TCDS E36NE

* PAGE 1 2 3 4 5 6 7 8 REV. 7 5 7 5 5 6 7 7 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 E36NE TCDS NUMBER E36NE REVISION: 7* DATE: May 28, 2014 PRATT & WHITNEY PW4164 PW4170 PW4168 PW4168A-1D PW4168A PW4168-1D PW4164C PW4164-1D PW4164C/B PW4164C-1D PW4164C/B-1D Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E36NE) 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 I. MODELS PW4164 PW4168 PW4168A PW4164C PW4164C/B TYPE Axial airflow, dual-spool, turbofan, single-stage fan, 5-stage low-pressure compressor, 11-stage high pressure compressor, annular combustor, 2-stage high- pressure turbine 5-stage low-pressure turbine. RATINGS (See NOTE 5) Static thrust at sea level, lbs. Takeoff, Dry 5 Minutes (see NOTE 19) Maximum Continuous 64,500 55,800 68,600 59,357 - - - - 64,500 55,800 68,600 - - COMPONENTS Fuel Metering unit Fuel pump and filter Electronic engine control (EEC) Ignition Exciter Ignitors Hamilton Standard Model Number JFC-131 Argo-Tech Model 723300 Hamilton Standard EEC Model Number 170 Unison Industries Model Number TFN – 29 PW P/N IC709520 TCDS E36NE PAGE 2 II. MODELS PW4170 PW4168A-1D PW4168-1D PW4164-1D PW4164C-1D PW4164C/B- 1D TYPE RATINGS (See NOTE 5) Static thrust at sea level, lbs Takeoff, Dry 5 Minutes (see NOTE 19) Maximum Continuous COMPONENTS Fuel Metering unit Fuel pump and filter Electronic engine control (EEC) Ignition Exciter Ignitors Axial airflow, dual-spool, turbofan, single-stage fan, 5-stage low-pressure compressor 11-stage high pressure compressor, annular combustor, 2-stage high-pressure turbine, 5-stage low-pressure turbine 70,000 59,357 68,600 - - - - - - 64,500 55,800 - - - - 68,600 - - Hamilton Standard Model Number JFC-131 Argo-Tech Model 723300 Hamilton Standard EEC Model Number 170 Unison Industries Model Number TFN – 29 PW P/N IC709520 I. MODELS (CONT.). II. MODELS (CONT.) PW4164 PW4170 PW4168 PW4168A-1D PW4168A PW4168-1D PW4164C PW4164-1D PW4164C/B PW4164C-1D PW4164C/B-1D COMPONENTS EEC alternator Stator Rotor Fuel distribution valve Station 2.5 bleed actuator Hamilton Standard Model Number GTA42 PT2/TT2 probe PRINCIPAL DIMENSIONS (IN) Length Nominal diameter Maximum radial projection WEIGHT (DRY) Unison P/N 430073 Unison P/N 430074 Hamilton Standard Model Number GTA40 Hamilton Standard Model Number GTA42 Hamilton Standard Model Number GTA41 Rosemont Model Number 154 GT 167.220 123.246 61.623 12,900 lbs. Weight of basic engine includes all essential accessories, but excludes exhaust nozzle and power source for the ignition system. CENTER OF GRAVITY (IN) Axial: Engine station Vertical: Below engine centerline Lateral: Left of centerline 114.5 + 1.0 (Titanium Fan Case Containment) 117.1+ 1.0 (Kevlar Fan Case Containment) 117.4+1.0 (Kevlar Fan Case Containment and Ring Case Compressor) -0.9 + 0.5 -0.4 + 0.5 TCDS E36NE PAGE 3 FUEL See NOTE 9 OIL See NOTE 10 CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1 through 33-14 Type Certificate Number E36NE MODEL APPLICATION ISSUED PW4164 NOV 17, 1989 AUG 24, 1993 PW4168 NOV 17, 1989 AUG 24, 1993 PW4168A JULY 8, 1997 DEC 18, 1997 PW4164C MARCH 5, 2008 NOV 25, 2008 PW4164C/B MARCH 5, 2008 NOV 25, 2008 FAR 33 effective February 1, 1965, as amended by 33-1 through 33-14 FAR 33.28 Amendment 15 (EEC Software) FAR 33.78 Amendment 19 (Rain/Hail) Equivalent Level of Safety Finding: ELOS No. 8040 ELOS-08-NE08 to 14 CFR §33.87(a) & (b) PW4170 DEC 12, 2006 NOV 25, 2008 PW4168-1D DEC 12, 2006 NOV 25, 2008 PW4168A-1D DEC 12, 2006 NOV 25, 2008 PW4164-1D DEC 12, 2006 NOV 25, 2008 PW4164C-1D DEC 12, 2006 NOV 25, 2008 PW4164C/B-1D DEC 12,2006 NOV 25, 2008 The following models comply with 14 CFR part 34, amendment 5, effective December 31, 2012. See note 24, for detailed summary of the certification basis for fuel venting and exhaust emissions: PW4164, PW4168, PW4168A, PW4168A-1D, PW4168-1D, PW4164-1D. The following model complies with 14 CFR part 34, amendment 5, effective December 31, 2012. See note 25, for detailed summary of the certification basis for fuel venting and exhaust emissions: PW4170. PRODUCTION BASIS (All Models) Production Certificate Number 2 NOTES NOTE 1. Maximum Permissible Operating Speeds for Engine Rotors PW4164/PW4168/PW4168A/PW4164C/PW4164C/B/PW4168A-1D./PW4168-1D/PW4164- 1D/PW4164C-1D/PW4164C/B-1D only Low pressure rotor (N1), RPM 3,600 For PW4170 only Low Pressure Rotor (N1), RPM 3,680 For PW4170/PW4168A-1D/PW4168-1D/PW4164-1D/PW4164C-1D/PW4164C/B-1D and PW4164/PW4168/PW4168A/PW4164C/PW4164C/B High pressure rotor (N2), RPM 10,450 Minimum Permissible Operating Speeds for Engine Rotors Low pressure rotor (N1), RPM 736 (In-flight) High pressure rotor (N2), RPM 5,860 (In-flight and on ground operation) TCDS E36NE 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, the PW4164, PW4168, PW4168A, PW4164C, PW4164C/B, PW4170, PW4168A-1D, PW4168-1D, PW4164-1D, PW4164C-1D, and PW4164C/B-1D Maintenance Manual. External engine component maximum limiting temperatures are specified in the Installation and Operating Manual, Section 4.3. Turbine Exhaust gas temperature (See NOTE 18) At takeoff (5 minutes, see NOTE 19) 645oC/1193oF actual; 620oC/1148oF indicated Maximum continuous 615oC/1139oF actual; 600oC/1112oF indicated At start-up Ground 535oC/995oF In-flight 645oC/1193oF actual; 620oC/1148oF indicated Oil outlet temperature Continuous operation 163oC/325oF Transient operation (20 min.) 177oC/350oF 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: PERCENT OF PRIMARY ENGINE AIRFLOW 8TH STAGE BLEED NORMAL MAXIMUM BLEED (one engine out) Idle to 40% Maximum Continuous 0.0 0.0 Above 40% Maximum Continuous Thrust 4.0 6.0 15TH STAGE BLEED Idle to 40% Maximum Continuous 8.0 12.0 Above 40% Maximum Continuous Thrust 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. TCDS E36NE PAGE 5 NOTE 6. The following accessory drive provisions are incorporated: TORQUE (lb-in) DRIVE ROTATIO N SPEED RATIO TO TURBINE SHAFT CONTINUOUS STATI C OVERLOAD OVERHAN G (in-lb) High pressure rotor Starter IDGS Fluid power pump (R) Auxiliary fluid power pump CCW CCW CCW CCW 0.841:1 0.841:1 0.389:1 0.412:1 - - - ** 1,300 1,300 * 12,620 6,500 6,500 - - - ** 1,950*** 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 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 *** 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. Lightning protection requirements and electromagnetic interference emitted by the electronic engine control system, including cables, are specified in the Installation and Operating Manual, Section 4.12. NOTE 9. 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 10. The following oils are eligible: Oils conforming to Pratt & Whitney Turbojet engine Service Bulletin No. 238, latest revision. NOTE 11. Certain engine parts are life-limited. Limits are listed in Pratt & Whitney PW4164, PW4168, PW4168A, PW4164C, PW4164C/B, PW4170, PW4168A-1D, PW4168-1D, PW4164-1D, PW4164C-1D, PW4164C/B- 1D Turbofan Engine Manual, Part No. 51A342, Time Limit Section. 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 4.4, Report PWA-6335. NOTE 14. Limits regarding transient rotor shaft overspeed rpm and transient gas overtemperature and the number of overtemperature occurrences are specified in the Maintenance Document, Part No. 51A341. TCDS E36NE PAGE 6 NOTE 15. Information regarding approved fuel filter and oil filter replacement parts is in the PW4000 Series Illustrated Parts Catalog, Part No. 51A343. NOTE 16. Requirements and limitations associated with automatic fuel system anti-icing are specified in the Installation and Operating Manual, Section 4.5, Report PWA-6335. NOTE 17. The PW4164, PW4168, PW4168A, PW4164C, PW4164C/B, PW4170, PW4168-1D, PW4168A-1D, PW4164-1D, PW4164C-1D, and PW4164C/B-1D model 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 6436 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 Levels A and B 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 18, 1993, for Time Limited Dispatch of Engine fitted with FADEC Systems. NOTE 18. Electronic Engine Control (EEC) software version SCN5C has maximum permissible exhaust gas temperatures of 625oC actual and 620oC indicated for takeoff (5 minutes) and 600oC for maximum continuous. To provide an additional 20oC EGT margin, EEC software version SCN6B and later versions can provide maximum permissible EGT of 645oC actual (620oC indicated) for takeoff, and 615oC actual (600oC indicated) for maximum continuous. The noted engine ratings and limits are controlled by EEC P/N and Engine Programming Plug (EPP) P/N, and are implemented by specific Service Bulletin instructions only. The engine data plate also reflects the engine ratings and limits configuration. The indicated versus actual EGT values are controlled by EEC software. NOTE 19. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. NOTE 20. NOTE 21. NOTE 22. NOTE 23. The PW4168A engine model provides the same takeoff thrust as the PW4168 model at or below sea level pressure altitude, and increased takeoff thrust at pressure altitudes above sea level and below 14,100 feet and below temperatures of STD & 40oC. The PW4164C engine model provides the same takeoff thrust as the PW4164, and increased maximum climb thrust of the PW4168A. The PW4164C/B engine model provides the same takeoff thrust as the PW4168A, and increased maximum climb thrust of the PW4168A. The PW4170 engine model conversion requires the incorporation of the following MECs: MEC 06KA009, Ring Case HPC MEC 07KA171, HPC Rear Drum MEC 06KA104, HPT first vane MEC 06KA063, LPT third vane, and MEC 06KY002 LPT third blade MEC 06KA058, HPT first blade outer airseals MEC 07KA011G, LPT sixth disk MEC 06KY001, thicker nickel LPT shaft or MEC 05KM003, steel LPT shaft MEC 06KZ021, SCN 10 EEC software NOTE 24. 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: PW4164, PW4168, PW4168A, PW4168A-1D, PW4168-1D, PW4164-1D. Fuel Venting Emission Standards: 14 CFR §§ 34. 10 (a) and 34. 11; in addition, 40 CFR §§ 87.10(a) and 87.11. TCDS E36NE PAGE 7 Smoke Number (SN) Emission Standards: 14 CFR §34.21(e)(2); in addition , 40 CFR § 87.23(c)(l). Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(l)(ii); in addition, 40 CFR § 87.23(c)(l). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 87.23(c)(l). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(l); in addition, 40 CFR § 87.23(c)(3). 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 Ill, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2.e.3 for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been demonstrated. NOTE 25. 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: PW4170. 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----