- Effective
- September 24, 2026
- Published
- August 20, 2026 · 91 FR 53713–53717
- Issued
- September 4, 2026
- Models
- V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5 and 4 more
- Data sheet
- TCDSE40NE
- Registered aircraft
- 443 matched by model
- Product
- Engine · Large airplane
- ATA chapter
- 72 · Engine
- Amendment
- 39-23446
- Docket
- FAA-2025-2555
- Project
- AD-2025-00433-E
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 2026-16954. Only the govinfo PDF is the legal edition. DRS record last changed September 10, 2026.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 263 KB | 47761263…c42d643 | 2026-16954.pdf on govinfo.gov |
| Official PDF | 238 KB | fd37c28b…534702b | 2026-18423.pdf on govinfo.gov |
| Federal Register XML | 38 KB | 96724110…7117cea | 2026-16954.xml on federalregister.gov |
| Federal Register XML | 11 KB | 743c21bb…8072afd | 2026-18423.xml on federalregister.gov |
| FAA DRS HTML | 58 KB | 0430fe3c…a3a7133 | FAA DRS (API key needed) |
| FAA DRS HTML | 27 KB | 8c531223…68b6fa0 | FAA DRS (API key needed) |
On this page
Summary
The FAA is correcting an airworthiness directive (AD) that was published in the Federal Register. That AD applies to certain International Aero Engines AG (IAE AG) Model V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 engines. As published, paragraph (g) of the regulatory text contains a typographical error. This document corrects that error. In all other respects, the original document remains the same.
The airworthiness directive
2026-17-03 International Aero Engines AG: Amendment 39-23446; Docket No. FAA-2025-2555; Project Identifier AD-2025-00433-E.
(a) Effective Date
PDF page 1This airworthiness directive (AD) is effective September 24, 2026.
(b) Affected ADs
PDF page 1None.
(c) Applicability
PDF page 1This AD applies to International Aero Engines AG (IAE AG) Model V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 engines with a 3rd stage high-pressure compressor (HPC) rotor blade having part number (P/N) 6A8353 or P/N 6A8688 installed.
(d) Subject
PDF page 1Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section.
(e) Unsafe Condition
PDF page 1This AD was prompted by multiple reports of failed 3rd stage HPC rotor blades that resulted in engine fires, unplanned engine removals, aborted takeoffs, and in-flight shutdowns (IFSD). The FAA is issuing this AD to prevent failure of the 3rd stage HPC rotor blades. The unsafe condition, if not addressed, could result in engine fire, reduced control of the airplane, and engine IFSD.
(f) Compliance
PDF page 1Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
PDF page 1At the next engine shop visit after the effective date of this AD where the 3rd stage HPC rotor blade is exposed, replace the full set of 3rd stage HPC rotor blades with parts eligible for installation.
(h) Definitions
PDF page 1(1) For the purpose of this AD, a “part eligible for installation” is:
(i) A 3rd stage HPC rotor blade having P/N 6C8368, 6C8403, or later approved P/N; or
(ii) A 3rd stage HPC rotor blade modified to P/N 6A8353-001 or P/N 6A8688-001.
(2) For the purpose of this AD, a “3rd stage HPC rotor blade exposure” is when any 3rd stage HPC rotor blade is removed from the HPC stage 3 to 8 drum.
(3) For the purpose of this AD, an “engine shop visit” is the induction of an engine into the shop for maintenance.
(i) Alternative Methods of Compliance (AMOCs)
PDF page 2(1) The Manager, AIR-520 Continued Operational Safety Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the AIR-520 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to: AMOC@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(j) Additional Information
PDF page 2For more information about this AD, contact Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-7655; email: carol.nguyen@faa.gov.
(k) Material Incorporated by Reference
PDF page 2None.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
This correction is effective September 24, 2026. The effective date of AD 2026-17-03 remains September 24, 2026.
AddressesPage 1
AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2025-2555; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule; correction, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
For further information contactPage 1
Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-7655; email: carol.nguyen@faa.gov.
BackgroundPage 1
AD 2026-17-03, Amendment 39-23446 (91 FR 53713, August 20, 2026) (AD 2026-17-03), requires replacement of affected 3rd stage High Pressure Compressor (HPC) rotor blades with parts eligible for installation for certain IAE AG Model V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 engines.
Need for the CorrectionPage 1
As published, paragraph (g) of AD 2026-17-03 contains a typographical error. The word “blade” was inadvertently omitted from the final regulatory text. Paragraph (g) of AD 2026-17-03 should read, “... where the 3rd stage HPC rotor blade is exposed...,” which is consistent with the intent of the proposed AD (90 FR 51600, November 18, 2025).
Correction of PublicationPage 1
This document corrects an error and correctly adds the AD as an amendment to 14 CFR 39.13. Although no other part of the preamble or regulatory information has been corrected, the FAA is publishing the entire rule in the Federal Register.
The effective date of this AD remains September 24, 2026.
Since this action only corrects the typographical error, it has no adverse economic impact and imposes no additional burden on any person. Therefore, the FAA has determined that notice and public procedures are unnecessary.
Adoption of the AmendmentPage 1
Accordingly, pursuant to the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
Adoption of the amendmentPage 1
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 443
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1997 | 2 |
|---|---|
| 1998 | 3 |
| 1999 | 1 |
| 2000 | 5 |
| 2001 | 4 |
| 2002 | 4 |
| 2003 | 3 |
| 2004 | 3 |
| 2005 | 8 |
| 2006 | 20 |
| 2007 | 19 |
| 2008 | 13 |
| 2009 | 20 |
| 2010 | 3 |
| 2011 | 24 |
| 2012 | 33 |
| 2013 | 27 |
| 2014 | 63 |
| 2015 | 62 |
| 2016 | 48 |
| 2017 | 52 |
| 2018 | 24 |
| 2019 | 1 |
1 with no year recorded