Proposed Rule2025-11697
Airworthiness Directives; Airbus Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
June 25, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2021-26-07, which applies to all Airbus Helicopters Model EC120B helicopters. AD 2021-26-07 requires performing repetitive inspections of the tail rotor (TR) hub body and, depending on the inspection results, replacing certain parts, and accomplishing further inspections. AD 2021-26-07 also requires for certain helicopters removing from service any bolt, washer, and nut installed on the TR hub body at certain life limits and replacing them with airworthy parts and accomplishing further inspections. Additionally, AD 2021-26-07 prohibits the installation of a certain part-numbered TR hub body unless certain requirements are met. Since the FAA issued AD 2021-26- 07, it was determined that modifying the link of the TR hub body and splined flange by adding red paint marks is necessary to enable the detection of any loss of tightening torque. This proposed AD would require the same repetitive inspections and corrective actions as AD 2021-26-07 and would require modification of the link of the TR hub body, which would be a terminating action for the repetitive inspections. The proposed AD would also require repetitive inspections of the red paint line added during the modification of the link of the TR hub body for alignment. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 120 (Wednesday, June 25, 2025)</title>
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[Federal Register Volume 90, Number 120 (Wednesday, June 25, 2025)]
[Proposed Rules]
[Pages 26951-26955]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-11697]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0922; Project Identifier MCAI-2024-00650-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2021-26-07, which applies to all Airbus Helicopters Model EC120B
helicopters. AD 2021-26-07 requires performing repetitive inspections
of the tail rotor (TR) hub body and, depending on the inspection
results, replacing certain parts, and accomplishing further
inspections. AD 2021-26-07 also requires for certain helicopters
removing from service any bolt, washer, and nut installed on the TR hub
body at certain life limits and replacing them with airworthy parts and
accomplishing further inspections. Additionally, AD 2021-26-07
prohibits the installation of a certain part-numbered TR hub body
unless certain requirements are met. Since the FAA issued AD 2021-26-
07, it was determined that modifying the link of the TR hub body and
splined flange by adding red paint marks is necessary to enable the
detection of any loss of tightening torque. This proposed AD would
require the same repetitive inspections and corrective actions as AD
2021-26-07 and would require modification of the link of the TR hub
body, which would be a terminating action for the repetitive
inspections. The proposed AD would also require repetitive inspections
of the red paint line added during the modification of the link of the
TR hub body for alignment. The FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments on this NPRM by August 11, 2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0922; 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:
<bullet> For Airbus Helicopters material identified in this
proposed AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand
Prairie, TX 75052; phone: (972) 641-0000 or: (800) 232-0323; fax: (972)
641-3775; website: <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-2025-0922.
FOR FURTHER INFORMATION CONTACT: Camille Seay, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5149; email: <a href="/cdn-cgi/l/email-protection#751614181c1919105b195b0610140c351314145b121a03"><span class="__cf_email__" data-cfemail="3e5d5f535752525b1052104d5b5f477e585f5f10595148">[email protected]</span></a>.
[[Page 26952]]
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-0922;
Project Identifier MCAI-2024-00650-R'' 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 the 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
<a href="http://regulations.gov">regulations.gov</a>, 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
Camille Seay, 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
The FAA issued AD 2021-26-07, Amendment 39-21866 (86 FR 72829,
December 23, 2021) (AD 2021-26-07), for Airbus Helicopters Model EC120B
helicopters. AD 2021-26-07 was prompted by European Union Aviation
Safety Agency (EASA) AD 2021-0069, dated March 11, 2021 (EASA AD 2021-
0069), issued by EASA, which is the Technical Agent for the Member
States of the European Union, to address loss of tightening torque in
the interface between the TR hub body and splined flange, which creates
the risk of crack initiation from a fretting area located on the TR hub
body and splined flange or on the TR hub body and flange bolts.
AD 2021-26-07 requires performing repetitive inspections of the TR
hub body for a crack, and depending on the inspection results, removing
the affected parts from service and inspecting the TR spline flange
and, depending on those inspection results, removing an affected
splined flange from service. AD 2021-26-07 also requires, for certain
helicopters, removing from service any bolt, washer, and nut installed
on the TR hub body that has exceeded a certain life limit, and
thereafter removing these parts from service within specific intervals
and accomplishing further inspections and corrective actions.
Additionally, AD 2021-26-07 prohibits installing a certain part-
numbered TR hub body unless certain requirements are met. The FAA
issued AD 2021-26-07 to detect cracking and fretting, which if not
addressed, could result in potential loss of the TR drive and
consequent loss of yaw control of the helicopter.
Actions Since AD 2021-26-07 Was Issued
Since the FAA issued AD 2021-26-07, EASA superseded EASA AD 2021-
0069 with EASA AD 2024-0209, dated October 28, 2024 (EASA AD 2024-0209)
(also referred to as the MCAI), to address an unsafe condition on all
Airbus Helicopters Model EC 120 B helicopters. The MCAI states that,
Airbus Helicopters developed a modification, which consists of adding a
line of red paint on each bolt and each nut of the link between the TR
hub and the splined flange. The MCAI further states that an
Airworthiness Limitations Section task was published for checking
alignment of the marks.
The FAA is proposing this AD to detect cracking and fretting of the
TR hub body, which, if not addressed, could lead to loss of the TR
drive, and consequent loss of yaw control of the helicopter.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0922.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin 05A020, Revision 3, dated September 19, 2024 (EASB 05A0020 Rev
3), which specifies procedures for repetitive inspections of the TR hub
body for cracks and the TR spline flange for cracks and fretting and
the appropriate corrective actions to include replacing the hub body
and the splined flange. EASB 05A0020 Rev 3 also excludes helicopters
that have complied with Airbus Helicopters Alert Service Bulletin
EC120-64-21-0001, Issue 001, dated September 19, 2024 (ASB EC120-64-21-
0001) from its effectivity and limits the effectivity for ``non
installed equipment or parts''.
The FAA also reviewed ASB EC120-64-21-0001, which specifies
procedures for inspecting the torque applied on the nut of the link
between the TR hub and the splined flange, and depending on the
inspection results, applying torque and replacing parts. ASB EC120-64-
21-0001 also specifies procedures for applying a red paint line on the
screw, nut, washer, TR hub, and splined flange.
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 NPRM after
determining that the unsafe condition described previously is likely to
exist or develop on other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require some of the same repetitive
inspections and corrective actions as AD 2021-26-07 and would also
require modifying the helicopter by applying torque and adding a red
paint mark on each bolt and nut on the link between the TR hub and the
splined flange after applying torque, which would be a terminating
action for the repetitive inspection requirements. The proposed AD
would also require repetitive inspections of the red paint line added
during the modification of the link of the TR hub body for alignment.
Differences Between This Proposed AD and the MCAI
EASA AD 2024-0209 allows a non-cumulative tolerance of 100 FH
[flight hours] to be applied to the compliance times to allow for
synchronization of the required inspections with other
[[Page 26953]]
maintenance tasks, whereas this proposed AD would not allow a non-
cumulative tolerance to be applied to the compliance times.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 70 helicopters of U.S. registry. Labor rates are estimated at
$85 per hour. Based on these numbers, the FAA estimates the following
costs to comply with this proposed AD.
Visually inspecting a TR hub body for a crack would take 0.25 work-
hour for an estimated cost of $22 per helicopter and $1,540 for the
U.S. fleet.
Visually inspecting a TR spline flange for corrosion, impacts,
fretting, wear, and a crack would take 0.25 work-hour for an estimated
cost of $22 per helicopter and $1,540 for the U.S. fleet.
Replacing a T/R hub body bolt, washer, and nut would take 0.5 work-
hour and parts would cost $25 (per hardware set) for an estimated cost
of $68 per helicopter.
Inspecting torque and adding a red paint line on each bolt and each
nut would take 4 work-hours for an estimated cost of $340 per
helicopter and $23,800 for the U.S. fleet.
If required, replacing a TR hub body would take 2 work-hours and
parts would cost $16,485 for an estimated cost of $16,655 per
helicopter.
If required, replacing a TR spline flange would take 0.5 work-hour
and parts would cost $2,950 for an estimated cost of $2,993 per
helicopter.
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 that the 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:
0
a. Removing Airworthiness Directive 2021-26-07, Amendment 39-21866 (86
FR 72829, December 23, 2021); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters: Docket No. FAA-2025-0922; Project Identifier
MCAI-2024-00650-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by August 11, 2025.
(b) Affected ADs
This AD replaces AD 2021-26-07, Amendment 39-21866 (86 FR 72829,
December 23, 2021).
(c) Applicability
This AD applies to Airbus Helicopters Model EC120B helicopters,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6422, Tail rotor
system.
(e) Unsafe Condition
This AD was prompted by analysis of recurrent loss of tightening
torque on several attachment bolts on the tail rotor (TR) hub body.
The FAA is issuing this AD to detect cracking and fretting of the TR
hub body. The unsafe condition, if not addressed, could lead to loss
of the TR drive, and consequent loss of yaw control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 15 hours time-in-service (TIS) or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 15 hours TIS, using a light source and
mirror, visually inspect TR hub body part number (P/N) C642A0100103
for a crack in the entire inspection area depicted in Figure 1 of
Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision
3, dated September 19, 2024. If any crack is found, before further
flight, perform the actions in paragraphs (g)(1)(i) and (ii) of this
AD.
(i) Remove the TR hub body and each bolt, washer, and nut
installed on the TR hub body from service and replace with airworthy
parts.
(ii) Inspect the TR splined flange for corrosion, impacts,
fretting, wear, and a crack in the areas identified in Figure 2 to
paragraph (g)(1)(ii) of this AD. If the condition of the part
(including corrosion, impacts, fretting, wear, or cracks) exceeds
the criteria as specified in Figure 1 to paragraph (g)(1)(ii) of
this AD, before further flight, remove the splined flange from
service and replace with an airworthy part.
Note 1 to paragraph (g)(1)(ii): You may refer to ``Detailed
Check-Splined Flange,'' Task 64-21-00, 6-5, Airbus Aircraft
Maintenance Manual (AMM), dated October 15, 2020, which pertains to
the TR splined flange inspection.
Figure 1 to Paragraph (g)(1)(ii)--Inspection Criteria for TR Splined
Flange
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Maximum damage, which causes
replacement (E1, Dia. 2, Dia.
Location as specified in Figure 2 to 3, and Dia. 4 are shown in
paragraph (g)(1)(ii) of this AD Figure 2 to paragraph
(g)(1)(ii) of this AD)
------------------------------------------------------------------------
Zone A................................. Scratch depth >0.2 mm (0.008
in.).
Crack.
E1 <2.75 mm (0.108 in.).
Dia. 3 >6.02 mm (0.2371 in.).
Dia. 2 >33.03 mm (1.3004 in.).
[[Page 26954]]
Zone B................................. Touch-up depth >0.1 mm (0.004
in.).
Crack.
Zone C................................. Crack.
Scratch depth >0.2 mm (0.008
in.).
Zone D [Dia. 4 = 14 mm <plus-minus>0.1 Touch-up depth >0.1 mm (0.004
mm (0.548; 0.555in.)]. in.).
Crack.
E1 <2.75 mm (0.108 in.).
------------------------------------------------------------------------
Figure 2 to Paragraph (g)(1)(ii)--Inspection Areas of Tail Rotor
Splined Flange
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[GRAPHIC] [TIFF OMITTED] TP25JN25.000
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BILLING CODE 4910-13-C
(2) For helicopters with 9,000 or more total hours TIS or with
unknown total hours TIS, within 15 hours TIS or 7 days, whichever
occurs first after the effective date of this AD, and thereafter at
intervals not to exceed 1,000 hours TIS, remove each bolt washer,
and nut installed on the TR hub body from service and replace with
airworthy parts and perform the actions in paragraph (g)(1)(ii) of
this AD.
(3) For helicopters with less than 9,000 total hours TIS, within
1,000 hours TIS or before accumulating 9,000 total hours TIS,
whichever occurs first after the effective date of this AD, and
thereafter at intervals not to exceed 1,000 hours TIS, remove each
bolt, washer, and nut installed on the TR hub body from service and
replace with airworthy parts and perform the actions in paragraph
(g)(1)(ii) of this AD.
(4) Within 24 months after the effective date of this AD,
inspect the torque on the nut of the TR hub body in accordance with
paragraph 4.1.2 of Airbus Helicopters Alert Service Bulletin ASB
EC120-64-21-0001, dated September 19, 2024.
(i) If the torque is not within allowable limits, before further
flight, remove the nut on the TR hub body from service and replace
it with an airworthy nut; and accomplish the actions in paragraph
(g)(4)(ii) of this AD.
(ii) If the torque is within allowable limits, before further
flight, using polyurethane paint, apply a red paint line to the bolt
and washer on the TR hub body; and apply a red paint line to the nut
and washer on the splined flange. These actions terminate the
repetitive inspections and replacements required by paragraphs
(g)(1) through (3) of this AD.
(5) Within 100 hours TIS or 12 months, whichever occurs first
after the action required in paragraph (g)(4)(ii) of this AD, and
thereafter at intervals not to exceed 100 hours TIS or 12 months,
whichever occurs first, inspect the red paint line for alignment. If
the red paint line is misaligned, before further flight, perform the
actions as specified in paragraphs (g)(4)(i) of this AD.
(h) Parts Installation Limitations
As of the effective date of this AD, do not install on any
helicopter a TR hub body P/N C642A0100103 or a splined flange unless
the part is new (zero hours TIS) or has passed the inspection
requirements required by paragraph (g)(1) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the initial instance of the
actions required by paragraphs (g)(1) through (3) of this AD, if
those actions were performed before the effective date of this AD in
accordance with Airbus Helicopters Emergency Alert Service Bulletin
05A020 Revision 0, dated October 29, 2019; Revision 1, dated
November 8, 2019; or Revision 2, dated February 8, 2021.
(j) 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 (k)(1) of this AD
and email to: <a href="/cdn-cgi/l/email-protection#bafbf7f5f9fadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="57161a18141731363679303821">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office. The following provisions
also apply to this AD.
(k) Additional Information
(1) For more information about this AD, contact Camille Seay,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5149; email:
<a href="/cdn-cgi/l/email-protection#a6c5c7cbcfcacac388ca88d5c3c7dfe6c0c7c788c1c9d0"><span class="__cf_email__" data-cfemail="086b69656164646d2664267b6d6971486e6969266f677e">[email protected]</span></a>.
(2) For Airbus Helicopters material identified in this AD that
is not incorporated by reference, can be found at the contact
information identified in paragraph (m)(3) of this AD.
(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 the AD specifies otherwise.
(i) Airbus Helicopters Emergency Alert Service Bulletin 05A020,
Revision 3, dated September 19, 2024.
(ii) Airbus Helicopters Alert Service Bulletin EC120-64-21-0001,
dated September 19, 2024.
(3) 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; website: <a href="http://airbus.com/en/products-services/helicopters/hcare-services/airbusworld">airbus.com/en/products-services/helicopters/hcare-services/airbusworld</a>.
(4) You may view this material at 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 <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#5036227e393e2320353324393f3e103e3122317e373f26"><span class="__cf_email__" data-cfemail="e98f9bc780879a998c8a9d808687a987889b88c78e869f">[email protected]</span></a>.
Issued on June 20, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-11697 Filed 6-24-25; 8:45 am]
BILLING CODE 4910-13-P
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