Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 90, Number 51 (Tuesday, March 18, 2025)]
[Rules and Regulations]
[Pages 12449-12452]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-04334]



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Federal Register / Vol. 90, No. 51 / Tuesday, March 18, 2025 / Rules 
and Regulations

[[Page 12449]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1701; Project Identifier MCAI-2024-00153-T; 
Amendment 39-22986; AD 2025-05-14]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted 
by a report indicating that the thrust reverser and pylon thermal 
blankets were found damaged due to air leaking from the pre-cooler 
exchanger (PCE). This AD requires repetitively testing the PCE for air 
leaks and reporting the results, and, depending on findings, inspecting 
the thermal blankets for damage and replacing the PCE, 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 [INSERT DATE 35 DAYS AFTER DATE OF 
PUBLICATION IN THE FEDERAL REGISTER].
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 22, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1701; 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 [email protected]; 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 regulations.gov under 
Docket No. FAA-2024-1701.

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 all Airbus SAS Model 
A350-941 and A350-1041 airplanes. The NPRM published in the Federal 
Register on July 1, 2024 (89 FR 54393). The NPRM was prompted by AD 
2024-0058R1, dated April 16, 2024, issued by EASA, which is the 
Technical Agent for the Member States of the European Union. EASA AD 
2024-0058R1 stated that during a maintenance inspection, thrust 
reverser and pylon thermal blankets were found damaged due to air 
leaking from the PCE.
    In the NPRM, the FAA proposed to require repetitively testing the 
PCE for air leaks and reporting the results, and, depending on 
findings, inspecting the thermal blankets for damage and replacing the 
PCE.
    Since the NPRM was issued, EASA issued AD 2024-0058R2, dated 
October 4, 2024 (EASA AD 2024-0058R2) (also referred to as the MCAI). 
EASA AD 2024-0058R2 adds guidance regarding updated inspection 
procedures with instructions for additional inspections that can be 
accomplished before contacting Airbus. EASA AD 2024-0058R2 retains all 
requirements of EASA AD 2024-0058R1 and does not introduce any new 
requirements.
    The FAA is issuing this AD to address damage to thermal blankets 
that, if combined with an independent event of engine fire, could lead 
to a temporary uncontrolled fire.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2024-1701.

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 additional comments from Delta Airlines (Delta). 
The following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request To Clarify Conflicting Compliance Time

    Delta stated that EASA AD 2024-0058R1 and Airbus Alert Operator's 
Transmission (AOT) A36P010-23, Revision 01, dated April 17, 2024, have 
conflicting compliance times for the next leak test requirement after 
initial testing. Delta requested clarification of the compliance time 
for the PCE repetitive leak tests.
    The FAA agrees to clarify. EASA had previously responded to a 
similar question in the Comment Response Document for EASA Proposed AD 
(PAD) 2024-0058. In that document, EASA confirmed that the first leak 
test must be accomplished before 5,500 flight cycles since new, which 
serves as the initial starting point for subsequent flight-cycle 
intervals. Thereafter, all subsequent inspections must occur at 
intervals not greater than 100 flight cycles. The FAA notes that if an 
operator conducts the first leak test at, for example, 5,400 total 
flight cycles, then the next leak test must occur before 5,500 total 
flight cycles (i.e., an interval not to exceed 100 flight cycles since 
the previous leak test). However, if the operator decides to perform 
the leak test at, for example, 4,500 total flight cycles, then the next 
leak test must be performed before 4,600 total flight cycles. The FAA 
has not changed this AD in this regard.

[[Page 12450]]

Request To Revise Initial Compliance Time

    Delta stated that Airbus has recommended not to perform the PCE 
leak test earlier than 100 flight cycles before reaching the 5,500-
flight-cycle threshold, due to the availability of spare parts. The FAA 
infers that Delta is requesting the compliance time be revised to 
specify that the initial leak test should not be accomplished prior to 
the accumulation of 5,400 flight cycles on the PCE.
    The FAA does not agree to change this compliance time. The FAA 
notes that operators may choose to complete the initial leak test at 
any point before the 5,500-flight cycle threshold, including several 
flight cycles before that threshold. Additionally, in developing an 
appropriate compliance time for this action, the FAA considered the 
recommendations of EASA, the urgency associated with the subject unsafe 
condition, the availability of required parts, and the practical aspect 
of accomplishing the required actions. However, under the provisions of 
paragraph (i)(1) of this AD, the FAA will consider requests for 
approval of an extension of the compliance time if sufficient data are 
submitted to substantiate that the new compliance time would provide an 
acceptable level of safety. The FAA has not changed this AD in this 
regard.

Request To Limit Reporting Requirement

    Delta requested that paragraph (h) of the proposed AD be revised to 
exclude the requirement to contact Airbus and provide pictures of PCEs 
information, as specified in Airbus AOT A36P010-23, Revision 01, dated 
April 17, 2024. Delta stated that operators should not be mandated to 
provide pictures of an affected unit's cold path and smart aircraft 
condition monitoring system recorder (SAR017) data from flights because 
use of this information would not directly impact safety. Delta 
expressed concern over the risk of non-compliance with the proposed AD 
if they were unable to obtain SAR017 data from the next flight after 
PCE replacement. Delta stated that Airbus uses reporting for safety 
condition investigations and software development. Delta also stated 
that Airbus indicated that any SAR017 data of any flight after PCE 
replacement is acceptable, when SAR017 data is available.
    The FAA disagrees with removing the reporting requirement but does 
agree to extend the compliance time for reporting SAR017 data. The 
reporting requirement is intended to provide the original equipment 
manufacturer (OEM) with information to determine the root cause of the 
unsafe condition identified in this AD. Furthermore, the OEM and EASA 
will review the inspection results, and other corrective actions may 
result from the reported data. Although the SAR017 data will be helpful 
for the OEM and EASA to determine if future action is needed, reporting 
that data is not an immediate or urgent requirement. Therefore, in 
consideration of Delta's comment, the FAA has revised the reporting 
requirement so that the SAR017 data is due 6 months after the 
completion of the applicable actions in this AD.

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, 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

    The FAA reviewed EASA AD 2024-0058R2, dated October 4, 2024. This 
material specifies procedures for performing repetitive air leak tests 
of a certain PCE and reporting the results. If a leak is detected, EASA 
AD 2024-0058R2 specifies to replace the PCE and visually inspect the 
thrust reverser and pylon thermal blankets and replace if damaged. EASA 
AD 2024-0058R2 also requires performing an air leak test on any newly 
installed PCE. EASA AD 2024-0058R2 also limits the installation of 
affected PCEs.
    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.

Interim Action

    The FAA considers that this AD is an interim action. If final 
action is later identified, the FAA might consider further rulemaking 
then.

Costs of Compliance

    The FAA estimates that this AD affects 32 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
                        Labor cost                            Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255.......................              $0                 $255           $8,160
----------------------------------------------------------------------------------------------------------------


                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                Labor cost                          Parts cost                       Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 24 work-hours x $85 per hour = Up    Up to $18,844...............  Up to $20,884.
 to $2,040.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to take 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the

[[Page 12451]]

data needed, and completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden, to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

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(f), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2025-05-14 Airbus SAS: Amendment 39-22986; Docket No. FAA-2024-1701; 
Project Identifier MCAI-2024-00153-T.

(a) Effective Date

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

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A350-941 and A350-1041 
airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report indicating that the thrust 
reverser and pylon thermal blankets were found damaged due to air 
leaking from the pre-cooler exchanger (PCE). The FAA is issuing this 
AD to address the PCE leaking air. The unsafe condition, if not 
addressed, could result in thermal blanket damage that, if combined 
with an independent event of engine fire, could lead to a temporary 
uncontrolled fire.

(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, European Union Aviation Safety Agency (EASA) AD 
2024-0058R2, dated October 4, 2024 (EASA AD 2024-0058R2).

(h) Exceptions to EASA AD 2024-0058R2

    (1) Where EASA AD 2024-0058R2 refers to March 11, 2024 [the 
effective date of the original issue of this [EASA] AD], this AD 
requires using the effective date of this AD.
    (2) Where paragraph (4) of EASA AD 2024-0058R2 specifies if 
``any discrepancy, as defined in the AOT, is identified, before next 
flight, contact Airbus for approved repair instructions and 
accomplish those instructions accordingly,'' this AD requires 
replacing that text with ``any discrepancy is detected, the 
discrepancy 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) Paragraph (6) of EASA AD 2024-0058R2 specifies to report air 
leak test results to Airbus within a certain compliance time. For 
this AD, report test results at the applicable times specified in 
paragraphs (h)(3)(i) and (ii) of this AD.
    (i) Report test results, except smart aircraft condition 
monitoring system recorder (SAR017) data, at the applicable time 
specified in paragraph (h)(3)(i)(A) or (B) of this AD.
    (A) If the test was done on or after the effective date of this 
AD: Submit the report within 30 days after the test.
    (B) If the test was done before the effective date of this AD: 
Submit the report within 30 days after the effective date of this 
AD.
    (ii) Report SAR017 data at the applicable time specified in 
paragraph (h)(3)(ii)(A) or (B) of this AD.
    (A) If the test was done on or after the effective date of this 
AD: Submit the SAR017 data within 6 months after the completion of 
each air leak test and applicable corrective actions required by 
this AD.
    (B) If the test was done before the effective date of this AD: 
Submit the SAR017 data within 6 months after the effective date of 
this AD.
    (4) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0058R2.

(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: [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 (i)(2) of this AD, if any material referenced in EASA AD 
2024-0058R2 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

[[Page 12452]]

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 Dan Rodina, Aviation 
Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; 
phone: 206-231-3225; email: [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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 2024-0058R2, 
dated October 4, 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]; website easa.europa.eu. You may 
find this material on the EASA website ad.easa.europa.eu.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th 
Street, 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 March 6, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-04334 Filed 3-17-25; 8:45 am]
BILLING CODE 4910-13-P

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