Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 91, Number 165 (Thursday, August 27, 2026)]
[Rules and Regulations]
[Pages 55250-55252]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-17552]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-3879; Project Identifier MCAI-2025-01452-T; 
Amendment 39-23444; AD 2026-17-01]
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 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 fatigue test that 
identified cracks in the forward and aft upper corner of the bulk cargo 
door. This AD requires a rototest inspection for cracks and applicable 
on-condition actions. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective October 1, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 1, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-3879; 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-2026-3879.

FOR FURTHER INFORMATION CONTACT: Camille Seay, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-
222-5149; 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 certain Airbus SAS 
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 was published in the Federal Register on May 4, 2026 (91 FR 
23922). The NPRM was prompted by EASA AD 2025-0193, dated September 8, 
2025 (EASA AD 2025-0193) (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 during a fatigue test on a Model 
A320 airplane in support of the extended service goal (ESG) campaign, 
cracks were identified in the area of fastener holes at the forward and 
aft upper corner of the bulk cargo door at section 16 and 17, both 
left-hand (LH) and right-hand (RH) sides. This condition, if not 
addressed, could affect the structural integrity of the airplane.
    In the NPRM, the FAA proposed to require a rototest inspection for 
cracks and applicable on-condition actions, as specified in EASA AD 
2025-0193. 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-2026-3879.

Discussion of Final Airworthiness Directive

Comments

    The FAA received and reviewed a comment that did not include a 
specific request to change the AD. This comment is outside the scope 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

[[Page 55251]]

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 2025-0193 specifies procedures for a rototest inspection 
for cracks in the area of the fastener holes at the forward and aft 
upper corner of the bulk cargo door at section 16 and 17, both LH and 
RH sides, and applicable on-condition actions. On-condition actions 
include contacting the manufacturer for repair instructions and doing 
the repair if cracks are detected, or modifying the affected area by 
cold working the fastener holes if no crack is detected.
    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 1,069 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
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340...........................              $0             $340         $363,460
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             Estimated Costs of On-Condition Modification *
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
4 work-hours x $85 per hour = $340....              $0             $340
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* The FAA has received no definitive data on which to base the cost
  estimates for the on-condition repairs 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:

2026-17-01 Airbus SAS: Amendment 39-23444; Docket No. FAA-2026-3879; 
Project Identifier MCAI-2025-01452-T.

(a) Effective Date

    This airworthiness directive (AD) is effective October 1, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A320-211, -212, -214, -216, 
-231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2025-0193, dated September 8, 2025 (EASA AD 2025-0193), 
having an extended service goal (ESG) in the airworthiness 
limitations section of the instructions for continued airworthiness.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a fatigue test that identified cracks in 
the area of the fastener holes at the forward and aft upper corner 
of the bulk cargo door at section 16 and 17. The FAA is issuing this 
AD to address cracks in the forward and aft upper corner of the bulk 
cargo door, which, if not addressed, could affect the 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 paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2025-0193.

(h) Exceptions to EASA AD 2025-0193

    (1) Where EASA AD 2025-0193 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where the definition of the ``affected area'' in EASA AD 
2025-0193 specifies ``as

[[Page 55252]]

defined in the SB'', this AD requires replacing that text with ``as 
specified in Airbus Service Bulletin A320-53-1303, dated March 7, 
2025''.
    (3) Where paragraph (2) of EASA AD 2025-0193 specifies ``if any 
crack is detected, 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 ``if any crack is detected, the 
crack must be repaired before further flight using a method approved 
by the Manager, AIR-520, 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 ``Remarks'' section of EASA AD 
2025-0193.

(i) Additional AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-
520, 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 (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, 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 (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 Camille Seay, 
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 
98198; phone: 817-222-5149; 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) European Union Aviation Safety Agency (EASA) AD 2025-0193, 
dated September 8, 2025.
    (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 [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 August 11, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division, 
Aircraft Certification Service.
[FR Doc. 2026-17552 Filed 8-26-26; 8:45 am]
BILLING CODE 4910-13-P

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