Rule2025-22348
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
December 9, 2025
Effective
January 13, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2022-15- 05, which applied 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. AD 2022-15-05 required repetitive high frequency eddy current (HFEC) inspections for cracks on the web horizontal flange and inner cap, and applicable corrective actions. Since the FAA issued AD 2022-15-05, additional cracks have been found at the door stop fitting number 1 holes at frame (FR) 68, after disassembly of the door stop fitting as part of the inspections required by AD 2022-15-05. This AD continues to require the actions in AD 2022-15-05, but with reduced compliances times for some inspections, and requires an additional inspection at door stop fitting number 1. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 234 (Tuesday, December 9, 2025)</title>
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[Federal Register Volume 90, Number 234 (Tuesday, December 9, 2025)]
[Rules and Regulations]
[Pages 56969-56971]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-22348]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0758; Project Identifier MCAI-2024-00651-T;
Amendment 39-23192; AD 2025-23-09]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-15-
05, which applied 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.
AD 2022-15-05 required repetitive high frequency eddy current (HFEC)
inspections for cracks on the web horizontal flange and inner cap, and
applicable corrective actions. Since the FAA issued AD 2022-15-05,
additional cracks have been found at the door stop fitting number 1
holes at frame (FR) 68, after disassembly of the door stop fitting as
part of the inspections required by AD 2022-15-05. This AD continues to
require the actions in AD 2022-15-05, but with reduced compliances
times for some inspections, and requires an additional inspection at
door stop fitting number 1. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 13, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 13,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0758; 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 European Union Aviation Safety Agency (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#1150556251747062703f7464637e61703f7464"><span class="__cf_email__" data-cfemail="38797c4b785d594b59165d4d4a574859165d4d">[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-2025-0758.
FOR FURTHER INFORMATION CONTACT: Tim Dowling, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3667;
email: <a href="/cdn-cgi/l/email-protection#74001d191b001c0d5a045a101b03181d1a13341215155a131b02"><span class="__cf_email__" data-cfemail="c0b4a9adafb4a8b9eeb0eea4afb7aca9aea780a6a1a1eea7afb6">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2022-15-05, Amendment 39-22125 (87 FR
45013, July 27, 2022) (AD 2022-15-05). AD 2022-15-05 applied to all
Airbus SAS Model A318-111, A318-112, A318-121, A318-122, A319-111,
A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133,
A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, A320-233,
A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231,
and A321-232 airplanes, except those airplanes with certain
modifications installed that convert the airplane to a corporate jet.
AD 2022-15-05 required repetitive HFEC inspections for cracks on the
web horizontal flange and inner cap and applicable corrective actions,
in accordance with EASA AD 2022-0030, dated February 25, 2022 (EASA AD
2022-0030) which specifies using the original or later-approved
revisions of Airbus Service Bulletin A320-53-1491. The FAA issued AD
2022-15-05 to address a report that cracks were found on the web
horizontal flange and inner cap on FR 68, left-hand (LH) and right-hand
(RH) sides, at stringer (STGR) 22, which could result in reduced
structural integrity of the fuselage.
The NPRM was published in the Federal Register on May 16, 2025 (90
FR 20952). The NPRM was prompted by AD 2024-0210, dated October 29,
2024, issued by EASA, which is the Technical Agent for the Member
States of the European Union (EASA AD 2024-0210) (also referred to as
the MCAI). The MCAI states that after EASA AD 2022-0030 was issued,
cracks have been found at the door stop fitting number 1 holes at FR
68, after the door stop fitting disassembly as part of the inspections
in Airbus Service Bulletin A320-53-1491 Revision 1. Therefore, Airbus
issued revision 2 of its service bulletin to include an additional
inspection of the FR 68 door stop fitting number 1 holes with a larger
inspection area, and an additional HFEC inspection on FR68 around the
door stop fitting number 1 nuts. Some compliance times have been
reduced and the procedures in the service bulletin have been updated.
In the NPRM, the FAA proposed to continue to require the actions in
AD 2022-15-05, but with reduced compliances times for some inspections,
and proposed to require an additional inspection at door stop fitting
number 1, as specified in EASA AD 2024-0210. The FAA is issuing this AD
to address cracks on the door stop 1, web horizontal flange and inner
cap on FR 68, LH and RH sides, at STGR 22, which could result in
reduced structural integrity of the fuselage.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0758.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from Delta Air Lines (Delta). The
following presents the comment and the FAA's response.
Request for an Exception To Address Outdated Material Number Reference
Delta requested that the FAA modify paragraph (h) of the proposed
AD to allow use of a compound having consumable material list (CML)
code 12ADB1 instead of the compound having CML code 12ABC1 that is
specified in the service information referenced by EASA AD 2024-0210.
Delta explained that CML code 12ABC1 references a Type I corrosion
inhibiting compound (CIC) which is a water dispersing compound used in
the old temporary protection system (TPS) configuration which was
phased out in
[[Page 56970]]
the early 2000s. Delta added that CML code 12ABC1 was replaced by CML
code 12ADB1, which is a Type III CIC having both water displacing and
corrosion protection properties, and is prescribed by Delta's corrosion
prevention control program (CPCP) and is also identified in section 51-
23-12 of the A320 Structural Repair Manual section as the replacement
for CML code 12ABC1. Delta stated that it requested and received
confirmation from Airbus to use CML code 12ADB1 in lieu of CML code
12ABC1 and quoted Airbus as saying ``it is acceptable to locally apply
CML code 12ADB1 in lieu of 12ABC1 for the embodiment of SB 53-1491 for
the re-protection of the inspection areas on Web Horizontal Flange
Radii. . . .''
The FAA agrees to add an exception to paragraph (h) of this AD to
allow the use of CML code 12ADB1 in lieu of CML code 12ABC1.
Conclusion
These products have been approved by the civil aviation authority
of another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, that authority has notified the FAA of the unsafe condition
described in the MCAI referenced above. 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, 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
The FAA reviewed EASA AD 2024-0210 which specifies procedures for
repetitive inspections of certain areas of the fuselage and taking
corrective actions if there are cracks or discrepancies by following
the manufacturer's service information. EASA AD 2024-0210 also
specifies reporting all inspection findings to Airbus. Specifically,
the inspections are high frequency eddy current inspections of the
frame horizontal flange radii, inner cap fillet radius, the door stop 1
fasteners, and the frame inner cap corner at FR 68. The instructions
for the inspections depend on whether a repair part has been installed.
On-condition corrective actions include additional inspections for
cracking, inspections to determine if a certain modification or repair
was done, and repair of cracking at the web horizontal flange. 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 1,924 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection for repair part....... 1 work-hour x $85 $0 $85................. $163,540.
per hour = $85.
High frequency eddy current 27 work-hours x $85 0 $2,295 per $4,415,580 per
inspection. per hour = $2,295 inspection cycle. inspection cycle.
per inspection
cycle.
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The FAA estimates the following costs to do any on-condition
inspections that would be required based on the results of the high
frequency eddy current inspections. The FAA has no way of determining
the number of airplanes that might need these on-condition inspections:
Estimated Costs of On-Condition Actions
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Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
On-condition inspections................ Up to 30 work-hours x $85 $0 Up to $2,550.
per hour = $2,550.
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The extent of cracking and other conditions found during the
inspections could vary significantly from airplane to airplane. The FAA
has no way of determining which conditions may be found on each
airplane, the cost to correct or repair each airplane, or the number of
airplanes that may require repair.
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.
[[Page 56971]]
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:
0
a. Removing Airworthiness Directive (AD) 2022-15-05, Amendment 39-22125
(87 FR 45013, July 27, 2022); and
0
b. Adding the following new AD:
2025-23-09 Airbus SAS: Amendment 39-23192; Docket No. FAA-2025-0758;
Project Identifier MCAI-2024-00651-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 13, 2026.
(b) Affected ADs
This AD replaces AD 2022-15-05, Amendment 39-22125 (87 FR 45013,
July 27, 2022) (AD 2022-15-05).
(c) Applicability
This AD applies to Airbus SAS Model airplanes identified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2024-0210, dated October 29, 2024 (EASA AD 2024-0210).
(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 a report that cracks were found on the
web horizontal flange and inner cap on frame (FR) 68, left-hand (LH)
and right-hand (RH) sides, at stringer (STGR) 22, and at the door
stop fitting number 1 holes at FR 68. The FAA is issuing this AD to
address the cracks on the door stop 1, web horizontal flange and
inner cap on FR 68, LH and RH sides, at STGR 22. The unsafe
condition, if not addressed, could result in reduced structural
integrity of the fuselage.
(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 2024-0210.
(h) Exceptions to EASA AD 2024-0210
(1) Where EASA AD 2024-0210 refers to ``22 November 2021 [the
effective date of EASA AD 2021-0242]'', this AD requires using
August 31, 2022 (the effective date of AD 2022-15-05).
(2) Where EASA AD 2024-0210 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0210 refers to ``the
SDI'', this AD requires replacing that text with ``the applicable
inspections''.
(4) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0210.
(5) This AD does not adopt paragraphs (2) and (3) of EASA AD
2024-0210.
(6) Where paragraph (4) of EASA AD 2024-0210 states
``discrepancies'', this AD requires replacing that word with
``conditions''.
(7) Where paragraph (4) of EASA AD 2024-0210 states ``within the
compliance time specified therein'', this AD requires replacing that
text with ``before further flight''.
(8) Where paragraph (6) of EASA AD 2024-0210 specifies ``the
instructions provided by Airbus'', for this AD, those instructions
must be approved by the FAA, EASA, or Airbus SAS's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(9) Where the material referenced in EASA 2024-0210 states to
use consumable material list (CML) code 12ABC1, this AD also allows
using CML code 12ADB1 instead.
(i) No Reporting Requirement
Although paragraph (7) of and the material referenced in EASA AD
2024-0210 specify 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
the 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#01404c4e42416760602f666e77"><span class="__cf_email__" data-cfemail="d6979b999596b0b7b7f8b1b9a0">[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, 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
paragraphs (h), (i), and (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 Tim Dowling,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3667; email: <a href="/cdn-cgi/l/email-protection#dda9b4b0b2a9b5a4f3adf3b9b2aab1b4b3ba9dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="abdfc2c6c4dfc3d285db85cfc4dcc7c2c5ccebcdcaca85ccc4dd">[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 2024-0210,
dated October 29, 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#8acbcef9caefebf9eba4effff8e5faeba4efff"><span class="__cf_email__" data-cfemail="5011142310353123317e3525223f20317e3525">[email protected]</span></a>; website easa.europa.eu. 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#2a4c58044344595a4f495e4345446a444b584b044d455c"><span class="__cf_email__" data-cfemail="83e5f1adeaedf0f3e6e0f7eaecedc3ede2f1e2ade4ecf5">[email protected]</span></a>.
Issued on November 12, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-22348 Filed 12-8-25; 8:45 am]
BILLING CODE 4910-13-P
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