TCDS 1E3

Page No. 1 2 3 4 5 Rev. No. 15 15 16 15 16 Reformatted 10/94 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1E3 Revision 16 General Electric CT58-100-2 CT58-110-1 CT58-110-2 CT58-140-1 CT58-140-2 Sept 4, 2018 TYPE CERTIFICATE DATA SHEET NO. 1E3 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. 1E3) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft i n accordance with pertinent aircraft data sheets and applic able portions of the Civil Air Regulations/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 CT58-100-2 CT58-110-1 CT58-110-2 CT58-140-1 CT58-140-2 Type Axial flow, free turbine turboshaft Ten stage compressor Annular combustion chamber Two stage gas generator turbine Single stage power turbine Ratings (See NOTE 14) At nominal power turbine speed of 19,500 r.p.m. Max. continuous at sea level; hp. 990 1050 - - 1250 Takeoff (5 min.) at sea level; hp. 1050 1250 - - 1400 30 min. helicopter rating at sea level; hp.  1250 - - 1400 2½ min. helicopter rating at sea level; hp.  1350 - - 1500 Alternate rating (See NOTE 9) Max. continuous & takeoff at sea level; hp. 730 - - - - - - Fuel control Hamilton Standard JFC-26 & Pesco 023104 gear type fuel pump with integral boost. - - - - - - Fuel (See NOTE 15) Fuel conforming to General Electric Company Jet Fuel Specification No. D50TF2, current revision. Kerosene, JF4 and JP5 fuels are acceptable but whenever a change is made, re- adjustment of the fuel control to the appropriate setting must be made. - - - - - - 1E3 2 Model (cont'd) CT58-100-2 CT58-110-1 CT58-110-2 CT58-140-1 CT58-140-2 Oil Oil conforming to General Electric Specification No. D50TF1, current revision. See applicable Operations Bulletin for specific oils approved per the subject specification. - - - - - - Principal dimensions Length, in. 59 - - - - - - Max. diameter, in. 16 - - - - - - Weight (dry), lb. (includes essential engine accessories and turbine bucket guard) 295 315 335 340 C.G. Location with down exhaust Aft of front mount centerline, in. 18.45 - - 18.88 19.65 Below engine centerline, in. 1.50 - - - - 1.80 Ignition system (24 volts D.C. 150 watts max.) Bendix Scintilla dual ignition unit type TGLN with integral junction box assembly and two igniter plugs - - - - - - Igniter plugs P/N 37B200275 - - - - - - NOTES 1 through 13, 15, 17, & 18 1 thru 18 - - 1 thru 15, 17, & 18 "- -" indicates "same as preceding model" "" indicates "does not apply" Certification basis: Regulations & Amendments Model Date of Application Date Type Certificate No. 1E3 Issued/Revised Date of Cancellation CAR 13, effective June 15, CT58-100-1 June 2, 1958 July 1, 1959 September 15, 1982 1956 as amended by 13-1, CT58-100-2 September 15, 1959 December 29, 1960 13-2, 13-3, 13-4, 13-5, & 13-6 CT58-110-1 September 24, 1959 July 13, 1961 CT58-140-1 June 23, 1964 June 10, 1965 CT58-110-2 October 31, 1967 March 29, 1968 CT58-140-2 January 25, 1968 April 18, 1968 Production basis: Production Certificate No. 107. NOTE 1. Maximum permissible gas generator operating speeds (r.p.m.) are as follows: CT58-100-2 CT58-110-1 CT58-110-2 CT58-140-1 CT58-140-2 2½ minute helicopter rating  26,800 - - - - 27,200 30 minute helicopter rating  26,300 - - - - - - Takeoff 25,600 26,300 - - - - - - Maximum continuous 25,600 24,300 - - - - - - Alternate rating 24,300 - - - - - - - - 3 1E3 NOTE 2. Maximum permissible temperatures: CT58-100-2 CT58-110-1 CT58-110-2 CT58-140-1 CT58-140-2 Power Turbine Inlet (T5)* 2½ minute helicopter rating  1300°F - - 1330°F 1397° 30 minute helicopter rating  1250°F - - 1285°F - - Takeoff 1175°F 1250°F - - 1285°F - - Maximum continuous 1115°F 1175°F - - 1220°F - - Maximum transient 1545°F (2 sec.) - - - - 1545°F (2 sec.) 1465°F (20 sec.) - - Starting 1545°F (4 sec.) - - - - 1740°F (2 sec.) - - Oil inlet 250°F - - - - - - - - *The power turbine inlet gas temperature is measured by eight (8) thermocouples mounted in a radial plane in the second stage turbine casing. Refer to General Electric Maintenance Manual SEI 101 CT58-100-2/-110-1/-110-2) and SEI-182 (CT58-140-1/140-2) for inspection requirements when limits are exceeded. NOTE 3. Fuel and oil pressure limits: Fuel: Minimum at engine pump inlet, 0.3 V/L (max.) with maximum 50 p.s.i. above ambient atmospheric pressure. Oil: At ground idle, 8 p.s.i.g. minimum Operating range, 20 to 60 p.s.i.g. NOTE 4. Accessory drive provisions: Rotation Facing Max. Torque (in. lb.) Drive Type Engine Pad Speed Continuous Static Starter Special CC 1.0* 180 336 Gas generator tachometer AND 20005 Type XVB C 0.160* 7 50 Power turbine tachometer AND 20005 Type XVB CC 0.200** 7 50 Fuel filter Special CC 0.160* 5 50 "C"- Clockwise, "CC" - Counter-clockwise * Speed - Times gas generator r.p.m. ** Speed - Times power turbine r.p.m. NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: Static sea level standard conditions of 59°F and 29.92 in. Hg. General Electric air inlet #1076669-886 and bullet nose #1076669-424. No external air bleed or accessory drive power for aircraft accessories. Exhaust configuration as defined by G.E. drawing #37E500110 (100-2, 110-1, 110-2) & #4006T87 (140-1, 140-2). No anti-icing airflow. Additional performance parameters are contained in General Electric Operating Instructions SEI-103 (100-2), SEI- 180 (110-1, 110-2) and SEI-197 (140-1, 140-2). NOTE 6. Maximum permissible air bleed extraction is 5.6 percent at standard conditions for 100- 2, 110-1, and 110-2; and 3.0 percent for 140-1 and 140-2. 1E3 4 NOTE 7. Power Turbine Normal Operating Range. The nominal power turbine operating speed is 19,500 r.p.m. An alternate nominal speed of 20,250 r.p.m. can also be provided. For engine identification and fuel control requirements refer to G.E. Service Bulletin 124. The engine control system provides for power turbine speed governing within the following limits: Model Min. Governing Speed Governor Topping Speed 100-2 16,600 r.p.m. 21,275 r.p.m. 110-1, 110-2 16,600 r.p.m. 21,275 r.p.m. 140-1, 140-2 17,000 r.p.m. 21,275 r.p.m. NOTE 8. Power Turbine Shaft Torque Limits - All Models: Static 11,100 in. lb. Maximum continuous No limit, provided that all other power, speed and temperature limits are maintained. NOTE 9. All models can be provided with alternate power ratings as noted. A fuel control change is required to make this rating change. Refer to CT58 Service Bulletin #45 for listing of approved fuel controls. In addition the following CT58-140 ratings are provided: CT58-140-1 CT58-140-2 Horsepower Horsepower Rating 59°F 80°F 59°F 80°F 2½ Minute 1500 1350 1500 1500 30 Minute & Takeoff 1250 1250 1250 1250 Maximum Continuous 1050 1050 1050 1050 NOTE 10. To be eligible for use in certificated aircraft, the engine installation must include an accurate engine output torque measuring device or an acceptable alternate means of determining engine power. NOTE 11. This engine meets FAA requirements for operation in icing conditions, for adequate turbine disc integrity and rotor blade containment and does not require airframe-mounted armoring. NOTE 12. Maximum permissible overspeeds are: Gas generator 27,600 r.p.m. for 15 seconds (CT58-100-2/-110-1/-110-2) 28,300 rpm for 20 seconds (CT58-140- 1/140-2) Power Turbine 23,100 r.p.m. for 15 seconds. When either of these limits is exceeded, the engine must be disassembled for inspection. NOTE 13. Because of differences in engine application and installation, each engine installation design must be evaluated with regard to engine overspeed protection and an airframe-mounted speed switch provided if deemed necessary. NOTE 14. Below 59°F the sea level static power limits for the CT58-110-1/-2 and CT58-140-1/-2 engines will vary as follows: Rating CT58-110-1/110-2 CT58-140-1 CT58-140-2 2½ Min. Helicopter No variation - engine is flat rated Increases linearly from 1500 hp. Increases linearly from 1500 hp. at 1350 hp. at 59°F and below. at 59°F to 1545 hp. at -65°F at 59°F to 1560 hp. at -65°F. Takeoff & 30 Min. Increases from 1250 hp. at 59°F Increases linearly from 1400 hp. Increases linearly from 1400 hp. Helicopter to 1350 hp. at +23°F and flat at 59°F to 1510 hp. at 22°F and at 59° to 1530 hp. at 13°F and rated below this temperatures. to 1540 hp. at -65°F. to 1560 hp. at -65°F. Max. Continuous Increases linearly from 1050 hp. Increases linearly from 1250 hp. - - at 59°F to 1230 hp. at 29°F and at 59 F to 1390 hp. at 39°F flat rated at 1230 hp. at 29°F and flat rated at 1390 hp. at and below 39°F and below. 5 1E3 For power rating variation between standard day conditions and the temperatures listed above, refer to General Electric Operating Instructions No. 180 (CT58-110-1, 110-2) and No. 197 (CT58-140-1, 140-2). The ratings referred to herein and the limitations on the usage of these ratings are defined in the applicable FARs. 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 provided all other engine parameters are not exceeded. NOTE 15. 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-I-27686E at a concentration not in excess of 0.15% by volume. (2) SOHIO Biobor JF biocide additive at a concentration not in excess of 20 p.p.m. elemental boron (270 ppm total additive). (3) Shell ASA-3 anti-static additive at a concentration that will provide not in excess of 300 conductivity units which is approximately equivalent to 1 p.p.m. The above additives may be used in combination. With the fuel boost pump (Part Number 5183T66P01) installed, fuel system icing inhibitor ( FSII) must be added to the fuel when flight conditions are known or forecast to be at or below 32 degrees F (0 degrees C). NOTE 16. A speed decreaser gear defined by General Electric drawing 37R600175 is eligible for use on CT58-110-1, -110-2 engines. This provides a gear reduction ratio of 3.25 to 1 and includes an integral torque sensing device. Oil conforming to General Electric Specification No. 050TF1 must be supplied to the gear box from the airframe oil supply system. Normal oil pressure operating limits for the gear box are 35 to 75 p.s.i. NOTE 17. The CT58-100-2 and CT58-110-1 engines incorporate improved hot section parts to permit operation at higher turbine inlet temperatures and increased ratings. The CT58- 100-2 does not utilize the higher rating. "Military T58-GE-1 engines with serial numbers below 277135 were manufactured identical to the CT58-110-1, and military T58-GE-5 engines with serial numbers below 285373 and below 291053 were manufactured identical to the CT58-140-1. These engines are eligible for use in certificated aircraft if they conform to the FAA approved parts lists, are in an acceptable airworthiness condition, and the engine nameplate has been revised or replaced to include the corresponding civil model designation and Type Certificate number. Consult General Electric for specified requirements. The T58-GE-1 and T58-GE-5 models were removed from active certification status on 16 September 1971." The CT58-140-1 engine is similar to the CT58-110-1 except for improved parts, increased airflow and compressor efficiency. The CT58-110-2 engine is similar to the CT58-110-1 with selected CT58-140-1 hardware incorporated for life and performance improvements. The CT58-140-2 engine is identical to the CT58-140-1 except for improved performance at above standard day temperature conditions and an increased flow fuel control. Refer to NOTES 9 and 14. NOTE 18. "Life limits established for critical rotating components are published in the CT58 Overhaul Manuals SEI-102 (CT58-100-2/-110-1/-110-2) and SEI-183 (CT58-140-1, -2)." ....END...