# TCDS E00017AT: Continental Aerospace Technologies, Inc. - Type: Type certificate data sheet - Status: Current - Holder: Continental Aerospace Technologies, Inc. - Revision: 3 - Revised: June 1, 2020 - Product: Engine - Certification basis: Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/b2/32/b232e8ad7716e9b7bec03e331e0b4bbc919b4f2e6554cde21247e7437b186ae8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9B4D54859EC2B3F5862585CA00719441.0001 - Page: https://openairdocs.org/tcds/E00017AT ## Models (2) As the data sheet lists them. - TD-300-B - TD-300-C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 Rev No. 3 3 3 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00017AT Revision 3 CONTINENTAL AEROSPACE TECHNOLOGIES, INC. TD-300-B, TD-300-C June 01, 2020 TYPE CERTIFICATE DATA SHEET NO. E00017AT Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E00017AT) 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 app licable portions of the Federal Aviation regulations provided they are installed, operate, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Continental Aerospace Technologies, Inc. (Continental®) 2039 South Broad St. Mobile, Alabama 36615 Type Certificate Holder Record Continental Motors, Inc. Company name change January 1, 2020 (Continental Aerospace Technologies, Inc.) Model TD-300-B TD-300-C Type 4HOA - - Rating, ICAO or ARDC Standard Atmosphere at Sea Level Pressure Altitude Max Continuous HP 230 - - Max Continuous RPM 2200 - - Max Continuous Critical Altitude, feet (m) 0 (0) 9,800 (2987) Max Altitude, feet (m) 12,500 (3810) 20,000 (6096) Fuel JET A-1 DEF STAN 91 -91 (NATO F-35), JET A -1 (ASTM D1655 -14) JET A (ASTM D1655 -14), Jet Fuel No. 3 per GB 6537-2006 See Note 3, Note 7, and Note 18 Use anti-icing additive for fuel temperature < 32 °F (0 °C) See Note 7 and Note 18 Pre-filter with mesh size 300 micron to be used for fuel inlet - - Lubricating Oil 100% synthetic a. Standard: ACEA E4 / API CF / MIL L 2104E b. Viscosity: 10W-40 (See Note 3 and Note 7) - - Bore and Stroke, in. (mm) 4.961 (126) x 3.937 (100) - - Displacement, in3 (cm3) 304.36 (4987.6) - - Compression ratio 17:1 - - Weight (dry) pounds (kg), 426.4 (193.4) Refer to Installation Manual, OI-30, for definition of engine dry weight 440.1 (199.6) Refer to Installation Manual, OI-30, for definition of engine dry weight E00017AT Page 2 of 4 Certification basis TD-300-B – 14 CFR 33 through Amendment 30 effective November 2, 2009 TD-300-C – 14 CFR 33 through Amendment 33 effective September 20, 2012 Production Basis None, before original airworthiness certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data, and a check of the flight characteristics. In the event of an app lication for a standard airworthiness certificate or, if an applicant intends to produce a new aircraft under 14 CFR § 21.183(d), and the applicant is manufacturing, building, or assembling to another person’s type certificate, the applicant must provide written evidence of permission from the type certificate holder. Conduct of such activity without written evidence of permission may be a violation of 49 U.S.C. § 44704 a)(3). Note 1. Engine ratings are based on a calibrated test stand with sea level stati c standard day inlet conditions (29.92 inHg, 59 °F, and no water vapor), all accessory drives unloaded (no external power extraction), and fuel with a minimum cetane number of 36 per ASTM D613. Note 2. Maximum permissible temperatures Maximum cylinder head temperature 420°F (216°C) Maximum turbine inlet temperature 1346°F (730°C) (-B); 1400°F (760°C) (-C) Maximum oil temperature 248°F (120°C) (-B); 240°F (115.6°C) (-C) Maximum intake air temperature (at intake manifold inlet) 150°F (65.6°C) Maximum fuel temperature (at low pressure pump inlet) 149°F (65°C) Minimum permissible temperatures Minimum oil temperature for power up/maximum power 150°F (65.6°C) Minimum oil temperature for starting 20°F (-7°C) (see Note 17) Minimum fuel temperature without use of anti-ice additive 32°F (0°C) (see Note 7) Oil Sump Capacity, Qts.(L) total 6.86 (6.5) Usable: 20° Nose Up 3.43 (3.25) Usable: 12° Nose Down 3.43 (3.25) - - - - - - Model TD-300-B TD-300-C Principal Dimensions Length, in (mm) Width, in (mm) Height, in (mm) 32.3 (820) 36.6 (930) 30.9 (785) - - - - 37.58 Center of Gravity (Basic Engine) Aft of propeller flange, in (mm) Beside crankshaft centerline toward the 3-4 side Below Crankshaft Centerline, in (mm) 15.5 (393.7) 0.2 (5.08) 2.0 (50.8) 14.42 (366.2) 0.14 (3.55) 2.50 (63.5) Propeller Shaft AS127D (SAE 6) with five long bushings engaging the propeller and one short bushing in line with the right front cylinder when the #1 piston is at TDC. - - Fuel Injection In-line high pressure pump -line- nozzle system ( Continental PN 969038) Injection Timing BTDC 20.5° ± 0.5° as defined in the Maintenance Manual (M-30) - - Control System Single channel electronic engine control system with manual backup. The S/W of the engine control system has been developed and tested per DO178B, Level C. - - Applicable Notes 1 through 19, 21 1 through 21 “- -“ indicates "same as previous model" "—" indicates "does not apply" Page 3 of 4 E00017AT Note 3. Fuel Pressure Limits Minimum absolute pressure (at low pressure pump inlet) 8.7 psia (60 kPa) Oil Pressure (gauge pressure) Limits Maximum, cold engine 174 psig (1200 kPa) Nominal 46.4 to 80 psig (320 to 552 kPa) Minimum at idle 14.5 psig (100 kPa) Note 4. The following accessory drive or mounting provisions are available for the TD-300 series engines. Accessory-Drive Direction of Rotation* Drive Ratio to Crankshaft (RPM) ** Maximum Torque In. lb. (Nm) or Power Max Overhang Moment In. Lbs (Nm) Drive Propeller Governor CCW 1.231:1 212 (24) 26 (3) AND 20010 AND20000 Accessories CW 1.177:1 93 (10.5) 26 (3) AND 20000 Alternator CCW *** 4 kW 48.75 (5.5) Belt ISO 9982 A/C compressor or 2nd Alternator CCW *** 4 kW 79.8 (9) Belt ISO 9982 * CCW = counterclockwise, CW = Clockwise. The rotation direction of the power drives for the accessories is indicated looking at the drive from the outside or from the front of the engine for accessories driven from the front pulley of the engine. ** The speed of rotation for the accessory power drives is indicated for a reference engine speed of 2200 rpm. *** Driving pulley speed. Accessory rotation speed dependent on accessory pulley ratio. Note 5. The TD-300-C is similar to the TD -300-B except for the turbocharger and turbocharge r subsystem. The turbocharger subsystem was replaced to provide higher critical altitude and ceiling. Note 6. Turbocharger Speed Limits TD-300-B 146,000 rpm TD-300-C 136,000 rpm Note 7. Approved oil specifications are listed in the Installation & Operation Manual (OI-30) Approved fuel additives:  MIL-DTL-85470 (DiEGME), Type: Anti-Ice Additive, in a concentration of 0.1 to 0.15 percent by volume.  T1301 (SH0396-92), Type: Anti-Ice Additive, in a concentration of 0.1 to 0.15 percent by volume.  Prist Hi -Flash (MIL -DTL-85470; ASTM D4171) , Type : Anti -Ice Additive, in a concentration of 0.1 to 0.15 percent by volume. Note 8. The engine is approved for installation in Normal and U tility aircraft categories only where the engine is in the hor izontal tractor configuration Note 9. The list of propellers that are approved for use with the engine are published in the Installation & Operation Manual (OI-30) Note 10. Engine models are only available as 24 Volt systems Note 11. The electronic control system for the TD-300 series contains level “C” software which has been shown to meet the re quirements for single and multi-engine aircraft of less than 6,000 lbs. maximum takeoff weight. The following electronic control unit has been approved for use with the corresponding engines (Continental part numbers below): Engine Model ECU ECU software OTP Control Cartography TD-300-B 995001 965016 995134 995135 TD-300-C 995001 965016 995134 995136 Note 12. The electronic control unit must not be installed in a dedicated fire zone Note 13. Installation and evaluation of fault lamps is subject to the requirements established by the certification basis of the aircraft Note 14. 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. Takeoff is prohibited in mechanical back-up mode. Takeoff is prohibited with annunciated faults showing on the fault lamps. Note 15. Engine model numbers may include a suffix to define minor specification changes and/or accessory packages. Example: TD-300- B (10). E00017AT Page 4 of 4 Note 16. See Installation & Operation Manual (OI-30) for maximum manifold air pressure relative to atmospheric conditions. Note 17. The operating envelope is provided in the Installation & Operation Manual (OI-30) Note 18. Fuel cetane number of 36 per ASTM D613 has been demonstrated Note 19. See Maintenance Manual (M-30) for Airworthiness Limitations / Life Limited Component(s) Note 20. Alternative marketing / sales name for the TD-300-C is CD-230 Note 21. Instructions for Continued Airworthiness (ICA) are incomplete. The aircraft with the engine installed is eligible for delivery when the ICAs are complete and accepted. .…END…. ``` ## ADs None name its models. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.