TCDS E14EA

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 22 22 22 22 22 22 22 22 17 16 16 16 16 17 21 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E14EA Revision 22 Lycoming Engines TIO-540-A1A, -A1B, -A2A, -A2B, -A1C, -A2C, -C1A, -E1A, -F2BD, -G1A, -H1A, -J2B, -J2BD, -K1AD, -N2BD, -R2AD, -S1AD, -T2AD, -U2A, -V2AD, -W2A, -AA1AD, -AB1AD, -AB1BD -AE2A, -AF1A, -AF1B, -AG1A, -AH1A, -AJ1A, AK1A LTIO-540-F2BD, -J2B, -J2BD, -K1AD, -N2BD, -R2AD, -U2A, -V2AD, -W2A May 24, 2012 TYPE CERTIFICATE DATA SHEET NO. E14EA Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E14EA) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certification 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 manual and other approved instructions. Type Certificate Holder Lycoming Engines, An operating Division of Avco Corporation Williamsport, Pennsylvania 17701 Type Certificate Holder Record Textron Lycoming, AVCO Co rporation transferred TC E14EA to Lycoming Engines, An Operating Division of Avco Corporation on December 17, 2003. 2 of 15 E14EA Model Lycoming TIO-540-A1A, -A1B, -A2A, -A2B TIO-540-A1C, -A2C TIO-540-E1A Type 6HOA Direct Drive Turbocharged Rating (See Notes 4 and 13) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft . 310-2575-40.2-15,000 310-2575-42.-15,000 260-2575-36.0-15000 Standard density sea level alt. ft. 310- 2575-38.6-S.L. 310-2575-40.0- S.L. 260-2575-34.1-S.L. Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft . 310-2575-40.2-15,000 310-2575-41.5-15,000 260-2575-36.0-15000 Standard density sea level alt., ft. 310- 2575-38.6-S.L. 310-2575-40.0- S.L. 260-2575-34.1-S.L. Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 22.22 - - 19.47 Off crankshaft C.L., in. 0.88 below & 0.18 right - - 3.00 below & 0.11 left Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - Crankshaft dampers (torsional) One 5th order One 6th order - - - - - - One 6th order (Note 8) Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 - - - - Usable oil, qt. (20° nose up or down) 9 1/4 - - - - NOTES - as applicable 1-7, 9, 10 1-7, 9, 10 1-10 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 3 of 15 E14EA Model Lycoming TIO-540-H1A TIO-540-F2BD LTIO-540-F2BD TIO-540-J2B, -J2BD, -N2BD, LTIO-540-J2B, -J2BD, -N2BD Type 6HOA Direct Drive Turbocharged Rating (See Notes 4 and 13) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft . 270-2575-37.5-15,000 325-2575-46.0-15000 350-2575-46.0-15000 Standard density sea level alt. ft. 270- 2575-35.9-S.L. 325-2575-43.5- S.L. 350-2575-43.0-S.L. Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft . 270-2575-37.5-15,000 325-2575-46.0-15000 350-2575-46.0-15000 Standard density sea level alt., ft. 270-2575-35.9-S.L. 325-2575-43.5-S.L. 350-2575-43.0-15000 Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 19.47 22.19 22.75 Off crankshaft C.L., in. 3.00 below & 0.11 left 0.88 below & 0.18 right 0.75 below & 0.16 right Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - Crankshaft dampers (torsional) One 5th order One 6th order (Note 8) - - One 6th order - - - - Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 - - - - Usable oil, qt. (20° nose up or down) 9 1/4 - - - - NOTES -- as applicable 1-10 1-7, 9, 10 1-7, 9, 10 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 4 of 15 E14EA Model Lycoming TIO-540-R2AD LTIO-540-R2AD TIO-540-C1A, -G1A TIO-540-K1AD LTIO-540-K1AD Type 6HOA Direct Drive Turbocharged Rating (See Note 4) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft. 340-2575-44.0-15000 250-2575-34.0-15000 250-2575-34.0-15000 Standard density sea level alt. ft. 350- 2575-44.0-S.L. 250-2575-33.0- S.L. 250-2575-34.0-S.L. Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft. 340-2575-44.0-15000 250-2575-34.0-15000 250-2575-34.0-15000 Standard density sea level alt., ft. 350- 2575-44.0-S.L. 250-2575-33.0- S.L. 250-2575-34.0-S.L. Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 22.75 19.27 21.0 Off crankshaft C.L., in. 0.75 below & 0.16 right 2.30 below & 0.23 left 0.50 below & 0.31 left Propeller shaft flange, SAE A.S. 127 Type 2 modified - - Crankshaft dampers (torsional) One 5th order One 6th order - - One 6th order (Note 8) - - - - Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 - - 8 Usable oil, qt. (20° nose up or down) 9 1/4 - - 6 NOTES - as applicable 1-7, 9, 10, 11, 13 1-10 1-10 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 5 of 15 E14EA Model Lycoming TIO-540-S1AD TIO-540-T2AD TIO-540-U2A LTIO-540-U2A Type 6HOA Direct Drive Turbocharged Rating (See Note 4) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft. 295-2700-36.0-16000 330-2400-43.0-12000 350-2500-42.2-12000 Standard density sea level alt. ft. 300-2700-36.0-S.L. & 12000 ft. 330-2400-40.5-S.L. 350-2500-41.2-S.L. Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft. 295-2700-36.0-16000 330-2400-43.0-12000 350-2500-42.2-12000 Standard density sea level alt., ft. 300-2700-36.0-S.L. & 12000 ft. 330-2400-43.0-S.L. 350-2500-41.2-S.L. Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 18.58 22.75 20.38 Off crankshaft C.L., in. 1.31 below & 1.00 right 0.75 below & 0.16 right 1.4 below & 0.25 right Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - Crankshaft dampers (torsional) One 5th order One 6th order (Note 8) - - - - - - - - Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 - - - - Usable oil, qt. (20° nose up or down) 9 3/4 - - - - NOTES - as applicable 1-10 1-7, 9. 10 1-7, 9, 10 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 6 of 15 E14EA Model Lycoming TIO-540-V2AD LTIO-540-V2AD (See Note 14) TIO-540-W2A LTIO-540-W2A (See Note 14) TIO-540-AA1AD* TIO-540-AB1AD TIO-540-AB1BD Type 6HOA Direct Drive Turbocharged Rating (See Note 4) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft. 340-2600-42.0-18000 350-2600-44.2-15000 250-2575-32.5-15000 Standard density sea level alt. ft. 350- 2600-42.0-S.L. 350-2600-44.2- S.L. 250-2575-32.5-S.L. Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft. 340-2600-42.0-18000 350-2600-44.2-15000 250-2575-32.5-15000 Standard density sea level alt., ft. 350- 2600-42.0-S.L. 350-2600-44.2- S.L. 250-2575-32.5-S.L. Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 23.05 22.10 18.91 Off crankshaft C.L., in. 0.59 below & 0.14 right 0.10 below & 0.48 right 2.20 below & 0.67 left Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - Crankshaft dampers (torsional) One 5th order One 6th order - - - - - - - - Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 - - - - ** Usable oil, qt. (20° nose up or down) 9 1/4 - - - - *** NOTES - as applicable 1-7, 9, 10, 14 1-7, 9, 10, 14 1-7, 9, 10, 15 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. *TIO-540-AA1AD Model is approved with an alternate rating of 270hp/2575 rpm from S.L. to 15,000 ft. ** 10 for AA1AD *** 7 1/4 for AA1AD. 7 of 15 E14EA Model Lycoming TIO-540-AE2A TIO-540-AF1A TIO-540-AF1B TIO-540-AG1A Type 6HOA Direct Drive Turbocharged Rating (See Note 4) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft. 350-2500-42.0-20000 270-2575-36.5-20000 270 - 2575 - 36.5 -15000 Standard density sea level alt. ft. 350-2500- 42.0-S.L. 270-2575-35.0-S.L. 270 - 2575 - 36.5 - SL Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft. 350-2500-42.0-20000 270-2575-36.5-20000 270 - 2575 - 36.5 -15000 Standard density sea level alt., ft. 350-2500- 42.0-S.L. 270-2575-35.0-S.L. 270 - 2575 - 36.5 - SL Fuel (minimum grade aviation gasoline) 100/100LL - - - - Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301-F Service Instruction No. 1014 - - - - Bore and stroke, in. 5.125 X 4.375 - - - - Displacement, cu. in. 541.5 - - - - Compression ratio See Note 10. - - - - Weight (dry) lb. See Note 10. - - - - C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 18.88 18.30 19.00 Off crankshaft C.L., in. 0.95 below & 0.63 left 2.30 below & 0.64 left 1.75 below & 1.20 left Propeller shaft flange, SAE A.S. 127 Type 2 modified - - - - Crankshaft dampers (torsional) One 5th order One 6th order - - - - - - - - Fuel injection Note 10 - - - - Turbocharger Note 10 - - - - Ignition, dual Note 10 - - - - Ignition timing °BTC 20 - - - - Spark plugs Note 6 - - - - Oil sump capacity, qt. 12 10 10 Usable oil, qt. (20° nose up or down) 9 1/4 7 1/4 5 NOTES - as applicable 1-7, 9, 10, 11 1-7, 9, 10 1-10, 12 “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. 8 of 15 E14EA Model Lycoming TIO-540-AH1A*** TIO-540-AJ1A TIO-540-AK1A Type 6HOA Direct Drive Turbocharged Rating (See Note 4) Maximum continuous hp., rpm, in. Hg. at: Standard density critical alt. ft. 300 - 2500 - 38.0 -12000 310 - 2500 - 39.0 – 14000 235 – 2400 – 32.0 -15000 Standard density sea level alt. ft. 300 - 2500 - 38.0 - SL 310 - 2500 - 39.0 - SL 235 – 2400 – 32.0 - SL Takeoff (5 min.) hp., rpm, in. Hg. at: Standard density critical alt. ft. 300 - 2500 - 38.0 –12000 310 - 2500 - 39.0 – 14000 235 – 2400 – 32.0 -15000 Standard density sea level alt., ft. 300 - 2500 - 38.0 - SL 310 - 2500 - 39.0 - SL 235 – 2400 – 32.0 - SL Fuel (minimum grade aviation gasoline) 100/100LL - - -- Lubricating oil (lubrication should conform to the specification as listed or to subsequent revisions thereto) Lycoming Spec. No. 301- F Service Instruction No. 1014 - - -- Bore and stroke, in. 5.125 - - -- Displacement, cu. in. 4.375 - - -- Compression ratio See Note 10. - - -- Weight (dry) lb. See Note 10. - - -- C.G. location (with starter and alternator installed) From front face of prop. mounting flange, in. 18.70 18.50* 18.94* Off crankshaft C.L., in. 1.87 below & 1.00 right 0.75 below & 1.13 left* 1.50 below & 1.25 left* Propeller shaft flange, SAE A.S. 127 Type 2 modified - - -- Crankshaft dampers (torsional) One 5th order One 6th order - - -- Fuel injection Note 10 - - -- Turbocharger Note 10 - - -- Ignition, dual Note 10 - - -- Ignition timing °BTC 20 - - 23** Spark plugs Note 6 - - -- Oil sump capacity, qt. 12 11 8 Usable oil, qt. (20° nose up or down) 9 1/4 5 1/2 4 NOTES - as applicable 1-10, 12 - - -- “- -” indicates “same as preceding model.” For alternate fuel grades, see the latest revision of Lycoming Service Instruction 1070. * No alternator installed ** See Note 16 *** See Note 17 Certification Basis: Regulations and Amendments Date Type Certificate Model Date of Application E14EA Issued/Revised CAR 13 effective June 15, 1956 TIO-540-A1A May 26, 1964 December 6, 1965 as amended by 13-1, 13-2, 13-3, 13-4 TIO-540-A1B October 6, 1967 October 9, 1967 TIO-540-A2A March 26, 1968 April 1, 1968 TIO-540-A2B March 26, 1968 April 1, 1968 TIO-540-C1A September 7, 1967 June 6, 1968 TIO-540-E1A September 3, 1970 September 18, 1970 TIO-540-G1A September 2, 1970 September 18, 1970 TIO-540-A1C November 17, 1970 January 6, 1971 TIO-540-A2C November 17, 1970 January 6, 1971 TIO-540-H1A April 8, 1971 April 16, 1971 TIO-540-F2BD April 20, 1970 July 23, 1971 9 of 15 E14EA Certification Basis: (cont’d) Regulations and Amendments Date Type Certificate Model Date of Application E14EA Issued/Revised LTIO-540-F2BD February 9, 1972 February 16, 1972 L/TIO-540-J2BD August 25, 1971 April 7, 1972 L/TIO-540-K1AD December 4, 1973 February 28, 1974 L/TIO-540-N2BD January 29, 1973 February 16, 1973 TIO-540-R2AD April 23, 1975 September 25, 1975 LTIO-540-R2AD October 7, 1977 October 13, 1977 TIO-540-S1AD January 31, 1977 June 14, 1977 TIO-540-T2AD February 17, 1981 March 5, 1981 L/TIO-540-U2A June 2, 1981 February 12, 1982 L/TIO-540-J2B August 20, 1981 September 9, 1981 L/TIO-540-V2AD December 22, 1981 January 31, 1983 L/TIO-540-W2A October 29, 1982 August 17, 1984 TIO-540-AB1AD June 14, 1984 January 16, 1985 TIO-540-AA1AD February 20, 1985 June 25, 1985 TIO-540-AE2A March 9, 1987 August 12, 1988 TIO-540-AF1A September 13, 1988 June 23, 1989 TIO-540-AB1BD May 18, 1993 August 11, 1993 TIO-540-AG1A December 1, 1994 June 20, 1995 TIO-540-AF1B December 7, 1995 January 25, 1996 TIO-540-AH1A February 12, 1997 June 25, 1997 TIO-540-AJ1A March 5, 1998 April 30, 1998 TIO-540-AK1A February 22, 2000 February 2, 2001 Production basis: Production Certificate No. 3. NOTE 1. Maximum permissible temperatures: Cylinder head (well type thermocouple) 500°F (480°F model - W2A, -V2AD, -AJ1A) Cylinder base Note 5 Oil inlet 245°F Exhaust gas *1650° F (See Note 4 for turbo inlet location) Fuel injector inlet air 400°F Compressor temperature rise Not applicable (see Note 4) *TIO-540-AE2A, -AF1A, -AF1B m odels are approved for 1750°F E.G.T. model TIO-540-AJ1A approved for 1675° F E.G.T., model TIO-540-AK1A approved for 1685°F E.G.T. NOTE 2. Pressure Limits: Fuel pressure (p.s.i. above injector inlet air pressure) Minimum (p.s.i.) Maximum (p.s.i.) Idle (min p.s.i.) at inlet to fuel injector (-A models except -A1C, -A2C) 25 45 12 at inlet to fuel injector (-A1C, -A2C , -AJ1A models) 25 55 12 at inlet to fuel injector (-C, -E, -G, -H models) 18 45 12 at inlet to fuel injector (-F model) 30 65 12 at inlet to fuel injector (-J, -N model) 34 65 12 at inlet to fuel injector (-K model) 20 45 12 at inlet to fuel injector (-R model) 34 65 12 at inlet to fuel injector (-S model) 25 65 12 at inlet to fuel injector (-T model) 34 65 12 at inlet to fuel injector (-U model) 30 65 12 at inlet to fuel injector (-V, -AH models) 27 65 12 at inlet to fuel injector (-W model) 31 65 12 at inlet to fuel injector (-AB1AD, -AB1BD models) 20 65 12 at inlet to fuel injector (-AA1AD model) 20 65 12 at inlet to fuel injector (-AE2A model) 29 65 12 at inlet to fuel injector (-AF1A, -AF1B models) 24 55 12 at inlet to fuel injector (-AG1A, -AK1A models) 20 55 12 10 of 15 E14EA NOTE 2. (cont’d) Fuel Pressure (p.s.i. above ambient air pressure) Minimum (p.s.i.) Maximum (p.s.i.) Idle (min p.s.i.) at inlet to engine fuel pump (-A , -F, -R, -S, -U, -V, -W) -2 65 -- (-J, -N, -T, -AE2A, -AH1A, -AJ1A models) at inlet to engine fuel pump (-C, -E, -G, -H, -K -AF1A,) (-AF1B, -AG1A, -AK1A models) -2 55 -- Manifold Pressure (cumulative total with altitude adjustment) Maximum (in. Hg Abs) -A models (except -A1C, -A2C) 45 -A1C, -A2C models 46 -C, -E, -G models 39.5 -H models 40.7 -F, -J, -N models 49 -K models 34.5 -R models 44 -S models 36 -T models 45.2 -U models, AE2A 42.0 -W models 50.6 -AA1AD, -AB1AD, -AB1BD, -AF1A, -AF1B, -AH1A models 38 -AG1A, -AJ1A models 39 -AK1A model 32 Oil Pressure Minimum (p.s.i.) Maximum (p.s.i.) Normal (all models) 55 95 Idle (all models) 25 -- Starting and warm-up (all models) -- 115 Turbocharger exhaust back pressure 0.5 11 of 15 E14EA NOTE 3. The following accessory provisions are available: -A1A, -A1B, -A2A, -A2B, -A1C, -A2C, -C1A, -E1A, -G1A, -H1A, -J2B, -U2A, AK1A -AF1A -F2BD, -J2BD, -N2BD, -R2AD, -S1AD, -T2AD, -U2A, -V2AD, -W2A, -J2B, -AB1AD, -AA1AD, Rotating Facing Drive Pad Speed Ratio to Maximum Torque in. lb. Maximum Overhang Moment Accessory -W2A -AJ1A -AE2A -AF1B - AG1A, -AH1A -AB1BD -K1AD TIO LTIO Crankshaft Cont. Static in.-lb. Starter * * * * * * * CC C 16.556:1 --- 450 150 Alternator * -- -- -- * * * C CC 3.200:1 60 120 175 Alternator - -- * -- - - - C - 3.800:1 60 120 175 Vacuum pump ** * * * * * * CC C 1.300:1 70 450 25 Hydraulic pump ** * * * -- -- -- C CC 1.385:1 100 800 40 Hydraulic pump -- -- -- -- * -- * C CC 1.300:1 100 800 40 Tachometer * * -- * * * * C CC 0.500:1 7 50 5 Propeller governor*** * -- -- -- -- -- * C CC 0.895:1 125 1200 25 Propeller governor**** * * * * * -- -- C CC 0.947:1 125 2200 25 Propeller governor**** -- -- -- -- -- * -- C CC 1.3000:1 125 2200 25 Fuel pump - * - - * * * C CC 1.000:1 25 450 25 Fuel pump * -- * * -- -- -- CC C 1.000:1 25 450 25 Freon comp. -- -- - - -- -- ** C CC 1.300:1 180 2200 150 Freon comp. -- -- * * ** * -- C CC 1.462:1***** Limited by belt. “C” Clockwise, “CC” Counter Clockwise *Standard **Optional ***Narrow deck engines ****Wide deck engines *****With compressor pulley diameter of 6.00 inches. 12 of 15 E14EA NOTE 4. The Turbocharger meets the containment requirements of CAR 13.116 and does not require external protection. Measure exhaust gas temperature at inlet lo cation shown on Lycoming Drawing No. 63232(-A1A, -A2A, -A1B, -A2B, -A1C, -A2C), 63281 (-C1A, -E1A , -G1A, -H1A), 63393 (-F2BD), 63397 (-J2B/D), 63433 (-N2BD), 63416 (K1AD), 63444(-R2AD), 63517 (-T2AD), 63533 (-U2A), 63534 (-V2AD), 63537 (-W2A), 63545 (-AB1AD), 63582 (-AB1BD), 63546 (-AA1AD), 04D63570(-AE2A), 04063573 (-AF1A, -AF1B), 63583 (-AG1A), 63592 (-AH1A), O4D63594 (-AJ1A), 04D63601 (-AK1A). Performance data for these engines are presen ted on Lycoming Curves No. 12993 (-A1A, -A2A, -A1B, -A2B), 13195-B (-A1C, -A2C), 13107-B (-C1A ), 13172(-E1A), 13190-A (-G1A), 13208 (-H1A), 13201-A (-F2BD), 13215 (-J2BD, -N2BD), 13257-A (-K1AD), 13296 (-R2AD), and 13329(-S1AD), 13395 (-T2AD), 13399 (-U2A), 13415 (-V2AD), 13441 (-W2A), 13455 (-AB1AD, -AB1BD, -AA1AD), 13482(-AE2A), 13491(-AF1A -AF1B), 13509 (-AG1A), 13525 (-AH1A), 13538 (-AJ1A), 13556 (AK1A). Maximum turbocharger speed is now being governed by manifold pressure rather than temperature rise. Maximum manifold pressure versus altitude ar e presented on Lycoming Curve Numbers 13166-A (-A1A), -A2A, -A1B, -A2B), 13196-C (-A1C, -A2C), 13197-A (-C1A, -G1A), 13209 (-H1A), 13202-B (-F2BD), 13216-C (-J2B/D, -N2BD), 13297 (-R2AD), 13263 (-K1AD), 13330 (-S1AD), 13396 (-T2AD), 13416 (-V2AD), 13442 (-W2A), 13456 (-AB1AD, -AB1BD , -AA1AD), 13483 (-AE2A), 13492 (-AF1A,-AF1B), 13510 (-AG1A), 13537 (AH1A), 13540-A (-AJ1A), 13558 (AK1A). 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 ar e listed in the latest revision of Lycoming Service Instruction No. 1042. NOTE 7. These engines incorporate the following similarities or differences: TIO-540-A1A Basic model. Six cylinder, air-cooled , horizontally-opposed, direct drive, fuel injected, top exhaust, turbocharged engine incorpor ating internal piston cooling oil jets. Uses two-blade propeller. TIO-540-A1B Similar to -A1A but has density controller with faster temperature response. TIO-540-A2A Similar to -A1A except has prope ller flange bushings which accommodate either a two-blade or three-blade propeller. TIO-540-A2B Similar to -A1B except has prope ller flange bushings which accommodate either a two-blade or three-blade propeller. TIO-540-A1C Similar to -A1B except BSFC is in creased to .67/bhp-hr and the manifold pressure increased to 40.0 inches Hg. TIO-540-A2C Similar to -A2B except BSFC is in creased to .67/bhp-hr and the manifold pressure increased to 40.0 inches Hg. TIO-540-C1A Differs from -A1A with lower compre ssion ratio, different counterweights, and parallel valve cylinders. TIO-540-E1A Similar to -C1A except rating is incr eased, different turbocharger control setting and uses Bendix S6LN-1227 magneto instead of S6LN-1208 magneto. TIO-540-G1A Similar to -C1A except for higher compression ratio. TIO-540-H1A Similar to -E1A except rating is increased. TIO-540-F2BD Similar to -A2B except rated power is increased and incorporates the Bendix Dual Magneto. LTIO-540-F2BD Similar to -F2DB except that it has counter-clockwise (reversed) rotation. TIO-540-J2BD Similar to TIO-540-F2BD except rated power is increased and is equipped with an Air Research Model THO8460 turbocharger.