TCDS E00079EN

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET TCDS NUMBER: E00079EN REVISION: Revision 2 DATE: May 13 , 2021 MODELS: Centurion 4.0 BE-210, Centurion 4.0 BE-221 Centurion 4.0 BE-228, Centurion 4.0 BE-239 Centurion 4.0 BE-250, Centurion 4.0 BE-257 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00079EN 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 (TC) HOLDER: Continental Aerospace Technologies GmbH Platanenstrasse 14 D-09356 Sankt Egidien Germany TYPE CERTIFICATE HOLDER RECORD: Technify Motors GmbH transferred TC E00079EN to Continental Aerospace Technologies GmbH on August 1, 2019 Thielert Aircraft Engines GmbH transferred TC E00079EN to Technify Motors GmbH on August 19, 2013 MODELS (see Note 15) Centurion 4.0 BE-210 Centurion 4.0 BE-221 Centurion 4.0 BE-228 Centurion 4.0 BE-239 Centurion 4.0 BE-250 Centurion 4.0 BE-257 TYPE The Centurion 4.0 engine is a liquid-cooled 8 cylinder, 4 stroke diesel cycle engine with a displacement of 3996 cm3. It is equipped with common rail high pressure direct injection, 2 turbochargers, gearbox with reduction ratio of 1:1.689, propeller, governor, and FADEC. RATINGS (US Standard Atmosphere at Sea Level Pressure Altitude), KW, (Note 17) Takeoff 210 at 3900 rpm 221 at 3900 rpm 228 at 3900 rpm 239 at 3900 rpm 250 at 3900 rpm 257 at 3900 rpm Max. Continuous 210 at 3900 rpm 221 at 3900 rpm 228 at 3900 rpm 228 at 3900 rpm 228 at 3900 rpm 228 at 3900 rpm Max. Best Economy Cruising 154 at 3300rpm 154 at 3300rpm 154 at 3300rpm 154 at 3300rpm 154 at 3300rpm 154 at 3300rpm FUEL (Also see Operation & Maintenance Manual) Jet A, Jet A-1, Jet Fuel No.3, JP-8 and JP-8+100 OIL (See NOTE 4) Use the approved oil with exact declaration only. See Operation and Maintenance Manual OM-03-01 (US-Version) or Installation Manual IM-03-01 for approved oils OIL SUMP CAPACITY, liters Maximum level 10 Minimum level 7 Max. oil consumption 0.1 liter per hour PRINCIPAL DIMENSIONS Length, mm Width, mm Height, mm 900 670 770 PAGE 1 2 3 4 REV. 2 - - - - - - LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY ARE BLACK. LINED IN THE LEFT MARGIN MODELS (Continued) Centurion 4.0 BE-210 Centurion 4.0 BE-221 Centurion 4.0 BE-228 Centurion 4.0 BE-239 Centurion 4.0 BE-250 Centurion 4.0 BE-257 CENTER OF GRAVITY, mm Relating to propeller flange, z-axis point downwards (Refer to Installation Manual) X=635 Y=0 Z=10 WEIGHT (dry), kg 286 BORE, mm 86.00 STROKE, mm 86.00 Displacement Total, cm3 3996 COMPRESSION RATIO 18.5:1 PROPELLER ROTATION CCW GEAR REDUCTION (crankshaft to propeller) 1.689 : 1 CONTROL SYSTEM (See Notes 11-14) Full Authority Digital Engine Control (FADEC): P/N 02-7610-55003R1 or later approved standard Software P/N : Refer to Service Bulletin (SB) TM TAE 000-0007 or later approved standard Software Mapping : Refer to SB TM TAE 000-0007 for approved installation version CERTIFICATION BASIS FAR 21.29 and FAR 33 effective February 1, 1965 and Amendments 33-1 through Amendment 33-20. Model Date of Application Date Type Certificate Issued/Revised Centurion 4.0 BE-210 October 8, 2006 April 14 2008 Centurion 4.0 BE-221 October 8, 2006 April 14 2008 Centurion 4.0 BE-228 October 8, 2006 April 14 2008 Centurion 4.0 BE-239 October 8, 2006 April 14 2008 Centurion 4.0 BE-250 October 8, 2006 April 14 2008 Centurion 4.0 BE-257 October 8, 2006 April 14 2008 IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States shall be accompanied by a Certificate of Airworthiness for export with EASA Form 1, Authorized Release Certificate. The EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00079EN, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, "Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States." MODELS Centurion 4.0 BE-210 Centurion 4.0 BE-221 Centurion 4.0 BE-228 Centurion 4.0 BE-239 Centurion 4.0 BE-250 Centurion 4.0 BE-257 NOTE 1: Engine permissible maximum crankshaft speed 4220 rpm NOTE 2: Temperature Limitations, deg F(C) Min ambient temperature for starting -13 (-25) NOTES TCDS E00079EN Page 3 of 4 MODELS (Continued) Centurion 4.0 BE-210 Centurion 4.0 BE-221 Centurion 4.0 BE-228 Centurion 4.0 BE-239 Centurion 4.0 BE-250 Centurion 4.0 BE-257 Max Oil Temperature 284 (140) Min opening up Oil Temperature 122 (50) Min opening up Cooling Fluid Temperature 140 (60) Max Cooling Fluid Temperature 221 (105) Max Gearbox Temperature 248 (120) NOTE 3: Altitude 1. Maximum altitude, 25,000 ft 2. Critical altitude, 12,000 ft NOTE 4: Fuel and Oil Pressure Limits, kPa Min Fuel Pressure at LP Engine pump Inlet 70 Max Oil Pressure for cold start, up to 20 seconds 700 Min Oil Pressure 100 Normal Oil Pressure 300-400 NOTE 5: Dispatch Limitations: All engine systems and equipment must be functional prior to aircraft take-off. Any detected engine system or equipment failure must be corrected before next flight. NOTE 6: Centurion 4.0 engine is Life-Limited. The core engine must be removed from service in accordance with the Airworthiness Limitations Section, Chapter 5 of the Operation & Maintenance manual OM-03-01 (US-Version). NOTE 7: Overhaul of the core engine is not permitted. See Overhaul Manual for the accessory/parts permitted for overhaul. NOTE 8: The Instructions for Continued Airworthiness contained in the Operation & Maintenance Manual, OM-03-01 (US-Version) have been approved by the FAA. NOTE 9: Any repair other than those covered by the Instructions for Continued Airworthiness or DER approved repairs in accordance with FAR Part 183 must be approved by the Engine Certification Office. NOTE 10: The engine is approved for installation in FAR 23 Normal and Utility aircraft categories only. NOTE 11: The software of the ECU has been validated according to DO 178 B, level C. NOTE 12: The FADEC system relies on electrical power supplied from the aircraft. Interruption of the FADEC electrical power supply will result with FADEC reboot and reinitiate. NOTE 13: The electrical interface requirements between the FADEC and the aircraft electrical system are defined in the Installation Manual. NOTE 14: EMI/Lightning: The engine control system has been tested according to DO 160 D for lightning protection and magnetic interference. The demonstrated levels are provided in the Installation Manual. NOTE 15: Engine model numbers may include suffixes in parentheses to define installation specific configuration changes. Each application has a specific software mapping. Refer to SB TM TAE 000-0007 for installation of the software of engine control. NOTE 16: Engine Manual : Installation Manual : IM-03-01 Operation & Maintenance Manual : OM-03-01(US version) Overhaul Manual : OHM-03-01 NOTE 17: Convert from kW to Horsepower (hp), use conversion factor- 1kW=1.341022 hp (international) TCDS E00079EN Page 4 of 4 NOTE 18: Service Information: Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA). Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved.  Service bulletins,  Structural repair manuals,  Vendor manuals,  Aircraft flight manuals, and  Overhaul and maintenance manuals. These approvals pertain to the type design only. ---THE END---