TCDS E10EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E10EA Revision 8 Lycoming Engines TIO-541-A1A TIO-541-E1A4, -E1B4 -E1C4, -E1D4 November 04, 2010 TYPE CERTIFICATE DATA SHEET NO. E10EA Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E10EA) 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 the 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 E10EA to Lycoming Engines, An Operating Division of AVCO Corporation on November 04, 2010 Model Lycoming TI0-541 -A1A -E1A4, -E1B4 , -E1C4, -E1D4 Type 6H0A Direct Drive Turbosupercharged Rating (See NOTE 4) Maximum continuous, hp., r.p.m, in. Hg., at: 310-2575-37.0-15,000 380-2900-41.9-15,000 Standard density, critical alt. ft. 310-2575-37.0-S.L. 380-2900-41.0-S.L. Standard density, sea level alt. ft. Takeoff (5 min.), hp., r.p.m., in. Hg., at: Standard density, critical alt. ft. 310-2575-37.0-15,000 380-2900-41.9-15000 Standard density sea level alt. ft. 310-2575-37.0-S.L. 380-2900-41.0-S.L. Fuel (minimum grade aviation gasoline) 100/130 - - Lubricating oil (lubricants should conform to the specification as listed or to subsequent revisions thereto) See Latest Edition of Lycoming Service Instruction No. 1014 - - Bore and stroke, in. 5.125 x 4.375 - - Displacement, cu. in. 541.5 - - Compression Ratio 7.3:1 - - Weight (dry), lb. See NOTE 7 - - C.G. location (with starter & generator installed) See NOTE 7 - - Propeller shaft flange, SAE No. AS127 Type 2 modified - - Crankshaft dampers (torsional) See NOTE 6 - - Fuel injection See NOTE 7 - - Turbosupercharger Kelly Aerospace* (See NOTE 4) - - Ignition, dual TCM+ (See NOTE 7) Ignition timing BTC 20 - - Spark plugs See NOTE 5 - - Oil, sump capacity, qts. - total and usable See NOTE 7 - - NOTES 1 thru 9 - - "- -" indicates "same as preceding model"; " " indicates "does not apply" * Kelly Aerospace formerly AiResearch + TCM formerly Scintilla Certification basis: Regulations and Amendments Model Date of Application Date Type Certificate No. E10EA Issued/Revised CAR 13 Effective June 15, 1956 TIO-541- A1A December 16, 1963 February 23, 1965 As Amended By 13-1, 13-2, & 13-3 & 13-4 TIO-541-E1A4 December 14, 1965 December 16, 1966 TIO-541-E1B4 June 1, 1966 December 16, 1966 TIO-541-E1C4 October 13, 1969 October 21, 1969 TIO-541-E1D4 October 13, 1969 October 21, 1969 Production basis: Production Certificate No. 3 NOTE 1. Maximum permissible temperatures: Cylinder head (well type thermocouple) 475°F Cylinder base - This parameter dispensed with four engines equipped with internal piston cooling oil jets. See NOTE 8. Oil inlet 245°F Fuel injector air inlet 300°F Exhaust gas (Turbo inlet at location shown 1650°F on Lycoming Dwg. Nos. 63204 (-A1A) -63250 (-E1A4, -E1B4) -63304 (-E1C4 & -E1D4)) Compressor temperature rise (-A1A) 280°F (-E1A4, -E1B4, -E1C4, -E1D4) 320°F NOTE 2. Pressure limits. Min. Max. Idle (Min.) Fuel pressure limits -A1A 29 p.s.i. 60 p.s.i. 12 p.s.i. (above fuel injector inlet air press.) -E1A4, -E1B4 (at inlet to fuel injector) -E1C4, -E1D4 20 p.s.i. Oil pressure limits: 60 p.s.i. 90 p.s.i. 25 p.s.i. Start and warm-up  100 p.s.i.  Fuel injector inlet pressure  40.5 in. Hg.  Manifold pressure  40 in. Hg.  Turbo supercharger exhaust back  0.5 in. Hg.  pressure NOTE 3. The following accessory provisions are available: -E1A4 -E1B4 Maximum To rque Maximum Overhang -E1C4 Rotation Facing Speed Ratio in. -lb. Moment Accessory -A1A -E1D4 Drive Pad to Crankshaft Cont Static in. - lb. Starter * * CC 16.566:1  450 150 Alternator * * C 3.250:1 60 120 175 Vacuum or Hydraulic Pump *  C 1.500:1 200 1600 50 Vacuum or Hydraulic Pump *  CC 1.500:1 Total Total 50 Vacuum or Hydraulic Pump  * C 1.000:1 200 1600 50 Vacuum or Hydraulic Pump  * CC 1.000:1 Total Total 50 Tachometer * * CC .500:1 7 50 5 Propeller Governor * * CC .895:1 125 825 25 Fuel Pump * * CC 1.000:1 25 450 25 Air Compressor  * CC 1.000:1 Belt Limited 100 "C" - Clockwise, "CC" - Counter clockwise * Standard ** Optional NOTE 4. These engines are equipped with a Kelly Aerospace* tur bosupercharger models mounted as an integral part of the engines as shown on Lycoming Drawings: * Kelly Aerospace formerly AiResearch Turbosupercharger Model Drawing No. -A1A T-1823 63204 -E1A4, -E1B4 T-1823 63250 -E1C4, -E1D4 T-1879 63304 Performance data for these engines are presented on Lycoming Curve Nos. 12987B(A1A), 13055A (E1A4, -E1B4, - E1C4, -E1D4). This turbocharger meets the containment requirements of CAR 13.166 and does not require external protection. Air from the compressor of this turbocharger may be used for cabin pressurization. NOTE 5. Spark plugs approved for use on these engines are listed in the latest revision of Lycoming Service Instruction No. 1042. NOTE 6. These engines incorporate crankshafts with one fifth order and one sixth order dampers unless the digit "4" follows the model designation, i.e., -E1A4. Engines so designated, (---4), have one 3.5 order, one fourth order, one fifth order and one sixth order pendulum type counterweights. NOTE 7. The following tabulation shows weight, C.G., fuel injectors, oil sump capacities and ignition: Center of Gravity, in. Fuel Oil Sump Capacities (Qts) From Front Face of Off Centerline Injector + Usable 20° Ignition Dual Model Weight Prop Shaft Flange of Crankshaft PAC* Total Nose up or down Bendix -A1A 549 21.00 .06 Below & .13 Right RSA- 10AD1 14 10.0 S6LN-1208; S6RN-1209 -E1A4 595 23.35 .05 Below & .05 Left RSA-10DB1 13 10.5 S6LN-1208; S6RN-1209 -E1B4 595 23.35 .05 Below & .05 Left RSA-10DB1 13 10.5 S6LN-1208; S6RN-1209 -E1C4 586 22.86 .06 Below & .03 Right RSA-10DB1 13 10.5 S6LN-1208; S6RN-1209 -E1D4 584 22.86 .06 Below & .03 Right RSA-10DB1 13 10.5 S6LN-1208; S6RN-1209 + For alternate fuel injectors see latest edition of Lycoming Service Instruction 1532 * PAC formerly Bendix NOTE 8. Model similarities and differences. TI0-541-A1A Basic model. Six cylinder, air cooled, horizontally opposed, direct drive, fuel injection, turbosupercharged engine with topside induction, down exhaust and side mounted accessory drives. Provides for single acting, controllable pitch propeller and has internal piston cooling oil jets. -E1A4 Similar to -A1A but has hi gher rating, uses different cylinder heads, cam shaft, crankshaft and additional counterweights. Has cabin pressurizing venturi. -E1B4 Similar to -E1A4 but does not in corporate a cabin pressurization venturi. -E1C4 Similar to -E1A4 except for different tur bosupercharger with cast bracket, cast transition and separate wastegate. -E1D4 Similar to -E1B4 except for different tur bosupercharger with cast bracket, cast transition and separate wastegate. NOTE 9. Starters, generators and alternat ors approved for use on these engines are listed in the latest revision of Lycoming Service Instruction No. 1154. - END -