# TCDS E40NE: International Aero Engines AG (IAE) - Type: Type certificate data sheet - Status: Current - Holder: International Aero Engines AG (IAE) - Revision: 14 - Revised: August 6, 2024 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 443, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/8f/a7/8fa75603e070b7d208db45d37300e72dca8473e33e14e03738b9707bc17c300e - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID120559842520240807131501.0001 - Page: https://openairdocs.org/tcds/E40NE ## Models (10) As the data sheet lists them. - V2528-D5 - V2533-A5 - V2531-E5 - V2530-A5 - V2525-D5 - V2527-A5 - V2524-A5 - V2527E-A5 - V2522-A5 - V2527M-A5 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 5 6 7 8 9 10 REV. 14 10 14 10 10 10 10 13 10 14 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE SHEET E40NE TCDS NUMBER E40NE REVISION: 14 * DATE: August 6, 2024 INTERNATIONAL AERO ENGINES AG MODELS: V2522-A5 V2525-D5 V2524-A5 V2528-D5 V2527-A5 V2533-A5 V2527E-A5 V2531-E5 V2527M-A5 V2530-A5 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E40NE) 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 HOLDER International Aero Engines AG (IAE) c/o IAE Airworthiness 400 Main Street East Hartford, CT 06118 I. MODELS V2530-A5 V2527-A5 & V2527E-A5 V2527M-A5 V2522-A5 V2524-A5 TYPE Dual rotor, axial flow, high bypass turbofan, single-stage fan; four-stage low pressure compressor, ten-stage high pressure compressor, annular combustor, two-stage high-pressure turbine, five-stage low pressure turbine. RATINGS (SEE NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min.) at sea level, static thrust, lb OEI (See NOTE 21) 26,950 29,900 22,240 24,800 19,200 23,040 19,200 24,480 COMPONENTS For information refer to the Installation and Operating Manual (IOM); Installation Handbook; Illustrated Parts Catalogue or Approved Parts List. PRINCIPAL DIMENSIONS (in) Length Normal diameter Maximum radial projection 126.0205 66.23 43.048 - - - - - - 126.0205 66.23 43.048 - - - - - - TCDS E40NE PAGE 2 I. MODELS V2528-D5 V2525-D5 V2533-A5 V2531-E5 TYPE Dual rotor, axial flow, high bypass turbofan, single-stage fan; four-stage low pressure compressor, ten-stage high pressure compressor, annular combustor, two-stage high-pressure turbine, five-stage low pressure turbine. RATINGS (SEE NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min.) at sea level, static thrust, lb 25,660 28,000 23,900 25,000 26,950 31,600 25,430 31,330 COMPONENTS For information refer to the Installation and Operating Manual (IOM); Installation Handbook; Illustrated Parts Catalogue or Approved Parts List. PRINCIPAL DIMENSIONS (in) Length Normal diameter Maximum radial projection 126.0205 66.23 43.665 - - - - - - - - - - 43,048 - - - - 43.048 I. MODELS (cont.) V2530-A5 V2533-A5 V2527-A5 V2527E-A5 V2527M-A5 V2522-A5 V2524-A5 V2525-D5 V2528-D5 V2531-E5 WEIGHT (DRY) (Includes all essential accessories, but excludes starter, exhaust nozzle, and power source for the ignition system for the -A5/-E5 series, and exhaust nozzle for the –D5 series) 2,404 kg/ 5,300 lb - - - - 2,595 kg/ 5,720 lb 2,404 kg / 5,300 lb CENTER OF GRAVITY (in) Aft of front mount area centerline Below engine centerline Starboard of engine vertical centerline 15.7+1.0 1.7+0.5 0.7+.5 - - - - - - - - - - - - 14.1+1.0 1.6+.5 0.1+.5 14.8 + 1.0 0.3 + 0.5 -2.4 + 0.5 FUEL (SEE NOTE 10) OIL (SEE NOTES 11) TCDS E40NE PAGE 3 CERTIFICATION BASIS 1. For V2530-A5, V2527-A5, V2527E-A5, V2528-D5, V2525-D5: 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-14 inclusive. For V2522-A5, V2524-A5, V2527M-A5, V2533-A5, V2531-E5: 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-14, inclusive and 14 CFR 33.28, amendment 33-15. 2. The following models comply with 14 CFR part 34, amendment 5a, effective October 23, 2013: See note 13 for detailed summary of the certification basis for fuel venting and exhaust emissions for: V2525-D5, V2528-D5 and the following engine models with engine serial numbers (S/N) up to and including S/N V15001; V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5. See note 14 for detailed summary of the certification basis for fuel venting and exhaust emissions for the following: V2531-E5 and the following engine models with engine S/N after S/N V15001; V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5. The following models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024: See note 23 for detailed summary of the certification basis for fuel venting and exhaust emissions for the following engine models with engine S/N after S/N V19014: V2533-A5, V2530-A5, V2527-A5, V2527E-A5, V2527M-A5, V2524- A5, V2522-A5, and the following engine model with engine S/N after S/N V30019; V2531-E5. Model Date of Application Issued/Revised V2530-A5/V2527-A5 NOV.17 1989 (Orig) NOV 24, 1992 OCT 12, 1992 (Rev) V2528-D5/V2525-D5 MAR 22, 1990 (Orig) NOV 24, 1992 OCT 19, 1992 (Rev) V2527E-A5 JUN 6, 1995 AUG 4, 1995 V2522-A5/V2524-A5 JUL 24, 1995 APR 19, 1996 V2533-A5 DEC 16, 1994 AUG 21, 1996 V2527M-A5 FEB 25, 1999 MAY 3, 1999 V2531-E5 AUG 15, 2011 JUL 31, 2014 PRODUCTION BASIS Production Certification No. 114NE TCDS E40NE PAGE 4 NOTES NOTE 1. Maximum permissible engine operating speeds for the engine rotors as follows: Low Pressure rotor (N1), RPM 5,650 (100%) High Pressure rotor (N2), RPM 14,950 (100%) NOTE 2. Turbine Exhaust Gas Temperature (Actual/Indicated °C) (See NOTE 19) Takeoff ( 5 min) Maximum Continuous Start Ground Inflight Takeoff ( 5 min) Maximum Continuous Start Ground Inflight Oil Outlet Temperature Continuous operation Transient operation (15 min.) V2527-A5* & V2527E-A5 & V2530-A5 V2527M-A5 V2522-A5 V2524-A5 V2525-D5 V2528-D5 650/650 645/635 625/635 635/635 620/620 635/635 610/610 - - - - - - - - - - 635/635 - - - - - - - - - - 635/635 - - - - - - - - - - V2533-A5 V2531-E5 670/650 670/670 610/610 - - 635/635 - - 635/635 - - (All Models) 155°C/311°F 165°C/329°F maximum *The cockpit and aircraft flight manuals for SCN9A (V2527-A5) will reflect a ground and air start limit of 635ºC, but the ECC software allows an actual limit of 645ºC. All other and subsequent software versions have a software limit of 635ºC. NOTE 3. Fuel Pressure Oil Pressure Fuel and oil 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. 60 psig minimum. NOTE 4. (A) Maximum permissible air bleed extraction for the V2522-A5, V2524-A5, V2527-A5, V2527M-A5, V2530-A5, V2527E-A5, V2533-A5 and V2531-E5 is as follows: Max Bleed Limit(2) 7th Stage Bleed ( % of core flow (WA26)) At or below 90% 8.2% Corrected high rotor speed From 90% to 97% Linear variation from Corrected high rotor speed 8.2% to 6.0% At or above 97% 6.0% Corrected high rotor speed TCDS E40NE PAGE 5 NOTE 4. (Continued) 10th Stage Bleed(1) At or below 61% corrected 13.7% high rotor speed From 61% to 78% corrected Linear variation from high rotor speed 13.7% to 12.0% From 78% to 97% corrected Linear variation from high rotor speed 12.0% to 6.0% At or above 97% corrected 6.0% high rotor speed (1) No 10th Stage bleed allowed below 22,000 ft. at Max. Continuous Rating and above. (2) Simultaneous use of 7th and 10th stage bleed at limiting conditions is allowed only when required by a malfunction and only until the next landing. (B) Maximum permissible air bleed extraction for the V2525-D5, V2528-D5 is as follows: Single Stage Bleed: Max Single Stage Bleed Limit(2) 7th Stage Bleed (% of core flow (WA26)); At or below 100% corrected N2 9.2% 10th Stage Bleed(1) From minimum idle to 65% corrected N2 linear variation from 16% to 18%(5) From 65% to 75% corrected N2 linear variation from 18% to 16% From 75% to 84% corrected N2 16% From 84% to 97.5% corrected N2 linear variation from 16% to 7% From 97.5% to 100% corrected N2 7% Mixed Stage Bleed: Max Mixed Stage Bleed Limit(3) 7th Stage Bleed (% of core flow (WA26)) From 79% to 86.5% corrected N2 linear variation from 0% to 9% From 86.5% to 96% corrected N2 9% 10th Stage Bleed(4) From 79% to 84% corrected N2 16% From 84% to 93.6% corrected N2 linear variation from 16% to 4% From 93.6% to 96% corrected N2 4% TCDS E40NE PAGE 6 NOTE 4. (Continued) (1) Below 24,000 ft.: - At ambient temperatures above 40°F, no 10th stage bleed is allowed at Max. Continuous Rating and above. - At 40°F ambient temperature and below, a maximum of 2% 10th stage bleed is allowed at takeoff rating and 4% 10th stage bleed at Max. Continuous Rating. (2) The allowable 7th and/or 10th stage bleed is in addition to the bleed used for inlet cowl anti-icing. (3) Simultaneous use of 7th and 10th stage bleed is allowed at any power condition due to malfunction and only until the next landing. (4) When simultaneous bleed flow is required, the addition of the 7th and 10th stage bleed may not exceed the total extraction limits shown below. (5) 18% for ambient temperatures of 30°F and below only. Total Simultaneous Bleed Flow Max Combined Bleed Limit (%WA26) From 79% to 80% corrected N2 linear variation from 16% to 16.5% From 80% to 87.5% corrected N2 16.5% From 87.5% to 91% corrected N2 linear variation from 16.5% to 12.5% From 91% to 96% corrected N2 12.5% NOTE 5. The ratings are based on Sea Level Static test stand operation under the following condition: - Engine inlet air at 59°F and 29.92 in.Hg. - Specified fuel and oil (see NOTES 10 and 11). - No fan or compressor air bleed or load on accessory drives. - Ideal inlet pressure recovery. - A mixed exhaust system having no internal pressure losses and a mixed primary nozzle velocity coefficient equal to 1.0. - Takeoff rating is a maximum thrust certified for takeoff operation. The specified takeoff thrust is available at and below: V2527-A5 & V2530-A5 & V2527E-A5 & V2522-A5 V2525-D5 V2533-A5 V2527M-A5 V2524-A5 V2528-D5 V2531-E5 ISA+15°C/27°F ISA+31°C/56°F ISA+40°C/72°F ISA+15°C/27°F ISA+20oC/36°F Maximum Continuous rating is the maximum thrust certified for continuous operation. The specified thrust is available at and below ISA +18°F (10°C) ambient temperature. TCDS E40NE PAGE 7 NOTE 6. The accessory drive provisions shown in the following tabulation are incorporated in the V2530-A5, V2527-A5, V2527E-A5, V2527M-A5, V2522-A5, V2524-A5, V2533-A5, V2531-E5 Speed Ratio Torque Torque to Turbine (lb.-in.) (lb.-in.) Overhang Drive Rotation Shaft Cont. Static Overload (lb. - in.) Starter CCW 0.941:1 - * - 550 IDGS CCW 0.604:1 ** 11000 ** 800 Fluid Power Pump CCW 0.267:1 1300 6500 1950 400 CCW = Counterclockwise * Maximum starter torque = 470 lb.-ft. at zero rpm. The maximum allowable starter torque value is 1175 lb.-ft. ** Maximum allowable continuous torque values are equivalent to 175 horsepower at any engine speed. The following overload conditions can be accommodated. Recurring Horsepower Duration Time Time (Hours) 225 5 minutes 1000 225 5 seconds 1 450 5 seconds 1000 NOTE 6. (cont.) The accessory drive provisions shown in the following tabulation are incorporated in the V2528-D5, V2525-D5 Speed Ratio Torque Torque to Turbine (lb.-in.) (lb.-in.) Overhang Drive Rotation Shaft Cont. Static Overload (lb. - in.) Starter CCW 0.941:1 - * - 550 VSCF CCW 1.582:1 ** 5500 ** 1000 Fluid Power Pump CCW 0.275:1 1100 4700 2100 100 CCW = Counterclockwise * Maximum starter torque = 470 lb.-ft. at zero rpm. The maximum allowable starter torque value is 1175 lb.-ft. ** Maximum allowable continuous torque values are equivalent to 140 horsepower at any engine speed. The following overload conditions can be accommodated. Recurring Horsepower Duration Time Time (Hours) 167 5 minutes 1000 225 5 seconds 1 335 5 seconds 1000 TCDS E40NE PAGE 8 NOTE 7. Power setting, power checks, and control of engine output in all operations is to be based upon International Aero Engines AG 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 is 24.8% (1,400 RPM). NOTE 9. Lightning and EMI protection capability of the electronic engine control system, including cables, are specified in the Installation and Operating Manual, IAE-0043 (V2500-A5) section 4.12, IAE-0174 (V2500-D5) section 4.12, IAE-0287 (V2500-E5) section 6.12. NOTE 10. Fuels and fuel additives conforming to the specifications listed in the latest applicable revision of the Installation and Operating Manual, IAE-0043 (V2500-A5), IAE-0174 (V2500-D5), IAE-0287 (V2500-E5), are approved for use in the V2500-A5/-D5/-E5 engine.. These fuels may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. NOTE 11. Oils conforming to the specifications listed in the latest applicable revision of the Installation and Operating Manual, IAE-0043 (V2500-A5), IAE-0174 (V2500-D5), IAE-0287 (V2500-E5), are approved for use in the V2500-A5/-D5/-E5 engine. NOTE 12. The V2500-A5/-D5/-E5 engines meet Federal Aviation Administration requirements for adequate turbine disk integrity and rotor blade containment and does not require external armoring. Certain engine parts are life limited. These limits are listed in the FAA approved International Aero Engines AG V2500 Series Time Limit Manual, Chapter 5. NOTE 13. 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: V2525-D5, V2528-D5 and the following engine models with engine S/N up to and including S/N V15001; V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5. 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 87.21 Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1); in addition, 40 CFR 87.21 Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.21 Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.21(d); in addition, 40 CFR 87.21 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 known as CAEP/4 have been demonstrated for the applicable serial numbers of these models. NOTE 14. 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: V2531-E5 and the following engine models with engine S/N after S/N V15001; V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5. 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. TCDS E40NE PAGE 9 NOTE 15. The maximum permissible V2500-A5/-D5/-E5 engine inlet distortion limit is specified in the Installation and Operating Manual, IAE-0043 (V2500-A5), IAE-0174 (V2500-D5), IAE-0287 (V2500-E5). NOTE 16. Information regarding transient rotor shaft overspeed rpm, as well as transient gas overtemperature and number of overtemperature occurrences, is specified in the Maintenance Document. NOTE 17. Note removed. NOTE 18. Time limited dispatch (TLD) limits for the V2500-A5/-D5/-E5 FADEC control system are listed in the Installation and Operating Manual, IAE-0043 (V2500-A5) section 4.13, IAE-0174 (V2500-D5) section 4.13 and IAE-0287 (V2500-E5) section 6.13. The technical data substantiating the IOM TLD limits are contained in IAE V2500 Reports IAE-0184, PWA-6564, PWA-6243 and PWA- 9834. NOTE 19. EEC software provides the capability of biasing indicated versus actual EGT values so as to provide consistent displayed EGT limit values to the aircraft. The actual versus indicated EGT values are controlled by a combination of EEC software, and Data Entry Plug (DEP) wiring scheme. Engine EGT limits are controlled by EEC P/N and DEP P/N, and are only implemented by specific service bulletin instructions. The engine data plate also reflects the engine limits configuration. NOTE 2 gives the maximum permissible approved EGT values for individual engine models, although these maximum values may not be implemented on all models. See the Installation and Operating Manual, IAE-0043 (V2500-A5), IAE-0174 (V2500-D5), IAE-0287 (V2500-E5), for information defining the EGT limit values currently assigned to specific engine models. NOTE 20. NOTE 21. Model Description: V2527-A5: Basic Model, Airbus A320 applications. V2530-A5: Basic Model, Airbus A321 applications. V2528-D5: Base Model, Douglas MD-90 applications. V2525-D5: Base model, Douglas MD-90 applications. V2527E-A5: Enhanced takeoff thrust model, Airbus A320 applications. The V2527E-A5 provides increased takeoff thrust at altitudes above sea level relative to the V2527-A5 base model. V2527M-A5: Enhanced climb thrust for Airbus A319 applications. V2522-A5: Reduced thrust model, Airbus A319 applications. V2524-A5: Reduced thrust model, Airbus A319 applications. V2533-A5: Increased takeoff thrust model, Airbus A321 applications. V2531-E5: Base Model, Embraer EMB-390 applications. Use of takeoff thrust for more than five minutes (not to exceed ten minutes) is approved for use only in the event of an inoperative engine due to shutdown or failure. TCDS E40NE PAGE 10 NOTE 22. Operating and Service Instructions Manuals required by 14 CFR 33.5 Manuals V2500-A5 V2500-D5 V2500-E5 Installation and Operating Manual IAE-0043 IAE-0174 IAE-0287-01 Operating Instructions OI-V2500-1IA OI-V2500-3IA OI-V2500-5IA Manuals required by 14 CFR 33.4 Instructions for Continued Airworthiness (ICA) V2500-A5 V2500-D5 V2500-E5 Time Limits Manual T-V2500-1IA 2A4408 T-V2500-3IA 2A4417 2A4384 Engine Shop Manual E-V2500-1IA 2A4407 E-V2500-3IA 2A4416 2A4383 Standard Practices Manual SPP-V2500-1IA / 2A4414 Powerplant Maintenance Manual * * 2A4386 Powerplant Fault Isolation Manual * * 2A4403 Component Maintenance Manuals As published by IAE Service Bulletins As published by IAE Consumable Materials Index 2A4413 * These instructions for continued airworthiness submitted in compliance to 14 CFR § 33.4 and Appendix A 33.3(a) resides in Chapter 70 of the respective Aircraft Maintenance Manual for all the identified models. NOTE 23. 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 the following engine models with engine S/N after S/N V19014: V2533-A5, V2530-A5, V2527-A5, V2527E-A5, V2527M-A5, V2524-A5, V2522-A5, and the following engine models with engine S/N after S/N V30019; V2531-E5. 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 finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards known as CAEP/6 have been demonstrated for Oxides of Nitrogen Emission Standards for Subsonic Engines, Carbon Monoxide Hydrocarbons, Part II Chapter 2 for fuel venting and CAEP/10 & 11 have been demonstrated for Non-Volatile Particulate Matter for the applicable serial numbers of these models. ---THE END--- ``` ## ADs (34, in force first) - [AD 2026-17-03](https://openairdocs.org/ad/2026-17-03): Turbine Engine Compressor Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Sep 24, 2026 - [AD 2025-19-13](https://openairdocs.org/ad/2025-19-13): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Oct 29, 2025 - [AD 2025-17-16](https://openairdocs.org/ad/2025-17-16): Turbine Engine Compressor Sections · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Oct 10, 2025 - [AD 2024-11-03](https://openairdocs.org/ad/2024-11-03): Turbine Engine · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Jun 26, 2024 - [AD 2022-02-09](https://openairdocs.org/ad/2022-02-09): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Mar 15, 2022 - [AD 2021-14-19](https://openairdocs.org/ad/2021-14-19): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Aug 5, 2021 - [AD 2021-11-51](https://openairdocs.org/ad/2021-11-51): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2527-A5 and 4 more. Effective Jul 19, 2021 - [AD 2021-05-18](https://openairdocs.org/ad/2021-05-18): Turbine Section · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 8 more. Effective Apr 29, 2021 - [AD 2021-01-03](https://openairdocs.org/ad/2021-01-03): Turbine Section · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 8 more. Effective Jan 21, 2021 - [AD 2020-09-03](https://openairdocs.org/ad/2020-09-03): Turbine Engine Compressor Section · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 8 more. Effective May 29, 2020 - [AD 2020-07-51](https://openairdocs.org/ad/2020-07-51): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 6 more. Effective Apr 28, 2020 - [AD 2019-18-01](https://openairdocs.org/ad/2019-18-01): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2527-A5 and 4 more. Effective Oct 15, 2019 - [AD 2019-16-01](https://openairdocs.org/ad/2019-16-01): Turbine section · International Aero Engines V2525-D5 and V2528-D5. Effective Sep 19, 2019 - [AD 2017-14-07](https://openairdocs.org/ad/2017-14-07): Turbine Engine · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Aug 21, 2017 - [AD 2016-25-11](https://openairdocs.org/ad/2016-25-11): No. 3 bearing · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Jan 20, 2017 - [AD 2016-18-10](https://openairdocs.org/ad/2016-18-10): High- pressure turbine (HPT) stage 2 hub · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 6 more. Effective Oct 7, 2016 - [AD 2015-10-04](https://openairdocs.org/ad/2015-10-04): HPC stage 3 to 8 drum · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Jul 1, 2015 - [AD 2013-07-10](https://openairdocs.org/ad/2013-07-10): Bearing internal scavenge tube and bearing external scavenge tube · International Aero Engines V2525-D5 and V2528-D5. Effective May 20, 2013 - [AD 2011-25-08](https://openairdocs.org/ad/2011-25-08): High- pressure turbine (HPT) case burn-through events · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Jan 17, 2012 - [AD 2010-06-18](https://openairdocs.org/ad/2010-06-18): Vortex reducers · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Apr 22, 2010 - [AD 2009-22-06](https://openairdocs.org/ad/2009-22-06): HPC stage 9-12 disc assembly · International Aero Engines V2500-A1, V2527E-A5, V2528-D5 and 1 more. Effective Nov 30, 2009 - [AD 2008-14-15](https://openairdocs.org/ad/2008-14-15): No. 4 bearing oil system components · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Aug 20, 2008 - [AD 2007-21-05](https://openairdocs.org/ad/2007-21-05): Monitoring of N2 vibration on all IAE V2500 series engines · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Nov 15, 2007 - [AD 2006-25-01](https://openairdocs.org/ad/2006-25-01): Master magnetic chip detector (MCD) · International Aero Engines V2522-A5, V2524-A5, V2527-A5 and 4 more. Effective Jan 8, 2007 - [AD 2004-12-08](https://openairdocs.org/ad/2004-12-08): Airworthiness Limitations Section (ALS) · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Jul 23, 2004 - [AD 2000-22-07](https://openairdocs.org/ad/2000-22-07): High Pressure Turbine (HPT) · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 6 more. Effective Dec 6, 2000 - [AD 99-13-01](https://openairdocs.org/ad/99-13-01): High Pressure Turbine (HPT) Stage 1 Inner Rotating Airseal (TOBI ID seal) · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 4 more. Effective Jun 25, 1999 - [AD 99-04-03](https://openairdocs.org/ad/99-04-03): High Pressure Compressor (HPC) Stage 9-12 Drum · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 5 more. Effective Apr 12, 1999 - [AD 2021-11-15](https://openairdocs.org/ad/2021-11-15) (historical): Turbine Section · International Aero Engines V2522-A5, V2524-A5, V2525-D5 and 7 more. Effective Jul 13, 2021 - [AD 2019-06-06](https://openairdocs.org/ad/2019-06-06) (historical): Turbine Engine Combustion Section · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Apr 12, 2019 - [AD 2012-09-09](https://openairdocs.org/ad/2012-09-09) (historical): High-pressure compressor (HPC) stage 3 to 8 drums · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Jun 27, 2012 - [AD 2010-20-07](https://openairdocs.org/ad/2010-20-07) (historical): Initial and repetitive on-wing ultrasonic inspections · International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective Nov 1, 2010 - [AD 2003-11-23](https://openairdocs.org/ad/2003-11-23) (historical): Master magnetic chip detector (MCD) · International Aero Engines V2522-A5, V2524-A5, V2527-A5 and 3 more. Effective Jun 20, 2003 - [AD 99-08-11](https://openairdocs.org/ad/99-08-11) (historical): International Aero Engines V2500-A1, V2522-A5, V2524-A5 and 7 more. Effective May 13, 1999 ## Registered aircraft by registry model (OpenAirDocs) - [IAE V2533-A5](https://openairdocs.org/engine/iae-v2533-a5): 270 aircraft (registry code 34611) - [IAE V2527-A5](https://openairdocs.org/engine/iae-v2527-a5): 113 aircraft (registry code 34604) - [IAE V2524-A5](https://openairdocs.org/engine/iae-v2524-a5): 27 aircraft (registry code 34608) - [IAE V2527E-A5](https://openairdocs.org/engine/iae-v2527e-a5): 27 aircraft (registry code 34605) - [IAE V2522-A5](https://openairdocs.org/engine/iae-v2522-a5): 2 aircraft (registry codes 34607, 34612) - [IAE V2528-D5](https://openairdocs.org/engine/iae-v2528-d5): 2 aircraft (registry code 34609) - [IAE V2530-A5](https://openairdocs.org/engine/iae-v2530-a5): 2 aircraft (registry code 34603) - [IAE V2525-D5](https://openairdocs.org/engine/iae-v2525-d5): 0 aircraft (registry code 34610) - [IAE V2527M-A5](https://openairdocs.org/engine/iae-v2527m-a5): 0 aircraft (registry code 34606) ## STCs approved under this data sheet (1) - [STC SE1091NE](https://openairdocs.org/stc/SE1091NE): Installation of thrust reverser/exhaust system.. Rohr Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.