Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 91, Number 123 (Monday, June 29, 2026)]
[Rules and Regulations]
[Pages 39002-39005]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-13062]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-3485; Project Identifier MCAI-2025-00437-T; 
Amendment 39-23381; AD 2026-12-11]
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 adopting a new airworthiness directive (AD) for 
certain Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX 
airplanes. This AD was prompted by a review of the cold working process 
on the assembly line that detected a deviation to the manufacturing 
process. This AD requires repetitive inspections for the nominal design 
condition of the fastener holes in certain center fuselage frame foot 
joint connections and, as applicable, an inspection for cracking at the 
frame foot joint connections and corrective actions. The FAA is issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective August 3, 2026. The Director of the Federal 
Register approved the incorporation by reference of a certain 
publication listed in this AD as of August 3, 2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-3485; 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

[[Page 39003]]

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-
2026-3485.

FOR FURTHER INFORMATION CONTACT: Nicholas Benson, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3647; 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 Airbus SAS 
Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. The 
NPRM was published in the Federal Register on April 15, 2026 (91 FR 
20081). The NPRM was prompted by EASA AD 2025-0067, dated March 28, 
2025 (EASA AD 2025-0067) (also referred to as the MCAI), issued by 
EASA, which is the Technical Agent for the Member States of the 
European Union. The MCAI states that, during a review of the cold 
working process on the assembly line, a deviation to the manufacturing 
process was detected, which could adversely affect the fatigue life of 
the affected area (i.e., center fuselage frame (FR) foot joint 
connections at FR37 to FR41 inclusive, between stringers (STR) STR21 to 
STR23, on both left-hand and right-hand sides). This condition, if not 
detected and corrected, could lead to crack initiation and propagation, 
possibly resulting in reduced structural integrity of the airplane.
    In the NPRM, the FAA proposed to require repetitive inspections for 
the nominal design condition of the fastener holes in certain center 
fuselage frame foot joint connections and, as applicable, an inspection 
for cracking at the frame foot joint connections and corrective 
actions, as specified in EASA AD 2025-0067. The FAA is issuing this AD 
to address the unsafe condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2026-3485.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from an anonymous commenter who 
supported the NPRM without change.

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, 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 2025-0067 specifies procedures for repetitive inspections 
for any discrepancy of the fastener holes, which consists of doing a 
check to determine if the fastener holes in the affected area are not 
in nominal design condition. Nominal design condition is that fasteners 
installed have a nominal diameter as specified in the material 
referenced in EASA AD 2025-0067. EASA AD 2025-0067 also specifies 
procedures for a rototest inspection of the fastener holes for any 
discrepancy (i.e., cracking) at each affected area and corrective 
actions, as applicable. Corrective actions include contacting Airbus 
for approved repair instructions and accomplishing those instructions. 
EASA AD 2025-0067 also specifies procedures for repairing fastener 
holes, which would terminate the repetitive inspections.
    EASA AD 2025-0067 also specifies accomplishment of a high frequency 
eddy current (HFEC) inspection around the fastener holes at an affected 
area is an acceptable method of compliance for the rototest inspection 
for that affected area.
    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 22 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 per      Cost on U.S.
                             Labor cost                               Parts cost      product       operators
----------------------------------------------------------------------------------------------------------------
23 work-hours x $85 per hour = $1,955..............................           $0        $1,955          $43,010
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                Estimated Costs of On-Condition Actions *
------------------------------------------------------------------------
                                                             Cost per
                Labor cost                  Parts cost       product
------------------------------------------------------------------------
60 work-hours x $85 per hour = $5,100             $884           $5,984
 (rototest inspection)...................
------------------------------------------------------------------------
* The FAA has received no definitive data on which to base the cost
  estimates for the on-condition repairs specified in this AD.


[[Page 39004]]


                                      Estimated Costs for Optional Actions
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Terminating action............................  15 work-hours x $85 per hour =        Negligible          $1,275
                                                 $1,275.
----------------------------------------------------------------------------------------------------------------

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:

2026-12-11 Airbus SAS: Amendment 39-23381; Docket No. FAA-2026-3485; 
Project Identifier MCAI-2025-00437-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 3, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A321-251NX, -252NX, -253NX, 
-271NX, and -272NX airplanes, certificated in any category, as 
identified in European Union Aviation Safety Agency (EASA) AD 2025-
0067, dated March 28, 2025 (EASA AD 2025-0067).

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a review of the cold working process on 
the assembly line that detected a deviation to the manufacturing 
process. The FAA is issuing this AD to address a deviation to the 
manufacturing process, which could adversely affect the fatigue life 
of the center fuselage frame (FR) foot joint connections at FR37 to 
FR41 inclusive, between stringer (STR) STR21 to STR23. The unsafe 
condition, if not addressed, could lead to crack initiation and 
propagation, resulting 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 2025-0067.

(h) Exceptions to EASA AD 2025-0067

    (1) Where paragraph (2) of EASA AD 2025-0067 specifies ``any 
discrepancy is detected, as defined in the SB'', this AD requires 
replacing that text with ``any fastener hole is not in nominal 
design condition, as defined in the SB''.
    (2) Where paragraph (3) of EASA AD 2025-0067 specifies ``no 
discrepancy is detected'', this AD requires replacing that text with 
``fastener holes are in nominal design condition, as defined in the 
SB''.
    (3) Where paragraph (4) of EASA AD 2025-0067 specifies a ``High 
Frequency Eddy Current (HFEC) inspection around the fastener holes 
at an affected area is an acceptable method'', this AD requires 
replacing that text with ``High Frequency Eddy Current (HFEC) 
inspection around the fastener holes at an affected area, in 
accordance with the instructions of the SB, is an acceptable 
method''.
    (4) Where paragraph (5) of EASA AD 2025-0067 specifies ``any 
crack is detected, as defined in the SB, before next flight, contact 
Airbus for approved repair instructions and, within the compliance 
time specified therein, accomplish those instructions 
accordingly.'', this AD requires replacing that text with ``any 
crack is detected, the crack 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.''
    (5) Where paragraph (7) of EASA AD 2025-0067 specifies ``no 
discrepancy'', this AD requires replacing that text with ``no 
cracking''.
    (6) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0067.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0067 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 
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

[[Page 39005]]

be accomplished using a method approved by the Manager, AIR-520, 
Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's 
EASA 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)(3), (h)(4), 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 Nicholas Benson, 
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 
98198; phone: 206-231-3647; 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 2025-0067, 
dated March 28, 2025.
    (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 June 10, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division, 
Aircraft Certification Service.
[FR Doc. 2026-13062 Filed 6-26-26; 8:45 am]
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