TCDS E00092EN

* PAGE 1 2 3 4 5 6 REV. 1 1 1 1 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 E00092EN TCDS NUMBER E00092EN REVISION: REVISION 1 DATE: April 6, 2023 Raikhlin aircraft Engine Developments, GmbH MODELS: RED A03-003 RED A03-102 RED A03-005 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00092EN) 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 Raikhlin aircraft Engine Developments, GmbH Am alten Wehr 23 D-53518 Adenau Germany MODELS RED A03-003 RED A03-102 RED A03-005 TYPE (See NOTE 5) The RED A03 engine is a 12 cylinder (V-configuration), four stroke Diesel reciprocating engine with a displacement of 6134 cm3, equipped with common rail high pressure direct injection, turbocharger, and gearbox with a ratio of 1:1.88. The engine is equipped with a single lever controlled Full Authority Digital Engine Control (FADEC) and Electronic Engine Control System (EECS).. RATINGS Takeoff power (5 min.) : Max. continuous power : (sea level pressure altitude) Maximum Best Economy Cruising 368 kW/500 HP at 4000 rpm (2127 prop RPM) 338 kW/460 HP at 3750 rpm (1995 prop RPM) - - 294 kW/400 hp at 3500 rpm (1862 prop RPM) - - - - - - 405 kW/550 hp at 4000 rpm (2127 prop rpm - - - - FUEL (See Note 11) Def Stan 91-91, ASTM D1655 (Jet A, Jet A-1) OIL Castrol Edge FST, 10W/60 CAPACITY N/A – engine utilizes a dry sump system. Total oil capacity is 18.5 liters (19.5 quarts). Difference between minimum and maximum oil levels is 1.2 liters(1.3 quarts). WEIGHT (See Note 11) 363kg (800.3 lbs) 357kg (787 lbs) 363kg (800.3 lbs) DISPLACEMENT 6,134 cm3 (374.3 in3) BORE 86.00 mm (3.386 in) STROKE 88.00 mm (3.465 in) COMPRESSION RATIO 16:1 PROPELLER ROTATION CCW (viewed in flight direction assuming tractor configuration) CONTROL SYSTEM See NOTE 11 FADEC/EECS is controlled by the Engine Electronic Control Unit (EECU) and the software is verified to RTCA Dcoument DO-178B Level B. EECU: P/N A03-111-06-001-01 or later approved standard. Hardware/software: TEM_RED_ECU_ECU-1.0.3 or later approved standard TCDS E00092EN PAGE 2 CERTIFICATION BASIS 14 CFR, part 33 effective February 1, 1965, and Amendments 33-1 through Amendment 33-33. DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED RED A03-003 January 8, 2015 October 24,2016 RED-A03-102 December 19, 2022 April 6, 2023 RED A03-005 December 19, 2022 April 6, 2023 NOTES NOTE 1 ENGINE RATINGS The performance values specified above correspond to minimum values defined under the conditions of ICAO or ARDC standard atmosphere. NOTE 2 TEMPERATURE LIMITS MODELS RED A03-003 / RED A03-102 RED A03-005 Temperature in °C/ °F Minimum engine structure and internal engine fluids temperature for starting -20 / -4 Oil temperature measured at entry into engine Minimum engine oil temperature for takeoff 60 / 140) Engine oil temperature range (normal operation) (measured at engine entry) 60-100 / 140 – 212 60-102 / 140 – 216 Maximum engine oil temperature (10 min.) 108 / 226 116/241 Cooling fluid and gearbox oil temperatures measured at exit from engine or gearbox prior to cooling Minimum cooling fluid temperature for takeoff 60 / 140 Cooling fluid temperature range (normal operation) 60-91 / 140-195 Maximum cooling fluid temperature (10 min.) 105 / 221 Minimum gearbox oil temperature for takeoff 50 / 122 Gearbox oil temperature (normal operation) 50-95 / 122-203 Maximum gearbox oil temperature (10 min.) 100 / 212 109/228 Minimum exhaust gas temperature 250 / 482 Exhaust gas temperature (normal operation) 500 – 830 / 932 – 1526 Maximum exhaust gas temperature 850 / 1562 Maximum exhaust gas temperature transient limit 900 / 1652 (maximum 5 minutes) NOTE 3 FUEL AND OIL PRESSURE LIMITS Minimum fuel pressure (at inlet of HP engine pump) 5.0 bar absolute (72.5 psia) Maximum fuel pressure (at inlet of HP engine pump) 7.0 bar absolute (101.5 psia) Minimum oil pressure at idle conditions 2.4 bar absolute (34.8 psia) Minimum oil pressure at maximum continuous power 4.3 bar absolute (62.4 psia) Maximum oil pressure 7.0 bar absolute (101.5 psia) TCDS E00092EN PAGE 3 NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS AIRCRAFT ACCESSORY DRIVES Rotation* Max. speed** Max. torque Max. power Type of drive Accessory Drive A (in type certificate configuration used by governor) CW 2736 RPM 1.7 N*m / 15.1 in*lb 0.5 kW / 0.67 hp AND 20010 Accessory Drive B CW 3706 RPM 9.1 N*m / 80.5 in*lb 3.5 kW / 4.69 hp AND 20000 Accessory Drive C CW 4000 RPM 30.2 N*m / 267.3 in*lb 6.9 kW / 9.25 hp for V-belt Accessory Drive D (Not available on RED A03-102) CW 6182 RPM 19.5 N*m / 172.6 in *lb 6.9 kW / 9.25 hp for V-belt *Accessory drive rotation direction as viewed when facing the drive. ** Speed is indicated for an engine crankshaft reference speed of 4000 RPM. NOTE 5. MODEL DESCRIPTION: RED A03-003 Initially certified under the designation “RED A03”is approved for the installation in Part 23 normal and utility category airplanes. RED A03-102 Approved for the installation in Part 23 normal, utility & aerobatic category airplanes. RED A03-005 Approved for the installation in Part 23 normal and utility category airplanes 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 Installation and Maintenance Manuals NOTE 10 POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS AS APPLICABLE The engine is equipped wih a common rail high pressure direct injection and turbocharger.. TCDS E00092EN PAGE 4 NOTE 11 SPECIAL INSTALLATION REQUIREMENTS Suffixes in parenthesis may be added to the engine model number to define minor engine changes related to installation specific configurations. These differences are specified in applicable service bulletins. The software of the electronic engine control for each application has specific software application data. Refer to the applicable service bulletins associated with different installations and the Engine Installation Manual for more information. Fuel Type The RED A03 series engines are approved for operation with kerosene type fuels according to ASTM D1655, Def Stan 91-91 and GOST 10227 (see Engine Operation Manual). The engine has been tested for fuels up to a maximum ignition delay time of 8.06 ms / minimum derived cetane number of 27.9 (determined according to EN 15195/ASTM D6890. Refer to Engine Operation Manual for more details. Principle Dimensions MODELS RED A03-003 RED A03-102 RED A03-005 Overall Length 1114mm / 443.9 Overall Height 750mm /29.5 inches 712mm/28 inches 750mm/29.5 inches Width 850mm / 33.5 inches Center of Gravity Refer to Engine Installation Manual. Engine weight The engine dry weight includes the engine loom with brackets, electrical engine starter, oil-coolant heat exchanger, integrated oil tank, exhaust systems with turbochargers and wastegates, oil pumps and water pumps. It does not include the propeller, governor, water coolers, coolant piping, charge coolers, oil catch tanks, exhaust gas tailpipes, electronic engine control unit and glow plug unit, adapter loom, alternators, belt drives, and engine fluids. Electronic Engine Control Unit (EECU) The EECU must not be installed in a dedicated fire zone. The installation conditions are found in the Engine Installation Manual. The EECU must have a backup power source which is independent and isolated from the primary power supply when installed on an aircraft. EMI/Lightning: The FADEC and EECS have been tested according to RTCA Document DO-160G for lightning protection and magnetic interference. The demonstrated levels are provided in the Engine Installation Manual. Dispatch Limitations: No Time Limited Dispatch has been approved. 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. Refer to the Engine Operation Manual for special instructions. Propellers: The RED A03 engine is approved for use with propellers and propeller governors as listed in the Engine Installation Manual. The propellers and propeller governors are not part of the engine type design. The engine propeller feathering and reversing functions are not part of the engine type design. Propeller feathering and reversing installation and operation procedures must be implemented and certified by the aircraft manufacturer without violating the general engine instructions which are described in the Engine Installation Manual and the Engine Operation Manual. TCDS E00092EN PAGE 5 NOTE 12 MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS 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, • Vendor manuals, • Installation and Operation manuals, and • Airworthiness Limitations Section. These approvals pertain to the type design only. NOTE 13 SPECIAL OPERATING PROCEDURES OR LIMITATIONS Speeds Maximum engine overspeed (crankshaft) 4200 RPM (2234 prop RPM) Takeoff speed 4000 RPM (2127 prop RPM) Maximum continuous speed 3750 RPM (1995 prop RPM) Maximum turbocharger speed 135,000 RPM Containment has been demonstrated for maximum turbocharger speed of 140,000 RPM Maximum altitude 7620 m (25,000 ft) The RED A03-102 engine may be used under sustained negative g or inverted flight conditions for continuous periods not exceeding 20 seconds. NOTE 14 SPECIAL REPAIR OR OVERHAUL LIMITATIONS The recommended Time Between Overhaul is published in the Engine Maintenance Manual. NOTE 15 APPLICABLE MANUALS Manuals required by 14 CFR 33.4: Manuals RED A03-003 RED A03-102 RED A-3-005 Maintenance Manual A03-180-03-001-01 A03-180-03-003-01 A03-180-03-005-01 Overhaul Manual Not yet issued Not yet issued Not yet issued The Airworthiness Limitations Section is FAA approved. Instructions for continued airworthiness are incomplete. 14 CFR 21.50(b) requires the holder of this type certificate to ensure these instructions are complete and furnished prior to when the aircraft incorporating these engines are issued standard airworthiness certificates or delivered/returned to service, whichever occurs later. Manuals required by 14 CFR 33.5: Manuals RED A03-003 RED A03-102 RED A-3-005 Installetion Manual A03-180-01-001-01 A03-180-01-005-01 A03-180-01-005-01 Operation Manual A03-180-02-001-01 A03-180-02-005-01 A03-180-02-005-01 TCDS E00092EN PAGE 6 NOTE 16 IMPORT REQUIREMENTS STATEMENT FOR FOREIGN MANUFACTURED ENGINES 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 Certification 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) Not applicable NOTE 20 CENTER OF GRAVITY TABULATION (IF NOT SHOWN IN BODY OF TCDS) Reference the Installation Manual, latest revision NOTE 21 VIBRATION DAMPER PROVISION LIMITATIONS Not applicable ---END---