# TCDS E6SO: Continental Aerospace Technologies, Inc. - Type: Type certificate data sheet - Status: Current - Holder: Continental Aerospace Technologies, Inc. - Revision: 2 - Revised: June 1, 2020 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/45/21/45218aad7df7dc44aee551b08e83e1bd856bbfbc278028f2289dbd429ed56d71 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/6CFCE05AD6F5E5B7862585CA0071981F.0001 - Page: https://openairdocs.org/tcds/E6SO ## Models (1) As the data sheet lists them. - TP500E ## 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 Rev. No. 2- -2 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E6SO Revision 2 CONTINENTAL AEROSPACE TECHNOLOGIES, INC. TP500E June 01, 2020 TYPE CERTIFICATE DATA SHEET NO. E6SO Engines of models described herein conforming with this data sheet (which is part of type certificate No. E6SO) 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 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.) Teledyne Continental Motors Ownership & name change as of April 19, 2011 (Continental Motors, Inc.) Model TP500E Type Single-shaft turboprop with single stage centrifugal compressor, single reverse flow annual combustion chamber and two stage axial turbine. Prop Drive Ratio 24.8262:1 (cw, alf) Ratings (see note 3) Maximum continuous Shaft hp 425 Equivalent shaft hp 447 Prop drive rpm 2014 Takeoff (2 minutes) Shaft h.p. 425 Equivalent shaft hp 447 Prop drive rpm 2014 Thermodynamic Shaft h.p. 480 Equivalent shaft h.p. 500 Prop drive rpm 2014 Production basis None. The manufacturer does not hold a production certificate for the production of engines under this certificate and, therefore, each engine so produced is subject to an inspection for workmanship and conformity with the approved data by a Federal Aviation Administration representative. In addition, the engine must demonstrate rated power, for given ambient conditions, during sea level dynamometer testing. Upon satisfactory completion of the above, the FAA representative will tag the engine with tag form 8130-3. Note 1. Temperature limits Maximum rated turbine inlet temperature 1960F (thermodynamic) Measured gas temperatures (exhaust minus inlet air) Takeoff 1081F Maximum continuous 1036F E6SO 2 Start transient 1200F Oil inlet temperature -20 to 175F Fuel inlet temperature 32 to 130F Note 1. Component temperatures Fuel control (HPMU) -66F to 250F DC/SV -65F to 293F EECU -71F to 160F Note 2. Pressure Limits Fuel, at control inlet 7 psig minimum 32 psig maximum Oil, operating 55 psig minimum 75 psig maximum Prop Drive Flanged, 8 holes 0.594  0.005” dia. on 4.250” B.C. per ARP 880A Fuel Control Lucas pgc400 series Hydromechanical pump and metering unit Lucas Sta900 series Electronic engine control unit Lucas DC/SV 100 series distribution control and shutoff valve Fuel ASTM D1655, Type Jet A or A-1 Oil MIL-L-23699 conforming to TCMContinental Spec. MHS-460 Principal Dimensions Length, in. 52.18 Width, in. 23.31 Height, in. 21.30 Weight (dry), lb. 336 (includes basic engine and engine mounted fuel control system, but excludes electronic engine control unit and ignition exciter) C. G. location (dry weight) (tailpipe end looking forward to prop flange) aft of propeller flange, in. 24.63 right of engine centerline, in. 0.12 below engine centerline, in. 0.14 Ignition system Dual spark plug system, Champion CH34055 plug, Bendix 10-381550-1 Exciter Type TGLN-28 Certification basis CFR Part Part 33 effective February 1, 1965, and Amendments 33-1 to 33-11 inclusive, type certificate no. E6SO issued October 18, 1988. Note 3. Engine ratings are based upon U.S. standard atmosphere, sea level static conditions. Engine inlet air (dry) 59F, 29.92 in. hg. No bleed air extraction no external accessory loads, no inlet duct losses, and utilizing the exhaust configuration defined by TCM Continental Drawing TP100818. Note 4. Equivalent shaft horsepower (ESHP) for static conditions is based on: ESHP = Net Thrust, Lbs. + SHP 2.5 3 E6SO Note 5. Accessory provisions RPM at Maximum 100% Overhang (1) Direction Engine Maximum Torque Moment Accessory Rotation Speed (in-lb) (in-lb) Continuous Static Fuel control drive CW 5984 (2) 800 65.4 Tachometer CCW 4107 (3) 100 1.25 (and 20005 modified) Propeller governor (and 20010 modified) CW 4107 (4) 850 11 Starter/generator (MS3326-6 modified) CW 11636 43.25 1400 86.8 Accessory (and 20000 modified) CW 3611 100 800 17.6 (1) Direction of rotation viewing pad, cw-clockwise, ccw-counter-clockwise. (2) Continuous torque associated with lucas pgc400 series fuel control. (3) Continuous torque associated with Globe Industries P/N 25140-22A703 tach generator. (4) Continuous torque associated with Hartzell Model T-1 propeller governor. (5) No power extraction allowed. (6) Aircraft services air extraction may not exceed 5% of engine mass flow. (7) Provision for fuel venting emission control is not included on this engine and, therefore, airframe compliance must be provided in accordance with sfar-27. (8) These engines have not been tested to evaluate the effect of bird, ice ball, and foreign object ingestion, and are, therefore, limited to protective inlet installations. the bird, ice ball, and foreign object ingestion characteristics of the protective airframe inlet and engine combination must be evaluated by the FAA prior to approval of the engine installation. (9) These engines meet FAA requirements for operation in icing conditions; however, icing characteristics of the airframe inlet system and the engine combination must be evaluated by the FAA prior to installation approval. (10) Installation of the TP500E engine in a certificated aircraft is not authorized until the required maintenance and overhaul manuals become available. (11) Certain engine parts are life limited. these limits are listed in FAA approved service bulletin number 500E-72-88-A. ...END... ``` ## ADs (1, in force first) - [AD 2012-03-06](https://openairdocs.org/ad/2012-03-06): Fuel servo diaphragm · Continental Motors 6-260-A, 6-285-A, 6-285-B and 482 more. Effective Feb 24, 2012 ## Registered aircraft by registry model (OpenAirDocs) - [Continental TP500](https://openairdocs.org/engine/continental-tp500-series): 1 aircraft (registry code 17050) - [Continental TP500E](https://openairdocs.org/engine/continental-tp500e): 0 aircraft (registry code 17165) --- 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.