TCDS E1SO

Page No. 1 2 Rev. No. 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E1SO Revision 2 CONTINENTAL AEROSPACE TECHNOLOGIES, INC. 6-320B May 04, 2020 TYPE CERTIFICATE DATA SHEET NO. E1SO Engines of models described herein conforming with this data sheet (which is part of type certificate No. E1SO) 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. (Continental®) 2039 South Broad St. Mobile, Alabama 36615 Type Certificate Holder Record Continental Motors, Inc. Company name change January 1, 2020 (Continental Aerospace Technologies, Inc.) Teledyne Continental Motors Ownership & name change as of April 19, 2011 (Continental Motors, Inc.) Model 6-320-B Type 6HOGA Reduction Gear Ratio .5:1 Rating, ICAO or ARDC standard atmosphere Max. continuous hp, rpm, pressure altitude 300-4000 Takeoff hp, 5 min. rpm, full throttle at sea level pressure altitude 320-4400 Fuel (aviation gasoline, minimum grade) 100/130 Lubricating oil Lubricating oils qualified under SAE-J1899 or J1966 are considered qualified under Continental Spec MHS-24 Bore and stroke, in. 4.875 x 3.625 Displacement, cu. in. 406 Compression ratio 9.1:1 Weight (dry), lb. 382 C. G. location (basic engine) Aft of front face of prop flange, in. 21.47 Below crankshaft centerline, in. .38 Beside crankshaft centerline, in. left .73 (view from anti-propeller end) Propeller shaft ARP-502 Type I Flange 4-7/8 in. O.D. with six 1/2 in. bolt holes in 4 in. diameter circle Fuel injection Continental Injection system Ignition, dual magneto One Continental D-2000 Timing, BTC 30 Spark plugs (see NOTE 3) Oil Sump Capacity, qt. 9.0 - 5.0 usable at 36 nose up and 5.0 usable at 24 nose down NOTES 1, 2, 3, 4 E1SO 2 Certification basis Federal Aviation Regulations Part 33 dated February 1, 1965, as amended by 33-1 through 33-4. Application for Type Certificate dated February 3, 1970. Type Certificate No. E1SO issued May 27, 1975. Production basis None. Each engine produced is subject to compliance with 14 CFR Part 21.128, and a detailed inspection by an FAA representative for workmanship and conformance to the approved technical data. NOTE 1. Operating Limitations A. Maximum permissible temperatures: Cylinder head bayonet, thermocouple 460F Oil inlet 240F B. Fuel pressure limits: Inlet to injection pump, min. - minus 3.5 p.s.i.g. max. - plus 5.5 p.s.i.g. Recommended flight min. - minus 1.0 p.s.i.g. C. Fuel flow limits: See manufacturer’s FAA approved fuel flow schedule Curve No. 75-028 D. Oil pressure limits: 30 - 60 p.s.i.g. (30 p.s.i.g. min. in flight) 2-4-6 side - Normal 10 p.s.i.g. Idle 100 p.s.i.g. NOTE 2. The following accessory drive or mounting provisions are available: Direction of Speed Ratio Max. Torque (in.-lb.) Maximum Overhang Accessory Rotation* to Crankshaft Continuous Static Moment (in.-lb.) **Propeller governor C .59:1 30 825 50 Tachometer C .5:1 7 50 25 Optional (2) C .75:1 50*** 800 80 Alternator (belt driven) C 2:1 150 800 150 Oil Cooler -- -- -- -- 65 Starter: Continental P/N 636364 eligible *C - Clockwise viewing drive pad **Modified AND 20010 pad. ***One drive approved at 100 in. lbs. max. cont. provided second does not exceed 50 in. lbs. max. cont. NOTE 3. The following spark plugs and/or those listed in Section 6-4.9 of the latest revision of M-0, Standard Practice Maintenance Manual are approved on this engine: Champion RHU-27E, RHU-30E, RHU-30P, RHU-30W, and Smith Industries, Ltd. RS101R. NOTE 4. Overhaul Manual X 30144, approved May 31, 1973. .....END......