# TCDS 1E4: Lycoming Engines - Type: Type certificate data sheet - Status: Current - Holder: Lycoming Engines - Revision: 26 - Revised: February 28, 2018 - Product: Engine - Certification basis: Part 33, CAR 13 - Registered aircraft: 7,582, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/fe/18/fe1863b12437a62c2415eb070ca513dab58efcc314fa7cdd3595b870843c8bb7 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/ED61CF457FEE2DC686258250006AC097.0001 - Page: https://openairdocs.org/tcds/1E4 ## Models (81) As the data sheet lists them. - IO-540-L1A5D - IO-540-L1C5 - IO-540-M2A5D - AEIO-540-L1B5 - IO-540-A1A5 - IO-540-W1A5 - IO-540-AA1B5 - IO-540-B1C5 - IO-540-K1J5D - IO-540-AE1A5 - IO-540-G1A5 - AEIO-540-D4B5 - IO-540-C4D5 - IO-540-K1K5 - IO-540-W3A5D - IO-540-K1B5D - IO-540-C1B5 - IO-540-G1B5 - IO-540-K2A5 - IO-540-G1F5 - IO-540-B1B5 - IO-540-N1A5 - IO-540-AC1A5 - IO-540-C4B5 - AEIO-540-D4A5 - AEIO-540-L1B5D - IO-540-V4A5 - IO-540-K1F5D - IO-540-K1J5 - IO-540-M1C5 - IO-540-K1H5 - IO-540-K1D5 - IO-540-C4D5D - IO-540-P1A5 - IO-540-K1B5 - IO-540-S1A5 - IO-540-T4A5D - IO-540-K1E5 - IO-540-K1C5 - IO-540-D4C5 - IO-540-AA1A5 - IO-540-G1D5 - IO-540-T4B5 - IO-540-G1C5 - IO-540-E1A5 - IO-540-C4C5 - IO-540-M1A5 - IO-540-U1A5D - IO-540-D4A5 - IO-540-G1E5 - HIO-540-A1A - IO-540-J4A5 - IO-540-AG1A5 - IO-540-AF1A5 - IO-540-AB1A5 - IO-540-U1B5D - IO-540-E1C5 - IO-540-E1B5 - IO-540-L1A5 - IO-540-L1B5D - IO-540-B1A5 - IO-540-V4A5D - IO-540-M1A5D - IO-540-T4C5D - IO-540-C1C5 - IO-540-D4B5 - IO-540-K1A5D - IO-540-K1G5 - IO-540-K1G5D - IO-540-W1A5D - IO-540-K1E5D - IO-540-C2C - IO-540-R1A5 - IO-540-C4B5D - AEIO-540-D4D5 - IO-540-M1B5D - IO-540-K1F5 - AEIO-540-D4C5 - IO-540-T4B5D - AEIO-540-L1D5 - IO-540-K1A5 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev No. 26 26 26 24 16 25 25 24 24 24 22 26 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TCDS NUMBER 1E4 REVISION: 26 LYCOMING ENGINES MODELS: IO-540-A1A5, - B1A5, -B1B5, -B1C5, -C1B5, -C1C5, -C2C, -C4B5, -C4B5D, -C4D5, -C4C5, -C4D5D, -D4A5, -D4B5, -D4C5, -E1A5, -E1B5, -E1C5, -G1A5, -G1B5, -G1C5, -G1D5, -G1E5, -G1F5 -J4A5, -K1A5, -K1A5D, -K1B5, -K1B5D -K1C5, -K1D5, -K1E5, -K1E5D, -K1F5, -K1F5D, -K1G5 -K1G5D, -K1H5, -K1J5, -K1J5D, -K1K5, -K2A5, -L1A5 -L1A5D, -L1B5D, -L1C5, -M1A5, -M1A5D, -M1B5D, -M1C5, -M2A5D, -N1A5, -P1A5, -R1A5, -S1A5, -T4A5D, -T4B5, -T4B5D, -T4C5D, -U1A5D, -U1B5D, -V4A5D, -V4A5, -W1A5 -W1A5D, -W3A5D, -AA1A5, -AA1B5, -AB1A5, -AC1A5, -AE1A5 -AF1A5, -AG1A5 MODEL HIO-540-A1A MODEL AEIO-540-D4A5, -D4B5, -D4C5, -D4D5, -L1B5D, -L1B5, -L1D5 February 28, 2018 TYPE CERTIFICATE DATA SHEET NO. 1E4 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. 1E4) 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 652 Oliver Street Williamsport, Pennsylvania 17701 Type Certificate Holder Record Textron Lycoming transferred TC 1E4 to Lycoming Engines, An Operating Division of AVCO Corporation on December 17, 2003 1E4 Page 2 of 12 I. Models: IO-540 A1A5, -B1A5, -B1B5, -C1B5, -W1A5D, +-AA1A5 B1C5, -E1A5, -C1C5, -C2C, -W3A5D -AA1B5 -E1B5, -E1C5, G1A5, -C4B5, -C4C5, -W1A5 -G1B5, -G1C5, -G1D5, -J4A5, -C4D5D G1E5, -G1F5, -P1A5, -C4D5 HIO-540-A1A -C4B5D Type 6HOA DIRECT DRIVE - - - - - - Rating 290-2575 250-2575 235-2400 270-2700 Takeoff and maximum SEE NOTE 8 continuous hp., rpm, full throttle at: Sea level pressure altitude +Alternate Rating 250-2425-S.L. Fuel (Minimum grade aviation gasoline) 100/100LL* - - - - - - Injection SEE NOTE 5 - - - - - - Pump drive SEE NOTE 3 - - - - - - Oil Lubrication (Lubricants should conform to the Lycoming Specification - - specifications as listed or to No. 301-E and Service subsequent revisions thereto.) Instruction No. 1014 Oil sump capacity, qt. 12 - - 8 12 Usable oil qt., Normal operation 9.25 - - 6.0 9.25 20° nose up or down (except AEIO)) 9.25 - - 6.0 9.25 30° nose up or down (except AEIO) 8.0 - - 6.0 8.0 30° nose up (AEIO only) # # # # 18° nose down (AEIO only) # # # # Inverted flight (AEIO only) # # # # Ignition, dual # # # # Magnetos SEE NOTE 9 - - - - - - Timing °BTC 20 25 23 20 Spark plugs SEE NOTE 4 - - - - - - Compression Bore and stroke, in. 5.125 X 4.375 - - - - - - Displacement, cu. in. 541.5 - - - - - - Compression ratio 8.7:1 8.5:1 8.5:1 7.3:1 Turbo-supercharger # SEE NOTE 8 # SEE NOTE 8 Weight (dry), lb. SEE NOTE 5 - - - - - - C.G. location SEE NOTE 9 - - - - - - Propeller shaft - Specification Type 2 Flange Modified - - - - - - A.S. 127 Crankshaft dampers (torsional) SEE NOTE 7 - - - - - - NOTES 1,2,3,4,5,6,7 1,2,3,4,5,6,7 1,2,3,4,5,6,7 1,2,3,4,5, 6,7,8,9,10 "- -" indicates "same as preceding" "#" indicates "does not apply" *See latest revision of Lycoming Service Instruction No. 1070 for alternate fuel grades 1E4 Page 3 of 12 II. MODELS: IO-540- -K1A5, -K1A5D, +-K1B5, -K2A5, -K1B5D, +-K1C5, IO-540 -D4A5, IO-540- -T4A5D, +-K1D5, -K1E5, -K1E5D, -D4B5, -T4B5, +-K1F5, -K1F5D, -K1G5, -K1G5D, -K1H5, +-K1J5, -D4C5, -N1A5, -T4B5D, -T4C5D, +-K1J5D, -K1K5, -L1A5, -R1A5, -V4A5D -L1A5D, -L1B5D, -L1C5, AEIO-540-L1B5D, -D4A5 -V4A5 -M1A5, -M1A5D, -M1B5D, - M1C5, -M2A5D, -S1A5, AEIO-540-L1B5, AEIO-540-L1D5 AEIO-540- -U1A5D, -U1B5D -D4A5, -D4B5, -D4C5 -D4D5 Type 6HOA DIRECT DRIVE - - - - - - Rating 300-2700 300-2700 260-2700 260-2700 Takeoff and maximum continuous hp., rpm, full throttle at: sea level pressure altitude + Alternate Rating 290 - 2575 - S.L. Fuel (minimum grade aviation gasoline) 100/100LL* - - - - - - Injection See NOTE 5 - - - - - - Pump drive See NOTE 3 - - - - - - Oil, lubrication (Lubricants should conform to the Lycoming Specification specifications as listed or to No. 301-E and Service subsequent revisions thereto.) Instruction No. 1014. Oil sump capacity, qt. 12 16 12 8 Usable oil qt., Normal operation 9.25 8.0 9.25 6.0 20° nose up or down (except AEIO) 9.25 # 9.25 6.0 30° nose up or down (except AEIO) 8.0 # 8.0 6.0 30° nose up (AEIO only) # 8.0 (37° up, 20° down) 18° nose down (AEIO only) # 7.0 (25° down 6.0 # Inverted flight (AEIO only) # 8.0 6.0 Ignition, dual Magnetos SEE NOTE 9 - - - - - - Timing, °BTC 20 - - 25 - - Spark Plugs SEE NOTE 4 - - - - - - Compression Bore and stroke, in. 5.125 X 4.375 - - - - - - Displacement, cu. in. 541.5 - - - - - - Compression ratio 8.7:1 - - 8.5:1 # Turbo-supercharger # # SEE NOTE 8 # Weight (dry), lb. SEE NOTE 5 C.G. location SEE NOTE 9 - - - - - - Propeller shaft - Specification Type 2 Flange Modified - - - - - - A.S. 127 Crankshaft dampers (torsional) See NOTE 7 - - - - - - NOTES 1,2,3,4,5,6,7,9,10 - - 1,2,3,4,5, 1,2,3,4,5, 6,7,8,9,10 6,7,8,9, 10 "- -" indicates "same as preceding" "#" indicates "does not apply" *See latest revision of Lycoming Service Instruction No. 1070 for alternate fuel grades 1E4 Page 4 of 12 I. Models: IO-540 AB1A5 -AC1A5 -AE1A5 -AF1A5 -AG1A5 Type 6HOA DIRECT DRIVE - - - - -- -- Rating Maximum continuous hp., rpm, in. Hg 230-2400 – FT 300 – 2700 - FT 235 – 2800 – 24.5 260 -2700 260 – 2700 # # Takeoff (5 min) hp., rpm, in. Hg # # 260 – 2800 – 26.2 Fuel (Minimum grade aviation gasoline) 100/100LL* - - - - - - -- Injection SEE NOTE 5 - - - - - - -- Pump drive SEE NOTE 3 - - - - - - -- Oil Lubrication (Lubricants should conform to the Lycoming Specification - - - - - - -- specifications as listed or to No. 301-E and Service subsequent revisions thereto.) Instruction No. 1014 Oil sump capacity, qt. 8 11 12 8 12 Usable oil qt., Normal operation 6.0 5 ½ 2 3/4 6 9.25 20° nose up or down (except AEIO)) 6.0 5 ½ 6 # 30° nose up or down (except AEIO) 6.0 5 ½ 6 # 30° nose up (AEIO only) # - - # # 18° nose down (AEIO only) # - - # # Inverted flight (AEIO only) # - - # # Ignition, dual # - - Magnetos SEE NOTE 9 - - - - - - -- Timing °BTC 23 20 - - - - -- Spark plugs SEE NOTE 4 - - - - - - -- Compression Bore and stroke, in. 5.125 X 4.375 - - - - - - -- Displacement, cu. in. 541.5 - - - - - - -- Compression ratio 8.5:1 8.7:1 - - 8.5:1 7.3:1 Turbo-supercharger # - - - - - - -- Weight (dry), lb. SEE NOTE 5 - - - - - - -- C.G. location SEE NOTE 9 - - - - - - -- Propeller shaft - Specification Type 2 Flange Modified - - - - - - -- A.S. 127 Crankshaft dampers (torsional) SEE NOTE 7 - - - - - - -- NOTES 1,2,3,4,5,6,7 - - - - - - -- "- -" indicates "same as preceding" "#" indicates "does not apply" *See latest revision of Lycoming Service Instruction No. 1070 for alternate fuel grades 1E4 Page 5 of 12 Certification basis: Date Type Certificate Regulations & Amendments Model Date of Application No. 1E4 Issued/Revised CAR 13 effective June 15, 1956 IO-540-B1A5 January 7, 1960 May 5, 1960 As Amended by 13-1, 13-2, 13-3 IO-540-B1B5 June 1, 1960 June 9, 1960 IO-540-A1A5 April 6, 1961 June 30, 1961 IO-540-C1B5 July 6, 1961 January 2, 1962 IO-540-E1A5 April 6, 1962 June 15, 1962 IO-540-B1C5 April 18, 1963 May 20, 1963 IO-540-C1A5 August 9, 1963 August 21, 1963 IO-540-C4B5 October 3, 1963 October 9, 1963 IO-540-C1C5 December 2, 1963 December 31, 1963 IO-540-C2C December 17, 1963 December 31, 1963 Cancelled - IO-540-C1A5 ----- ----------Cancelled - March 6, 1964 IO-540-D4A5 April 1, 1964 May 4, 1964 IO-540-J4A5 December 23, 1964 May 7, 1965 IO-540-K1A5 August 10, 1965 February 9, 1966 IO-540-E1B5 March 11, 1966 March 29, 1966 IO-540-G1B5 May 16, 1966 July 8, 1966 IO-540-K1B5 July 8, 1966 July 22, 1966 IO-540-M1A5 August 18, 1966 January 27, 1967 IO-540-C4C5 August 31, 1966 September 2, 1966 IO-540-G1C5 September 21, 1966 October 14, 1966 IO-540-L1A5 November 2, 1966 May 23, 1967 I0-540-G1D5 December 20, 1966 January 27, 1967 IO-540-G1E5 May 16, 1967 May 26, 1967 IO-540-E1C5 March 8, 1968 March 14, 1968 IO-540-N1A5 November l9, 1968 December 5, 1968 IO-540-P1A5 December 4, 1968 December 9, 1968 IO-540-K1C5 March 24, 1969 March 25, 1969 IO-540-K1D5 August 29, 1969 September 4, 1969 IO-540-R1A5 September 29, 1969 October 6, 1969 IO-540-G1F5 March 5, 1970 March 11, 1970 IO-540-K1E5 November 24, 1970 December 7, 1970 IO-540-K1E5D October 12, 1972 October 21, 1972 IO-540-M2A5D January 4, 1973 January 16, 1973 IO-540-D4B5 March 13, 1973 March 20, 1973 IO-540-K1F5 May 16, 1973 May 25, 1973 IO-540-S1A5 May 16, 1973 May 25, 1973 IO-540-K1F5D May 17, 1973 May 30, 1973 HIO-540-A1A June 18, 1973 March 5, 1974 IO-540-K1A5D May 1, 1974 June 3, 1974 IO-540-K1B5D May 1, 1974 June 3, 1974 IO-540-D4C5 October 30, 1974 November 8, 1974 AEIO-540-D4A5 November 12, 1974 November 26, 1974 AEIO-540-D4B5 November 12, 1974 November 26, 1974 AEIO-540-D4C5 November 12, 1974 November 26, 1974 IO-540 T4A5D April 17, 1975 April 28, 1975 IO-540-U1A5D June 2, 1975 June 12, 1975 IO-540-K1G5 September 10, 1975 September 24, 1975 IO-540-K1G5D September 10, 1975 September 24, 1975 IO-540-U1B5D September 30, 1975 October 23, 1975 IO-540-K1H5 November 12, 1975 December 10, 1975 IO-540-K1J5 November 12, 1975 December 10, 1975 IO-540-K1J5D November 12, 1975 December 10, 1975 IO-540-T4B5D September 20, 1976 September 23, 1976 IO-540-V4A5D July 11, 1978 July 21, 1978 IO-540-L1A5D September 28, 1978 October 6, 1978 IO-540-M1A5D January 22, 1979 January 26, 1979 IO-540-M1B5D November 15, 1979 November 29, 1979 IO-540-C4D5D March 4, 1980 March 13, 1980 1E4 Page 6 of 12 Certification Basis (cont'd) Date Type Certificate Regulations & Amendments Model Date of Application No. 1E4 Issued Revised CAR 13 effective June 15, 1956 IO-540-W1A5D May 6, 1980 June 2, 1980 As Amended by 13-1, 13-2, 13-3 IO-540-AA1A5 September 10, 1980 October 30, 1980 AEIO-540-L1B5D December 16, 1980 February 27, 1981 IO-540-K1K5 June 9, 1981 June 23, 1981 IO-540-W3A5B March 11, 1985 June 6, 1985 IO-540-L1C5 May 7, 1985 June 17, 1985 IO-540-T4C5D January 12, 1987 January 20, 1987 AEIO-540-L1B5 June 1, 1989 June 22, 1989 IO-540-L1B5D February 12, 1987 February 20, 1987 IO-540-T4B5 October 29,1989 November 3,1989 IO-540-K2A5 February 19, 1990 March 29, 1990 IO-540-C4D5 May 15, 1990 June 20, 1990 IO-540-AA1B5 February 19, 1992 February 28, 1992 IO-540-W1A5 June 29, 1992 August 12, 1992 IO-540-M1C5 December 11, 1992 December 18, 1992 IO-540-C4B5D December 23, 1992 February 26, 1993 IO-540-V4A5 October 25, 1995 June 18, 1996 IO-540-AB1A5 April 15, 1996 June 18, 1996 AEIO-540-D4D5 July 9, 1996 July 24, 1996 IO-540-AC1A5 April 3, 1998 May 27, 1998 AEIO-540-L1D5 April 24, 2001 August 1, 2001 IO-540-AE1A5 November 9, 2001 January 22, 2002 Regulations & Amendments Model Date of Application Date Type Certificate FAR 33 effective February 1, 1965 As IO-540-AF1A5 September 26, 2007 May 27, 2008 Amended by 33-1 through 33-20 IO-540-AG1A5 May 10 2012 November XX 2012 Production basis: Production Certificate No. 3 NOTE 1. Temperature Limits (Maximum permissible): Cylinder head (well type thermocouple) 500°F Cylinder base 325°F Cylinder base temperature limits are not applicable to engine models which incorporate internal piston cooling oil jets. Oil inlet 245°F Air inlet to injector See NOTE 8 NOTE 2. Pressure Limits: p.s.i. at inlet to fuel pump Maximum Minimum Fuel: IO-540-C1B5,-C1C5,-C2C,-C4B5,-C4B5D,-C4C5,-C4D5,-C4D5D,-D4A5,-D4B5,-D4C5, -L1C5,-N1A5,-T4A5D,-T4B5,-T4B5D,-T4C5D,-V4A5D,-V4A5,-W1A5D,-W1A5,-W3A5D, -AB1A5, -AC1A5, -AE1A5, -AF1A5; AEIO-540-D4A5,-D4B5,-D4C5,-D4D5 35 -2 IO-540-M2A5D,-M1A5D,-M1B5D 45 -2 IO-540-L1A5, -AG1A5,-K1A5,-K1A5D,-K1B5,-K1B5D, -K1F5D, -K2A5 -K1K5, -M1A5, -M1C5 55 -2 IO-540- K1F5,-K1G5,-K1G5D,-K1H5,-K1J5,-K1J5D,-L1A5D,-L1B5D,-U1A5D,-U1B5D; AEIO-540-L1B5D,-L1B5, L1D5 40 -2 IO-540-J4A5, -R1A5 45 -4 IO-540-AA1A5, -AA1B5 55 -4 IO-540-E1C5,-G1B5,-G1C5,-G1D5,-K1D5,-P1A5,-S1A5; HIO-540-A1A 40 -4 1E4 Page 7 of 12 p.s.i. at inlet to fuel injector Max. Injector Maximum Minimum Minimum Idle in Idle cutoff IO-540-A1A5,-B1A5,-B1C5,-E1A5,-E1B5,-G1A5,-G1E5,-G1F5, 26 20 # # -K1C5,-K1E5,-K1E5D IO-540-B1B5 5 2 # # IO-540-AB1A5,-C1B5,-C1C5,-C2C,-C4B5,-C4B5D,-C4C5, -C4D5,-C4D5D, -D4A5, -D4B5, -D4C5,-J4A5,-N1A5,-R1A5,-T4A5D,-T4B5, -T4B5D, -T4C5D,-V4A5D, -V4A5,-W1A5,-W1A5D, -W3A5D, -AF1A5, -AC1A5; AEIO-540-D4A5,-D4B5,-D4C5 ,-D4D5 45 14 12 55 IO-540-E1C5,-G1B5,-G1C5,-G1D5, -K1D5,-K1F5,-K1J5,-P1A5,-S1A5, -U1A5D,-U1B5D, -L1A5D -L1B5D; AEIO-540-L1B5D,-L1B5, L1D5; HIO-540-A1A 40 18 12 55 IO-540-AE1A5, -M2A5D, -M1A5D, -M1B5D 45 18 12 55 IO-540-K1A5, -K2A5,-K1A5D,-K1B5, -K1B5D, -K1F5D,-K1G5,-K1G5D, -K1H5, -K1J5D, -K1K5, -AA1A5,-AA1B5, -L1A5,-L1C5,-M1A5, -M1C5, -AG1A5 55 18 12 55 Boost Pump Outlet Limits to Injector: Parallel Boosts Series Boosts Maximum Minimum Maximum Minimum Zero fuel flow 45 p.s.i. - 35 p.s.i. - Maximum fuel flow - 14 p.s.i. - 14 p.s.i. Oil: Maximum Minimum Normal operation 95 p.s.i. 55 p.s.i. Idling # 25 p.s.i. Starting, warm-up, Taxi and Take off 115 p.s.i. # "#" indicates does not apply NOTE 3. Accessory Drive Provisions: For additional information on engine drives, refer to the Lycoming Operator's Manual. Accessory Rotation Facing Drive pad Speed Ratio to Crankshaft Maximum Torque (in-lb.) Continuous Static Maximum Overhung Moment (in.-lb.) Starter CC 16.556:1 # 450 150 Generator C 1.910:1 60 120 175 Generator C 2.500:1 60 120 175 Alternator C 3.200:1 60 120 175 Alternator C 3.630:1 60 110 175 Vacuum pump CC 1.300:1 70 450 25 Hydraulic pump C 1.385:1 100 800 40 Hydraulic pump C 0.480:1 100 800 40 Hydraulic pump C 1.300:1 100 800 40 Hydraulic pump C 1.300:1 180 2200 150 Tachometer C 0.500:1 7 50 5 Prop governor C 0.895:1 125 1200 25 Prop governor C 0.947:1 125 2200 25 Fuel pump Plunger 0.500:1 # # 10 Fuel pump CC 1.000:1 25 450 25 Fuel pump C 1.000:1 25 450 25 "#" indicates: Does not apply. "C" Clockwise, "CC" Counter-Clockwise Fuel pump drive pad used for fuel injector drive on Model IO-540-BlB5 "Narrow deck" engines have a propeller governor drive ratio of 0.895:1 and "wide deck" engines have a 0.947:1 ratio. 1E4 Page 8 of 12 NOTE 4. Spark Plugs: See latest revision of Lycoming Service Instruction no. 1042 for approved equipment NOTE 5. Model similarities and differences: Models Weight * (dry) lb. Fuel Injection ** Characteristics IO-540 -A1A5 414 RS-1OED1 Basic model - 6 cylinder, - horizontally opposed aircooled direct drive, with fuel injection, tuned induction, downdraft cooling and bottom side exhaust ports. -AA1A5 448 RSA-10ED1 Same as -S1A5 except has low compression (7.3:1) ratio pistons. -AA1B5 448 RSA-10ED1 Same as -AA1A5 except uses a Slick pressurized impulse magneto instead of a retard magneto. -AB1A5 372 RSA-5AD1 Similar to IO-540-W1A5 Except has more effective counterweights , two Slick impulse magnetos and the fuel injector is located on the bottom of the sump -AC1A5 444 RSA-10ED1 Similar to IO-540-K1C5 except top intake down exhaust -AE1A5 416 RSA-10ED1 Similar to O-540-F1B5 with IO-540-K angle valve cylinders, pistons, piston squirts and fuel injection and induction system -AF1A5 384 RSA-5AD1 Same as -D4B5 except has an oil sump from an O-540-J3A5D modified to accept an injector. -B1A5 411 RS-10B1 Same as -A1A5 except has updraft cooling air and top side exhaust ports. -B1B6 406 Simmonds 530 Same as -B1A5 except has a Simmonds fuel injector. -B1C5 411 RS-10B1 Same as -B1A5 except servo-bleed removed from PAC injector servo vent. -C1B5 374 RSA-5AD1 Differs from A & B series in that it has parallel valve cylinders, untuned induction system, an RSA-5AD1 PAC fuel injector mounted on the bottom of the sump and a diaphragm fuel pump. -C1C5 373 RSA-5AD1 Similar to -C1B5 except accessory housing converted with an AN fuel pump drive to provide for turbocharging. -C2C 373 RSA-5AD1 Similar to -C1B5 except has two 6th order dampers and S6LN-21, S6LN-20 TCM magnetos and an AN fuel pump drive. -C4B5 374 RSA-5AD1 Similar to -C1B5 except incorporates heavier crankshaft counterweights, eligible for use with Hartzell compact propeller. -C4D5 373 RSA-5AD1 Similar to -C4B5 except uses an impulse magneto in place of the retard breaker magneto. -C4D5D 379 RSA-5AD1 Similar to -C4B5 except has a TCM D6LN-2031 impulse coupling dual magneto. -C4C5 373 RSA-5AD1 Same as -C1C5 except incorporates heavier crankshaft counterweights, eligible for use with Hartzell compact propeller. -C4B5D 379 RSA-5AD1 Similar to C4D5D except has retard breaker magneto instead of an impulse magneto. -D4A5 379 RSA-5AD1 Similar to -C4B5 except for hybrid camshaft. -D4B5 381 RSA-5AD1 Same as -D4A5 except has TCM S1200 series magnetos with impulse coupling instead of S-200 series with retard breaker. -D4C5 380 RSA-5AD1 Same as -D4B5 except has a S6LN-1208 magneto instead of S6LN- 1277 magneto. -E1A5 411 RS-10B1 Same as -B1A5 except has internal piston cooling oil jets, thereby increasing maximum heat rejected to oil to 1150 BTU per minute. -E1B5 412 RS-10B1 Same as -E1A5 except has TCM S6LN-1208 and -1209 magnetos. -E1C5 416 RSA-10ED1 Same as -E1B5 except for fuel injector. -G1A5 416 RS-10ED1 Similar to -A1A5 except has internal piston cooling oil jets thereby increasing maximum heat rejected to oil to 1150 BTU per minute. -G1B5 419 RSA-10ED1 Similar to -G1A5 except incorporates TCM 1200 series magnetos and different fuel control. -G1C5 420 RSA-10ED1 Similar to -G1B5 and -G1D5 but has a 38 1/2° angle fuel injector adapter. -G1D5 420 RSA-10ED1 Similar to -G1B5 except TCM S6LN-1227 impulse coupling magneto on left side. * Less starter and alternator 1E4 Page 9 of 12 NOTE 5. Model similarities and differences: (cont'd) Models Weight * (dry) lb. Fuel Injection ** Characteristics IO-540 -G1E5 417 RS-10ED1 Same as -G1A5 except incorporates TCM 1200 series high altitude magnetos. -G1F5 418 RS-10ED1 Same as -G1E5 except has different magneto models. -J4A5 380 RSA-5AD1 Differs from -C4B6 by particulars adapting it for possible turbocharger. -K1A5 438 RSA-10ED1 Similar to -G1A5 except has TCM S6LN-1209 and 1227 magnetos, a RSA-10ED1 fuel injector mounted 38 1/2° left of rear and a stiffer crankshaft. -K1A5D 439 RSA-10ED1 Same as -K1A5 except equipped with a D6LN-2031 dual magneto. -K1B5 438 RSA-10ED1 Same as -K1A5 except that it has a straight air inlet housing. -K1B5D 439 RSA-10ED1 Same as -K1B5 except equipped with a D6LN-2031 dual magneto. -K1C5 438 RS-10ED1 Similar to the -K1A5 has different magnetos, different fuel injector and a straight air inlet adapter. -K1D5 442 RSA-10ED1 Similar to -K1B5 except has different magnetos and a flange fuel injector inlet coupling. -K1E5 439 RS-10ED1 Same as -K1B5 except has different fuel injector. -K1E5D 435 RS-10ED1 Same as -K1E5 except has TCM D-2000 series, impulse coupling dual magneto. -K1F5 442 RSA-10ED1 Same as -G1B5 but with IO-540-K series rotating system. -K1F5D 438 RS-10ED1 Same as -K1F5 but with TCM D-2000 series, retard breaker dual magneto. -K1G5 437 RSA-10ED1 Same as -K1A5 except equipped with a diaphragm type fuel pump and drive. -K1G5D 438 RSA-10ED1 Same as -K1A5D except equipped with a diaphragm type fuel pump and drive. -K1H5 437 RSA-10ED1 Same as -K1B5 except equipped with a diaphragm type fuel pump and drive. -K1J5 441 RSA-10ED1 Same as -K1F5 except equipped with a diaphragm type fuel pump and drive. -K1J5D 437 RSA-10ED1 Same as -K1F5D except equipped with a diaphragm type fuel pump and drive. -K1K5 438 RSA-10ED1 Same as -K1A5 except has high crush main bearings and crankcase rear oil drain holes. -K2A5 438 RSA-10ED1 Similar to -K1A5 except incorporates different propeller flange bushings. -L1A5 441 RSA-10AD1 Same as -K1A5 except for induction system housing and fuel injector mounted to the front. -L1A5D 437 RSA-10AD1 Same as -L1A5 except has a TCM D6LN-2031 impulse coupling dual magneto. -L1B5D 470 RSA-10AD1 Same as AEIO-540-L1B5D except not equipped with aerobatic components -L1C5 440 RSA-10AD1 Same as -L1A5 except equipped with a diaphragm type fuel pump. -M1A5 436 RSA-10AD1 Similar to -K1B6 except has up exhaust, different injector, different length ignition harness and ni-resist exhaust valve guides. -M1A5D 435 RSA-10AD1 Same as -M2A5D except has provisions for a controllable propeller. -M1B5D 436 RSA-10EA1 Similar to -M1A5D except has impulse magneto, straight inlet fuel injector adapter and a diaphragm type fuel pump. -M1C5 437 RSA-10AD1 Similar to -M1A5 except has impulse magneto instead of a retard magneto. -M2A5D 435 RSA-10AD1 Same as -M1A5 except has TCM D-2000 series magneto instead of S- 1200 series magnetos. * Less starter and alternator 1E4 Page 10 of 12 NOTE 5. Model similarities and differences: (cont'd) Models Weight * (dry) lb. Fuel Injection ** Characteristics IO-540 -N1A5 397 RSA-5AD1 Similar to the -D4A5 except has a stiffer crankshaft and heavier 5th and6th order dampers thereby being eligible for use with an extended hub propeller. -P1A5 424 RSA-10ED1 Similar to the -G1B5 except incorporates a larger engine oil pump and suitable for turbocharging. -R1A5 406 RSA-5AD1 Similar to -N1A5 except has different magnetos and is suitable for turbocharging. Incorporates piston cooling oil jets. -S1A5 444 RSA-10ED1 Same as -P1A5 but with IO-540-K series rotating system. -T4C5D 393 RSA-5AD1 Same as -T4B5D except equipped with TCM retard breaker dual magneto and has a maximum oil capacity of 10 quarts. -T4A5D 381 RSA-5AD1 Same as -D4B5 except has horizontal rear inlet fuel injector and equipped with a D6LN-2031 dual magneto. -T4B5D 381 RSA-5AD1 Same as -T4A5D except for fuel drain boss location. -T4B5 387 RSA-5AD1 Similar to -T4B5D except is equipped with two Slick magnetos in place of the TCM dual magneto. -U1A5D 423 RSA-10ED1 Same as -L1A5 except has top-side exhaust port cylinder heads and equipped with a D6LN-2031 dual magneto. -U1B5D 422 RSA-10ED1 Same as -J1A5D except equipped with a diaphragm type fuel pump and drive. -V4A5D 383 RSA-5AD1 Similar to -T4B5D except equipped with a front mounted fuel injector instead of a rear inlet fuel injector. -V4A5 389 RSA-5AD1 Similar to -V4A5D except is equipped with two Slick magnetos in place of the TCM dual magneto. -W1A5D 369 RSA-5AD1 Similar to O-540-J1A5D (TC-E295) except equipped with oil sump, intake pipes, and fuel injection system from the -V4A5D. -W1A5 369 RSA-5AD1 Similar to -W1A5D except is equipped with two Slick magnetos in place of the TCM dual magneto. -W3A5D 370 RSA-5AD1 Same as -W1A5D except has heavier crankshaft counterweights. HIO- 540-A1A 443 RSA-10ED Same as IO-540-K1A5 except to be used in helicopter application. AEIO- 540-D4A5 384 RSA-5AD1 Same as IO-540-D4A5 except equipped with an inverted oil system kit for aerobatic flight. -D4B5 386 RSA-5AD1 Same as IO-540-D4B5 except equipped with an inverted oil system kit for aerobatic flight. -D4C5 385 RSA-5AD1 Same as IO-540-D4C5 except equipped with an inverted oil system kit for aerobatic flight. -D4D5 386 RSA-5AD1 Same as AEIO-540-D4A5 except AN type fuel pump -L1B5D 445 RSA-10AD1 or RSA- 10DB1 (Opt.) Similar to IO-540-L1A5D except equipped with an inverted oil system and modified oil sump for aerobatic flight. -L1B5 449 RSA-10AD1 or RSA- 10DB1 (Opt.) Same as AEIO-540 -L1B5D except is equipped with two Slick magnetos in place of the TCM dual magneto. -L1D5 449 RSA-10AD1 or RSA- 10DB1 (Opt.) Same as AEIO-540-L1B5 except has larger capacity oil pump. -AG1A5 436 RSA-10ED1 Similar to the IO-540-M1A5 except low compression pistons large capacity oil pump and high flow nozzles. * Less starter and alternator NOTE 6. Accessories and Equipment: Starter, generators and alternators approved for use on these engines are listed in the latest revisions of Lycoming Service Instruction No. 1154. NOTE 7. These engines incorporate crankshafts with one fifth order and one sixth order dampers unless the number "5" is omitted in the fourth position of the model designation, i.e. -C2C which has two sixth order dampers. These engines also have variations in crankshafts and counterweights; therefore, for approved engine and propeller combinations refer to the specific propeller and aircraft TC data sheets. 1E4 Page 11 of 12 NOTE 8. Engine models IO-540-J4A5 and -R1A5 are eligible for turbocharging and under these conditions, the following additional limits apply: intake air manifold pressure max. 29.0 in. Hg. absolute exhaust back pressure max. 32 in. Hg. absolute at inlet to turbocharger for - J4A5; (33.5 in. Hg. for -R1A5); air inlet temperature to injector max.400 degrees F. Engine model IO-540-AA1A5 is eligible for turbo charging when equipped in accordance with Piper Aircraft Corporation installation Drawing No. 300076 and under these conditions the following additional modified limits apply: intake air manifold pressure max. 37.0 in. Hg. absolute at 2425 r.p.m.; exhaust back pressure max. 43 in. Hg. absolute at intake to turbocharger; air inlet temperature to injector max. 400 degrees F; and fuel pressure limits to the injector are 21 to 40 p.s.i. NOTE 9. For all models - ignition and center of gravity: C.G. location (dry with starter and generator installed) Models Ignition, dual* + From front face of propeller mounting flange (in.) Off prop. shaft C.L. (in.) Vertical Lateral IO-540 -A1A5, -B1B5, -B1A5,-B1C5 TCM S6LN-200, S6LN-204 18.34 1.41 below 0.18 left -C1B5; -C1C5, TCM S6LN-200, S6LN-204 or 18.16 1.15 below 0.21 left -C4B5, -C4C5 Slick 675, 674 -C2C, C4D5 TCM S6LN-21, S6LN-20 18.16 1.15 below 0.21 left -C4D5D TCM D6LN-2031 or 3000 18.16 1.15 below 0.21 left -D4A5 TCM S6LN-200, S6LN-204 18.16 1.15 below 0.21 left -D4B5 TCM S6LN-1227, S6LN-1209 18.16 1.15 below 0.21 left -D4C5 TCM S6LN-1208, S6LN-1209 18.16 1.15 below 0.21 left -E1A5 TCM S6LN-200, S6LN-204 18.34 1.15 below 0.21 left -E1B5, -E1C5 TCM S6LN-1208, S6LN-1209 18.34 1.41 below 0.18 left -G1A5 TCM S6LN-200, S6LN-204 18.34 1.41 below 0.18 left -G1B5 TCM S6LN-1208, S6LN-1209 18.34 1.41 below 0.18 left -G1C5, -G1D5 TCM S6LN-1227, S6LN-1209 18.44 0.98 below 0.03 left -G1E5 TCM S6LN-1208, S6LN-1209 18.34 0.98 below 0.03 left -G1F5 TCM S6LN-1227, S6LN-1227 or 18.34 1.41 below 0.18 left S6LN-1209 -J4A5 TCM S6LN-1208, S6LN-1209 18.16 1.41 below 0.18 left -K1A5, -K1B5, TCM S6LN-1227, S6LN-1227 or 18.25 1.15 below 0.21 left -K1K5, -K2A5 S6LN-1209 -K1A5D TCM D6LN-2031 or 3000 18.25 0.88 below 0.16 right -K1B5D TCM D6LN-2031 or 3000 18.25 0.88 below 0.16 right -K1C5, -K1D5 TCM S6LN-200, S6LN-204 18.25 0.88 below 0.16 right -K1E5 TCM S6LN-1227, S6LN-1209 or 18.25 0.88 below 0.16 right S6LN-1227 -T4C5D TCM D6LN-3200 18.36 -K1E5D, -L1A5D TCM D6LN-2031 or 3000 18.25 0.88 below 0.16 right -K1F5, -AA1A5 TCM S6LN-1208, S6LN-1209 18.25 0.88 below 0.16 right -K1F5D TCM D6LN-2230 or 3200 18.25 0.88 below 0.16 right -K1G5, -K1H5 TCM S6LN-1227, S6LN-1209 or S6LN-1227 18.25 0.88 below 0.16 right -K1G5D TCM D6LN-2031 or 3000 18.25 0.88 below 0.16 right -M1B5D TCM D6LN-2031 or 3000 13.29 0.89 below 0.17 right -K1J5 TCM S6LN-1208, S6LN-1209 18.25 0.88 below 0.16 right -K1J5D TCM D6LN-2230 or 3200 18.25 0.88 below 0.16 right -L1A5, -L1C5 TCM S6LN-1227, S6LN-1209 17.91 0.88 below 0.16 right *For alternate magnetos see latest Lycoming Service Instruction (S.I.) 1443. + TCM formally Bendix ¶ 1E4 Page 12 of 12 NOTE 9. For all models - ignition and center of gravity: (cont'd) C.G. location (dry with starter and generator installed) Models Ignition, dual* + From front face of propeller mounting flange (in.) Off prop. shaft C.L. (in.) Vertical Lateral IO-540 -M1A5 TCM S6LN-1208, S6LN-1209 18.29 0.89 below 0.17 right -M2A5D,-M1A5D TCM D6LN-2230 or 3200 18.29 0.89 below 0.17 right -N1A5 TCM S6LN-200, S6LN-204 17.76 1.10 below 0.12 left -P1A5 TCM S6LN-1208, S6LN-1209 18.44 0.98 below 0.03 left -R1A5 TCM S6LN-1208, S6LN-1209 17.76 1.10 below 0.12 left -S1A5 TCM S6LN-1208, S6LN-1209 18.25 0.88 below 0.16 right -T4A5D,-T4B5D TCM D6LN-2031 or 3000 18.36 1.08 below 0.17 left -T4B5 Slick 6251, 6250 or 6251 18.36 1.08 below 0.17 left -U1A5D,-U1B5D TCM D6LN-2031 or 3000 17.91 0.88 below 0.16 right -V4A5D TCM D6LN-2031 or 3000 17.25 0.50 below 0.25 left -V4A5 Slick 6351, 6350 17.25 0.50 below 0.25 left -W1A5D,-W3A5D TCM D6LN-3000 17.60 0.77 below 0.20 left -W1A5 Slick 6361, 6350 17.60 0.77 below 0.20 left -AB1A5 Slick 6351 (2) 17.60 (#) 0.77 below 0.20 left -AA1B5 Slick 6360, 6361 18.25 0.88 below 0.16 right -AC1A5 Slick 6351 (2) 18.03 (#) 0.13 above 0.11 left -AE1A5 TCM S6LN-204, S6LN-200 18.44 0.98 below 0.03 left -AF1A5 TCM S6LN-1227, S6LN-1209 or S6LN-1227 17.94 0.69 below 0.19 left -AG1A5 TCM S6LN-1208, S6LN-1209 or Slick 6393, 6350 18.29 0.89 below 0.17 right HIO-540 -A1A TCM S6LN-1227, S6LN-1209 or One each Slick 6351 and 6350 18.25 0.88 below 0.16 right AEIO-540 -D4A5 TCM S6LN-200, S6LN-204 18.16 1.15 below 0.21 left -D4B5 TCM S6LN-1227, S6LN-1209 18.16 1.15 below 0.21 left -D4C5 TCM S6LN-1208, S6LN-1209 18.16 1.15 below 0.21 left -D4D5 Slick6393, 6350 18.16 1.15 below 0.21 left AEIO &IO- 540- -L1B5D TCM D6LN-3000 17.19 0.77 below 0.16 right AEIO-540 -L1B5 Slick 6351 (2), 6350 or 6351 17.19 0.77 below 0.16 right -L1D5 Slick 6351 (2) , 6350 or 6351 17.19 0.77 below 0.16 right *For alternate magnetos see latest Lycoming Service Instruction (S.I.) 1443. + TCM formally Bendix (#) No Alternator installed NOTE 10. 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Effective Oct 19, 1998 - [AD 97-15-11](https://openairdocs.org/ad/97-15-11): Cylinder kits · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 538 more. Effective Aug 12, 1997 - [AD 97-01-04](https://openairdocs.org/ad/97-01-04): Cylinder assemblies · Lycoming Engines IO-540-M1B5D, LTIO-540-F2BD, LTIO-540-J2B and 10 more. Effective Apr 22, 1997 - [AD 96-23-03](https://openairdocs.org/ad/96-23-03): High pressure fuel pumps · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 174 more. Effective Dec 23, 1996 - [AD 96-09-10](https://openairdocs.org/ad/96-09-10): Oil pump · Lycoming Engines AEIO-320-E1A, AEIO-320-E1B, AEIO-320-E2A and 334 more. Effective Jul 15, 1996 - [AD 95-26-02](https://openairdocs.org/ad/95-26-02): Aviation Gasoline · Lycoming Engines IO-320-B1A, IO-320-B1B, IO-320-B1C and 182 more. Effective Jan 24, 1996 - [AD 95-07-01](https://openairdocs.org/ad/95-07-01): Connecting Rod Bolt · Lycoming Engines AEIO-360-A1E, AEIO-360-B1G6, AEIO-360-H1A and 177 more. Effective Apr 12, 1995 - [AD 92-12-05](https://openairdocs.org/ad/92-12-05): Piston Pins · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 532 more. Effective Jul 10, 1992 - [AD 87-10-06 R1](https://openairdocs.org/ad/87-10-06-R1): Rocker Arm Assembly · Lycoming Engines IO-360-B4, IVO-360-A1A, O-340-A1A and 243 more. Effective Sep 1, 1989 - [AD 83-22-04](https://openairdocs.org/ad/83-22-04): Injector Fuel Diaphragm Stem · Lycoming Engines AEIO-540-L1B5D, IO-540-AA1A5, IO-540-G1B5 and 30 more. Effective Nov 4, 1983 - [AD 81-03-05](https://openairdocs.org/ad/81-03-05): Mixture Control Shaft Assembly · Lycoming Engines IGO-540-A1A, IGO-540-B1A, IGO-540-B1C and 9 more. Effective Feb 11, 1981 - [AD 79-04-05](https://openairdocs.org/ad/79-04-05): Regulator Diaphragm Stem Assembly · Lycoming Engines AEIO-320-D1B, AEIO-320-E1A, AEIO-320-E1B and 215 more. Effective Sep 26, 1979 - [AD 78-23-08](https://openairdocs.org/ad/78-23-08): Fuel Pump To Fuel Injector Tube Elbow · Lycoming Engines IO-540-G1B5, IO-540-K1F5, IO-540-P1A5 and 1 more. Effective Nov 7, 1978 - [AD 78-23-10](https://openairdocs.org/ad/78-23-10): Center Body Bellows Seal Assembly · Lycoming Engines AEIO-320-D1B, AEIO-320-E1A, AEIO-320-E1B and 218 more. Effective Nov 7, 1978 - [AD 75-08-09](https://openairdocs.org/ad/75-08-09): Oil Pump Drive Shaft · Lycoming Engines AEIO-360-A1B, AEIO-360-A1B6, AEIO-360-A1C and 365 more. Effective Aug 18, 1977 - [AD 73-23-01](https://openairdocs.org/ad/73-23-01): Piston Pin Assembly · Lycoming Engines AIO-360-A1A, AIO-360-A1B, AIO-360-A2A and 215 more. Effective Jan 13, 1977 - [AD 75-09-15](https://openairdocs.org/ad/75-09-15): Fuel Starvation To The Engine · Lycoming Engines AIO-320-A1A, AIO-320-A1B, AIO-320-A2A and 130 more. Effective Apr 30, 1975 - [AD 73-10-02](https://openairdocs.org/ad/73-10-02): Bendix Fuel Injectors · Bendix Fuel Injectors, AIO-320-A1A, AIO-320-A1B and 88 more. Effective May 16, 1973 - [AD 69-08-09](https://openairdocs.org/ad/69-08-09): Lycoming Engines IO-540-G1A5. Effective Apr 23, 1969 - [AD 66-06-03](https://openairdocs.org/ad/66-06-03): Connecting Rod Assemblies · Lycoming Engines GO-435-C2 (O-435-17), GO-435-C2A, GO-435-C2A2 and 317 more. Effective Jan 16, 1969 - [AD 67-22-06](https://openairdocs.org/ad/67-22-06): Fuel Injectors · Lycoming Engines HIO-360-A1A, HIO-360-B1A, HIO-360-B1B and 28 more. Effective Aug 9, 1967 - [AD 66-20-04](https://openairdocs.org/ad/66-20-04): Oil Filter Adapter Gasket · Lycoming Engines IO-320-A1A, IO-320-A2A, IO-320-B1A and 121 more. Effective Aug 27, 1966 - [AD 64-16-05](https://openairdocs.org/ad/64-16-05): AC Pumps · Lycoming Engines HIO-360-B1A, HIO-360-B1B, IO-320-B1A and 86 more. Effective Jul 10, 1964 - [AD 63-14-03](https://openairdocs.org/ad/63-14-03): Oil Pump Drive Shaft · Lycoming Engines IO-540-A1A5, IO-540-B1A5, IO-540-B1B5 and 21 more. Effective Jul 6, 1963 - [AD 2024-21-02](https://openairdocs.org/ad/2024-21-02) (historical): Engine (Reciprocating) · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 548 more. Effective Dec 5, 2024 - [AD 2011-26-04](https://openairdocs.org/ad/2011-26-04) (historical): Externally mounted fuel injector fuel lines · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1B and 186 more. Effective Jan 25, 2012 - [AD 2011-15-10](https://openairdocs.org/ad/2011-15-10) (historical): Fuel servos · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 256 more. Effective Aug 16, 2011 All 61: https://openairdocs.org/tcds/1E4/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Lycoming IO-540 series](https://openairdocs.org/engine/lycoming-io-540-series): 4,219 aircraft (registry codes 41530, 41585) - [Lycoming IO-540-AE1A5](https://openairdocs.org/engine/lycoming-io-540-ae1a5): 1,040 aircraft (registry code 41899) - [Lycoming IO-540-AB1A5](https://openairdocs.org/engine/lycoming-io-540-ab1a5): 771 aircraft (registry code 41808) - [Lycoming AEIO-540 series](https://openairdocs.org/engine/lycoming-aeio-540-series): 433 aircraft (registry code 41568) - [Lycoming IO-540-D4A5](https://openairdocs.org/engine/lycoming-io-540-d4a5): 237 aircraft (registry code 41798) - [Lycoming IO-540-C4B5](https://openairdocs.org/engine/lycoming-io-540-c4b5): 179 aircraft (registry code 41651) - [Lycoming AEIO-540-D4A5](https://openairdocs.org/engine/lycoming-aeio-540-d4a5): 56 aircraft (registry code 41799) - [Lycoming AEIO-540-L1B5](https://openairdocs.org/engine/lycoming-aeio-540-l1b5): 56 aircraft (registry code 41792) - [Lycoming IO-540-K1G5D](https://openairdocs.org/engine/lycoming-io-540-k1g5d): 52 aircraft (registry code 41598) - [Lycoming IO-540-AC1A5](https://openairdocs.org/engine/lycoming-io-540-ac1a5): 50 aircraft (registry code 41809) - [Lycoming IO-540-K1G5](https://openairdocs.org/engine/lycoming-io-540-k1g5): 48 aircraft (registry code 41674) - [Lycoming IO-540-K1A5](https://openairdocs.org/engine/lycoming-io-540-k1a5): 44 aircraft (registry code 41663) - [Lycoming AEIO540-L1B5D](https://openairdocs.org/engine/lycoming-aeio540-l1b5d): 41 aircraft (registry code 41791) - [Lycoming IO-540-V4A5D](https://openairdocs.org/engine/lycoming-io-540-v4a5d): 39 aircraft (registry code 41807) - [Lycoming IO-540-C4D5D](https://openairdocs.org/engine/lycoming-io-540-c4d5d): 31 aircraft (registry code 41652) - [Lycoming IO-540-W1A5](https://openairdocs.org/engine/lycoming-io-540-w1a5): 31 aircraft (registry code 41660) - [Lycoming IO-540-G1D5](https://openairdocs.org/engine/lycoming-io-540-g1d5): 26 aircraft (registry code 41644) - [Aerosport IO-540-D4A5](https://openairdocs.org/engine/aerosport-io-540-d4a5): 25 aircraft (registry code 01308) - [Lycoming IO-540-L1C5](https://openairdocs.org/engine/lycoming-io-540-l1c5): 18 aircraft (registry code 41782) - [Lycoming IO-540-K1B5](https://openairdocs.org/engine/lycoming-io-540-k1b5): 17 aircraft (registry codes 41665, 42718) - [Lycoming IO-540-T4B5](https://openairdocs.org/engine/lycoming-io-540-t4b5): 17 aircraft (registry code 41804) - [Lycoming IO-540-A1A5](https://openairdocs.org/engine/lycoming-io-540-a1a5): 16 aircraft (registry code 41634) - [Lycoming IO-540-D4B5](https://openairdocs.org/engine/lycoming-io-540-d4b5): 13 aircraft (registry code 41794) - [Lycoming IO-540-K1J5](https://openairdocs.org/engine/lycoming-io-540-k1j5): 10 aircraft (registry code 41676) - [Lycoming IO-540-S1A5](https://openairdocs.org/engine/lycoming-io-540-s1a5): 10 aircraft (registry code 41788) - [Lycoming IO-540-C1B5](https://openairdocs.org/engine/lycoming-io-540-c1b5): 9 aircraft (registry code 41649) - [Lycoming IO-540-J4A5](https://openairdocs.org/engine/lycoming-io-540-j4a5): 9 aircraft (registry code 41655) - [Lycoming IO-540-AA1A5](https://openairdocs.org/engine/lycoming-io-540-aa1a5): 8 aircraft (registry code 41661) - [Lycoming IO-540-W1A5D](https://openairdocs.org/engine/lycoming-io-540-w1a5d): 8 aircraft (registry code 41658) - [Lycoming IO-540-G1A5](https://openairdocs.org/engine/lycoming-io-540-g1a5): 7 aircraft (registry code 41641) - [Lycoming IO-540-N1A5](https://openairdocs.org/engine/lycoming-io-540-n1a5): 7 aircraft (registry code 41796) - [Lycoming IO-540-K1E5](https://openairdocs.org/engine/lycoming-io-540-k1e5): 5 aircraft (registry code 41671) - [Lycoming IO-540-B1A5](https://openairdocs.org/engine/lycoming-io-540-b1a5): 4 aircraft (registry code 41635) - [Lycoming IO-540-E1A5](https://openairdocs.org/engine/lycoming-io-540-e1a5): 4 aircraft (registry code 41638) - [Lycoming IO-540-E1B5](https://openairdocs.org/engine/lycoming-io-540-e1b5): 4 aircraft (registry code 41639) - [Lycoming IO-540-L1B5D](https://openairdocs.org/engine/lycoming-io-540-l1b5d): 4 aircraft (registry code 41781) - [Lycoming IO-540-P1A5](https://openairdocs.org/engine/lycoming-io-540-p1a5): 4 aircraft (registry code 41647) - [Lycoming IO-540-T4A5D](https://openairdocs.org/engine/lycoming-io-540-t4a5d): 4 aircraft (registry code 41803) - [Lycoming AEIO-540-D4B5](https://openairdocs.org/engine/lycoming-aeio-540-d4b5): 3 aircraft (registry code 41800) - [Lycoming IO-540-G1B5](https://openairdocs.org/engine/lycoming-io-540-g1b5): 3 aircraft (registry code 41642) - [Lycoming IO-540-G1C5](https://openairdocs.org/engine/lycoming-io-540-g1c5): 3 aircraft (registry code 41643) - [Lycoming IO-540-K1A5D](https://openairdocs.org/engine/lycoming-io-540-k1a5d): 3 aircraft (registry code 41664) - [Lycoming HIO-540-A1A](https://openairdocs.org/engine/lycoming-hio-540-a1a): 2 aircraft (registry code 41648) - [Lycoming IO-540-K1F5](https://openairdocs.org/engine/lycoming-io-540-k1f5): 2 aircraft (registry code 41672) - [Lycoming IO-540-K1H5](https://openairdocs.org/engine/lycoming-io-540-k1h5): 2 aircraft (registry code 41675) - [Lycoming IO-540-M1B5D](https://openairdocs.org/engine/lycoming-io-540-m1b5d): 2 aircraft (registry code 41785) - [Lycoming IO-540-M1C5](https://openairdocs.org/engine/lycoming-io-540-m1c5): 2 aircraft (registry code 41786) - [Lycoming IO-540-C2C](https://openairdocs.org/engine/lycoming-io-540-c2c): 1 aircraft (registry code 41653) - [Lycoming IO-540-D4C5](https://openairdocs.org/engine/lycoming-io-540-d4c5): 1 aircraft (registry code 41795) - [Lycoming IO-540-K1C5](https://openairdocs.org/engine/lycoming-io-540-k1c5): 1 aircraft (registry code 41668) All 79: https://openairdocs.org/tcds/1E4/aircraft.md ## STCs approved under this data sheet (70, first 50) - [STC SE04651CH](https://openairdocs.org/stc/SE04651CH): To allow use of l00R grade aviation fuel meeting Swift Fuel, LLC specification SPEC-l00R-22. Swift Fuels LLC - [STC SE00825WI](https://openairdocs.org/stc/SE00825WI): Installation of Specialty Products Spin-on oil filter on Lycoming Engines.. B & C Specialty Products Inc. - [STC SE04349CH](https://openairdocs.org/stc/SE04349CH): Installation of SureFly electronic ignition. SureFly Partners Ltd. - [STC SE01954SE](https://openairdocs.org/stc/SE01954SE): Installation of engine crankcase seal.. Ly-Con Rebuilding Company - [STC SE02352CH](https://openairdocs.org/stc/SE02352CH): Installation of Challenger cleanable oil filter assembly. Challenger Aviation Products Inc. - [STC SE00939WI](https://openairdocs.org/stc/SE00939WI): Installation of B&C Specialty Products Model BC 315-( ) Starter on Lycoming engines.. B & C Specialty Products Inc. - [STC SE2387CE](https://openairdocs.org/stc/SE2387CE): Installation of B & C Speciality Products lightweight (10.2 pounds) engine starter P/N BC 315-100-1(12 volt) or P/N BC 315-100-3(24 volt).. B & C Specialty Products Inc. - [STC SE03309CH](https://openairdocs.org/stc/SE03309CH): Installation of Engine Preheat Kit, p/n TSP6CYL-2927-115 for 115 volt application. Hartzell Propeller Inc. - [STC SE60WE](https://openairdocs.org/stc/SE60WE): Installation of two Rajay Turbochargers P/N RJ 0327-1 or -2 and 9 lb. Sonic nozzle.. TALCO Aviation - [STC SE6WE](https://openairdocs.org/stc/SE6WE): Installation of two Roto-Master Turbochargers Model No. 3DT5FF10J2, P/N 600572-00 (formerly Rajay Model 315F10, P/N RJ0080-100, or 102). TALCO Aviation - [STC SE85WE](https://openairdocs.org/stc/SE85WE): Installation of two Roto-Master turbochargers Model 3DT5FF10J2, P/N RJ 0080-102. TALCO Aviation - [STC SE01436LA](https://openairdocs.org/stc/SE01436LA): Installation of Firewall Forward Technologies LLC modified camshaft. Centri-lube Technologies LLC - [STC SE04577CH](https://openairdocs.org/stc/SE04577CH): Install an electronic engine ignition system. Electroair Acquisition Corp - [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc. - [STC SE01537AT](https://openairdocs.org/stc/SE01537AT): Replace counterweights on Lycoming O-540-A1A5, -A1B5, -A1C5, -A1D5, and IO-540-C1B5 engines.. Whelen Aerospace Technologies - [STC SE3873NM](https://openairdocs.org/stc/SE3873NM): Installation of two AiResearch induction air intercoolers.. Franklin Aircraft Engines Inc. - [STC SE8628SW](https://openairdocs.org/stc/SE8628SW): Installation of oil nozzles for lubrication of cam and filters.. Cygnet Aerospace Corp - [STC SE09445SC](https://openairdocs.org/stc/SE09445SC): Installation of fuel injector nozzles.. General Aviation Modifications Inc. - [STC SE03498AT](https://openairdocs.org/stc/SE03498AT): Conversion of Lycoming IO-540-D4B5 to Alamo Aerospace Model IO-540-D4B5-AA that has the same performance ratings and limitations as Lycoming Model IO-540-D4B5. Air Plains Services Corporation - [STC SE1339SW](https://openairdocs.org/stc/SE1339SW): Modify pistons to Drawings 11007 and 11015; piston rings. Continental Motors, Inc. - [STC SE4408SW](https://openairdocs.org/stc/SE4408SW): Miscellaneous engine cylinder replacement parts.. Continental Motors, Inc. - [STC SE7509SW](https://openairdocs.org/stc/SE7509SW): Installation of any or all parts listed on Airmotive Engineering Drawing List No. 852-1, Rev. 1, dated 10/4/88, or later FAA approved revision.. Continental Motors, Inc. - [STC SE7667SW](https://openairdocs.org/stc/SE7667SW): Installation of parts listed on Drawing List No. 8810-3, Rev 6.. Continental Motors, Inc. - [STC SE8776SW](https://openairdocs.org/stc/SE8776SW): Installation of coated cylinders and piston rings.. Continental Motors, Inc. - [STC SE00218NY](https://openairdocs.org/stc/SE00218NY): Replacement of Lycoming starter with SKY-TEC 12 volt starter installed.. Hartzell Engine Technologies, LLC - [STC SE00226NY](https://openairdocs.org/stc/SE00226NY): Replacement of Lycoming starter with SKY-TEC 24-volt starter Models 149-24HT and 122-24HT. Approval limited to 24-volt DC source available to the starter.. Hartzell Engine Technologies, LLC - [STC SE00357NY](https://openairdocs.org/stc/SE00357NY): Replacement of Lycoming starter with SKY-TEC 24-volt starter installed.. Hartzell Engine Technologies, LLC - [STC SE2901NM](https://openairdocs.org/stc/SE2901NM): Lycoming valve cover gasket. Real Gaskets Tennessee - [STC SE2902NM](https://openairdocs.org/stc/SE2902NM): Lycoming valve cover gasket. Real Gaskets Tennessee - [STC SE3329NM](https://openairdocs.org/stc/SE3329NM): Lycoming valve cover gasket. Real Gaskets Tennessee - [STC SE7582SW](https://openairdocs.org/stc/SE7582SW): Grinding of high compression NITRIDED Cylinders to .010 oversize, as an alternative to chrome plating or rebarreling, and the installation of SL10207 P10 Piston, SL74241 P10 Top and second compression ring, and SL 73857 P10 oil control ring. Superior Air Parts, Inc - [STC SE01211SE](https://openairdocs.org/stc/SE01211SE): Installation of the Merlyn Products Inc. turbocharger system. Merlyn Products Inc. - [STC SE02050AK](https://openairdocs.org/stc/SE02050AK): Grind nitrided high compression cylinder barrels to plus 0.010 oversize and install P10 piston, P10 compression rings, and P10 oi l rings.. Custom Aircraft Inc - [STC SE00357DE](https://openairdocs.org/stc/SE00357DE): Modification to Textron Lycoming engine for the installation of turbonormalizing system.. Fly In Vacations - [STC SE02436AT](https://openairdocs.org/stc/SE02436AT): Installation of 200F series fuel pump assembly.. Kelly Aerospace Energy Systems LLC - [STC SE02555AT](https://openairdocs.org/stc/SE02555AT): Consolidated Fuel Systems 201F series fuel pump assembly on various Textron Lycoming engine models.. Kelly Aerospace Energy Systems LLC - [STC SE00768CH](https://openairdocs.org/stc/SE00768CH): Replace Slick 6000, 6100, 6200 and 6300 series magnetos and TCM/Bendix S6-20, S6-200 and S6-1200 series magnetos with the Champion Limited Authority Spark Advance Regulator (LASARTM) ignition system. Champion Aerospace LLC - [STC SE01524CH](https://openairdocs.org/stc/SE01524CH): Replace Slick 6000, 6100, 6200, 6300, 4000, 4100, 4200, and 4300 series magnetos and TCM/Bendix S6-20, S6-200, S6-1200, S-20, S-200, and S-1200 series magnetos with Champion Limited Authority Spark Advance Regulator (LASAR ) Model 4755 and 6755 bush kit ignition systems.. Champion Aerospace LLC - [STC SE8193SW](https://openairdocs.org/stc/SE8193SW): Grind nitriden high compression cylinder barrles to plus .010 oversize and install SL75089 P10 piston, SL74242 P10 compression ring, and SL73857 P10 oil ring.. Superior Air Parts Inc. - [STC SE611GL](https://openairdocs.org/stc/SE611GL): Incorporation of a fuel flow transducer.. Shadin Avionics - [STC SE01930NY](https://openairdocs.org/stc/SE01930NY): Installation of Casper Labs 90 degree oil filter housing adapter.. Casper Labs Inc - [STC SE7734SW](https://openairdocs.org/stc/SE7734SW): Modification of engine for operation with ethanol fuel.. Shauck Dr Maxwell E Jr. - [STC SE1779NM](https://openairdocs.org/stc/SE1779NM): Installation of Precise Flight, Inc. Standby Vacuum System SVS III. Precise Flight Inc - [STC SE21WE](https://openairdocs.org/stc/SE21WE): Installation of Turbosupercharger 406610-3.. GE Engine Services-Corporate Aviation Inc. DBA Garrett Aviation Services - [STC SE22WE](https://openairdocs.org/stc/SE22WE): Installation of AiResearch Turbosupercharger 406610-3. Approved for IO-540-J4A5 model.. GE Engine Services-Corporate Aviation Inc. DBA Garrett Aviation Services - [STC SE5743NM](https://openairdocs.org/stc/SE5743NM): Intallation of adapter for externally mounted oil filter.. Aviation Development Corporation - [STC SE00890LA](https://openairdocs.org/stc/SE00890LA): Installation of Nickson's cylinder barrels on Lycoming reciprocating engine models.. Nickson's Machine Shop Inc - [STC SE1657NM](https://openairdocs.org/stc/SE1657NM): Installation of Rotomaster3AU2ME60H3 (or H2) and3AV2ME60H3 (or H2), turbo- chargers, optional intercooler and associated systems.. Machen Inc - [STC SE3590NM](https://openairdocs.org/stc/SE3590NM): Installation of Machen intercooler and associated systems.. Machen Inc - [STC SE09492SC](https://openairdocs.org/stc/SE09492SC): Installation and usage of Exxon 20W50 multigrade aircraft engine oil conforming to Exxon Oil formulation WS-3013.. Exxon Company USA All 70: https://openairdocs.org/tcds/1E4/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.