TCDS E00069EN

I I I I I I I TCDS NUMBER: E00069EN U.S. DEPARTMENT OF TRANSPORTATION REVISION: 7 FEDERAL AVIATION ADMINISTRATION DATE: Oct 21, 2021 TYPE CERTIFICATE DATA SHEET MODELS: TAE 125-01, TAE 125-02-99, TAE 125-02-114, TAE 125-02-125 EN00069EN Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00069EN 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 Platanenstrasse 14 D-09356 Sankt Egidien Germany TYPE CERTIFICATE HOLDER RECORD Technify Motors GmbH transferred TC E00069EN to Continental Aerospace Technologies GmbH on August 1, 2019 Thielert Aircraft Engines GmbH transferred TC E00069EN to Technify Motors GmbH on August 19, 2013 I. MODELS TAE 125-01 TAE 125-02-99 TAE 125-02-114 TAE 125-02-125 TYPE The TAE 125 engine is a liquid -cooled 4 cylinder, 4 stroke in -line diesel cycle engine with Double Overhead Camshaft. It is equipped with common rail high pressure direct injection, turbocharger, and gearbox with reduction ratio of 1:1.689, propeller governor and FADEC, including propeller pitch control. RATINGS (See Note 1), HP (KW) Takeoff (5 min) - - 167.6 (125) at 3900 rpm Max. Continuous 132.8 (99) at 3900 rpm 152.6 (114) at 3900 rpm 152.6 (114) at 3800 rpm Max Recommended Cruising - - 118 (88) at 3400 rpm Max. Best Economy Cruising 95 (71) at 3400 rpm 130 (97) at 3400 rpm 95 (71) at 3250 rpm FUEL (Also see Operations and Maintenance Manual) See Operations and Maintenance Manual for approved fuels OIL (See NOTE 3) See Operations and Maintenance Manual for approved oils PAGE 1 2 3 4 5 6 REV. 7 7 7 7 7 7 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY ARE BLACK.LINED IN THE LEFT MARGIN I. MODELS (CONTINUED) TAE 125-01 TAE 125-02-99 TAE 125-02-114 TAE 125-02-125 OIL SUMP CAPACITY Gallons (Liters) Maximum level 1.59 (6.0) - - - - - - Minimum level 1.19 (4.5) - - - - - - Total (in addition to the volume in the hosing and oil cooler) 1.59 (6.0) - - - - - - PRINCIPAL DIMENSIONS Length, in (mm) 32.12 (816) - - - - - - Width, in (mm) 30.63 (778) - - - - - - Height, in (mm) 25.03 (636) - - - - - - CENTER OF GRAVITY Refer to Installation Manual IM 02-01 Refer to Installation Manual IM-02-02 Refer to Installation Manual IM-02-02 Refer to Installation Manual IM-02-02B WEIGHT (dry) 134 kg - - - - 156 kg DISPLACEMENT 1,689 cm3 1,991 cm3 - - - - BORE 80.00 mm 83.00 mm - - - - STROKE 84.00 mm 92.00 mm - - - - COMPRESSION RATIO 18:1 - - - - 15.5:1 PROPELLER ROTATION CCW - - - - - - GEAR REDUCTION (Crankshaft to propeller) 1.689:1 - - - - - - CONTROL SYSTEM (see NOTE 11) Full Authority Digital Engine Control (FADEC) FADEC P/N 02-7610-55001 R1 05-7610-K000101 - - 05-7611-E0019 06 SOFTWARE P/N TAE-125 m2.91 TAE-125 m3.0 - - D4-190 SOFTWARE MAPPING Refer to Service Bulletin TM TAE 000-0007 - - - - - - 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 33-20. The aviation authority for Germany, Luftfahrt-Bundesamt, originally type certificated this engine under its type certificate Number 4631. The type certificate was transferred to EASA under EASA type certificate E.055 on March 24, 2006. The European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. The FAA validated this product under U.S. Type Certificate Number E00069EN. Model Date of Application Date Type Certificate Issued/Revised TAE125-01 April 17, 2001 October 14, 2004 TAE125-02-99 September 18, 2006 October 25, 2006 TAE125-02-114 January 17, 2007 March 27, 2007 TAE 125-02-125 March 29, 2021 October 15, 2021 IMPORT To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the REQUIREMENTS United States with Luftfahrt-Bundesamt (LBA) or 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 E00069EN, 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." II. 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: 284 (140) 248 (120) (TAE 125-02-125 only) Minimum Ambient Temperature for Starting: -26 (-32) -13(-25) (TAE 125-02-125 only) Minimum opening up Cooling Fluid Temperature: 140 (60) Maximum Cooling Fluid Temperature: 221 (105) Maximum Gearbox Fluid Temperature: 248 (120) NOTE 3. FUEL AND OIL PRESSURE LIMITS PSI (kPa) Minimum Fuel Pressure: 2.9 (20) Maximum Oil Pressure: 94.3 (650) Minimum Oil Pressure: Minimum Oil Pressure at Idle: 33.4 (230) 14.5 (100) NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS There are no provisions for customer/aircraft furnished equipment. NOTE 5. MODEL DESCRIPTION TAE 125-01 – Base model (also known as CENTURION 1.7) TAE 125-02-99 – Base model with increased displacement (also known as CD-135) TAE 125-02-114 – Model TAE 125-02-99 with increased power ratings (also known as CD-155) TAE 125-02-125 – Model TAE 125-02-114 with increased take off rating and lowered max continuous speed (also known as CD-170) Engine model numbers may include suffixes in parentheses to define installation specific configuration changes. Refer to SB TM TAE 000-0007 and Installation Manual. 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 a turbocharger Max manifold air temperature, deg F (C): Max manifold pressure Psi (kPa): Max turbine inlet temperature, deg F (C): Max turbocharger speed, rpm: 176 (80) 32.6 (225) (TAE 125-01 and TAE 125-02-99) 34.4 (237.5) (TAE 125-02-114) 35.9 (247.5) (TAE 12502-125) 1652 (900) (TAE 125-01) 1472 (800) (TAE 125-02-99 and TAE 125-02-114) 1562 (850) (TAE-125-02-125) 145000 (TAE 125-01 only) 175000 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS 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 & Maintenance Manual. The electronic control unit 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 TAE 125-01 engine, including the FADEC, is approved for use with the propeller MTV-6-A/187- 129, MTV-6-A/190-129 and MTV-6-A-C-F/CF187-129 models. The TAE 125-02-99 and TAE 125-02-114 engine models, including the FADEC, are approved for use with the propeller models; MTV-6-A-(1*)/(2**)-(3***)-(4****) (1*) Feather provision (Hub): - blank = no feather position possible - C - F = counterweights for pitch change forces to increase pitch and feather position possible (2**) Position of pitch change pin: - blank = pin position for pitch change forces to decrease pitch (Constant Speed) - CF (Constant Speed & Feather) pin position to allow feather, pitch change forces to increase pitch (3***) Propeller Diameter: - Propeller diameter from 175cm to 190cm (4****) Identification of blade design: - 69 - 80 - 129 The TAE 125-02-125 engine, including the FADEC, is approved for use with the propeller MTV-6-R/190-69 model. These approvals do 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 approved. (These approvals pertain to the design data only). NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS Maximum Permissible Engine Crankshaft Speed (RPM): 4220 NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS For the TAE 125-01 core engine a recommended engine life has been established. The Time Between Replacement (TBR) of the TAE 125- 01 and the Time Between Overhaul (TBO) of the TAE 125-02 models is published in Service Bulletin TM TAE 125-0001. NOTE 15. APPLICABLE MANUALS The following Engine Instructions for Continued Airworthiness (ICA’s) have been accepted by the FAA: TAE 125-01 TAE 125-02-99 & TAE 125-02-114 TAE 125-02-125 Installation Manual IM-02-01 IM-02-02 IM-02-02B Version: 1/1 Operation & Maintenance Manual OM-02-01 (US Version) OM-02-02 (US Version) OM-02-02B Version: 1/-1 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 aircraft 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 order 8130.2, Airworthiness Certificates of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. . NOTE 17. LIFE LIMITED PART INFORMATION Not Applicable 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