Rule2026-04967
Airworthiness Directives; Airbus Helicopters
Primary source
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Published
March 13, 2026
Effective
April 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-09-15 which applied to certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. AD 2020-09-15 required removing the removable parts of the dual hoist installation or removing the de-icing system and allows, for certain helicopters, revising the rotorcraft flight manual (RFM) for the helicopter and installing a placard as an optional method of compliance. Since the FAA issued AD 2020-09-15, analysis revealed that additional vibration level measurements are necessary. This AD retains all the requirements of AD 2020-09-15 and requires for certain helicopters repetitively measuring vibration levels in-flight, and depending on the results, performing corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 49 (Friday, March 13, 2026)</title>
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[Federal Register Volume 91, Number 49 (Friday, March 13, 2026)]
[Rules and Regulations]
[Pages 12289-12292]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-04967]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-5389; Project Identifier MCAI-2024-00716-R;
Amendment 39-23284; AD 2026-05-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-09-15
which applied to certain Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters. AD 2020-09-15 required removing the
removable parts of the dual hoist installation or removing the de-icing
system and allows, for certain helicopters, revising the rotorcraft
flight manual (RFM) for the helicopter and installing a placard as an
optional method of compliance. Since the FAA issued AD 2020-09-15,
analysis revealed that additional vibration level measurements are
necessary. This AD retains all the requirements of AD 2020-09-15 and
requires for certain helicopters repetitively measuring vibration
levels in-flight, and depending on the results, performing corrective
actions. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective April 17, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 17,
2026.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 20,
2020 (85 FR 30589, May 20, 2020).
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-5389; 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 Airbus Helicopters material identified in this AD,
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX
75052; phone: (972) 641-0000 or (800) 232-0323; fax: (972) 641-3775; or
at <a href="http://airbus.com/en/products-services/helicopters/hcare-services/airbusworld">airbus.com/en/products-services/helicopters/hcare-services/airbusworld</a>.
<bullet> 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. It is also available at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2025-5389.
FOR FURTHER INFORMATION CONTACT: Matthew Williams, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (316) 946-4134; email: <a href="/cdn-cgi/l/email-protection#c3aea2b7b7aba6b4edb7edb4aaafafaaa2aeb083a5a2a2eda4acb5"><span class="__cf_email__" data-cfemail="fb969a8f8f939e8cd58fd58c929797929a9688bb9d9a9ad59c948d">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-09-15, Amendment 39-19911 (85 FR
30589, May 20, 2020), (AD 2020-09-15). AD 2020-09-15 applied to Airbus
Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters,
equipped with a dual hoist installation and de-icing system, except
those that have Airbus Helicopters modification 0722907 installed in
production. AD 2020-09-15 required removing the removable parts of the
dual hoist installation or removing the de-icing system and allows, for
certain helicopters, revising the RFM for the helicopter and installing
a placard as an optional method of compliance. The FAA issued AD 2020-
09-15 to prevent divergent aeromechanic coupling between the helicopter
structure and rotor. The unsafe condition, if not addressed, could
generate divergent aeromechanic coupling between the helicopter
structure and the rotor, possibly resulting in mechanical failure of
structural parts and loss of control of the helicopter.
The NPRM was published in the Federal Register on December 17, 2025
(90 FR 58515). The NPRM was prompted by European Union Aviation Safety
Agency (EASA) AD 2024-0233, dated December 5, 2024 (EASA AD 2024-0233)
(also referred to as the MCAI). The MCAI was issued by EASA, which is
the Technical Agent for the Member States of the European Union. The
MCAI states it was determined that further vibration level measurements
were necessary after performing certain maintenance tasks. The MCAI
further states that EASA AD 2024-0233 is considered to be an interim
action.
In the NPRM, the FAA proposed to retain all the requirements of AD
2020-09-15 and also proposed to require repetitively measuring the
vibration level, interpreting the results, and depending on the
results, removing certain parts and further inspections. In the NPRM
the FAA also proposed to allow an alternative to removing parts by
placing a placard and revising the RFM for the helicopter.
Additionally, in the NPRM the FAA proposed to prohibit installing the
de-icing system and the dual hoist unless certain requirements are
accomplished.
In the NPRM the FAA specifies measuring the vibration levels in-
flight and revising the existing RFM for the helicopter may be
performed by the owner/operator (pilot) holding at least a private
pilot certificate and must be entered into the aircraft records showing
compliance with this action in accordance with 14 CFR 43.9(a) and
91.417(a)(2)(v). The pilot may perform these actions because they only
involve recording data in-flight and revising the existing RFM by
inserting pages, which are not considered maintenance actions.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These products have been approved by the civil aviation authority
of another country and are approved for operation
[[Page 12290]]
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 Airbus Helicopters Alert Service Bulletin ASB
AS332-04-00-0001, Issue 002, dated December 4, 2024 (ASB AS332-04-00-
0001), which specifies procedures for installing the accelerometer in
the cockpit of the helicopter, repetitively inspecting the vibration
level at 12 Hz each time a specific maintenance task is completed, and
interpreting the results. Depending on the results of this inspection,
ASB AS332-04-00-0001 specifies procedures for corrective actions, which
include changing the configuration by either removing the dual hoist
system or removing the de-icing harness and contacting Airbus
Helicopters for further instructions.
The FAA also reviewed Airbus Helicopters Emergency Alert Service
Bulletin (EASB) AS332 01.00.91, Revision 1, dated December 4, 2019
(EASB 01.00.91 Rev 1) for Model AS332C, and AS332C1 helicopters, and
EASB AS332 01.00.96, Revision 0, dated December 4, 2019 (EASB 01.00.96)
for Model AS332L and AS332L1 helicopters. EASB 01.00.91 Rev 1 specifies
procedures for removing parts of the dual hoist installation or
removing the de-icing system. EASB 01.00.96 describes procedures for
amending the RFM of Airbus Helicopters Model AS332L and AS332L1
helicopters to limit the flight envelope and the Vne and installing a
placard. EASB 01.00.96 also describes procedures for removing parts of
the dual hoist installation or removing the de-icing system. The
Director of the Federal Register approved EASB 01.00.91 Rev 1 and EASB
01.00.96 for incorporation by reference as of May 20, 2020 (85 FR
30589, May 20, 2020).
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 this AD as an interim action. If final action is
later identified, the FAA might consider further rulemaking.
Costs of Compliance
The FAA estimates that this AD affects five helicopters of U.S.
registry.
The FAA estimates the following costs to comply with this AD.
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Remove the removable parts of the 12 work-hours x $85 $0 $1,020.................... $5,100
dual hoist. per hour = $1,020
per helicopter.
Remove the de-icing system....... 12 work-hours x $85 0 $1,020.................... 5,100
per hour = $1,020
per helicopter.
Measure vibrations to include 7 work-hours x $85 0 $595 per cycle............ 2,975
interpreting results. per hour = $595.
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The FAA estimates the following costs to do any actions that would
be required based on the results of the inspection. The agency has no
way of determining the number of helicopters that might need these
repairs or replacements:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Revise the RFM.............................. 1 work-hour x $85 per hour = $0 $85
$85.
Install a placard........................... 1 work-hour x $85 per hour = 0 85
$85.
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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 has determined that 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.
[[Page 12291]]
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:
0
a. Removing Airworthiness Directive 2020-09-15, Amendment 39-19911 (85
FR 30589, May 20, 2020); and
0
b. Adding the following new airworthiness directive:
2026-05-11 Airbus Helicopters: Amendment 39-23284; Docket No. FAA-
2025-5389; Project Identifier MCAI-2024-00716-R.
(a) Effective Date
This airworthiness directive (AD) is effective April 17, 2026.
(b) Affected ADs
This AD replaces AD 2020-09-15, Amendment 39-19911 (85 FR 30589,
May 20, 2020) (AD 2020-09-15).
(c) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters, certificated in any category,
equipped with a dual hoist installation and de-icing system.
(d) Subject
Joint Aircraft System Component (JASC) Code 1810, Helicopter
vibration analysis.
(e) Unsafe Condition
This AD was prompted by a report of vibrations around the 12 Hz
frequency due to the specific helicopter configuration and
determination that additional vibration level measurements are
necessary. The FAA is issuing this AD to prevent divergent
aeromechanic coupling between the helicopter structure and rotor.
The unsafe condition, if not addressed, could result in mechanical
failure of structural parts and consequent loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For helicopters without Airbus Helicopters modification
0722907 installed, within 7 days after May 20, 2020 (the effective
date of AD 2020-09-15): Remove the removable parts of the dual hoist
installation or remove the de-icing system in accordance with the
instructions of section 3.B of Airbus Helicopters Emergency Alert
Service Bulletin (EASB) AS332 01.00.91, Revision 1, dated December
4, 2019 (EASB AS332 01.00.91 Rev 1), or Section 3.B.2 of Airbus
Helicopters EASB AS332 01.00.96, Revision 0, dated December 4, 2019
(EASB AS332 01.00.96), as applicable to the helicopter, except you
are not required to contact Airbus Helicopters.
(2) For helicopters with Airbus Helicopters modification 0722907
installed, within 110 hours time-in-service (TIS) or 30 days
whichever occurs first after the effective date of this AD and
thereafter, during the first flight after each time any of the
maintenance tasks identified in the COMPLIANCE: MANDATORY section of
Airbus Helicopters Alert Service Bulletin ASB AS332-04-00-0001,
Issue 002, dated December 4, 2024 (ASB AS332-04-00-0001) is
accomplished, perform a vibration level measurement in accordance
with paragraphs (g)(2)(i) and (ii) of this AD.
(i) With the accelerometer already installed, check the
measurement of the vibration level in-flight, at 12 Hz by following
figure 1 to paragraph (g)(2)(i) of this AD. The owner/operator
(pilot) holding at least a private pilot certificate may perform
this check and must enter compliance with these paragraphs 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.
Figure 1 to Paragraph (g)(2)(i)--Method of Measurement
[GRAPHIC] [TIFF OMITTED] TR13MR26.003
(ii) Interpret the results in accordance with the instructions
in Section 4.4 of ASB AS332-04-00-0001 except you are not required
to send any information to Airbus Helicopters. If the vibration
level between 11.7 Hz and 12.7 Hz is more than 0.08g (0.40 IPS),
before further flight, revise the helicopter configuration by
removing the dual hoist system or removing the blade de-icing
harnesses in accordance with instructions of section 4.5 through
4.5.2.1 of ASB AS332-04-00-0001.
(h) Optional Method of Compliance
For helicopters without Airbus Helicopters modification 0722907
installed: Revising the rotorcraft flight manual for your helicopter
by inserting the information specified in Appendix 4A, 4B, or 4C of
EASB AS332 01.00.96, as applicable to your helicopter model and
configuration, and installing a locally made placard on the
instrument panel, in accordance with the instructions of section
3.B.1 of EASB AS332 01.00.96, is an acceptable method for compliance
with the requirements of paragraph (g)(1) of this AD.
(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 responsible Flight
Standards 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) of this AD and
email to: <a href="/cdn-cgi/l/email-protection#3d7c70727e7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="4d0c00020e0d2b2c2c632a223b">[email protected]</span></a>.
[[Page 12292]]
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(j) Additional Information
For more information about this AD, contact Matthew Williams,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (316) 946-4134; email:
<a href="/cdn-cgi/l/email-protection#bfd2decbcbd7dac891cb91c8d6d3d3d6ded2ccffd9dede91d8d0c9"><span class="__cf_email__" data-cfemail="305d5144445855471e441e47595c5c59515d43705651511e575f46">[email protected]</span></a>.
(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 the AD specifies otherwise.
(3) The following material was approved for IBR on April 17,
2026.
(i) Airbus Helicopters Alert Service Bulletin ASB AS332-04-00-
0001, Issue 002, dated December 4, 2024.
(ii) [Reserved]
(4) The following material was approved for IBR on May 20, 2020,
(85 FR 30589, May 20, 2020).
(i) Airbus Helicopters Emergency Alert Service Bulletin AS332
01.00.91, Revision 1, dated December 4, 2019.
(ii) Airbus Helicopters Emergency Alert Service Bulletin AS332
01.00.96, Revision 0, dated December 4, 2019.
(5) For Airbus material identified in this AD, contact Airbus
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone:
(972) 641-0000 or (800) 232-0323; fax: (972) 641-3775; or at
<a href="http://airbus.com/en/products-services/helicopters/hcare-services/airbusworld">airbus.com/en/products-services/helicopters/hcare-services/airbusworld</a>.
(6) 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.
(7) 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#2d4b5f0344435e5d484e594442436d434c5f4c034a425b"><span class="__cf_email__" data-cfemail="5c3a2e7235322f2c393f283533321c323d2e3d723b332a">[email protected]</span></a>.
Issued on March 4, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-04967 Filed 3-12-26; 8:45 am]
BILLING CODE 4910-13-P
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