TCDS E00067EN

PAGE 1 2 3 4 5 1 REV. 8 8 8 8 8 9 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" “---” INDICATES “DOES NOT APPLY” NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NUMBER : E00067EN E00067EN REVISION: 9 SMA Aero Engines GmbH MODELS: SR305-230 SR305-230E June 25, 2021 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00067EN) 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 SMA Aero Engines GmbH Flugplatz 63329 Egelsbach, Germany TYPE CERTIFICATE (TC) RECORD Safran Aircraft Engines transferred TC E00067EN to SMA Aero Engines GmbH on June 25, 2021 Société de Motorisations Aéronautiques (SMA) transferred TC E00067EN to Safran Aircraft Engines on February 15, 2019 I. MODELS SR305-230 SR305-230E TYPE The SR305-230 and SR305-230E are 4 stroke diesel cycle piston engines (4988 cm3) air cooled with a secondary oil cooling system. Engines are equipped with a direct injection system and are turbocharged with air/air intercooling. The engines are direct drive with flat four cylinders, horizontally opposed RATINGS (U.S Standard Atmosphere at Sea Level Pressure Altitude) Takeoff, HP(KW)) Maximum duration Max Continuous, HP(KW) Maximum duration 226.6 (169) at 2200 rpm 5 minutes 226.6 (169) at 2200 rpm unlimited 226.6 (169) at 2200 rpm 5 minutes 226.6 (169) at 2200 rpm unlimited FUEL (See NOTE 4 and NOTE 13) JET-A1 (F-35) JET-A1 (ASTM D1655) JET-A (ASTM D1655) TS-1 (GOST 10227) Use of anti-icing additive for fuel temperature <0 degrees Celsius JET-A1 (F-35) JET-A1 (ASTM D1655) JET-A (ASTM D1655) TS-1 (GOST 10227) JP8 (MIL-DTL-83133) JET-A1 (GOST R 52050-2006) No. 3 Jet Fuel (GB 6537-2006) Use of anti-icing additive for fuel temperature <0 degrees Celsius OIL (See NOTE 4 and NOTE 12) 1. Type: 100% synthetic a. Standard: ACEA E4 / API CF / MIL L 2104E b. Viscosity: 10W40 2. Oil sump capacity, Gallon (liters) Total capacity: 1.72 (6.5, 6.72 including filter) 1. Type: 100% synthetic a. Standard: ACEA E4 / API CF / MIL L 2104E b. Viscosity: 10W40 2. Oil sump capacity, Gallon (liters) Total capacity: 2.11 (8, 8.16 including filter) TCDS E00067EN PAGE 2 of 5 I. MODELS (cont.) SR305-230 SR305-230E PRINCIPAL DIMENSIONS Length, in (mm) Width, in (mm) Height, in (mm) 32.8 (834) 36.6 (930) 29.5 (750)) 32.8 (834) 36.7 (931) 30.9 (784) CENTER OF GRAVITY Refer to applicable Engine Installation Manual. WEIGHT (dry) pounds (kg), 430 (195), Refer to applicable Engine Installation Manual for definition of engine dry weight 456 (207), Refer to applicable Engine Installation Manual for definition of engine dry weight CONTROL SYSTEM Single channel electronic engine control system with mechanical backup. The S/W of the engine control system has been developed and tested iaw DO178B, Level C. SR305-230 SR305-230E CERTIFICATION BASIS Model Effective Date of TC Application Type Certificate Number Issue Date Date Model Added to TC FAR 21.29 and FAR 33, effective February 1, 1965, and Amendments 33-1 through Amendment 33-18 SR305-230 September 13, 1999 E00067EN July 8, 2002 July 8, 2002 Direction Generale de l’Aviation Civile (DGAC) originally type certificated this engine under its type certificate Number M23 The FAA validated this product under U.S. Type Certificate Number E00067EN. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. The EASA Type Certificate number is E.076. FAR 21.29 and FAR 33, effective February 1, 1965, and Amendments 33-1 through Amendment 33-30 SR305-230E May 21, 2010 E00067EN July 8, 2002 March 31, 2011 European Aviation Safety Agency (EASA) originally type certificated this engine under its type certificate Number E.076 The FAA validated this product under U.S. Type Certificate Number E00067EN. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with DGAC or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00067EN, is in a condition for safe operation and has undergone a final operational check. TCDS E00067EN PAGE 3 of 5 NOTES SR305-230 SR305-230E NOTE 1. Rotation Speed Limits: Engine maximum speeds, rpm Steady State: Transient (3 seconds): Turbocharger maximum speed rpm: 2200 2350 146,000 2200 2350 135,000 NOTE 2. Temperature limits: 1. Maximum cylinder head temperature, deg F (C) : 392 (200) oC 2. Maximum intake air temperature (at intake manifold inlet) deg F(C): 149 (65) 3. Maximum exhaust gas temperature, deg F(C): 1346 (730) 4. Maximum oil temperature deg F (C): 248(120) 5. Minimum oil temperature for power up, deg F (C) : 149 (65) 6. Minimum oil temperature for starting, deg F (C): -4 (-20) 7. Maximum fuel temperature (at low pressure pump inlet), deg F(C): 149 (65) 8. Minimum fuel temperature without use of anti-ice additive, degs F(C): 32 (0). (see Note 13) 1. Maximum cylinder head temperature, deg F (C) : 392 (200) oC 2. Maximum intake air temperature (at intake manifold inlet) deg F(C): 149 (65) 3. Maximum exhaust gas temperature, deg F(C): 1454 (790) 4. Maximum oil temperature deg F (C): 248(120) 5. Minimum oil temperature for power up, deg F (C) : 149 (65) 6. Minimum oil temperature for starting, deg F (C): -4 (-20) 7. Maximum fuel temperature (at low pressure pump inlet), deg F(C): 149 (65) 8. Minimum fuel temperature without use of anti-ice additive, degs F(C): 32 (0). (see Note 13) NOTE 3. Altitude (Standard Atmospheres) Maximum altitude, ft (m): 12,500 (3810) Maximum altitude, ft (m): 20,000 (6100) NOTE 4. Fuel and Oil Pressure Limits, PSI (kPa) 1. Fuel: minimum absolute pressure (at low pressure pump inlet): 8.7 (60) 2. Oil (relative pressure):  Maximum, cold engine: 174 (1200)  Nominal: 46.4 to 90 (320 to 620)  Minimum at idle: 14.5 (100) 1. Fuel: minimum absolute pressure (at low pressure pump inlet): 8.7 (60) 2. Oil (relative pressure):  Maximum, cold engine: 174 (1200)  Nominal: 60.9 to 94.4 (420 to 650)  Minimum at idle: 14.5 (100) NOTE 5. Not Used NOTE 6. Induction System (absolute pressure), PSI (kPa), at U.S Standard Atmosphere at Sea Level Pressure Altitude Minimum in normal mode and maximum in mechanical backup mode 39.3 (271) Refer to the applicable Engine Operating Manual for other operating conditions Minimum in normal mode and maximum in mechanical backup mode 41.7 (288) Refer to the applicable Engine Operating Manual for other operating conditions NOTE 7. Aircraft Accessory Drive SR305-230 and SR305-230E Accessory-Drive Direction of Rotation (See Note 7a) Rotation Speed (Rpm) (See Note 7b) Maximum Torque In. lb. (Nm) Drive Propeller Governor CCW 2708 212 (24) AND 20010 Air Pump – SR305-230 CW 2589 93 (10.5) AND 20000 Air Pump – SR305-230E CW 3492 81 (9.2) AND 20000 Alternator CCW 2200 (see Note 7c) N/A Belt ISO 9982 A/C compressor or 2nd Alternator CCW 2200 (see Note 7c) N/A Belt ISO 9982 Note 7a: CCW = counterclockwise. The rotation direction of the power drives for the accessories is indicated considering the power drive seen from the outside or from the front of the engine for accessories driven from the front pulley of the engine. Note 7b: The speed of rotation for the accessory power drives is indicated for a reference engine speed of 2200 rpm. Note 7c: Driving pulley speed. Accessory rotation speed depending on accessory pulleys ratio. TCDS E00067EN PAGE 4 of 5 NOTE 8. Oil Systems: Refer to the applicable Engine Installation Manual. NOTE 9. Installation Assumptions: See applicable Engine Installation Manual. NOTE 10. Electrical Equipment: Refer to applicable Engine Installation Manual. NOTE 11. Time Limited Dispatch: The engines are not approved for Time Limited Dispatch. NOTE 12. Approved Oils: Refer to the applicable Engine Operating Manual or Engine Maintenance Manual NOTE 13. Approved fuel additives: Refer to the applicable Engine Operating Manual or Engine Maintenance Manual NOTE 14. The FAA and EASA approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness is published in the applicable Engine Maintenance Manual, Chapter 5, Airworthiness Limitations. NOTE 15. SR305-230 & SR305-230-1 (See NOTE 21) Manuals required by FAR 33.4 and 33.5: Engine Installation Manual: TP230-EIM (DJC 01-01) Engine Operating Manual: TP230-OM (DJC 01-02) Engine Maintenance Manual:TP230-EMM (DJC 01- 03) Engine Overhaul Manual: TP230-EOM (DJC 01-04) Engine Illustrated Parts Catalog: TP230-EIPC Service bulletins Each of the documents listed above must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the DGAC. Any such documents are accepted by the FAA and are considered FAA approved. SR305-230E Configuration MA01 and MA02 (See NOTE 21) Manuals required by FAR 33.4 and 33.5: Engine Installation Manual: TP230E-EIM (NT-CE 01-01) Engine Operating Manual: TP230E-OM (NT-CE 01-02) Engine Maintenance Manual:TP230E-EMM (NT-CE 01-03) Engine Overhaul Manual: TP230E-EOM (NT-CE 01-04) Engine Illustrated Parts Catalog: TP230E-EIPC (NT-CE 01-05) Service bulletins Each of the documents listed above must state that it is approved by the European Aviation Safety Agency (EASA). Any such documents are accepted by the FAA and are considered FAA approved. SR305-230E Configuration C1 (See NOTE 21) Manuals required by FAR 33.4 and 33.5: Engine Installation Manual: TP230E—C1-EIM Engine Operating Manual: TP230E-C1-OM Engine Maintenance Manual:TP230E- C1-EMM Engine Overhaul Manual: TP230E-EOM (NT-CE 01-04) Engine Illustrated Parts Catalog: TP230E- C1-EIPC Service bulletins Each of the documents listed above must state that it is approved by the European Aviation Safety Agency (EASA). Any such documents are accepted by the FAA and are considered FAA approved. TCDS E00067EN PAGE 5 of 5 NOTE 15 (Cont). SR305-230E Configuration MA03 (See NOTE 21) Engine Installation Manual: TP230E-MA03-EIM (NT-CE 01-01) Engine Operating Manual: TP230E-MA03-OM (NT-CE 01-02) Engine Maintenance Manual: TP230E-EMM (NT-CE 01-03) Engine Overhaul Manual: TP230E-EOM (NT-CE 01-04) Engine Illustrated Parts Catalog: TP230-EIPC (NT-CE 01-05) Each of the documents listed above must state that it is approved by the European Aviation Safety Agency (EASA). Any such documents are accepted by the FAA and are considered FAA approved. NOTE 16. Removed at Revision: 6 NOTE 17. The engine is approved for installation in Normal and Utility aircraft categories only. NOTE 18. The electronic control unit must not be installed in a dedicated fire zone. The installation conditions are defined in the applicable Engine Installation Manual. NOTE 19. The software of the ECU has been validated according to DO 178 B, level C. NOTE 20. The operating/starting envelope is provided in the applicable Engine Installation Manual. NOTE 21. A suffix may be added to the SR305-230 basic engine model number on the engine nameplate to identify minor variations in the engine configuration, installation components, or differences peculiar to aircraft requirements as follows: 1. SR305-230-1 – Same as the SR305-230 except the SR305-230-1 incorporate modifications that increase the EMI/lightning protection levels. (See note 22 for levels). The -1 suffix may also be added to existing engines by incorporation of SMA SB SB-01-76-002. The -1 configuration level is required for U.S. Installations. 2. SR305-230E has the same level of EMI/lightning protection as the SR305-230-1 3. A Configuration may be added to the SR305-230E data plate with C1 appearing in the “Configuration” data field to identify a modified starter gear to the Cessna C182 aircraft. 4. A Configuration may be added to the SR305-230E data plate with –MA01, -MA02 or –MA03 to identify a certificated baseline with minor engine variations in relation to the aircraft application. NOTE 22. EMI/Lightning: The protection of the engine electronic control system against lightning and electromagnetic interference has been tested in accordance with DO 160D. The levels of protection are defined in the applicable Engine Installation Manual. NOTE 23. The SR305-230 engine model was initially certified with a 2 blade constant speed propeller of 3.5 kg-m2 moment of inertia and 35 kg weight. The list of propellers that are approved for use with the engine is published in the applicable Engine Installation Manual. ---END---