Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 90, Number 157 (Monday, August 18, 2025)]
[Rules and Regulations]
[Pages 40032-40035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-15686]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0342; Project Identifier MCAI-2024-00477-T; 
Amendment 39-23103; AD 2025-16-05]
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 A300 B4-2C, A300 B4-203, A300 B4-603, A300 B4-
605R, A300 B4-622, A300 B4-622R, and A300 F4-605R airplanes. This AD 
was prompted by reports of cracking of the main landing gear (MLG) 
support rib 5 lower flange on certain modified airplanes due to 
incorrect accomplishment of modification instructions. This AD requires 
a special detailed inspection (geometrical inspection) of the MLG rib 5 
lower flange holes on the left-hand wing and right-hand wing and repair 
if necessary. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective September 22, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
22, 2025.

ADDRESSES: 

[[Page 40033]]

    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2025-0342; 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-2025-0342.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aviation Safety Engineer, 
FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3225; 
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 A300 B4-2C, A300 B4-203, A300 B4-603, A300 B4-605R, A300 B4-622, 
A300 B4-622R, A300 C4-203, A300 C4-620, A300 F4-203, A300 F4-605R, and 
A300 F4-608ST airplanes. The NPRM was published in the Federal Register 
on March 12, 2025 (90 FR 11815). The NPRM was prompted by AD 2024-0162, 
dated August 20, 2024 (EASA AD 2024-0162) (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 as a result of in-
service cracking in an MLG attachment fitting at rib 5, the gear rib 5 
lower flange area is the subject of two consecutive mandated retrofit 
modifications (mandated by EASA AD 2011-0029, dated February 24, 2011 
(which corresponds to FAA AD 2012-01-05, Amendment 39-16917 (77 FR 
26937, May 8, 2012)) and EASA AD 2011-0028, dated February 24, 2011 
(for Model A300 F4-608ST airplanes)) to increase the corner radius, 
diameter, and depth of the critical spotfaces in order to decrease the 
stress level generated in the structure. Following occurrences of lower 
flange cracking reported on airplanes in mandated retrofit post-
modification but production pre-modification 11912 configuration, 
Airbus published an all operators telex (AOT) to require a one-time 
fluorescent penetrant inspection for cracks of all pre-modification 
Airbus 11912 airplanes. Airbus conducted an additional investigation 
after that AOT was published and determined the root cause of the 
cracking was the incorrect accomplishment of the instructions of a 
modification service bulletin, leading to deviation from approved 
design. This condition, if not detected and corrected, could reduce the 
structural integrity of the airplane.
    In the NPRM, the FAA proposed to require a special detailed 
inspection (geometrical inspection) of the MLG rib 5 lower flange holes 
on the left-hand wing and right-hand wing and repair if necessary, as 
specified in EASA AD 2024-0162. 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-2025-0342.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from FedEx Express and ProTech Aero 
Services Limited who supported the NPRM without change.
    The FAA received additional comments from one anonymous commenter, 
several of which are outside the scope of the NPRM. The following 
presents the relevant comments received on the NPRM and the FAA's 
response to each comment.

Request for Clarification on Remarks Section

    The commenter requested that the FAA clarify whether the exception 
in paragraph (h)(2) of the proposed AD excludes any critical safety 
information from the Remarks section of the EASA AD that should be 
considered.
    During development of the NPRM, the FAA reviewed the Remarks 
section of EASA AD 2024-0162 and determined that it does not contain 
any safety critical information. No change to this AD is necessary in 
this regard.

Request for Clarification Flexibility for Small Operators

    The commenter asked if the FAA will provide additional technical 
support or compliance flexibility to smaller carriers 
disproportionately affected by costly repair mandates.
    During development of the NPRM, the FAA determined that the 
proposed rule would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act. Further, the FAA did not receive any 
comments on the proposal from small air carriers regarding their 
ability to comply with the requirements or the economic impact. 
Therefore, the FAA does not foresee the need to provide any additional 
support or flexibility beyond what is normally provided under the FAA's 
regulatory and oversight responsibilities. No change to this AD is 
necessary in this regard.

Request for Clarification on Aircraft Converted to Cargo

    An anonymous commentator asked if the FAA will assess whether A300 
airplanes converted to cargo airplanes have different stress profiles 
that could accelerate flange cracking, and if so, whether supplementary 
inspections are needed.
    The FAA will adhere to its bilateral agreement with EASA. Should 
EASA notify the FAA that further action is necessary to address the 
unsafe condition on any Model A300 airplane, the FAA would at that time 
evaluate the need for rulemaking. No change to this AD is necessary in 
this regard.

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 NPRM. 
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 2024-0162, which specifies procedures for 
performing a one-time geometrical inspection of the spotfaces of the 
MLG rib 5 lower flange holes on the left-hand wing and right-hand wing 
to assess

[[Page 40034]]

geometric compliance to a terminating modification, including a 
spotface geometry check using ``GO/NO-GO'' gauges, and repair. 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 128 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                     Labor cost                       Parts cost     Cost per product    Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
137 work-hours x $85 per hour = $11,645............           $0              $11,645                $1,490,560
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repair 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:

2025-16-05 Airbus SAS: Amendment 39-23103; Docket No. FAA-2025-0342; 
Project Identifier MCAI-2024-00477-T.

(a) Effective Date

    This airworthiness directive (AD) is effective September 22, 
2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A300 B4-2C, A300 B4-203, 
A300 B4-603, A300 B4-605R, A300 B4-622, A300 B4-622R, and A300 F4-
605R airplanes, certificated in any category, as identified in 
European Union Aviation Safety Agency (EASA) AD 2024-0162, dated 
August 20, 2024 (EASA AD 2024-0162).

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracking of the main landing 
gear (MLG) support rib 5 lower flange on certain modified airplanes 
due to incorrect accomplishment of modification instructions. The 
FAA is issuing this AD to address such cracking, which, if not 
addressed, could result in reduced 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 2024-0162.

(h) Exceptions to EASA AD 2024-0162

    (1) Where EASA AD 2024-0162 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0162.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0162 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 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 (i) and (j)(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

[[Page 40035]]

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.

(k) Additional Information

    For more information about this AD, contact Dan Rodina, Aviation 
Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; 
phone: 206-231-3225; 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 2024-0162, 
dated August 20, 2024.
    (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 4, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-15686 Filed 8-15-25; 8:45 am]
BILLING CODE 4910-13-P

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