Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 90, Number 130 (Thursday, July 10, 2025)]
[Rules and Regulations]
[Pages 30583-30585]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-12894]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1702; Project Identifier MCAI-2024-00067-T; 
Amendment 39-23076; AD 2025-13-10]
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 superseding Airworthiness Directive (AD) 2021-25-
14, which applied to all 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. AD 2021-25-14 required repetitive 
inspections for cracking at the wing manhole access panel attachment 
holes at certain wing skin panels, and corrective action if necessary. 
Since the FAA issued AD 2021-25-14, new investigation results 
determined that additional airplanes are subject to the unsafe 
condition and certain structural repair manual (SRM) tasks should not 
be used to accomplish repairs. This AD continues to require the actions 
in AD 2021-25-14. This AD also changes the applicability to both add 
and remove airplane models, updates the compliance times, and prohibits 
the use of certain SRM tasks for repair. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective August 14, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 14, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1702; 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 European Union Aviation Safety Agency (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-2024-1702.

FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-
222-5102; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2021-25-14, Amendment 39-21858 (86 FR 
72171, December 21, 2021) (AD 2021-25-14). AD 2021-25-14 applied to all 
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. AD 2021-25-14 required repetitive inspections for 
cracking at the wing manhole access panel attachment holes at certain 
wing skin panels and corrective action if necessary. The FAA issued AD 
2021-25-14 to address this unsafe condition, which could lead to crack 
propagation, possibly resulting in reduced structural integrity of the 
wings.
    The NPRM was published in the Federal Register on July 3, 2024 (89 
FR 55123). The NPRM was prompted by AD 2024-0027, dated January 25, 
2024 (EASA AD 2024-0027), issued by EASA, which is the Technical Agent 
for the Member States of the European Union. EASA AD 2024-0027 states 
new investigation results highlighted that

[[Page 30584]]

inspections must be applied to all models of A319, A320, and A321 
airplanes in an affected configuration, and the associated compliance 
time must be adapted to these configurations. It was determined that 
fatigue cracking may occur in affected areas on airplanes having 
Sharklets installed during production or in service.
    In the NPRM, the FAA proposed to retain the actions of AD 2021-25-
14 and to revise the applicability by adding new engine option (NEO) 
airplane models and removing Airbus SAS Model A321-111, -112, and -131 
airplanes. The FAA also proposed to update the compliance times as 
specified in EASA AD 2024-0027.
    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 to supersede AD 2021-25-14. The SNPRM was 
published in the Federal Register on February 13, 2025 (90 FR 9523). 
The SNPRM was prompted by EASA AD 2024-0230, dated December 2, 2024 
(EASA AD 2024-0230) (also referred to as ``the MCAI''), which 
superseded EASA AD 2024-0027. Since EASA AD 2024-0027 was issued, 
Airbus published certain SRM tasks for repair as a result of the 
repetitive inspections at revision dated May 2024 to remove inadequate 
instructions for bush installation at steps 2 to 9 dated February 2024 
or earlier. Accordingly, EASA AD 2024-0230 prohibits the use of SRM 
tasks 57-21-11-300-010, 57-21-11-300-021, and 57-21-11-300-025 that 
were deactivated at revision dated August 2023 for accomplishing 
repairs.
    In the SNPRM, the FAA revised the proposals in the NPRM by adding a 
prohibition against accomplishing a repair using certain SRM tasks. 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-2024-1702.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from United Airlines, who supported the 
SNPRM without change.

Conclusion

    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 reviewed the relevant 
data, considered any 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 these products. Except for 
minor editorial changes, this AD is adopted as proposed in the SNPRM. 
None of the changes will increase the economic burden on any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2024-0230, which specifies procedures for 
repetitive detailed inspections for cracks of the affected areas (left-
hand and right-hand wing manhole access panel attachment holes in the 
bottom wing skin panels 2, between rib 13 and rib 23) and applicable 
corrective actions (i.e., repair). EASA AD 2024-0230 also prohibits 
accomplishing a repair using certain SRM tasks. 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 1,650 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost     Cost per  product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  14 work-hours x $85              $0  $1,190 per           $1,963,500 per
                                    per hour = $1,190.                   inspection cycle.    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The extent of damage found during the required inspection could 
vary significantly from airplane to airplane. The FAA has no way of 
determining how much damage may be found on each airplane, the cost to 
repair the damage on each airplane, or the number of airplanes that may 
require repair.

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.

[[Page 30585]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2021-25-14, Amendment 39-21858 
(86 FR 72171, December 21, 2021); and
0
b. Adding the following new AD:

2025-13-10 Airbus SAS: Amendment 39-23076; Docket No. FAA-2024-1702; 
Project Identifier MCAI-2024-00067-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 14, 2025.

(b) Affected ADs

    This AD replaces AD 2021-25-14, Amendment 39-21858 (86 FR 72171, 
December 21, 2021) (AD 2021-25-14).

(c) Applicability

    This AD applies to all Airbus SAS airplanes identified in 
paragraphs (c)(1) through (3) of this AD, certificated in any 
category.
    (1) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -
151N, -153N, and -171N 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 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a determination that fatigue cracking 
may occur at the left-hand and right-hand wing manhole access panel 
attachment holes in the bottom wing skin panels 2, between rib 13 
and rib 23, on airplanes with Sharklets or their structural 
reinforcements installed. This AD was also prompted by a 
determination that additional airplanes are subject to the unsafe 
condition and certain structural repair manual tasks should not be 
used to accomplish repairs. The FAA is issuing this AD to address 
fatigue cracking that may occur in affected areas on airplanes 
having Sharklets installed during production or in service. The 
unsafe condition, if not addressed, could result in crack initiation 
and propagation, possibly resulting in reduced structural integrity 
of the wings.

(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 
2024-0230, dated December 2, 2024 (EASA AD 2024-0230).

(h) Exceptions to EASA AD 2024-0230

    (1) Where EASA AD 2024-0230 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2024-0230 refers to February 8, 2024 (the 
effective date of EASA AD 2024-0027, dated January 25, 2024), this 
AD requires using the effective date of this AD.
    (3) Where paragraph (2) of EASA AD 2024-0230 specifies ``any 
finding is detected as defined in the AOT, 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, 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 requirements of paragraph (4) of 
EASA AD 2024-0230.
    (5) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0230.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0230 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 (i) and (j)(2) of this AD, if any material referenced in 
EASA AD 2024-0230 contains paragraphs that are labeled as RC, the 
instructions in RC paragraphs, including subparagraphs under an RC 
paragraph, must be done to comply with this AD; any paragraphs, 
including subparagraphs under those paragraphs, that are not 
identified as RC are recommended. The instructions in paragraphs, 
including subparagraphs under those paragraphs, 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 instructions identified as RC can 
be done and the airplane can be put back in an airworthy condition. 
Any substitutions or changes to instructions 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; phone: 817-222-5102; 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 2024-0230, 
dated December 2, 2024.
    (ii) [Reserved]
    (3) For the 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 June 30, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-12894 Filed 7-9-25; 8:45 am]
BILLING CODE 4910-13-P

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