 4.35 4.36 4.37 4.38 4.39 4.40 4.41 4.42 4.43 4.44 4.45 4.46 4.47 Christy, Joe: Engines for Homebuilt Aircraft & Ultralights, pages 77-80 TAB Books, 1983. ISBN 0-8306-2347-7
  5. ↑ Experimental Aircraft Association (2009). Engine Models Approved. Retrieved on 2009-06-06.
  6. ↑ Lycoming Engines (2008). 2008 Lycoming Service Engine Price List (PDF). Retrieved on 2008-12-20.
  7. ↑ Cessna Aircraft: Pilot Operating Handbook 1977 Skyhawk Cessna Model 172N, page 1-3. Cessna Aircraft, 1976.

Bibliography

  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

External links

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This article is licensed under the GNU Free Documentation License.
It uses material from the Wikipedia article "Lycoming O-320".


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