TCDS E8EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. E8EA Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E8EA) and other approved data on file with the Federal Aviation Administration meet the minimum standard 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: Ozark Aeroworks, LLC 3300 S. Golden Ave. (S. Farm Rd. 135) Springfield, Missouri 65807 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. Transferred TC E8EA to Ozark Aeroworks, LLC on May 06, 2022 AlliedSignal Transferred TC E8EA to Honeywell International Inc. December 14, 1999 Textron Lycoming Transferred TC E8EA to AlliedSignal on January 31, 1995 TYPE AXIAL - centrifugal flow, free turbine turboprop. Five stage axial and single stage centrifugal compressor. External annular vaporizing combustion chamber. Single stage gas producer turbine. Single stage power turbine. RATING At nominal output shaft speed of 1710 rpm Maximum continuous at sea level, hp. 1000 Takeoff (5 min.) at sea level, hp. 1100 FUEL CONTROL Chandler Evans Model TA-2F with integral dual element pump FUEL (see Note 10) OIL Synthetic type conforming to MIL-L-7808 PRINCIPAL DIMENSIONS Length, in. 58.62 Nominal diameter, in. 23.70 Maximum radius, in. 13.31 WEIGHT (dry), lb. 560 (includes essential engine accessories but excludes starter, two tachometer generators, oil tank and oil cooler) C.G. LOCATION (dry weight) Aft of front mount pad centerline in. 11.50 Below engine horizontal centerline in. .................................................................... 71 IGNITION SYSTEM (28 volts D.C.) Scintilla type TGLN 1112 with spark splitter coil and two shunted surface gap igniter plugs IGNITER PLUGS AC 5610719 NOTES 1,2,3,4,5,6,7,8,9,10 E8EA Revision: 6 OZARK AEROWORKS, LLC T5307A MAY 06, 2022 Model T5307A E8EA 2 CERTIFICATION BASIS CAR 13, effective June 15, 1956, as amended by 13-1, 13-2, and 13-3. Type Certificate Model Date of Application Type Certificate Issued T5307A September 26, 1 963 July 17, 1964 PRODUCTION BASIS NONE NOTE 1. Maximum permissible gas producer speeds are: 25,200 rpm - takeof f 24,700 rpm - maximum continuous NOTE 2. Maximum permissible temperatures: Maximum permissible exhaust gas temperature varies with ambient temperature as shown in the Ozark Aeroworks, LLC manual of FAA approved data. The exhaust gas temperature is measured by three thermocouples located in the exhaust diffuser of the engine. Oil outlet temperature 300°F. Ignition unit surface temperature 238°F. Fuel control ambient temperature 240°F. Igniter solenoid valve surface temperatures 250°F. Air bleed control ambient temperature 260°F. NOTE 3. Fuel and oil pressure limits: Fuel: 0-50 p.s.i.g. Oil: Minimum - 10 p.s.i. ground idle 60 p.s.i. takeoff and maximum continuous Maximum - 80 p.s.i. NOTE 4. Accessory drive provisions: Drive AND Type No. Required Gear Ratio Maximum Torque (in.-lb.) Rotation* Cont. Static Gas producer tachometer 20005 XV-B modifie d 1 .1670 7 50 C Starter-generator 20002 XII-D modifie d 1 .2833 220 1296 C Power takeoff 20002 XII-D modifie d 1 .5397 150 680 C Power turbine tachometer 20005 XV- B 1 .1997 7 50 C *C - Clockwise; CC - Counterclockwise The customer accessory horsepower extraction limits are presented in graphical form in the Ozark Aeroworks, LLC manual of FAA approved data. NOTE 5. Engine ratings are based on calibrated stand performance under the following conditions: Static sea level standard conditions of 59°F and 29.92 in.Hg. No inlet duct losses, no loading of the accessory drives and minimum permissible bleed air flow. Exhaust configuration as defined by Ozark Aeroworks, LLC drawing 1-000-029-03. NOTE 6. Maximum permissible air bleed ex traction is 3.0% at standard sea level static conditions at 92% maximum continuous power and below. NOTE 7. The nominal power turbine operating speed is 21 ,190 rpm. Maximum power turbine speed is 21,300 rpm at all conditions including takeoff. NOTE 8. Power turbine output shaft torque limits: Takeoff 3580 ft. lb. Maximum continuous 3280 ft. lb. NOTE 9. These engines meet FAA requi rements for operation in icing conditions, for adequate turbine disc integrity and rotor blade containment and do not require airframe mounted armoring. They have not, however, been tested to evaluate the effects of ingestion of birds. The bird ingestion characteristics of the airframe air inlet and engine combination are to be evaluated prior to the approval of the engine installation in an airplane. NOTE 10. MIL-DTO-5624, Grades JP-4 and JP-5. MIL-DT O-83133, Grade JP-8. ASTM D1655 Jet A, Jet A-1, and Jet B. Refer to Ozark Aeroworks, LLC Maintena nce Manual 330.2 for equivalent fuels and additives. ---END--