Airworthiness Directives; Airbus SAS Airplanes

[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 [www.gpo.gov]
[FR Doc No: 2025-22348]


=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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 regulations.gov 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 [email protected]. 
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 regulations.gov 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: [email protected].

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 regulations.gov 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
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                 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.
----------------------------------------------------------------------------------------------------------------

    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: 
[email protected]. 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: [email protected].

(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 [email protected]; 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 www.archives.gov/federal-register/cfr/ibr-locations, or email [email protected].

    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

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T00:52:40.738056+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

5e039a076bc1c125cd350bee38e48efc2f05a6cc68cd10384dc06d47af11a5c3

Text SHA-256

c7c2f12ac8e1c5fdff6aec7978fd9ab697d02981a38e72b5995cd5896a2d6724