TCDS E00009NY

Page No. 1 2 3 Rev. No. 5 4 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TCDS NUMBER E00009NY Revision No. 5 LYCOMING ENGINES MODEL : TEO-540-A1A, C1A October 22, 2020 TYPE CERTIFICATE DATA SHEET NO. E00009NY Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E00009NY) 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 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 652 Oliver Street Williamsport, Pennsylvania 17701 Model: TEO-540 -A1A -C1A Type 6 HOA Direct Drive Turbocharged, electronically controlled -- Rating Maximum continuous hp., rpm at standard density critical alt. ft 350-2500 – 8,000 375-2575 – 10,000 Fuel Minimum grade aviation gasoline Lycoming Service Instruction 1070 -- Pressure NOTE 2 -- Pump NOTE 5 -- Pump drive NOTE 3 -- Oil, Lubrication (Lubricants should conform to the specification as listed or to subsequent revisions thereto) Lycoming Service Instruction 1014 -- Temperature NOTE 1 -- Pressure NOTE 2 -- Sump capacity, qt. 12 -- Usable oil qt. Engine Position 9 NOTE 8 -- Ignition, electronic -- ECU (electronic control unit) NOTE 5 -- Timing °BTC Variable (electronic) -- Spark plugs NOTE 4 -- Bore and stroke, in. 5.125 x 4.375 -- Displacement, cu. in. 541.5 -- Compression Ratio 7.3:1 -- Weight (dry) lb. NOTE 5 -- C.G. Location NOTE 5 -- Crankshaft Counterweights & Rollers One 5th order, One 6th order -- Turbocharger TAO411 TH08A60 Propeller shaft, SAE No. AS-127 Flange, Type 2 Modified -- NOTES 1 through 12 1 through 12 "--" indicates "same as preceding models" "─ " indicates "does not apply" Page 2 of 3 E00009NY Certification basis: Regulations & Amendments FAR 33 effective February 1, 1965, as amended by 33-1 through 33-34 Model Date of Application Date Type Certificate No. E00009NY Issued/Revised TEO-540-A1A December 27, 2008 November 1, 2018 TEO-540-C1A February 4, 2016 November 26, 2018 Production basis: Production Certificate No. 3 NOTE 1. Maximum permissible temperatures: Cylinder Head (Well Type Thermocouple) Oil Inlet Exhaust Gas TEO-540-A1A 500°F 245°F 1750°F TEO-540-C1A 500°F 245°F 1650°F NOTE 2. Pressure limits: Fuel: p.s.i.g. at Inlet to Fuel Pump Fuel Rail Pressure Maximum Minimum TEO-540-A1A, -C1A 65 -2 43 psid (above Manifold pressure) Manifold: Maximum (in. Hg. Abs.) TEO-540-A1A 42.0 TEO-540-C1A 57.9 Oil: Maximum (p.s.i.) Minimum (p.s.i.) Normal 95 55 Idle  25 Starting and warm-up 115  Turbocharger exhaust back pressure: Maximum (in. Hg.) 0.5 NOTE 3. The following accessory provisions are available: Accessory TEO-540-A1A TEO-540-C1A Direction of Rotation Drive Ratio Maximum Torque (in. lb) Maximum Overhang Moment Continuous Static (in. lb.) Starter• ** ** CC 16.556:1 -- 450 150 Alternator• ** -- C 3.80:1 60 120 175 Alternator• -- ** C 3.65:1 60 120 175 Alternator• -- ** C 3.10:1 60 120 175 Accessory Drive #1× * * CC 1.30:1 70 800 25 Accessory Drive #2× * -- C 1.30:1 100 800 40 Accessory Drive #2× -- * C 1.385:1 100 800 40 Accessory Drive #3× * -- C 3.54:1 40 300 25 Fuel Pump * * C 1.0:1 25 450 25 Propeller Governor * * C 0.947:1 125 2200 25 Freon Comp. Drive -- ** C 1.462:1*** Limited by belt. -- "C" - Clockwise, "CC" - Counter-Clockwise, * Typical, ** Optional ***With compressor pulley diameter of 6.00 inches • These accessories are optional, see latest revision of SI 1154 for the approved alternates. × These drives are optional and accessory pads may be cast over. Rotation facing drive pad Page 3 of 3 E00009NY NOTE 4. Spark plugs approved for use on this engine are listed in the latest revision of Lycoming Service Instruction No. 1042. NOTE 5. The following tabulations show std. dry weight (less alternator, starter, ECU, and power box), C.G.'s, fuel pumps and ECUs for this model. Center of Gravity Model Weight Lb. * From Front Face of Prop Shaft Flange in. Off Crankshaft Center Line, in. Fuel Pump ECU TEO-540-A1A 588.6 21.08 1.69 below 0.05 left HET 200F-5007 ACU-100 TEO-540-C1A 553.5 22.50 0.25 below 0.00 right HET 200F-5007 ACU-100 * Less Starter, Alternator, ECU, and Power Box  See latest revision of Lycoming SI 1573 for the approved alternates. NOTE 6. The listed models incorporate the following additional similarities or differences: Model Characteristics TEO-540-A1A Basic Model. Six cylinder, air-cooled, horizontally opposed, direct drive, turbocharged engine with electronic fuel injection, electronic ignition, electronic boost control, electronic propeller control, down exhaust and incorporates induction air coolers. The rotating section is similar to the TIO-540-J2BD. The induction and turbo supercharging systems are similar to the TIO-540- AE2A. TEO-540-C1A Similar to -A1A except rating is increased, does not have electronic propeller control, is equipped with one TH08A60 turbocharger, and includes density compensation. NOTE 7. Starters and alternators approved for use on this engine are listed in the latest revision of Lycoming Service Instruction No. 1154. NOTE 8. Maximum flight attitudes for the TEO-540-A1A, -C1A are 20° nose up or down. NOTE 9. The electronic control system for the TEO-540-A1A, -C1A contains level “B” software according to RTCA Document DO-178B which has been shown to meet the requirements for 14 CFR Part 23 single and multi engine aircraft regardless of takeoff weight, with the exception of commuter category aircraft. See latest revision of Lycoming SI 1573 for approved electronic control units. The ECUs specified in SI 1573 control all engine cylinders. NOTE 10. The electronic control system for the TEO-540-A1A, -C1A must be supplied with secondary 14 or 28 VDC power source via an aircraft essential bus, backed up with the aircraft backup battery. The aircraft backup battery must be serviced and/or replaced at the interval specified in the aircraft or battery Maintenance Manual. NOTE 11. Installation and evaluation of the ECU cockpit indications is subject to the requirements established by the certification basis of the aircraft. NOTE 12. Takeoff is prohibited with annunciated NTO (No Take-off) faults shown on the ECU cockpit indications. ......END.....