# TCDS E1EA: Ozark Aeroworks LLC - Type: Type certificate data sheet - Status: Current - Holder: Ozark Aeroworks LLC - Revision: 7 - Revised: May 6, 2022 - Product: Engine - Certification basis: CAR 13 - Registered aircraft: 3, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/17/59/1759d56ff82e25fc2cbd908dbc882f825f0e9cb18a724ad16d054641accded32 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2F4BAF7FEA79601E8625886000457B50.0001 - Page: https://openairdocs.org/tcds/E1EA ## Models (5) As the data sheet lists them. - T5309B - T5309A - T5311A - T5311B - T5309C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E1EA Revision 7 Ozark Aeroworks, LLC T5309A T5309B T5309C T5311A T5311B MAY 06, 2022 TYPE CERTIFICATE DATA SHEET NO. E1EA Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E1EA) 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 Ozark Aeroworks, LLC 3300 S. Golden Ave. (S. Farm Rd. 135) Springfield, Missouri 65807 Type Certificate Holder Record Honeywell International Inc. Transferred TC E1EA to Ozark Aeroworks, LLC on May 06, 2022 AlliedSignal Transferred TC E1EA to Honeywell International Inc. December 14, 1999 Textron Lycoming Transferred TC E1EA to AlliedSignal on January 31, 1995 Model T5309A T5309B T5309C T5311A T5311B Type Axial - centrifugal flow, free turbine turboshaft. Five stage axial and single stage centri- fugal compressor. External annular vaporizing combustion chamber. Single stage gas producer turbine. Single stage power turbine. Ratings At nominal output shaft speed of 6610 r.p.m. Maximum continuous at sea level, hp. 900 - - - - - - Takeoff (5 min.) at sea level, hp. 1100 - - - - - - Fuel control Chandler Evans Model - - - - Chandler Evans Model TA-2B with integral - - TA-2G with integral dual element pump dual element pump Fuel (See NOTE 10) Oil Synthetic type conforming to MIL-L-7808 - - - - - - Principal dimensions Length, in. nominal 47.80 - - - - - - Nominal diameter, in. 23.70 - - - - - - Nominal radius, in. 13.56 - - - - - - E1EA 2 Weight (dry), lb. (includes essential engine accessories but excludes starter, two tachometer generators, oil tank and oil cooler) 485 490 - - 496 Page No. 1 2 3 Rev No. 6 6 6 T5309A T5309B T5309C T5311A T5311B C.G. location (dry weight) Aft of front mount pad centerline, in. 14.10 - - - - - - Below engine horizontal centerline, in. .65 - - - - - - Ignition system (28 volts D.C.) Bendix type TGLN 1112 with spark splitter coil and two shunted surface gap igniter plugs - - - - - - Igniter plugs Bendix 10-165660-1 - - AC 5610719 - - NOTES “- -“ indicates “same as preceding model” “__” indicates “does not apply” 1,2,3,4,5,6,7,8,9,10,11 - - - - - - Certification Basis Regulations and Amendments Model Date of Application Date Type Certificate E1EA Issued/Amended CAR 13, effective June 15, 1956 T5309A December 28, 1960 September 20, 1962 As amended by 13-1, 13-2, & 13-3 T5309B September 27, 1962 November 6, 1962 T5309C April 4, 1963 April 18, 1963 T5311A June 15, 1962 September 3, 1963 T5311B October 16, 1968 October 23, 1968 Production Basis: NONE NOTE 1. Maximum permissible gas producer speeds are: 25,200 r.p.m. – takeoff 24,700 r.p.m. – 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 temperature 250° F Air bleed control ambient temperature 260° F NOTE 3. Fuel and oil pressure limits: Fuel: 0 – 50 p.s.i.g. Oil: Ground idle 10 p.s.i. minimum E1EA 3______________________________ Operating range 20 to 80 p.s.i. Takeoff and maximum continuous 60 p.s.i. minimum NOTE 4. Accessory drive provisions: Drive AND Type No. Required Gear Ratio Maximum Torque (in.-lb.) Static Rotation Continuous Short Time(1) Gas producer tachometer 20005 XV-B Modified 1 .1670 7 ---- 50 c Starter-generator 20002 XII-D Modified 1 .2833 220 320(3) 1296(2) c Power takeoff 20002 XII-D Modified 1 .5397 150 22 680 c Power turbine tachometer 20005 XV-B Modified 1 .1992 7 --- 50 c c - Clockwise (1) Maximum permissible torque for 5-minute periods, recurring at not less than 4-hour intervals. (2) Maximum permissible torque during starts is 1296 in.-lb. (3) Generator torque in excess of 320 in.-lb. is permissible up to a maximum of 625 in.-lb. for a period of not more than 15 seconds. The customer accessory horsepower extraction limits are presented 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 extraction shall be in accordance with Figure 4 in the Ozark Aeroworks, LLC Manual of FAA Approved Data. NOTE 7. The nominal power turbine operating speed is 21,190 r.p.m. Maximum power turbine speed is 21,300 r.p.m. at all conditions including takeoff. NOTE 8. Power turbine output shaft torque limits: Takeoff 926 ft.-lb. Maximum continuous 850 ft.-lb. NOTE 9. These engines meet FAA requirements for operation in icing conditions, for adequate turbine disc integrity and rotor blade containment and do not require airframe mounted armoring. NOTE 10. MIL-DTO-5624, Grades JP-4 and JP-5. MIL-DTO-83133, Grade JP-8. ASTM D1655 Jet A, Jet A-2, and Jet B. Refer to Ozark Aeroworks, LLC Maintenance Manual 330.2 for equivalent fuels and additives. NOTE 11. The above models incorporate the following general characteristics: T53 Model Characteristics 09A Basic model. Bleed air bled from peripheral gap in centrifugal compressor housing. 09B Same as 09A except bleed air bled from series of holes in rear vanes of diffuser. 09C Same as 09B except revised combustion chamber parts to permit operation on JP-5 fuel 11A Same as 09C except fuel regulator provides control of the transient air bleed for decreased acceleration time. 11B Same as 11A except for output shaft spline. ….END…. ``` ## ADs (9, in force first) - [AD 2022-10-02](https://openairdocs.org/ad/2022-10-02): Engine Controls · Honeywell International T53-L-703, T53-L-13B S/SB, T53-L-13B S/SA and 14 more. Effective Jun 28, 2022 - [AD 2006-11-16](https://openairdocs.org/ad/2006-11-16): Fuel control regulator assemblies · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B and 8 more. Effective Jul 5, 2006 - [AD 2006-01-05](https://openairdocs.org/ad/2006-01-05): Turboshaft engine · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B S/SB and 12 more. Effective Feb 16, 2006 - [AD 2002-09-09](https://openairdocs.org/ad/2002-09-09): Centrifugal Compressor Impeller · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B and 10 more. Effective Jun 13, 2002 - [AD 97-07-05](https://openairdocs.org/ad/97-07-05): Accessory Drive Assembly · Honeywell International T53-L-703, T5311A, T5311B and 4 more. Effective Jun 24, 1997 - [AD 77-17-08](https://openairdocs.org/ad/77-17-08): Fuel Regulator P1 Multiplier Lever · Honeywell International T53-L-703, T5307A, T5309A and 7 more. Effective Mar 30, 1978 - [AD 75-22-02](https://openairdocs.org/ad/75-22-02): Secondary Failure N2 Accessory Drive Shaft · Honeywell International T5307A, T5309A, T5309B and 6 more. Effective Oct 29, 1975 - [AD 74-09-03](https://openairdocs.org/ad/74-09-03): Compressor Rotor Discs · Honeywell International T5309C, T5311A and T5311B. Effective May 2, 1974 - [AD 2002-03-01](https://openairdocs.org/ad/2002-03-01) (historical): Reduction Gearbox Assembly · Honeywell International T5311A, T5311B, T5313B and 2 more. Effective Mar 21, 2002 ## Registered aircraft by registry model (OpenAirDocs) - [Lycoming T5311B](https://openairdocs.org/engine/lycoming-t5311b): 2 aircraft (registry code 41607) - [Honeywell T5309B](https://openairdocs.org/engine/honeywell-t5309b): 1 aircraft (registry code 33912) - [Alliedsign T5309A](https://openairdocs.org/engine/alliedsign-t5309a): 0 aircraft (registry code 02510) - [Alliedsign T5309B](https://openairdocs.org/engine/alliedsign-t5309b): 0 aircraft (registry code 02511) - [Alliedsign T5309C](https://openairdocs.org/engine/alliedsign-t5309c): 0 aircraft (registry code 02512) - [Alliedsign T5311A](https://openairdocs.org/engine/alliedsign-t5311a): 0 aircraft (registry code 02513) - [Alliedsign T5311B](https://openairdocs.org/engine/alliedsign-t5311b): 0 aircraft (registry code 02514) - [Honeywell T5309A](https://openairdocs.org/engine/honeywell-t5309a): 0 aircraft (registry code 33911) - [Honeywell T5309C](https://openairdocs.org/engine/honeywell-t5309c): 0 aircraft (registry code 33913) - [Honeywell T5311A](https://openairdocs.org/engine/honeywell-t5311a): 0 aircraft (registry code 33914) - [Lycoming T5309A](https://openairdocs.org/engine/lycoming-t5309a): 0 aircraft (registry code 41603) - [Lycoming T5309B](https://openairdocs.org/engine/lycoming-t5309b): 0 aircraft (registry code 41604) - [Lycoming T5309C](https://openairdocs.org/engine/lycoming-t5309c): 0 aircraft (registry code 41605) - [Lycoming T5311A](https://openairdocs.org/engine/lycoming-t5311a): 0 aircraft (registry code 41606) ## STCs approved under this data sheet (1) - [STC SE00028EN](https://openairdocs.org/stc/SE00028EN): Installation of Pratt & Whitney Engine Services Inc. SmartCycle Plus Engine Monitoring System, P/N EMU-K-010-1 on specified T53 engine models.. Pratt & Whitney Engine Services Inc. --- 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.