TCDS E00093EN

PAGE 1 2 3 4 5 6 REV. 6 6 4 4 5 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 E00093EN TCDS NUMBER E00093EN REVISION 6 DATE: August 9, 2024 PRATT & WHITNEY CANADA CORP. MODELS: PW814GA, PW815GA, PW812D, PW812GA Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00093EN) 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 Canada Corp. 1000 Boulevard Marie-Victorin Longueuil, QC, Canada J4G 1A1 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 five-stage low pressure turbine (4 stages in PW812D and PW812GA) that directly drives a two-stage low pressure compressor, and a single stage high bypass ratio fan. The high pressure compressor has eight axial stages driven by a two-stage cooled high pressure turbine. MODELS: PW814GA PW815GA PW812D PW812GA RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Takeoff (5 minutes) (See NOTE 2) Maximum Continuous 15,429 14,155 16,011 15,568 13,850 12,989 13,716 11,368 FLAT RATING AMBIENT TEMPERATURE Takeoff Maximum Continuous 33°C / 91°F 28°C / 82°F - - - - 35°C / 95°F 25°C / 77°F 30°C / 86°F 25°C / 77°F FADEC Hardware PN Data Storage Unit PN (Ratings Plug) 33B3787 33B7268 - - 33B6719 33B7751 33B3212 33B7753 33B7736 COMPONENTS/CONFIGURATION For information regarding components and engine configuration, refer to: Installation Drawing 33B1172 for the PW814GA and PW815GA Installation Drawing 33B7509 for the PW812D Installation Drawing 33B7074 for the PW812GA Page 2 of 6 MODELS: (cont.) PW814GA PW815GA PW812D PW812GA PRINCIPAL DIMENSIONS (Room temperature) Length (flange to flange, in.) Length (fan spinner face to aft tail cone, in.) Nominal diameter (fan case, in.) Maximum radial projection (in.) (at drain mast) CENTER OF GRAVITY (in.) Axial engine station, relative to A-flange (in.): Vertical, relative to engine centerline (in.): Lateral, relative to centerline (in.): 105.710 130.452 49.39 38.984 55.2 -2.0 0.4 starboard - - - - - - - - - - - - - - 102.665 113.137 43.57 36.632 50.7 -1.3 0.5 starboard 102.7 113.1 43.57 36.63 50.6 -2.1 0.3 starboard WEIGHT * (DRY) Basic engine (lbs.) 3,135.7 - - 2719 2692 FUEL The Engine Maintenance Manual defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the PW800 series turbofan engine. LUBRICATING OILS The Engine Maintenance Manual provides a listing of approved turbine oils for use in the PW800 series turbofan engine. CERTIFICATION BASIS MODELS PW814GA, PW815GA PW812D, PW812GA Airworthiness Standards 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-33 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 Emissions Standards All 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: TYPE CERTIFICATE NUMBER E00093EN MODEL APPLICATION ISSUED/AMENDED PW814GA May 25, 2011 February 24, 2017 PW815GA May 25, 2011 February 24, 2017 PW812D June 13, 2018 November 22, 2022 PW812GA June 26, 2016 February 24, 2023 Page 3 of 6 NOTES NOTE 1. NOTE 2. NOTE 3. ENGINE RATINGS: Engine ratings are based on calibrated test stand performance under the following conditions: 1. ICAO Standard Atmospheric Conditions a. Sea level static conditions, standard pressure (14.696 psia), ISA ambient temperature °F b. Specific humidity 0.00629 kg water / kg dry air 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. 7. Exhaust Nozzle with no leakage and with a velocity coefficient equal to 1.0 TEMPERATURES: Maximum permissible Indicated Turbine Temperatures (ITT) are as follows: Engine Models PW814GA/PW815GA PW812D PW812GA Takeoff (5 minutes)* Maximum Continuous Indicated Turbine Temperatures (ITT) at start-up 965 °C / 1769 °F 956 °C / 1753 °F 975 °C / 1787°F 985 °C / 1805°F 920 °C / 1688°F 975 °C / 1787°F 979 °C / 1794°F 897 °C / 1647°F 975 °C / 1787°F *The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. Oil temperatures: °C See Installation and Operating Manual for details (All Models). Fuel Temperatures See Installation and Operating Manual for details (All Models). Component Temperatures See Installation and Operating Manual for details (All Models). PRESSURES: PW814GA/PW815GA Fuel System 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 or ambient pressure plus 1 psi whichever limit is reached first with a vapor/liquid ratio of zero, but not greater than 141 psi above the ambient pressure. The maximum allowable pressure at the fuel pump inlet after shutdown is 185 psig. PW812D and PW812GA Fuel System The fuel system pressure limits are provided in the PW812D and PW812GA Installation & Operation Instructions Manual. Minimum Pressure at FMU Interface: Normal operating conditions shall allow a minimum engine inlet pressure at FMU interface of TVP+5psi or ambient + 1 psi, whichever is reached first, without time limitation and without operating envelope restriction. Maximum Pressure at FMU Interface: The maximum engine inlet pressure at the FMU interface is 55 psig. In the event of engine shutdown from a power setting above ground idle, the engine can tolerate a pressure pulse of 211 psig. Oil Pressure limits PW814GA / PW815GA PW812D / PW812GA* Minimum Maximum 35 psig at idle. Variable by N2 Speed off idle.* 275 psig Otherwise 185 psig 35 psig at idle. Variable by N2 Corrected Speed off idle. 275 psig with time restrictions. Otherwise 185 psig continuous *See Installation and Operating Manual 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. Page 4 of 6 NOTE 4. NOTE 5. NOTE 6. NOTE 7. NOTE 8. ACCESSORY DRIVE PROVISIONS: ACCESSORY DRIVES PW812D Drive Pad Rotation Speed ratio to N2 Torque (lb-in) Overhung Moment (lb-in) Continuous Overload Static Hydraulic Pump A (front) Variable Frequency Generator Aircraft PMA Hydraulic pump B (rear) CW CW CW CW 0.3337:1 0.5275:1 0.7512:1 0.3270:1 106.2 348.6 8 106.2 185.8 1013.1* 15 185.8 1194 3540 N/A 1194 26.5 504.4 3.5 26.5 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. *Maximum allowable torque for a duration of 5 seconds maximum. MODEL DESCRIPTION: The PW800GA engine series consist of the following engine models: PW814GA Gulfstream G500 reduced thrust model PW815GA Gulfstream G600 basic thrust model PW812D Dassault F6X PW812GA Gulfstream G400 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 ACCESSORY DRIVES PW814GA / PW815GA [1] and PW812GA [2] Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overload Static Hydraulic Pump Integrated Drive Generator (IDG) CW CW [1] 0.1777:1 [2] 0.1712:1 [1] 0.3292:1 [2] 0.3173:1 160 180 * 252 300 * 3600 3650 450 500 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. Page 5 of 6 NOTE 9. NOTE 10. NOTE 11. NOTE 12. NOTE 13. NOTE 14. ENGINE MOUNT SYSTEM PROVISIONS: Engine mount system provisions are specified in Installation Drawing 33B1172 and Installation and Operating Manual 33B1410 for the PW814GA and PW815GA models. Engine mount system provisions are specified in Installation Drawing 33B7509 and Installation and Operating Manual 33B9460 for the PW812D model. Engine mount system provisions are specified in Installation Drawing 33B7074 and Installation and Operating Manual 33B6360 for the PW812GA model. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable SPECIAL INSTALLATION REQUIREMENTS: 1) Engine design and operating limitations are defined in the Installation and Operating Manual. 2) The PW814GA, PW815GA, PW812D and PW812GA engines are not eligible for Extended Twin Engine Operations, (ETOPS) Operation. 3) The minimum N1 certified for in-flight operation in icing conditions is controlled by the Electronic Engine Control. 4) The PW814GA, PW815GA and PW812D engines are approved with Time Limited Dispatch (TLD) Limitations. Criteria pertaining to the engine control systems’ dispatch and maintenance requirements are specified in Control System Interface Control Document (CSICD) and the Airworthiness Limitations Manual (ALM) which define the various configurations and maximum operating intervals. (See NOTE 15 for identification of the CSICD and ALS). 5) Lightning protection requirements and electromagnetic interference emitted by the electronic engine control system, including cables, are specified in the Installation and Operating Manual. 6) The PW814GA, PW815GA, PW812D and PW812GA thrust reverser are not part of the engine type design and is certified as part of the aircraft. Information and part number for installation of a thrust reverser is contained in the Installation and Operating Manual. 7) Exhaust Emissions and Fuel Venting: The following emissions standards promulgated in 14 CFR Part 34, Amendment 5a, effective October 23, 2013, and 40 CFR Part 87, effective October 31, 2012, have been complied with for the PW814GA and PW815GA engine models. 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)(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 for non-vilatile particulate matter emissions (nvPM) the PW814GA, PW815GA, PW812D and PW812GA engine models have been show to comply with AWM Chapter 516 at Change 516-15 which refer to ICAO Annex 16 Volume II, Amendment 10 (CAEP/11). MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Service Bulletins, structural repair manuals, vendor manuals, AFMs, and overhaul and maintenance manuals, which contain a statement that the document is approved by the TCCA, are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only). SPECIAL OPERATING PROCEDURES: Requirements and limitations for ground operation in icing conditions are specified in the Installation and Operating Manual. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: Not Applicable Page 6 of 6 NOTE 15. NOTE 16. NOTE 17. NOTE 18. NOTE 19. NOTE 20. NOTE 21. NOTE 22 APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: The following Instructions for Continued Airworthiness (ICA) have been accepted under the requirements of 14 CFR § 33.4 Engine Models PW814GA / PW815GA PW812D PW812GA Engine Maintenance Manual 33B1390 33B7515 33B1430 Airworthiness Limitation Manual (ALM) Approved 33B1391 33B7516 33B1431 Engine Shop Manual (ESM) 33B1393 33B7518 33B1433 Cleaning, Inspection & Repair Manual 33B1401 33B7519 33B7519 Standard Practices Manual 585005 The following manuals have been approved under the requirements of 14 CFR § 33.5 Installation and Operating Manual 33B1410 33B9460 33B6360 Other approved documents Control System Interface Control Document 33B1286 33B7438 33B6446 Instructions for Continued Airworthiness are incomplete for the PW812GA engines. 14 CFR 21.50(b) requires the holder of this type certificate to ensue these instructions are complete and furnished prior to when the aircraft incorporating these engines are issued standard airworthiness certificates or delivered/returned to service, whichever occurs later. The aircraft must not be issued a standard airworthiness certificate or approved for return to service until the ICA are complete and determined acceptable. IMPORT REQUIREMENTS: 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: Life limits for critical components and mandatory inspection requirements are specified in the Airworthiness Limitation Manual. MILITARY MODEL INFORMATION: Not Applicable ROTOR SPEEDS: Engine Models PW814GA / PW815GA PW812D / PW812GA Maximum permissible Low Pressure Rotor (N1) 6,378 rpm 7,678 rpm Maximum permissible High Pressure Rotor (N2) 24,283 rpm 25,368 rpm Power setting, power checks, and control of engine thrust output in all operations are based on Low Rotor Speed (N1). OUTPUT/PROPELLER SHAFT TORQUE LIMITS: Not Applicable. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: Maximum Permissible Bleed Air Extraction limits are specified in the Installation and Operating Manual. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply): Not Applicable. ---END---