[Federal Register Volume 90, Number 183 (Wednesday, September 24, 2025)]
[Rules and Regulations]
[Pages 45907-45909]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-18469]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0926; Project Identifier AD-2025-00200-E;
Amendment 39-23153; AD 2025-19-13]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
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. This AD was prompted by a manufacturer
investigation that revealed a quality escape following angled
ultrasonic inspections (AUSIs) performed on certain high-pressure
turbine (HPT) 1st-stage hubs and HPT 2nd-stage hubs. This AD requires
removal and replacement of certain HPT 1st-stage hubs and HPT 2nd-stage
hubs. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective October 29, 2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0926; 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, 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 CONTACT: Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7655; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to 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. The NPRM was published in the
Federal Register on June 13, 2025 (90 FR 25002). The NPRM was prompted
by a report of a quality escape on HPT 1st-stage hubs and HPT 2nd-stage
hubs that had AUSIs performed at production. A manufacturer
investigation of these AUSIs revealed that the quality escape resulted
from the misinterpretation of the rejection criteria for the AUSIs
performed on affected HPT 1st-stage hubs and HPT 2nd-stage hubs. In the
NPRM, the FAA proposed to require removal and replacement of certain
HPT 1st-stage hubs and HPT 2nd-stage hubs. The FAA is issuing this AD
to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from two commenters. The commenters were
the Air Line Pilots Association,
[[Page 45908]]
International (ALPA) and an anonymous commenter. ALPA supported the
NPRM without change. The following presents the comments received on
the NPRM and the FAA's response to each comment.
Request To Limit Engine Applicability
An anonymous commenter requested that the FAA limit the
applicability of the proposed AD to apply only to engine serial numbers
(S/N) that are known to have incorporated the eight identified affected
hubs. The commenter stated that limiting the applicability would make
future compliance checks more efficient and would also eliminate the
need for repetitive verification across the fleet. The commenter also
stated that the proposed AD would apply indefinitely to all engines
within the listed models, which creates an unnecessary and continuing
compliance burden for maintenance providers and operators in that each
future engine shop visit will require verification of S/N eligibility
even though removal will be required within a finite period.
The FAA disagrees with the request. This final rule includes an
installation prohibition that currently applies to all models listed in
the Applicability paragraph of this AD. If the Applicability paragraph
of this AD is revised to apply only to the engines that currently have
the affected hubs installed, the installation prohibition will only
apply to engines that already have affected hubs installed rather than
all engines. The FAA did not change this AD as a result of this
comment.
Request To Add Terminating Action
An anonymous commenter requested that the FAA include a terminating
action in the proposed AD stating that once all affected hubs are
removed, the AD would no longer apply to any engines.
The FAA disagrees with the request because complying with the
required actions in paragraph (g) of this AD removes the unsafe
condition and thus provides a terminating action for that portion of
the AD. In addition, as stated earlier, this AD includes an
installation prohibition, so removing all affected hubs from service
does not make the AD no longer applicable. The FAA did not change this
AD as a result of this comment.
Request To Supersede or Cancel the Proposed AD
An anonymous commenter requested that the FAA consider superseding
or cancelling the proposed AD once all suspect parts have been removed
and no longer create an airworthiness concern. The commenter stated
that there is an established precedent for terminating or superseding
ADs once unsafe conditions have been fully mitigated. The FAA infers
that by cancelling an AD, the commenter is referring to rescinding an
AD.
The FAA disagrees with this request. The FAA would not supersede or
rescind this AD once all suspect parts have been removed because an
unsafe condition would still exist, as this AD includes an installation
prohibition and removing all affected hubs from service does not make
the AD no longer applicable. The FAA did not change this AD as a result
of this comment.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM. None of the changes will
increase the economic burden on any operator.
Costs of Compliance
The FAA estimates that this AD affects two engines of U.S.
registry. The FAA estimates that two engines need replacement of the
HPT 1st-stage hub and no engines need replacement of the HPT 2nd-stage
hub.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replace HPT 1st-stage hub................ 100 work-hours x $85 per $460,000 $468,500 $937,000
hour = $8,500.
Replace HPT 2nd-stage hub................ 100 work-hours x $85 per 360,000 368,500 0
hour = $8,500.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 45909]]
Sec. 39.13 [Amended]
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2025-19-13 International Aero Engines AG: Amendment 39-23153; Docket
No. FAA-2025-0926; Project Identifier AD-2025-00200-E.
(a) Effective Date
This airworthiness directive (AD) is effective October 29, 2025.
(b) Affected ADs
None.
(c) Applicability
This 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.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer investigation that
revealed a quality escape following angled ultrasonic inspections
performed on certain high-pressure turbine (HPT) 1st-stage hubs and
HPT 2nd-stage hubs. The FAA is issuing this AD to prevent failure of
the HPT 1st-stage hub and HPT 2nd-stage hub. The unsafe condition,
if not addressed, could result in an uncontained hub failure,
release of high-energy debris, damage to the engine, damage to the
airplane, and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
For engines with an installed part, part number (P/N) and serial
number (S/N) identified in table 1 to paragraph (g) of this AD, at
the next engine shop visit after the effective date of this AD
before exceeding the applicable removal cycle limit listed in table
1 to paragraph (g) of this AD or within 100 flight cycles from the
effective date of this AD, whichever occurs later, remove the
affected part from service and replace with a part eligible for
installation.
Table 1 to Paragraph (g)--Affected HPT 1st Stage and HPT 2nd Stage Hubs
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Removal cycle limit
Part P/N S/N (cycles since new)
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HPT 1st-stage hub........................................ 2A5001 PKLBSK9287 100
HPT 1st-stage hub........................................ 2A5001 PKLBSS9200 4,800
HPT 1st-stage hub........................................ 2A5001 PKLBST5011 5,500
HPT 1st-stage hub........................................ 2A5001 PKLBST7489 6,200
HPT 2nd-stage hub........................................ 2A4802 PKLBST5005 4,000
HPT 2nd-stage hub........................................ 2A4802 PKLBSS9840 3,900
HPT 2nd-stage hub........................................ 2A4802 PKLBSS0301 5,000
HPT 2nd-stage hub........................................ 2A4802 PKLBSR2100 6,000
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(h) Installation Prohibition
After the effective date of this AD, do not install an HPT 1st-
stage hub or HPT 2nd-stage hub that has a P/N and S/N listed in
table 1 to paragraph (g) of this AD in any engine.
(i) Definitions
For the purpose of this AD:
(1) A ``part eligible for installation'' is an HPT 1st-stage hub
or HPT 2nd-stage hub having a P/N and S/N that is not listed in
table 1 to paragraph (g) of this AD.
(2) An ``engine shop visit'' is the induction of an engine into
the shop for maintenance involving the separation of any major
mating engine flanges, H-P, except for the following situations,
which do not constitute an engine shop visit:
(i) Separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Engine removal for the purpose of performing field
maintenance activities at a maintenance facility in lieu of
performing them on-wing.
(j) Alternative Methods of Compliance (AMOCs)
(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 (k) of this AD and email to: [email protected].
(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.
(k) Additional Information
For 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: [email protected].
(l) Material Incorporated by Reference
None.
Issued on September 19, 2025.
Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2025-18469 Filed 9-23-25; 8:45 am]
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