TCDS E-285

Page No. 1 2 Rev. No. 3 2 FEDERAL AVIATION AGENCY E-285 Revision 3 LYCOMING Engines SO-580-A1A SO-580-A1B VSO-580-A1A November 04, 2010 AIRCRAFT ENGINE SPECIFICATION Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation Agency, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft specifications and applicable portions of the Civil Air Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer’s manuals and other approved instructions. Type Certificate Holder Lycoming Engines An Operating Division of AVCO Corporation Williamsport, Pennsylvania 17701 Type Certificate Holder Record Avco Lycoming Division, Avco Corp. transferred TC E-285 to Lycoming Engines, An Operating Division of AVCO Corporation on November 04, 2010 Model Lycoming SO-580-A1A, -A1B; VSO-580-A1A Type 8HOA - Direct Drive Rating Max. continuous, hp, rpm, in. Hg., at: Rated press. alt. (ft.) 350-3000-36.2-6000 Sea level press. alt. (ft.) 350-3000-37.5-S.L. Takeoff (5 min.), hp, rpm, in. Hg., at: Rated press. alt. (ft.) 400-3300-40.8-4200 Sea level press. alt. (ft.) 400-3300-41.5-S.L. Fuel (Min. grade aviation gasoline) 100/130 Lubricating Oil MIL-L-6082 Latest Edition of Lycoming Service Instruction No. 1014 Bore and stroke, in. 4.875 x 3.875 Displacement, Cu. In. 578 Supercharging ratio 7.91:1 Compression ratio 7.30:1 Weight (dry) lbs. See NOTE 4 C. G. location (dry) See NOTE 4 Propeller shaft Flanged type power takeoff Carburetion PAC+ PS9BDE Ignition Dual See NOTE 4 Timing, B T C 2 5 Spark plugs See NOTE 7 Oil Sump - capacity Dry Sump NOTES 1,2,3,4,5,6,7 “_ _” indicates “same as preceding model” + PAC formerly Bendix Certification basis Type Certificate No. 285 Production basis Production Certificate No. 3 E-285 2 NOTE 1. Maximum permissible temperatures: Cylinder Head (Well type) Cylinder Base Oil Inlet 475F 325 F 225 F NOTE 2. Min. Max.. Fuel Pressure Limits 9 psi 15 psi Oil Pressure Limits (Normal Operation) 65 psi 85 psi (Idling) 25 psi NOTE 3. The following accessory provisions are provided: Speed X Maximum Torque Direction of Rotation Cranksha ft (in.-lb.) Maximum Overhang Accessory Facing Engine Pad RPM Cont. Static Moment (in.-lb.) Starter C 1.000:1 - 12000 300 Generator C 2.600:1 500 2200 400 Fuel Pump CC .803:1 25 150 25 Vac. Pump C 1.219:1 200 800 25 Hyd. Pump C 1.083:1 300 1650 75 Tachometer CC .50:1 7 50 - NOTE 4. SO-580-A1A SO-580-A1B VSO-580-A1A Engine Dry Weight (lbs) 596 578 592 Center of Gravity Position Off Propeller Shaft C.L., in. .67 Above & .52 Above & .31 Below & .10 Right .10 Right .10 Right From Front Face of crankcase, in. 20.7 20.4 21.65 Ignition - Dual (4 Mags.) (2) S4LN-50 (2) S4LN-20 (2) S4LN-20 (2) S4LN-51 (2) S4LN-21 (2) S4LN-21 NOTE 5. These engines are approved for helicopter application and operation. The SO-580-A1A and A1B engines are designed for installation in a horizontal position or up to 35 nose up attitude. The VSO-580-A1A is intended for vertical installation. NOTE 6. The SO-580-A1A and A1B are furnished with a flange power takeoff at the front end of the crank shaft. An oil seal or closure suitabl e to the requirements of the helicopter transmission system must be provided by the helicopter manufacturer. Doman Helicopters Inc. Kit No. 15001 is one approved arrangement. NOTE 7. The following spark plugs are approved on these engines: AC S-86R, SR-83P, HSR-83P Autolite SH-2M, SH-20, SH-20A RG RB485S Champion R25S, RED37N, REM37N RHD37N, RHM37N ...END...