# TCDS E00056SE: Continental Aerospace Technologies, Inc. - Type: Type certificate data sheet - Status: Current - Holder: Continental Aerospace Technologies, Inc. - Revision: 4 - Revised: February 12, 2020 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 3, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/be/e9/bee9ae6b3da8302ff7aae47835b9b5af2da985393f01c42563191a1bf01e18a0 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F3095AE90E411EE48625851800704A83.0001 - Page: https://openairdocs.org/tcds/E00056SE ## Models (5) As the data sheet lists them. - IO-370-CL - IO-370-DA3A - IO-370-CM - IO-370-C1F - IO-370-D3A ## 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 Page No. 1 2 3 4 5 6 7 Rev No. 4 4 4 3 3 3 4 E00056SE Revision 4 CONTINENTAL AEROSPACE TECHNOLOGIES, INC. IO-370-CL, -CM, -C1F, -DA3A, -D3A February 12, 2020 TYPE CERTIFICATE DATA SHEET NO. E00056SE Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E00056SE) 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 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 Continental Aerospace Technologies, Inc. 2039 South Broad Street Mobile, AL 36615 Type Certificate Record Holder Continental Motors, Inc. Company name change January 1, 2020 (Continental Aerospace Technologies, Inc.) Model IO-370-CL IO-370-CM IO-370-C1F Type - 4HOA Direct Drive Naturally Aspirated - - - - Rating (see NOTE 1) Standard Atmosphere at Sea Level Pressure Altitude: Max Continuous HP 195 - - 190 Max Continuous RPM 2700 - - - - Fuel (Min. Grade Aviation Gasoline) 100 or 100LL - - - - Per ASTM D-910 Lubricating Oil Compliant with - - - - specifications SAE- J1899 or J1966 by Continental Specification MHS-24 Bore and Stroke – In. (mm) 5.125 (130.1) x 4.5 (114.3) - - - - Displacement, In3 (cm3) 371 (6079) - - - - Compression Ratio 9.6:1 - - - - Weight (Dry), lbs (kg) 295 (133.8) - - 289.5 (131.3) Oil Sump Capacity, qt (L) 8.0 (6.5) - - - - Usable - 30° Nose Up 4.0 (3.79) - - -- Usable - 30° Nose Down 5.0 (4.73) - - -- E 0 0 0 5 6 S E Pa ge 2 of 7 IO-370-CL IO-370-CM IO-370-C1F Physical Dimensions Length, in (mm) 29.90 (759.5) - - 29.90 (759.5) Width, in (mm) 33.41 (848.6) - - - - Height, in (mm) 22.39 (568.7) - - 25.28 (642.1) Center of Gravity, in (mm) Aft of propeller flange 14.0 (355.6) - - 14.1 (360.4) Beside crank centerline 0.0 (0.0) - - - - Below crankshaft centerline 0.75 (19) - - 0.407 (10.3) Propeller Shaft AS127D Flange, Type 2 modified - - - - Fuel Injection Servo-style fuel injection system, AC Type fuel pump - - - - Control System Manual Control -- -- Ignition, Dual Magnetos S4LSC-21, S4LSC-204 - - - - Timing R-20°, L-20° - - - - Spark Plugs Tempest UREM38E - - - - Applicable Notes NOTE 1 through NOTE 7, - - - - NOTE 9, NOTE 15, NOTE 21, NOTE 22 and NOTE 23 E 0 0 0 5 6 S E Pa ge 3 of 7 Model IO-370-DA3A IO-370-D3A Type - 4HOA Direct Drive Naturally Aspirated - - Rating (see NOTE 1) Standard Atmosphere at Sea Level Pressure Altitude: Max Continuous HP 180 185 Max Continuous RPM 2700 - - Fuel (Min. Grade Aviation Gasoline) 100 or 100LL - - Per ASTM D-910 Lubricating Oil Compliant with - - specifications SAE- J1899 or J1966 by Continental Specification MHS-24 Bore and Stroke – In. (mm) 5.125 (130.1) x 4.5 (114.3) - - Displacement, In3 (cm3) 371 (6079) - - Compression Ratio 8.1:1 - - Weight (Dry), lbs (kg) 292.5 (132.7) - - Oil Sump Capacity, qt (L) 8.0 (6.5) - - Usable - 30° Nose Up 4.0 (3.79) - - Usable - 30° Nose Down 5.0 (4.73) - - Physical Dimensions Length, in (mm) 33.02 (838.7) - - Width, in (mm) 33.41 (848.6) - - Height, in (mm) 24.43 (620.5) - - Center of Gravity, in (mm) Aft of propeller flange 14.45 (367.0) - - Beside crank centerline, 0.18 (4.6) - - toward 2-4 side Above crankshaft centerline 0.79 (20.1) - - Propeller Shaft AS127D Flange, Type 2 modified - - Fuel Injection Servo-style fuel injection system, AC Type fuel pump - - Control System Manual Control -- Ignition, Dual Magnetos S4LSC-21 (2) - - Timing R-22°, L-22° R-25°, L-25° Spark Plugs Tempest UREM38E - - Applicable Notes NOTE 1 through NOTE 7, - - - - NOTE 9, NOTE 15, NOTE 21, NOTE 22 and NOTE 23 E 0 0 0 5 6 S E Pa ge 4 of 7 Certification Basis: IO-370-CL – 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 except replace §33.8 with compliance to CAR13.16(c). IO-370-CM – 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 except replace §33.8 with compliance to CAR13.16(c). IO-370-C1F – 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 except replace §33.8 with compliance to CAR13.16(c). IO-370-DA3A – 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33- 34 except replace §33.8 with compliance to CAR13.16(c). IO-370-D3A – 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 except replace §33.8 with compliance to CAR13.16(c). TYPE CERTIFICATE NUMBER E00056SE MODEL APPLICATION ISSUED/AMENDED DELETED IO-370-CL February 17, 2018 ISSUED June 18, 2018 IO-370-CM February 17, 2018 ISSUED June 18, 2018 IO-370-C1F March 13, 2018 AMENDED May 29, 2019 IO-370-DA3A September 2018 AMENDED June 12, 2019 IO-370-D3A September 2018 AMENDED June 12, 2019 PRODUCTION BASIS FAA Production Certificate 508 E 0 0 0 5 6 S E Pa ge 5 of 7 NOTES NOTE 1. ENGINE RATINGS Engine ratings are based on calibrated test stand performance under the following conditions: 1) US Standard Atmosphere. Horsepower may vary up to +/- 2.5% 2) Sea level static, standard day conditions (29.92 inHg, 59°F, no water vapor) for sea level ratings 3) No external power extraction (all accessory drives unloaded) 4) Ideal inlet and exhaust (no losses) 5) 0% Relative Humidity (no water vapor) 6) Manifold temperature maintained at 56 °F above inlet temperature (115°F at sea level, standard day) NOTE 2. TEMPERATURE LIMITS Maximum Temperature Limits Maximum cylinder head temperature (CHT) 500°F (260°C) (well type thermocouple) Maximum Oil Temperature 245°F (118.3°C) Minimum Temperature Limits Minimum CHT for Takeoff 150°F (65.6°C) Minimum Oil Temperature for Takeoff/Maximum Power 245°F (118.3°C) Minimum Oil Temperature for Starting 20°F (-7°C) NOTE 3. PRESSURE LIMITS Fuel Pump Pressure Limits Minimum Pressure -2 psig (-0.13 bar) Maximum Pressure 35 psig (2.41 bar) Oil Pressure Limits Maximum Gauge Pressure, Cold Engine 115 psig (7.9 bar) Normal Gauge Pressure 55 to 95 psig (3.79 to 6.6 bar) Minimum gauge pressure at idle 25 psig (1.7 bar) at or below 200°F NOTE 4. ACCESSORY DRIVE PROVISIONS Original Accessory Direction of Rotation* Speed Ratio to Crankshaft Maximum Continuous Torque in-lb (Nm) Maximum Static Torque in-lb (Nm) Maximum Overhang Moment in-lb (Nm) Drive Propeller Governor Tachometer Alternator Starter Vacuum Pump CW CW CW CCW CCW 0.895:1 0.5:1 ** 16.56:1 1.30:1 125 (14.1) 7 (.79) 60 (6.7) -- 100(11.3) 1200 (135.5) 50 (5.6) 120 (13.5) 450 (50.8) 800(90.3) 40 (4.5) 5 (.56) 40 (4.5) 25 (2.8) 25 (2.8) AND 20010 AS54 Type 1 Belt ISO 9982 N/A AND 20000 * CCW = counterclockwise, CW = Clockwise. The rotation direction is indicated facing the drive pad or from the front of the engine for accessories driven from the front pulley of the engine. ** Driving pulley speed. Accessory rotation speed dependent on accessory pulley ratio. NOTE 5. MODEL DESCRIPTION IO-370-CL Base Model. Four cycle, four cylinder air/oil cooled, horizontally opposed, direct drive engine with a wet sump, positive displacement lubrication system, 9.6:1 compression ratio, engine cranking accomplished by a geared Bendix-style starter mounted on the crankcase that engages an external ring gear, fuel delivery via a traditional diaphragm-style AC, plunger-driven pump assembly mounted on the rear accessory housing, a fuel servo mounted below the engine, and a flow divider to direct the fuel flow to nozzles installed in each cylinder head. The engine is attached to the airframe using a Dynafocal mount. IO-370-CM Same as the IO-370-CL except the aircraft mounting interface is conical. IO-370-C1F Same as the IO-370-CL except hot oil sump, straight barrel fins, different cylinder baffle configuration. IO-370-D3A Same as the IO-370-C1F except straight oil filter adapter; non-counterweighted, solid crankshaft. IO-370-DA3A Same as the IO-370-D3A except the timing is set to 22° to reduce power. E 0 0 0 5 6 S E Pa ge 6 of 7 NOTE 6. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES PROVIDED A S PART OF THE ENGINE TYPE DESIGN Ignition IO-370-CL, CM, C1F S4LSC-21, S4LSC-204 Magnetos Radio Shielded Ignition Harness Tempest UREM38E Spark Plugs (8) IO-370-DA3A, D3A S4LSC-21 Magnetos Radio Shielded Ignition Harness Tempest UREM38E Spark Plugs (8) NOTE 7. COMPATIBLE ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES NOT PART OF THE ENGINE TYPE DESIGN Alternators As approved by the Aircraft Type Certificate Propeller Governors As approved by the Aircraft Type Certificate NOTE 8. ANTI-ICING REQUIREMENTS Not Applicable NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS The IO-370 has four integral mount legs at rear of crankcase, two on each crankcase half. The IO-370-CL, -C1F, -D3A, -DA3A crankcase is designed for a dynafocal mount; the IO-370-CM crankcase is designed for a conical mount. The aircraft manufacturer must incorporate appropriate mounting interface and engine mount isolators. Engine mount bosses have been tested to meet utility category aircraft load requirements specified in 14 CFR §23.337. NOTE 10. POWER BOOST, INJECTION, OR AUGMENTATION SYSTEMS AND LIMITS Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS Not Applicable NOTE 12. MANUFACTURER’S SERVICE BULLETIN Not Applicable NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS Not Applicable NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS Not Applicable NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS Document IO-370-CL IO-370-CM IO-370-C1F IO-370-DA3A IO-370-D3A Installation Drawing AEL30064 AEL30064 658805 658807 658807 Installation and Operation Manual OI-32 Maintenance and Overhaul Manual M-32 Instructions for Continuous Airworthiness are contained in M-32 NOTE 16. IMPORT REQUIREMENTS STATEMENT FOR FOREIGN MANUFACTURED ENGINES Not Applicable E 0 0 0 5 6 S E Pa ge 7 of 7 NOTE 17. LIFE LIMITED PART INFORMATION Not Applicable NOTE 18. MILITARY MODEL INFORMATION Not Applicable NOTE 19. HORIZONTAL OR VERTICAL INSTALLATION (ROTORCRAFT) Not Applicable NOTE 20. CENTER OF GRAVITY TABULATION Not Applicable – CG data provided in body of TCDS E00056SE NOTE 21. VIBRATION DAMPER PROVISION LIMITATIONS The IO-370-CL, -CM, & -C1F have counterweighted crankshafts. One 6.3 order; one 8th order counterweight installed on the crankshaft cheeks. The IO-370-D3A & -DA3A have non-counterweighted crankshafts. NOTE 22. ENGINE MODEL SPECIFICATION NUMBERS Engine model numbers may include a suffix to define minor specification changes and/or accessory packages. Example: IO-370-CL (C1U8). NOTE 23. ALTERNATIVE MARKING / SALES NAMES Continental will market the IO-370 Series engines as Continental Prime. …END… ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Continental IO-370-C1F](https://openairdocs.org/engine/continental-io-370-c1f): 1 aircraft (registry code 17495) - [Continental IO-370-DA3A](https://openairdocs.org/engine/continental-io-370-da3a): 1 aircraft (registry code 17491) - [TCM IO-370](https://openairdocs.org/engine/tcm-io-370-series): 1 aircraft (registry code 42980) ## STCs approved under this data sheet (1) - [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.