TCDS E24NE

STATIC THRUST AT SEA LEVEL, LBS MODEL MAXIMUM CONTINUOUS TAKEOFF, DRY 5 MINUTES (SEE NOTE 13 & 21) PW4050 PW4052 PW4056 PW4056 PW4060 PW4060A PW4152 PW4156 PW4156A PW4158 PW4160 PW4460 PW4062 PW4062A PW4462 PW4060C PW4650 48,120* 49,820* 49,530*(B767) 47,970**(B747) 50,250* 50,250* 49,200** 49,580** 49,200** 49,580** 49,600** 51,050** 50,250* 47,970** 51,050** 50,250* 48,700* 50,000*** 52,200*** 56,750*** 56,750*** 60,000*** 61,570*** 52,000***** 56,000** 56,000*** 58,000** 60,000** 60,000** 62,000** 62,000** 62,000** 60,000*** 51,400**** * Flat-rated to 77oF/25oC ** Flat- rated to 86oF/30oC *** Flat- rated to 92oF/33oC **** Flat- rated to 95oF/35oC ***** Flat-rated to 108oF/42oC TCDS NUMBER E24NE REVISION: 14 DATE: June 25, 2024 U.S. DEPARTMENT OF TRANSPORTATION PRATT & WHITNEY MODELS: FEDERAL AVIATION ADMINISTRATION PW4050 PW4062 PW4158 TYPE CERTIFICATE DATA SHEET E24NE PW4052 PW4062A PW4160 PW4056 PW4152 PW4460 PW4060 PW4156 PW4462 PW4060A PW4156A PW4650 PW4060C Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E24NE) 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 Division United Technologies Corporation East Hartford, Connecticut 06108 TYPE Axial airflow, dual-spool, turbofan, single-stage fan, 4-stage low-pressure compressor, 11-stage high pressure compressor, annular combustor, 2-stage high- pressure turbine, 4-stage low-pressure turbine. RATINGS (See NOTE 5) * PAGE 1 2 3 4 5 6 REV. 14 14 9 13 4 14 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: AL L PAGES ARE REFORMATTED. SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E24NE PAGE 2 PW4060/4052/4056/4050/4060A/4062 4062A//4060C PW4152/4156/4156A/4158/4160 4460/4462/4650 9.4 + 1.0 0.7 + 0.5 0.1 + 0.5 - - 0.8 + 0.5 0.1 + 0.5 left COMPONENTS For information regarding components, refer to the approved parts list. PRINCIPAL DIMENSIONS (inches) Length Nominal diameter Maximum radial projection 153.6 97.5 52.8 WEIGHT (DRY) 9,420 POUNDS Weight of basic engine includes all essential accessories, but excludes starter, exhaust nozzle, and power source for the ignition system. CENTER OF GRAVITY (IN) Axial: Engine station Vertical: Relative to engine Lateral: Relative to centerline FUEL See NOTE 10 OIL See NOTE 11 CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1 through 33-9, and Amendment 33-10 for FARs 33.7/.14/.23/.27/.77/.88/.90/.92/.94 Type Certificate Number E24NE MODEL PW4056 APPLICATION OCT 26, 1983 ISSUED JUL 09, 1986 PW4156 OCT 26, 1983 JUL 09, 1986 PW4152 APR 01, 1986 JUL 09, 1986 PW4052 JUL 09, 1987 OCT 13, 1987 PW4060 JUN 04, 1987 OCT 21, 1988 PW4160 JUN 04, 1987 OCT 21, 1988 PW4460 JUN 04, 1987 OCT 21, 1988 PW4158 JUL 23, 1987 APR 29, 1988 PW4050 FEB 24, 1989 OCT 12, 1989 PW4060A JUN 26, 1989 MAR 30, 1990 PW4156A MAR 02, 1990 AUG 06, 1991 PW4062 MAY 04, 1989 JAN 21, 1992 PW4462 MAY 04, 1989 JAN 21, 1992 PW4060C JUL 22, 1992 SEP 24, 1992 PW4650 FEB 24, 1995 MAR 03, 1995 PW4062A MARCH 22,2002 APRIL 19, 2002 PW4256: APPLICATION OCT 26, 1983 / ADDED JUL 09, 1986 / DELETED SEP 25, 1986 PRODUCTION BASIS (All Models) The following models comply with 14 CFR part 34, amendment 5A, effective October 23, 2013: PW4158, PW4060. The following model complies with 14 CFR part 34, amendment 7A, effective May 24, 2024: PW4062. See note 23, for detailed su mmary of the certification basis for fuel ve nting and exhaust emissions. Production Certificate Number 2 TCDS E24NE PAGE 3 MAXIMUM PERMISSIBLE OPERATING SPEEDS FOR ENGINE ROTORS (ALSO SEE NOTE 16) PW4050/PW4052/PW4152 PW4056/PW4060/PW4060A/W4060C/PW4156/ PW4156A/PW4158PW4160/ PW4460/PW4462/PW4650 PW4062 PW4062A 4,012 10,300 4,012 10,450 4,044 10,450 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, the PW4000 Maintenance Manual. External engine component maximum limiting temperatures are specified in the Installation and Operating Manual, Section 4.3. MODELS: PW 4050 MODELS: PW 4052 MODELS: PW 4152 MODELS: PW 4056/4156/4156A/ 4158/4060/4060A/ 4160/4460/4062/ 4062A/4462/4060C MODELS: PW 4650 625oC/1157oF 600oC/1112oF 535oC/995oF 625oC/1157oF 163oC/325oF 177oC/350oF 644°C/1191°F 629°C/1164oF - - 640oC/1184oF - - - - 644oC/1191oF 619oC/1146oF - - 640oC/1184oF - - - - 654°C/1209°F 629°C/1164°F - - 650°C/1202°F - - - - 650°C/1202°F 625°C/1157°F - - 650°C/1202°F - - - - *Transient operation above 163oC/325oF is limited to 20 minutes. NOTES NOTE 1. Low pressure rotor N1, RPM) High pressure rotor N2, RPM) NOTE 2. Turbine exhaust gas temperature At takeoff (5 min. see NOTE 21) Max. continuous At start-up Ground In-flight Oil outlet temperature Continuous operation Transient operation* 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 70 psig with a vapor/liquid ratio of zero. OIL PRESSURE LIMITS: Minimum 70 psid 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: 8TH STAGE BLEED Idle to 40% Maximum Continuous 40% Maximum Continuous to Takeoff: NORMAL M AXIMUM 0.0 0.0 6.0 6.0 TCDS E24NE PAGE 4 15TH STAGE BLEED Idle to 40% Maximum Continuous 12.0 12.0 40% Maximum Continuous to Takeoff: 6.0 7.6 NOTE 5. The Sea Level Static Ratings are ideal and are based on ICAO Standard Atmosphere conditions, a Pratt & Whitney hardwall bellmouth 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. NOTE 6. The following accessory drive provisions are incorporated: TORQUE (lb-in) DRIVE ROTATION SPEED RATIO TO TURBINE SHAFT CONTINUOUS STATIC OVERLOAD OVERHUNG MOMENT (in-lb) High pressure rotor Starter CCW 0.841:1 --- * --- 500 IDGS CCW 0.841:1 ** 12,620 ** 2,000 Fluid power pump (R) CCW 0.389:1 1,300 6,500 1,950*** 400 Auxiliary fluid power pump CCW 0.379:1 1,300 6,500 1,950*** 400 LEGEND: CCW = counterclockwise * Maximum starter torque = 910 lb-ft at zero rpm and 1,250 lb-ft maximum impact torque. Maximum allowable starter torque value is 1,498 lb-ft. ** Maximum allowable continuous torque values are equivalent to 175 horsepower at any engine speed at or above sea level idle. The following overload conditions can be accommodated: HORSEPOWER DURATION TIME RECURRING TIME 225 5 minutes 1,000 hours 225 5 seconds 1 hour 450 5 seconds 1,000 hours ** For engines operating without an Auxiliary Fluid Power Pump, the maximum allowable continuous torque values are equivalent to 222 horsepower at any engine speed at or above sea level idle. The following overload conditions can be accommodated: HORSEPOWER DURATION TIME RECURRING TIME 295 5 minutes 1,000 hours 295 5 seconds 1 hour 500 5 seconds 1,000 hours *** Maximum allowable for 5-minute duration recurring at four hour intervals minimum. 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. For inflight operation during icing conditions, the minimum allowable fan speed (N1) is 20% (720 rpm). TCDS E24NE PAGE 5 NOTE 9. Lightning protection requirements and electromagnetic interference omitted by the electronic engine control system, including cables, are specified in the Installation and Operating Manual, Section 4.12. NOTE 10. Fuel and fuel additives conforming 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 11. The following oils are eligible: Oils conforming to Pratt & Whitney Turbojet Engine Service Bulletin No. 238, latest revision. NOTE 12. Certain engine parts are life-limited. Limits are listed in Pratt & Whitney PW4000 Turbofan Engine Manuals, Part Nos. 50A443, 50A605 and 50A822, Time Limit Section. NOTE 13. The engines meet the January 1, 1984, smoke and gaseous emission requirements of SFAR 27. The same requirements are now incorporated into Federal Aviation Regulation Part 34, effective September 10, 1990. NOTE 14. The engines meet the January 1, 1975, fuel venting emission requirements of SFAR 27. The same requirements are now incorporated into Federal Aviation Regulation Part 34, effective September 10, 1990. NOTE 15. The maximum permissible engine inlet distortion limit is specified in the Installation and Operating Manual, Section 4.4, Report PWA-6049. NOTE 16. Limits regarding transient rotor shaft overspeed rpm and transient gas overtemperature and the number of overtemperature occurrences are specified in the Maintenance Documents, Part Nos. 50A444, 50A606, and 50A823. NOTE 17. Information regarding approved fuel filter and oil filter replacement parts is in the PW4000 Series Illustrated Parts Catalogs, Part Nos. 50A445, 50A607, and 50A824. NOTE 18. Requirements and limitations associated with automatic fuel system anti-icing are specified in the Installation and Operating Manual, section 4.5, Report PWA-6049. NOTE 19. The PW4000 series engines have been 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-6139 and PWA-6139 Addendum, which defines the various configurations and maximum operating intervals as follows: Fault Level A: No dispatch allowed Fault Level B: Dispatchable; maximum operating interval for Fault level B fault(s) is 20 days. Fault Level C: Dispatchable; maximum operating interval for Fault level C is 1000 operating hours Review of EEC fault data from only the most recent flight leg is sufficient at the 1000 hour interval except for the following EEC part numbers: P&W P/N 50D791, 50D824, 51D037, 50D823, 51D319, 51D586. Fault Levels A, B, and C 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. 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 28, 1993, for Time Limited Dispatch of Engines fitted with FADEC Systems. NOTE 20. Incorporation of Pratt & Whitney Service Bulletin PW4ENG 79-43 provides an alternative means of compliance with the requirements of FAR 33.71(c)(1). NOTE 21. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. NOTE 22. Engines in which Engineering Change Number EC92KK322G, H, I, J, and K were incorporated during manufacturer are designated by a (-3) on the Engine Data Plate. TCDS E24NE PAGE 6 NOTE 23. The following e missions standards promulgated in 14 CFR Part 34, Am endment 5A, effective October 23, 2013, and 40 CFR Part 87, effective October 31, 2012, have been complied with for: PW4158 with TALON II combustor, and PW4060. Fuel V enting E mission St andards: 14 CFR §§ 34. 10 (a) and 34. 11; in addition, 40 CFR §§ 87.10(a) and 87.11. Smoke Num ber (SN) E mission St andards: 14 CFR §34.21(e)(2); in addition , 40 CFR § 87.23(c)(l). Carbon Monoxide (CO) E mission St andards: 14 CFR § 34.21(d)(l)(ii); in addition, 40 CFR § 87.23(c)(l). Hydrocarbons (HC) E mission St andards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 87.23(c)(l). Oxides of Nitrogen (NOx) Emission St andards: 14 CFR § 34.23(a)(2); in addition, 40 CFR § 87.23(c)(2) for PW4060; 14 CFR § 34.23(b)(1); in addition, 40 CFR § 87.23(c)(3) for PW4158 with TALON II combustor. In addition to t he F AA's finding of compliance based on the certification requirements defined in this TCDS, the engine m anufacturer has declared t hat the ICAO e missions st andards 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 for NOx (also known as CAEP/6) for PW4060, Section 2.3.2.e for NOx (also known as CAEP/8) for PW4158 with TALON II combustor, and Part II Chapter 2 for fuel venting for PW4158 with TALON II combustor, and PW4060 have also been demonstrated. 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: PW4062. Fuel Venting Emission Standards: 14 CFR §§ 34.10 (a) and 34.11; in addition, 40 CFR § 1031.30(b)(2). Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(l)(ii); 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(a)(2); in addition 40 CFR § 1031.60(e)(4). 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 findings 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 II, Chapter 2 for Fuel Venting, Part III, Chapter 2, Section 2.2.2 for SN , Section 2.3.2 for CO and HC, Section 2.3.2.d for NOx (also known as CAEP/6) and Annex 16, Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, Part III, Chapter 4, Section 4.2.2 for non- volatile Particulate Matter (also known as CAEP/10 & CAEP/11) have also been demonstrated for PW4062. ----END----