TCDS E17NE

* PAGE 1 2 3 4 5 6 7 8 REV. 16 16 16 15 16 16 16 16 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E17NE TCDS NUMBER E17NE REVISION: 16* DATE: October 24, 2025 PRATT & WHITNEY MODELS: PW2037 PW2037D PW2037M PW2040 PW2040D F117-PW-100 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E17NE) 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 RTX Corporation (formerly United Technologies Corporation) East Hartford, Connecticut 06108 I. MODELS PW2037 PW2040 PW2037(M) F117-PW-100 TYPE Dual Rotor, axial flow high bypass turbofan, single stage fan, four stage low pressure compressor, twelve stage high pressure compressor, annular combustor, two stage high pressure turbine, five stage low pressure turbine. RATINGS (See NOTE 5, 18 and 22) Maximum continuous at sea level, static thrust, pounds Takeoff (5 min. at sea level, static thrust, pounds) 34,640 37,530 - - 40,900 - - 37,530 - - 40,900 COMPONENTS Fuel control Collins Aerospace (formerly Hamilton Standard) Fuel pump Collins Aerospace (formerly Sundstrand) Electronic engine control Collins Aerospace (formerly Hamilton Standard) Ignition system Simmonds exciter type Two igniters: PWA P/N EEC alternator Stator: Simmonds P/N Alternate Simmonds P/N Rotor: Simmonds P/N Alternate Simmonds P/N JFC-104 025769 EEC 104 47649 IC709520 45100 --- 45099 46038 - - - - - - - - - - - - --- - - - - - - - - - - - - - - - - --- - - - - - - - - - - - - - - 46303 46998 46304 --- TCDS E17NE PAGE 2 I. MODELS (Continued) PW2040D PW2037D TYPE Dual Rotor, axial flow high bypass turbofan, single stage fan, four stage low pressure compressor, twelve stage high pressure compressor, annular combustor, two stage high pressure turbine, five stage low pressure turbine. RATINGS (See NOTE 5, 18 and 21) Maximum continuous at sea level, static thrust, pounds Takeoff (5 min. at sea level, static thrust, pounds 36,420 40,900 - - 37,530 COMPONENTS Fuel control Collins Aerospace (formerly Hamilton Standard) Fuel pump Collins Aerospace (formerly Sundstrand) Electronic engine control Collins Aerospace (formerly Hamilton Standard) Ignition system Simmonds exciter type Two igniters: PWA P/N EEC alternator Stator: Simmonds P/N Alternate Simmonds P/N Rotor: Simmonds P/N Alternate Simmonds P/N JFC-104 025870 EEC 104 47649 IC709520 45100 --- 45099 46038 - - - - - - - - - - - - --- - - - - I. MODELS PW2037 PW2040 PW2037(M) F117-PW-100 COMPONENTS (Cont.) Fuel distribution valve ExCello P/N or P/N Sta. 2.5 bleed actuator Parker Hannifin P/N Stator vane actuator Parker Hannifin P/N 14th stage bleed valve Parker Hannifin P/N 505P044 516P636 3800047 3800035 5830212 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS (INCHES) Length Nominal diameter Maximum radial projection 146.8 84.8 54.7 - - - - - - - - - - - - - - - - - - WEIGHT (DRY) (POUNDS): 7,300 - - - - 7,220 Weight of basic engine, including all essential accessories necessary for engine operation, but excluding starter, exhaust nozzle, and power source for the ignition system. CENTER OF GRAVITY (INCHES) Aft front mount area centerline Below engine centerline 21.5+1.0 2.5+0.5 - - - - - - - - 22.2+1.0 - - FUEL SEE NOTE 10 OIL SEE NOTE 11 TCDS E17NE PAGE 3 I. MODELS (Continued) PW2040D PW2037D COMPONENTS (Cont.) Fuel distribution valve ExCello P/N or P/N Sta. 2.5 bleed actuator Parker Hannifin P/N Stator vane actuator Parker Hannifin P/N 14th stage bleed valve Parker Hannifin P/N 505P044 516P636 3800047 3800035 5830212 - - - - - - - - - - PRINCIPAL DIMENSIONS (INCHES) Length Nominal diameter Maximum radial projection 146.8 84.8 54.7 - - - - - - WEIGHT (DRY) (POUNDS): 7,300 - - Weight of basic engine, including all essential accessories necessary for engine operation, but excluding starter, exhaust nozzle, and power source for the ignition system. CENTER OF GRAVITY (INCHES) Aft front mount area centerline Below engine centerline 21.5+1.0 2.9+0.5 - - - - FUEL SEE NOTE 10 OIL SEE NOTE 11 CERTIFICATION BASIS: PW2037 PW2037M PW2040 F117-PW-100 PW2240 PW2337 PW2043 PW2643 PW2143 PW2040D PW2037D FAR 33, effective February 1, 1965, as amended by 33-1/2/3/4/5/6/7/8 and 9, including Federal Aviation Administration Exemption Numbers ANE-82-001E and ANE-82-003E. Type Certificate E17NE was applied for, issued, and amended as follows: APPLICATION ISSUED AMENDED WITHDRAWN DEC 22 1980 DEC 28 1983 SEP 15 1987 SEP 21 1987 APR 21 1986 JAN 30 1987 DEC 11 1985 DEC 08 1988 DEC 17, 1991 FEB 25, 1992 JAN 06, 2005 DEC 17, 1991 FEB 25, 1992 JAN 06, 2005 DEC 05, 1994 FEB 14, 1995 OCT 24, 2025 DEC 05, 1994 FEB 14, 1995 OCT 24, 2025 FEB 24, 1995 MAR 06, 1995 OCT 24, 2025 APR 2, 2001 OCT 10, 2003 APR 2, 2001 OCT 10, 2003 The following model complies with 14 CFR part 34, amendment 5, effective December 31, 2012. See note 22, for detailed summary of the certification basis for fuel venting and exhaust emissions: PW2037. PRODUCTION BASIS. All models Production Certificate Number 2 TCDS E17NE PAGE 4 NOTES I. MODELS PW2037 PW2040 PW2037(M) F117-PW-100 NOTE 1. MAXIMUM PERMISSIBLE OPERATING SPEED FOR ENGINE ROTORS (See Note 16) Low pressure rotor (N1), RPM High pressure rotor (N2), RPM High pressure rotor (N2), RPM (5 seconds - transient) 4,575 12,250 12,335 - - 12,360 12,445 - - - - - - - - - - - - NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (See Note 15) DEGREES CENTIGRADE / FAHRENHEIT External engine component maximum limiting temperatures are specified in the Installation and Operating Handbook. TURBINE EXHAUST TEMP (T4.9) (1) oC / oF oC / oF oC / oF oC / oF (See NOTE 22) Take-off (5 minutes) Take-off (5 sec transient) Maximum continuous Maximum continuous (5 sec trans) At start-up, ground (3) At start-up, in-flight (2) 645 / 1193 660 / 1220 615 / 1139 630 / 1166 545 / 1013 645 / 1193 - - - - - - - - - - - - - - - - - - - - - - - - 655 / 1211 670 / 1238 625 / 1157 640 / 1184 555 / 1031 655 / 1211 (1) The maximum permissible exhaust gas temperatures (EGT) for Models PW2040 and PW2037(M) are indicated EGTs measured with the approved shunt resistors specified in the applicable engine manual. The actual EGT is 10oC higher than the indicated value at takeoff. (2) If during an in-flight start, the normal ground starting EGT limit is exceeded, maximum EGT and duration must be recorded. Maintenance action is required in accordance with Maintenance Manual Part Number 1A6230 for the PW2037, PW2037(M), PW2040, and 1B2413 for the F117-PW- 100. (3) Reference Maintenance Manual P/N 1A6230 for the PW2037, PW2037M, PW2040, PW2040M and IB2413 for the F117-PW-100, section 72- 00-00 for the specific ground start maximum EGT versus time temperature limit curve. OIL OUTLET TEMP oC / oF oC / oF oC / oF oC / oF Continuous operation Transient operation (20 min) 163 / 325 177 / 350 - - - - - - - - - - - - NOTE 3. FUEL PRESSURE LIMITS At inlet to engine system pump, not less than 5 psig above the true vapor pressure of the fuel and not greater than 55 psig with a vapor/liquid ratio of zero. OIL PRESSURE MINIMUM LIMITS Idle Above idle 70 psid 80 psid - - - - - - - - - - - - NOTE 4. MAXIMUM PERMISSIBLE AIR BLEED / PERCENT OF PRIMARY ENGINE AIRFLOW 10TH-STAGE HPC BLEED Idle to 30% maximum continuous Normal bleed Maximum bleed (1) Above 30% maximum continuous Normal bleed Maximum bleed (1) 0.0% 9.0% 6.0% 6.0% (3) - - - - - - - - - - - - - - - - - - - - - - 6.0% 14TH-STAGE HPC BLEED Idle to 30% maximum continuous Normal bleed Maximum bleed Above 30% maximum continuous Normal bleed Maximum bleed (1) 12.0% 12.0% (2) 0.0% 13.0% - - - - - - - - - - - - - - - - (4) (4) (4) (4) TCDS E17NE PAGE 5 I. MODELS (Continued) PW2040D PW2037D NOTE 1. MAXIMUM PERMISSIBLE OPERATING SPEED FOR ENGINE ROTORS (See Note 16) Low pressure rotor (N1), RPM High pressure rotor (N2), RPM High pressure rotor (N2), RPM (5 seconds - transient) 4,575 12,360 12,445 - - - - - - NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (See Note 15) DEGREES CENTIGRADE / FAHRENHEIT External engine component maximum limiting temperatures are specified in the Installation and Operating Handbook. TURBINE EXHAUST TEMP (T4.9) (1) oC / oF oC / oF Take-off (5 minutes) Take-off (5 sec transient) Maximum continuous Maximum continuous (5 sec trans) At start-up, ground At start-up, in-flight (2) 655 / 1211 670 / 1238 625 / 1157 640 / 1184 495 / 923 655 / 1211 - - - - - - - - - - - - (1) The maximum permissible exhaust gas temperatures (EGT) for Models PW2040 and PW2037(M) are indicated EGTs measured with the approved shunt resistors specified in the applicable engine manual. The actual EGT is 10oC higher than the indicated value at takeoff. (2) If during an inflight start, the normal ground starting EGT limit is exceeded, maximum EGT and duration must be recorded. Maintenance action is required in accordance with Maintenance Manual Part Number 1A6230 for the PW2037, PW2037(M), PW2040, PW2040D and PW2037D, 1B2413 for the F117-PW-100. OIL OUTLET TEMP oC / oF oC / oF Continuous operation Transient operation (20 min) 163 / 325 177 / 350 - - - - NOTE 3. FUEL PRESSURE LIMITS At inlet to engine system pump, not less than 5 psig above the true vapor pressure of the fuel and not greater than 55 psig with a vapor/liquid ratio of zero. OIL PRESSURE MINIMUM LIMITS Idle Above idle 70 psid 80 psid - - - - NOTE 4. MAXIMUM PERMISSIBLE AIR BLEED / PERCENT OF PRIMARY ENGINE AIRFLOW 10TH-STAGE HPC BLEED Idle to 30% maximum continuous Normal bleed Maximum bleed (1) Above 30% maximum continuous Normal bleed Maximum bleed (1) 0.0% 9.0% 6.0% 6.0% (3) - - - - - - - - 14TH-STAGE HPC BLEED Idle to 30% maximum continuous Normal bleed Maximum bleed Above 30% maximum continuous Normal bleed Maximum bleed (1) 12.0% 12.0% (2) 0.0% 13.0% - - - - - - - - TCDS E17NE PAGE 6 NOTE 4. (Continued) PW2037 PW2040 PW2037(M) F117-PW-100 PW2040D PW2037D MAXIMUM PERMISSIBLE AIR BLEED / PERCENT OF PRIMARY ENGINE AIRFLOW 17TH- STAGE HPC BLEED Idle to 30% maximum continuous Normal bleed Maximum bleed (1) Above 30% maximum continuous Normal bleed Maximum bleed (1) --- --- --- --- --- --- --- --- --- --- --- --- 12.0% 12.0% (5) 0.0% 12.0% -- -- -- -- (1) Usable only when required by malfunction and only until next landing. (2) 13% allowable with 0% 10th-stage bleed. (3) 9% allowable with 0% 14th-stage bleed. (4) When primary source of aircraft system bleed air is from 10th-and 17th stage HPC bleeds as shown in the table, supplement bleed air may be extracted continuously from the 14th stage bleed up to 0/5% of primary engine airflow. (5) When altitude less than 30,000 feet and corrected HPC speed (N2C2) less than 9,600 rpm, the 17th-stage maximum bleed amount equals 14%. NOTE 5. Ratings are based on static test stand operation under the following conditions: Compressor inlet air at 15oC / 59oF and 29.92 in. Hg. Engine air inlet TAM 168397, primary exhaust nozzle TAM 168399, fan exhaust nozzle TAM 168400, and exhaust cone TAM 168422. No aircraft accessory loads or bleed air extraction. Turbine outlet gas temperature limits and engine rotor speed limits not exceeded. NOTE 6. ACCESSORY DRIVE PROVISIONS ROTATION (1) SPEED RATIO TO TURBINE SHAFT TORQUE (lb-in) OVERHANG (in-lb) CONTINUOUS STATIC OVERLOAD High pressure rotor Starter IDGS Fluid power Pump (R) Pump (L) (3) CCW CCW CCW CCW 0.800:1 0.728:1 0.315:1 0.315:1 - - (4) 1300 1300 (2) 12620 6500 6500 - - (4) 1950 1950 500 2000 400 400 (1) CW = Clockwise / CCW = Counterclockwise (2) Maximum starter torque equals 970 lb.-ft. at zero rpm. Maximum allowable starter torque value is 2231 lb.-ft. 3) Applicable to Models F117-PW-100 4) Maximum allowable continuous torque values at any engine speed are equivalent to 175 horsepower. For an overload it is 225 horsepower. NOTE 7. Power setting, power checks, and control of engine output in all operations are to be based upon Pratt & Whitney engine charts referring to either engine pressure ratio or low rotor speeds. Pressure probes and low rotor speed sensor are included in the engine assembly for this reason. NOTE 8. For inflight operation during icing conditions, the minimum allowable fan speed (N1) is 22% (1000 rpm). TCDS E17NE PAGE 7 NOTE 9. Lightning protection requirements and electromagnetic interference emitted by the Electronic Engine Control System (EECS), including cables, are specified in the Installation and Operating Handbook. NOTE 10. Fuels and fuel additives conforming to the FAA-approved Pratt & Whitney Turbojet Engine Service Bulletin Number 2016, latest revision, may be used separately or mixed in any proportion without adversely affecting the operation or power output. NOTE 11. The following oils are eligible: Oils conforming to Pratt & Whitney Turbojet Engines Service Bulletin Number 238, latest revision. NOTE 12. Certain engine parts are life-limited. These limits are listed in the time limit sections of the following Pratt & Whitney Engine Manuals: For the PW2037 / PW2037(M) / PW2040 / PW2040D / PW2037D Engine Manual P/N 1A6231 For the F117-PW-100 Engine Manual P/N 1B2412 NOTE 13. All of these models meet fuel venting and exhaust emission requirements of 14 CFR Part 34, Amendment 3, dated February 3, 1999. NOTE 14. The maximum permissible engine inlet distortion limits for these models are specified in the Installation and Operating Handbook. Inlet distortion on an installed engine must be determined by the method of measurement specified in the Installation and Operating Handbook or an equivalent method in order to verify that the installed engine is within the limits. NOTE 15. Limits regarding transient rotor shaft overspeed and transient gas overtemperature and number of occurrences are specified in the following Pratt & Whitney Maintenance Manuals: For the PW2037 / PW2037(M) / PW2040 / PW2040D / PW2037D Maintenance Manual P/N 1A6230 For the F117-PW-100 Maintenance Manual P/N 1B2413 NOTE 16. Information regarding approved fuel filter and oil filter replacement parts is specified in the following PW2000 Series Illustrated Parts Catalog (IPC): For the PW2037 / PW2037(M) / PW2040 / PW2040D / PW2037D IPC P/N 1A6232 For the F117-PW-100 IPC P/N 1B2441 TCDS E17NE PAGE 8 NOTE 17. PW2037 PW2040 PW2037(M) F117-PW-100 PW2040D PW2037D CHARACTERISTICS Takeoff rating of 37, 530 pounds at and below 87oF / 30oC ambient temperature sea level static. Maximum continuous rating of 34,640 pounds at and below 77oF / 25oC ambient temperature sea level static. Basically same as PW2037, except takeoff rating of 40,900 pounds at and below 87oF / 30oC ambient temperature sea level static, and minor hardware changes. Same as PW2040, except operated at PW2037 ratings via appropriate electronic engine control data entry plug. Basically the same as PW2040, except addition of stage 17 cabin air bleed, a second hydraulic pump drive and external plumbing changes. Same as supercharged PW2040 ratings via appropriate electronic engine control data entry plug. Same as supercharged PW2037 ratings via appropriate electronic engine control data entry plug. NOTE 18: REMOVED NOTE 19. Pratt & Whitney document number FR-22024 (latest revision), titled "Configuration Management Accounting Report", is a cross reference list of commercial (PW2000 engine series) service bulletins and their military equivalent (F117 engine model). This document is updated monthly. NOTE 20. Ground operation in icing condition requires adherence to procedures stated in Aircraft Flight Manual (AFM) for all engine models. These procedures include periodic speed run ups and/or inspections and de-icing procedures (reference applicable AFM for details). NOTE 21. NOTE 22. The 5 minute takeoff time limit may be extended to 10 minutes for one engine(s) inoperative or shutdown. The following emissions standards promulgated in 14 CFR Part 34, Amendment 5, effective December 31, 2012, and 40 CFR Part 87, effective July 18, 2012, have been complied with for: PW2037. Fuel Venting Emission Standards: 14 CFR §§ 34.10 (a) and 34.11; in addition, 40 CFR §§ 87. 10(a) and 87.11. Smoke Number (SN) Emission Standards: 14 CFR §34.21 (e)(2); in addition, 40 CFR § 87.23(c)(1). Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(1)(ii); in addition, 40 CFR § 87.23(c)(l). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(l)(i); in addition, 40 CFR § 87.23(c)(l). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(a)(2); in addition, 40 CFR § 87.23(c)(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, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2.d.3 for NOx (also known as CAEP/6), and Part II Chapter 2 for fuel venting have also been demonstrated. ----END----