Lycoming 0 320 E3d Manual

Contents.Design and development The O-320 family of engines includes the O-320, the IO-320, the inverted mount, fuel-injected AIO-320 and the, fuel-injected AEIO-320 series. The LIO-320 is a 'left-handed' version with the crankshaft rotating in the opposite direction for use on twin-engined aircraft to eliminate the.The first O-320 (with no suffix) was on 28 July 1953 to CAR 13 effective 5 March 1952; this same engine was later re-designated, without change, as the O-320-A1A. 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.The O-320 family of engines externally resembles the and family from which they were derived. The O-320 shares the same 3.875 in (98 mm) stroke as the smaller engines, but produces more power with the bore increased to 5.125 in (130 mm). 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.The O-320 uses a conventional system for lubrication.

Department of Transportation Federal Aviation Administration 800 Independence Avenue, SW Washington, DC 20591 (866) tell-FAA ((866) 835-5322).

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. A remotely mounted oil cooler is used, connected to the engine by flexible hoses.The 150 hp (112 kW) versions of the carbureted O-320, are approved for the use of 87 AKI automotive. Only one model of the 160 hp (119 kW) variants of the 0-320 is not approved, and that is the H2AD model. All other 160 hp (119 kW) 0-320s are approved for 91 AKI.

Airframe approval is also necessary to use automotive gasoline in any aircraft.The factory retail price of the O-320 varies by model. In 2010 the retail price of an O-320-B1A purchased outright was 47,076 Variants O-320 series O-320 (No suffix) later redesignated O-320-A1A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87, compression ratio 7.00:1. Provisions for a controllable-pitch propeller and 25-degree spark advance. O-320-A1B 150 hp (112 kW) 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. O-320-A2A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with fixed-pitch propeller.

O-320-A2B 150 hp (112 kW) 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. O-320-A2C 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A2B but with retard breaker magnetos.

O-320-A2D 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E3D but with conical mounts.

O-320-A3A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A1A but with 7/16' prop bolts. O-320-A3B 150 hp (112 kW) 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. O-320-A3C 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A3B but with retard breaker magnetos.O-320-B1A 160 hp (119 kW) 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. O-320-B1B 160 hp (119 kW) 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. O-320-B2A 160 hp (119 kW) 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. O-320-B2B 160 hp (119 kW) 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.

An O-320-B2C mounted in a helicopter O-320-B2C 160 hp (119 kW) 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. O-320-B2D 160 hp (119 kW) 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. O-320-B2E 160 hp (119 kW) 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. O-320-B3A 160 hp (119 kW) 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. Toshiba satellite c600 web camera drivers for mac. O-320-B3B 160 hp (119 kW) 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. O-320-B3C 160 hp (119 kW) 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.O-320-C1A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B1A.

O-320-C1B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B1B. O-320-C2A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2A. O-320-C2B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2B.

O-320-C2C 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B2C. O-320-C3A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B3A. O-320-C3B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Low compression version converted through field conversion of B3B. O-320-C3C 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Low compression version converted through field conversion of B3C.O-320-D1A 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as B3B but with Type 1. O-320-D1B 160 hp (119 kW) 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.

O-320-D1C 160 hp (119 kW) 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, O-320-D1D 160 hp (119 kW) 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.

This model was used in the twin. O-320-D1F 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Same as E1F except with high compression pistons. A brand new Lycoming O-320-D2A engine with baffles already mounted O-320-D2A 160 hp (119 kW) 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.

O-320-D2B 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D2A but retard breaker magnetos. O-320-D2C 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 100/130 or 91/96 avgas, compression ratio 8.50:1. Same as D2A except -1200 series magnetos.

O-320-D2F 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2F except with high compression pistons. O-320-D2G 160 hp (119 kW) 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. O-320-D2H 160 hp (119 kW) 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.

O-320-D2J 160 hp (119 kW) 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. O-320-D3G 160 hp (119 kW) 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.O-320-E1A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as A3B but with Type 1 dynafocal mounts. O-320-E1B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1A but with retard breaker magnetos. O-320-E1C 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

O-320-E1F 150 hp (112 kW) 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. O-320-E1J 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as the E1F but with Slick magnetos. O-320-E2A 150 hp (112 kW) at 2700 rpm, or 140 hp (104 kW) 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 140 hp (104 kW).

O-320-E2B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but with retard breaker magnetos. O-320-E2C 150 hp (112 kW) at 2700 rpm, or 140 hp (104 kW) 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 140 hp (104 kW). O-320-E2D 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Similar to E2A but with Slick magnetos and O-235 front. Used in the I to M models. O-320-E2F 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E1F but with fixed pitch prop provisions. O-320-E2G 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Same as E2D but with O-320-A sump and intake pipes. O-320-E2H 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Same as E2D but with S4LN-20 and -21 magnetos. O-320-E3D 150 hp (112 kW) 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. O-320-E3H 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E3D but with S4LN-20 and -21 magnetos.O-320-H1AD 160 hp (119 kW) 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. O-320-H1BD 160 hp (119 kW) 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. O-320-H2AD 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 100LL avgas, compression ratio 9.00:1. Same as H1AD but with provisions for a fixed-pitch propeller.

This was the troublesome engine that was installed on the 1977 to 1980. It was notable from all other Lycoming models by incorporating that were barrel shaped instead of mushroom type, in an attempt to make the lifters possible to be serviced without having to disassemble the entire engine case, but the higher load on the lobes resulted in severe. Multiple service bulletins and have been issued regarding this specific model, and multiple modifications exist to attempt to mitigate its design defects. O-320-H2BD 160 hp (119 kW) 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. O-320-H3AD 160 hp (119 kW) 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. O-320-H3BD 160 hp (119 kW) 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.

IO-320 series IO-320-A1A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Base model with a Bendix RSA -5AD1 fuel injection system. IO-320-A2A 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Same as A1A but with provisions for fixed-pitch propeller. IO-320-B1A 160 hp (119 kW) 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. IO-320-B1B 160 hp (119 kW) 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. IO-320-B1C 160 hp (119 kW) 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. IO-320-B1D 160 hp (119 kW) 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. IO-320-B1E 160 hp (119 kW) 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.

IO-320-B2A 160 hp (119 kW) 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. IO-320-C1A 160 hp (119 kW) 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 This engine has internal piston cooling oil nozzles. IO-320-C1B 160 hp (119 kW) 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. IO-320-D1A 160 hp (119 kW) 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. IO-320-D1B 160 hp (119 kW) 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. IO-320-D1C 160 hp (119 kW) at 2700 rpm, Minimum fuel grade 91/96 or 100LL avgas, compression ratio 8.50:1.

Same as the D1B but with Slick Magnetos. IO-320-E1A 150 hp (112 kW) 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. IO-320-E1B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1.

Same as E1A but with Slick 4050 and 4051 magnetos. IO-320-E2A 150 hp (112 kW) 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. IO-320-E2B 150 hp (112 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.00:1. Same as E2A but with Slick 4050 and 4051 magnetos.

IO-320-F1A 160 hp (119 kW) 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. LIO-320 series LIO-320-B1A 160 hp (119 kW) 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. LIO-320-C1A 160 hp (119 kW) 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. AIO-320 series AIO-320-A1A 160 hp (119 kW) 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. AIO-320-A1B 160 hp (119 kW) 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. AIO-320-A2A 160 hp (119 kW) 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. AIO-320-A2B 160 hp (119 kW) 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. AIO-320-B1B 160 hp (119 kW) 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. AIO-320-C1B 160 hp (119 kW) 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. AEIO-320 series AEIO-320-D1B 160 hp (119 kW) 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.

AEIO-320-D2B 160 hp (119 kW) 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. AEIO-320-E1A 150 hp (112 kW) 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. AEIO-320-E1B 150 hp (112 kW) 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.

AEIO-320-E2A 150 hp (112 kW) 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. Torrent bodybuilding books. AEIO-320-E2B 150 hp (112 kW) 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.

Applications. Series 2 and 3.Specifications (O-320-A1A) Data from TYPE CERTIFICATE DATA SHEET NO. E-274 Revision 20 General characteristics. Type: Four-cylinder air-cooled.: 5.125 in (130.18 mm).: 3.875 in (98.43 mm).: 319.8 cu in (5.24 l).: 244 lb (111 kg)Components.: Two per cylinder. Fuel system:.

Fuel type: minimum grade of 80/87. Oil system: Wet sump. Cooling system: Air-cooledPerformance.

Power output: 150 hp (112 kW).: 7:1.:.61 hp/lb (0.99 kW/kg)See also.References Notes. Gunston 1989, p.98. ^ (September 2005). Retrieved 15 January 2009. ^ (December 2003). Retrieved 16 January 2009.

^ Christy, Joe: Engines for Homebuilt Aircraft & Ultralights, pages 77-80 TAB Books, 1983. Petersen Aviation, Inc. Retrieved 14 November 2017. (January 2010). Retrieved 3 October 2010.: Pilot Operating Handbook 1977 Skyhawk Cessna Model 172N, page 1-3. Cessna Aircraft, 1976.

Lycoming Service Bulletins #424 (new lifter modification), #446C, #435C, #1406B ('T' case modification), Ney Nozzles modification. Cessna Owner Organization. 23 February 2004. Archived from on 2 April 2015. McBride, Paul (5 March 2015). General Aviation News.Bibliography.

SUMMARY OF FEDERAL AVIATION ADMINISTRATIONSUPPLEMENTAL TYPE CERTIFICATES JANUARY 1998Engine Section TEXTRON AVCO CORPORATION, LYCOMING DIVISION ENGINE MAKE MODEL & T.C. NO.O-145, O-235, O-290, O-350, O-360, HO-360-A1A, O-435, GO-435, O-320, O-340, VO-435, VO-360, TO-360, LTO-360, VO-540-B, & C, TVO-540-A1A, O-540 Series; T.C. 199, 210, 233, 227, 228, 229, 274, 277, 279, 295, 1E1, E26EA, 304, 1E14, E-286STC NO.DESCRIPTIONACOSTC HOLDERSE1-201Installation of Richter B-4 or B-5 probes in Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-5, MA-6, HA-9 and Bendix NA-S3B and NA-S3A1 carburetors. Amended 9/20/77.EARichter Aero Equip. Essex, NY 12936Use of Kling Aviation Oil, Specifications KL-100, KL-200 and KL-300 in Continental and Lycoming engines.WEKling Oil Company 1492 Oddstad Drive Redwood City, CA 94063O-145-A, O-145-B, -C, SE44WE GO-145, O-233- A1, O-235, O-290, O-320, IO-320, O-340, O-350, IO-360, O-360, HO-360, VO-360, O-435-1, -4, -5, -11, -13, O-435-2, GO-435, -6, -17; GSO-435, -B, -B2; VO-435, -21-23; TVO-435; GO-480; TSO-480 -1, IGSO-480, -2; IO-540, O-540; IGO-540; IGSO-540; VO-540; TVO-540; GSO-580; SO-580, VSO-580; T.C. 199, 210, 229, 274, 1E12, 277, 227, 1E10, 1E1, 228, 276, 279, 1E13, 275, E284, 295, 1E4, 1E11, 1E7, 304, 1E14,1E15, E-223, 256, 285, E-286Avco Textron Lycoming ENGINE MAKE MODEL & T.C.

NO.2 of 30 STC NO.O-145A Series, B, C, GO-145, O-233-A1, O-235, O-290, O-320, IO-320, AIO-320, LIO-320, AEIO-320, O-340, O-350, O-360, HO-360, IO-360, HIO-360, AIO-360, LO-360, LIO-360, IVO-360, VO-360, LHIO-360, AEIO-360, O-435, GO-435, Mil-O-435-2-MI, GSO-435B, -B2, VO-435, GO-480, IGO-480, R-530-D1, -D2, O-540, IO-540, IGO-540 Series; T.C.