[Federal Register Volume 90, Number 176 (Monday, September 15, 2025)]
[Proposed Rules]
[Pages 44350-44353]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-17731]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-2544; Project Identifier MCAI-2025-00531-T]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus SAS Model A318-111, -112, and -122; A319-111, -112,
-113, -114, -115, -131, -132, and -133; A320-211, -212, -214, -216, -
232, -233, -251N, -252N, -253N, -271N, -272N, and -273N; and A321-211,
-212, -213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -
252NX, -253NX, -271NX, -272NX airplanes. This proposed AD was prompted
by the detection of a deviation from the manufacturing process during a
review of the cold working process in the assembly line. This proposed
AD would require repetitive special detailed inspections (SDIs) and
rototest or high frequency eddy current (HFEC) and rototest inspections
of the affected fasteners and fastener holes, and applicable on-
condition 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 October 30,
2025.
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 44351]]
p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-2544; 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-2025-2544.
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: Dan Rodina, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3225;
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-2025-2544;
Project Identifier MCAI-2025-00531-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 Dan
Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 206-231-3225; 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 2025-0078, dated April 9, 2025 (EASA
AD 2025-0078) (also referred to as the MCAI), to correct an unsafe
condition for certain Airbus SAS Model A318-111, -112, and -122; A319-
111, -112, -113, -114, -115, -131, -132, and -133; A320-211, -212, -
214, -215, -216, -232, -233, -251N, -252N, -253N, -271N, -272N, and -
273N; and A321-211, -212, -213, -231, -232, -251N, -252N, -253N, -271N,
-272N, -251NX, -252NX, -253NX, -271NX, -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 a
deviation from the manufacturing process was detected during a review
of the cold working process in the assembly line, which could adversely
affect the fatigue life of the affected areas (Forward pressure
bulkhead connection to frame (FR) 35 for Airbus A319 and A320 airplanes
and FR35.8 for Airbus A321 airplanes, between stringer (STR) 28 and STR
31, both left-hand (LH) and right-hand (RH) sides; and fuselage skin at
FR35 for Airbus A318, A319 and A320 airplanes and FR35.8 for Airbus
A321 airplanes, at STR30, both LH and RH sides). This condition, if not
detected and corrected, could lead to crack initiation and propagation,
possibly 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-2025-2544.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2025-0078 specifies procedures for repetitive SDIs around
the fastener holes at FR35, stringer (STGR) 28 to STGR 31 to check if
the fasteners and fastener holes are in nominal design condition;
repetitive rototest or HFEC and rototest inspections around the
fasteners and fastener holes for cracks, and applicable corrective
actions. Corrective actions include 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.
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 2025-0078 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 2025-0078 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2025-0078 in its entirety through that incorporation, except
for any differences identified as exceptions in the
[[Page 44352]]
regulatory text of this proposed AD. Using common terms that are the
same as the heading of a particular section in EASA AD 2025-0078 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 2025-0078. Material required by EASA AD 2025-0078 for
compliance will be available at regulations.gov under Docket No. FAA-
2025-2544 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,946 airplanes of U.S. registry. The FAA estimates the
following costs to comply with this proposed AD:
Estimated Costs for Required Actions
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Labor cost Parts cost Cost per product Cost on U.S. operators
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Up to 63 work-hours x $85 per $0 Up to $5,355................ Up to $10,420,830.
hour = $5,355.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs 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-2025-2544; Project Identifier MCAI-2025-
00531-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 30, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS airplanes specified in paragraphs
(c)(1) through (4), certificated in any category, as identified in
European Union Aviation Safety Agency (EASA) AD 2025-0078, dated
April 9, 2025 (EASA AD 2025-0078).
(1) Model A318-111, -112, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -232, -233, -251N, -252N,
-253N, -271N, -272N, and -273N airplanes.
(4) Model A321-211, -212, -213, -231, -232, -251N, 252N, -253N,
-271N, -272N, -251NX, 252NX, -253NX, -271NX, and 272NX airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by the detection of a deviation from the
manufacturing process during a review of the cold working process in
the assembly line. The FAA is issuing this AD to address reduced
fatigue life of the affected areas of the forward pressure bulkhead
connection to, and fuselage skin at, certain frames. 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 paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2025-0078.
(h) Exceptions to EASA AD 2025-0078
(1) Where EASA AD 2025-0078 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraphs (2) and (3) of EASA AD 2025-0078 specify
``discrepancy'', this AD requires replacing that text with
``fastener or fastener hole that is not in a nominal design
condition''.
(3) Where paragraph (6) of EASA AD 2025-0078 specifies ``if,
during inspection as required by paragraph (3), (4), or (5) of this
AD, any crack is found, 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 ``if,
during any inspection required by paragraph (3), (4), or (5) of this
AD, any cracking is found, 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.''
(4) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0078.
(i) No Reporting Requirement
Although the material referenced EASA AD 2025-0078 specifies to
submit certain information to the manufacturer, this AD does not
include that requirement.
[[Page 44353]]
(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 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 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 (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 Dan Rodina, Aviation
Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198;
phone: 206-231-3225; 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 2025-0078,
dated April 9, 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 September 10, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-17731 Filed 9-12-25; 8:45 am]
BILLING CODE 4910-13-P