Rule2025-06006
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
April 8, 2025
Effective
May 13, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by an updated stress analysis on the forward (FWD) cargo door and its attachment piano hinges that revealed a risk of cracking and crack propagation on piano hinges 2 and 3, originating from opening- closing fatigue cycles of the FWD cargo door. This AD requires an inspection of the affected parts, and applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 66 (Tuesday, April 8, 2025)</title>
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[Federal Register Volume 90, Number 66 (Tuesday, April 8, 2025)]
[Rules and Regulations]
[Pages 15114-15116]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-06006]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2320; Project Identifier MCAI-2024-00268-T;
Amendment 39-23006; AD 2025-07-05]
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 A350-941 and -1041 airplanes. This AD was
prompted by an updated stress analysis on the forward (FWD) cargo door
and its attachment piano hinges that revealed a risk of cracking and
crack propagation on piano hinges 2 and 3, originating from opening-
closing fatigue cycles of the FWD cargo door. This AD requires an
inspection of the affected parts, and applicable corrective actions, as
specified in a European Union Aviation Safety Agency (EASA) AD, which
is incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective May 13, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 13,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2320; 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 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#b4f5f0c7f4d1d5c7d59ad1c1c6dbc4d59ad1c1"><span class="__cf_email__" data-cfemail="c48580b784a1a5b7a5eaa1b1b6abb4a5eaa1b1">[email protected]</span></a>; website easa.europa.eu. 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-2024-2320.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3531; email: <a href="/cdn-cgi/l/email-protection#244a45504c454a0a540a53414d43454a40644245450a434b52"><span class="__cf_email__" data-cfemail="9cf2fde8f4fdf2b2ecb2ebf9f5fbfdf2f8dcfafdfdb2fbf3ea">[email protected]</span></a>.
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 A350-941 and -1041 airplanes. The NPRM published in the Federal
Register on September 30, 2024 (89 FR 79477). The NPRM was prompted by
AD 2024-0129, dated July 5, 2024, issued by EASA, which is the
Technical Agent for the Member States of the European Union (EASA AD
2024-0129) (also referred to as the MCAI). The MCAI states an update of
the stress analysis resulted in a new definition of interface load
distribution between the FWD cargo door and the associated fuselage
piano hinges. Further investigation revealed a risk of cracking and
crack propagation on the affected parts, originating from opening-
closing fatigue cycles of the FWD cargo door. Under this condition,
door operation could cause damage to the FWD cargo door surrounding
structure and consequent reduced structural integrity of the airplane.
In the NPRM, the FAA proposed to require an inspection of the
affected parts, and applicable corrective actions, as specified in EASA
AD 2024-0129. 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-2024-2320.
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, Inc.
(Delta). The following presents the comment received on the NPRM and
the FAA's response to the comment.
[[Page 15115]]
Request To Use an Alternative Safety Harness Manufacturer Part Number
Delta requested permission to use an alternative approved safety
harness manufacturer part number (MPN) to accomplish step 5.3.B.(2) of
Airbus Alert Operators Transmission (AOT) A53P17-24 Revision 01, dated
June 26, 2024. Delta stated the AOT specifically requires safety
harness MPN 98L12003001000 for compliance. Delta stated that based on
previously approved alternative methods of compliance (AMOCs),
alternative approved safety harness MPNs provide an acceptable level of
safety during compliance with the requirements. Delta suggested
revising paragraph (h) of the proposed AD to add the statement,
``equivalent harness MPN(s) are acceptable.''
The FAA agrees to clarify. As specified in paragraph (i)(3) of this
AD, if any material referenced in EASA AD 2024-0129 contains paragraphs
that are identified as required for compliance (RC), those paragraphs
must be done to comply with this AD; any paragraphs that are not
identified as RC are recommended. The instructions in paragraph 5.3,
including step 5.3.B.(2), in the Airbus AOT referenced in EASA AD 2024-
0129 are not labeled as RC. Therefore, using the safety harness part
number specified in the Airbus AOT is not required for compliance with
this AD, and operators may use a safety harness with a different part
number provided the instructions identified as RC can be done and the
airplane can be put back in an airworthy condition. The FAA has not
revised this AD in this regard.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
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 this product. 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
EASA AD 2024-0129 specifies procedures for performing a detailed
inspection for cracks and damage (including dents, discoloration,
punctures, nicks, and scratches) of the FWD cargo door piano hinges 2
and 3, and obtaining and following instructions for repair of cracks
and damage. EASA AD 2024-0129 also specifies procedures for checking
the condition and integrity of the temporary protection system (TPS)
layer, if installed, removing any damaged TPS layer, and applying a new
layer if the TPS layer was damaged, removed, or cleaned. 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 28 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection (cargo door piano hinges) 1 work-hour x $85 per $0 $85 $2,380
and TPS layer check. hour = $85.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions 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:
2025-07-05 Airbus SAS: Amendment 39-23006; Docket No. FAA-2024-2320;
Project Identifier MCAI-2024-00268-T.
[[Page 15116]]
(a) Effective Date
This airworthiness directive (AD) is effective May 13, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A350-941 and -1041
airplanes, certificated in any category, as identified in European
Union Aviation Safety Agency (EASA) AD 2024-0129, dated July 5, 2024
(EASA AD 2024-0129).
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an updated stress analysis on the
forward (FWD) cargo door and its attachment piano hinges that
revealed a risk of cracking and crack propagation on piano hinges 2
and 3, originating from opening-closing fatigue cycles of the FWD
cargo door. The FAA is issuing this AD to address potential failure
of the piano hinges due to cracking. The unsafe condition, if not
addressed, could result in damage to the FWD cargo door surrounding
structure and consequent 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 2024-0129.
(h) Exceptions to EASA AD 2024-0129
(1) Where EASA AD 2024-0129 refers to ``16 May 2024 [the
effective date of EASA AD 2024-0098],'' this AD requires using the
effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0129 specifies ``if,
during the DET as required by paragraph (1) of this AD, any crack or
damage is detected, before next flight, contact Airbus for approved
instructions and, within the compliance time specified therein,
accomplish those instructions accordingly,'' this AD requires
replacing that text with ``if any crack or damage is detected, the
crack or damage 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.''
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0129.
(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
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, mail it to the address
identified in paragraph (j) of this AD. Information may be emailed
to: <a href="/cdn-cgi/l/email-protection#d3929e9c9093b5b2b2fdb4bca5"><span class="__cf_email__" data-cfemail="e2a3afada1a2848383cc858d94">[email protected]</span></a>. 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 (h)(2) and (i)(2) of this AD, if any material referenced
in EASA AD 2024-0129 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.
(j) Additional Information
For more information about this AD, contact Nathan Weigand,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3531; email: <a href="/cdn-cgi/l/email-protection#ddb3bca9b5bcb3f3adf3aab8b4babcb3b99dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="4a242b3e222b24643a643d2f232d2b242e0a2c2b2b642d253c">[email protected]</span></a>.
(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 2024-0129,
dated July 5, 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 <a href="/cdn-cgi/l/email-protection#94d5d0e7d4f1f5e7f5baf1e1e6fbe4f5baf1e1"><span class="__cf_email__" data-cfemail="4405003704212537256a2131362b34256a2131">[email protected]</span></a>; website easa.europa.eu. You may
find this EASA AD 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#ea8c98c48384999a8f899e838584aa848b988bc48d859c"><span class="__cf_email__" data-cfemail="8ceafea2e5e2fffce9eff8e5e3e2cce2edfeeda2ebe3fa">[email protected]</span></a>.
Issued on March 28, 2025.
Victor Wicklund,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-06006 Filed 4-7-25; 8:45 am]
BILLING CODE 4910-13-P
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