[Federal Register Volume 90, Number 125 (Wednesday, July 2, 2025)]
[Rules and Regulations]
[Pages 28885-28889]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-12377]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-1116; Project Identifier MCAI-2024-00708-R;
Amendment 39-23071; AD 2025-13-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters Model H160-B helicopters. This AD was prompted by
occurrences of premature in-service degradation of the main rotor
swashplate assembly (swashplate) bearing. This AD requires repetitively
inspecting the swashplate bearing for the presence of grease, and
depending on the inspection results, performing corrective actions.
This AD requires performing certain operational checks, downloading and
analyzing certain data, and, depending on the results of the
operational checks, further corrective actions. This AD also requires
repetitively performing one flight under specific conditions.
Additionally, this AD requires inspecting grease on the swashplate
bearing and, depending on the inspection results, applying a certain
grease or replacing the grease. This AD allows installing certain part-
numbered swashplate bearings provided certain requirements are met. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective July 17, 2025.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 17,
2025.
The FAA must receive comments on this AD by August 18, 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-2025-1116; 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
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For European Union Aviation Safety Agency (EASA) material
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone +49 221 8999 000; email: [email protected];
website: easa.europa.eu. You may find the EASA material on the EASA
website at ad.easa.europa.eu. It is also available at regulations.gov
under Docket No. FAA-2025-1116.
You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of this
material at the FAA, call (817) 222-5110.
FOR FURTHER INFORMATION CONTACT: Aryanna Sanchez, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-4058; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2025-1116; Project
Identifier MCAI-2024-00708-R'' at the beginning of your comments. The
most helpful comments reference a specific portion of the final rule,
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 final rule 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 final rule.
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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Aryanna
Sanchez, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590. 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 2024-0229, dated December 2, 2024
(EASA AD 2024-0229) (also referred to as the MCAI) to correct an unsafe
condition on Airbus Helicopters Model H160-B helicopters. The MCAI
states multiple occurrences were reported of premature in-service
degradation of the swashplate bearing, which could have been due to the
use of the wrong grease or a mixture of incompatible greases. The MCAI
also states the health usage monitoring system (HUMS) has been
effective to detect early degradation of the swashplate bearings;
however, data shows that additional inspections and repetitive flights
are needed to ensure HUMS data is analyzed on a regular basis to detect
the degradation.
The FAA is issuing this AD to prevent premature swashplate bearing
degradation. The unsafe condition, if not addressed, could result in
failure of the swashplate bearing and consequent reduced control of the
helicopter.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-1116.
[[Page 28886]]
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2024-0229, which specifies procedures for:
repetitively inspecting the swashplate assembly and
surrounding areas for the presence of black grease, and if abnormal
grease is detected, performing corrective actions. Corrective actions
include performing a functional test of the swashplate bearing and,
depending on the results, replacing the main rotor mast assembly or
repeating the functional tests.
performing a check of the HUMS flight report and a check
of the condition of the HUMS vibration overlimit monitoring operation,
including downloading and analyzing the HUMS data of the swashplate
bearing. If a discrepancy is detected, the MCAI specifies to contact AH
[Airbus Helicopters] for corrective actions.
repetitively performing one flight under specific
conditions to verify the status of the HUMS vibration overlimit
monitoring.
identifying the type of grease that was applied during the
last swashplate bearing lubrication and if incorrect grease was applied
or if the grease is unknown, replacing it.
EASA AD 2024-0229 allows an affected swashplate bearing to be
installed on a helicopter provided the swashplate bearing is new and
has not previously been installed on a helicopter.
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
These products have been approved by the 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, it has notified the FAA of the unsafe condition described in
the MCAI referenced above. The FAA is issuing this AD after determining
that the unsafe condition described previously is likely to exist or
develop on other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in EASA AD
2024-0229, described previously, as incorporated by reference, except
for any differences identified as exceptions in the regulatory text of
this AD. See ``Differences Between this AD and the MCAI'' for a
discussion of the general differences included in this AD. The owner/
operator (pilot) holding at least a private pilot certificate may
perform the initial check of the HUMS flight report or repetitively
perform one flight to verify the status of the HUMS vibration overlimit
monitoring and must enter compliance with the applicable paragraph(s)
of the AD into the helicopter maintenance records in accordance with 14
CFR 43.9(a) and 91.417(a)(2)(v). The pilot may perform these actions
because they only involve visually checking the HUMS flight report or
performing a flight. These actions could be performed equally well by a
pilot or a mechanic. This is an exception to the FAA's standard
maintenance regulations.
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,
EASA AD 2024-0229 is incorporated by reference in this AD. This AD
requires compliance with EASA AD 2024-0229 in its entirety through that
incorporation, except for any differences identified as exceptions in
the regulatory text of this AD. Using common terms that are the same as
the heading of a particular section in EASA AD 2024-0229 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
2024-0229. Material required by EASA AD 2024-0229 for compliance will
be available at regulations.gov under Docket No. FAA-2025-1116 after
this AD is published.
Differences Between This AD and the MCAI
Where the MCAI does not specify who is authorized to download and
analyze the HUMS vibration overlimit checks, this AD requires those
actions to be accomplished by persons authorized under 14 CFR 43.3.
Where the MCAI requires accomplishing corrective actions in
accordance with the instructions of the service material, and within
the compliance times specified in the service material referenced in
the MCAI, this AD requires accomplishing the instructions or corrective
actions in accordance with a method approved by the FAA, EASA; or
Airbus Helicopters' EASA Design Organization Approval (DOA).
Where material referenced in the MCAI does not specify who may
perform a functional test or who may perform the dedicated maintenance
instructions for any other exceedance, this AD does not allow those
procedures to be performed by a pilot (owner/operator) and requires
those procedures to be accomplished by persons authorized under 14 CFR
43.3.
Where the material referenced in the MCAI allows ``operations and
maintenance'' to analyze a flight report, perform a check of the HUMS
vibration overlimit monitoring operation, download and transfer HUMS
data to Airbus Helicopters, and perform one flight to verify the status
of the HUMS vibration overlimit monitoring, this AD only allows a pilot
to perform the initial check of the HUMS flight report for the presence
of a reported event and to repetitively perform one flight to verify
the status of the HUMS vibration overlimit monitoring.
Interim Action
The FAA considers that this AD is an interim action. If final
action is later identified, the FAA might consider further rulemaking.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because several occurrences have already been reported of in-service
degradation on these swashplate bearings, which are critical to the
control of the helicopter. Additionally, the cause of the unsafe
condition is still being investigated and the reporting requirements
may be crucial to
[[Page 28887]]
understanding the root cause. In light of this, the initial action
required by this AD must be accomplished before further flight or
within 15 hours time-in-service for some helicopters, which is shorter
than the time necessary for the public to comment and for publication
of the final rule. Accordingly, notice and opportunity for prior public
comment are impracticable and contrary to the public interest pursuant
to 5 U.S.C. 553(b).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects nine helicopters of U.S.
registry. Labor costs are estimated at $85 per hour. Based on these
numbers, the FAA estimates the following costs to comply with this AD.
Visually inspecting for the presence of black grease will take 0.5
work-hours for an estimated cost of $43 per helicopter and $387 for the
U.S. fleet.
Accomplishing a check of the HUMS vibration overlimit monitoring
will take 0.25 work-hours for an estimated cost of $21 per helicopter
and $189 for the U.S. fleet.
Downloading and sending the HUMS data to Airbus Helicopters for
analysis, which is considered a reporting requirement in this AD, will
take 1 work-hour for an estimated cost of $85 per helicopter and $765
for the U.S. fleet.
Verifying helicopter records to determine which grease was applied
will take 0.25 work-hours for an estimated cost of $21 per helicopter
and $189 for the U.S. fleet.
If required, removing and replacing grease will take 5 work-hours
for an estimated cost of $425 per helicopter.
If required, accomplishing a functional test will take 1 work-hour
for an estimated cost of $85 per helicopter.
If required, replacing an affected main rotor mast will take 114
work-hours and parts will cost up to $316,023 for an estimated cost of
$325,713 per helicopter.
The FAA has no way of determining the number of work-hours it will
take to accomplish the corrective actions if HUMS support is needed.
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 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, and
(2) Will not affect intrastate aviation in Alaska.
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:
2025-13-05 Airbus Helicopters: Amendment 39-23071; Docket No. FAA-
2025-1116; Project Identifier MCAI-2024-00708-R.
(a) Effective Date
This airworthiness directive (AD) is effective July 17, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Model H160-B helicopters,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code: 6230, Main rotor
mast/swashplate.
(e) Unsafe Condition
This AD was prompted by reports of premature degradation of the
main rotor swashplate assembly (swashplate) bearing. The FAA is
issuing this AD to prevent premature swashplate bearing degradation.
The unsafe condition, if not addressed, could result in failure of
the swashplate bearing and consequent reduced control of the
helicopter.
(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
[[Page 28888]]
accordance with, European Union Aviation Safety Agency AD 2024-0229,
dated December 2, 2024 (EASA AD 2024-0229).
(h) Exceptions to EASA AD 2024-0229
(1) Where EASA AD 2024-0229 requires compliance in terms of
flight hours, this AD requires using hours time-in-service (TIS).
(2) Where EASA AD 2024-0229 refers to its effective date or
where EASA AD 2024-0229 refers to December 25, 2023 [the effective
date of EASA AD 2023-0222-E], this AD requires using the effective
date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0229 specifies ``Within
15 flight hours (FH) or before the next cleaning of the swashplate
bearing, whichever occurs first after December 25, 2023 [the
effective date of EASA AD 2023-0222-E], and, thereafter, before any
cleaning of the swashplate bearings or at intervals not exceeding 15
flight hours [FH], whichever occurs first'', this AD requires
replacing that text with ``Within 15 hours TIS or at the next 50
hour Swashplate Bearing--Functional Test or 300 hour Swashplate
Bearing--Lubrication, whichever occurs first after July 17, 2025,
the effective date of FAA AD 2025-13-05, and thereafter at intervals
not to exceed 15 hours TIS''.
(4) Where the material referenced in paragraph (3) of EASA AD
2024-0229 specifies a check of the Health Usage Monitoring System
(HUMS) flight report for reporting of MR SWASHPLATE: EXCEEDANCE in
accordance with paragraph 4.3 of the accomplishment procedure of the
ASB [Alert Service Bulletin], for this AD, the owner/operator
(pilot) holding at least a private pilot certificate may perform
only the initial check of the HUMS flight report for the presence of
a reported event and must enter compliance into the helicopter
maintenance records in accordance with 14 CFR 43.9(a) and
91.417(a)(2)(v). The record must be maintained as required by 14 CFR
91.417, 121.380, or 135.439.
Note 1 to paragraph (h)(4): The initial check of the HUMS flight
report is part of the normal flight report procedures, and the
flowcharts are not required to perform the initial check.
(5) Where paragraph (4) of EASA AD 2024-0229 specifies a check
of the HUMS vibration overlimit monitoring for reporting of MR
SWASHPLATE: UNDEFINED or MR SWASHPLATE: EXCEEDANCE in accordance
with the instructions of paragraph 4.4 of the accomplishment
procedure of the ASB, this AD requires those actions be accomplished
by persons authorized under 14 CFR 43.3 and may not be performed by
the owner/operator (pilot) holding at least a private pilot
certificate.
(6) Where paragraph (6) of EASA AD 2024-0229 specifies ``perform
one flight to verify the status of the HUMS vibration overlimit
monitoring in accordance with the instructions of paragraph 4.6 of
the accomplishment procedure of the ASB'', this AD requires
replacing that text with ``perform one flight to verify the status
of the HUMS vibration overlimit monitoring. The owner/operator
(pilot) may perform this flight and verification and must enter
compliance with this paragraph into the helicopter maintenance
records in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The
record must be maintained as required by 14 CFR 91.417, 121.380, or
135.439''.
(7) Where paragraph (7) of EASA AD 2024-0229 specifies ``Where
the ASB provides instruction to contact AH [Airbus Helicopters] HUMS
support, this AD requires to contact AH for applicable instructions
and to accomplish those instructions accordingly'', this AD requires
replacing that text with ``Accomplish the instructions or corrective
actions in accordance with a method approved by the Manager,
International Validation Branch, FAA; or EASA; or Airbus
Helicopters' EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature''.
(8) Where paragraph (8) of EASA AD 2024-0229 specifies
``check'', this AD requires replacing that text with ``test''.
(9) Where paragraph (8) of EASA AD 2024-0229 refers to any
discrepancy, for the purposes of this AD, a discrepancy (pertaining
to any functional test [check]) is identified as any abnormal relief
or hard point (ratcheting or blocking) felt during rotation at a low
constant speed, or any axial play on the installed rotating
swashplate. An abnormal relief occurs when the passage of the balls
on a spalling of the race can be felt by vibrations in the hands and
arms during the rotation. A hard point occurs when there is a
ratcheting or blocking of the ball bearing and is felt by a
sensation of braking or stopping exerting an additional force during
the rotation. Axial play is detected by manually shaking the
equipped rotating swashplate vertically from top to bottom (up and
down).
Note 2 to paragraph (h)(9): Additional information to identify
discrepancies is included in the video specified in Work Card
Swashplate Bearing--Functional test 62-32-3001, 340, dated November
4, 2022.
(10) Where paragraph (8) of EASA AD 2024-0229 specifies
``replace the main rotor mast assembly in accordance with the
instructions of the ASB'', this AD requires replacing that text with
``remove the main rotor mast assembly from service in accordance
with the instructions of the ASB and replace it with an airworthy
main rotor mast assembly''.
(11) Instead of complying with paragraph (10) of EASA AD 2024-
0229, for this AD, as of the effective date of this AD, do not
lubricate the swashplate bearing with unknown grease or any grease
other than Nyco Grease GN10.
(12) Where paragraph (11) of EASA AD 2024-0229 specifies
``Before next swashplate bearings lubrication or within 15 FH
whichever occurs first after 25 December 2023 [the effective date of
EASA AD 2023-0222-E],'', this AD requires replacing that text with
``Within 15 hours TIS or at the next 300 hour Swashplate Bearing--
Lubrication, whichever occurs first, after the effective date of AD
2025-13-05''.
(13) Where paragraph (12) of EASA AD 2024-0229 specifies ``it is
determined that the grease used during the last swashplate bearings
lubrication is not listed in CM115 type 1, or it is unknown'', this
AD requires replacing that text with ``unknown grease or any grease
other than Nyco Grease GN10 was used''.
(14) Where paragraph (14) of EASA AD 2024-0229 specifies
``Inspection, corrective actions, and greasing accomplished on a
helicopter before the effective date of this AD in accordance with
the instructions of ASB H160-B 62-32-0001 Issue 001 are acceptable
for compliance with the requirements of paragraphs (1) to (5), and
(7) to (12) of this AD, as applicable, for that helicopter'', this
AD requires replacing that text with ``Initial inspection,
corrective actions, and greasing accomplished on a helicopter before
the effective date of AD 2025-13-05 in accordance with the
instructions of ASB H160-B 62-32-0001 Issue 001, dated December 19,
2023, are acceptable for compliance with the requirements of
paragraphs (1) through (5), and (7) through (12) of EASA AD 2024-
0229, as applicable, for that helicopter''.
(15) This AD does not adopt the Remarks section of EASA AD 2024-
0229.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation 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 local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (j)(1) of
this AD and email to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local Flight Standards District Office/certificate holding
district office.
(j) Additional Information
(1) For more information about this AD, contact Aryanna Sanchez,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-4058; email:
[email protected].
(2) Airbus Helicopters material identified in this AD that is
not incorporated by reference is available at Airbus Helicopters,
2701 North Forum Drive, Grand Prairie, TX 75052; phone: (972) 641-
0000 or (800) 232-0323; fax: (972) 641-3775; or at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
(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 the AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2024-0229,
dated December 2, 2024.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: [email protected];
[[Page 28889]]
website: easa.europa.eu. You may find the EASA material on the EASA
website at ad.easa.europa.eu.
(4) You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(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 June 27, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-12377 Filed 6-30-25; 4:15 pm]
BILLING CODE 4910-13-P