[Federal Register Volume 90, Number 99 (Friday, May 23, 2025)]
[Proposed Rules]
[Pages 22028-22031]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-09095]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0910; Project Identifier MCAI-2023-01167-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)
2020-06-13, which applies to certain Airbus Helicopters Model AS332C,
AS332C1, AS332L, and AS332L1 helicopters. AD 2020-06-13 requires
determining the accumulated hours time-in-service (TIS) of certain
part-numbered main gearbox (MGB) suspension bar rear attachment
fittings (fittings) and bolts and establishes reduced life limits.
Since the FAA issued AD 2020-06-13, it was determined that modifying
the MGB suspension bar fittings link and installing improved MGB
suspension bar fitting bolts are necessary. This proposed AD would
require modifying the MGB suspension bar link, installing newly-
designed bolts, and prohibit installing certain parts. The FAA is
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this NPRM by July 7, 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-2025-0910; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For EASA material identified in this proposed 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 this material on the EASA website at ad.easa.europa.eu.
[[Page 22029]]
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
regulations.gov under Docket No. FAA-2025-0910.
FOR FURTHER INFORMATION CONTACT: Camille Seay, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5149; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-0910;
Project Identifier MCAI-2023-01167-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
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
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 2020-06-13, Amendment 39-19882 (85 FR 19080,
April 6, 2020) (AD 2020-06-13), for Airbus Helicopters Model AS332C,
AS332C1, AS332L, and AS332L1 helicopters with an MGB suspension bar
right-hand (RH) side rear fitting part number (P/N) 330A22-2702-07 and
bolt P/N 330A22-0135-20, MGB suspension bar left-hand (LH) side rear
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB
suspension bar front bolt P/N 330A22-0134-20 installed. AD 2020-06-13
was prompted by an MCAI originated by EASA, which is the Technical
Agent for the Member States of the European Union. EASA issued AD 2018-
0260, dated December 3, 2018 (EASA AD 2018-0260), to address MGB
suspension bar fittings and bolts remaining in service beyond their
fatigue life. From review of reported Model EC 225 LP data, EASA
advised that the installation of the MGB upper deck fittings of the
three MGB suspension bars (front, RH side rear, and LH side rear) could
lead to tightening torque loss on the fittings' attachment screws
(bolts). Due to design similarities, Model AS 332 C, AS 332 C1, AS 332
L, and AS 332 L1 helicopters could also be affected by the same
installation condition.
AD 2020-06-13 requires determining the total hours TIS of the MGB
suspension bar RH side and LH side rear fittings, removing these
fittings and bolts from service based on the accumulated total hours
TIS and other conditions, and thereafter removing these fittings and
bolts from service within specific intervals. AD 2020-06-13 also
requires removing the front bolts from service during each major
inspection ``G.'' The FAA issued AD 2020-06-13 to prevent failure of an
MGB attachment assembly, detachment of an MGB suspension bar, and
consequent loss of helicopter control.
Actions Since AD 2020-06-13 Was Issued
Since the FAA issued AD 2020-06-13, EASA superseded EASA AD 2018-
0260 and issued EASA AD 2023-0194, dated November 8, 2023 (EASA AD
2023-0194), to address an unsafe condition on all Airbus Helicopters
Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. EASA AD
2023-0194 stated that, following the loss of tightening torque of the
attachment screws of the upper deck fittings of the three MGB
suspension bars and previous interim action, Airbus Helicopters
developed modification (mod) 0728496 (for helicopters with machined
frames) and mod 0729200 (for helicopters with sheet metal frames),
which improve the link of the fittings of the MGB suspension bars and
include improved fitting screws. After EASA issued EASA AD 2023-0194,
EASA superseded EASA AD 2023-0194 with EASA AD 2023-0194R1 Revision 1,
dated March 19, 2025 (EASA AD 2023-0194R1) (also referred to as the
MCAI). The MCAI states that since EASA AD 2023-0194 was issued, a new
risk analysis determined the calendar time compliance time for the
modification can be extended. The MCAI further states that EASA AD
2023-0194R1 is considered to be an interim action. This condition, if
not addressed, could lead to structural failure of an MGB attachment
assembly, detachment of an MGB suspension bar, and consequent loss of
control of the helicopter.
The FAA is proposing this AD to address the unsafe condition on
these products. You may examine the MCAI in the AD docket at
regulations.gov under Docket No. FAA-2025-0910.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2023-0194R1, which specifies procedures
for determining the accumulated service life of the RH side and LH side
rear fittings of the MGB suspension bars and repetitively replacing the
RH side and LH side rear fittings and screws before exceeding
accumulated service life limits. As an alternative to the first
replacement of the RH side rear fittings and screws, if certain
conditions are met, EASA AD 2023-0194R1 allows measuring the tightening
torque, and depending on the measurement results, replacing affected
parts with serviceable parts within extended compliance times. EASA AD
2023-0194R1 also specifies procedures for replacing each MGB front
fitting screw at the next major inspection (G) and modifying the
helicopter to improve the link of the fittings of the MGB suspension
bar, which includes installing MGB fitting screws with an improved
design. EASA AD 2023-0194R1 prohibits installing certain parts on any
helicopter. Finally, EASA AD 2023-0194R1 specifies procedures for a
terminating action if the helicopter has been modified as defined in
EASA AD 2023-0194R1 and provides credit for certain previously
accomplished requirements.
This material is reasonably available because the interested
parties have access to it through their normal course
[[Page 22030]]
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 retain none of the requirements of AD 2020-
06-13. This proposed AD would require accomplishing the actions
specified in EASA AD 2023-0194R1, described previously, as incorporated
by reference, except for any differences identified as exceptions in
the regulatory text of this proposed AD. See ``Differences Between this
AD and the MCAI'' for a discussion of the general differences included
in this AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2023-0194R1 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2023-0194R1 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2023-0194R1 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 2023-
0194R1. Material referenced in EASA AD 2023-0194R1 for compliance will
be available at regulations.gov under Docket No. FAA-2025-0910 after
the FAA final rule is published.
Differences Between This Proposed AD and the MCAI
Where the MCAI allows an option of an inspection of the torque
instead of replacement of the first MGB RH side rear fitting, which
includes different replacement compliance times based on the torque
inspection results, this proposed AD would not.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect eight 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.
Determining the total hours TIS of the rear MGB fittings would take
0.5 work-hour for an estimated cost of $43 per helicopter and $344 for
the U.S. fleet.
Replacing a RH rear MGB fitting and its set of four bolts would
take 8 work-hours and parts would cost $3,589 for an estimated cost of
$4,269 per helicopter and $34,152 for the U.S. fleet, per replacement
cycle.
Replacing a set of four LH rear MGB fitting bolts would take 4
work-hours and parts would cost $100 for an estimated cost of $440 per
helicopter and $3,520 for the U.S. fleet, per replacement cycle.
Replacing a LH rear MGB fitting would take 8 work-hours and parts
would cost $3,807 for an estimated cost of $4,487 per helicopter and
$35,896 for the U.S. fleet, per replacement cycle.
Replacing a set of front MGB fitting bolts (4 bolts per set) would
take about 8 work-hours and parts would cost $98 for an estimated cost
of $778 per helicopter and $6,224 for the U.S. fleet, per replacement
cycle.
Modifying the MGB suspension bar (LH side and RH side) would take
56 work-hours and parts would cost $115,509 for an estimated cost of
$120,269 per helicopter.
The extent of corrective action that may needed if there is damage,
a crack, or insufficient clearance found while modifying the MGB
suspension bar could vary significantly from helicopter to helicopter.
The FAA has no way of determining the cost to correct or repair each
helicopter or the number of helicopters that may require repair.
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 2020-06-13, Amendment 39-19882 (85
FR 19080, April 6, 2020); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters: Docket No. FAA-2025-0910; Project Identifier
MCAI-2023-01167-R.
[[Page 22031]]
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by July 7, 2025.
(b) Affected ADs
This AD replaces AD 2020-06-13, Amendment 39-19882 (85 FR 19080,
April 6, 2020).
(c) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332C1,
AS332L, and AS332L1 helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6330, Main rotor
transmission mount.
(e) Unsafe Condition
This AD was prompted by tests and analyses performed by the
manufacturer. The FAA is issuing this AD to prevent fatigue failure
of the main gearbox (MGB) suspension bar attachment fittings and
bolts by remaining in service beyond their fatigue life. The unsafe
condition, if not addressed, could result in failure of an MGB
attachment assembly, detachment of an MGB suspension bar, and
consequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency AD 2023-
0194R1, dated March 19, 2025 (EASA AD 2023-0194R1).
Note 1 to paragraph (g): EASA AD 2023-0194R1 and Airbus
Helicopters material that is referenced in EASA AD 2023-0194R1 refer
to MGB suspension bar attachment ``bolts'' as ``screws.''
Note 2 to paragraph (g): Table No. 1 of Airbus Helicopters Alert
Service Bulletin No. AS332-53.02.13, Revision 1, dated April 5,
2024, identifies the helicopter group configurations referenced in
EASA AD 2023-0194R1.
(h) Exceptions to EASA AD 2023-0194R1
(1) Where EASA AD 2023-0194R1 requires compliance in terms of
flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2023-0194R1 refers to its effective date,
December 17, 2018 (the effective date of EASA AD 2018-0260, dated
December 3, 2018), or November 22, 2023 (the effective date of EASA
AD 2023-0194, dated November 8, 2023), this AD requires using the
effective date of this AD.
(3) Where the material referenced in EASA AD 2023-0194R1
specifies discarding parts, this AD requires removing those parts
from service.
(4) This AD does not adopt paragraphs (3) through (5) of EASA AD
2023-0194R1.
(5) Where paragraphs (2) and (6) of EASA AD 2023-0194R1 state
``paragraph 3.B.3,'' this AD requires replacing that text with
``paragraphs 3.B.2. and 3.B.3.''
(6) Where the modification ASB, as defined and referenced in
EASA AD 2023-0194R1, specifies contacting Airbus Helicopters
Technical Support if there is visible damage, a crack, or
insufficient clearance after replacing hardware, this AD requires,
before further flight, accomplishing further action in accordance
with a method approved by the Manager, International Validation
Branch, FAA; EASA; or Airbus Helicopters' EASA Design Organization
Approval (DOA). If approved by the DOA, the approval must include
the DOA-authorized signature.
(7) Where the modification ASB, as defined and referenced in
EASA AD 2023-0194R1, specifies to keep parts after removing, for
this AD, keeping these parts is not required.
(8) Where the modification ASB, as defined and referenced in
EASA AD 2023-0194R1, specifies repairing X3855 frame drilling kit
(also identified as a Guide having part number X530P8102101 and
referred to as Item ``zz''), this AD prohibits using X3855 frame
drilling kit for the actions required by this AD if there is any
damage that consists of cracks, corrosion, lengthening or
deformation of the rods or arms, or excessive wear.
(9) Sections 11 through 14 in Appendix 4.A. of the modification
ASB, as defined and referenced in EASA AD 2023-0194R1, are not
required by this AD.
(10) This AD does not adopt the Remarks section of EASA AD 2023-
0194R1.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2023-0194R1
specifies to submit information to the manufacturer, this AD does
not require these actions.
(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: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(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:
[email protected].
(2) For material identified in this AD that is not incorporated
by reference, contact Airbus Helicopters, 2701 North Forum Drive,
Grand Prairie, TX 75052; phone: (972) 641-0000 or (800) 232-0323;
fax: (972) 641-3775; website: airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
(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) European Union Aviation Safety Agency (EASA) AD 2023-0194R1,
dated March 19, 2025.
(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]; website: easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu.
(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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on May 15, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-09095 Filed 5-22-25; 8:45 am]
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