[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
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.
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