TCDS E00098EN

PAGE 1 2 3 4 5 REV. 1 0 0 1 1 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET EN00098EN TCDS NUMBER: E00098EN REVISION: 1 DATE: December 19, 2023 Continental Aerospace Technologies GmbH MODEL: Centurion 3.0 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E000 98EN and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft i n 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 Platanenstr. 14 D-09356 Sankt Egidien Germany TYPE CERTIFICATE HOLDER RECORD Technify Motors GmbH (befpre August 1, 2019) (Name change of TC Holder) TYPE The Centurion 3.0 engine is a V6 -cylinder, four stroke Diesel piston engine, equipped with common rail high pressure direct injection, dual turbochargers, reduction gearbox and an Electronic Engine Control Unit (EECU). MODEL Centurion 3.0 RATINGS (See Note 1) Takeoff (5 min) 300 HP (221 Kw) at 3880 rpm (2340 prop rpm) Max. Continuous 272 HP (200 Kw) at 3830 rpm (2300 prop rpm) FUEL The Centurion 3.0 series engines are approv ed for operation with jet fuels . See Operations and Maintenance Manual for approved fuels and NOTE 11. OIL See Operations and Maintenance Manual for approved oils CAPACITY Maximum 3.17 Gal / 12 L Minimum 2.64 Gal /10 L WEIGHT (dry) 265 kg/584 lb DISPLACEMENT 103.07 in3 / 1,689 cm3 PRINCIPAL DIMENSIONS Length 38.58 in (980 mm) Width 27.56 in (700 mm) Height 31.10 in (790 mm) BORE 3.27 in / 83.00 mm STROKE 3.62 in / 92.00 mm COMPRESSION RATIO 15.5:1 PROPELLER ROTATION CCW (viewed from the engine to the propeller) TCDS E00098EN PAGE 2 GEAR REDUCTION (Crankshaft to propeller) 1.66:1 MODEL (CONTINUED) Centurion 3.0 CONTROL SYSTEM (see NOTE 11) Electric Engine Control Unit (EECU) FADEC P/N 06-7610-E000202 SOFTWARE P/N D6-v1.0 SOFTWARE MAPPING Refer to Service Bulletin TM TAE 000 -0007 for approved software part number FLUIDS (Fuel/Oil/Additives) See Operation and Maintenance Manual for approved fluids CERTIFICATION BASIS 14 CFR part 33 effective February 1, 1965 and Amendments 33-1 through Amendment 33-33. Model Date of Application Date Type Certificate Issued/Revised Centurion 3.0 May 17, 2023 June 23, 2023 IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with EASA airworthiness approval shall have a 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 E00098EN, is in a condition for safe operation, and has undergone a final operational check. NOTES: NOTE 1. ENGINE RATINGS The performance values specified correspond to minimum values defined under the conditions of ICAO or ARDC standard atmosphere. NOTE 2. TEMPERATURE LIMITS (°F/°C): Oil Temperature: Minimum opening up Oil Temperature: 122 (50) Maximum Oil Temperature: 257 (125) Minimum Ambient Temperature for Starting: 41 (5) With 32 ≤ Cetane No. < 38 -13 (-25) With Cetane No. ≥ 38 Minimum Fuel Temperature during opration -13 (-25) Minimum opening up Cooling Fluid Temperature: 140 (60) Maximum Cooling Fluid Temperature: 221 (105) Maximum Gearbox Fluid Temperature: 230 (11`0) Maximum Exhaust Gas Tempe rature 1562 (850) NOTE 3. FUEL AND OIL PRESSURE LIMITS (PSI / bar) Minimum Fuel Pressure (at inlet of feed pump) 4.4 (-0.3) Maximum Fuel Pressure (at inlet of feed pump) 14.5 (1.0) Maximum Oil Pressure at Idle Conditions: 29 (2) Oil Pressure (normal operation) 33.4 to 101.5 (2.3 to 7.0) Maximum Oil Pressure: 108.8 (7.5) TCDS E00098EN PAGE 3 NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS Rotation Speed (rpm) Max.Torque Type of Drive Counter Clock Wise 3900 13Nm AND 20000 modified Speed is indicated for a reference engine speed of 3880 rpm. Accessory drive direction of rotation is as viewed facing the drive. NOTE 5. MODEL DESCRIPTION Centurion 3.0 – Base model (Sales name is CD-300) Suffixes in parentheses may be added to the engine model number to define installation specific configuration changes. The software of the electronic engine control for each application has a specific software mapping. See Service Bulletin TM TAE 000-0007 for the installation versions and softwa re mappings. Also refer to Installation Manual for appropriate installation. NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not Applicable NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS See Operation and Maintenance Manual NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS AS APPLICABLE Engine is equipped with dual turbochargers Max turbocharger speed, rpm: 195500 TCDS E00098EN PAGE 4 NOTE 11. SPECIAL INSTALLATION REQUIREMENT S The Centurion 3.0 series engines are approv ed for operation with jet fuels . The engine has been tested for fuels up to a maximum ignition delay time of 6,78 ms resp. a minimum derived cetane number of 32 (determined accor ding EN 15195/ASTM D6890). 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. Time Limited Dispatch : The engine is not approved for Time Limited Dispatch. 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. For special instructions, see applicable Operation Manual. The electronic control unit (EECU) must not be installed in a dedicated fire zone. The installation conditions are defined in the Installation Manual. The engine is approved for installation in 14 CFR part 23 Normal and Utility aircraft categories only. The engine design features an integrated propeller control in the FADEC. The software in the FADEC has been developed in accordance with DO -178B at level C. The approval of the engine and its FADEC does not include approval of the propeller control system. The Centuron 3.0 engine, including the FADEC, is approved for use with the propeller MTV -12-D/210-56 models. This approval does not include the approval of the propellers and their control systems. NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS Service Bulletins, structural repair manuals, vendor manuals, AFMs, and overhaul and maintenance manuals, which contain a statement that the document is approved by EASA, are accepted by the FAA and are considered FAA ap proved. (These approvals pertain to the design data only). NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS Crankshaft Speed RPM Maximum Engine Over -speed 4220 (2500 prop) Take off 3880 (2340 prop) Maximum continuous 3830 (2300 prop) Maximum altitude 25,000 ft / 7620 m NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS Engine maintenance is limited to instructions identi fied in Maintenence Manual OM-06-01 and Repair Manual RM-06-01. Refer to the Airworthiness Limitations Section of OM-06-01 for engine assembly life limits and c ertain maintenance restrictions. NOTE 15. APPLICABLE MANUALS The following Engine Instructions for Continued Airworthiness (ICA’s) have been accepted by the FAA : Maintenance Manual OM-06-01 Repair Manual RM-06-01 The following manuals have been approved under the requirements of 14 CFR § 33.5 Installation Manual IM-06-01 Operation Manual OM-06-01 TCDS E00098EN PAGE 5 NOTE 16. IMPORT REQUIREMENTS STATEMENT FOR FOREIGN MANUFACTURED ENGINES See import requirements above. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used airc raft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA or der 8130.2, Airworthiness Certificates of Aircraft , for requirements for issuance of an airworthiness certificate for imported aircraft. . NOTE 17. LIFE LIMITED PART INFORMATION The engine assembly has a life limt of 2000 hours of operation or 12 years, whichever comes first, and must be removed from service. Maintenance actions that require engine disassembly and inspection t o make an airworthiness dertemination that are not identied in the Maintenance Manual or R epair Manual require the engine to be removed from service. NOTE 18. MILITARY MODEL INFORMATION Not Applicable NOTE 19. HORIZONTAL OR VERTICAL INSTALLATION (ROTORCRAFT) Horizontal for part 23 installations NOTE 20. CENTER OF GRAVITY TABULATION (IF NOT SHOWN IN BODY OF TCDS) See Installation Manual NOTE 21. VIBRATION DAMPER PROVISION LIMITATIONS Not Applicable END