Rule2025-07488
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
May 1, 2025
Effective
June 5, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by cracks being found during full-scale fatigue testing of the keel beam bottom panel between the edge profile and stringer run-out at a certain frame and stringer. This AD requires repetitive special detailed inspections (SDI) of the affected area, and corrective actions, if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 90 Issue 83 (Thursday, May 1, 2025)</title>
</head>
<body><pre>
[Federal Register Volume 90, Number 83 (Thursday, May 1, 2025)]
[Rules and Regulations]
[Pages 18627-18629]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-07488]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 90, No. 83 / Thursday, May 1, 2025 / Rules
and Regulations
[[Page 18627]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2548; Project Identifier MCAI-2024-00401-T;
Amendment 39-23026; AD 2025-09-05]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus SAS Model A318 series airplanes, Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212,
-214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted
by cracks being found during full-scale fatigue testing of the keel
beam bottom panel between the edge profile and stringer run-out at a
certain frame and stringer. This AD requires repetitive special
detailed inspections (SDI) of the affected area, and corrective
actions, if necessary, as specified in a European Union Aviation Safety
Agency (EASA) AD, which is incorporated by reference. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective June 5, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 5,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2548; 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, the mandatory continuing airworthiness
information (MCAI), 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.
Material Incorporated by Reference:
<bullet> For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999
000; email <a href="/cdn-cgi/l/email-protection#79383d0a391c180a18571c0c0b160918571c0c"><span class="__cf_email__" data-cfemail="abeaefd8ebcecad8ca85ceded9c4dbca85cede">[email protected]</span></a>. You may find this material on the EASA
website at ad.easa.europa.eu.
<bullet> You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2548.
FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 206-231-3667; email <a href="/cdn-cgi/l/email-protection#3d69545052495544136d1379524a5154535a7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="2a7e4347455e4253047a046e455d4643444d6a4c4b4b044d455c">[email protected]</span></a>.
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 Airbus SAS
Model A318 series airplanes, Model A319-111, -112, -113, -114, -115, -
131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231,
-232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. The NPRM published in the Federal
Register on December 9, 2024 (89 FR 97564). The NPRM was prompted by AD
2024-0135, dated July 10, 2024, issued by EASA, which is the Technical
Agent for the Member States of the European Union (EASA AD 2024-0135)
(also referred to as the MCAI). The MCAI states that during full-scale
fatigue testing, cracks were found on the keel beam bottom panel
between the edge profile and stringer run-out at frame 46 and stringer
37, left- and right-hand sides. Crack propagation in this area could
possibly result in reduced structural integrity of the airplane.
In the NPRM, the FAA proposed to require repetitive SDIs of the
affected area, and corrective actions, if necessary, as specified in
EASA AD 2024-0135. The FAA is issuing this AD to address the unsafe
condition on these products.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2548.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from Air Line Pilots Association,
International (ALPA) and United Airlines, who supported the NPRM
without change.
The FAA received an additional comment from American Airlines. The
following presents the comments received on the NPRM and the FAA's
response to each comment.
Request for Change to Paragraph (h)(3)
American Airlines requested that paragraph (h)(3) of the proposed
AD be updated to read: ``Where paragraph (3) of EASA AD 2024-0135 does
not allow corrective action as terminating action for the repetitive
inspection requirements `unless otherwise stated in the repair
instructions provide by Airbus,' this AD requires that any terminating
action be specified in repair instructions approved using a method
approved by the Manager, AIR-520, Continued Operational Safety Branch,
FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must include the DOA-authorized
signature.'' The commenter stated that this change would align
paragraph (h)(3) of the proposed AD with paragraph (h)(2) of the
proposed AD and still require proper approval for any terminating
repair instructions, and would also reduce unnecessary duplicate
Alternative Method of Compliance (AMOC) requests from operators if
multiple airplanes have similar repair procedures accomplished.
The FAA agrees to clarify. The FAA has determined that paragraph
(h)(3) of the proposed AD was not clearly written. The intent of that
exception is to specify that the ``repair instructions'' referenced in
paragraph (3) of EASA AD 2024-0135 are the same repair instructions
obtained as specified in paragraph (h)(2) of this AD. The FAA has
revised paragraph (h)(3) of this AD to specify that the repair
instructions are those obtained from the Manager, AIR-
[[Page 18628]]
520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's
EASA DOA.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comment 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 this product. Except for minor editorial changes,
and any other changes described previously, this AD is adopted as
proposed in the NPRM. None of the changes will increase the economic
burden on any operator.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0135 specifies procedures for repetitive SDIs for
discrepancies (cracks) of the keel beam bottom panel between the edge
profile and stringer run-out at frame 46 and stringer 37, left-hand and
right-hand sides. EASA AD 2024-0135 also specifies corrective actions
including crack repair. This material is reasonably available because
the interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 1,920 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................ $0 $1,360 $2,611,200
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2025-09-05 Airbus SAS: Amendment 39-23026; Docket No. FAA-2024-2548;
Project Identifier MCAI-2024-00401-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 5, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS airplanes, certificated in any
category, as identified in paragraphs (c)(1) through (4) of this AD
and in European Union Aviation Safety Agency (EASA) AD 2024-0135,
dated July 10, 2024 (EASA AD 2024-0135).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by cracks being found during full-scale
fatigue testing of the keel beam bottom panel between the edge
profile and stringer run-out at frame 46 and stringer 37, left- and
right-hand sides. The FAA is issuing this AD to address crack
propagation in this area. The unsafe condition, if not addressed,
could result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, EASA AD 2024-0135.
(h) Exceptions to EASA AD 2024-0135
(1) Where EASA AD 2024-0135 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0135 specifies ``if,
during any inspection as required by paragraph (1) of this AD,
discrepancies are detected, as defined in the SB, before next
flight, contact Airbus for approved repair instructions and
accomplish those instructions accordingly,'' this AD requires
replacing that text with ``if, during
[[Page 18629]]
any inspection as required by paragraph (1) of this AD, any cracking
is detected, the cracking must be repaired before further flight
using a method approved by the Manager, AIR-520, Continued
Operational Safety Branch, FAA; or EASA; or Airbus SAS's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.''
(3) Where paragraph (3) of EASA AD 2024-0135 specifies ``unless
otherwise stated in the repair instructions provide by Airbus,''
this AD requires replacing that text with ``unless otherwise stated
in the repair instructions provided by the Manager, AIR-520,
Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.''
(4) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0135.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2024-0135 specifies
to submit certain information to the manufacturer, this AD does not
include that requirement.
(j) Additional AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): 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 responsible Flight Standards Office,
as appropriate. If sending information directly to the manager of
AIR-520, Continued Operational Safety Branch, send it to the
attention of the person identified in paragraph (k) of this AD and
email to: <a href="/cdn-cgi/l/email-protection#c7868a888487a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="f7b6bab8b4b7919696d9909881">[email protected]</span></a>. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, AIR-520,
Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (j)(2) of this AD, if any material contains procedures or
tests that are identified as RC, those procedures and tests must be
done to comply with this AD; any procedures or tests that are not
identified as RC are recommended. Those procedures and tests that
are not identified as RC may be deviated from using accepted methods
in accordance with the operator's maintenance or inspection program
without obtaining approval of an AMOC, provided the procedures and
tests identified as RC can be done and the airplane can be put back
in an airworthy condition. Any substitutions or changes to
procedures or tests identified as RC require approval of an AMOC.
(k) Additional Information
For more information about this AD, contact Timothy Dowling,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206-231-3667; email
<a href="/cdn-cgi/l/email-protection#47132e2a28332f3e6917690328302b2e29200721262669202831"><span class="__cf_email__" data-cfemail="f6a29f9b99829e8fd8a6d8b299819a9f9891b6909797d8919980">[email protected]</span></a>.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2024-0135,
dated July 10, 2024.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#f9b8bd8ab99c988a98d79c8c8b968998d79c8c"><span class="__cf_email__" data-cfemail="d39297a093b6b2a0b2fdb6a6a1bca3b2fdb6a6">[email protected]</span></a>. You may find this material on
the EASA website at ad.easa.europa.eu.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call 206-231-3195.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#274155094e4954574244534e4849674946554609404851"><span class="__cf_email__" data-cfemail="bcdace92d5d2cfccd9dfc8d5d3d2fcd2ddcedd92dbd3ca">[email protected]</span></a>.
Issued on April 24, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-07488 Filed 4-30-25; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on May 1, 2025.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.