TCDS E46NE

* PAGE 1 2 3 4 5 6 7 REV. 9 9 9 9 9 9 9 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 E46NE TCDS NUMBER E46NE REVISION: 9 DATE: January 28, 2026 PRATT & WHITNEY MODELS: PW4074 PW4074D PW4077 PW4077D PW4084 PW4084D PW4090 PW4090-3 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E46NE) 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) 400 Main Street East Hartford, Connecticut 06118 I. MODELS PW4074 PW4077 PW4084 TYPE Axial airflow, dual-spool, turbofan, single- stage fan, 6-stage low-pressure compressor, 11-stage high pressure compressor, annular combustor, 2-stage high-pressure turbine, 7-stage low-pressure turbine. RATINGS (See NOTE 5) Static thrust at sea level, lbs. Takeoff, Dry 5 Minutes (See NOTE 18) Maximum Continuous 77,440 69,600 79,960 70,990 86,760 70,990 COMPONENTS Fuel Metering unit Fuel pump and filter Electronic engine control (EEC) Ignition Exciter Ignitors Collins Aerospace (formerly Hamilton Standard) Model Number JFC-131-4 Argo-Tech Model 723300 Collins Aerospace (formerly Hamilton Standard) EEC 170 P/N 812460-All Unison Industries P/N 10-621630-1 Auburn P/N 0270408 Champion P/N AA1345-1 TCDS E46NE PAGE 2 I. MODELS (CONT.) PW4074 PW4077 PW4084 COMPONENTS (CONT.) EEC alternator Stator Rotor Fuel distribution valve Station 2.5 bleed actuator Stator vane actuator PT2/TT2 probe Unison (formerly B.F. Goodrich) P/N 430073 Unison (formerly B.F. Goodrich) P/N 430074 Collins Aerospace (formerly Hamilton Standard) P/N GTA40 Collins Aerospace (formerly Hamilton Standard) P/N GTA42 Collins Aerospace (formerly Hamilton Standard) P/N GTA41 Rosemount P/N 154 GT PRINCIPAL DIMENSIONS Room Temperature Length (flange to flange) Nominal diameter (fan case) Maximum radial projection (oil tank) 190.423 (in.) 119.000 (in.) 69.946 (in.) WEIGHT (DRY) 15,095 Weight of basic engine includes PW supplied engine build-up components. CENTER OF GRAVITY (IN) Axial: Engine station Vertical: Relative to engine Lateral: Relative to centerline 117.2 + 1.0 -1.4 + 0.5 -0.6 + 0.5 II. MODELS PW4074D PW4077D PW4084D PW4090 PW4090-3 TYPE Axial airflow, dual-spool, turbofan, single- stage fan, 6-stage low-pressure compressor, 11-stage high pressure compressor, annular combustor, 2-stage high-pressure turbine, 7-stage low-pressure turbine. RATINGS (See NOTE 5) Static thrust at sea level, lbs. Takeoff, Dry 5 Minutes (See NOTE 18) Maximum Continuous 77,440 69,600 79,960 70,990 86,760 70,990 91,790 74,950 91,790 (See Note 19) 74,950 COMPONENTS Fuel Metering unit Fuel pump and filter Electronic engine control (EEC) Ignition Exciter Ignitors Collins Aerospace (formerly Hamilton Standard) Model Number JFC-131-4 Argo-Tech Model 723300 Collins Aerospace (formerly Hamilton Standard) EEC 170 P/N 816200-All Unison Industries P/N 10-621630-2 Auburn P/N 0270307 Champion P/N AA72S COMPONENTS (CONT.) EEC alternator Stator Rotor Fuel distribution valve Station 2.5 bleed actuator Stator vane actuator PT2/TT2 probe Unison (formerly B.F. Goodrich) P/N 430073 Unison (formerly B.F. Goodrich) P/N 430074 Collins Aerospace (formerly Hamilton Standard) P/N GTA40-1 Collins Aerospace (formerly Hamilton Standard) P/N GTA42-2 Collins Aerospace (formerly Hamilton Standard) P/N GTA41-1 Rosemount P/N 154GT TCDS E46NE PAGE 3 II. MODELS (CONT.) PW4074D PW4077D PW4084D PW4090 PW4090-3 PRINCIPAL DIMENSIONS Room Temperature Length (flange to flange) Nominal diameter (fan case) Maximum radial projection (oil tank) 190.423 (in.) 119.000 (in.) 69.946 (in.) WEIGHT (DRY) 15,741 Weight of basic engine includes PW supplied engine build-up components. CENTER OF GRAVITY (IN) Axial: Engine station Vertical: Relative to engine Lateral: Relative to centerline 119.0+1.0 -1.2+0.5 -0.5+0.5 FUEL See NOTE 9 OIL See NOTE 10 CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1 through 33-15 Type Certificate Number E46NE MODEL APPLICATION ISSUED WITHDRAWN PW4074 DEC 10, 1990 APR 29, 1994 PW4077 DEC 10, 1990 APR 29, 1994 PW4084 DEC 10, 1990 APR 29, 1994 PW4074D MAR 17, 1998 MAR 27, 1998 PW4077D JUN 19, 1996 JUN 28, 1996 PW4084D JUN 19, 1996 JUN 28, 1996 PW4090 JUL 28, 1994 JUN 28, 1996 PW4090-3 JAN 22, 1999 APR 8, 1999 PW4090D JUL 23, 1998 JUL 24, 1998 JAN 28, 2026 PW4098 JUL 25, 1995 JUL 24, 1998 JAN 28, 2026 PRODUCTION BASIS (All Models) Production Certificate Number 2 NOTES NOTE 1. Maximum Permissible Operating Speeds for Engine Rotors PW4074/PW4077/ PW4077D/PW4084D/ PW4084 PW4090/PW4074D/ PW4090-3 Low pressure rotor (N1), RPM 2,990 3,045 High pressure rotor (N2), RPM 10,850 10,850 -transient (25 seconds) - s t e a d y s t a t e Minimum Permissible Operating Speeds for Engine Rotors Low pressure rotor (N1), RPM 590 (In-flight) High pressure rotor (N2), RPM 5,900 (In-flight and on ground operation) TCDS E46NE PAGE 4 NOTE 2. Maximum Permissible Temperatures For in-flight starts which result in exceedance of the ground start limit, the maximum temperature and duration must be recorded for maintenance action, per the PW4000-112 series Engine Maintenance Manual. External engine component maximum limiting temperatures are specified in the Installation and Operating Manual, Section 4.3. Turbine Exhaust gas temperature PW4074/PW4077/ PW4077D/PW4084D/ PW4084 PW4090/PW4074D/ PW4090-3 At takeoff (5 minutes, see NOTE 18) 625 oC/1157oF 675 oC/1247oF Maximum continuous 605 oC/1121oF 650 oC/1202oF At start-up Ground 535 oC/995oF 535 oC/995oF In-flight 625 oC/1157oF 675 oC/1247oF Oil outlet temperature Continuous operation 163 oC/325oF 163 oC/325oF Transient operation (20 min.) 177 oC/350oF 177 oC/350oF NOTE 3. Fuel Pressure Limits: At inlet to engine system pump, not less than 3.25 psi above the true vapor pressure of the fuel and not greater than 70 psig with a vapor/liquid ratio of zero. Oil Pressure Limits: Minimum 70 psig Temporary interruption of oil pressure associated with negative "G" operation is limited to 30 seconds maximum. Normal oil pressure will be restored rapidly once the negative "G" effect has been eliminated. There is no maximum oil pressure limit. NOTE 4. Maximum Permissible Air Bleed: 11.4 pounds/second airflow - PW4074, PW4077 and PW4084 10.7 pounds/second airflow - PW4077D, PW4084D, PW4090, PW4090-3, a n d P W 4 0 7 4 D NOTE 5. The Sea Level Static Ratings ar e ideal and are based on ICAO Standard Atmosphere conditions, a Pratt & Whitney ideal inlet, no fan or compressor air bleed or load on accessory drives, an exhaust system having no internal pressure or external scrubbing losses, and fan duct and primary nozzle velocity coefficients equal to 1.0. TCDS E46NE PAGE 5 NOTE 6. The following accessory drive provisions are incorporated: TORQUE (lb-in) DRIVE ROTATION SPEED RATIO TO TURBINE SHAFT CONTINUOUS STATIC OVERLOAD OVERHANG (in-lb) High pressure rotor Starter IDGS Fluid power pump (R) VSCF CCW CCW CCW CCW 0.841:1 0.841:1 0.391:1 2.435:1 - - - ** 1,500 *** * 10,500 6,500 4,500 - - - ** 1,950 *** 500 2,000 400 400 LEGEND: CCW = counterclockwise * Maximum starter continuous torque = 1050 lb-ft at zero rpm and 1,250 lb-ft maximum impact torque. Maximum allowable starter torque value is 1,498 - 1,732 lb-ft. ** Maximum allowable continuous torque values are equivalent to 243 horsepower at any engine speed at or above sea level idle. The following overload conditions can be accommodated: HORSEPOWER DURATION TIME RECURRING TIME 304 5 minutes 1,000 hours 304 5 seconds 1 hour 500 5 seconds 1,000 hours *** Maximum allowable continuous torque values are equivalent to 58 horsepower at any engine speed at or above sea level idle. The following overload conditions can be accommodated: HP DURATION TIME RECURRING TIME (HRS) 87 5 min 1000 87 5 sec 1 128 5 sec 1000 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 turbine discharge section gas pressure or low rotor speed. Pressure probes and a low rotor speed sensor are included in the engine assembly for this reason. NOTE 8. Lightning protection re quirements and electromagnetic interference emitted by the electronic engine control system, including cables, are specified in the Installation and Operating Manual, Section 5.12. NOTE 9. Fuel and fuel additives conformi ng to the latest applicable issue of FAA-approved Pratt & Whitney Turbojet Engine Service Bulletin No. 2016 may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. NOTE 10. The following oils are eligible: Oils conforming to Pratt & Whitney Turbojet Engine Service Bulletin No. 238, latest revision. TCDS E46NE PAGE 6 NOTE 11. Certain engine parts are life limited. Limits are lis ted in Pratt & Whitney PW4000-112 series engine Turbofan Engine Manual, Part Number 51A345, time limit section for models PW4074, PW4077 and PW4084 and Part Number 51A751 for models PW4077D, PW4084D, PW4090, PW4090-3, and PW4074D. NOTE 12. The engines meet the smoke and gaseous emission requirements of Part 34. NOTE 13. The maximum permissible engine inlet distortion limit is specified in the Installation and Operating Manual, Section 5.4, Report PWA-6510-09. NOTE 14. Limits regarding transient ro tor shaft overspeed rpm and transient gas overtemperature and the number of overtemperature occurrences are specified in the Maintenance Document, Part No. 51A344. NOTE 15. Information regarding approved fuel filter and oil filter replacement is in the PW4000 Series Illustrated Parts Catalog, Part Number 51A346 for models PW4074, PW4077 and PW4084 and Part Number 51A742 for models PW4077D, PW4084D, PW4090, PW4090-3, and PW4074D. NOTE 16. Requirements and limitations associat ed with automatic fuel system anti-icing are specified in the Installation and Operating Manual, Section 5.5, Report PWA-6510-09. NOTE 17. The PW4000-112 series engine model engines have b een approved to operate with certain faults present in the control system, based on satisfaction of FAR 33 requirements and appropriate FAR 25 control system reliability requirements. The following criteria exist as dispatch and maintenance requirements for the engine control system. These criteria are specified in Pratt & Whitney Report PWA-6600-05 which defines the various configurations and maximum operating intervals as follows: Fault Level A: No dispatch allowed Fault Level B: Dispatchable: maximum operati ng interval for Fault Level B fault(s) is 20 days. Fault Level D: Unlimited dispatch Fault Levels A, B and D: unlimited dispatch constitute Pratt & Whitney nomenclature. The airframe manufacturers may use different nomenclature in adapting these fault categories to the aircraft maintenance and display systems. However, the maximum operating intervals are restricted as shown above. Fault Level C is not applicable for PW4000-112 series engines. A control system reliability monitoring program has been established with Pratt & Whitney in compliance with the reporting requirements as outlined in the Engine and Propeller Directorate Policy, letter dated October 18, 1993, for Time Limited Dispatch of Engine fitted with FADEC Systems. NOTE 18. The normal 5 minute takeoff time limit may be extende d to 10 minutes for one engine inoperative contingency. NOTE 19. The PW4090-3 engine model provides the same ta keoff thrust as the PW4090 engine model up to a 1000 foot altitude for all temperature days. Above 1000 feet in altitude the PW4090-3 rating provides increased takeoff thrust as a function of both ambient temperature and altitude as shown in the Installation and Operating Manual, Section 4 and Table 1, Report PW-6510-09. Above ambient temperatures of 86oF the altitude ratings do not exceed that of the sea level rating for the PW4090 and PW4090-3 engine models. ----END----