TCDS 1E11

Page No. 1 2 3 Rev. No. 6 6 6 Reformatted 12/93 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1E11 Revision 6 LYCOMING ENGINES IGO-540-A1A IGO-540-A1B IGO-540-A1C IGO-540-B1A IGO-540-B1B IGO-540-B1C June 23, 2010 TYPE CERTIFICATE DATA SHEET NO. 1E11 Engines of models described herein conforming with this data sheet (which is part of type certificate No. 1E11) 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 Lycoming Division., AVCO Corp., Williamsport, PA. transferred TC 1E-11 to Lycoming Engines, An Operating Division of AVCO Corporation on June XX, 2010 Model: Lycoming IGO-540-A1A, -A1B -B1A, -B1B, -B1C IGO-540-A1C Type: 6HOA, reduction gear ratio 77:120 - - Rating: Maximum continuous, hp., r.p.m., full throttle at: Sea level pressure altitude 325-3000-S.L. 325-3000-S.L. Takeoff, 5 min., hp., r.p.m., full throttle at: Sea Level Pressure a ltitude 350-3400-S.L. 350-3400-S.L. Fuel (minimum grade aviation gasoline) 100/130 - - Lubricating oil (lubricants should conform to the Specifications as listed or to subsequent revisions thereto.) Lycoming Spec. No. 301-G* - - Bore and stroke, in. 5.125 x 4.375 - - Displacement, cu. in. 541.5 - - Compression ratio 8.7:1 - - Weight (dry), lb. See NOTE 7 - - C.G. location From front face of thrust nut face, in. 19.59 20.23 Off crankshaft center line, in. .56 be low & .21 left .41 below & .26 right Propeller shaft, SAE No. 30 spline - - Crankshaft dampers (torsional) Five 3rd order & one 6th order - - Fuel injection See NOTE 7 - - Ignition, dual See NOTE 7 - - Timing, °BTC 25 - - Spark plugs See NOTE 4 - - Oil sump capacity Dry sump - - NOTES: 1,2,3,4,5,6,7,8 - - "- -" indicates "same as preceding model" "—" indicates "does not apply" * See latest edition of Lycoming Service Instruction 1014 1E11-5 Page 2 Certification basis: Date of Date Type Certificate Regulations & Amendments Model Application No. 1E11 Issued/Revised Car 13 Effective June 15, 1956 IGO- 540-B1A July 5, 1960 October 28, 1960 As Amended by 13-1, 13-2 IGO-540-A1A June 2, 1961 August 22, 1961 13-3 IGO-540-A1B July 10, 1961 August 22, 1961 IGO-540-B1B July 10, 1961 August 22, 1961 13-4 IGO-540-B1C April 18, 1963 May 20, 1963 IGO-540-A1C February 18, 1972 March 14, 1972 Production basis: Production Certificate No. 3 NOTE 1. Maximum permi ssible temperature: Cylinder Head Cylinder Oil (Well type thermocouple) base Inlet 475°F (500°F for -A1C model) (NOTE 8) 235°F NOTE 2. Fuel pressure limits: Injector in Min. Max. Idle (min.) Idle cutoff Inlet to injector (except -A1C model) 20 p.s.i. 26 p.s.i. — — -A1C 25 p.s.i 40 p.s.i. 12 p.s.i. 55 p.s.i. (max.) Oil pressure limits: (Normal operation) 65 p.s.i. 85 p.s.i. (Idling) 25 p.s.i. NOTE 3. The following accessory drives are provided: Accessory -A1A, -A1B -B1A, -B1B, -B1C A1C Rotation Pacing Drive Pad Speed Ratio to Crankshaft Maximum Torque (in. - lb.) Cont. Static Max. Overhang Moment (in. - lb.) Starter * * C 1.000:1 — 12,000 300 Generator * — C 2.600:1 500 2,200 400 Alternator — * C 2.600:1 500 2,200 400 Vacuum Pump * * C 1.083:1 200 800 25 Hydraulic Pump * * C 1.083:1 400 1,650 175 Tachometer * * CC .500:1 7 50 — Propeller Governor * — C .779:1 125 1,200 25 Fuel Pump * * C 1.000:1 25 450 25 * Standard ** Optional "C" Clockwise "CC" Counter Clockwise NOTE 4. Spark plugs: See latest revision of Lycomi ng Service Instruction No. 1042 for approved equipment. NOTE 5. This engine incorporates provisions for absorbing pr opeller thrust in both tractor and pusher type installations. 1E11-5 Page 3 NOTE 6. These engines incorporate th e following additional characteristics: IGO-540 Models -A1A Basis model. -A1B Similar to -A1A except inco rporates low tension ignition system. -A1C Similar to -A1A except for fuel in jector, magnetos, fuel pump, and alternator. -B1A Similar to -A1A except has exhaust ports on the top side of the cylinders and updraft cooling provisions. -B1B Similar to -B1A except inco rporates low tension ignition system. -B1C Similar to -B1A except does not have servo-bleed in Injector servo-vent line and requires external servo-fuel restrictor in servo-vent line of aircraft fuel system. NOTE 7. IGO-540 Models Weight (dry lb. Fuel Injection* Ignition, dual* -A1A 506 RS10ED1 S6RN-204, S6RN-200 -A1B 517 RS10ED1 S6RN-604, S6RN-600 -A1C 509 RSA10DB1 S6RN-1208, S6RN-1209 -B1A 500 RS10ED2 S6RN-204, S6RN-200 -B1B 511 RS10ED2 S6RN-604, S6RN-600 -B1C 500 RS10ED2 S6RN-204, S6RN-200 * Precision Airmotive LLC was Bendix + TCM was Bendix NOTE 8. Cylinder base temperature limits are not applicable to e ngine models which incorporate internal piston cooling oil jets. .....END.....