# TCDS E00100EN: General Electric Company - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company - Revision: 0 - Revised: March 7, 2025 - Product: Engine - Certification basis: Part 33, Part 34 - Data sheet PDF: https://openairdocs.org/files/sha256/c7/cb/c7cb93e52d153c4b067297c3a81d08120d77ad8c9e9aed28f66f073b275eea1a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID168944805920250307190803.0001 - Page: https://openairdocs.org/tcds/E00100EN ## Models (1) As the data sheet lists them. - GE Catalyst 1300-CS1A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00100EN TCDS NUMBER E00100EN REVISION: REVISION 0 DATE: 7 March 2025 GENERAL ELECTRIC COMPANY MODELS: GE CATALYST 1300-CS1A Engines of model described herein conforming with this data sheet (which is part of Type Certificate Number E00100EN) 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: General Electric Company 1 Neumann Way Cincinnati, OH 45215-6310 I. MODELS GE Catalyst 1300-CS1A TYPE Turboprop; reverse flow; two spool; free-turbine. Four-stage axial and single-stage centrifugal compressor; annular reverse flow combustion chamber; two-stage gas generator turbine; three- stage power turbine; integral propeller gearbox; gas generator accessory drive system; dual channel Full Authority Digital Engine and Propeller Control (FADEPC) system. (See Note 1) Power at Sea Level: Takeoff (5 minutes) • Shaft horsepower • Output rpm (power turbine / propeller) Maximum continuous • Shaft horsepower • Output rpm (power turbine / propeller) Flat Rating Ambient Temperature at Sea Level: °F (°C) • Takeoff • Maximum continuous 1,300 24,768 /1,800 1,300 23,392 / 1,700 100 (38) 99 (37) COMPONENTS Part Number Electronic Engine and Propeller Controller Software (field loadable) Software (field loadable) Fuel Metering Unit Ignition Exciter Igniter 3133M00 3138M99 3145M10 3133M01 3138M05 3133M22 PAGE 1 2 3 4 5 6 7 8 REV. 0 0 0 0 0 0 0 0 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES “NOT APPLICABLE” NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. E00100EN 2 of 8 I. MODELS (Cont.) GE Catalyst 1300-CS1A FUEL • Approved fuels and additives are defined in the Installation Manual and Operating Instructions Manual. Additional information can be found in GE Catalyst Service Bulletin SB 73-00-0001. (See Notes 12 & 15) OIL • Approved oils are defined in the Installation Manual and Operating Instructions Manual. Refer to GE Catalyst Service Bulletin SB 79-00-0001 for detailed information pertaining to type of oils. (See Note 12) PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length: in (mm) Propeller flange to most AFT of FMU Width: in (mm) Exhaust seal to exhaust seal Height: in (mm) PGB case 71.59 (1,818.39) 20.00 (508.00) 20.13 (511.30) WEIGHT (DRY): lb (kg) Includes dry weight. Not to Exceed: 639.7 (290.2) CENTER OF GRAVITY LOCATION Nominal, Dry Engine Only - Vibration Isolator Mass Station (axial): in (mm) Waterline: in (mm) Butt line: in (mm) 194.95 (4951.73) 99.59 (2529.59) 100.63 (2556.00) THIS SPACE INTENTIONALLY LEFT BLANK E00100EN 3 of 8 CERTIFICATION BASIS • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-34. • 14 CFR part 34, amendment 7A, effective May 24, 2024. See Note 11 for more details. • ELOS: None • Special Conditions: None • Exemptions: o Ice Crystal Icing §33.68(e) – Exemption No. 22984, dated October 10, 2024 MODEL APPLICATION DATE TC ISSUED / AMENDED GE Catalyst 1300-CS1A 11 April 2017 27 February 2025 PRODUCTION BASIS GE Aviation Czech s.r.o. Production Organization Approval CZ.21G.0042 (See Note 16 for Import Requirements) THIS SPACE INTENTIONALLY LEFT BLANK E00100EN 4 of 8 NOTE 1. ENGINE RATING Engine rating is based on calibrated stand performance under the following conditions: Takeoff power is nominally independent of ambient temperature (flat rated) up to ambient temperature of: Std + 23 °C (38 °C, 100 °F), except as noted above. Maximum continuous power is nominally independent of ambient temperature (flat rated) up to ambient temperature of Std. + 22 °C (37 °C, 99 °F). Assumptions: 1. Sea level static, standard day: 101.325 kPa Pressure (14.696 psia); 15 °C temperature (59 °F) 2. No customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery, exhaust stacks 4. Fuel lower heating value of 18,400 BTU/lb (42,798 kJ/kg) 5. Relative humidity – dry day (0% RH) 6. No internal anti-ice bleed 7. Production instrumentation NOTE 2. TEMPERATURE LIMITS Maximum Permissible Power Turbine Inlet Gas Temperature Takeoff (5 minutes) Maximum Continuous Transient (12 seconds) Starting 1775 °F (968 °C) 1775 °F (968 °C) 1790 °F (977 °C) 1725 °F (941 °C) Fuel Pump Inlet Temperature Maximum Minimum (Cold Start) 165 °F (74 °C) -40 °F (-40 °C) Or the relevant fuel freezing point, whichever is higher Oil Temperature Continuous operation Transient (15 minutes) 280 °F (138 °C) 300 °F (149 °C) As measured in the oil tank THIS SPACE INTENTIONALLY LEFT BLANK NOTES E00100EN 5 of 8 NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel Pressure Limits at The Engine Pump Inlet The engine fuel system provides the fuel flows and pressures required for starting and operating the engine throughout the operating envelope with the following fuel pressure provided at the engine pump inlet: • Minimum: true vapor pressure plus 5.25 psia • Maximum: 50 psig Oil Pressure Limits • The minimum pressure limit sensed by the engine oil pressure sensor at idle is 29.9 psid (206.2 kPa) and varies up to 43 psid (296.5 kPa) at redline. • The maximum oil supply pump discharge pressure is limited during cold starts by a 400 psid (2758 kPa differential) pressure-relief valve. • The oil pressure limits are defined as outlined in the Installation Manual and Operating Instructions (See Note 15). NOTE 4. GE Catalyst-1300-CS1A ACCESSORY DRIVE CHARACTERISTICS ACCESSORY DEFINITION ROTATION (NOTE #4a) GEAR RATIO TO CORE ROTOR DRIVE SHAFT at 100% CORE SPEED (RPM) (NOTE #4b) MAXIMUM WET WEIGHT LB (lbs) MAXIMUM OVERHUNG MOMENT IN-LB (in-lbs) CONTINUOUS PAD RATING HP (SHP) OVERLOAD HP (SHP) ACCESSORY SHEAR TORQUE IN-LB (in-lbs) CORE TURN (CRANK PORT) 0.5 SQUARE DRIVE CCW 0.250 11122 N/A N/A N/A N/A N/A STARTER GENERATOR MS3326-2 CW 4.096 10875 40 200 19 28.5 1600 GENERATOR CW 4.096 10875 40 200 19 28.5 1600 ACCESSORY DRIVE NOTES: a. Rotation is defined facing the pad. b. 100 percent core engine speed is 44,550 rpm. c. Accessory pad is capable of handling overload power for 5 seconds without damage to the accessory gearbox. d. The total (combined for the two pads) customer horsepower extraction at the pads location shall not exceed the following values for both steady-state and transient operation: • At or below 25,000 feet: 29.1 shp • Above 25,000 feet: 22.25 shp NOTE 5. ENGINE MODEL DESCRIPTION The models shown on this TCDS have the following general characteristics: Model/Rating Description GE Catalyst-1300-CS1A Base Model NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN • NOT APPLICABLE NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN • Fire detection sensor kit P/N: 750L101 NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS • NOT APPLICABLE NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS • The overall engine installation to the airframe is done via 4 planar mounts in a single plane. Mount pads plane is located on the Rear Combustion Case. Refer to Installation Manual for details on engine mount system (See Note 15). NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS • NOT APPLICABLE E00100EN 6 of 8 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS • Inlet Foreign Object Protection Refer to the GE Catalyst Installation Manual for specific aircraft inlet requirements (See Note 15). • Time Limited Dispatch Criteria The GE Catalyst Engine Control has been approved for Time Limited Dispatch. Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the Airworthiness Limitations Section of the Line Maintenance Manual (GEK 133909 Ch.5), which defines the various configurations and maximum operating intervals. • Induction System Icing Demonstration of compliance to 14 CFR part 33.68, Induction System Icing, is installation specific to the Beechcraft Denali model aircraft inlet described in GE Catalyst Installation Manual (See Note 15). Installation of this engine model on different airplane models or types will require a separate evaluation and finding of compliance to 14 CFR part 33.68. • Exhaust Emissions and Fuel Venting The following emissions standards promulgated in 14 CFR part 34, Amendment 7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for the GE Catalyst engine series. Fuel Venting Emissions Standards: 14 CFR 34.11; in addition, 40 CFR 1031.30 (b) In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the following: 1. Part II, Chapter 2 for Fuel Venting. NOTE 12. MANUFACTURER’S SERVICE BULLETINS OF SPECIAL INTEREST • 73-00-0001 Approved Fuels and Additives • 79-00-0001 Approved Oils • 72-00-0007 B-Sump Pressurization Circuit Inspection • 72-00-0008 C-Sump Pressurization Tubes Inspection • 72-00-0009 Power Turbine Stator Cooling External Hardware Inspection • 71-00-0001 Catalyst Recommended Tasks for Servicing and Inspection • 71-00-0002 Engine Event Data Collection • 72-00-0003 Hardware Exposed to Abnormal Operating Events THIS SPACE INTENTIONALLY LEFT BLANK E00100EN 7 of 8 NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS • Negative G Operation: During negative g operation only, it is permissible to operate below minimum oil pressure limits for a maximum of 5 seconds under -0.2G and maximum 2 seconds under -0.5G as outlined in the GE Catalyst Installation Manual and Operating Instructions (see Note 15). • Icing Operation: For operation in icing conditions: requirements, limitations, and notes are outlined in the GE Catalyst Installation Manual and Operating Instructions (see Note 15). NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATION • NOT APPLICABLE NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS Instructions for Continued Airworthiness (ICA) are incomplete. The aircraft must not be issued a standard airworthiness certificate until the ICA are complete and determined acceptable. The applicable installation and operating manuals are: 1. Installation Manual (IM): GEK 133915 2. Operating Instructions (OI): GEK 133916 The applicable engine shop and overhaul (ICA) manuals are: 1. Line Maintenance Manual (LMM): GEK 133909 2. Engine Shop Manual (ESM): GEK 133908 3. Time Limited Dispatch Summary: GEK 133949 4. Systems Description Section (SDS): GEK 133912 5. Standard Practices Manual (SPM): GEK 9250 6. Component Maintenance Manuals (CMM): Various GEK as published by GE 7. Abbreviated Component Maintenance Manuals (ACMM): Various GEK as published by GE 8. Service Bulletins (SB): Various as published by GE (see Note 12) NOTE 16. IMPORT REQUIREMENTS FOR FOREIGN MANUFACTURED ENGINES To be considered for installation on aircraft registered in the United States, each imported engine produced under EASA Production Organization Approval CZ.21G.0042 must be accompanied by an EASA Form 1. NOTE 17. LIFE LIMITED AND CRITICAL ENGINE PARTS Life limits established for critical engine parts are published in the Airworthiness Limitations Section (GEK 133909 Ch.5). NOTE 18. MILITARY MODEL INFORMATION (differences from civil aviation model) • NOT APPLICABLE THIS SPACE INTENTIONALLY LEFT BLANK E00100EN 8 of 8 NOTE 19. MAXIMUM PERMISSIBLE MAIN ROTOR SPEEDS AND OUTPUT SHAFT SPEED SPOOL RPM % Takeoff (5 minutes) Power turbine rotor 24,892 105.8 Gas Generator rotor 46,197 103.7 Propeller 1,809 106.4 Maximum Continuous Power turbine rotor 23,509 99.9 Gas Generator rotor 46,197 103.7 Propeller 1,709 100.5 Transient (12-sec) Power turbine rotor 25,789 109.6 Gas Generator rotor 46,509 104.4 Propeller 1,874 110.2 NOTE 20. MAXIMUM ALLOWABLE OUTPUT/PROPELLER SHAFT TORQUE LIMIT Ft-lbf Takeoff (5 minutes) 3,883 Maximum Continuous 4,111 Transient (12-sec) 4,276 NOTE 21. MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION LOCATION FLOW LIMIT – all speeds above min idle (% of physical engine air flow at compressor inlet) HPC Plane 2.5 5.5 HPC Plane 3.0 Sum HPC Planes 2.5 and 3.0 5.5 7.0 * For details of maximum permissible bleed flow extractions refer to the Catalyst Installation Manual (See Note 15). NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT • NOT APPLICABLE ----END---- ``` ## ADs None name its models. --- 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.