Airworthiness Directives; Airbus SAS Airplanes

Issuing agencies

Abstract

The FAA is superseding Airworthiness Directive (AD) 2025-04- 05, which applied to all Airbus SAS Model A330-841 and -941 airplanes. AD 2025-04-05 required a revision of the existing airplane flight manual (AFM) and removal of the previously required limitations; a revision of the existing minimum equipment list (MEL); one-time or repetitive seal integrity tests of each engine bleed air system (EBAS) high pressure valve (HPV); additional maintenance instructions and corrective actions; and repetitive replacement of affected HPV clips; as applicable. AD 2025-04-05 also limited the installation of affected HPV clips. Since the FAA issued AD 2025-04-05, an improved EBAS HPV with unaffected HPV clips was certified, and it was determined that the bleed monitoring computer (BMC) software (SW) must be updated. This AD continues to require the actions in AD 2025-04-05, except for repetitive replacement of affected HPV clips. This AD also requires updating the BMC SW, additional work, and an additional revision of the existing MEL for the engine bleed overpressure valve; as applicable. This AD also prohibits the installation of certain BMC software. The FAA is issuing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 91 Issue 200 (Monday, October 19, 2026)</title>
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[Federal Register Volume 91, Number 200 (Monday, October 19, 2026)]
[Rules and Regulations]
[Pages 65954-65958]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-21331]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-4649; Project Identifier MCAI-2025-00835-T; 
Amendment 39-23488; AD 2026-20-15]
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) 2025-04-

[[Page 65955]]

05, which applied to all Airbus SAS Model A330-841 and -941 airplanes. 
AD 2025-04-05 required a revision of the existing airplane flight 
manual (AFM) and removal of the previously required limitations; a 
revision of the existing minimum equipment list (MEL); one-time or 
repetitive seal integrity tests of each engine bleed air system (EBAS) 
high pressure valve (HPV); additional maintenance instructions and 
corrective actions; and repetitive replacement of affected HPV clips; 
as applicable. AD 2025-04-05 also limited the installation of affected 
HPV clips. Since the FAA issued AD 2025-04-05, an improved EBAS HPV 
with unaffected HPV clips was certified, and it was determined that the 
bleed monitoring computer (BMC) software (SW) must be updated. This AD 
continues to require the actions in AD 2025-04-05, except for 
repetitive replacement of affected HPV clips. This AD also requires 
updating the BMC SW, additional work, and an additional revision of the 
existing MEL for the engine bleed overpressure valve; as applicable. 
This AD also prohibits the installation of certain BMC software. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective November 23, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 23, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2026-4649; 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 <a href="/cdn-cgi/l/email-protection#3574714675505446541b5040475a45541b5040"><span class="__cf_email__" data-cfemail="d09194a390b5b1a3b1feb5a5a2bfa0b1feb5a5">[email&#160;protected]</span></a>. 
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-2026-4649.

FOR FURTHER INFORMATION CONTACT: Rochelle Montgomery, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 405-
551-0414; email: <a href="/cdn-cgi/l/email-protection#20724f4348454c4c450e6d4f4e54474f4d455259604641410e474f56"><span class="__cf_email__" data-cfemail="ebb98488838e87878ec5a684859f8c84868e9992ab8d8a8ac58c849d">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2025-04-05, Amendment 39-22963 (90 FR 
10853, February 28, 2025) (AD 2025-04-05). AD 2025-04-05 applied to all 
Airbus SAS Model A330-841 and -941 airplanes. AD 2025-04-05 required a 
revision of the existing AFM and removal of the previously required 
limitations; a revision of the existing MEL; one-time or repetitive 
seal integrity tests of each EBAS HPV; additional maintenance 
instructions and corrective actions; and repetitive replacement of 
affected HPV clips; as applicable. AD 2025-04-05 also limited the 
installation of affected HPV clips. The FAA issued AD 2025-04-05 to 
address a leaking HPV that may expose the pressure regulating valve 
(PRV), which is installed downstream from the HPV to high pressure, 
possibly damaging the PRV itself and preventing its closure. The unsafe 
condition, if not addressed, could result in high pressure and 
temperatures in the duct downstream from the PRV, with possible duct 
burst, damage to several systems, and consequent loss of control of the 
airplane.
    The NPRM was published in the Federal Register on June 4, 2026 (91 
FR 33674). The NPRM was prompted by EASA AD 2025-0104R1, dated March 
19, 2026 (EASA AD 2025-0104R1) (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 an improved HPV has been certified 
(Airbus Modification 210503), which introduces several design 
improvements and is equipped with HPV clips that do not have to be 
replaced at predefined intervals. The MCAI also states that it has been 
determined that the optional modification to install BMC SW 5.0 must be 
mandated on airplanes on which BMC SW 4.0 or 4.1 is installed, 
additional work defined in a later revision of the other service 
information must be accomplished, and new master minimum equipment list 
(MMEL) content must be implemented for airplanes on which BMC SW 4.0 or 
4.1 is installed. The MCAI further specifies that modification of both 
affected HPVs terminates the HPV clip replacement for the airplane, 
provided no affected HPV is re-installed on that airplane.
    In the NPRM, the FAA proposed to continue to require the actions in 
AD 2025-04-05 except for repetitive replacement of affected HPV clips, 
as specified in EASA AD 2025-0104R1. The NPRM also proposed to require 
updating the BMC SW, additional work, and an additional revision of the 
existing MEL for the engine bleed overpressure valve, as applicable; 
and to prohibit the installation of certain BMC software; as specified 
in EASA AD 2025-0104R1. 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-2026-4649.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from the Air Line Pilots Association, 
International (ALPA) who supported the NPRM without change.
    The FAA received an additional comment from Delta Air Lines 
(Delta). The following presents the comments received on the NPRM and 
the FAA's response.

Request To Provide Credit for Replacement of Affected HPVs

    Delta requested that the FAA revise the proposed AD to provide 
credit for replacement of affected EBAS HPVs (part number (P/N) 
71070A010001 or P/N 71070A020001) with non-affected EBAS HPVs (P/N 
71070A030001), using FAA-approved maintenance data, including the 
Airbus aircraft maintenance manual (AMM). Delta noted Option 2 of 
Airbus Service Bulletin A330-36-3057, dated October 28, 2024 (Airbus 
Service Bulletin A330-36-3057), provides procedures for replacing 
affected HPVs with non-affected HPVs using Airbus AMM Tasks 36-11-51-
000-806 and 36-11-51-400-806, in lieu of modification of the HPVs in 
Option 1 of that service bulletin as referenced in paragraph (30) of 
EASA AD 2025-0104R1. Delta stated operators are already conducting 
unscheduled removal and replacement of HPVs during normal operations, 
and that allowing credit for replacement of affected HPVs with non-
affected HPVs using approved AMM procedures would provide operational 
flexibility during unscheduled maintenance while achieving the same 
configuration and

[[Page 65956]]

maintaining an acceptable level of safety.
    The FAA agrees it acceptable to replace the affected HPVs with non-
affected HPVs using Option 2 of Airbus Service Bulletin A330-36-3057 in 
lieu of modifying the affected HPVs using Option 1 of that service 
bulletin. Accordingly, the FAA has revised the exception in paragraph 
(h)(10) to specify that the modification or replacement of both 
affected HPVs in accordance with Airbus Service Bulletin A330-36-3057 
constitutes terminating action for the HPV clip replacement. In 
addition, the FAA has added new paragraph (i) to this AD to provide 
credit for accomplishing the replacement using AMM Tasks 36-11-51-000-
806 and 36-11-51-400-806 before the effective date of this AD. Under 
the provisions of paragraph (k)(1) of this AD, the FAA will consider 
requests for alternative methods of compliance, should operators wish 
to use other maintenance data or the applicable AMM tasks after the 
effective date of this AD.

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.

Material Incorporated by Reference Under 1 CFR Part 51

    EASA AD 2025-0104R1 specifies procedures for the following retained 
actions:
    <bullet> For Group 1 airplanes (equipped with BMC SW 4.0) and Group 
2 airplanes (equipped with BMC SW 4.1 standard), a revision of the 
Limitations section of the existing AFM; and for Groups 1 and 2 and 
Group 3 (equipped with BMC SW 5.0 or later approved SW standard and an 
affected HPV) airplanes, removal of the previously required 
limitations.
    <bullet> For Groups 1 and 2 airplanes, implementation of the MMEL 
update that includes new provisions and procedures for Air Conditioning 
Pack, Engine Bleed Air Supply System, Engine Bleed IP (Intermediate 
Pressure) Check Valve, and Engine Bleed HP (High Pressure) Valve; and 
cancellation of the dispatch restrictions.
    <bullet> For Group 2 airplanes, a seal integrity test of each HPV; 
for Group 1 airplanes, repetitive seal integrity tests of each HPV; and 
corrective actions, which include replacement of the HPV, a detailed 
inspection of the wing bellow on engine 1(2), and replacement of any 
damaged or deformed wing bellow.
    EASA AD 2025-0104R1 describes the following retained maintenance 
instructions, among other actions, to be accomplished following certain 
faults or failures, on Groups 1 and 2 airplanes:
    <bullet> HPV troubleshooting procedure and additional maintenance 
actions after any Class 1 maintenance message associated with an HPV 
fault and corrective actions, which includes replacement of the HPV or 
wing bellow.
    <bullet> HPV seal integrity test and the additional maintenance 
actions after any Class 1 or Class 2 maintenance message associated 
with a PRV fault and corrective actions, which includes replacement of 
the HPV and PRV, a detailed inspection of the wing bellow on engine 
1(2), and replacement of any damaged or deformed wing bellow.
    <bullet> A visual (borescope) inspection of the EBAS to detect 
signs of foreign object debris (FOD), including metallic debris in the 
butterfly valve and dents or damage of the flaps of the intermediate 
pressure check valve (IPCV), and dents and missing segments in the PRV, 
the header of the HP/IP duct, y-duct, and pylon ducts after any failure 
of an HPV clip and/or any of the HPV butterfly sealing rings, and 
corrective actions, which includes FOD removal and replacement of the 
IPCV or PRV.
    <bullet> A seal integrity test of each HPV after any takeoff or go-
around accomplished with ``packs OFF'' or ``APU bleed ON'' or ``engine 
bleed OFF'' and corrective actions, which include replacement of the 
HPV, a detailed inspection of the wing bellow on engine 1(2), and 
replacement of any damaged or deformed wing bellow.
    <bullet> Additional actions to be performed for any Class 1 
maintenance message associated with an HPV fault.
    EASA AD 2025-0104R1 also specifies the following retained 
limitations for the installation of affected parts:
    <bullet> For Groups 1, 2, and 3 airplanes, installation of an 
affected HPV clip on an affected HPV on an airplane, provided it is a 
new affected clip (i.e., not previously installed on any HPV) and that 
following installation, it is replaced according to the referenced 
service information.
    <bullet> For Groups 1, 2, and 3 airplanes, installation of an 
affected HPV on an airplane, provided it is a serviceable HPV and that 
following installation, the affected HPV clips of that HPV are replaced 
with new clips according to the referenced service information.
    EASA AD 2025-0104R1 also specifies that, for Group 1 airplanes, 
modification (update to BMC SW 4.1) of the airplane terminates the 
repetitive seal integrity tests of each HPV.
    EASA AD 2025-0104R1 specifies the following new actions:
    <bullet> For Groups 1 and 2 airplanes, modification (update to BMC 
SW 5.0) of the airplane, which includes deletion of the operations 
engineering bulletin (OEB) reminder data from the flight warning 
computer (FWC) database.
    <bullet> For Group 3 airplanes, accomplishment of additional work 
(deletion of the OEB reminder data from the FWC database).
    <bullet> For Groups 1 and 2 airplanes, implementation of the MMEL 
update that includes new provisions for Engine Bleed Overpressure 
Valve.
    EASA AD 2025-0104R1 also prohibits the installation of the 
following affected parts:
    <bullet> BMC SW 4.0 or BMC SW 4.1 on any Group 3 or Group 4 
(embodied with Airbus modifications 210503 and 210504 in production) 
airplane, and on any Group 1 or 2 airplane after modification (update 
to BMC SW 5.0) of the airplane.
    <bullet> An affected HPV on any Group 4 airplane.
    EASA AD 2025-0104R1 also specifies that, for Groups 1, 2, and 3 
airplanes, modification of both affected HPVs terminates the HPV clip 
replacement for the airplane, provided no affected HPV is re-installed 
on that airplane; and if modification of the two affected HPVs are 
accomplished at different times, the HPV clip replacement is only 
applicable to the affected HPV.
    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 would affect 22 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 65957]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2025-04- Up to 15 work-      Up to $28.........  Up to $1,303......  Up to $28,666.
 05.                               hours x $85 per
                                   hour = $1,275.
New actions for Groups 1 and 2    5 work-hours x $85  $524..............  $949..............  Up to $20,878 *.
 airplanes (software update,       per hour = $425.
 additional work, and MEL
 revision).
New actions for Group 3           2 work-hours x $85  $0................  $170..............  Up to $3,740 *.
 airplanes (additional work).      per hour = $170.
----------------------------------------------------------------------------------------------------------------
* The FAA has no definitive data to determine how many affected airplanes are in each airplane group.

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
           Labor cost                 Parts cost       Cost per product
------------------------------------------------------------------------
Up to 19 work-hours x $85 per     Up to $114,742....  Up to $116,357.
 hour = $1,615.
------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the maintenance actions specified in this AD.

                         Estimated Costs for Optional Modification of Both Affected HPVs
----------------------------------------------------------------------------------------------------------------
                            Labor cost                                  Parts cost          Cost per product
----------------------------------------------------------------------------------------------------------------
11 work-hours x $85 per hour = $935..............................             $96,885                   $97,790
----------------------------------------------------------------------------------------------------------------

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:
0
a. Removing Airworthiness Directive (AD) 2025-04-05, Amendment 39-22963 
(90 FR 10853, February 28, 2025); and

0
b. Adding the following new AD:

2026-20-15 Airbus SAS: Amendment 39-23488; Docket No. FAA-2026-4649; 
Project Identifier MCAI-2025-00835-T.

(a) Effective Date

    This airworthiness directive (AD) is effective November 23, 
2026.

(b) Affected ADs

    This AD replaces AD 2025-04-05, Amendment 39-22963 (90 FR 10853, 
February 28, 2025) (AD 2025-04-05).

(c) Applicability

    This AD applies to all Airbus SAS Model A330-841 and -941 
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 36, Pneumatic.

(e) Unsafe Condition

    This AD was prompted by reports of leaking bleed system high 
pressure valves (HPV), likely due to HPV clip failure and sealing 
ring damage. This AD was also prompted by certification of an 
improved

[[Page 65958]]

HPV with unaffected HPV clips and the determination that the bleed 
monitoring computer (BMC) software must be updated. The FAA is 
issuing this AD to address a leaking HPV that may expose the 
pressure regulating valve (PRV), which is installed downstream from 
the HPV to high pressure, possibly damaging the PRV itself and 
preventing its closure. The unsafe condition, if not addressed, 
could result in high pressure and temperatures in the duct 
downstream from the PRV, with possible duct burst, damage to several 
systems, and consequent loss of control 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), (i), and (j) of this AD: 
Comply with all required actions and compliance times specified in, 
and in accordance with, European Union Aviation Safety Agency (EASA) 
AD 2025-0104R1, dated March 19, 2026 (EASA AD 2025-0104R1).

(h) Exceptions to EASA AD 2025-0104R1

    (1) Where EASA AD 2025-0104R1 refers to May 21, 2025 (the 
effective date of the original issue of EASA AD 2025-0104, dated May 
7, 2025), this AD requires using the effective date of this AD.
    (2) Where EASA AD 2025-0104R1 refers to May 28, 2024 (the 
effective date of EASA AD 2023-0111R1, dated May 28, 2024), this AD 
requires using April 4, 2025 (the effective date of AD 2025-04-05).
    (3) Where EASA AD 2025-0104R1 refers to June 2, 2023 (the 
effective date of the original issue of EASA AD 2023-0111, dated May 
26, 2023), this AD requires using April 4, 2025 (the effective date 
of AD 2025-04-05).
    (4) Where paragraph (19) of EASA AD 2025-0104R1 refers to 
December 8, 2022 (the effective date of EASA AD 2022-0227, dated 
November 24, 2022), this AD requires using April 4, 2025 (the 
effective date of AD 2025-04-05).
    (5) Where paragraph (21) of EASA AD 2025-0104R1 refers to 
December 8, 2022 (the effective date of EASA AD 2022-0227, dated 
November 24, 2022), this AD requires using July 18, 2023 (the 
effective date of AD 2023-11-08, Amendment 39-22454 (88 FR 38384, 
June 13, 2023)).
    (6) Where EASA AD 2025-0104R1 refers to September 5, 2022 (the 
effective date of EASA AD 2022-0181, dated August 29, 2022), this AD 
requires using September 15, 2022 (the effective date of AD 2022-19-
05, Amendment 39-22174 (87 FR 54870, September 8, 2022)).
    (7) Where EASA AD 2025-0104R1 defines a Serviceable HPV, in 
part, as ``EBAS HPV, eligible for installation in accordance with 
Airbus instructions'', this AD requires replacing that text with 
``EBAS HPV eligible for installation''.
    (8) Where paragraphs (1), (2), (3), (7), and (29) of EASA AD 
2025-0104R1 specify to inform all flightcrews of airplane flight 
manual (AFM) revisions and dispatch limitations, and thereafter 
operate the airplane accordingly, this AD does not require those 
actions, as those actions are already required by existing FAA 
operating regulations (see 14 CFR 91.9, 91.505, and 121.137 for AFM 
requirements and 14 CFR 121.628(a)(2) and (5) for minimum equipment 
list requirements).
    (9) Where paragraph (20) of EASA AD 2025-0104R1 specifies ``as 
required by paragraph (17) of the original issue of this AD'', this 
AD requires replacing that text with ``as required by AD 2025-04-05 
as specified in paragraph (17) of EASA AD 2023-0111R1''.
    (10) Where paragraph (30) of EASA AD 2025-0104R1 specifies 
``Modification of both EBAS HPV'', this AD requires replacing that 
text with ``Modification or replacement of both affected HPVs''.
    (11) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0104R1.

(i) Credit for Previous Actions

    Replacing both affected HPVs with non-affected HPVs having part 
number 71070A030001 before the effective date of this AD using 
Airbus Aircraft Maintenance Manual (AMM) Tasks 36-11-51-000-806 and 
36-11-51-400-806 may be accomplished in lieu of modifying both 
affected HPVs, as specified in paragraph (30) of EASA AD 2025-
0104R1.

(j) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0104R1 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(k) 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 (l)(1) of this AD and email to: 
<a href="/cdn-cgi/l/email-protection#f7b6bab8b4b7919696d9909881"><span class="__cf_email__" data-cfemail="0f4e42404c4f696e6e21686079">[email&#160;protected]</span></a>.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (ii) AMOCs approved previously for AD 2025-04-05 are approved as 
AMOCs for the corresponding provisions of EASA AD 2025-0104R1 that 
are required by paragraph (g) of this AD.
    (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 
paragraphs (j) and (k)(2) of this AD, if any material referenced in 
EASA AD 2025-0104R1 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.

(l) Additional Information

    (1) For more information about this AD, contact Rochelle 
Montgomery, Aviation Safety Engineer, FAA, 2200 South 216th St., Des 
Moines, WA 98198; phone: 405-551-0414; email: 
<a href="/cdn-cgi/l/email-protection#61330e0209040d0d044f2c0e0f15060e0c041318210700004f060e17"><span class="__cf_email__" data-cfemail="64360b070c010808014a290b0a10030b0901161d240205054a030b12">[email&#160;protected]</span></a>.
    (2) For Airbus SAS material identified in this AD that is not 
incorporated by reference, 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 
<a href="/cdn-cgi/l/email-protection#bdded2d3c9d4d3c8d8d990dcd4cfcad2cfc9d5d4d3d8cece93dc8e888dfd81dc9dd5cfd8db80" http: airbus.com">airbus.com</a>">continued-airworthiness.a350@<a href="http://airbus.com">airbus.com</a></a>; website <a href="http://airbus.com">airbus.com</a>.

(m) 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 2025-0104R1, 
dated March 19, 2026.
    (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#7d3c390e3d181c0e1c5318080f120d1c531808"><span class="__cf_email__" data-cfemail="5e1f1a2d1e3b3f2d3f703b2b2c312e3f703b2b">[email&#160;protected]</span></a>. 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#4f293d6126213c3f2a2c3b2620210f212e3d2e61282039"><span class="__cf_email__" data-cfemail="3355411d5a5d40435650475a5c5d735d5241521d545c45">[email&#160;protected]</span></a>.

    Issued on October 9, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division, 
Aircraft Certification Service.
[FR Doc. 2026-21331 Filed 10-16-26; 8:45 am]
BILLING CODE 4910-13-P


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