TCDS E13EA

Page No. 1 2 3 4 Rev. No. 12 12 12 12 Reformatted 10/94 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E13EA Revision 12 GENERAL ELECTRIC CT64-820-4 July 16, 1986 TYPE CERTIFICATE DATA SHEET NO. E13EA Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E13EA) 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: General Electric Company Aircraft Engine Group Lynn, Massachusetts 01910 Model Type CT64-820-4 Axial Flow 14 Stage Compressor Annular combustor 2 Stage Gas Generator Turbine 2 Stage Free Power Turbine Turboprop Reduction Ratio 13.44:1 Propeller Shaft above Power Unit Centerline Ratings Maximum continuous at sea level: Equivalent Shaft, hp 2830 Shaft, hp. 2745 Thrust, lb. 213 Output, r.p.m. (See NOTE 2) 1015 Takeoff (5 min.) at sea level: Equivalent Shaft hp. 3227 Shaft hp. 3133 Thrust, lb. 236 Output, r.p.m. (See NOTE 2) 1160 Propeller Shaft AND 10152-60A Fuel Control Ham. Std. Model JFC-42-2 (Turboprop), & Pesco (Sundstrand) type 023966, 024836 gear type fuel pump Fuel Fuel conforming to G.E. Jet Fuel Spec. No. D50TF2, current revision. Kerosene JP-4 & JP-5 fuels are acceptable Oil Synthetic type conforming to G.E. specification D50TF1, current revision Principal Dimensions Length, in. 110.20 Width, in. 26.90 Height, in. 40.40 Weight (dry) lb. 1145 (includes essential engine accessories & torque sensor for CT64-820-4 only) Center of Gravity Location, in., Forward of rear mount forward face 19.76 E13EA 2 Model Type CT64-820-4 Engine Centerline above 1.89 left 0.30 Ignition System (20-29 volts D.C., 150 watts) Bendix Scintilla type 10-324830 or General Laboratory Associates type 43661 dual ignition unit with two ignitor plugs Champion type FHE111 NOTES 1 through 12 Certification basis: Regulations & Amendments Model Date of Application Date Type Certificate No. E13EA Issued/Revised Inactive CAR 13 effective June 15, 1956 CT64-410-1 September 19, 1963 March 25, 1965 August 30, 1967 as amended by 13-1, 13-2, 13-3, CT64-610-1 September 19, 1963 March 25, 1965 August 30, 1967 13-4, 13-5, & 13-6 CT64-810-1 September 19, 1963 March 25, 1965 April 29, 1971 T64-GE-10 September 19, 1963 March 25, 1965 April 29, 1971 CT64-820-1 February 26, 1965 January 27, 1967 April 24, 1975 CT64-820-2 January 9, 1967 January 27, 1967 April 24, 1975 CT64-820-3 May 4, 1973 May 31, 1973 April 24, 1975 CT64-820-4 February 12, 1974 October 21, 1974 CT64-630-1 February 15, 1966 June 28, 1968 May 20, 1983 T64-GE-16 May 15, 1967 June 28, 1968 May 20, 1983 CT64-630-1A March 11, 1970 April 15, 1971 May 20, 1983 Production basis: Production Certificate No. 107 NOTE 1. Maximum permissible temperatures: CT64-820-4 Power turbine inlet (T5)* Takeoff 1370°F Maximum continuous 1300°F Starting 1650°F (3 sec.) Oil Inlet 240°F *The power turbine inlet gas temperature is measured by thermocouples mounted in a radial plane in the turbine casing (14 thermocouples, 820-4). NOTE 2. Engine Rotor Speeds, r.p.m.: CT64-820-4 Gas Generator (maximum permissible) Takeoff 18,230 Maximum continuous 17,800 Overspeed (10 seconds) 18,500 Output Shaft Operating Range Maximum 1,160* Nominal 1.015* Overspeed (Max. permissible, 5 sec.) 1,450* *Propellers to be used with this engine must have the functioning characteristics compatible with the engine and control system. When these limits are exceeded, refer to General Electric Operation Instruction SEI-447 for appropriate action. 3 E13EA NOTE 3. Fuel and Oil Pressure Limits: CT64-820-4 Fuel Inlet Pressure 50 p.s.i.g. maximum No Boost 0.45 V/L (Maximum) S.L. to 6000 ft. Oil Pump Discharge Ground idle Engine 10 p.s.i.g. minimum Speed Decreaser Gear 5 p.s.i.g. minimum Operating Range Engine 50-90 p.s.i.d. Speed Decreaser Gear 60-95 p.s.i.d. Refer to applicable Operating/Maintenance Instructions for operating range limits and for reduced oil pressure limits above 15,000 feet altitude. NOTE 4. Accessory Drive Provisions: Drives Type Direction of Rotation* Speed, r.p.m. Maximum Torque in. lb. Engine Gearcase Cont Static Engine Tach Generator AND 20005 Type XVB Modified CC 0.246** 7 50 Starter (used as starter pad) AND 20002 Type X11S Modified C 0.697** 1370 3000 Starter (used as driving pad) AND 20002 Type X11S Modified C 0.697** 370 (1) 3000 Fluid Power Pump AND 20002 Type X11J CC 0.259** 1000 (1) 4400 Speed Decreaser Gearcase Power Turbine Tach Generator AND 20005 Type XVB C 0.270*** 7 50 Fluid Power Pump AND 20002 Type X11J Modified C 0.237*** 600 2700 Fluid Power Pump AND 20000 Type XA Modified CC 0.233*** 100 800 * - Facing pad, "C" - Clockwise; "CC" - Counter-clockwise ** - Times gas generator r.p.m. *** - Times power turbine r.p.m. (1) Total combined power extraction from gas generator accessory gearcase pads not to exceed 55.6 s. hp. Refer to General Electric Installation Manual SEI-123 and SEI-429 for further accessory drive power limitations. NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: Standard sea level static conditions of 59°F and 14.696 p.s.i.a. Air inlet as defined by G.E. Drawing 1076678-335 Jet nozzle area of 450 sq. in. No external air bleed or accessory drive loads No anti-icing airflow ESHP = Jet Thrust, lb./2.5 + s. hp. Engines with individual performance characteristics and capabilities to develop the low temperature power ratings noted above at higher ambient temperatures may be operated up to these power limits at any ambient conditions providing the limits on all other engine parameters are not exceeded. The CT64-820-4 model is flat rated at 3133 shaft h.p. to 100°F for takeoff and 2745 shaft h.p. to 86°F for maximum continuous. Performance data is further described in General Electric Specification Nos. E1209 (CT64-820-4). E13EA 4 NOTE 6. Maximum permissible continuous air bleed extraction is 6%. See General Electric Installation Manual SEI-429 for further limitations. NOTE 7. Output Shaft Torque Limits (ft. -lb.) CT64-820-4 Transient (5 sec.) 21,800 Steady state 14,200 NOTE 8. Torque signals are provided by the engine for airframe torque reading system. NOTE 9. The CT64-820-4 engine when operating in icing conditions must have ignition on and be operated above flight idle. NOTE 10. The only optional additives which may be used in approved fuels are as follows: (1) Phillips PFA-55MB or anti-icing additives to specification MIL-1-27686E at a concentration not in excess of 0.15% by volume. (2) S0H10 Biobor JF biocide additive at a concentration not in excess of 20 p.p.m. elemental boron (270 p.p.m. total additive). (3) Shell ASA-3 antistatic additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to 1 p.p.m. NOTE 11. Certain engine parts are life limited. These limits are listed in CT64 Service Bulletin No. 93. NOTE 12. Fuel venting emission control is not included on these engines; and therefore, beginning January 1, 1975, airframe compliance must be provided. .....END.....