[Federal Register Volume 91, Number 7 (Monday, January 12, 2026)]
[Proposed Rules]
[Pages 1101-1104]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-00430]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-0009; Project Identifier MCAI-2025-00436-T]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes; Model A320 series airplanes; and Model A321-
211, -212, -213, -231,-232, -251N, -251NX, -252N, -252NX, -253N, -
253NX, -271N, -271NX, -272N, and -272NX airplanes. This proposed AD was
prompted by a review of the cold working process on the assembly line
that detected a deviation to the manufacturing process. This proposed
AD would require repetitive inspections for the nominal design
condition of the fastener holes in the pressure deck membrane to center
wing box attachment and, as applicable, an inspection for cracking at
the affected area and corrective actions. The FAA is proposing this AD
to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by February
26, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5
[[Page 1102]]
p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2026-0009; 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 NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For European Union Aviation Safety Agency (EASA) material
identified in this proposed 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. It is also available at regulations.gov under Docket
No. FAA-2026-0009.
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.
FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 404-
545-5064; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2026-0009;
Project Identifier MCAI-2025-00436-T'' at the beginning of your
comments. The most helpful comments reference a specific portion of the
proposal, explain the reason for any recommended change, and include
supporting data. The FAA will consider all comments received by the
closing date and may amend this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Bill
Ashforth, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 404-545-5064; email: [email protected].
Any commentary that the FAA receives which is not specifically
designated as CBI will be placed in the public docket for this
rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2025-0066, dated March 28, 2025
(EASA AD 2025-0066) (also referred to as the MCAI), to correct an
unsafe condition for certain Airbus SAS Model A319-111, -112, -113, -
114, -115, -131, -132, -133; Model A320-211, -212, -214, -215, -216, -
231, -232, -233, -251N, -252N, -253N, -271N, -272N, -273N; and Model
A321-211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N,
-253NX, -271N, -271NX, -272N, and -272NX airplanes. Model A320-215
airplanes are not certificated by the FAA and are not included on the
U.S. type certificate data sheet; this proposed AD therefore does not
include those airplanes in the applicability. 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 pressure deck membrane to
center wing box attachment. This condition, if not addressed, could
lead to crack initiation and propagation, resulting in reduced
structural integrity of the airplane.
The FAA is proposing 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-2026-0009.
Material Incorporated by Reference Under 1 CFR Part 51
This proposed AD would require repetitive inspections for the
nominal condition of the fastener holes in the pressure deck membrane
and, as applicable, an inspection for cracking at the affected area and
corrective actions.
EASA AD 2025-0066 specifies procedures for repetitive special
detailed inspections (SDI) for any discrepancy of the fastener holes
(i.e., fastener holes that are not in nominal design condition) in the
pressure deck membrane to the center wing box attachment, under
titanium angle connection and corner brackets at frame 36, at stringer
30, both left hand and right hand sides. EASA AD also specifies
procedures for a rototest inspection for any discrepancy (i.e.,
cracking) at the affected area and corrective actions, as applicable.
Corrective actions include contacting Airbus for approved repair
instructions and accomplishing those instructions. EASA AD 2025-0066
also specifies procedures for repairing fastener holes, which would
terminate the repetitive inspections.
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.
FAA's Determination
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 is issuing this NPRM
after determining that the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2025-0066 described previously, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2025-0066 by
[[Page 1103]]
reference in the FAA final rule. This proposed AD would, therefore,
require compliance with EASA AD 2025-0066 in its entirety through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this proposed AD. Using common terms that are
the same as the heading of a particular section in EASA AD 2025-0066
does not mean that operators need comply only with that section. For
example, where the AD requirement refers to ``all required actions and
compliance times,'' compliance with this AD requirement is not limited
to the section titled ``Required Action(s) and Compliance Time(s)'' in
EASA AD 2025-0066. Material required by EASA AD 2025-0066 for
compliance will be available at regulations.gov under Docket No. FAA-
2026-0009 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 477 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 76 work-hours x $85 per Up to $183............. Up to $6,643........... Up to $3,168,711.
hour = $6,460.
----------------------------------------------------------------------------------------------------------------
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 *
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
1 work-hour x $85 per hour = $85 $0 $85
(rototest inspection)..........
------------------------------------------------------------------------
* The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this proposed AD.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this proposed AD may be covered under warranty, thereby reducing the
cost impact on affected operators.
The FAA has received no definitive data on which to base the cost
estimates for the optional actions specified in this proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus SAS: Docket No. FAA-2026-0009; Project Identifier MCAI-2025-
00436-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by February 26, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model airplanes specified in
paragraphs (c)(1) through (3) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2025-0066, dated March 28, 2025 (EASA AD 2025-0066).
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(2) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -
252N, -253N, -271N, -272N, and -273N airplanes.
(3) Model A321-211, -212, -213, -231, -232, -251N, -251NX, -
252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX
airplanes.
(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
[[Page 1104]]
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 pressure deck membrane to center wing box
attachment. This 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 2025-0066.
(h) Exceptions to EASA AD 2025-0066
(1) Where paragraph (2) of EASA AD 2025-0066 specifies ``any
discrepancy, 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 2025-0066 specifies ``no
discrepancy'', 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 2025-0066 specifies if ``any
discrepancy 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
cracking is detected, repair the cracking 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''.
(4) Where paragraph (6) of EASA AD 2025-0066 specifies ``no
discrepancy'', this AD requires replacing that text with ``no
cracking''.
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0066.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2025-0066 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 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), (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 Bill Ashforth,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 404-545-5064; 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 2025-0066,
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 January 8, 2026.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2026-00430 Filed 1-9-26; 8:45 am]
BILLING CODE 4910-13-P