TCDS E00072EN

I I I I I I U. S. DEPARTMENT OF TRANSPORTATION TCDS NUMBER E00072EN Revision: 5 FEDERAL AVIATION ADMINISTRATION ENGINE ALLIANCE TYPE CERTIFICATE DATA SHEET MODELS: GP7200 Series: GP7270 E00072EN GP7272 GP7277 November 30, 2021 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00072EN) 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: Engine Alliance 411 Silver Lane East Hartford, CT 06118 TYPE Axial-airflow, dual-spool, turbofan engine, single stage fan, five-stage low-pressure compressor, nine-stage high-pressure compressor, single annular combustor, two-stage high- pressure turbine, six-stage low-pressure turbine. MODELS: GP7270 GP7272 GP7277 RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Maximum Continuous Takeoff (5 minutes) (See NOTE 2) 73,470 74,735 73,470 76,470 73,850 80,290 FLAT RATING AMBIENT TEMPERATURE Maximum Continuous Takeoff 25°C / 77°F 30°C / 86°F - - - - - - - - Electronic Engine Control Rating Plug (Part Number) 2122M76P11 2122M76P05 2122M76P08 2122M76P17 2122M76P29 COMPONENTS/CONFIGURATION For information regarding components and engine configuration, refer to the approved parts list: GP7270 P/N GP7270G01 GP7272 P/N GP7272G01 GP7277 P/N GP7277G01 P/N 5700600 defines both engine model assemblies. PAGE 1 2 3 4 5 REV. 5 5 4 4 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. MODELS: (cont.) GP7270 GP7272 GP7277 PRINCIPAL DIMENSIONS (Room temperature) Length (flange to flange, in.) 185.782 ± 0.099 - - - - Length (fan spinner face to aft flange, in.) 193.722 - - - - Nominal diameter (fan case, in.) 123.740 - - - - Maximum radial projection (in.) (at drain mast) CENTER OF GRAVITY (in.) 77.901 - - - - Axial engine station: relative to A-flange 213.500 ± 1.0 - - - - Vertical, relative to engine centerline: -0.600 ± 0.5 - - - - Lateral, relative to centerline: 0.190 ± 0.5 - - - - WEIGHT * (DRY) Basic engine (lbs) * The engine dry weight is defined as the dry weight of the basic engine with EA supplied engine build-up (EBU) components. The EBU includes: hydraulic filter and pressure switch, intermediate pressure check valve, fan inlet temperature sensor, and inlet anti-icing valve and ducts. The following buyer furnished equipment (BFE) are not part of the basic engine weight: variable frequency generator, two (2) hydraulic pumps, one high pressure valve, pressure regulating valve, nacelle inlet cowl, fan cowls and associated hardware, thrust reverser assembly including activation system, attachment hardware and associated electrical harnesses, aft pylon fairing and attachment hardware, forward engine mount, rear engine mount, and attachment hardware (thrust links). 14,798 - - - - FUEL GE Specification No. D50TF2 and Engine Alliance Service Bulletin EA-GP7-73-1 define the fuels requirements and provide a listing of approved fuels and fuel additives for use in the GP7200 series turbofan engine. LUBRICATING OILS Engine Alliance Service Bulletin EA-GP7-79-1 provides a listing of approved turbine oils for use in the GP7200 series turbofan engine. CERTIFICATION BASIS 1. 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-20 with the following equivalent level of safety (ELOS) findings: • 33.27, Rotor Integrity, par. (c), ELOS No. 8040-ELOS-05-NE-04 • 33.77, Foreign Object Ingestion-Ice, par. (c) and (e), ELOS No. 8040-ELOS-05- NE-05 • 33.78, Rain and Hail Ingestion, par. (a)(1), ELOS No. 8040- ELOS-05-NE-06 2. The following models comply with 14 CFR part 34, amendment 5, effective December 31, 2012. See note 15 for detailed summary of the certification basis for fuel venting and exhaust emissions for GP7270 and GP7272. See note 16 for detailed summary of the certification basis for fuel venting and exhaust emissions for GP7277. MODEL APPLICATION ISSUED/AMENDED DELETED GP7270 02/05/2003 12/29/2005 --- GP7272 01/15/2012 01/14/2014 --- GP7277 02/05/2003 12/29/2005 --- PRODUCTION BASIS (All Models) Production Certificate No. 2 for engines produced by Pratt & Whitney (P&W) Production Certificate No. 108 for engines produced by General Electric Aircraft Engines (GEAE). The Engine Alliance (EA) is a partnership between GEAE and P&W. With respect to the benefits of type certification for production, GEAE and P&W function as licensees of EA. NOTES NOTE 1: Nameplate thrust values are defined at sea level static, standard pressure (14.696 psia), up to the flat rating ambient temperature, with 100% inlet recovery, no fan or compressor customer bleed, no horsepower extraction from BFE, and the production flight exhaust ((fan duct assembly comprised of left half, P/N 40113476-987G01, and right half, P/N 40113476-987G02) and primary nozzle (P/N L12192)). The nameplate ratings were derived using engine performance cycle simulations JV3.14.32.A and JV3.14.32.B for the maximum continuous and takeoff thrust ratings, respectively. For the GP7270, Electronic Engine Control Rating Plug (Part Number) 2122M76P05 provides increased Takeoff Flat Rating Ambient Temperature limits of 36°C / 97°F; the Sea Level Static Takeoff Thrust Rating is the same as Electronic Engine Control Rating Plug (Part Number) 2122M76P11. For the GP7272, Electronic Engine Control Rating Plug (Part Number) 2122M76P17 provides increased Takeoff Flat Rating Ambient Temperature limits of 34°C / 93°F; the Sea Level Static Takeoff Thrust Rating is the same as Electronic Engine Control Rating Plug (Part Number) 2122M76P08. NOTE 2: The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. NOTE 3. TEMPERATURES GP7270 GP7272 GP7277 Maximum permissible Turbine Exhaust Gas Temperatures (EGT) * are as follows: Takeoff (5 minutes) (See NOTE 2) Maximum Continuous * Measured by two sets of four dual-element thermocouple probes installed at the leading edge of the low pressure turbine stage 2 vanes. 1002°C / 1836°F 970°C / 1778°F - - - - - - - - Turbine Exhaust Gas Temperatures at start-up, Ground Flight 745°C / 1373°F 865°C / 1589°F - - - - - - - - Oil outlet temperature: Continuous operation Transient operation (limited to 20 minutes) Minimum oil temperature at idle, before takeoff power operation: 163°C / 325°F 177°C / 350°F 50°C / 122°F - - - - - - - - - - - - Fuel Temperatures (All Models) See Installation and Operating Manual, EA-0126 NOTE 4. ROTOR SPEEDS GP7270 GP7272 GP7277 Maximum permissible Low Pressure Rotor (N1) Minimum Low Pressure Rotor (N1), Ground Idle Flight Idle (See Note 10) Maximum permissible High Pressure Rotor (N2) Minimum High Pressure Rotor (N2), Ground Idle Flight Idle 2,738 rpm 450 rpm 620 rpm 13,060 rpm 6,974 rpm 7,279 rpm - - - - - - - - - - - - - - - - - - - - - - - - Power setting, power checks, and control of engine thrust output are based on N1. NOTE 5. PRESSURES Fuel pressure limits Fuel pressure at the engine fuel pump inlet during operation shall be maintained at greater than or equal to 5 psi above the true vapor pressure of the fuel, but less than or equal to 100 psi above absolute ambient pressure, with a vapor/liquid ratio of zero. The maximum allowable pressure at the fuel pump inlet after shutdown is 100 psig. Oil pressure limits N2 Speed (rpm) Minimum Oil Pressure (psig) 6,620 10,500 13,060 25 62 101.8 Oil supply pressure is measured relative to sump/vent pressure. Temporary interruption associated with negative “g” operation is limited to 15 seconds maximum. Normal oil pressure will be restored rapidly once the negative "g" effect has been eliminated. NOTE 6. ACCESSORY DRIVE PROVISIONS Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overload Static Hydraulic Pump #1 Hydraulic Pump #2 Variable Frequency Generator (VFG) Air Turbine Starter CCW CCW CCW CCW 0.3034 : 1 0.3116 : 1 1.6171 : 1 0.935 : 1 2,615 2,615 * --- 3,190 ** 3,190 ** * --- 8,497 8,497 8,860 18,600 450 450 1,220 307 CCW = Counterclockwise (facing the drive pad) * Maximum VFG allowable continuous torque values are equivalent to 249 horsepower at any engine speed at or above sea level ground idle. ** The engine-driven hydraulic pump overload is based on 5 minutes of operation at 4-hour intervals. The following VFG overload conditions can be accommodated: Horsepower Duration Time Recurring Time 319 319 402 5 minutes 5 seconds 5 seconds Once / 1000 hours Once / hour Once / 1000 hours NOTE 7. MAXIMUM PERMISSIBLE AIR BLEEDS Corrected Fan Speed High Pressure Compressor Bleed Location (percent of core engine airflow) At or below 740 rpm 740 rpm to 2,319 rpm At or above 2,319 rpm Stage 4 5.8% 5.8% 5.8% Stage 7 1.2% * 0.54% Stage 9 13.1% 13.1% 6.8% * Linear transition between 740 rpm and 2,319 rpm NOTE 8: The maximum permissible engine inlet pressure distortion is specified in the Installation and Operating Manual, EA-0126. NOTE 9: During ground operations in icing conditions with an outside air temperature of +37.4°F / +3.0°C or less, periodic engine run-ups must be performed to shed ice from the spinner, fan blades, and low-pressure compressor stators. Run-ups must be to a minimum of 60 percent N1 at intervals not to exceed 30 minutes (and must include taxi-in, ground hold, and taxi-out time). See EA GP7200 Operating Instructions Manual, P/N 5702515. NOTE 10: The minimum N1 certified for in-flight operation in icing conditions is 620 rpm. NOTE 11: Life limits for critical components and mandatory inspection requirements are specified in the Airworthiness Limitation Section of GP7200 Series Engine Turbofan Engine Manual (P/N 5700147). NOTE 12: The GP7200 series turbofan engine is certified to operate with certain faults present in the control system based on 14 CFR Part 33 and appropriate engine control system reliability requirements. The time limited dispatch configurations for the engine control system are defined in EA report GEK 112848. The allowable time limited dispatch intervals are provided in the Airworthiness Limitation Section of the GP7200 Engine Manual (P/N 5700147). NOTE 13: Overhaul of the GP7270, GP7272 and GP7277 engine and its components is only authorized when done in accordance with procedures approved by the Type Certificate holder or Manuals accepted by the FAA. NOTE 14: Engine Instructions for Continued Airworthiness (ICA’s) have been reviewed and accepted by the FAA Engine Certification Office.. The following Manuals are approved or accepted for GP7200 series engines: Installation and Operating Manual EA-0126 Operating Instructions P/N 5702515 Engine Manual P/N 5700147 Clean, Inspect, & Repair Manual P/N 5700309 Standard Practices Manual P/N 5700139 NOTE 15: 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 GP7270 and GP7272. 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)(1). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 87.23(c)(1). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(1); 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 III, 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 16: 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 GP7277. 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)(1). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 87.23(c)(1). 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