Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 90, Number 83 (Thursday, May 1, 2025)]
[Rules and Regulations]
[Pages 18627-18629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-07488]



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Federal Register / Vol. 90, No. 83 / Thursday, May 1, 2025 / Rules 
and Regulations

[[Page 18627]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2548; Project Identifier MCAI-2024-00401-T; 
Amendment 39-23026; AD 2025-09-05]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
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. This AD was prompted 
by cracks being found during full-scale fatigue testing of the keel 
beam bottom panel between the edge profile and stringer run-out at a 
certain frame and stringer. This AD requires repetitive special 
detailed inspections (SDI) of the affected area, and corrective 
actions, if necessary, as specified in a European Union Aviation Safety 
Agency (EASA) AD, which is incorporated by reference. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 5, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 5, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-2548; 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 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-2024-2548.

FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 206-231-3667; 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 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. The NPRM published in the Federal 
Register on December 9, 2024 (89 FR 97564). The NPRM was prompted by AD 
2024-0135, dated July 10, 2024, issued by EASA, which is the Technical 
Agent for the Member States of the European Union (EASA AD 2024-0135) 
(also referred to as the MCAI). The MCAI states that during full-scale 
fatigue testing, cracks were found on the keel beam bottom panel 
between the edge profile and stringer run-out at frame 46 and stringer 
37, left- and right-hand sides. Crack propagation in this area could 
possibly result in reduced structural integrity of the airplane.
    In the NPRM, the FAA proposed to require repetitive SDIs of the 
affected area, and corrective actions, if necessary, as specified in 
EASA AD 2024-0135. 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-2024-2548.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from Air Line Pilots Association, 
International (ALPA) and United Airlines, who supported the NPRM 
without change.
    The FAA received an additional comment from American Airlines. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request for Change to Paragraph (h)(3)

    American Airlines requested that paragraph (h)(3) of the proposed 
AD be updated to read: ``Where paragraph (3) of EASA AD 2024-0135 does 
not allow corrective action as terminating action for the repetitive 
inspection requirements `unless otherwise stated in the repair 
instructions provide by Airbus,' this AD requires that any terminating 
action be specified in repair instructions approved 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.'' The commenter stated that this change would align 
paragraph (h)(3) of the proposed AD with paragraph (h)(2) of the 
proposed AD and still require proper approval for any terminating 
repair instructions, and would also reduce unnecessary duplicate 
Alternative Method of Compliance (AMOC) requests from operators if 
multiple airplanes have similar repair procedures accomplished.
    The FAA agrees to clarify. The FAA has determined that paragraph 
(h)(3) of the proposed AD was not clearly written. The intent of that 
exception is to specify that the ``repair instructions'' referenced in 
paragraph (3) of EASA AD 2024-0135 are the same repair instructions 
obtained as specified in paragraph (h)(2) of this AD. The FAA has 
revised paragraph (h)(3) of this AD to specify that the repair 
instructions are those obtained from the Manager, AIR-

[[Page 18628]]

520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's 
EASA DOA.

Conclusion

    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 reviewed the relevant data, considered the 
comment 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 this product. 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

    EASA AD 2024-0135 specifies procedures for repetitive SDIs for 
discrepancies (cracks) of the keel beam bottom panel between the edge 
profile and stringer run-out at frame 46 and stringer 37, left-hand and 
right-hand sides. EASA AD 2024-0135 also specifies corrective actions 
including crack 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.

Costs of Compliance

    The FAA estimates that this AD affects 1,920 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................              $0           $1,360       $2,611,200
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this 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

    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:

2025-09-05 Airbus SAS: Amendment 39-23026; Docket No. FAA-2024-2548; 
Project Identifier MCAI-2024-00401-T.

(a) Effective Date

    This airworthiness directive (AD) is effective June 5, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus SAS airplanes, certificated in any 
category, as identified in paragraphs (c)(1) through (4) of this AD 
and in European Union Aviation Safety Agency (EASA) AD 2024-0135, 
dated July 10, 2024 (EASA AD 2024-0135).
    (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 cracks being found during full-scale 
fatigue testing of the keel beam bottom panel between the edge 
profile and stringer run-out at frame 46 and stringer 37, left- and 
right-hand sides. The FAA is issuing this AD to address crack 
propagation in this area. 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, EASA AD 2024-0135.

(h) Exceptions to EASA AD 2024-0135

    (1) Where EASA AD 2024-0135 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where paragraph (2) of EASA AD 2024-0135 specifies ``if, 
during any inspection as required by paragraph (1) of this AD, 
discrepancies are detected, as defined in the SB, before next 
flight, contact Airbus for approved repair instructions and 
accomplish those instructions accordingly,'' this AD requires 
replacing that text with ``if, during

[[Page 18629]]

any inspection as required by paragraph (1) of this AD, any cracking 
is detected, 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.''
    (3) Where paragraph (3) of EASA AD 2024-0135 specifies ``unless 
otherwise stated in the repair instructions provide by Airbus,'' 
this AD requires replacing that text with ``unless otherwise stated 
in the repair instructions provided 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 
2024-0135.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0135 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 
AIR-520, 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 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 
paragraph (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, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 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 2024-0135, 
dated July 10, 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]. 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 April 24, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-07488 Filed 4-30-25; 8:45 am]
BILLING CODE 4910-13-P

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