[Federal Register Volume 90, Number 81 (Tuesday, April 29, 2025)]
[Proposed Rules]
[Pages 17749-17751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-06776]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0628; Project Identifier MCAI-2024-00728-T]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus SAS Model A350-941 and -1041 airplanes. This
proposed AD was prompted by reports of deep spot faces on rib 9 at the
lower flange bolting with the lower spar. This proposed AD would
require a special detailed inspection for discrepancies of certain
pylon bolts, and applicable corrective actions, as specified in a
European Union Aviation Safety Agency (EASA) AD, which is proposed for
incorporation by reference (IBR). The FAA is proposing this AD to
address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 13,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0628; 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 NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For Airbus material identified in this proposed 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.
For EASA material identified in this proposed 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. It is also available at
regulations.gov under Docket No. FAA-2025-0628.
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.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-
3225; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-0628;
Project Identifier MCAI-2024-00728-T'' at the beginning of your
comments. The most helpful comments reference a specific portion of the
proposal, explain the reason for any recommended change, and include
supporting data. The FAA will consider all comments received by the
closing date and may amend this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Dan
Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone 206-231-3225; email [email protected]. Any
commentary that the FAA receives which is not specifically designated
as CBI will be placed in the public docket for this rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2024-0234, dated December 6, 2024
(EASA AD 2024-0234) (also referred to as the MCAI), to correct an
unsafe condition for certain Airbus SAS Model A350-941 and -1041
airplanes. The MCAI states deep spot faces have been detected on the
production line on rib 9 at the lower flange bolting with the lower
spar. This condition, if not detected and corrected, could lead to
reduced fatigue life, which could adversely affect the structural
integrity of the airplane. The FAA is proposing 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-2025-0628.
[[Page 17750]]
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0234 specifies procedures for a special detailed
inspection for discrepancies of the 2 pylon bolts at rib 9, left-hand
and right-hand sides, and applicable corrective actions (repair).
Discrepancies include washers that are not correctly aligned with the
nut, cracks, scratches, corrosion, damage, and missing hardware. In
addition, discrepancies include a no-go condition found after measuring
the spot face depth with a ``GO-NoGO GAUGE.'' The compliance times for
the applicable corrective actions range from before next flight to
3,000 flight cycles from completion of inspection.
The FAA reviewed Airbus Service Bulletin A350-54-P011, dated July
4, 2024. This material identifies affected airplanes specified in EASA
AD 2024-0234.
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.
FAA's Determination
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 and
material referenced above. The FAA is issuing this NPRM after
determining that the unsafe condition described previously is likely to
exist or develop in other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2024-0234 described previously, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2024-0234 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2024-0234 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2024-0234 does not mean that
operators need comply only with that section. For example, where the AD
requirement refers to ``all required actions and compliance times,''
compliance with this AD requirement is not limited to the section
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2024-
0234. Material required by EASA AD 2024-0234 for compliance will be
available at regulations.gov under Docket No. FAA-2025-0628 after the
FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 17 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs for Required Actions
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Labor cost Parts cost Cost per product Cost on U.S. operators
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8 work-hours x $85 per hour = $680................ $0 $0 $11,560
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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 proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus SAS: Docket No. FAA-2025-0628; Project Identifier MCAI-2024-
00728-T.
[[Page 17751]]
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by June 13, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A350-941 and -1041
airplanes, certificated in any category, having manufacturer serial
numbers listed in Airbus Service Bulletin A350-54-P011, dated July
4, 2024.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.
(e) Unsafe Condition
This AD was prompted by reports of deep spot faces that were
detected on the production line on rib 9 at lower flange bolting
with the lower spar. The FAA is issuing this AD to address deep spot
faces on rib 9, which if not addressed, could result in reduced
fatigue life and could adversely 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 paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2024-0234, dated December 6, 2024 (EASA AD 2024-0234).
(h) Exception to EASA AD 2024-0234
(1) Where paragraph (2) of EASA AD 2024-0234 specifies
``accomplish the corrective actions,'' this AD requires replacing
that text with ``accomplish the corrective actions, including any
inspection instructions.''
(2) Where paragraph (2) of EASA AD 2024-0234 specifies ``Where
the SB instructs to contact Airbus for approved repair instructions,
this AD requires to contact Airbus for corrective action(s)
instructions, and within the compliance time specified therein, to
accomplish those instructions accordingly,'' this AD requires
replacing that text with ``Where the SB instructs to contact Airbus
for instructions or inspections, this AD requires contacting Airbus
for instructions and inspections, as applicable, and within the
compliance time specified therein, accomplishing those instructions
accordingly; except if any cracking is found, the cracking 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
2024-0234.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2024-0234 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 DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (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 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;
telephone 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) Airbus Service Bulletin A350-54-P011, dated July 4, 2024.
(ii) European Union Aviation Safety Agency (EASA) AD 2024-0234,
dated December 6, 2024.
(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) 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.
(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 April 15, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-06776 Filed 4-28-25; 8:45 am]
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