# TCDS E00006NY: Lycoming Engines - Type: Type certificate data sheet - Status: Current - Holder: Lycoming Engines - Revision: 10 - Revised: January 12, 2023 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 1,290, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ca/d8/cad8d38e64281927e3903c815d33429788a8079223b6fa665814b0a535d0d754 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID130116124920240105154016.0001 - Page: https://openairdocs.org/tcds/E00006NY ## Models (17) As the data sheet lists them. - AEIO-390-A3B6 - AEIO-390- A1A6 - IO-390-A1A6 - IO-390-A3A6 - IO-390-A3B6 - AEIO-390-A3A6 - AEIO-390-A1B6 - IO-390-A1B6 - IO-390-C1A6 - IO-390-C3A6 - IO-390-C1B6 - IO-390-C3B6 - HIO-390-A1A - IO-390-D1A6 - IO-390-D3A6 - IO-390-D1B6 - IO-390-D3B6 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TCDS NUMBER E00006NY Revision No. 10 LYCOMING ENGINES MODEL : IO-390-A1A6, -A3A6, -A1B6, A3B6, -C1A6, -C3A6, -C1B6, -C3B6, -D1A6, -D3A6, -D1B6, -D3B6 AEIO-390-A1A6, -A3A6, -A1B6, -A3B6 HIO-390-A1A January 12, 2023 TYPE CERTIFICATE DATA SHEET NO. E00006NY Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E00006NY) 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 Model: IO-390-A1A6, -A3A6, -A1B6, -A3B6 AEIO-390-A1A6, -A3A6, -A1B6, -A3B6 IO-390-C1A6, -C3A6, -C1B6, -C3B6 IO-390-D1A6, -D3A6, -D1B6, -D3B6 Type 4 HOA Direct Drive -- -- Rating Takeoff and Maximum continuous, hp., r.p.m. full throttle at: Sea level pressure altitude 210-2700-FT 215-2700-FT -- Fuel Grade aviation gasoline L ycoming Service Instruction 1070 -- -- Pressure NOTE 2 -- -- Injector and pump NOTE 6 -- -- Pump drive NOTE 3 -- -- Oil, Lubrication (Lubricants should conform to the specification as listed or to subsequent revisions thereto) Lycoming Service Instruction 1014 -- -- Temperature NOTE 1 -- -- Pressure NOTE 2 -- -- Sump capacity, qt. 8 7 -- Usable oil qt. (except AEIO series) Engine Position 6 NOTE 9 3.5 -- -- -- Usable oil qt. (AEIO series) 4 ─ ─ Ignition, dual Magnetos NOTE 6 -- -- Timing °BTC 20 -- 20* Spark plugs NOTE 4 -- -- Bore and stroke, in. 5.319 x 4.375 -- -- Displacement, cu. in. 389 -- -- Compression Ratio 8.9:1 -- -- Weight (dry) lb. NOTE 6 -- -- C.G. Location NOTE 6 -- -- Propeller shaft, SAE No. AS-127 Flan ge, Type 2 Modified -- -- NOTES 1,2,3,4,5,6,7,8,9,10 -- -- "--" indicates "same as preceding models" "─ " indicates "does not apply" *The base spark advance is 20°BTC. Timing is varied based on MAP and RPM. Page No. 1 2 3 4 5 6 Rev. No. 10 10 10 10 9 10 E00006NY Page 2 of 6 Model: HIO-390-A1A Type 4 HOA Direct Drive Rating Maximum continuous, hp., r.p.m. full throttle at: Sea level pressure altitude 210-2700-F.T. Takeoff (5 min) hp., r.p.m., in. Hg at: Sea level pressure altitude 210-2800-28.5 Fuel Grade aviation gasoline L ycoming Service Instruction 1070 Pressure NOTE 2 Injector and pump NOTE 6 Pump drive NOTE 3 Oil, Lubrication (Lubricants should conform to the specification as listed or to subsequent revisions thereto) Lycoming Service Instruction 1014 Temperature NOTE 1 Pressure NOTE 2 Sump capacity, qt. 8 Usable oil qt. Engine Position 6 NOTE 9 Ignition, dual Magnetos NOTE 6 Timing °BTC 20 Spark plugs NOTE 4 Bore and stroke, in. 5.319 x 4.375 Displacement, cu. in. 389 Compression Ratio 8.9:1 Weight (dry) lb. NOTE 6 C.G. Location NOTE 6 Propeller shaft, SAE No. AS-127 Flan ge, Type 2 Modified NOTES 1,2,3,4,6,7,8,9,10 "--" indicates "same as preceding models" "─ " indicates "does not apply" Certication basis: Regulations & Amendments FAR 33 effective February 1, 1965, as amended by 33-1 through 33-24 (except §33.8 replaced by compliance with CAR 13.16(c)) Model Date of Application Date Type Certificate No. E00006NY Issued/Revised IO 390-A1A6 April 11, 2008 March 30, 2009 IO-390-A3A6 Februar y 20, 2009 Au gust 27, 2009 IO-390-A1B6, -A3B6 Jul y 9, 2009 Januar y 21, 2010 AEIO-390-A1A6, -A3A6 April 6, 2010 April 5, 2012 AEIO-390-A1B6, -A3B6 April 6, 2010 April 5, 2012 Regulations & Amendments FAR 33 effective February 1, 1965, as amended by 33-1 through 33-34 (except §33.8 replaced by compliance with CAR 13.16(c)) Date of Application Date Type Certificate No. E00006NY Issued/Revisied IO-390-C1A6, -C3A6, -C1B6, -C3B6 March 29, 2016 Januar y 25, 2017 HIO-390-A1A July 2, 2014 November 22, 2017 IO-390-D1A6, -D3A6, -D1B6, -D3B6 February 11, 2019 March 25, 2020 Production basis: Production Certificate No. 3 E00006NY Page 3 of 6 NOTE 1. Maximum permissible temperatures: C ylinder Head (Well Type Thermocouple) Oil Inlet IO-390-A1A6, -A3A6 -A1B6, -A3B6 -C1A6, -C3A6, -C1B6, -C3B6 -D1A6, -D3A6 -D1B6, -D3B6 AEIO-390-A1A6, -A3A6 -A1B6, -A3B6 465°F 235°F HIO-390-A1A 465°F 245°F NOTE 2. Pressure limits: Fuel: Inlet to Fuel Pump Inlet to In jector Maximum Minimum Maximum Minimum Minimum Idle IO-390-A1A6, -A3A6 -A1B6, -A3B6 -C1A6, -C3A6, -C1B6, -C3B6 -D1A6, -D3A6 -D1B6, -D3B6 AEIO-390-A1A6, -A3A6 -A1B6, -A3B6 HIO-390-A1A 35 p.s.i. -2 p.s.i. 45 14  Oil: Maximu m Minimum Normal 95 p.s.i. 55 p.s.i. Idle  25 p.s.i. Starting and warm-up 115 p.s.i.  NOTE 3. The following accessory provisions are available: (AE) IO-390-Series Accessory -A1A6, -A3A6 -A1B6 -A3B6 -C1A6, -C3A6 -C1B6 -C3B6 -D1A6, -D3A6 -D1B6 -D3B6 Direction of Drive Ratio Maximum Torque (in. lb) Maximum Overhang R o t a t i o n  Continuous Static Moment Starter ■ ■ ■ ■ ■ ■ CCW 16.556:1 -- 450 150 Alternator ■ ■ ■ ■ ■ ■ CW 3.20:1 60 120 175 Alternator - - - ■ ■ ■ CW 3.70:1 60 120 175 Accessory Drive #1× * * * * ** ** CCW 1.300:1 70 450 25 Accessory Drive #2× - * - * - ** CW 1.300:1 100 800 40 Tachometer× * * ** ** ** ** CW 0.500:1 7 50 5 Fuel Pump * * * * * * Plunge r 0.500:1 - - 10 Propeller Governor * - * - * - CW 0.866:1 125 1200 40 Propeller Governor - * - * - * CW 0.895:1 125 1200 40 Compressor - - - ** - - CW 1.965:1 Limite d by belt "C" - Clockwise, "CC" - Counter-Clockwise, * Typical, ** Optional ■ These accessories are optional, see latest revision of SI 1154 for the approved alternates. × These drives are optional and accessory pads may be cast over. Rotation facing drive pad E00006NY Page 4 of 6 (cont’d) HIO-390 Accessory -A1A Direction of Drive Ratio Maximum Torque (in. lb) Maximum Overhang Rotation  Continuous Static Moment Starter ■ CCW 16.556:1 -- 450 150 Alternator ■ CW 3.20:1 60 120 175 Accessory Drive #1× * CCW 1.300:1 70 450 25 Accessory Drive #2× * CW 1.300:1 100 800 40 Tachometer× * CW 0.500:1 7 50 5 Fuel Pump * Plun ger 0.500:1 - - 10 "C" - Clockwise, "CC" - Counter-Clockwise, * Typical, ** Optional ■These accessories are optional, see latest revision of SI 1154 for the approved alternates. × These drives are optional and accessory pads may be cast over. Rotation facing drive pad NOTE 4. Spark plugs approved for use on this engine ar e listed in the latest revision of Lycoming Service Instruction No. 1042. NOTE 5. These engines incorporate provisions for absorb ing propeller thrust in both tractor and pusher installations. NOTE 6. The following tabulations show std. dry weight (less alternator and starter), C.G.'s, fuel injectors, fuel pumps and magnetos for this model. Center of Gravit y Model Weight * From Front Face of Prop Shaft Flange in. Off Crankshaft Center Line, in. Fuel Injector+ Fuel Pump Ignition, Dual IO-390-A1A6, -A3A6 307 14.13 .64 below .16 left LFR-NNSS5 Diaphragm Type Slick 4345 Slick 4370 IO-390-A1B6, -A3B6 307 14.13 .64 below .16 left LFR-NNSS5 Diaphragm Type Slick 4345 Slick 4370 IO-390-C1A6, -C3A6 298 14.44 .31 below .02 left LFR-NNSLH10, LFR-NNSM10 Diaphragm Type Slick 4345 Slick 4370 IO-390-C1B6, -C3B6 300 14.44 .31 below .02 left LFR-NNSLH10, LFR-NNSM10 Diaphragm Type Slick 4345 Slick 4370 IO-390-D1A6, -D3A6 288 14.93 .19 below .01 left LFR-NNSM10 Diaphragm Type (2) EIS ■ IO-390-D1B6, -D3B6 285 14.75 .14 below .05 left LFR-NNSM10 Diaphragm Type (2) EIS ■ AEIO-390- A1A6, -A3A6 312 14.13 .64 below .16 left LFR-NNSS5 Diaphragm Type Slick 4345 Slick 4370 AEIO-390- A1B6, -A3B6 312 14.13 .64 below .16 left LFR-NNSS5 Diaphragm Type Slick 4345 Slick 4370 HIO-390-A1A 296 15.1 .37 below .44 left LFR-NNLS10 Diaphragm Type Slick 4345 Slick 4370 * Less Starter and Alternator + For alternate fuel injectors, see latest revision of Lycoming SI 1532.  For alternate ignition systems, see latest revision of Lycoming SI 1443. ■ Electronic Ignition System (EIS) E00006NY Page 5 of 6 NOTE 7. The listed models incorporate the following additional similarities or differences: Model Characteristics IO-390-A1A6 Basic Model. Four cylinder air-cooled, horizontally opposed, direct drive, fuel injected, tuned induction engine having oil jets for internal piston cooling. Provisions for single action controllable pitch propeller. IO-390-A3A6 Same as the -A1A6 ex cept propeller flange bushings are reindexed. IO-390-A1B6 Same as the –A1A6 except pr opeller governor located on left front of crankcase. IO-390-A3B6 Same as the –A3A6 except pr opeller governor located on left front of crankcase. AEIO-390-A1A6 Same as the IO-390-A1A6 ex cept equipped with an inverted oil system kit for aerobatic flight. AEIO-390-A3A6 Same as the IO-390-A3A6 ex cept equipped with an inverted oil system kit for aerobatic flight. AEIO-390-A1B6 Same as the IO-390-A1B6 except equipped with an inverted oil system kit for aerobatic flight. AEIO-390-A3B6 Same as the IO-390-A3B6 except equipped with an inverted oil system kit for aerobatic flight. IO-390-C1A6 Similar to IO-390-A1A6 except lightweight oil sump, cold air induction housing, tuned intake pipes, and an LFR-NNSLH10 or LFR-NNSM10 fuel injector. IO-390-C3A6 Same as the -C1A6 ex cept propeller flange bushings are reindexed. IO-390-C1B6 Same as the –C1A6 except pr opeller governor located on left front of crankcase. IO-390-C3B6 Same as the –C3A6 except pr opeller governor located on left front of crankcase. IO-390-D1A6 Similar to IO-390-C1A6 except with a conical engine mount interface, magnesium oil sump, magnesium induction housing, a crankshaft with weight reduction provisions, and two variable timing EIS units. IO-390-D3A6 Same as the -D1A6 ex cept propeller flange bushings are reindexed. IO-390-D1B6 Same as the –D1A6 except pr opeller governor located on left front of crankcase and magnesium accessory housing. IO-390-D3B6 Same as the –D3A6 except pr opeller governor located on left front of crankcase and magnesium accessory housing. HIO-390-A1A Similar to IO-390-A3A6 except without counterweights, rear inlet injector tuned sump, LFR-NNLS10 injector, Type 2 dynafocal mounts, and no propeller governor provisions. E00006NY Page 6 of 6 NOTE 8. Starters and alternators approved for use on this engine are listed in the latest revision of Lycoming Service Instruction No. 1154. NOTE 9. Maximum flight attitudes for the IO-390-A Series and HIO-390-A1A are 30° nose up and 30° nose down. Maximum flight attitudes for the AEIO-390-A Series are 30° nose up and 8° nose down, except when the 3½ inch extended oil strainer sump fitting is installed, the maximum nose down angle is 20. For the IO-390-C and -D Series, the maximum flight attitudes are 30° nose up and 12° nose down. NOTE 10. Engine Power variation of -2% to +5% is applicable to IO-390-A, C, and -D Series, AEIO-390-A Series, and the HIO-390-A1A engine models. ......END..... ``` ## ADs (5, in force first) - [AD 2026-04-11](https://openairdocs.org/ad/2026-04-11): Engine (Reciprocating) · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 605 more. Effective Apr 8, 2026 - [AD 2012-19-01](https://openairdocs.org/ad/2012-19-01): Crankshafts · Lycoming Engines AEIO-360-A1A, AEIO-360-A1B, AEIO-360-A1B6 and 321 more. Effective Oct 24, 2012 - [AD 2012-03-06](https://openairdocs.org/ad/2012-03-06): Fuel servo diaphragm · Continental Motors 6-260-A, 6-285-A, 6-285-B and 482 more. Effective Feb 24, 2012 - [AD 2009-02-03](https://openairdocs.org/ad/2009-02-03): Fuel injection servos · Lycoming Engines AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 261 more. Effective Feb 9, 2009 - [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 ## Registered aircraft by registry model (OpenAirDocs) - [Lycoming IO-390-C3B6](https://openairdocs.org/engine/lycoming-io-390-c3b6): 793 aircraft (registry code 42710) - [Lycoming IO-390 series](https://openairdocs.org/engine/lycoming-io-390-series): 312 aircraft (registry code 41678) - [Lycoming IO-390-D3B6](https://openairdocs.org/engine/lycoming-io-390-d3b6): 73 aircraft (registry code 42714) - [Lycoming IO-390-A1B6](https://openairdocs.org/engine/lycoming-io-390-a1b6): 47 aircraft (registry code 42407) - [Lycoming AEIO-390-A1B6](https://openairdocs.org/engine/lycoming-aeio-390-a1b6): 35 aircraft (registry code 42409) - [Lycoming IO-390-A1A6](https://openairdocs.org/engine/lycoming-io-390-a1a6): 20 aircraft (registry code 41602) - [Aerosport IO-390](https://openairdocs.org/engine/aerosport-io-390-series): 9 aircraft (registry code 01304) - [Lycoming IO-390-A3A6](https://openairdocs.org/engine/lycoming-io-390-a3a6): 1 aircraft (registry code 42421) ## STCs approved under this data sheet (6) - [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 SE02352CH](https://openairdocs.org/stc/SE02352CH): Installation of Challenger cleanable oil filter assembly. Challenger Aviation Products Inc. - [STC SE03232CH](https://openairdocs.org/stc/SE03232CH): Installation of Engine Preheat Kit p/n TA2925-1 for 115 volt application. Hartzell Propeller Inc. - [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. --- 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.