TCDS E00087EN

LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN PAGE 1 2 3 4 5 6 7 8 9 10 11 12 REV. 13 13 13 13 13 13 11 13 13 13 12 13 TCDS NUMBER E00087EN Revision 13 U. S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00087EN International Aero Engines, LLC MODELS: PW1133G-JM, PW1133G1-JM, PW1133G1R-JM, PW1133GA-JM, PW1133GAR-JM, PW1133GR-JM, PW1133GS-JM, PW1133GAS-JM, PW1133G1S-JM, PW1130G-JM, PW1130GS-JM, PW1129G-JM, PW1127G-JM, PW1127G1-JM, PW1127G1A-JM, PW1127G1B-JM, PW1127GA-JM, PW1124G-JM, PW1124G1-JM, PW1134G1/2-JM, PW1134GA/2-JM, PW1133G/2-JM, PW1133G1/2-JM, PW1133G1R/2-JM, PW1133GA/2-JM, PW1133GAR/2-JM, PW1133GH/2-JM, PW1133GR/2-JM, PW1133GS/2-JM, PW1133GAS/2-JM, PW1133G1S/2-JM, PW1130G/2-JM, PW1130GS/2-JM, PW1129G/2-JM, PW1127G/2-JM, PW1127G1/2-JM, PW1127G1A/2-JM, PW1127G1B/2-JM, PW1127GA/2-JM, PW1127GH/2-JM, PW1124G/2-JM, PW1124G1/2-JM, PW1431G-JM, PW1431GA-JM, PW1431GH-JM, PW1428G- JM, PW1428GA-JM, and PW1428GH-JM Date: 07/10/2026 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00087EN ) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft i n accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided t hey are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: International Aero Engines, LLC 400 Main Street East Hartford, CT 06118 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 three-stage low pressure turbine that directly drives a three-stage low pressure compressor, and a single stage high bypass ratio fan through a fan drive gear speed reduction system. The high pressure compressor has eight axial stages driven by a two-stage cooled high-pressure turbine. MODELS: PW1133G-JM PW1133GA-JM PW1133G1-JM PW1130G-JM PW1130GS-JM PW1133G/2-JM PW1133GA/2-JM PW1133G1/2-JM PW1130G/2-JM PW1130GS/2-JM PW1431G-JM PW1431GA-JM PW1431GH-JM PW1428G-JM PW1428GA-JM PW1428GH-JM PW1129G-JM PW1129G/2-JM RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Takeoff (5 minutes) Maximum Continuous 33,110 32,780 30,410 (PW1130G-JM & PW1130G/2-JM) 21,400 (PW1130GS- JM, PW1130GS/2-JM) 31,572 31,068 29,761 28,450 29,245 26,345 FLAT RATING AMBIENT TEMPERATURE Takeoff Maximum Continuous 30°C / 86°F 25°C / 77°F 55°C / 131°F (PW1130GS-JM, PW1130GS/2-JM) 30°C / 86°F 25°C / 77°F 30°C / 86°F 30°C / 86°F 44°C / 111°F 25°C / 77°F Data Storage Unit (DSU) PN (Ratings Plug) Service Bulletin PW30K-A-73-00-0066-00A-930A-D provides a listing of DSU Part Numbers. TCDS E00087EN Page 2 of 12 COMPONENTS/CONFIGURATION For information regarding components and engine configuration, refer to: PW1100G-JM Installation Drawing 5320001 PW1400G-JM Installation Drawing 5330001 PW1100G/2-JM Installation Drawing 5360001 MODELS: PW1127G-JM PW1127GA-JM PW1127G/2-JM PW1127GA/2-JM PW1124G-JM PW1124G1-JM PW1124G/2-JM PW1124G1/2-JM PW1127G1-JM PW1127G1A-JM PW1127G1B-JM PW1127G1/2-JM PW1127G1A/2-JM PW1127G1B/2-JM PW1127GH/2-JM PW1133GR-JM PW1133GAR-JM PW1133G1R-JM PW1133GS-JM PW1133GAS-JM PW1133G1S-JM PW1133GR/2-JM PW1133GAR/2-JM PW1133G1R/2-JM PW1133GS/2-JM PW1133GAS/2-JM PW1133G1S/2-JM PW1133GH/2-JM PW1134GA/2-JM PW1134G1/2-JM RATINGS (See NOTE 1) SEA LEVEL STATIC THRUST (lb.) Takeoff (5 minutes) Maximum Continuous 27,075 26,345 24,240 24,035 27,075 24,070 33,110 23,250 FLAT RATING AMBIENT TEMPERATURE Takeoff Maximum Continuous 47°C / 117°F 25°C / 77°F 51°C / 123°F 25°C / 77°F 47°C / 117°F 30°C / 86°F 30°C / 86°F 55°C / 131°F Data Storage Unit (DSU) PN (Ratings Plug) Service Bulletin PW30K-A-73-00-0066-00A-930A-D provides a listing of DSU Part Numbers. TCDS E00087EN Page 3 of 12 MODELS: (cont.) PW1133G-JM PW1133GA-JM PW1133G1-JM PW1130G-JM PW1130GS-JM PW1133G/2-JM PW1133GA/2-JM PW1133G1/2-JM PW1130G/2-JM PW1130GS/2-JM PW1431G-JM PW1431GA-JM PW1431GH-JM PW1428G-JM PW1428GA-JM PW1428GH-JM PW1129G-JM PW1129G/2-JM PRINCIPAL DIMENSIONS (Room temperature) Length (flange to flange, in.) Length (fan spinner face to #6 bearing heatshield, in.) Nominal diameter (fan case, in.) Maximum radial projection (in.) (at oil tank) CENTER OF GRAVITY (in.) Axial engine station, relative to A-flange: Vertical, relative to engine centerline: Lateral, relative to centerline: 129.285 in +/- 0.051 134.350 in 87.566 in 50.150 in 63.510 in 63.688 in (PW1100G/2-JM models) - 1.420 in - 1.250 in (PW1100G/2-JM models) 0.820 in 0.290 in (PW1100G/2-JM models) -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- WEIGHT * (DRY) Basic engine (lbs.) 6,300 6,300 6,300 6,300 *The PW1100G-JM & PW1100G/2-JM engine weight is defined as the dry weight of the basic engine with IAE, LLC supplied engine build-up component (EBU1). EBU1 components include: Low Oil Pressure Switch; Core Nacelle Temperature Sensor; GBX Breather Tube; Engine Air Turbine Starter; starter attachment hardware and seals to gearbox; duct from starter to Starter Air Valve; Starter Air Valve; electrical harnesses; Mass Fuel Flow Meter; environmental control system Intermediate Pressure Check Valve. The PW1400G-JM engine weight is defined as the dry weight of the basic engine with standard equipment only FUEL Service Bulletin PW1000G-D-73-00-0002-00A-930A-D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the PW1100G-JM & PW1100G/2-JM series turbofan engines. Service Bulletin PW1000G-C-73-00-0001-00B-930A-D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the series turbofan engines. PW1400G-JM series turbofan engines. LUBRICATING OILS Service Bulletin PW1000G-D-79-00-0002-00A-930A-D provides a listing of approved turbine oils for use in the PW1100G-JM & PW1100G/2-JM series turbofan engines. Service Bulletin PW1000G-C-79-00-0001-00B-930A-D provides a listing of approved turbine oils for use in the PW1400G-JM series turbofan engines. TCDS E00087EN Page 4 of 12 MODELS: (cont. ) PW1127G-JM PW1127GA-JM PW1127G/2-JM PW1127GA/2-JM PW1124G-JM PW1124G1-JM PW1124G/2-JM PW1124G1/2-JM PW1127G1-JM PW1127G1A-JM PW1127G1B-JM PW1127G1/2-JM PW1127G1A/2-JM PW1127G1B/2-JM PW1127GH/2-JM PW1133GR-JM PW1133GAR-JM PW1133G1R-JM PW1133GS-JM PW1133GAS-JM PW1133G1S-JM PW1133GR/2-JM PW1133GAR/2-JM PW1133G1R/2-JM PW1133GS/2-JM PW1133GAS/2-JM PW1133G1S/2-JM PW1133GH/2-JM PW1134GA/2-JM PW1134G1/2-JM PRINCIPAL DIMENSIONS (Room temperature) Length (flange to flange, in.) Length (fan spinner face to #6 bearing heatshield, in.) Nominal diameter (fan case, in.) Maximum radial projection (in.) (at oil tank) CENTER OF GRAVITY (in.) Axial engine station, relative to A-flange: Vertical, relative to engine centerline: Lateral, relative to centerline: 129.285 in +/- 0.051 134.350 in 87.566 in 50.150 in 63.510 in 63.688 in (PW1100G/2-JM models) - 1.420 in - 1.250 in (PW1100G/2-JM models) 0.820 in 0.290 in (PW1100G/2-JM models) -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- WEIGHT * (DRY) Basic engine (lbs.) 6,300 6,300 6,300 6,300 *The PW1100G-JM & PW1100G/2-JM engine weight is defined as the dry weight of the basic engine with IAE, LLC supplied engine build-up component (EBU1). EBU1 components include: Low Oil Pressure Switch; Core Nacelle Temperature Sensor; GBX Breather Tube; Engine Air Turbine Starter; starter attachment hardware and seals to gearbox; duct from starter to Starter Air Valve; Starter Air Valve; electrical harnesses; Mass Fuel Flow Meter; environmental control system Intermediate Pressure Check Valve. The PW1400G-JM engine weight is defined as the dry weight of the basic engine with standard equipment only FUEL Service Bulletin PW1000G-D-73-00-0002-00A-930A-D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the PW1100G-JM & PW1100G/2- JM series turbofan engines. Service Bulletin PW1000G-C-73-00-0001-00B-930A-D defines the fuels requirements and provides a listing of approved fuels and fuel additives for use in the and PW1400G-JM series turbofan engines. LUBRICATING OILS Service Bulletin PW1000G-D-79-00-0002-00A-930A-D provides a listing of approved turbine oils for use in the PW1100G-JM & PW1100G/2-JM series turbofan engines. Service Bulletin PW1000G-C-79-00-0001-00B-930A-D provides a listing of approved turbine oils for use in the PW1400G-JM series turbofan engines. TCDS E00087EN Page 5 of 12 CERTIFICATION BASIS PW1100G-JM & PW1400G-JM Engine Models • 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-32 • Equivalent Level of Safety findings: o 33.76, Bird Ingestion, par. (c)(7)(i) ELOS No. TC3289EN-E-P-8-R1 o 33.77, Foreign Object Ingestion-Ice, par. (c) ELOS No. TC3289EN-E-P-5-R1 o 33.78, Rain and Hail Ingestion, par. (a)(1) ELOS No. TC3289EN-E-P-6-R1 o 33.27, Rotor Overspeed, par. (c) & (e) ELOS No TC3289EN-E-P-9 • Exemptions: o 33.76, Bird Ingestion, par. (c)(6)(i) and (c)(7)(vii), Exemption No. 23174A. Applicable to engine models PW1133GR-JM, PW1133GAR-JM, PW1133G1R-JM, PW1130GS-JM, PW1133GS-JM, PW1133GAS-JM, and PW1133G1S-JM only. • 14 CFR, Part 34, Amendment 34-1 through 34-7A, effective May 24, 2024. See NOTE 23 for detailed summary of the certification basis for fuel venting and exhaust emissions. TYPE CERTIFICATE NUMBER: E00087EN MODEL APPLICATION ISSUED/AMENDED DELETED PW1133G-JM December 15, 2011 December 19, 2014 PW1133GA-JM June 12, 2015 October 23, 2015 PW1130G-JM December 15, 2011 October 23, 2015 PW1127G-JM December 15, 2011 October 23, 2015 PW1127GA-JM June 12, 2015 October 23, 2015 PW1127G1-JM December 15, 2011 August 16, 2023 PW1124G-JM December 15, 2011 October 23, 2015 PW1124G1-JM December 15, 2011 October 23, 2015 PW1122G-JM December 15, 2011 October 23, 2015 January 28, 2026 PW1431G-JM January 20, 2015 May 6, 2016 PW1129G-JM April 11, 2017 May 29, 2018 PW1431GA-JM October 3, 2017 May 29, 2018 PW1431GH-JM October 3, 2017 May 29, 2018 PW1428G-JM October 3, 2017 May 29, 2018 PW1428GA-JM October 3, 2017 May 29, 2018 PW1428GH-JM October 3, 2017 May 29, 2018 PW1127G1A-JM June 22, 2021 August 16, 2023 PW1127G1B-JM June 22, 2021 August 16, 2023 PW1133G1-JM December 11, 2023 December 12, 2024 PW1133GR-JM December 11, 2023 December 12, 2024 PW1133GAR-JM December 11, 2023 December 12, 2024 PW1133G1R-JM December 11, 2023 December 12, 2024 PW1130GS-JM April 23, 2025 June 26, 2026 PW1133GS-JM April 23, 2025 June 26, 2026 PW1133GAS-JM April 23, 2025 June 26, 2026 PW1133G1S-JM April 23, 2025 June 26, 2026 TCDS E00087EN Page 6 of 12 PW1100G/2-JM Engine Models • 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-32, §§33.68 & 33.77, Amendment 34 with the following • Equivalent Level of Safety findings: o 33.78, Rain and Hail Ingestion, par. (a)(1) ELOS No. TC3289EN-E-P-6-R1 o 33.27, Rotor Overspeed, par. (c) & (e) ELOS No TC3289EN-E-P-9 • Exemptions: o 33.76, Bird Ingestion, par. (c)(6)(i) and (c)(7)(vii), Exemption No. 23174A. Applicable to engine models: PW1133GH/2-JM, PW1134GA/2-JM, PW1134G1/2- JM, PW1133GR/2-JM, PW1133GAR/2-JM, PW1133G1R/2-JM, PW1130GS/2-JM, PW1133GS/2-JM, PW1133GAS/2-JM and PW1133G1S/2-JM only. • 14 CFR, Part 34, Amendment 34-1 through 34-7A, effective May 24, 2024. See NOTE 23 for detailed summary of the certification basis for fuel venting and exhaust emissions. TYPE CERTIFICATE NUMBER: E00087EN MODEL PW1133GR/2-JM PW1133GAR/2-JM PW1133G1R/2-JM PW1133GH/2-JM PW1134GA/2-JM PW1134G1/2-JM PW1133G/2-JM PW1133GA/2-JM PW1133G1/2-JM PW1130G/2-JM PW1129G/2-JM PW1127G/2-JM PW1127GA/2-JM PW1127G1/2-JM PW1127G1A/2-JM PW1127G1B/2-JM PW1127GH/2-JM PW1124G/2-JM PW1124G1/2-JM PW1122G/2-JM PW1130GS/2-JM PW1133GS/2-JM PW1133GAS/2-JM PW1133G1S/2-JM APPLICATION April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 03, 2019 April 23, 2025 April 23, 2025 April 23, 2025 April 23, 2025 ISSUE/AMENDED February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 February 26, 2025 June 26, 2026 June 26, 2026 June 26, 2026 June 26, 2026 DELETED January 28, 2026 PRODUCTION BASIS (ALL MODELS) Production Certificate No. 114 TCDS E00087EN Page 7 of 12 NOTES NOTE 1. ENGINE RATINGS Engine ratings are based on calibrated test stand performance under the following conditions: 1. Sea level static, standard pressure (14.696 psia), up to the flat rating ambient temperature °F 2. No customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery 4. Production aircraft flight cowling corrected to ideal conditions 5. Production instrumentation 6. Fuel lower heating value of 18,400 BTU/lb. 7. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. NOTE 2. TEMPERATURES Maximum permissible Indicated Turbine Temperatures (ITT) are as follows: Condition Inter-Turbine Temperature (PW1100G-JM) Inter-Turbine Temperature (PW1100G/2-JM) 2 Takeoff (5 Minutes) 1 Actual Redline 1,083 degC / 1,982 degF 1,093 degC / 1,999 degF Cockpit Indicated 1,083 degC / 1,982 degF 1,083 degC / 1,982 degF Maximum Continuous Actual Redline 1,043 degC / 1,909 degF 1,051 degC / 1,923 degF Cockpit Indicated 1,043 degC / 1,909 degF 1,043 degC / 1,909 degF Start-up Ground Actual Redline 1,083 degC / 1,982 degF 1,093 degC / 1,999 degF Cockpit Indicated 1,083 degC / 1,982 degF 1,083 degC / 1,982 degF Start-up In-flight Actual Redline 1,083 degC / 1,982 degF 1,093 degC / 1,999 degF Cockpit Indicated 1,083 degC / 1,982 degF 1,083 degC / 1,982 degF 1. May be extended to 10 minutes for One Engine Inoperative (O.E.I.) contingency. 2. The cockpit and aircraft flight manuals will reflect temperature limits consistent with PW1100G-JM, but the EEC Software allows Actual Redline limits shown above. Oil outlet temperature: Continuous operation: Engine main oil temperature maximum limit varies with engine power level. The limit decreases from 152 degC /305 degF at idle power; to 146 degC /295 degF at cruise power; to 141 degC /285 deg F at high power. See PW1100G-JM & PW1100G/2-JM Installation and Operating Manual, PWA-9851 or PW1400G-JM Installation and Operating Manual, PWA-9914 for details. Minimum oil temperature at idle, before takeoff power operation: For PW1100G-JM & PW1100G/2-JM series turbofan engines: 51.7 degC / 125 degF For PW1400G-JM series turbofan engines: 37.7 degC / 100 degF Fuel Temperatures: See PW1100G-JM & PW1100G/2-JM Installation and Operating Manual, PWA-9851 or PW1400G-JM Installation and Operating Manual, PWA-9914 for details Component Temperatures: See PW1100G-JM & PW1100G/2-JM Installation and Operating Manual, PWA-9851 or PW1400G-JM Installation and Operating Manual, PWA-9914 for details NOTE 3. PRESSURES 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 but not greater than 60 psig with a vapor/liquid ratio of zero. The maximum allowable pressure at the fuel pump inlet after shutdown is 151 psig. Oil pressure limits: Minimum: 63 psig at idle. Variable by N2 Speed off idle. See PW1100G-JM & PW1100G/2-JM Installation and Operating Manual, PWA- 9851 or PW1400G-JM Installation and Operating Manual, PWA-9914 for details. Maximum: 270 psig Oil supply pressure is measured relative to ambient pressure: Temporary interruption associated with negative “g” operation is limited to 10 seconds maximum. Normal oil pressure will be restored rapidly once the negative “g” effect has been eliminated. TCDS E00087EN Page 8 of 12 NOTE 4. ACCESSORY DRIVE PROVISIONS PW1100G-JM & PW1100G/2-JM ACCESSORY DRIVES Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overload Static Hydraulic Pump Integrated Drive Generator (IDG) Air Turbine Starter CCW CCW CCW 0.1768 : 1 0.3932 : 1 0.407 : 1 1300 1990* --- 1800 4475* 10692 4250 9400 9084 400 900 280 CCW = Counterclockwise (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. PW1400G-JM ACCESSORY DRIVES Drive Pad Rotation Speed Ratio to N2 Torque (lb.-in.) Overhung Moment (lb.-in.) Continuous Overload Static Hydraulic Pump Variable Frequency Generator (VFG) Air Turbine Starter CCW CCW CCW 0.1763 : 1 0.9611 : 1 0.407 : 1 1300 1000* --- 1800 1300* 10692 4250 7655 9084 400 1275 280 CCW = Counterclockwise (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. NOTE 5. MODEL DESCRIPTION The PW1100G-JM engine series consists of the following engine models: PW1100G-JM Engine Models Associated A/C Model Description PW1124G-JM A319-171N Basic Model PW1124G1-JM A320-272N Alternate Climb Thrust Model PW1127G-JM A320-271N Basic Model PW1127GA-JM A320-271N Alternate Climb Thrust Model PW1127G1-JM+ A319-173N Hot and High Thrust Model, Reduced Go Around Thrust A320-271N Basic Model, Reduced Go Around Thrust PW1127G1A-JM+ A320-271N Alternate Climb Thrust Model, Reduced Go Around Thrust Alternate Climb C, Reduced Go Around Thrust PW1127G1B-JM+ A320-271N Alternate Climb Thrust Model, Reduced Go Around Thrust PW1129G-JM+ A320-273N High and Hot Airfield Thrust Model PW1130G-JM A321-272N A321-272NX Reduced Thrust Model PW1130GS-JM+ A321-272N A321-272NX Reduced Thrust Model, Reduced Go Around Thrust PW1133G-JM A321-271N A321-271NX Basic Model PW1133GA-JM A321-271N A321-271NX Alternate Climb Thrust Model Alternate Climb C Thrust Model PW1133G1-JM^ A321-271N A321-271NX Hot Day Take Off Boost PW1133GR-JM+ A321-271NY Basic Model, Reduced Go Around Thrust PW1133GS-JM+ A321-271N A321-271NX Basic Model, Reduced Go Around Thrust PW1133GAS-JM+ A321-271NX A321-271NX Alternate Climb A Thrust Model, Reduced Go Around Thrust PW1133G1S-JM+^ A321-271N A321-271NX Hot Day Take Off Boost, Reduced Go Around Thrust PW1133GAR-JM+ A321-271NY Alternate Climb Thrust Model, Reduced Go Around Thrust PW1133G1R-JM+^ A321-271NY Hot Day Take Off Boost, Alternate Climb Thrust Model, Reduced Go Around Thrust TCDS E00087EN Page 9 of 12 NOTE 5 – cont’d. The PW1100G/2-JM engine series consists of the following engine models: PW1100G/2-JM Engine Models Associated A/C Model Description PW1124G/2-JM A319-171N Basic Model PW1124G1/2-JM A320-272N Alternate Climb Thrust Model PW1127G/2-JM A320-271N Basic Model PW1127GA/2-JM A320-271N Alternate Climb Thrust Model PW1127G1/2-JM+ A319-173N Hot and High Thrust Model, Reduced Go Around Thrust A320-271N Basic Model, Reduced Go Around Thrust PW1127G1A/2-JM+ A320-271N Alternate Climb Thrust Model, Reduced Go Around Thrust PW1127G1B/2-JM+ A320-271N Alternate Climb Thrust Model, Reduced Go Around Thrust PW1127GH/2-JM+ A320-271N Hot and High Thrust Model PW1129G/2-JM+ A320-273N High and Hot Airfield Thrust Model PW1130G/2-JM A321-272N Reduced Thrust Model A321-272NX PW1130GS/2-JM+ A321-272N A321-272NX Reduced Thrust Model, Reduced Go Around Thrust PW1133G/2-JM A321-271N Basic Model A321-271NX PW1133GA/2-JM A321-271N Alternate Climb Thrust Model A321-271NX PW1133G1/2-JM^ A321-271N Hot Day Take Off Boost A321-271NX PW1133GR/2-JM+ A321-271NY Basic Model, Reduced Go Around Thrust PW1133GS/2-JM+ A321-271N A321-271NX Basic Model, Reduced Go Around Thrust PW1133GAS/2-JM+ A321-271N A321-271NX Alternate Climb A Thrust Model, Reduced Go Around Thrust PW1133G1S/2-JM+^ A321-271N A321-271NX Hot Day Take Off Boost, Reduced Go Around Thrust PW1133GAR/2-JM+ A321-271NY Alternate Climb Thrust Model, Reduced Go Around Thrust PW1133G1R/2-JM+^ A321-271NY Hot Day Take Off Boost, Alternate Climb Thrust Model, Reduced Go Around Thrust PW1133GH/2-JM+ A321-271NY Hot and High Thrust Model, Reduced Go Around Thrust A321-271N Hot and High Thrust Model, Reduced Go Around Thrust A321-271NX PW1134GA/2-JM+ A321-271NY 4% Take Off & Max Continuous Boost, Alternate Climb Thrust Model, Reduced Go Around Thrust PW1134G1/2-JM+ A321-271NY 4% Take Off & Max Continuous Boost, Reduced Go Around Thrust + These models include different thrust levels for Go-Around. The thrust is selected by the Electronic Engine Control (EEC) based on aircraft & engine inputs. The Go-Around thrust is less than the maximum rated takeoff thrust of the PW1100G-JM & PW1100G/2-JM engine, as agreed with the Aircraft Type Certificate Holder. See Installation and Operating Manual PWA-9851. ^ These models include a cockpit selectable thrust boost of 2% increased thrust. The 2% thrust boost is equal to or less than the maximum rated takeoff thrust of the PW1100G-JM & PW1100G/2-JM engine. The PW1400G-JM engine series consists of the following engine models: PW1400G-JM Engine Models Associated A/C Model Description PW1428G-JM Irkut MC21-200 Basic Model PW1428GA-JM Irkut MC21-200 Alternate Climb Thrust Model PW1428GH-JM Irkut MC21-200 High and Hot Airfield Thrust Model PW1431G-JM Irkut MC21-300 Basic Model PW1431GA-JM Irkut MC21-300 Alternate Climb Thrust Model PW1431GH-JM Irkut MC21-300 High and Hot Airfield Thrust Model TCDS E00087EN Page 10 of 12 NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN For the PW1100G-JM & PW1100G/2-JM Engine Models: Air Turbine Starter; Starter Air Valve. NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN For the PW1400G-JM Engine Models: Environmental Control System Intermediate Pressure Check Valve NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not Applicable NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS PW1100G-JM Engine mount system provisions are specified in Installation Drawing 5320001 and Mount and Maneuver Load Drawing 5360003. PW1400G-JM Engine mount system provisions are specified in Installation Drawing 5330001 and Mount and Maneuver Load Drawing 5330003. PW1100G/2-JM Engine mount system provisions are specified in Installation Drawing 5360001 and Mount and Maneuver Load Drawing 5360003. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS