Proposed Rule2025-03159
Airworthiness Directives; Airbus SAS Airplanes
Primary source
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Published
February 27, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2017-14-14, which applies to all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-14-14 requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. Since the FAA issued AD 2017-14-14, further analysis determined that the compliance times for the inspections must also be based on flight hours. This proposed AD would continue to require the actions in AD 2017-14-14, and would require revised compliance times and add a provision for optional modifications, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 38 (Thursday, February 27, 2025)</title>
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[Federal Register Volume 90, Number 38 (Thursday, February 27, 2025)]
[Proposed Rules]
[Pages 10801-10804]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-03159]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0213; Project Identifier MCAI-2024-00385-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 supersede Airworthiness Directive (AD)
2017-14-14, which applies to all Airbus SAS Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes. AD 2017-14-14 requires
repetitive inspections for cracking in the cabin floor beam junction at
certain fuselage frame locations, and repair if necessary. Since the
FAA issued AD 2017-14-14, further analysis determined that the
compliance times for the inspections must also be based on flight
hours. This proposed AD would continue to require the actions in AD
2017-14-14, and would require revised compliance times and add a
provision for optional modifications, as specified in a European Union
Aviation Safety Agency (EASA) AD, which is proposed for incorporation
by reference (IBR). 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 April 14,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0213; 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:
<bullet> For EASA material identified in this proposed AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#bbfaffc8fbdedac8da95decec9d4cbda95dece"><span class="__cf_email__" data-cfemail="1554516655707466743b7060677a65743b7060">[email protected]</span></a>; website easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu. It is also
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2025-0213.
<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.
FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
206-231-3667; email <a href="/cdn-cgi/l/email-protection#186c7175776c70613668367c776f7471767f587e7979367f776e"><span class="__cf_email__" data-cfemail="0a7e6367657e6273247a246e657d6663646d4a6c6b6b246d657c">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-0213;
Project Identifier MCAI-2024-00385-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
<a href="http://regulations.gov">regulations.gov</a>, 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
Timothy Dowling, Aviation Safety Engineer, FAA, 2200 South 216th St.,
Des Moines, WA 98198; telephone 206-231-3667; email
<a href="/cdn-cgi/l/email-protection#3a4e5357554e5243144a145e554d5653545d7a5c5b5b145d554c"><span class="__cf_email__" data-cfemail="94e0fdf9fbe0fcedbae4baf0fbe3f8fdfaf3d4f2f5f5baf3fbe2">[email protected]</span></a>. Any commentary that the FAA receives which
is not specifically designated as CBI will be placed in the public
docket for this rulemaking.
[[Page 10802]]
Background
The FAA issued AD 2017-14-14, Amendment 39-18958 (82 FR 33002, July
19, 2017) (AD 2017-14-14), for all Airbus SAS Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. AD 2017-14-14 was
prompted by an MCAI originated by EASA, which is the Technical Agent
for the Member States of the European Union. EASA issued AD 2016-0105,
dated June 6, 2016, to correct an unsafe condition.
AD 2017-14-14 requires repetitive inspections for cracking in the
cabin floor beam junction at certain fuselage frame locations, and
repair if necessary. The FAA issued AD 2017-14-14 to detect and correct
cracking in the cabin floor beam junction at certain fuselage frame
locations, which could result in reduced structural integrity of the
airplane.
Actions Since AD 2017-14-14 Was Issued
Since the FAA issued AD 2017-14-14, EASA revised EASA AD 2016-0105,
dated June 6, 2016, and issued EASA ADs 2016-0105R1, dated September
21, 2018 (EASA AD 2016-0105R1), and 2016-0105R2, dated October 8, 2021
(EASA AD 2016-0105R2), for all Airbus SAS Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. EASA AD 2016-0105R1 stated
that the manufacturer developed a modification that restores the
fatigue potential at each location (junction) by doing cold-working at
the cabin floor beam and fitting junction for airplanes with a pre-mod
155607 configuration. EASA AD 2016-0105R1 was revised by EASA AD 2016-
0105R2, which stated that the manufacturer developed optional
modification instructions for airplanes with a post-mod 155607
configuration. These modifications can be used to extend the compliance
time for an inspection cycle. EASA then superseded EASA AD 2016-0105R2
with EASA AD 2024-0128, dated July 3, 2024 (EASA AD 2024-0128) (also
referred to as the MCAI), to correct the unsafe condition for the same
airplanes. EASA AD 2024-0128 states that further analysis determined
that the compliance times for the inspections must also be based on
flight hours.
The FAA is proposing this AD to address cracking in the cabin floor
beam junction at certain fuselage frame locations, which could result
in reduced structural integrity of the airplane. You may examine the
MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2025-
0213.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2017-14-14, this proposed AD would retain all of the
requirements of AD 2017-14-14. Those requirements are referenced in
EASA AD 2024-0128, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0128 specifies procedures for inspections for cracking
on the frame to cabin floor beam junction at certain fuselage frame
locations (frames 35.1 and 35.2, left- and right-hand sides), and
repairs, and optional modifications to extend an inspection interval.
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
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
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 2024-0128 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 2024-0128 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2024-0128 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 2024-0128 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 2024-
0128. Material required by EASA AD 2024-0128 for compliance will be
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2025-0213 after the
FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 494 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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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Retained actions from AD 2017- Up to 8 work- None................. Up to $680........... Up to $335,920.
14-14. hours x $85 per
hour = $680.
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Estimated Costs for Optional Actions
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Labor cost Parts cost Cost per product
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Up to 135 work-hours x $85 per Up to $7,510...... Up to $18,985.
hour = $11,475.
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[[Page 10803]]
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 Ccosts of On-Condition Actions
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Labor cost Parts cost Cost per product
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Up to 50 work-hours x $85 per hour $1,600 $5,850
= $4,250.........................
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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(f), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-14-14, Amendment 39-18958
(82 FR 33002, July 19, 2017); and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2025-0213; Project Identifier MCAI-2024-
00385-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by April 14, 2025.
(b) Affected ADs
This AD replaces AD 2017-14-14, Amendment 39-18958 (82 FR 33002,
July 19, 2017) (AD 2017-14-14).
(c) Applicability
This AD applies to all Airbus SAS Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a determination from fatigue testing on
the Model A321 airframe that cracks could develop in the cabin floor
beam junction at certain fuselage frame locations. The FAA is
issuing this AD to address cracking in the cabin floor beam junction
at certain fuselage frame locations. 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 paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2024-0128, dated July 3, 2024 (EASA AD 2024-0128).
(h) Exceptions to EASA AD 2024-0128
(1) Where EASA AD 2024-0128 refers to ``13 June 2016 [the
effective date of EASA AD 2016-0105],'' this AD requires using
August 23, 2017 (the effective date of AD 2017-14-14).
(2) Where EASA AD 2024-0128 refers to its effective date, this
AD requires using the effective date of this AD.
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0128.
(4) Where paragraph (2) of EASA AD 2024-0128 specifies an option
to ``contact Airbus for approved repair instructions and, within the
compliance time specified therein, accomplish those instructions
accordingly,'' this AD requires replacing that text with ``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.''
(i) No Reporting Requirement
Although the material referenced in EASA AD 2024-0128 specifies
to submit certain information (inspection report sheet) 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#87c6cac8c4c7e1e6e6a9e0e8f1"><span class="__cf_email__" data-cfemail="0c4d41434f4c6a6d6d226b637a">[email protected]</span></a>.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2017-14-14 are approved as
AMOCs for the corresponding provisions of EASA AD 2024-0128 that are
required by paragraph (g) of this AD.
(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
[[Page 10804]]
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 Timothy Dowling,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; telephone 206-231-3667; email <a href="/cdn-cgi/l/email-protection#baced3d7d5ced2c394ca94ded5cdd6d3d4ddfadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="5f2b3632302b3726712f713b3028333631381f393e3e71383029">[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 2024-0128,
dated July 3, 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#febfba8dbe9b9f8d9fd09b8b8c918e9fd09b8b"><span class="__cf_email__" data-cfemail="38797c4b785d594b59165d4d4a574859165d4d">[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#d2b4a0fcbbbca1a2b7b1a6bbbdbc92bcb3a0b3fcb5bda4"><span class="__cf_email__" data-cfemail="e68094c88f8895968385928f8988a688879487c8818990">[email protected]</span></a>.
Issued on February 21, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-03159 Filed 2-26-25; 8:45 am]
BILLING CODE 4910-13-P
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