[Federal Register Volume 90, Number 233 (Monday, December 8, 2025)]
[Rules and Regulations]
[Pages 56673-56677]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-22218]
[[Page 56673]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-1736; Project Identifier MCAI-2024-00435-R;
Amendment 39-23190; AD 2025-23-07]
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) 2020-06-
12, which applied to certain Airbus Helicopters Model AS 332L2 and EC
225LP helicopters. AD 2020-06-12 required determining the accumulated
hours time-in-service (TIS) of certain part-numbered main gearbox (MGB)
suspension bar attachment bolts (bolt) and certain part-numbered MGB
suspension bar attachment fittings (fitting), applying a life limit
add-on factor, and inspecting the torque of certain MGB suspension bar
attachment nuts (nuts). Since the FAA issued AD 2020-06-12, the
manufacturer developed a design improvement, and the FAA determined
that modifying the helicopter is necessary. This AD retains the actions
required by AD 2020-06-12 and requires the modification of the MGB
suspension bar, inspection of the torque, and corrective actions. This
AD also allows credit for the initial service life calculations if
certain requirements are met and prohibits installing a certain bolt
after the modification is accomplished on any helicopter. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 12, 2026.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 12,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-1736; 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:
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: airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
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-2025-1736.
FOR FURTHER INFORMATION CONTACT: William McCully, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (781) 238-7244; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-06-12, Amendment 39-19881 (85 FR
19077, April 6, 2020) (AD 2020-06-12). AD 2020-06-12 applied to Airbus
Helicopters Model AS 332L2 and EC 225LP helicopters with a MGB
suspension bar front bolt part number (P/N) 332A22-1613-21 or 332A22-
1613-20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB
suspension bar front fitting P/N 332A22-1623-01, MGB suspension bar
rear left-hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB
suspension bar rear right-hand fitting P/N 332A22-1624-03 or 332A22-
1624-05 installed. AD 2020-06-12 required determining the accumulated
hours TIS of the affected bolts and fittings, applying a life limit
add-on factor, and inspecting the torque of the MGB suspension bar
attachment nuts. The FAA issued AD 2020-06-12 to address MGB suspension
bar bolts and fittings remaining in service beyond their fatigue life
and loose MGB suspension bar bolts and fittings, which could result in
structural failure of the MGB suspension bar and loss of helicopter
control.
The NPRM was published in the Federal Register on August 19, 2025
(90 FR 40262). The NPRM was prompted by a series of ADs related to this
unsafe condition issued by EASA, which is the Technical Agent for the
Member States of the European Union. EASA AD 2022-0021, dated February
1, 2022 (EASA AD 2022-0021), superseded EASA AD 2017-0189 due to Airbus
Helicopters developing a design improvement consisting of installing
new links on the fittings of the MGB suspension bars through
modifications 0728521, 0728904, 0728496 and 0729044. EASA AD 2022-0021
introduced new service life limits (SLL) for certain post-modification
parts and a new tightening torque check.
EASA AD 2022-0021 was subsequently superseded by EASA AD 2023-0147,
dated July 19, 2023 (EASA AD 2023-0147), after EASA determined that,
for helicopters modified with the new links on the fittings of the MGB
suspension bars using earlier revisions of the service information,
installing shims on the rear cooling rails of the MGB compartment was
necessary. EASA revised AD 2023-0147 and issued EASA AD 2023-0147R1,
dated March 12, 2025 (EASA AD 2023-0147R1) (also referred to as ``the
MCAI'') to address a difficulty with the installation of modification
kits for EC 225LP helicopters.
In the NPRM, the FAA proposed to retain the actions of AD 2020-06-
12, to include, using updated service information; determining the
accumulated hours TIS of certain part-numbered bolts and certain part-
numbered fittings; applying a life limit add-on penalty factor;
removing any bolt that has reached or exceeded its life limit;
inspecting the torque of certain nuts and, depending on the inspection,
removing the bolt and nut from service. The NPRM also proposed to
require modification of the MGB suspension bar, additional life limit
calculations, a tightening torque inspection with new torque values,
and removal and replacement of certain affected parts. Modification of
the MGB suspension bar is considered terminating action for the
proposed life limit calculations if certain requirements are met. The
NPRM also proposed to prohibit installing a certain bolt after the
modification is accomplished on any helicopter.
The FAA is issuing this AD to prevent MGB suspension bar attachment
fittings and bolts remaining in service beyond their fatigue life. The
unsafe condition, if not addressed, could result in structural failure
of an MGB attachment assembly, detachment of an MGB suspension bar, and
consequent loss of control of the helicopter.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-1736.
Comments
The FAA received a comment from one individual who requested more
information about the bolts. The
[[Page 56674]]
following presents the comment received on the NPRM and the FAA's
response to the comment.
Request for Additional Information
The individual commenter requested additional information on the
differences between the new MGB suspension bar rear bolts and the
previous MGB suspension bar front bolts. The commenter acknowledges the
affected bolts design may have been improved by installing new links on
the fittings of the MGB suspension bars but inquired as to how Airbus
Helicopters has ensured that these new bolts have a longer and safer
life span.
The FAA infers the commenter is requesting more detailed
information regarding the differences between the new and old MGB
suspension bar rear bolts, as well as the measures Airbus Helicopters
has implemented to ensure the improved performance of the new bolt.
Although the FAA does not have specific information on the differences
between the bolts and Airbus Helicopters manufacturing requirements,
the FAA worked with the State of Design (EASA) to assure that the
improved bolts are addressing the unsafe condition. The FAA has not
changed this AD as a result of this comment.
Conclusion
These products have been approved by the civil 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, 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 Emergency Alert Service
Bulletin (EASB) No. 01.00.86, Revision 4, dated January 6, 2022, for
Model AS 332L2 helicopters and Airbus Helicopters EASB No. 04A013,
Revision 4, dated January 6, 2022, for Model EC 225LP helicopters. This
material specifies procedures for applying an add-on factor to the
flying hours logged by the pins (bolts) and fittings and replacing them
if the SLL is exceeded.
The FAA also reviewed Airbus Helicopters Alert Service Bulletin
(ASB) No. AS332-53.02.03, Revision 2, dated June 15, 2023, for Model AS
332LP helicopters and Airbus Helicopters ASB No. EC225-53A065, Revision
4, dated May 28, 2024, for Model EC 225LP helicopters. This material
specifies procedures to install new links on the attachment brackets of
the MGB suspension bars and corresponds to Airbus Helicopters
modification 0728496, 0728521, 0728904, and 0729044.
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.
Differences Between This AD and the MCAI
The MCAI allows a 150-hour extension to the life limit of a fitting
for Model AS 332L2 helicopters if a dye-penetrant inspection is
performed on the fitting and no cracks are found. This AD does not
allow that option.
For Model AS 332L2 helicopters, the MCAI requires replacing bolts
installed with an incorrect torque value applied before the effective
date of the MCAI. This AD requires inspecting the torque of each nut
instead, and depending on the outcome, removing the nut and its bolt
from service.
The MCAI refers to the front and rear attachment bolts as ``pins,''
whereas this AD does not.
Costs of Compliance
The FAA estimates that this AD affects 30 helicopters (2 Model AS
332L2 helicopters and 28 Model EC 225LP helicopters) of U.S. registry.
The FAA estimates the following costs to comply with this AD. Labor
costs are estimated at $85 per hour.
For Model AS 332L2 Helicopters Only
Determining the adjusted life limit for the fittings takes 0.5
work-hour for an estimated cost of $43 per helicopter and $86 for the
U.S. fleet.
If required, replacing a fitting (including associated hardware)
and applying torque takes 8 work-hours and parts cost $7,000 for an
estimated cost of $7,680 per helicopter.
For All Applicable Helicopters
Determining the adjusted life limit for the bolts takes 0.5 work-
hour for an estimated cost of $43 per helicopter and $1,290 for the
U.S. fleet.
If required, replacing a bolt (including associated hardware) takes
4 work-hours and parts cost about $89 for an estimated cost of $429 per
bolt.
Modifying each MGB suspension bar takes up to 40 work-hours and
parts cost up to $54,445 for an estimated cost of up to $57,845
(depending on helicopter configuration) per modification (up to four
modifications per helicopter).
Performing a tightening torque inspection takes 4 hours for an
estimated cost of $340 per inspection.
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.
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:
[[Page 56675]]
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 2020-06-12, Amendment 39-19881 (85
FR 19077, April 6, 2020); and
0
b. Adding the following new airworthiness directive:
2025-23-07 Airbus Helicopters: Amendment 39-23190; Docket No. FAA-
2025-1736; Project Identifier MCAI-2024-00435-R.
(a) Effective Date
This airworthiness directive (AD) is effective January 12, 2026.
(b) Affected ADs
This AD replaces AD 2020-06-12, Amendment 39-19881 (85 FR 19077,
April 6, 2020).
(c) Applicability
This AD applies to Airbus Helicopters, certificated in any
category, identified in paragraphs (c)(1) and (2) of this AD.
(1) Model AS 332L2 helicopters with a main gearbox (MGB)
suspension bar front attachment bolt part number (P/N) 332A22-1613-
20 or 332A22-1613-21, MGB suspension bar rear attachment bolt P/N
332A22-1614-20, MGB suspension bar front attachment fitting P/N
332A22-1623-01, MGB suspension bar rear left-hand attachment fitting
P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar rear
right-hand attachment fitting P/N 332A22-1624-03 or 332A22-1624-05
installed.
(2) Model EC 225LP helicopters with MGB suspension bar front
attachment bolt P/N 332A22-1613-21 or MGB suspension bar rear
attachment bolt P/N 332A22-1614-20 installed.
Note 1 to paragraph (c): Airbus Helicopters refers to MGB
suspension bar attachment bolts as ``pins.''
(d) Subject
Joint Aircraft System Component (JASC) Code 6330, Main Rotor
Transmission Mount.
(e) Unsafe Condition
This AD was prompted by a report of torque loss on a MGB
suspension bar attachment bolt (bolt). The FAA is issuing this AD to
prevent MGB suspension bar attachment fittings (fitting) and bolts
remaining in service beyond their fatigue life. The unsafe
condition, if not addressed, could result in structural 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) Required Actions for Bolts
For helicopters identified in paragraphs (c)(1) and (2) of this
AD without Airbus Helicopters modifications 0728521, 0728904,
0728496, and 0729044 installed, within 30 hours time-in-service
(TIS) after the effective date of this AD, review records to
determine the total hours TIS of each bolt.
(1) Determine the life limit of each bolt by applying its total
hours TIS by the add-on factor listed in Table No. 1 of Airbus
Helicopters Emergency Alert Service Bulletin (EASB) No. 01.00.86,
Revision 4, dated January 6, 2022 (EASB 01.00.86 Rev 4), or Airbus
Helicopters EASB No. 04A013, Revision 4, dated January 6, 2022, as
applicable to your model helicopter.
(i) Before further flight, remove from service any bolt that has
reached or exceeded its life limit, and remove its associated MGB
suspension bar attachment nut (nut) and cotter pins from service.
Remove the associated convex and concave washers. Thereafter, before
each flight, continue to calculate and record the life limit of each
bolt on its component history card or equivalent record by applying
the add-on factor each time the helicopter accumulates hours TIS and
remove from service any bolt before reaching its life limit, along
with its associated nut and cotter pins. Remove its associated
convex and concave washers.
(ii) For each bolt that has not exceeded its life limit, before
each flight, continue to calculate and record the life limit on its
component history card or equivalent record by applying the add-on
factor each time the helicopter accumulates hours TIS and remove
from service any bolt before reaching its life limit, along with its
associated nut and cotter pins. Remove the associated convex and
concave washers.
(2) Before further flight, if any nut, bolt, or cotter pin was
removed from service as a result of the actions in paragraph (g)(1)
of this AD, replace those parts with airworthy parts, and install
new (never installed) convex and concave washers or reinstall the
convex and concave washers that were removed (if washers are
airworthy). Torque each newly-installed nut to the minimum allowable
torque value of: 735-840 lbf. in (8.3 daN.m to 9.5 daN.m) on the
front nuts of the fittings, and 496-566 lbf. in (5.6 daN.m to 6.4
daN.m) on the rear nuts of the fittings.
(h) Required Actions for Fittings
For helicopters identified in paragraph (c)(1) of this AD
without Airbus Helicopters modification 0728521, 0728904, 0728496,
and 0729044 installed, within 30 hours TIS after the effective date
of this AD, review records to determine the total hours TIS of each
fitting.
(1) Determine the life limit of each fitting by applying its
total hours TIS by the add-on factor listed in Table No. 1 of EASB
01.00.86 Rev 4.
(i) Before further flight, remove from service any fitting that
has reached or exceeded its life limit, and remove its associated
nuts, and cotter pins from service. Remove its associated convex and
concave washers and bolts. Thereafter, before each flight, continue
to calculate and record the life limit of each fitting on its
component history card or equivalent record by applying the add-on
factor each time the helicopter accumulates hours TIS and remove
from service any fitting before reaching its life limit, along with
its associated, nuts, and cotter pins. Remove its associated convex
and concave washers and bolt.
(ii) For each fitting that has not exceeded its life limit,
before each flight, continue to calculate and record the life limit
of each fitting on its component history card or equivalent record
by applying the add-on factor each time the helicopter accumulates
hours TIS and remove from service any fitting before reaching its
life limit, along with its associated, nuts and cotter pins from
service. Remove its associated bolts, convex and concave washers.
(2) Before further flight, if any fitting or its associated nut,
or cotter pin was removed from service as a result of the actions in
paragraph (h)(1) of this AD, replace those parts with airworthy
parts, and install new (never installed) convex and concave washers
and bolt or reinstall the convex and concave washers and bolt that
were removed (if the washers and bolt are airworthy). Torque each
newly-installed nut using the allowable torque value in paragraph
(g)(2) of this AD.
(i) Required Actions for Torque Values
For helicopters identified in paragraph (c)(1) of this AD
without Airbus Helicopters modification 0728521, 0728904, 0728496,
and 0729044 installed, within 150 hours TIS (without the add-on
factor) after the effective date of this AD, inspect the torque of
each nut.
(1) If the torque on any nut is higher than the maximum
allowable torque stated in paragraph (g)(2) of this AD, before
further flight, remove the nut, its associated bolt, and its cotter
pins from service.
(2) If the torque on any nut is lower than the minimum allowable
torque value stated in paragraph (g)(2) of this AD, before further
flight, tighten the nut to the allowable torque stated in paragraph
(g)(2) of this AD.
(3) Within 150 hours TIS (without the add-on factor), remove
from service any nut its associated bolt, and its cotter pins that
were tightened as required by paragraph (i)(2) of this AD, and
torque each newly-installed nut using the allowable torque value in
paragraph (g)(2) of this AD.
(j) Required Actions for Links
(1) For helicopters identified in paragraph (c)(1) of this AD
without Airbus Helicopters modification 0728521, 0728904, 0728496,
and 0729044 installed, within 825 hours TIS or 27 months after the
effective date of this AD, whichever occurs first, modify the
helicopter by installing attachment bracket links for the MGB
suspension bars in accordance with the Accomplishment Instructions,
paragraphs 3.B.2.a through 3.B.3.i., of Airbus Helicopters Alert
Service Bulletin (ASB) No. AS332-53.02.03, Revision 2, dated June
15, 2023 (ASB AS332-53.02.03 Rev 2), except as provided in
paragraphs (j)(1)(i) through (ix) of this AD.
Note 2 to the introductory text of paragraph (j)(1): Airbus
refers to the installation of the attachment bracket links
[[Page 56676]]
for the MGB suspension bar as modification 0728496, 0728521,
0728904, and 0729044.
(i) Instead of discarding parts, you must remove those parts
from service.
(ii) Where ASB AS332-53.02.03 Rev 2 uses the term check, this AD
requires doing an inspection.
(iii) You are not required to define or record the thickness of
the peel shims.
(iv) Instead of contacting Airbus Helicopters if there is damage
after removing corrosion, this AD requires that you remove the
affected part from service before further flight.
(v) Instead of contacting Airbus Helicopters if there are any
cracks on the frames at the attachment bracket fixations, this AD
requires that you remove the affected part from service before
further flight.
(vi) For purposes of this AD, ``correctly stacked'' as used in
ASB AS332-53.02.03 Rev 2 means the concave washers are installed
with the flat side towards the front bracket, and the convex washers
are installed with the flat side towards the nuts.
(vii) For purposes of this AD, ``correctly engaged'' as used in
ASB AS332-53.02.03 Rev 2 means the centering pin is engaged on the
front plate.
(viii) Instead of contacting Airbus Helicopters if the clearance
of J1 or J2 is less than 0.5 mm (0.0196 in) after inspecting the new
links of the rear brackets, you must take corrective action until
the clearance is at least 0.5 mm using a method approved by the
Manager, General Aviation & Rotorcraft Section, International
Validation Branch, FAA; or European Union Aviation Safety Agency
(EASA); or Airbus Helicopters EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
(ix) For the purposes of this AD, new as used in ASB AS332-
53.02.03 Rev 2 means the part has never been installed on a
helicopter.
(2) For helicopters identified in paragraph (c)(2) of this AD
without Airbus Helicopters modification 0728521, 0728904, 0728496,
and 0729044 installed, within 1,320 hours TIS or 40 months after the
effective date of this AD, whichever occurs first, modify the
helicopter by installing bracket links for the MGB suspension bars
in accordance with the Accomplishment Instructions, paragraphs
3.B.2. through 3.B.3.i, of Airbus Helicopters ASB No. EC225-53A065,
Revision 4, dated May 28, 2024 (ASB EC225-53A065 Rev 4), except as
provided in paragraphs (j)(2)(i) through (ix) of this AD.
(i) Instead of discarding parts, you must remove those parts
from service.
(ii) Where ASB EC225-53A065 Rev 4 uses the term check, this AD
requires doing an inspection.
(iii) You are not required to define or record the thickness of
the peel shims.
(iv) Instead of contacting Airbus Helicopters if there is damage
after removing corrosion, this AD requires that you remove the
affected part from service before further flight.
(v) Instead of contacting Airbus Helicopters if there are any
cracks on the frames at the attachment bracket fixations, this AD
requires that you remove the affected part from service before
further flight.
(vi) For the purposes of this AD, ``correctly stacked'' as used
in ASB EC225-53A065 Rev 4 means the concave washers are installed
with the flat side towards the bracket, and the convex washers are
installed with the flat side towards the nuts.
(vii) For purposes of this AD, ``correctly engaged'' as used in
ASB EC225-53A065 Rev 4 means the centering pin is engaged on the
front plate.
(viii) Instead of contacting Airbus Helicopters if the clearance
of J1 or J2 is less than 0.5 mm (0.0196 in) after inspecting the new
links of the rear brackets, you must take corrective action until
the clearance is at least 0.5 mm using a method approved by the
Manager, General Aviation & Rotorcraft Section, 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.
(ix) Where ASB EC225-53A065 Rev 4 uses the phrase ``if
necessary'', this AD requires replacing that text with ``if
applicable''.
(3) For helicopters identified in paragraphs (c)(1) and (2) of
this AD that have Airbus Helicopter modification 0728521, 0728904,
0728496, and 0729044 installed before the effective date of this AD,
within 27 months for Model AS 332L2 helicopters, and within 40
months for Model EC 225LP helicopters, after the effective date of
this AD, modify the helicopter in accordance with the Accomplishment
Instructions, paragraphs 3.B.2.c.1.b through 3.B.2.c.2.b of ASB
AS332-53.02.03 Rev 2 or ASB EC225-53A065 Rev 4, as applicable to
your model helicopter, and tighten to the standard torque value,
except instead of discarding parts, you must remove those parts from
service.
(4) Modifying the helicopter as required by paragraphs (j)(1) or
(2) of this AD terminates the life limit required by paragraphs (g)
and (h) of this AD.
(k) Installation Prohibition
As of the effective date of this AD, do not install front bolt
P/N 332A22-1613-20 or 332A22-1613-21, rear bolt P/N 332A22-1614-20,
front fitting P/N 332A22-1623-01, rear left-hand fitting P/N 332A22-
1624-02 or 332A22-1624-04, or rear right-hand fitting P/N 332A22-
1624-03 or 332A22-1624-05 on any helicopter, unless:
(1) The part has not exceeded the applicable service life limit
after accomplishing the actions required by paragraphs (g)(1) or
(h)(1) of this AD, as applicable; and
(2) After installation of the part, the life limit is calculated
in accordance with paragraph (g)(1) or (h)(1) of this AD and all
other applicable requirements of this AD are accomplished.
(l) Credit for Previous Actions
(1) For Model AS 332L2 helicopters, paragraph (l)(1) of this AD
provides credit for the initial life limit calculations required by
paragraphs (g)(1) and (h)(1) of this AD, if those calculations were
performed before the effective date of this AD using the material
identified in paragraphs (l)(1)(i) through (iv) of this AD.
(i) Airbus Helicopters EASB No. 01.00.86, Revision 0, dated July
27, 2017.
(ii) Airbus Helicopters EASB No. 01.00.86, Revision 1, dated
August 25, 2017.
(iii) Airbus Helicopters EASB No. 01.00.86, Revision 2, dated
March 2, 2020.
(iv) Airbus Helicopters EASB No. 01.00.86, Revision 3, dated
August 19, 2021.
(2) For Model EC 225LP helicopters, paragraph (l)(2) of this AD
provides credit for the initial life limit calculations required by
paragraph (g)(1) of this AD, if those calculations were performed
before the effective date of this AD using the material identified
in paragraphs (l)(2)(i) through (iv) of this AD.
(i) Airbus Helicopters EASB No. 04A013, Revision 0, dated July
27, 2017.
(ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated
August 25, 2017.
(iii) Airbus Helicopters EASB No. 04A013, Revision 2, dated
March 2, 2020.
(iv) Airbus Helicopters EASB No. 04A013, Revision 3, dated
August 19, 2021.
(m) 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 (n)(1) of
this AD. Information may be emailed 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.
(n) Additional Information
(1) For more information about this AD, contact Dan McCully,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue Suite 410,
Westbury, NY 11590; phone: (781) 238-7244; email:
[email protected].
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (o)(3)
of this AD.
(o) 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 Alert Service Bulletin No. AS332-
53.02.03, Revision 2, dated June 15, 2023.
(ii) Airbus Helicopters Alert Service Bulletin No. EC225-53A065,
Revision 4, dated May 28, 2024.
(iii) Airbus Helicopters Emergency Alert Service Bulletin No.
01.00.86, Revision 4, dated January 6, 2022.
(iv) Airbus Helicopters Emergency Alert Service Bulletin No.
04A013, Revision 4, dated January 6, 2022.
(3) For Airbus Helicopters material identified in this AD,
contact Airbus
[[Page 56677]]
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.
(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 December 2, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-22218 Filed 12-5-25; 8:45 am]
BILLING CODE 4910-13-P