TCDS E-295

Page No. 01 02 03 04 05 06 07 08 Rev. No. 19 19 19 18 18 18 18 18 Reformatted 9/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-295 Revision 19 Lycoming Engines O-540-A1A, -A1A5, -A1B5, -A1C5, -A1D, -A1D5, -A2B, -A3D5, -A4A5, -A4B5, -A4C5, -A4D5, -A4E5, O-540-B1A5, -B1B5, -B1D5, -B2A5, -B2B5, -B2C5, -B4A5, -B4A5, -B4B5, O-540-D1A5, O-540-E4A5, -E4B5, -E4C5, O-540-F1A5, -F1B5, O-540-G1A5, -G2A5, O-540-H1A5, -H2A5, -H1A5D, -H2A5D, -H1B5D, -H2B5D, O-540-J1A5D, -J2A5D, -J1B5D, -J2B5D, -J3A5D, -J3A5, -J1C5D -J2C5D, -J1D5D, -J2D5D, -J3C5D, -L3C5D April 30, 2013 TYPE CERTIFICATE DATA SHEET NO. E-295 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. 295) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificate 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 Willia msport Div., AVCO Corporation transferred TC E-295 to Lycoming Engines, An Operating Division of AVCO Corporation on December 17, 2003 E-295 2 Model Lycoming O-540 -A1A, -A1A5, -A1B5, -A1C5, -A1D, -A1D5, -A2B, -A3D5, -A4A5, -A4B5, -A4C5, -A4D5, -D1A5, -A4E5 -B1A5, -B1B5, -B1D5, -B2A5, -B2B5, -B2C5, -B4A5, -B4B5 -E4A5, -E4B5, -E4C5, -G1A5, -G2A5, -H1A5, -H2A5, -H1A5D, - H2A5D, -H1B5D, - H2B5D -F1A5, -F1B5 Type 6HOA Direct Drive - - - - - - Rating Maximum continuous, hp., r.p.m, in. Hg., at: Critical pressure altitude (ft.) ⎯ ⎯ ⎯ 235-2800-25.0,4000 Sea level pressure altitude 250-2575-F.T.-S.L . 235-2575-F.T.-S.L. 260-2700-F.T.-S.L. 235-2800-26.0-S.L. Takeoff (5 min.), hp., r.p.m., in. Hg., at: Critical pressure altitude (ft.) ⎯ ⎯ ⎯ 260-2800-27.5-800 Sea level pressure altitude 250-2575-F.T.-S.L . 235-2575-F.T.-S.L. 260-2700-F.T.-S.L. 260-2800-28.0-S.L. Fuel (Minimum grade aviation gasoline) See NOTE 8 - - - - - - Lubricating oil (lubricants which conform to the specifications as listed or to subsequent revision thereto.) See Latest edition of Lycoming Service Instruction 1014 - - - - - - Bore and stroke. in. 5.125 X 4.375 - - - - - - Displacement, cu. in. 541.5 - - - - - - Compression ratio See NOTE 8 - - - - - - Weight (dry) See NOTE 5 - - - - - - C.G. location (dry) See NOTE 5 - - - - - - From front face of prop shaft flange, in 17.9 - - - - - - Off propeller shaft C.L., in. 1.21 below 0.15 left - - - - - - Propeller shaft-AS-127 Type 2 flange modified - - - - - - Carburetion** LVC-5-5PA - - - - - - Ignition, dual See NOTE 8 - - - - - - Timing, °BTC 25 - - - - - - Spark plugs See NOTE 7 - - - - - - Oil sump capacity, qt. 12 - - - - - - Crankshaft dampers See NOTE 5 & 6 - - - - - - Minimum safe oil quantity qts. 20°nose up or down attitude 2-3/4 - - - - - - 30°nose up attitude 4 - - - - - - NOTES - As applicable 1 through 8, 10, 11 - - - - 1 through 11 "- -" indicates "same as preceding model" "⎯" indicates "does not apply" ** See latest revision of Lycoming Service Instruction 1523 for alternate carburetors. 3 E-295 Model Lycoming O-540 -J1A5D, -J2A5D, -J1B5D, -J2B5D, -J3A5D -J1C5D, -J2C5D, -J3C5D, -J1D5D, -J2D5D -L3C5D (See NOTE 12) -J3A5 Type 6HOA Direct Drive - - - - - - Rating Maximum continuous, hp., r.p.m, in. Hg., at: Critical pressure altitude (ft.) ⎯ ⎯ ⎯ ⎯ Sea level pressure altitude 235-2400-F.T.-S.L . 235-2400-F.T.-S.L. 235-2400-F.T.-S.L. 235-2400-F.T.-S.L. Takeoff (5 min.), hp., r.p.m., in. Hg., at: Critical pressure altitude (ft.) ⎯ - - - - - - Sea level pressure altitude 235-2400-F.T. -S.L. 235-2400-F.T.-S.L. 235-2400-F.T.-S.L. - - Fuel (Minimum grade aviation gasoline) See NOTE 8 - - - - - - Lubricating oil (lubricants which conform to the specifications as listed or to subsequent revision thereto.) See Latest edition of Lycoming Service Instruction 1014 - - - - - - Bore and stroke. in. 5.125 X 4.375 - - - - - - Displacement, cu. in. 541.5 - - - - - - Compression ratio See NOTE 8 - - - - - - Weight (dry) See NOTE 5 - - - - - - C.G. location (dry) From front face of prop shaft flange, in 17.75 17.94 18.10 17.99 Off propeller shaft C.L., in. 0.75 below 0.19 left 0.69 below 0.19 left 0.59 below 0.34 left 1.21 below 0.08 left Propeller shaft-AS-127 Type 2 flange modified - - - - - - Carburetion ** LVC-5-5PA LHC-6-6BPA LHC-6-6BA LVC-5-5PA Ignition dual See NOTE 8 - - - - - - Timing, °BTC 23 - - - - - - Spark plugs See NOTE 7 - - - - - - Oil sump capacity, qts. 12 - - - - - - Crankshaft dampers See NOTE 5 & 6 - - - - - - Minimum safe oil quantity qts. - - - - - - - - 20°nose up or down attitude 2-3/4 - - - - - - 30°nose up attitude 2 - - - - - - NOTES - As applicable 1 through 8, 10, 11 - - 1 through 8, 10, 11, 12, 13 1 through 8, 11 "- -" indicates "same as preceding model" "⎯" indicates "does not apply" ** See latest revision of Lycoming Service Instruction 1523 for alternate carburetors. E-295 4 Certification basis: Regulations and Amendments Model Date of Application Date Type Certificate No. E-295 Issued/Revised CAR 13 Effective June 15, 1956 O- 540-A1A July 2, 1957 October 31, 1957 As Amended By 13-1 & 13-2 O-540-A1A5 June 3, 1958 June 18, 1958 O-540-A2B July 24, 1958 July 24, 1958 O-540-D1A5 October 21, 1958 August 12, 1959 O-540-A1B5 January 21, 1959 February 10, 1959 O-540-A1C5 March 16, 1959 April 2, 1959 O-540-F1A5, -F1B5 April 3, 1959 August 12, 1959 O-540-A1D, -A1D5 January 21, 1960 March 17, 1960 13-3 O-540-A3D5 May 17, 1960 June 22, 1960 O-540-B1A5, -B2A5 November 30, 1960 May 3, 1961 O-540-B1B5 April 17, 1961 May 3, 1961 O-540-B2B5 December 8, 1961 December 26, 1961 13-4 O-540-A4A5, -A4B5, - A4C5, -A4D5, -B4A5, -B4B5 October 3, 1963 October 9, 1963 O-540-E4A5, -E4B5 April 1, 1964 May 4, 1964 O-540-E4C5 March 3, 1966 March 23, 1966 O-540-B1D5, -B2C5 November 23, 1966 December 2, 1966 O-540-G2A5 March 31, 1967 April 4, 1967 O-540-G1A5 October 6, 1967 October 9, 1967 O-540-H1A5, -H2A5 January 16, 1970 January 22, 1970 O-540-H1B5D, -H2B5D July 30, 1971 August 4, 1971 O-540-H1A5D, -H2A5D July 27, 1971 October 21, 1971 O-540-J1B5D, -J2B5D January 20, 1975 August 15, 1975 O-540-J1C5D, -J2C5D August 25, 1976 October 4, 1976 -J1D5D, -J2D5D O-540-J3C5D February 4, 1977 February 15, 1977 O-540-J3A5D November 23, 1977 November 30, 1977 O-540-L3C5D July 21, 1977 June 19, 1978 O-540-J3A5 March 17, 1987 March 31, 1987 O-540-A4E5 March 14, 2012 March 22, 2012 Production basis: Production Certificate No. 3 NOTE 1. Maximum permissible temperatures are as follows: Cylinder Head (well type) Cylinder Base Oil Inlet 500°F 325°F 245°F NOTE 2. Pressure limits - p.s.i. Minimum Maximum 0.5 30.0 (0-540-L3C5D: See NOTE No. 13) Fuel 0.5 8.0 Oil (Normal operation) 55.0 95.0 (Idle) 25.0 ⎯ (Starting and warm-up) ⎯ 115.0 5 E-295 NOTE 3. The following accessory provisions are incorporated: -A1A, -A1A5, -A1B5, -A1C5, -A1D, -A1D5, -A4A5, -A4B5, -A4C5, -B1A5 -A4D5 -A2B -B1B5 -A4E5 -B2A5 -B1D5, -E4A5, -B2B5 -B4A5 -E4B5 -B2C5 -B4B5, -H1A5 -F1A5 Accessory -E4C5 A3D5 -G2A5 -G 1A5 -D1A5 -H2A5 -F1B5 -L3C5D Starter * * * * * * ⎯ * Starter ⎯ ⎯ ⎯ ⎯ ⎯ ⎯ * ⎯ Generator * * * * * ⎯ * ⎯ Generator ** ** ** ** ** ⎯ ⎯ ⎯ Alternator ** ** ** ** ⎯ * ⎯ * Alternator ** ** ** ** ** ** ** ** Vacuum Pump * * * * * * * * Hydraulic Pump * * * * * * * ⎯ Hydraulic Pump ⎯ ⎯ ⎯ ⎯ ⎯ ⎯ ⎯ * Tachometer * * * * * * * * Propeller Governor * * ⎯ * * * ⎯ ⎯ Propeller Governor ⎯ ⎯ ⎯ ⎯ ⎯ ⎯ ⎯ * Fuel Pump ** ** ** ** ** ** ** ⎯ Fuel Pump (plunger) ** * ** ** ** ** ** * -J1A5D -J2A5D -J3A5D -J1B5D All Models -H1A5D -J2B5D Rotation Speed Maximum Max. -H2A5D -J3C5D Facing Ratio Torque Overhang -H1B5D -J2D5D -J1D5D Drive to (in. -lb.) Moment Accessory -H2B5D -J2C5D -J1C5D -J3A5 Pa d Crankshaft Cont. Static (in. -lb.) Starter * * * * CC 16.556:1 ⎯ 450 150 Starter ⎯ ⎯ ⎯ ⎯ CC 13.556:1 ⎯ 450 150 Generator ⎯ ⎯ ⎯ ⎯ C 1.010:1 60 120 175 Generator ⎯ ⎯ ⎯ ⎯ C 2.500:1 60 120 175 Alternator * * * * C 3.250:1 60 120 175 Alternator ** ** ⎯ ⎯ C 3.630:1 60 120 175 Vacuum Pump * * * ** CC 1.300:1 70 450 25 Hydraulic Pump ⎯ ⎯ ⎯ ** C 1.385:1 100 800 40 Hydraulic Pump * * * ⎯ C 1.300:1 100 800 40 Tachometer * * * * C 1.500:1 7 50 5 Propeller Governor ⎯ ⎯ ⎯ ⎯ C 0.895:1 125 1200 25 Propeller Governor * ⎯ * ** C 0.947:1 125 1200 25 Fuel Pump ** ⎯ ⎯ ⎯ CC 1.000:1 25 ⎯ 25 Fuel Pump (plunger) ** ** ** ** ⎯ 0.500:1 ⎯ ⎯ 10 "C" - Clockwise "CC" - Counter clockwise * - Standard ** - Optional NOTE 4. These engines incorporate provisions for absorbing pr opeller thrust in both tractor and pusher type installations. E-295 6 NOTE 5. These models incorporate a dditional characteristics as follows: O-540-Models Wt. dry, lb. Characteristics -A1A 374 Basic model, direct drive, six cyli nder, horizontally opposed, air cooled engine with one each S6LN-20 and -21 Magnetos and two 6th order dampers. -A1A5 374 Same as -A1A except has one fifth and one sixth order dampers. -A1B5 375 Same as -A1A5 except has propeller governor pad with short studs to accommodate AN type governor. -A1C5 375 Same as -A1A5 except has two S6LN-21 impulse coupling magnetos. -A1D 375 Similar to -A1B5 except has one each S6LN-200 and S6LN-204 magnetos and two sixth order crankshaft torsional dampers. -A1D5 375 Similar to -A1D except has one fi fth and one sixth order crankshaft torsional dampers. -A2B 374 Same as -A1B5 except for crankshaft damper arrangement and propeller flange has propeller locating bushings displaced 60° clockwise, viewed facing propeller. -A3D5 373 Similar to -A1D5 except has provisi ons for Goodrich propeller deicing equipment. -A4A5 374 Similar to -A1A5 except has heavier fi fth and sixth order crankshaft counterweights. -A4B5 375 Similar to -A1B5 except has heavier fi fth and sixth order crankshaft counterweights. -A4C5 375 Similar to -A1C5 except has heavier fi fth and sixth order crankshaft counterweights. -A4D5 375 Similar to -A1D5 except has heavier fi fth and sixth order crankshaft counterweights. -A4E5 375 Same as –A4B5 except has side mounted oil gage and fill tube. -B1A5 366 Same as -A1D5 except has lower compression ratio and performance. -B1B5 366 Field conversion of -A1A5, -A 1B5, or -A1C5 to lower compression ratio. -B1D5 367 Same as -B1A5 except for inco rporation of Bendix 1200 series magnetos. -B2A5 366 Similar to -B1A5 except does not ha ve provisions for controllable pitch propeller. -B2B5 366 Same as -B2A5 except has S6LN-20 and S6LN-21 magnetos. -B2C5 368 Same as -B2B5 except for incor poration of Bendix 1200 series magnetos and does not include generator as part of the engine. -B4A5 366 Similar to -B1A5 except has heavier fi fth and sixth order crankshaft counterweights. -B4B5 366 Similar to -B1B5 except has heavier fi fth and sixth order crankshaft counterweights. -D1A5 369 Same as -A1A5 except has increased strength crankcase. -F4A5 368 Similar to -A4D5 except has hybr id camshaft permitting higher 260 hp. @ 2700 r.p.m. -E4B5 369 Similar to -A4D5 except for left ma gneto S6LN-21 and minor difference in weight and length. -E4C5 370 Same as model -E4B5 excep t has S6LN-1227 and S6LN-1209 magnetos. -F1A5 367 Same as -A1A5 except rated for helic opter application and incorporates prototype bed mounting. -F1B5 369 Same as -D1A5 except rated for helic opter application and incorporates provisions for either bed or dynafocal type mounting. -G1A5 386 Similar to -E4C5 except incorporates heavier crankshaft, different crankcase and -A1D5 counterweights. -G2A5 386 Similar to -G1A5 except does not pr ovide for use of constant speed propeller. -H1A5 385 Similar to -G1A5 except has different magnetos and incorporates piston cooling oil jets. -H2A5 385 Similar to -G2A5 except has different magnetos and incorporates piston cooling oil jets. -H1A5D 381 Similar to -H 1A5 except incorporates dual magneto (impulse coupling). -H2A5D 381 Similar to -H1A5D except does not have provision for controllable propeller. -H1B5D 381 Similar to -H1A5 except incorporates dual magneto (retard). -H2B5D 381 Similar to -H1B5D except does not have provision for controllable propeller. -J1A5D 356 Similar to -A1A5 except incorporates dual magneto (impulse coupling), less weight and rated at 235 h.p. @ 2400 r.p.m. -J2A5D 356 Similar to -J1A 5D except does not have provision for controllable propeller. -J1B5D 356 Similar to -A1A5 ex cept incorporates dual magneto (retard), less weight and rated at 235 h.p. @ 2400 r.p.m. -J2B5D 356 Similar to -J1B5D except does not have provision for controllable propeller. -J1C5D 356 Same as -J1A5D except has horizontal carburetor and induction housing. -J2C5D 356 Same as -J1C5D except ha s no provision for controllable propeller. -J1D5D 356 Same as -J1C5D but with D6LN-3230 retard breaker dual magneto. -J2D5D 356 Same as -J1D5D except does not have provision for controllable propeller. 7 E-295 -J3C5D 357 Same as -J1C5D except has h eavier counterweights for use with McCauley controllable propeller. Note 5. These models incorporate additional characteristics as follows: cont. -J3A5D 357 Same as -J1A5D except has h eavier counterweights (same as O-540-J3C5D). -L3C5D 367 Same as -J3C5D except for features to make engine suitable for turbocharging. -J3A5 364 Same as -J3A5D excep t equipped with Slick magnetos. NOTE 6. These engines incorporate cra nkshafts with two sixth order dampers unless a "5" is part of the model designation, i.e., -A1A5. Engines so designated have one fifth order damper and one sixth order damper instead of two sixth order dampers. NOTE 7. Spark plugs approved for use on these engines are liste d in the latest revision of Lycoming Service Instruction No. 1042. NOTE 8. Fuel grade, compression and ignition: O-540-Models Fuel - Aviation Gasoline Compression Ratio Ignition, Dual TCM * -A1A 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -A1A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -A1B5 100 or 100 LL 8.50:1 S6LN-21, S6LN-21 -A1C5 100 or 100 LL 8.50:1 S6LN-21, S6LN-21 -A1D 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -A1D5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -A2B 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -A3D5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -A4A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -A4B5 100 or 100 LL 8.50:1 S6LN-21, S6LN-21 -A4C5 100 or 100 LL 8.50:1 S6LN-21, S6LN-21 -A4D5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -A4E5 100 or 100 LL 8.50:1 S6LN-21, S6LN-21 -B1A5 100 or 100 LL 7.20:1 S6LN-204, S6LN-200 -B1B5 100 or 100 LL 7.20:1 S6LN-20, S6LN-21 -B1D5 100 or 100 LL 7.20:1 S6LN-1209, S6LN-1208 -B2A5 100 or 100 LL 7.20:1 S6LN-204, S6LN-200 -B2B5 100 or 100 LL 7.20:1 S6LN-20, S6LN-21 -B2C5 100 or 100 LL 7.20:1 S6LN-1209, S6LN-1227 -B4A5 100 or 100 LL 7.20:1 S6LN-204, S6LN-200 -B4B5 100 or 100 LL 7.20:1 S6LN-20, S6LN-21 -D1A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -E4A5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -E4B5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -E4C5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -F1A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -F1B5 100 or 100 LL 8.50:1 S6LN-204, S6LN-200 -G1A5 100 or 100 LL 8.50:1 S6LN-1227, S6LN-1209 -G2A5 100 or 100 LL 8.50:1 S6LN-1227, S6LN-1209 -H1A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 -H2A5 100 or 100 LL 8.50:1 S6LN-20, S6LN-21 * For Alternate magnetos see latest copy of Lycoming Service Instruction 1443, TCM formally Bendix All models equipped with one impulse coupling magneto may use two impulse coupling magnetos as optional equipment. E-295 8 Note 8. Cont. O-540-Models Fuel - Aviation Gasoline Compression Ratio Ignition, Dual TCM * -H1A5D 100 or 100 LL 8.50:1 D6LN-3031 -H2A5D 100 or 100 LL 8.50:1 D6LN-3031 -H1B5D 100 or 100 LL 8.50:1 D6LN-3230 -H2B5D 100 or 100 LL 8.50:1 D6LN-3230 -J1A5D 100 or 100 LL 8.50:1 D6LN-3031 -J2A5D 100 or 100 LL 8.50:1 D6LN-3031 -J1B5D 100 or 100 LL 8.50:1 D6LN-3230 -J2B5D 100 or 100 LL 8.50:1 D6LN-3230 -J1C5D 100 or 100 LL 8.50:1 D6LN-3031 -J2C5D 100 or 100 LL 8.50:1 D6LN-3031 -J1D5D 100 or 100 LL 8.50:1 D6LN-3230 -J2D5D 100 or 100 LL 8.50:1 D6LN-3230 -J3A5 100 or 100LL 8.50:1 Slick 6350 / 6351 -J3C5D 100 or 100 LL 8.50:1 D6LN-3031 -J3A5D 100 or 100LL 8.50:1 D6LN-3031 -L3C5D 100 or 100 LL 8.50:1 D6LN-3031 * For Alternate magnetos see latest copy of Textron Lycoming Service Instruction 1443, TCM formerly Bendix, D6LN-2XXX series magnetos have been superseded by D6LN-3XXX series magnetos All models equipped with one impulse coupling magneto may use two impulse coupling magnetos as optional equipment. NOTE 9. Engine models O-540-F1A5 and -F1B5 are approved for helicopter application and operation in a horizontal installation. NOTE 10. Models O-540-A4A5, -A4B5, -A4C 5, -A4D5, -A4E5, -B4A5, -B4B5, -E4B5, -E4A5, and -E4C5 are equipped with fifth and sixth order crankshaft counterweights which are heavier than the usual fifth and sixth order counterweights employed in other O-540 engine models. NOTE 11. Starters, generators, and altern ators approved for use on these engines are listed in the latest revision of Lycoming Service Instruction No. 1154. NOTE 12. When equipped in accordance with Cessna Dwg. 2250065, this engine is certified for operation at a maximum manifold pressure of 31.0 in. Hg at 2400 r.p.m. NOTE 13. When complying with Lycoming Service Instruction No. 1398, the minimum permissible fuel pressure increase from 0.5 psi to 3 psi. Therefore, revised fuel pressure gage marking indicating a minimum red line of 3 psi is required. .....END.....