Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 91, Number 21 (Monday, February 2, 2026)]
[Rules and Regulations]
[Pages 4428-4431]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-02095]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0611; Project Identifier MCAI-2024-00763-T; 
Amendment 39-23243; AD 2026-02-07]
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 all 
Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by 
reports that certain lower torque links of the nose landing gear (NLG) 
were manufactured without bright shot peening; the omission of bright 
shot peening could result in reduced fatigue life of the parts. This AD 
requires replacement of affected parts before exceeding their reduced 
life limit and limits the installation of affected parts. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 9, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 9, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2025-0611; 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 Airbus material identified in this AD, contact Airbus 
SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 
80; email airbus.com">continued-airworthiness.a350@airbus.com; website airbus.com.
    <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-2025-0611.

FOR FURTHER INFORMATION CONTACT: Nicholas Benson, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3647; 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 all Airbus SAS Model 
A350-941 and -1041 airplanes. The NPRM was published in the Federal 
Register on April 7, 2025 (90 FR 14920). The NPRM was prompted by AD 
2024-0248,

[[Page 4429]]

dated December 18, 2024 (EASA AD 2024-0248) (also referred to as the 
MCAI), issued by EASA, which is the Technical Agent for the Member 
States of the European Union. The MCAI states that it has been reported 
that certain NLG lower torque links were manufactured without bright 
shot peening. The omission of bright shot peening may reduce the 
fatigue life of the component, depending on which weight variant and 
NLG standard the component is installed on. This condition, if not 
corrected, could lead to failure of the NLG, possibly resulting in 
damage to the airplane and injury to occupants.
    In the NPRM, the FAA proposed to require replacement of affected 
parts before exceeding their reduced life limit and limit the 
installation of affected parts, as specified in EASA AD 2024-0248. 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-2025-0611.

Discussion of Final Airworthiness Directive

Comments

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

Request To Clarify Compliance Time

    Delta requested clarification regarding the compliance time for 
operators to implement the new life limits. Delta stated that paragraph 
(1) of EASA AD 2024-0248 identifies the limit for when the affected 
parts must be replaced but does not specify how long operators have to 
implement the new life limits. Delta noted, in contrast, all EASA ADs 
pertaining to Airworthiness Limitations Section (ALS) Part 1 allow 12 
months to implement the new life limits, and the corresponding FAA ADs 
specify implementing all limits within 90 days after the effective date 
of the AD.
    The FAA notes that this AD does not require operators to revise 
their existing maintenance or inspection program to incorporate the 
reduced safe life limits for the affected parts. Instead, this AD 
requires replacing an affected part before it exceeds the reduced safe 
life limit. Since the FAA has not identified any affected parts that 
are close to exceeding the reduced life limits, it is not necessary to 
provide a 90-day compliance time for their incorporation. The FAA has 
not changed this AD in this regard.

Request To Omit Clearance Check if Replacement Is Done During NLG 
Overhaul

    Delta requested that the FAA add an exception to paragraph (h) of 
the proposed AD to specify if the affected lower torque link is 
replaced during NLG overhaul by the appropriate vendor, then a 
clearance check is not required, as specified in paragraph 3.E of the 
Accomplishment Instructions of the service information referenced in 
EASA AD 2024-0248. Delta noted that the clearance check is identified 
in the service information as required for compliance. However, Delta 
stated that replacement of the affected part will be performed during 
NLG overhaul and therefore the clearance check is not needed.
    The FAA disagrees with the request. If replacement of the lower 
torque link is accomplished while the NLG is off the airplane, the 
clearance check is required after the NLG is re-installed on the 
airplane. However, under the provisions of paragraph (i)(1) of this AD, 
the FAA will consider requests for AMOCs. The FAA has not changed this 
AD in this regard.

Request To Clarify Part Number (P/N) Definition for Component and 
Assembly

    Delta requested that the FAA add an exception to paragraph (h) of 
the proposed AD to include the following clarification to the 
definition of ``Affected parts'': Lower torque link component P/N 5035-
0401 (FIN 6010GN) is the main part of lower torque link assembly P/N 
5035A0400-01 (FIN 5011GN). Delta stated that EASA AD 2024-0248 requires 
replacement of NLG lower torque link component P/N 5035-0401 as 
referenced in Airbus Service Bulletin A350-32-P057, Revision 01, dated 
December 12, 2024 (Revision 01 of Airbus Service Bulletin A350-32-
P057), but the component is a non-procurable part and therefore does 
not appear in the component maintenance manual (CMM) for shock strut 
assembly P/N 4816A0000-06 or the CMM for shock strut assembly P/N 
6406A0000-01. Delta noted that the proposed AD does not address this 
concern.
    The FAA disagrees with the request. Clarification is not needed 
because the Accomplishment Instructions of Revision 01 of Airbus 
Service Bulletin A350-32-P057 specify that the NLG lower torque link 
component (FIN 6010GN) is a subcomponent of lower torque link assembly 
(FIN 5011GN) to distinguish between NLG lower torque link component 
(FIN 6010GN) P/N 5035-0401 and lower torque link assembly (FIN 5011GN), 
and the ``Life Limitations of the Affected Nose Landing Gear (NLG) 
Lower Torque Link Component'' table in Appendix B identifies lower 
torque link component 6010GN as P/N 5035-0401. Further, the FAA notes 
that replacing the lower torque link assembly (FIN 6010GN) would 
constitute replacement of the affected part. The FAA has not changed 
this AD in this regard.

Request To Correct the Sliding Piston Assembly Part Number

    Delta requested that the FAA add an exception to paragraph (h) of 
the proposed AD to correct the NLG sliding piston assembly part number 
referenced in flagnote 01 in Appendix B of Revision 01 of Airbus 
Service Bulletin A350-32-P057. Delta stated that service information 
references incorrect P/N 64072000-XX. Delta noted the CMM for shock 
strut assembly P/N 6406A0000-01 identifies the sliding piston assembly 
part number as P/N 6407A2000-XX, and that Airbus acknowledged the error 
in Revision 01 of Airbus Service Bulletin A350-32-P057 via a 
TechRequest message with Delta.
    The FAA agrees that P/N 6407A2000-XX is correct, as specified in 
Airbus Service Bulletin A350-32-P057, dated September 30, 2024. 
Accordingly, the FAA has added a new exception in paragraph (h)(4) of 
this AD to correct the part number in Revision 01 of Airbus Service 
Bulletin A350-32-P057.

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, 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.

[[Page 4430]]

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2024-0248, which specifies procedures for 
replacement of NLG lower torque links identified with P/N 5035-0401 and 
certain serial numbers before exceeding their reduced life limit. EASA 
AD 2024-0248 also limits installation of affected parts. The FAA also 
reviewed Airbus Service Bulletin A350-32-P057, Revision 01, dated 
December 12, 2024, which specifies procedures for an inspection or 
records check to determine if an affected part is installed, 
replacement of an affected part with a serviceable part, and applicable 
clearance check.
    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 34 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
----------------------------------------------------------------------------------------------------------------
9 work-hours x $85 per hour = $765...........................         $28,000          $28,765         $978,010
----------------------------------------------------------------------------------------------------------------

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:

2026-02-07 Airbus SAS: Amendment 39-23243; Docket No. FAA-2025-0611; 
Project Identifier MCAI-2024-00763-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 9, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A350-941 and -1041 
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing Gear.

(e) Unsafe Condition

    This AD was prompted by reports that certain lower torque links of 
the nose landing gear (NLG) were manufactured without bright shot 
peening; the omission of bright shot peening could result in reduced 
fatigue life of the parts. The FAA is issuing this AD to address 
omitted bright shot peening. The unsafe condition, if not addressed, 
could lead to failure of the nose landing gear, possibly resulting in 
damage to the airplane and injury to occupants.

(f) Compliance

    Comply with this AD within the compliance times specified, unless 
already done.

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in accordance 
with, European Union Aviation Safety Agency (EASA) AD 2024-0248, dated 
December 18, 2024 (EASA AD 2024-0248).

(h) Exceptions to EASA AD 2024-0248

    (1) Where EASA AD 2024-0248 refers to its effective date, this AD 
requires using the effective date of this AD.
    (2) Where EASA AD 2024-0248 defines a serviceable part as ``Any NLG 
Lower Torque Link eligible for installation in accordance with Airbus 
instructions, which is not an affected part'', this AD requires 
replacing that text with ``Any NLG lower torque link, eligible for 
installation, which is not an affected part''.
    (3) This AD does not adopt the ``Remarks'' section of EASA AD 2024-
0248.
    (4) Where flagnote 01 in Appendix B of Airbus Service Bulletin 
A350-32-P057, Revision 01, dated December 12, 2024, specifies ``PN 
64072000-XX'', this AD requires replacing that text with ``PN 
6407A2000-XX''.

(i) 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

[[Page 4431]]

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 (j) 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 
(i)(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.

(j) Additional Information

    For more information about this AD, contact Nicholas Benson, 
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 
98198; phone: 206-231-3647; email: [email protected].

(k) 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) Airbus Service Bulletin A350-32-P057, Revision 01, dated 
December 12, 2024.
    (ii) European Union Aviation Safety Agency (EASA) AD 2024-0248, 
dated December 18, 2024.
    (3) For Airbus material identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 
80; email airbus.com">continued-airworthiness.a350@airbus.com; website airbus.com.
    (4) 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.
    (5) 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.
    (6) 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 January 15, 2026.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2026-02095 Filed 1-30-26; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T00:51:35.607392+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

d0b161d0a4ef5b34830db31616e2fabd065d9474088896db1b5eee0df0780132

Text SHA-256

5365134c25da30f590f51bd66aa0be17fc4de00ab2cba95d4eb255150c54bad5