# TCDS E00001SC: Superior Air Parts Inc. - Type: Type certificate data sheet - Status: Current - Holder: Superior Air Parts Inc. - Revision: 4 - Revised: July 20, 2016 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 310, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/6d/39/6d39644a5b38a529ac1449d110d9f0965722d9ac89076fa0cfa53eda8b10be3b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EFE59EC584C1EE2B862580050056EFBD.0001 - Page: https://openairdocs.org/tcds/E00001SC ## Models (120) As the data sheet lists them. - IO-360-E1A2 - O-360-E6A1 - O-360-B5A1 - O-360-B1A1 - IO-360-D5A2 - IO-360-C4A2 - O-360-D4A2 - IO-360-A1A2 - O-360-A6A2 - IO-360-C3A2 - IO-360-C3A1 - O-360-A6A1 - IO-360-A5A1 - O-360-A1A1 - O-360-B4A1 - O-360-C1A1 - IO-360-C6A1 - IO-360-C6A2 - O-360-B2A2 - IO-360-C5A1 - O-360-A4A1 - IO-360-E6A2 - IO-360-E1A1 - O-360-C4A2 - IO-360-A3A2 - IO-360-B3A1 - O-360-D1A1 - IO-360-B1A2 - IO-360-C1A2 - IO-360-A5A2 - O-360-D3A2 - IO-360-A4A2 - IO-360-D6A2 - O-360-D4A1 - O-360-B6A1 - O-360-A1A2 - O-360-D3A1 - IO-360-D4A2 - O-360-C6A2 - O-360-E1A1 - IO-360-D1A2 - O-360-C5A2 - IO-360-C2A2 - IO-360-E5A2 - O-360-B6A2 - O-360-A3A2 - IO-360-A6A1 - IO-360-D3A1 - IO-360-B2A2 - IO-360-A2A1 - IO-360-C5A2 - O-360-E5A1 - O-360-E2A1 - IO-360-E2A1 - IO-360-A1A1 - IO-360-E6A1 - O-360-C2A1 - IO-360-E3A2 - IO-360-A6A2 - IO-360-B2A1 - IO-360-E5A1 - IO-360-E2A2 - IO-360-B4A2 - IO-360-A4A1 - O-360-E4A1 - O-360-D2A2 - O-360-A2A1 - O-360-A5A1 - O-360-A2A2 - O-360-D1A2 - O-360-C4A1 - O-360-C3A1 - IO-360-B4A1 - IO-360-D1A1 - O-360-C2A2 - O-360-B3A1 - O-360-D6A2 - O-360-C3A2 - O-360-D2A1 - IO-360-C1A1 - O-360-B3A2 - IO-360-E4A2 - IO-360-A3A1 - O-360-B5A2 - O-360-B1A2 - IO-360-D6A1 - O-360-E4A2 - IO-360-C4A1 - IO-360-B5A1 - IO-360-B3A2 - O-360-A5A2 - IO-360-D2A2 - O-360-A4A2 - O-360-B4A2 - IO-360-D5A1 - O-360-A3A1 - O-360-D5A2 - O-360-E3A1 - IO-360-D2A1 - IO-360-B1A1 - IO-360-E3A1 - IO-360-B6A2 - O-360-E2A2 - IO-360-A2A2 - IO-360-C2A1 - O-360-C5A1 - O-360-C6A1 - O-360-E3A2 - O-360-E1A2 - O-360-E6A2 - IO-360-E4A1 - IO-360-D3A2 - O-360-C1A2 - O-360-B2A1 - O-360-D6A1 - IO-360-B6A1 - O-360-D5A1 - IO-360-B5A2 - O-360-E5A2 - IO-360-D4A1 ## 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 Rev. No. 3 3 3 3 3 3 3 4 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00001SC REVISION: 4 Superior Air Parts Engines O-360-A1A1, A1A2, A2A1, A2A2, A3A1, A3A2, A4A1, A4A2, A5A1, A5A2 A6A1, A6A2, B1A1, B1A2, B2A1, B2A2, B3A1, B3A2, B4A1, B4A2, B5A1, B5A2, B6A1, B6A 2, C1A1, C1A2, C2A1, C2A2, C3A1, C3A2, C4A1, C4A2, C5A1, C5A2, C6A1, C6A2, D1A1, D1A2, D2A1, D2A2, D3A1, D3A2, D4A1, D4A2, D5A1, D5A2, D6A1, D6A2, E1A1, E1A2, E2A1, E2A2, E3A1, E3A2, E4A1, E4A2, E5A1, E5A2, E6A1, E6A2 IO-360-A1A1, A1A2, A2A1, A2A2, A3A1, A3A2, A4A1, A4A2, A5A1, A5A2 A6A1, A6A2, B1A1, B1A2, B2A1, B2A2, B3A1, B3A2, B4A1, B4A2, B5A1, B5A2, B6A1, B6A2, C1A1, C1A2, C2A1, C2A2, C3A1, C3A2, C4A1, C4A2, C5A1, C5A2, C6A1, C6A2, D1A1, D1A2, D2A1, D2A2, D3A1, D3A2, D4A1, D4A2, D5A1, D5A2, D6A1, D6A2, E1A1, E1A2, E2A1, E2A2, E3A1, E3A2, E4A1, E4A2, E5A1, E5A2, E6A1, E6A2 July 20, 2016 TYPE CERTIFICATE DATA SHEET NO. E00001SC Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E00001SC) 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: Superior Air Parts, Inc. 621 South Royal Lane, Suite 100 Coppell, TX 75019 Model O-360-A1A2, A2A2, A3A2 O-360-A4A2, A5A2, A6A2, B1A2, B2A2, B3A2, B4A2, B5A2, B6A2, C1A2, C2A2, C3A2 O-360-C4A2, C5A2, C6A2, D1A2, D2A2, D3A2, D4A2, D5A2, D6A2 Type 4HOA — — — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 180 — — — — Take-Off/Max. Continuous RPM 2700 — — — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — — — E00001SC, Rev 4 Page 2 Model O-360-A1A2, A2A2, A3A2 O-360-A4A2, A5A2, A6A2, B1A2, B2A2, B3A2, B4A2, B5A2, B6A2, C1A2, C2A2, C3A2 O-360-C4A2, C5A2, C6A2, D1A2, D2A2, D3A2, D4A2, D5A2, D6A2 Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — — — Bore and Stroke – in 5.125 x 4.375 — — — — Displacement – cubic in 361 — — — — Compression Ratio 8.5:1 — — — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 288 291 294 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — — — Principal Dimensions – in (Height x Width x Length) 24.6 x 33.4 x 32.8 — — — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — — — Fuel System Precision Airmotive Carburetor MA-4-5 type — — — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — — — Timing – °BTC R: 25°, L: 25° — — — — Spark Plugs Champion REM40E, Unison UREM40E — — — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — — indicates "same as preceding model" Model O-360-E1A2, E2A2, E3A2 O-360-E4A2, E5A2, E6A2 Type 4HOA — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 180 — — Take-Off/Max. Continuous RPM 2700 — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — Bore and Stroke – in 5.125 x 4.375 — — Displacement – cubic in 361 — — Compression Ratio 8.5:1 — — E00001SC, Rev. 4 Page 3 Model O-360-E1A2, E2A2, E3A2 O-360-E4A2, E5A2, E6A2 Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 295 298 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — Principal Dimensions – in (Height x Width x Length) 24.6 x 33.4 x 32.8 — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — Fuel System Precision Airmotive Carburetor MA-4-5 type — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — Timing – °BTC R: 25°, L: 25° — — Spark Plugs Champion REM40E, Unison UREM40E — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — indicates "same as preceding model" Model O-360-A1A1, A2A1, A3A1 O-360-A4A1, A5A1, A5A1, B1A1, B2A1, B3A1, B4A1, B5A1, B6A1, C1A1, C2A1, C3A1 O-360-C4A1, C5A1, C6A1, D1A1, D2A1, D3A1, D4A1, D5A1, D6A1 Type 4HOA — — — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 168 — — — — Take-Off/Max. Continuous RPM 2700 — — — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — — — Bore and Stroke – in 5.125 x 4.375 — — — — Displacement – cubic in 361 — — — — Compression Ratio 7.2:1 — — — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 288 291 294 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — — — Principal Dimensions – in (Height x Width x Length) 24.6 x 33.4 x 32.8 — — — — E00001SC, Rev 4 Page 4 Model O-360-A1A1, A2A1, A3A1 O-360-A4A1, A5A1, A5A1, B1A1, B2A1, B3A1, B4A1, B5A1, B6A1, C1A1, C2A1, C3A1 O-360-C4A1, C5A1, C6A1, D1A1, D2A1, D3A1, D4A1, D5A1, D6A1 Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — — — Fuel System Precision Airmotive Carburetor MA-4-5 type — — — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — — — Timing – °BTC R: 25°, L: 25° — — — — Spark Plugs Champion REM40E, Unison UREM40E — — — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — — — indicates "same as preceding model" Model O-360-E1A1, E2A1, E3A1 O-360-E4A1,E5A1, E6A1 Type 4HOA — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 168 — — Take-Off/Max. Continuous RPM 2700 — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — Bore and Stroke – in 5.125 x 4.375 — — Displacement – cubic in 361 — — Compression Ratio 7.2:1 — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 295 298 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — Principal Dimensions – in (Height x Width x Length) 24.6 x 33.4 x 32.8 — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — Fuel System Precision Airmotive Carburetor MA-4-5 type — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — Timing – °BTC R: 25°, L: 25° — — E00001SC, Rev. 4 Page 5 Model O-360-E1A1, E2A1, E3A1 O-360-E4A1,E5A1, E6A1 Spark Plugs Champion REM40E, Unison UREM40E — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — indicates "same as preceding model" Model IO-360-A1A2, A2A2, A3A2 IO-360-A4A2, A5A2, A6A2, B1A2, B2A2, B3A2, B4A2, B5A2, B6A2, C1A2, C2A2, C3A2 IO-360-C4A2, C5A2, C6A2, D1A2, D2A2, D3A2, D4A2, D5A2, D6A2 Type 4HOA — — — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 180 — — — — Take-Off/Max. Continuous RPM 2700 — — — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — — — Bore and Stroke – in 5.125 x 4.375 — — — — Displacement – cubic in 361 — — — — Compression Ratio 8.5:1 — — — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 290 293 296 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — — — Principal Dimensions – in (Height x Width x Length) 24.0 x 33.4 x 32.8 — — — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — — — Fuel System Precision Airmotive Fuel Injection RSA-5 type — — — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — — — Timing – °BTC R: 25°, L: 25° — — — — Spark Plugs Champion REM40E, Unison UREM40E — — — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — — indicates "same as preceding model" E00001SC, Rev 4 Page 6 Model IO-360-E1A2, E2A2, E3A2 IO-360-E4A2, E5A2, E6A2 Type 4HOA — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 180 — — Take-Off/Max. Continuous RPM 2700 — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — Bore and Stroke – in 5.125 x 4.375 — — Displacement – cubic in 361 — — Compression Ratio 8.5:1 — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 297 300 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — Principal Dimensions – in (Height x Width x Length) 24.0 x 33.4 x 32.8 — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — Fuel System Precision Airmotive Fuel Injection RSA-5 type — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — Timing – °BTC R: 25°, L: 25° — — Spark Plugs Champion REM40E, Unison UREM40E — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — indicates "same as preceding model" Model IO-360-A1A1, A2A1, A3A1 IO-360-A4A1, A5A1, A6A1, B1A1, B2A1, B3A1, B4A1, B5A1, B6A1, C1A1, C2A1, C3A1 IO-360-C4A1, C5A1, C6A1, D1A1, D2A1, D3A1, D4A1, D5A1, D6A1 Type 4HOA — — — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 168 — — — — Take-Off/Max. Continuous RPM 2700 — — — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — — — Fuel E00001SC, Rev. 4 Page 7 Model IO-360-A1A1, A2A1, A3A1 IO-360-A4A1, A5A1, A6A1, B1A1, B2A1, B3A1, B4A1, B5A1, B6A1, C1A1, C2A1, C3A1 IO-360-C4A1, C5A1, C6A1, D1A1, D2A1, D3A1, D4A1, D5A1, D6A1 Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — — — Bore and Stroke – in 5.125 x 4.375 — — — — Displacement – cubic in 361 — — — — Compression Ratio 7.2:1 — — — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 290 293 296 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — — — Principal Dimensions – in (Height x Width x Length) 24.0 x 33.4 x 32.8 — — — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — — — Fuel System Precision Airmotive Fuel Injection RSA-5 type — — — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — — — Timing – °BTC R: 25°, L: 25° — — — — Spark Plugs Champion REM40E, Unison UREM40E — — — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — — indicates "same as preceding model" Model IO-360-E1A1, E2A1, E3A1 IO-360-E4A1, E5A1, E6A1 Type 4HOA — — Rating U.S. Standard Atmosphere and ICAO at Sea Level Pressure Altitude Take-Off/Max. Continuous HP 168 — — Take-Off/Max. Continuous RPM 2700 — — Take-Off/Max. Cont. Manifold Press. – in Hg 29.5 — — Fuel Aviation Gasoline ASTM D910, Grade 100, 100LL or 100VLL ASTM D7547 — — Motor Gasoline (R+M/2) ASTM D4814, Min Octane 91 (no alcohol) — — Lubricating Oil SAE J-1899, See Installation & Operation Manual, SVIOM01 — — Bore and Stroke – in 5.125 x 4.375 — — E00001SC, Rev 4 Page 8 Model IO-360-E1A1, E2A1, E3A1 IO-360-E4A1, E5A1, E6A1 Displacement – cubic in 361 — — Compression Ratio 7.2:1 — — Weight (Basic Engine, Dry) – lbs See Installation & Operation Manual, SVIOM01, for detailed model weights 297 300 C.G. Location (Basic Engine) See Installation & Operation Manual, SVIOM01 — — Principal Dimensions – in (Height x Width x Length) 24.0 x 33.4 x 32.8 — — Propeller Shaft Direct, SAE Modified Type 2 per AS127 — — Fuel System Precision Airmotive Fuel Injection RSA-5 type — — Ignition – Two Magnetos Unison Impulse Magnetos 4371 with the appropriate ignition harness — — Timing – °BTC R: 25°, L: 25° — — Spark Plugs Champion REM40E, Unison UREM40E — — Oil Sump Capacity 8 quarts; 6 qts. usable at 20° noseup, and 6.5 qts. usable at 10° nosedown attitudes — — — — — indicates "same as preceding model" CERTIFICATION BASIS: FAR 33 Through Amendment 20, effective 12/13/2000 PRODUCTION BASIS: Production Certificate 14SW O-360 IO-360 NOTE 1. Maximum Permissible Temperatures Oil at Engine Inlet 245° F — — Cylinder Head Temperature 500° F — — NOTE 2. Fuel Pressure Limits Inlet to Pump, Min. +0.5 psig -2 psig Max. +8 psig +35 psig NOTE 3. Oil Pressure Limits into Engine Normal 55-95 psig — — Idle 20 psig — — Max (Cold Oil) 115 psig — — — — indicates "same as preceding model" NOTE 4. The following accessory drive or mounting provisions are available: Direction Drive Ratio Max. Torque Max. Overhang of to (in-lbs) Moment Accessory Rotation* Crankshaft Continuous Static (in-lbs) Tachometer CW 0.5:1 7 50 5 Starter CCW 16.56:1 N/A 450 150 Alternator (not supplied) CW 3.25:1 60 120 175 Propeller Governor, Rear** CW 0.866:1 125 825 40 Propeller Governor, Front** CW 0.895:1 125 825 40 Fuel Pump Reciprocating 0.5:1 N/A N/A 10 Accessory Drive*** CCW 1.3:1 70 450 25 E00001SC, Rev. 4 Page 9 * "CW" – Clockwise; and "CCW" – Counterclockwise (Viewing Drive Pad) ** This is an AND20010 drive pad and only applicable to models with provisions to control propeller pitch and shall be supplied with a cover. *** This is an AND20000 drive pad and shall be supplied with a cover. NOTE 5. See the chart at the end of the TCDS for the Engine Model Designation codes. NOTE 6. Experience has shown that there is a higher probability of vapor locking on aircraft, especially on those equipped with fuel injected reciprocating engines when operating with high volatility fuels such as motor gasoline. Aircraft fuel system designs for the powerplant installation of these engines may need to incorporate special design features or enhanced cooling to accommodate operation with high volatility fuel s such as motor gasoline. The aircraft fuel system hot weather testing requirements of FAR 23.961 must be successfully accomplished for each aircraft powerplant installation design of these engines (both carbureted and fuel injected) to obtain approval for operation with motor gasoline, reference AC 23.1521-1B. Model Designation Code: EXAMPLE: IO-360-A1A2 Fuel System: O- Carbureted IO- Fuel Injected Cylinder Type (Engine Displacement): 360- Parallel Valve Cylinder, 361 cubic inch displacement Crankshaft and Propeller Type: A- Thin Wall Front Main Bearing Journal Crankshaft, Fixed Pitch Propeller B- Thin Wall Front Main Bearing Journal Crankshaft, Constant Speed Propeller C- Heavy Wall Front Main Bearing Journal Crankshaft, Fixed Pitch Propeller D- Heavy Wall Front Main Bearing Journal Crankshaft, Constant Speed Propeller E- Solid Front Main Bearing Journal Crankshaft, Fixed Pitch Propeller Crankcase and Engine Mount Type: 1- Number 1 Dynafocal engine mount with Rear Propeller Governor 2- Number 2 Dynafocal engine mount with Rear Propeller Governor 3-Conical engine mount with Rear Propeller Governor 4- Number 1 Dynafocal engine mount with Front Propeller Governor 5-Number 2 Dynafocal engine mount with Front Propeller Governor 6-Conical engine mount with Front Propeller Governor 0.Note: Crankcase types 1, 2 and 3 incorporate a rear propeller governor pad and crankcase types 4, 5 and 6 incorporate a front propeller governor pad for constant speed propeller models. Engine crankcase types 4, 5, and 6 also include provisions for a front bed type engine mount. Accessory Package (Sump/Induction System): A- Wet Sump, Updraft Induction Power Rating (Compression Ratio): 1- 7.2:1 CR, 168 bhp 2- 8.5:1 CR, 180 bhp ...END... ``` ## ADs (1, in force first) - [AD 2020-25-12](https://openairdocs.org/ad/2020-25-12): Reciprocating Engine Power Section · Superior Air Parts IO-360-A1A1, IO-360-A1A2, IO-360-A2A1 and 146 more. Effective Jan 15, 2021 ## Registered aircraft by registry model (OpenAirDocs) - [Superior IO-360 series](https://openairdocs.org/engine/superior-io-360-series): 201 aircraft (registry code 59251) - [Superior O-360 series](https://openairdocs.org/engine/superior-o-360-series): 92 aircraft (registry code 59250) - [Superior IO-360-B1A2](https://openairdocs.org/engine/superior-io-360-b1a2): 9 aircraft (registry code 59259) - [Superior O360B1A2](https://openairdocs.org/engine/superior-o360b1a2): 4 aircraft (registry code 59266) - [Superior O-360-A3A2](https://openairdocs.org/engine/superior-o-360-a3a2): 3 aircraft (registry code 59262) - [Vantage O-360-A3A2](https://openairdocs.org/engine/vantage-o-360-a3a2): 1 aircraft (registry code 59555) ## STCs approved under this data sheet (4) - [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 SE04349CH](https://openairdocs.org/stc/SE04349CH): Installation of SureFly electronic ignition. SureFly Partners Ltd. - [STC SE04577CH](https://openairdocs.org/stc/SE04577CH): Install an electronic engine ignition system. Electroair Acquisition Corp - [STC SE02409AK](https://openairdocs.org/stc/SE02409AK): Installation of the Superior Air Parts Cold Air Induction System (CAIS). Wattum Aircraft Services --- 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.