AD 2025-01-02

[Federal Register Volume 90, Number 22 (Tuesday, February 4, 2025)]
[Rules and Regulations]
[Pages 8866-8868]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-02148]



[[Page 8866]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2327; Project Identifier MCAI-2024-00233-T; 
Amendment 39-22926; AD 2025-01-02]
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 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 a full-scale fatigue test 
that found cracks on the main landing gear (MLG) bay rear skin panel at 
the stringer run-out at Frame 46 and Stringer 32 on the left-hand and 
right-hand sides. This AD requires repetitive special detailed 
inspections (SDIs) of the affected area for cracking and applicable 
corrective actions, 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 March 11, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 11, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2024-2327; 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 <a href="/cdn-cgi/l/email-protection#0d4c497e4d686c7e6c2368787f627d6c236878"><span class="__cf_email__" data-cfemail="2160655261444052400f4454534e51400f4454">[email&#160;protected]</span></a>; website easa.europa.eu. 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 <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2024-2327.

FOR FURTHER INFORMATION CONTACT: Tim Dowling, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-
231-3667; email <a href="/cdn-cgi/l/email-protection#d6a2bfbbb9a2beaff8a6f8b2b9a1babfb8b196b0b7b7f8b1b9a0"><span class="__cf_email__" data-cfemail="15617c787a617d6c3b653b717a62797c7b72557374743b727a63">[email&#160;protected]</span></a>.

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 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 October 8, 2024 (89 FR 
81403). The NPRM was prompted by AD 2024-0089, dated April 15, 2024, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union (EASA AD 2024-0089) (also referred to as the MCAI). 
The MCAI states that cracks were found on the MLG bay rear skin panel 
at stringer runout at Frame 46 and Stringer 32 on the left-hand and 
right-hand sides during a full-scale fatigue test. This condition, if 
not addressed, could lead to crack propagation, possibly resulting in 
reduced structural integrity of the airplane.
    In the NPRM, the FAA proposed to require repetitive SDIs of the 
affected area for cracking and applicable corrective actions, as 
specified in EASA AD 2024-0089. The FAA is issuing this AD to address 
the unsafe condition on these products.
    You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2024-2327.

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.

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 
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 this product. 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 2024-0089 specifies procedures for repetitive SDIs of the 
MLG bay rear skin panel at the stringer run-out at Frame 46 and 
Stringer 32 on the left-hand and right-hand sides and applicable 
corrective actions. Corrective actions include 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 1,857 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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                Labor cost                  Parts cost        Cost per product          Cost on U.S. operators
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3 work-hours x $85 per hour = $255 per              $0  $255 per inspection cycle..  $473,535 per inspection
 inspection cycle.                                                                    cycle.
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[[Page 8867]]

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions 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:

2025-01-02 Airbus SAS: Amendment 39-22926; Docket No. FAA-2024-2327; 
Project Identifier MCAI-2024-00233-T.

 (a) Effective Date

    This airworthiness directive (AD) is effective March 11, 2025.

 (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 2024-0089, dated April 15, 2024 (EASA AD 2024-0089).
    (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (2) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (3) 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 a full-scale fatigue test that found 
cracks on the main landing gear (MLG) bay rear skin panel at the 
stringer run-out at Frame 46 and Stringer 32 on the left-hand and 
right-hand sides. The FAA is issuing this AD to detect potential 
fatigue cracking on the MLG bay rear skin panel at the stringer run-
out at Frame 46 and Stringer 32 on the left-hand and right-hand 
sides. The unsafe condition, if not addressed, could lead to crack 
propagation, possibly 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 2024-0089.

 (h) Exceptions to EASA AD 2024-0089

    (1) Where EASA AD 2024-0089 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where paragraph (2) of EASA AD 2024-0089 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 any inspection as required by 
paragraph (1) of this AD, any cracking is found, before next flight, 
repair the cracking using a method approved by the Manager, 
International Validation 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) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0089.

 (i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0089 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, 
International Validation 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 
International Validation 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#4504080a06052324246b222a33"><span class="__cf_email__" data-cfemail="4b0a0604080b2d2a2a652c243d">[email&#160;protected]</span></a>. 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, International 
Validation 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 
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 Tim Dowling, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 206-231-3667; email: 
<a href="/cdn-cgi/l/email-protection#5e2a3733312a3627702e703a3129323730391e383f3f70393128"><span class="__cf_email__" data-cfemail="62160b0f0d160a1b4c124c060d150e0b0c05220403034c050d14">[email&#160;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.

[[Page 8868]]

    (i) European Union Aviation Safety Agency (EASA) AD 2024-0089, 
dated April 15, 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#c08184b380a5a1b3a1eea5b5b2afb0a1eea5b5"><span class="__cf_email__" data-cfemail="2d6c695e6d484c5e4c0348585f425d4c034858">[email&#160;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#6402164a0d0a17140107100d0b0a240a0516054a030b12"><span class="__cf_email__" data-cfemail="f09682de999e8380959384999f9eb09e918291de979f86">[email&#160;protected]</span></a>.

    Issued on December 31, 2024.
John P. Piccola, Jr.,
Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-02148 Filed 2-3-25; 8:45 am]
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