TCDS E26EA

Page No. 1 2 3 Rev. No. 5 5 5 Reformatted 8/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E26EA Revision No. 5 Lycoming Engines TO-360-A1A6D, -C1A6D, -E1A6D, -F1A6D LTO-360-A1A6D, -E1A6D November 04, 2010 TYPE CERTIFICATE DATA SHEET NO. E26EA Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E26EA) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of Civil Air Regulations/Federal Aviation 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. Williamsport PA transferred TC E26EA to Lycoming Engines, An Operating Division of AVCO Corporation on November 04, 2010 Model Lycoming TO-360-A1A6D: TO-360-C1A6D: TO-360-E1A6D LTO-360 A1A6D TO-360-F1A6D LTO-360-E1A6D Type 4HOA Direct Drive Turbocharged Rating (See NOTE 4) Max. continuous, hp., r.p.m., in. Hg. at: Standard density critical alt. ft. 198-2575-40.0-10,000 207-2575-42.0-10,000 180-2575-36.5-12,000 Standard density 5000 ft. alt. 200-2575-40.0-5,000 — — Standard density sea level alt. ft. 196-2575-40.0-S.L. 210-2575-42.0-S.L. — Takeoff (5 min.), hp., r.p.m., in. Hg. at: Standard density critical alt. ft. 198-2575-40.0-10,000 207-2575-42.0-10,000 180-2575-36.5-12,000 Standard density 5000 ft. alt. 200-2575-40.0-5,000 — — Standard density sea level alt. ft. 196-2575-40.0-S.L. 210-2575-42.0-S.L. — Fuel (minimum grade aviation gasoline) 100 or 100LL - - - - Lubricating oil (lubricants should See Latest Edition - - - - conform to the specification as of Lycoming Service listed) Instruction No. 1014 Bore and stroke, in. 5.125 x 4.375 - - - - Displacement, cu. in. 361.0 - - - - Compression Ratio 8.0:1 7.30:1 8.0:1 Weight (dry), lb. 326 343 315 C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 15.50 15.27 15.94 Off crankshaft C.L., in. 0.975 below & 0.10 left 0.53 below & 0.88 right 0.75 below & 0.41 left Propeller shaft flange, SAE No. Type 2 modified - - - - Propeller shaft flange, SAE No. Type 2 modified - - - - Crankshaft dampers (torsional) one 6.3 order - - - - one 8th order - - - - Carburetion* Marvel-Schebler** HA-6 - - - - Turbocharger Kelly Aerospace+ 301E10-2 - - Kelly Aerospace+ TA04 Model Lycoming (cont'd) TO-360-A1A6D: TO-360-C1A6D: TO-360-E1A6D LTO-360 A1A6D TO-360-F1A6D LTO-360-E1A6D Ignition, dual TCM#: D4RN-3021 (LTO): D4LN-3021 D4LN-3021 (LTO): D4LN-3021 (TO) D4RN-3021 (TO) Ignition timing°BTC 20 - - - - Spark plugs See NOTE 6 - - - - Oil sump capacity, qt. 8 - - - - Usable oil, qt. 20° nose up or down 6 - - - - NOTES 1 through 10 - - - - * See latest edition of Lycoming SI 1523 for alternate approved Carburetors ** Marvel-Schebler formerly Volare, Precision Airmotive Corporation, Facet Aerospace, and Borg Warner Corp. + Kelly Aerospace, formerly AiResearch, formerly Rajay # TCM formerly Bendix CERTIFICATION BASIS: Regulations & Amendments FAR 33, 33-1 effective February 1, 1965, As Amended by 33-2 & 33-3 Date Type Certificate Model Date of Application E26EA Issued/Revised TO-360-A1A6D March 6, 1973 January 9, 1974 LTO-360-A1A6D March 6, 1973 January 9, 1974 TO-360-C1A6D December 10, 1975 February 9, 1976 TO-360-F1A6D January 30, 1979 March 23, 1979 TO-360-E1A6D July 19, 1979 September 28, 1979 LTO-360-E1A6D July 19, 1979 September 28, 1979 Production basis: Production Certificate No. 3 NOTE 1. Maximum permissible temperatures: Cylinder head (well type thermocouple) 500°F Cylinder base See NOTE 5 Oil inlet 245°F Carburetor inlet air (max) 160°F (-A1A6D) All other models 350°F Exhaust gas (turbo inlet at location shown on Lycoming Drawing No. 63441) 1650°F (-E1A6D) All other models 1725°F Magneto (at coil core) 225°F NOTE 2. Pressure limits: Minimum Maximum Fuel pressure limits (above carburetor inlet air pressure) at inlet to carburetor -A1A6D 0.5 p.s.i. 8 p.s.i. -C1A6D; -F1A6D 15 p.s.i. 30 p.s.i. -E1A6D 13 p.s.i. 30 p.s.i. Fuel pressure limits at inlet to engine fuel pump -A1A6D; -C1A6D; -E1A6D; -F1A6D -2 p.s.i. 30 p.s.i. Manifold pressure limits: -A1A6D — 40 in. Hg. -C1A6D; -F1A6D — 43.75 in. Hg. Exhaust back pressure limit (at turboc harger exhaust flange) — 0.5 in. Hg. Oil pressure limits: Normal (-A1A6D; -E1A6D ) 60 p.s.i. 95 p.s.i. Normal (-F1A6D; -C1A6D) 50 p.s.i. 95 p.s.i. Idle 25 p.s.i. — Idle (-E1A6D) 15 p.s.i. — Starting and warm-up — 100 p.s.i. Starting and warm-up (-E1A6D ; -F1A6D; -C1A6D) — 115 p.s.i. 3 E26EA NOTE 3. The following accessory provisions are available: Accessory TO-360 -A1A6D -F1A6D -C1A6D LTO-360 -A1A6D TO-360 -E1A6D LTO-360 -E1A6D Rotation Facing Drive Pad Speed Ratio To Crankshaft Maximum Torque in.-lb. Maximum Overhang Moment in.-lb. TO LTO Cont. Static Starter * * * * CC C 16.556:1 — 450 150 Alternator * * * * C CC 3.250:1 60 120 175 Vacuum Pump ** ** — — CC C 1.300:1 70 450 25 Vacuum Pump — — * * CC C 1.313:1 70 450 25 Hydraulic Pump ** ** C CC 1.300:1 100 800 40 Hydraulic Pump ** ** C CC 1.300:1 180 2200 150 Tachometer * * * * C CC .500:1 7 50 5 Propeller Governor ** ** — — C CC .895:1 125 1200 40 Propeller Governor — — * * CC C 1.000:1 125 1200 40 Fuel Pump * * * * Plunger .500:1 — — 10 * Standard "C" Clockwise **Optional "CC" Counter-Clockwise NOTE 4. Engine models -A1A6D, -C1A6D , -F1A6D are equipped with a Kelly Aerospace (formerly Rajay) Model 301E10-2 turbocharger mounted as an integral part of the engine. Performance data for these engines are presented on Lycoming Curve Number 13247 (-A1A6D) and 13280 (-C1A6D) (-F1A6D) Engine Model -E1A6D is equipped with Kelly Aerospace (formerly AiResearch) TA04 turbocharger mounted as an integral part of the engine. Performance data for this engine is presented on Lycoming Curve No. 13369. These turbocharger models meet the containment require ments of FAR 33-27 and do not require external protection. NOTE 5. Cylinder base temperature limits are not applicable to e ngine models which incorporate internal piston cooling oil jets. NOTE 6. Spark plugs approved for use on these engines are listed in the latest revision of Lycoming Service Instruction No. 1042. NOTE 7. These engines incorporate the following similarities or differences: Model TO-360-A1A6D - Basic model-four cylinder air c ooled, horizontally-opposed, direct drive, carbureted, turbocharged, engine incorporating internal piston cooling oil jets. LTO-360-A1A6D - Similar to TO-360-A1A6D excep t has counter-clockwise (reverse) rotation. TO-360-C1A6D - Similar to TO-360-A1A6D except pow er increased, lower compression ratio and carburetor located after the turbocharger instead of before the turbocharger. TO-360-F1A6D - Same as TO-360-C1A6D except has provisi ons for a rear type mounting (long type 1.12" conical mount). TO-360-E1A6D - Same as 0-360-E1A6D except equi pped with Kelly Aerospace (formerly AiResearch) TA402 turbocharger, 8.0:1 compression ratio pistons, piston cooling oil jets and high pressure fuel pump. LTO-360-E1A6D - Similar to TO-360-E1A6 D except has counter-clockwise rotation. NOTE 8. These engines incorporate provisions for absorbing propeller thrust in both tractor and pusher installations. NOTE 9. Starters and alternators approved for use on these engi nes are listed in the latest revision of the Lycoming Service Instruction No. 1154. NOTE 10. All models equipped with an impulse coupling magneto, may use both magnetos for starting. ....END....