TCDS E19EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E19EA Revision 5 Lycoming Engines TIGO-541-B1A, -C1A, -D1A, -D1B, -E1A, -G1AD November 04, 2010 TYPE CERTIFICATE DATA SHEET NO. E19EA Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E19EA) 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, Williamsport, PA. transferred TC E19EA to Lycoming Engines, An Operating Division of AVCO Corporation on November 04, 2010 Model Lycoming TIGO-541 -C1A -D1A -E1A Type 6H0A geared drive turbocharged Rating (See NOTE 4) - - - - Maximum continuous r.p.m., in.Hg. at: Standard density critical alt. ft. 400-3200-43.5-15,000 450-3200-48.0-15,000 425-3200-47.3-15,000 Standard density sea level alt. ft. 400-3200-43.3-SL 450-3200-46.6-SL 425-3200-45.0-SL Takeoff (5 min.) , hp., r.p.m., in.Hg. at: Standard density critical alt. ft. 400-3200-43.5-15,000 450-3200-48.0-15,000 425-3200-47.3-15,000 Standard density sea level alt. ft. 400-3200-42.3-SL 450-3200-46.6-SL 425-3200-45.0-SL Fuel (min. grade aviation gasoline) 100/100 LL - - - - Lubrication oil (lubricants should conform to the specification as listed). 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 7.30:1 - - - - Weight (dry) lb. (with starter and alternator) 703 706 - - C.G. location (with starter and alternator installed) From front face of prop 26.68 25.75 26.51 mounting flange, in Off 0.12 above; 0.01 left 0.61 above; 0.07 right 0.20 above; 0.09 left crankshaft C.L., in. Propeller shaft flange NOTE 8 - - - - Crankshaft dampers (torsional) 5-third order & 1 - - - - second order Fuel injection* PAC** RSA-10DB1 - - PAC** RSA-10DB2 Turbocharger-Kelly Aerospace+ model T-1879 (NOTES 4 & 9) T18A21 (NOTES 4 & 9) - - Ignition, dual TCM# S6LN-1208, - - - - S6RN-1209 "- -" indicates "same as preceding model." "" indicates "does not apply". * For alternate fuel injectors see latest edition of Lycoming Service Instruction 1532 **PAC formerly Bendix +Kelly Aerospace formerly AiResearch #TCM formerly Bendix Model Lycoming TIGO-541 -C1A -D1A -E1A Ignition timing °BTC 20 - - - - Spark plugs NOTE 6 - - - - Oil sump capacity, qt. 15 18 - - Usable oil, qt. (20° nose up, 13° nose down) 13 (22° nose up,) (24° nose down) 9 - - - - - - NOTES 1 through 9 - - - - Model Lycoming TIGO-541 -B1A -G1AD -DIB Type 6H0A geared drive turbocharged Rating (See NOTE 4) Maximum continuous r.p.m., in.Hg. at: Standard density critical alt. ft. 450-3200-48.0-15,000 445-3200-45.3-15,000 420-3200-48.4-15,000 Standard density sea level alt. ft. 450- 3200-46.6-SL 450-3200-45.3-S.L. 450-3200-48-4-S.L. Takeoff (5 min.) , hp., r.p.m., in.Hg. at: Standard density critical alt. ft. 450-3200-48.0-15,000 445-3200-43.3-15,000 420-3200-48.4-15,000 Standard density sea level alt. ft. 450- 3200-46.6-SL 450-3200-45.3-S. L. 450-3200-48.4-S.L. Fuel (min. grade aviation gasoline) 100/100/LL - - - - Lubrication oil (lubricants should conform to the specification as listed). 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 7.30:1 - - - - Weight (dry) lb. (with starter and alternator) 663 (starter only) 714 710 C.G. location (with starter and alternator installed) From front face of prop 27.56 25.65 27.12 mounting flange, in Off 0.25 above; 0.63 left 0.78 above; 0.15 right 0. 21 above, 0;0.50 left crankshaft C.L., in. Propeller shaft flange NOTE 8 - - - - Crankshaft dampers (torsional) 5-third order & 1-second order - - - - Fuel injection PAC* RSA-10DB1 PAC* RSA-10AA1 PAC* RSA-10DB2 Turbocharger-Kelly Aerospace+ model T1879 ( NOTES 4 & 9) T18A21 (NOTES 4 & 9) T18A51 Ignition, dual TCM# S6LN-1208, S6RN-1209 TCM# D6RN-2230 TCM# S6LN-1208, S6RN-1209 Ignition timing °BTC 20 - - - - Spark plugs NOTE 6 - - - - Oil sump capacity, qt. 23 14 Usable oil, qt. (20° nose up or down) 19.5 (18° nose up, 10° nose down (5) 22° nose up, 24° nose down) (9) (See NOTE 10) NOTES 1 through 8 1 through 9 1 through 10 "- -" indicates "same as preceding model." "" indicates "does not apply". *PAC formerly Bendix +Kelly Aerospace formerly AiResearch #TCM formerly Bendix Certification basis: Date of Date Type Certificate Regulations & Amendments Model Application E19EA issued/revised. FAR-33, 33-1, 33-2, 33-3 TIGO-541-C1 A February 29, 1968 November 19, 1968 effective February 1, 1965 TIGO- 541-D1A October 30, 1968 June 26, 1969 TIGO-541-E1A June 23, 1969 June 26, 1969 TIGO-541-B1A September 12, 1968 February 12, 1970 TIGO-541-G1AD October 6, 1971 May 1, 1975 TIGO-541-DIB June 17, 1976 December 3, 1976 Production basis: Production Certificate No. 3. NOTE 1. Maximum permissible temperatures: Models -C1A -D1A, -E1A -B1A -G1AD -DIB Cylinder Head 475°F - - - - - - - - Cylinder Base NOTES 5 - - - - - - - - Oil inlet 245°F - - - - - - - - Fuel injector inlet air 400°F - - - - - - - - Exhaust gas (turbo inlet) 1650°F - - - - - - - - at location shown on Lycoming Dwg. Nos. 63270 63303 63301 63435 63468 Compressor temperature rise 340°F - - - - - - - - NOTE 2. Pressure limits: Injector in Minimum Maximum Idle (min) Idle cut off Fuel pressure limits (above Fuel injector inlet air pressure) at inlet to fuel Injector All models except - DIB 29 p. s.i. 55 p.s.i. 12 p.s.i.  -DIB 29 p.s.i. 65 p.s.i. 12 p.s.i.  Fuel - pressure limits at inlet to engine fuel pump -B1A     -C1A, -D1A, -D1B, -E1A, -G1AD -2 p.s.i. 65 p.s.i.  55 p.s.i. Oil pressure limits: 55 p.s. i. 90 p.s.i. 10 p.s.i.  Starting and warm up  100 p.s.i.   To torquemeter  325 p.s.i.   Air pressure at fuel injector inlet -C1A  45.5 in. Hg.   -D1A  50.0 in. Hg.   -E1A  49.2 in. Hg.   -B1A  50.0 in. Hg.   -G1AD  46.3 in. Hg.   Manifold pressure (cumulative total with altitude adjustment) -C1A 45.0 in. Hg. -D1A 49.5 in. Hg. -E1A 48.7 in. Hg. -B1A 49.5 in. Hg. -G1AD 45.8 in. Hg. -D1B 48.9 in. Hg. Exhaust back pressure 0.5 in. Hg. NOTE 3. The following accessory provisions are available: -C1A, Rotation Speed Ratio Maximum Torque Maximum -D1A, -D1B, Facing to (in.-lb.) Overhang Accessory Drives -B1A -E1A, -G1AD Drive Pad Crankshaft Continuous Static Moment (in.-lb.) Alternator - * Generator *  C 2.800:1 500 2200 400 Tachometer * * CC 0.500:1 7 50 10 Propeller Governor * * CC 0.800:1 125 1500 25 Freon Compressor * * C 1.000:1*** Belt limited 100 Dual drives: (opposite ends of common shaft) Vacuum or * * C 1.000:1 50 Hydraulic Pump Hydraulic or Vacuum Pump * * CC 1.000:1 200 total 1600 total 50 "C" - Clockwise, "CC" - Counter clockwise *Standard, **Optional, ***with drive pulley diameter of 6.00 in. NOTE 4. These engines are equipped with integral mounted Kelly Aerospace (formerly AiResearch) turbochargers as shown on Lycoming Engines drawing numbers indicated: Engine Model Turbocharger Drawing Nos. -B1A T1879 63301 -C1A T1879 63270 -D1A & -E1A T18A21 63303 -G1AD T18A21 63435 -D1B T18A51 63468 Performance data for these engines are presented on Lycoming Curve Nos. as tabulated. Engine Models Curve No. -B1A 13082 -C1A 13034A -D1A 13082 -E1A 13152 -G1AD 13211 -D1B 13321-A These turbochargers meet the containment requirement s of FAR 33 and do not require external protection. NOTE 5. Cylinder base temperature limits are not applicable to engine 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. Description TIGO-541-C1A-Basic model. Six cylinder air cooled, hor izontally-opposed, geared drive, fuel, injected, top induction, down exhaust, turbocharged engine incorporating internal piston cooling oil jets, side mounted accessory drives and a single oil supply from prop. gov. Provision is also made for installation of reverse pitch propeller control. NOTE 7., cont. -D1A - Similar to the -C1A except ha s higher power rating and uses a different turbocharger with provisions for cabin bleed air. -E1A - Similar to the -D1A except has lower power rati ng with different turbocharger spring rate and variable absolute pressure controller. -B1A - Similar to the -C1A except has higher power rating and does not incorporate provisions for cabin bleed air. -G1AD - Similar to the -D1A except in corporates an intercooler, dual magneto and a fuel injector employing fuel head enrichment. -D1B - Similar to -D1A except has an integral wast egate turbocharger with revised exhaust system and incorporates low drag cylinders. NOTE 8. The propeller shaft has a 2:3 ratio to crankshaft rota tion and is positioned 4.92 in. above crankshaft centerline. Propeller rotation is counter clockwise and crankshaft rotation clockwise as viewed form the engine anti-propeller end. Propeller shaft provides a 5 1/4 in. O.D. flange with a 4.25 in. dia. bolt circle. NOTE 9. Air from the compressor of the Kelly Aero space (formerly AiResearch) models T-1879 and T18A21 turbochargers is suitable for cabin pressurization. The installation must provide for cabin air temperature control from 300°F to temperature at 20,000 feet (hot day conditions - maximum engine power). For cabin air inlet flange dimensions see Lycoming Dwg. No. 63270 for -C1A, No. 63303 for -D1A and E1A, No. 63435 for - G1AD, No. 63468 for -D1B. A sonic nozzle must be provided to preclude a ffecting engine performance by cabin air bleed. NOTE 10. With maximum oil temperature, the maximu m nose up is 17° and the maximum nose down is 15°. - END -