TCDS E00090EN

PAGE 1 2 3 4 5 6 7 8 REV. 13 13 13 13 8 13 13 5 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U. S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00090EN TCDS NUMBER E00090EN Revision 13 Pratt & Whitney MODELS: PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G-RC, PW1919G, PW1921G-RC, PW1921G, PW1922G, PW1923G, PW1923G-A Date: June 12, 2026 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00090EN) 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: Pratt & Whitney 400 Main Street East Hartford, CT 06118 TYPE CERTIFICATE HOLDER RECORD: Pratt & Whitney Canada Corporation Transferred TC E00090EN to Pratt & Whitney on December 6, 2016 TYPE High bypass ratio, axial-airflow, dual-spool, turbofan engine controlled by a Full Authority Digital Electronic Control (FADEC). The low pressure spool consists of a three-stage low pressure turbine that directly drives a three-stage low pressure compressor, and a single stage high bypass ratio fan through a fan drive gear speed reduction system. The high pressure compressor has eight axial stages driven by a two-stage cooled high pressure turbine. MODELS: PW1519G PW1521G, PW1521G-3, PW1521GA PW1524G, PW1524G-3, PW1525G, PW1525G-3 RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Takeoff (5 minutes) (See NOTE 2) Maximum Continuous 19,775 18,685 21,970 20,760 24,400 23,050 FLAT RATING AMBIENT TEMPERATURE Takeoff Maximum Continuous 30°C / 86°F 25°C / 77°F 30°C / 86°F 25°C / 77°F 30°C / 86°F 25°C / 77°F Data Storage Unit PN (Ratings Plug) 5325208 or 5327258 5325206 or 5327259 (PW1521G) 5325207 or 5327261 (PW1521G-3) 5325781 or 5327264 (PW1521GA) 5325211 or 5327260 (PW1524G) 5325205 or 5327263 (PW1524G-3) 5325209 or 5327257 (PW1525G) 5325212 or 5327262 (PW1525G-3) TCDS E00090EN Page 2 of 8 MODELS: PW1919G-RC, PW1919G PW1922G PW1921G-RC, PW1921G, PW1923G-A, PW1923G RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Normal Takeoff (5 minutes) (See NOTE 2) Maximum Takeoff (5 minutes) (See NOTE 2) Maximum Continuous 20,860 22,550 20,305 23,815 23,815 20,305 22,550 (PW1921G-RC) 22,550 (PW1921G) 23,815 (PW1923G-A) 23,815 (PW1923G) 24,110 21,805 FLAT RATING AMBIENT TEMPERATURE Normal Takeoff Maximum Takeoff Maximum Continuous 30°C / 86°F 30°C / 86°F 25°C / 77°F 35°C / 95°F 35°C / 95°F 25°C / 77°F 30°C / 86°F (PW1921G-RC) 30°C / 86°F (PW1921G) 30°C / 86°F (PW1923G-A) 35°C / 95°F (PW1923G) 33°C / 92°F (PW1921G-RC) 33°C / 92°F (PW1921G) 34°C / 93°F (PW1923G-A) 34°C / 93°F (PW1923G) 25°C / 77°F Data Storage Unit PN (Ratings Plug) 5332185 (PW1919G-RC) 5327459 or 5327587 (PW1919G) 5327453 or 5327578 5332186 (PW1921G-RC) 5322353 or 5327583 (PW1921G) 5328019 (PW1923G-A) 5322354 or 5327584 (PW1923G) COMPONENTS/CONFIGURATION For PW1500G information rega rding components and engine configuration, refer to: Installation Drawing 5310001 For PW1900G information regarding components and engine configuration, refer to: Installation Drawing 5350001 TCDS E00090EN Page 3 of 8 MODELS: (cont.) PW1519G PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3 PW1919G, PW1921G, PW1922G, PW1923G-A, PW1923G PRINCIPAL DIMENSIONS (Room temperature) Length (flange to flange, in.) Length (fan spinner face to aft flange, in.) Nominal diameter (fan case, in.) Maximum radial projection (in.) (at drain mast) CENTER OF GRAVITY (in.) Axial engine station, relative to A-flange: Vertical, relative to engine centerline: Lateral, relative to centerline: 119.9 125.4 79.0 45.7 58.5 -0.5 -1.0 -- -- -- -- -- -- -- -- -- -- -- -- -- -- WEIGHT (DRY) Basic engine (lbs.) with P&W supplied Standard Equipment 4,800 -- -- FUEL Service Bulletin PW1000G-A-73-00-0010-00A-930A- D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the PW1500G series turbofan engine. Service Bulletin PW1000G-A-73-00-0001-00B-930A-D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the PW1900G series turbofan engine. LUBRICATING OILS Service Bulletin PW 1000G-A-79-00-0001-00A-930A-D provides a listing of approved turbine oils for use in the PW1500G series turbofan engine. Service Bulletin PW1000G-A-79-00-0001-00B-930A-D provides a listing of approved turbine oils for use in the PW1900G series turbofan engine. CERTIFICATION BASIS PW1500G Engine Models: 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 with the following Equivalent Level of Safety findings:  33.78(a)(1), Rain and Hail Ingestion, documented in ELOS Memorandum No. TC3047EN-E-P-5-R1  33.201(c) and (e), Design and Test Requirements for Early ETOPS eligibility, documented in ELOS Memorandum No. TC3047EN-E-P-11 PW1900G Engine Models: 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 with the following Equivalent Level of Safety findings:  33.78(a)(1), Rain and Hail Ingestion, documented in ELOS Memorandum No. TC3047EN-E-P-5-R1  33.27(c) and (e), Turbine, Compressor, Fan, and Turbo supercharger Rotor Overspeed, documented in ELOS Memorandum No. MEC19CZ145-P-1 The following models comply with 14 CFR Part 34, Amendment 7A, effective May 24, 2024. See NOTE 11 for detailed summary of the certification basis for fuel venting and exhaust emissions: PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G-RC, PW1919G, PW1921G-RC, PW1921G, PW1922G, PW1923G, PW1923G-A TCDS E00090EN Page 4 of 8 TYPE CERTIFICATE NUMBER E00090EN MODEL APPLICATION ISSUED/AMENDED DELETED PW1519G February 3, 2013 January 22, 2016 PW1521G February 8, 2010 January 22, 2016 PW1524G February 8, 2010 January 22, 2016 PW1525G December 12, 2013 January 22, 2016 PW1521G-3 September 14, 2016 October 31, 2016 PW1524G-3 September 14, 2016 October 31, 2016 PW1525G-3 September 14, 2016 October 31, 2016 PW1919G November 9, 2016 April 28, 2017 PW1921G November 9, 2016 April 28, 2017 PW1922G November 9, 2016 April 28, 2017 PW1923G November 9, 2016 April 28, 2017 PW1521GA May 3, 2017 January 29, 2018 PW1923G-A June 6, 2018 November 27, 2018 PW1919G-RC July 15, 2024 June 8, 2026 PW1921G-RC July 15, 2024 June 8, 2026 PRODUCTION BASIS (All Models) PW1500G Engine Serial Numbers P735922-P735942 are produced by Pratt & Whitney Canada Corp. under Transport Canada Certificate of Management Approval 4-58. PW1500G Engine Serial Numbers P735943 and up will be produced by Pratt & Whitney under Production Certificate 02. PW1900G Engine Serial Numbers P783014 and up will be produced by Pratt & Whitney under Production Certificate 02. NOTES NOTE 1. NOTE 2. ENGINE RATINGS (all models): Engine ratings are based on calibrated test stand performance under the following conditions: 1. Sea level static, standard pressure (14.696 psia), up to the flat rating ambient temperature °F 2. No customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery 4. Production aircraft flight cowling 5. Production instrumentation 6. Fuel lower heating value of 18,400 BTU/lb. TEMPERATURES (all models): Maximum permissible Indicated Turbine Temperatures (ITT) are as follows: Takeoff (5 minutes)* 1,054 degC / 1,929 degF Maximum Continuous 1,017 degC / 1,863 degF *The normal and maximum 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. Indicated Turbine Temperatures (ITT) at start-up 1,054 degC / 1,929 degF Oil outlet temperature (all models): Continuous operation: 163 degC / 325 degF. Maximum oil temperature 174 degC / 345 degF for up to 20 minutes. Total operation between 163 degC / 325 degF and 174 degC / 345 degF cannot exceed 20 minutes. See PW1500G Installation and Operating Manual, PWA-8828 and PW1900G Installation and Operating Manual, PWA-10649 for details. PW1500G: Minimum oil temperature at idle, before takeoff power operation: 48 degC / 118 degF Minimum oil temperature for ground operation: 21 degC / 70 degF. PW1900G: Minimum oil temperature at idle, before takeoff power operation: 49 degC / 120 degF Minimum oil temperature for ground operation: 21 degC / 70 degF. PW1500G: Fuel Temperatures: See Installation and Operating Manual, PWA-8828 Component Temperatures: See Installation and Operating Manual, PWA-8828 TCDS E00090EN Page 5 of 8 NOTE 2 – cont’d. NOTE 3. PW1900G: Fuel Temperatures: See Installation and Operating Manual, PWA-10649 Component Temperatures: See Installation and Operating Manual, PWA-10649 PRESSURES (all models): Fuel pressure limits: Fuel pressure at the engine fuel pump inlet during operation shall be maintained at not less than 5.0 psi above the true vapor pressure of the fuel but not greater than 100 psi above the absolute ambient pressure with a vapor/liquid ratio of zero. The maximum allowable pressure at the fuel pump inlet after shutdown is 120 psig. Oil pressure limits: Minimum: 50 psig at idle. Variable by N2 Speed off idle. See PW1500G Installation and Operating Manual, PWA-8828 and PW1900G Installation and Operating Manual, PWA-10649. Maximum: 235 psig cold high MOP limit for MOT < 49 degC / 120 degF Otherwise, 175 psig. Oil supply pressure is measured relative to main lube pressure. Temporary interruption associated with negative “g” operation is limited to 7 seconds maximum. Normal oil pressure will be restored rapidly once the negative “g” effect has been eliminated. NOTE 4. NOTE 5. ACCESSORY DRIVE PROVISIONS: MODEL DESCRIPTION: The PW1500G engine series consist of the following engine models: PW1519G Bombardier CS100 reduced thrust model PW1521G Bombardier CS100 reduced thrust model PW1521GA Bombardier CS100 reduced climb thrust model PW1524G Bombardier CS100 basic model PW1525G Bombardier CS100 alternate climb thrust model PW1521G-3 Bombardier CS-300 reduced thrust model PW1524G-3 Bombardier CS-300 basic model PW1525G-3 Bombardier CS-300 alternate climb thrust model PW1500G ACCESSORY DRIVES Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overloa d Static Hydraulic Pump Variable Frequency Generator (VFG) CW CW 0.1835 : 1 0. 8595: 1 810 560 * 1650 1620 * 3600 5500 175 925 CW = Clockwise (facing the drive pad) * Maximum allowable continuous torque values are at any engine speed unless otherwise specified provided no destructive forces resulting from accessory torsional vibration are present. Maximum allowable continuous overhung bending moments of accessories about drive face are as shown provided no destructive forces resulting from vibration are present. PW1900G ACCESSORY DRIVES Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overloa d Static Hydraulic Pump Integrated Drive Generator (IDG) CW CW 0.1835 : 1 0. 8595: 1 420 280 1400 1120 3600 5500 185.5 925 CW = Clockwise (facing the drive pad) * Maximum allowable continuous torque values are at any engine speed unless otherwise specified provided no destructive forces resulting from accessory torsional vibration are present. Maximum allowable continuous overhung bending moments of accessories about drive face are as shown provided no destructive forces resulting from vibration are present. TCDS E00090EN Page 6 of 8 NOTE 5 – cont’d. NOTE 6. NOTE 7. NOTE 8. NOTE 9. NOTE 10. The PW1900G engine series consist of the following engine models: PW1919G-RC Embraer El 90-E2 model PW1921G-RC Embraer El 95-E2 model PW1919G Embraer E190-E2 model PW1921G Embraer E195-E2 model PW1922G Embraer E190-E2 model PW1923G Embraer E195-E2 model PW1923G-A Embraer E195-E2 model TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS: Not Applicable ENGINE MOUNT SYSTEM PROVISIONS: PW1500G Engine mount system provisions are specified in Installation Drawing 5310001 and Mount and Maneuver Load Drawing, 5310003. PW1900G Engine mount system provisions are specified in Installation Drawing 5350001 and Mount and Maneuver Load Drawing, 5350003. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: ETOPS: The PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, and PW1525G-3 engine models have complied with the requirements of §§ 33.4 (A33.3(c)), 33.71(c)(4) and 33.201, except for the requirements of 33.201(c) and (e) which were met by an equivalent level of safety, and are therefore eligible for installation on Extended Operations (ETOPS) and Early ETOPS approved airplanes. The demonstrated diversion time is 180 minutes at MCT plus 15 minutes at hold power. Note that ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. The PW1900G Engine models are not eligible for Early Extended Twin Engine Operations (ETOPS) Operation. Time Limited Dispatch: The PW1500G and PW1900G Engine Series are certified with Time Limited Dispatch. Criteria pertaining to the engine control systems’ dispatch and maintenance requirements for the PW1500G engine models installed on the Bombardier C Series Aircraft are specified in their Airworthiness Limitations Manuals PN 5305816 and PWA-11078 “PW1500G / Time Limited Dispatch Fault Message / Dispatch Category Cross-Reference Report” Criteria pertaining to the engine control systems’ dispatch and maintenance requirements for the PW1900G engine models installed on the Embraer E190/E195 Aircraft are specified in their Airworthiness Limitations Manual 5321709 and PWA-10710 “PW1900G Degraded Dispatch Maintenance Message / Dispatch Category Cross-Reference”. FADEC System faults fall into four categories as follows: A) No Dispatch, B) Short Term Dispatch, C) Long Term Dispatch, or D) Fix at Operators Discretion. Details on the short and long term dispatch intervals are provided in the Airworthiness Limitations Manual (See NOTE 15). Thrust Reverser: The thrust reverser is not part of the engine type design and is certified as part of the aircraft. Information for installation of a thrust reverser is contained in the Installation and Operating Manual (See NOTE 15). TCDS E00090EN Page 7 of 8 NOTE 11 – cont’d. NOTE 12. NOTE 13. NOTE 14. NOTE 15. 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 PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G-RC, PW1921G-RC, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engine models. Fuel Venting Emission Standards: 14 CFR §§ 34.10(a) and 34.11; in addition, in addition, 40 CFR § 1031.30(b)(2). Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(l)(ii); in addition, in addition, 40 CFR § 1031.60(d). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 1031.60(c) Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(l); in addition, in addition 40 CFR § 1031.60(e)(5). Non-volatile particulate nvPM mass concentration (nvPMMC): 14 CFR § 34.25(a)(1); in addition 40 CFR § 1031.60(a)(6). Non-volatile particulate nvPM mass (nvPMmass) & nvPM number (nvPMnum) : 14 CFR § 34.25(a)(2); in addition 40 CFR § 1031.60(b)(2). 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: • Part II, Chapter 2 for Fuel Venting • Part III, Chapter 2, Section 2.2.2 for Smoke Number • Part III, Chapter 2, Section 2.3.2 for Carbon Monoxide and Hydrocarbons • Part III, Chapter 2, Section 2.3.2 for Oxides of Nitrogen (also known as CAEP/8), and • Part III, Chapter 4, Section 4.2.2 for non-volatile Particulate Matter (also known as CAEP/10 & CAEP/11) Electromagnetic Protection: Lightning protection requirements and electromagnetic interference emitted by the electronic engine control system, including cables, are specified in the Installation and Operating Manual (See NOTE 15). MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Not Applicable SPECIAL OPERATING PROCEDURES: The minimum N1 certified for in-flight operation in icing conditions is 1,991 rpm. The Electronic Engine Control will prevent rotor speeds below this value while in flight. Requirements and limitations for ground operation in icing conditions are specified in the Installation and Operating Manual (See NOTE 15). SPECIAL REPAIR OR OVERHAUL LIMITATIONS: Not Applicable APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: PW1500G: The following manuals have been approved under the requirements of 14 CFR § 33.5: 1) Installation and Operating Manual, PWA-8828 The following Instructions for Continued Airworthiness (ICA) have been approved or accepted under the requirements of 14 CFR § 33.4 1) Airworthiness Limitation Manual, PN 5305816 2) Engine Maintenance Manual (EMM), PN 5305818 3) Engine Manual (EM), PN 5305815 4) Cleaning, Inspection, Repair Manual (CIR), PN 5305817 5) Fault Isolation Procedures Manual (FIM), PN 5319822 6) Standard Practices Manual (SPM), PN 585005 7) Special Procedures - Fan Drive Gear System (FDGS) Manual, PN 5317957 8) Special Procedures - High Pressure Compressor (HPC) Module, PN 5317961 9) Special Procedures - High Pressure Turbine (HPT) Module, PN 5317960 10) Special Procedures - High Pressure Turbine (HPT) Core, PN 5324688 11) Special Procedures - High Pressure Turbine (HPT) Nut, PN 5324694 12) Component Maintenance Manuals (CMM) PW1900G: The following manuals have been approved under the requirements of 14 CFR § 33.5: 1) Installation and Operating Manual, PWA-10649 TCDS E00090EN Page 8 of 8 NOTE 15 – cont’d. NOTE 16. NOTE 17. NOTE 18. NOTE 19. NOTE 20. NOTE 21. NOTE 22. The following Instructions for Continued Airworthiness (ICA) have been approved or accepted under the requirements of 14 CFR § 33.4 1) Airworthiness Limitation Manual, PN 5321709 2) Engine Maintenance Manual (EMM), PN 5321705 3) Engine Manual (EM), PN 5321708 4) Cleaning, Inspection, Repair Manual (CIR), PN 5321706 5) Fault Isolation Procedures Manual (FIM), PN 5324697 6) Standard Practices Manual (SPM), PN 585005 7) Special Procedures - Fan Drive Gear System (FDGS) Manual, PN 5321702 8) Special Procedures - High Pressure Compressor (HPC) Module, PN 5321703 9) Special Procedures - High Pressure Turbine (HPT) Module, PN 5321704 10) Special Procedures - High Pressure Turbine (HPT) Core, PN 5324689 11) Special Procedures - High Pressure Turbine (HPT) Nut, PN 5324695 12) Component Maintenance Manuals (CMM) IMPORT REQUIREMENTS: To be considered eligible for installation on United States (U.S.) registered aircraft, each engine to be exported to the U.S. shall be accompanied by a certificate of airworthiness for export or by a certifying statement, endorsed by the exporting cognizant civil airworthiness authority and containing the following language: 1. This engine conforms to its Type Certificate Number E00090EN and is in a condition for safe operation. 2. This engine has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. LIFE LIMITED PART INFORMATION: PW1500G life limits for critical components and mandatory inspection requirements are specified in the PW1500G Airworthiness Limitation Manual PN 5305816. PW1900G life limits for critical components and mandatory inspection requirements are specified in the PW1900G Airworthiness Limitation Manual PN 5321709. MILITARY MODEL INFORMATION: Not Applicable ROTOR SPEEDS: Maximum permissible Low Pressure Rotor (N1): 10,600 rpm Minimum Low Pressure Rotor (N1), Flight Idle: 1,991 rpm Ground Idle: 1,574 rpm (See Note 13) Maximum permissible High Pressure Rotor (N2): 24,470 rpm Minimum High Pressure Rotor (N2), Ground Idle: 13,264 rpm Flight Idle: 13,264 rpm Power setting, power checks, and control of engine thrust output in all operations are based on Low Rotor Speed (N1). Fan Speed, (NFAN) is directly proportional to Low Rotor Speed (N1) by a gear ratio of 1: 3.0625. OUTPUT/PROPELLER SHAFT TORQUE LIMITS: Not Applicable. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: Maximum Permissible Bleed Air Extraction limits are specified in the PW1500G Installation and Operating Manual, PWA-8828, and PW1900G Installation and Operating Manual, PWA-10649. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply): Not Applicable. ---END---