TCDS E11CE

Page No. 1 2 Rev. No. 5 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E11CE Revision 5 CONTINENTAL AEROSPACE TECHNOLOGIES, INC. 6-620-A June 01, 2020 TYPE CERTIFICATE DATA SHEET NO. E11CE Engines of models described herein conforming with this data sheet (which is part of type certificate No. E11CE) 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 6-260-A Type 6HOGA Reduction Gear Ratio .5:1 Rating,. ICAO or ARDC standard atmosphere Max. continuous hp., r.p.m. in. Hg. at Critical altitude, ft. 260-4000-F.T.S.L. Sea level pressure altitude 260-4000 F.T. Takeoff hp., 5 min., r.p.m. 260-4000 F.T. Full throttle at sea level pressure altitude 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 9.0:1 Weight (dry), lb. 354 C.G. location (basic engine) Aft of front face of prop. flange, in. 20.65 Below crankshaft centerline, in. .66 Beside crankshaft centerline 0 Propeller shaft ARP-502 Type I Flange 4-7/8 in. O.D. with six 1/2 in. bolt holes 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. 9:4,5 usable at 18 noseup and nosedown altitudes NOTES 1, 2, 3 E11CE Page 2 Certification basis Federal Aviation Regulations Part 33 dated February 1, 1965, as amended by 33-1 thru 33-3. Application for Type Certificate dated July 2, 1968. Type Certificate No. E11CE issued September 8, 1969 for Model 6-260-A. Production basis - None. Each engine produced is subject to a detailed inspection for workmanship and conformance with approved data by an FAA representative. Each engine must have a satisfactory run in. Upon completion of the above, the FAA representative shall tag the engine with Tag Form 8130-3. NOTE 1. Operating Limitations A. Maximum permissible temperature: Cylinder head bayonet, thermocouple 460F. Oil inlet 240F. B. Fuel pressure limits: Inlet to injection pump, min. - minus 2 p.s.i. max. - plus 5.5 p.s.i. Recommended flight min. minus 1.0 p.s.i. C. Fuel flow limits: See manufacturer’s FAA approved fuel flow schedule, Curve No. E-6591. D. Oil pressure limits: 2-4-6 side - Normal 30 - 60 p.s.i. Idle 10 p.s.i. Max.(Cold Oil) 100 p.s.i. NOTE 2. The following accessory drive or mounting provisions are available: Direction Speed Ratio Max. Torque (in.-lb.) Maximum Overhang Accessory of Rotation to Crankshaft Continuous Static Moment (in.-lb.) **Propeller governor C .67:1 29 825 50 Tachometer C .5:1 7 50 25 Optional (2) C .75:1 27 800 8.3 Generator (belt-driven) C 2:1 60 600 50 Oil cooler -- -- -- 65 Starter: Continental P/N 636364 eligible. *C - Clockwise viewing drive pad **Modified AND 20010 pad. NOTE 3. The following spark plugs are approved: Champion RHU-E-427. ...END...