TCDS 1E7

Page No. 1 2 3 4 Rev No. 7 6 7 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1E7 Revision 7 Lycoming Engines IGSO-540-A1A, -A1C -A1D, -A1E, -A1F, -A1H IGSO-540-B1A, -B1C June 23, 2010 TYPE CERTIFICATE DATA SHEET NO. 1E7 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. 1E7) 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 Div ., AVCO CORP., Williamsport, PA. transferred TC 284 to Lycoming Engines, An Operating Division of AVCO Corporation on June 23, 2010 Model IGSO-540-A1A, -A1D -A1C, -A1E, -A1H -A1F -B1A, -B1C Type 6H0A; reduction gear ratio 77:120 - - - - - - Rating Maximum continuous, hp., r.p.m, in. Hg., at: Critical pressure altitude 360-3200-41.7-10,500 360-3200-41.7-10,500 360-3200-41.7-10,500 360-3200-40.5-11,500 Sea level pressure altitude 360-3200-45.0-S.L. 360-3200-45.0-S.L. 360-3200-45. 0-S.L 360-3200-45.0-S.L. Takeoff (5 min.), hp., r.p.m., in. Hg., at: Critical pressure altitude 380-3400-43.5-10,500 380-3400-43.5-10,500 380-3400-43.5-10,500 380-3400-43.5-12,000 Sea level pressure altitude 380-3400-47.0-S.L. 380-3400-47.0-S.L. 380-3400-47.0- S.L. 380-3400-47.0-S.L. Fuel (Minimum grade aviation gasoline) 100/130 - - - - - - Lubricating oil (Lubricants should conform to the specifications as listed or later revision thereto.) Lycoming Spec. No. 301-G* - - - - - - Bore and stroke. in. 5.125 X 4.375 - - - - - - Displacement, cu. in. 541.5 - - - - - - Supercharger gear ratio 11.27:1 - - - - - - Compression ratio 7.30:1 - - - - - - Weight (dry), lb. See NOTE 8 - - - - - - C.G. location From front face of thrust nut face, in. 23.55 23.70 23.55 23.55 Off crankshaft center line, in. .50 above & .16 left .95 above & .16 left .50 above & .16 left .50 above & .16 left Propeller shaft, SAE No. AND 10152 30 spline - - - - - - Crankshaft dampers (torsional) Five 3rd order and One 6th order - - - - - - * See latest edition of Lycoming Service Instruction 1014 1E7 2 Model (cont'd) IGSO-540-A1A, -A1D -A1C, -A1E, -A1H -A1F -B1A, -B1C Fuel injection See NOTE 8 - - - - - - Ignition, dual See NOTE 8 - - - - - - Timing, °BTC 25 - - - - - - Spark plugs See NOTE 6 - - - - - - Oil sump capacity dry sump - - - - - - NOTES 1,2,3,4,5,6,7,8,9 1,2,3,4,5,6,8,9 1,2,3,4,5,6,8,9 1,2,3,4,5,6,7,8,9 "- -" indicates "same as preceding model" "" indicates "does not apply" Certification basis: Regulations and Amendments Model (s) Date of Application Date Type Certificate No. 1E7 Issued/Revised CAR 13 Effective June 15, 1956 As Amended By 13-1, 13-2, & 13-3 IG SO-540-B1A March 4, 1960 June 17, 1960 -A1A March 14, 1961 September 22, 1961 -A1B November 29, 1961 December 19, 1961 (Note No. 7) -A1C March 16, 1962 May 31, 1962 13-4 -B1B November 13, 1963 December 20, 1963 (Note No. 7) -A1D February 8, 1965 March 22, 1965 -B1C February 8, 1965 March 22, 1965 -A1E August 10, 1965 August 20, 1965 -A1F June 7, 1966 July 11, 1966 -A1H August 19, 1974 August 29, 1974 Production basis: Production Certificate No. 3 NOTE 1. Maximum permissible temperatures: Cylinder head (bayonet type thermocouple) 475° F (except 500°F for -A1A, -A1C, -A1H models) Cylinder base 315°F (See NOTE 9) Oil inlet 235°F NOTE 2. Fuel pressure limits - p.s.i. Emergency M i n . Max. Min. Max. For Simmonds injectors (-B1A, -B1C) Series 580 - P/N 580056-B -2 +15 +9 +15 Inlet to injector Integral supply pump Series 582 - P/S's 582025 & 582026 -2.5 +24 +9 +35 Inlet to injector Integral supply pump Integral supply pump to injector +9 +35 +9 +35 For PAC (formerly Bendix) injector Inlet to injector +17 +35   Oil pressure limits - p.s.i. Normal Operation Min. Max. Idle -A1D, -A1E, -A1F 65 85 25 -A1A, -A1C, -A1H 55 85 25 -B1A, -B1C 65 85 35 3 1E7 NOTE 3. The following accessory provisions are incorporated: -A1A, -A1D, Maximum Torque Maximum Overhang -A1C, -A1E, -B1A Rotation Faci ng Speed Ratio in. -lb. Moment Accessory A1F, -A1H -B1C Drive Pad to Crankshaft Cont Static in. - lb. Starter X X C 1.000:1  12,000 300 Generator X X C 2.600:1 500 2,200 400 Vacuum Pump X X CC 1.083:1 200 800 25 Hydraulic Pump X X C 1.083:1 400 1,650 175 Tachometer X X CC .500:1 7 50  Propeller governor X X C .779:1 125 1200 25 Fuel pump ** X  C 1.000:1 25 450 25 "C" - Clockwise, "CC" - Counter clockwise ** - Fuel pump pad supplied only on engines w ith PAC (formerly Bendix) Fuel Injector. X - Standard NOTE 4. These engines incorporate provisions for absorbing pr opeller thrust in both tractor and pusher type installations. NOTE 5. The above models incorporate additional characteristics as follows: IGSO-540 Models Characteristics -A1A Basic model - six-cylinder horizonta lly opposed air cooled, supercharged geared drive dry sump engine with side mounted accessories. Incorporates internal piston cooling oil jets. Has PAC* RS-10FB1 fuel injection system and new supercharger air inlet housing and supporting brackets. -A1C Same as -A1A has straight through inlet housing between injector and supercharger. -A1D Similar to -A1A except ha s TCM+ S6RN-1208 and S6RN-1209 magnetos. -A1E Similar to -A1C has TC M+ S6RN-1208 and S6RN-1209 magnetos. -A1F Same as -A1D excep t has no PAC* modulator unit. -A1H Same as -A1E except does not incorporate the PAC* modulator unit. -B1A Same as -A1A except has updraft exhaust cooling and Simmonds type 580 fuel injection system. -B1C Similar to -B1A except has TCM+ S6RN-1208 and S6RN-1209 magnetos. * PAC formerly Bendix +TCM formerly Bendix NOTE 6. Spark plugs: See latest revision of Lycomi ng Service Instruction No. 1042 for approved equipment. NOTE 7. The IGSO-540-A1B and -B1B engine models were canceled from Engine Type Certificate No. 1E7 on March 21, 1963 and March 22, 1965 respectively. Th ere were no production models of these engines. 1E7 4 NOTE 8. IGSO-540- Models Weight (dry), lb. Fuel Injection Ignition, dual -A1A 540 RS10-FB1+ S6RN-604, S6RN-600# -A1C 539 * (-A1C) RS10-FB1+ S6RN-604, S6RN-600# -A1D 530 RS10-FB1+ S6RN-1209, S6RN-1208# -A1E 529 RS10-FB1+ S6RN-1209, S6RN-1208# -A1F 530 RS10-FB1+ S6RN-1209, S6RN-1208# -A1H 541 RS10-FB1+ S6RN-1209, S6RN-1208# -B1A 532 Simmonds 580 Series, P/N 580056-B S6RN-604, S6RN-600# Simmonds 582 Series, P/N 582025 or 582026 -B1C 522 Simmonds 580 Series, P/N 580056-B S6RN-1209, S6RN-1208# Simmonds 582 Series, P/N 582025 or 582026 + PAC (Precision Airmotive Co rporation llC) formerly Bendix # TCM formerly Bendix * The fuel vent line between the fuel injector system a nd the aircraft fuel tank must incorporate a flow restriction within pressure limits of 20 to 28 p.s.i. at 30 p.p.h. fuel vapor vent flow for the IGSO-540-A1C only. NOTE 9. This parameter dispensed with, for engines of thes e models equipped with internal piston cooling oil jets. .....END.....