TCDS E17EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE SHEET NO. E17EA Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E17EA) 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: Ozark Aeroworks LLC 3300 S. Golden, Avenue (S. Farm Road 135) Springfield, Missouri 65807 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. Transferred TC E17EA to Ozark Aeroworks, LLC on May 06, 2022 AlliedSignal Transferred TC E17EA to Honeywell International Inc. December 14, 1999 Textron Lycoming Transferred TC E17EA to AlliedSignal on January 31, 1995 * I. MODELS T5313B T5317A T5317A-1 T5317B T5317BCV TYPE RATINGS Maximum continuous at sea level hp. Optimum output shaft r.p.m. (at maximum continous power) Takeoff (5 min.) at sea level hp. Optimum output shaft r.p.m. (at takeoff power) FUEL CONTROL FUEL (See NOTE 12) OIL Axial – centrifugal flow, free turbine turboshaft. Five stage axial and single stage centrifugal compressor. External annular atomizing combustion chamber. Two stage gas producer turbine. Two stage power turbine. 1250 1350 1350 1350 1350 6040 6210 6230 6229 6229 1400 1500 1500 1500 1500 6300 6450 6462 6461 6461 Goodrich Pump & Engine Control Systems (GPECS) Model TA-2S or TA-7 with Integral dual element pump GPECS Model TA-7 with integral dual element pump - - - - GPECS Model TA-7 or TA- 7CV with integral dual element pump - - - - - - - - - - MIL-PRF-7808 or MIL-PRF-23699 - - - - - - - - NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT BORDER. LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" PAGE 1 2 3 4 5 REV. 12 12 12 12 12 MODELS: T5313B T5317A T5317A-1 T5317B T5317BCV MAY 06, 2022 E17EA REVISION: 12 OZARK AEROWORKS, LLC E17EA 2 CERTIFICATION BASIS PRODUCTION BASIS: NONE NOTE 1. Maximum power turbine speed is 21,300 r.p.m. at all conditions including takeoff. NOTE 2. Power Turbine output shaft torque limits: T5313B T5317A T5317A-1 T5317B T5317BCV Takeoff Maximum continuous 1175 ft. lb. 1250 ft. lb. - - - - - - 1110 ft. lb. 1160 ft. lb. - - - - - - NOTE 3. Maximum permissible gas producer speeds are: Takeoff Maximum continuous T5313B T5317A T5317A-1 T5317B T5317BCV 25,650 r.p.m. 26,400 r.p.m. - - - - - - 24,900 r.p.m. 25,400 r.p.m. - - - - - - I. MODELS (Continued) T5313B T5317A T5317A-1 T5317B T5317BCV PRINCIPAL DIMENSIONS Length, in. nominal Maximum diameter, in. Weight (DRY), lb. (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. Below engine horizontal centerline, in. IGNITION SYSTEM (28 VOLTS D.C.) IGNITER PLUGS 47.602 24.50 - - - - - - - - - - - - - - - - 544 545 541 547 - - 14.38 .76 - - - - - - - - - - - - - - - - Bendix Type TGLN2125 or GLA Type 42416 with spark splitter coil and two shunted surface gap igniter plugs - - - - - - - - AC5611304 - - - - - - - - Model Date of Application Type Certificate No. E17EA Certification Basis T5313A 07/01/64 04/22/68 Issued CAR 13, 06/15/56, Amendment 13-1 thru 13-3 T5313B 10/01/69 12/24/69 Amended CAR 13, 06/15/56, Amendment 13-1 thru 13-3 T5317A 11/29/71 04/11/73 Amended CAR 13, 06/15/56, Amendment 13-1 thru 13-3 T5313A 08/01/85 Cancelled T5317A-1 06/24/92 07/21/93 Amended 14 CFR part 33, Amendment 5 T5317B 03/12/92 03/21/94 Amended 14 CFR part 33, Amendment 5 T5317BCV 5/20/03 10/06/06 Amended 14 CFR part 33, Amendment 5 NOTES 3 E17EA NOTE 4. Maximum permissible temperatures: For models T5313B, T5317A, and T5317A-1, maximum permissible exhaust gas temperature varies with ambient temperature as shown in the following FAA Approved documents: Model T5313B Installation Instructions 94-1519.14.5; Model T5317A FAA Approved Data Book, 94-1519.14.15; Model T5317A-1 Installation Instructions 21-12573. For Models T5317B and T5317BCV maximum permissible measured gas temperature is 1585oF for the takeoff power condition and 1508oF for the maximum continuous power condition. The gas temperature is measured by twelve thermocouples located between the gas producer turbine and power turbine stages. T5313B T5317A T5317A-1 T5317B T5317BCV Oil inlet temp. 200oF - - - - - - - - Oil outlet temp. 300oF - - 275oF - - - - Ignition unit surface 250oF - - - - - - - - temp. Fuel control ambient 250oF - - - - - - - - temp. Igniter solenoid valve 300oF - - - - - - - - surface temp. Air bleed control 300oF - - - - - - - - ambient temp. Thermocouple harness 350oF - - - - - - - - airframe interface connector NOTE 5: Fuel and oil pressure limits: T5313B T5317A T5317A-1 T5317B T5317BCV Fuel: Oil: Ground idle Operating range Takeoff & max. continuous 0 to 50 p.s.i.g - - - - - - - - 10 p.s.i. min. - - - - - - - - 20 to 100 p.s.i. - - - - - - - - 80 to 100 p.s.i. - - - - - - - - NOTE 6. Accessory drive provisions: Drive AND Type Number Required Gear Ratio Maximum Torque (in.-lb.) Continuous Short Time (1) Static Rotation Gas producer tachometer Starter-Generator Power takeoff Power turbine tachometer 20005 XV-B Modified 20002 XII-D Modified 20002 XII-D Modified 20005 XV-B Modified 1 1 1 1 .1670 .2833 .5397 .1993 7 250 150 7 - - 320(3) 225 - - 50 1600(2) 800(4) 50 C C C C C – Clockwise E17EA 4 (1) Maximum permissible torque 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. (4) 680 in.-lb. on power takeoff pad when starter is installed. The customer accessory horsepower extraction limits are presented in the following FAA approved documents: Model T5313B Installation Instructions 94-1519.14.5; Model T5317A FAA Approved Data Book 94-1519.14.15; Model T5317A-1 Installation Instructions 21-12573; Model T5317B Installation Instructions 21-12062; Model T5317BCV Installation Instructions 21-12440. The customer accessory horsepower extraction limits are presented in the Ozark Aeroworks’ Manual of FAA Approved Data. NOTE 7. Engine ratings are based on calibrated stand performance under the following conditions: Static sea level standard conditions of 59oF 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’ drawing 1-000-031-01. NOTE 8. The maximum permissible air bleed extraction limits are in the following FAA approved documents: Model T5313B Installation Instructions 94-1519.14.5 - Figure 8.1; Model T5317A FAA Approved Data Book 94-1519.14.15 - Figure 6.1; Model T5317A -1 Installation Instructions 21-12573 - Figure 1-5; Model T5317B Installation Instructions 21- 12062 - Figure 1-4; Model T5317BCV Installation Instructions 21-12440 - Figure 1-4. NOTE 9. These engines meet the FAA requirements for operation in icing conditions provided a minimum gas producer speed is maintained in accordance with the following FAA approved documents: Model T5313B Installation Instructions 94-1519.14.5 - Figure 8.5; Model T5317A FAA Approved Data Book 94-1519.14.15 - Figure 6.5; Model T5317A-1 Installation Instructions 21- 12573 - Figure 1-7; Model T5317B Installation Instructions 21 -12062 - Figure 1-6; Model T5317BCV Installation Instructions 21-12440 Figure 1-6. NOTE 10. These engines meet FAA requirements for adequate turbine disc integrity and rotor blad e containment and do not require airframe mounted armoring. An airframe provided switch is required to test the overspeed governor prior to flight. Models T5313B and T5317A -1 do not require an electronic power turbine overspeed system. Models T5317A, T5317B, and T5317BCV do not require an electronic power turbine overspeed system when installed in aircraft with main rotor transmissions limited to 1,400 shp maximum. NOTE 11. These engines have not been tested to evaluate the effects of bird and ice ball ingestion. The bird and ice ball ingestion characteristics of the airframe air inlet and engine combination are to be evaluated prior to the approval of the engine installation. NOTE 12. MIL-DTL-5624, Grades JP-4 and JP-5. MIL-DTL-83133, Grade JP-8. ASTM D1655 Jet A, Jet A-1 and Jet B. Refer to Ozark Aeroworks Maintenance Manual 330.2 for equivalent fuels and additives. NOTE 13. Airworthiness Directive Number 74-22-07, Amendment 39-1997, effective October 31, 1974, required all T5313A engines be converted to T5313B engines within 100 hours. NOTE 14. Certain engine parts are life limited as listed in FAA approved Service Bulletin No. T5313B/17- 0020. Time Between Overhaul and Time Between Inspection criteria are contained in the following Service Bulletins: T5313B/17-0001 Engine - General - Establishing a Time Between Overhaul (TBO) and Time Between Inspections (TBI) and SB T5313B/17-0024 Engine -Fuel Regulator and Overspeed Governor - Overhaul Schedule. 5 E17EA NOTE 15. Model T5317A is similar to Model T5313B except for the incorporation of improved combustor and turbine parts and improved cooling of the gas producer nozzles and rotors. Model T5317A-1 is similar to model T5317A except for incorporation of a unique power turbine governor and bleed band actuator. Model T5317B is similar to Model T5317A except for use of an interturbine (MGT) gas temperature measurement system. NOTE 16. Model T5317BCV is identical to Model T5317B except that Model T5317BCV may contain certain parts that have accumulated prior time in service provided those parts conform to the data contained in Ozark Aeroworks T5317BCV Hardware Conformity Process Manual, Document Number 360.5, and are marked with a “CV” suffix on the part number. “CV” part numbers may only be used on Model T5317BCV. ….END….