--------------------------------------------------------------------------------
 UNITED STATES ENVIRONMENTAL PROTECTION AGENCY
--------------------------------------------------------------------------------
REGION 8
--------------------------------------------------------------------------------
1595 Wynkoop Street
--------------------------------------------------------------------------------
Denver, CO   80202-1129
--------------------------------------------------------------------------------
Phone<PHONE_NUMBER>
--------------------------------------------------------------------------------
www.epa.gov/region8
Ref: 8ARD-PM

Mr. Mike Natchees
Director, Air Quality Program
Energy and Minerals Division
Ute Indian Tribe
P.O. Box 70
Fort Duchesne, Utah  84026

Dear Mr. Natchees:

The U.S. Environmental Protection Agency Region 8 is proposing to issue a synthetic minor permit for the existing Anadarko Uintah Midstream, LLC. (Anadarko), East Junior Compressor Station on the Uintah and Ouray Indian Reservation. As requested by Anadarko, this permit would incorporate enforceable requirements for two field gas fired, 4-stroke, lean-burn compressor engines using catalytic emissions control systems. Anadarko also requested enforceable requirements to install and operate only instrument air-driven or low- or no-bleed pneumatic controllers. This permit is only intended to incorporate requested emission limits and provisions from the permit application for existing emissions units operating at the facility.

A public comment period for the proposed permit will begin on July 30, 2019, and end on August 28, 2019.

We have enclosed a CD and paper copy containing the proposed permit and supporting documentation, and we ask that you please make this material available for public review until the end of the public comment period. Comments may be submitted via mail, via email to<EMAIL_ADDRESS>or through https://www.regulations.gov (Docket ID # EPA-R08-OAR-2018-0325). In addition, we have provided copies of the bulletin board public notice announcement and would appreciate it if you would post this announcement in prominent locations in your area. All of these documents will also be available for review in electronic format on our website at: https://www.epa.gov/caa-permitting/caa-permitpublic-comment-opportunities-region-8.

If you have any questions concerning the enclosed proposed permit or technical support documents, please contact Gregory Lohrke, of my staff, at<PHONE_NUMBER>.

                                       Sincerely,

                                      Carl Daly
                                      Acting Director
                                      Air and Radiation Division

Enclosures

cc:  Bruce Pargeets, Director, Energy and Minerals Division, Ute Indian Tribe


[Federal Register Volume 88, Number 149 (Friday, August 4, 2023)]
[Rules and Regulations]
[Pages 51695-51699]
[FR Doc No: 2023-16555]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-0016; Project Identifier MCAI-2022-00416-R;
Amendment 39-22506; AD 2023-14-06]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters. This
AD was prompted by a report of corrosion detected on certain part-
numbered landing gear assemblies. This AD requires, for helicopters
with certain part-numbered landing gear assemblies installed, visually
inspecting for cracks and corrosion; borescope inspecting; and if
required, removing corrosion, measuring thickness, interpreting results
of the measurements, applying chemical conversion coating and primer,
and removing affected parts (landing gear assembly) and affected part
sub-assemblies (front or rear crossbeam or left-hand or right-hand skid
assembly) from service and replacing with airworthy parts. This AD will
allow an affected part or affected part sub-assembly to be installed on
a helicopter if certain actions in this AD are accomplished. The FAA is
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective September 8, 2023.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 8,
2023.

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-0016; 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 European Union Aviation Safety
Agency (EASA) AD, 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 service information identified in this final rule,
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
     You may view this service information at the FAA, Office
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>. It is also available at
regulations.gov under Docket No. FAA-2023-0016.

FOR FURTHER INFORMATION CONTACT: Stephanie Sunderbruch, Aviation Safety
Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590;
telephone<PHONE_NUMBER>; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus Helicopters
Model EC120B, EC130B4, and EC130T2 helicopters. The NPRM published in
the Federal Register on January 19, 2023. The NPRM was prompted by EASA
AD 2022-0053, dated March 23, 2022 (EASA AD 2022-0053), issued by EASA,
which is the Technical Agent for the Member States of the European
Union. EASA advises of an occurrence of corrosion found on a landing
gear assembly of a Model EC 130 helicopter. EASA further advises that
other helicopter models are affected by the same unsafe condition due
to design similarity. This condition, if not addressed, could result in
the landing gear collapsing, damage to the helicopter, and injury to
occupants.
    Accordingly, EASA AD 2022-0053 requires, for helicopters with
certain part-numbered landing gear assemblies installed, a one-time
visual inspection of the external areas of the landing gear tubes for
corrosion and cracks, and a borescope inspection of the internal sides
of the landing gear tubes for corrosion (including, but not limited to,
leafing and exfoliant corrosion) and cracks. EASA AD 2022-0053 also
requires contacting Airbus Helicopters for approved corrective action
if any crack, or leafing or exfoliant corrosion, is found or if the
remaining thickness of affected part sub-assemblies do not meet
specified acceptability criteria during any of the inspections. EASA AD
2022-0053 allows replacing the affected part sub-assembly in lieu of
contacting Airbus Helicopters for approved corrective action. EASA AD
2022-0053 also requires reporting inspection results to Airbus
Helicopters within 30 days after the inspection or within 30 days after
the effective date of EASA AD 2022-0053, whichever occurs later.
    Additionally, EASA AD 2022-0053 allows credit for certain
inspections and corrective actions if those actions were done before
the effective date of EASA AD 2022-0053, and allows an affected part or
affected part sub-assembly to be installed on a helicopter if certain
requirements of EASA AD 2022-0053 are met. EASA considers its AD an
interim action and states that further AD action may follow.
    In the NPRM, the FAA proposed to require, for helicopters with
certain part-numbered landing gear assemblies installed, removing and
cleaning certain parts; visually inspecting certain areas of the
landing gear tubes for cracks and corrosion; and if any crack, leafing
corrosion, or exfoliant corrosion is detected, removing certain parts
from service and replacing with airworthy parts. If any corrosion other
than leafing or exfoliant corrosion is detected, the NPRM proposed to
require removing the corrosion.
    The NPRM also proposed to require borescope inspecting the internal
side of the landing gear tubes for cracks and corrosion. If any crack,
leafing corrosion, or exfoliant corrosion is detected, the NPRM
proposed to require removing any affected part from service and
replacing it with an airworthy part. If any corrosion other than
leafing or exfoliant corrosion is detected, the NPRM proposed to
require removing the corrosion.
    The NPRM also proposed, if any corrosion other than leafing or
exfoliant corrosion is detected during any of the inspections, removing
all corrosion and measuring the remaining thickness of the landing gear
tubes and interpreting the results of the measurements. If the
remaining thickness does not meet the permitted criteria as specified,
the NPRM proposed to require removing each affected sub-assembly from
service and replacing it with an airworthy part. If the remaining
thickness meets the permitted criteria as specified, the NPRM proposed
to require applying a chemical conversion coating and a double layer of
primer.
    Finally, the NPRM proposed to allow an affected part or affected
part sub-assembly to be installed on a helicopter, if certain proposed
requirements of the NPRM have been accomplished.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter, Air Methods.\1\ The
following presents the comments received on the NPRM and the FAA's
response to each comment.
---------------------------------------------------------------------------

    \1\ This comment does not appear in the docket because it was
marked ``proprietary information.''
---------------------------------------------------------------------------

Request To Allow Credit for Previously Issued Service Information

    Air Methods requested that the FAA allow credit for the inspections
and corrective actions proposed in the NPRM, if these actions were
performed in accordance with Revision 1 of the service information
before the effective

date of the AD. Air Methods added that Figure 4 of the service
information required by this AD does not properly label ``Zone B'' and
``Zone C,'' but commented that it considers the service information
sufficiently adequate to identify the areas.
    The FAA partially agrees. Paragraph (f) of this AD requires
compliance with this AD within the compliance times specified, unless
the actions have already been done. Therefore, this AD already permits
credit for complying with the AD's required actions if those actions
were performed before the effective date of this AD. However, the FAA
disagrees with allowing credit for all of this AD's required actions if
done in accordance with Revision 1 of the service information, before
the effective date of this AD, because the corrective actions in
Revision 1 of the service information differ from this AD's corrective
actions. Operators may request approval of specific corrective actions
as an alternative method of compliance (AMOC) under the provisions of
paragraph (h) of this AD.

Comments Regarding Methods To Remove Corrosion

    Air Methods stated that Revision 1 of the service information
refers to the Standard Practices Manual (MTC) for procedures to remove
corrosion and that the MTC includes details on important considerations
when removing corrosion from aluminum parts. Air Methods further stated
that the MTC contains safe procedures for corrosion removal based on
service history. Lastly, Air Methods stated that the specific use of
just a non-metal abrasive pad, as proposed in the NPRM, may not be
adequate to remove corrosion in severe cases and asserted that
restricting the corrosion removal procedure does not provide any
measurable improvement to the level of safety. The FAA infers that Air
Methods is requesting the FAA not limit corrosion removal to only using
a non-metal abrasive pad.
    The FAA agrees. The FAA has revised the required actions paragraph
of this final rule by removing the requirement to use a non-metal
abrasive pad, and only requires removing all corrosion from all zones.

Conclusion

    These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA reviewed the relevant
data, considered the 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 helicopters. Except
for minor editorial changes, and any other changes described
previously, this AD is adopted as proposed in the NPRM. None of the
changes increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. EC120-32A014 (EC120-32A014 Rev 1), for Model EC120B helicopters and
Airbus Helicopters ASB No. EC130-32A013 (EC130-32A013 Rev 1), for Model
EC130B4 and EC130T2 helicopters, both Revision 1, and both dated
October 17, 2022. This service information includes Detail A Figure 3
(EC120-32A014 Rev 1) and Detail A Figure 4 (EC130-32A013 Rev 1), which
identify the areas and zones to be inspected for cracks and corrosion
(including, but not limited to leafing and exfoliant corrosion). This
service information also includes Table 3, which identifies the minimum
material thickness permitted after corrosion is removed. Additionally,
this service information specifies procedures for visually inspecting
the external areas and borescope inspecting the internal areas of the
landing gear tubes, removing corrosion, measuring thickness,
interpreting results of the measurements, and applying a chemical
conversion coating and primer.
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES.

Differences Between This AD and EASA AD 2022-0053

    EASA AD 2022-0053 requires, for certain helicopters, the initial
inspections to be completed within certain compliance times specified
in Table 1 of EASA AD 2022-0053, whereas this AD requires the initial
inspections to be completed within 13 months after the effective date
of this AD. EASA AD 2022-0053 requires contacting Airbus Helicopters
for repair instructions if any cracks, leafing corrosion, or exfoliant
corrosion are found, or if the residual thickness of an affected part
sub-assembly does not meet certain criteria, whereas this AD requires
removing the affected part or part sub-assembly from service instead.
EASA AD 2022-0053 allows credit for certain inspections and corrective
actions if these requirements were accomplished in accordance with
previously issued service information, whereas this AD does not allow
credit for the inspections and corrective actions if previously issued
service information was used. EASA AD 2022-0053 requires reporting the
inspection results to Airbus Helicopters, whereas this AD does not
require reporting.

Interim Action

    The FAA considers that this AD is an interim action. Once final
action has been identified, the FAA might consider further rulemaking.

Costs of Compliance

    The FAA estimates that this AD affects 353 helicopters of U.S.
registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
    Removing and cleaning parts, and visually inspecting the external
surface of each landing gear tube for cracks and corrosion takes about
2 work-hours for an estimated cost of $170 per inspection, up to $680
per helicopter (4 landing gear tubes per helicopter), and up to
$240,040 for the U.S. fleet.
    Borescope inspecting the internal side of each landing gear tube
for cracks and corrosion (including, but not limited to, leafing and
exfoliant corrosion) takes about 1 work-hour for an estimated cost of
$85 per inspection, up to $340 per helicopter (4 landing gear tubes per
helicopter), and up to $120,020 for the U.S. fleet.
    If required, applying a chemical conversion coating and a double
layer of primer takes about 2 work-hours and parts cost a minimal
amount for an estimated cost of $170 per helicopter and up to $60,010
for the U.S. fleet.
    If required, disassembling certain zones and removing corrosion
takes about 1 work-hour for an estimated cost of $85 per helicopter.
    If required, measuring the thickness of the internal side of each
landing gear tube and interpreting the results takes up to 1 work-hour
for an estimated cost of $85 per helicopter.
    If required, replacing a landing gear assembly takes about 2 work-
hours and parts cost up to $106,612 for an estimated cost of up to
$106,782 per replacement.
    If required, replacing a front crossbeam takes about 1 work-hour
and parts cost up to $9,081 for an estimated cost of up to $9,166 per
replacement.
    If required, replacing a rear crossbeam takes about 1 work-hour and
parts cost up to $11,639 for an estimated cost of up to $11,724 per
replacement.
    If required, replacing a right-hand or left-hand skid assembly
takes about 1 work-hour and parts cost up to $21,447

for an estimated cost of up to $21,532 per skid assembly replacement.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (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:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive:

2023-14-06 Airbus Helicopters: Amendment 39-22506; Docket No. FAA-
2023-0016; Project Identifier MCAI-2022-00416-R.

(a) Effective Date

    This airworthiness directive (AD) is effective September 8,
2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model EC120B, EC130B4,
and EC130T2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 3213, Main Landing
Gear Strut, Axle, Truck.

(e) Unsafe Condition

    This AD was prompted by a report of corrosion detected on
certain part-numbered landing gear assemblies. The FAA is issuing
this AD to detect corrosion and cracks on the landing gear tubes.
The unsafe condition, if not addressed, could result in the landing
gear collapsing, damage to the helicopter, and injury to occupants.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Required Actions

    (1) Within 13 months after the effective date of this AD, for
Model EC120B helicopters with landing gear assembly part number (P/
N) C321A2106102, P/N C321A2501101, P/N C321A2501102, P/N
C321A2601051AA, P/N C321A2601051CA, or P/N C321A2601052 installed,
and for Model EC130B4 and EC130T2 helicopters with landing gear
assembly P/N 350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-
0080-1103, P/N 350A41-0081-0201, P/N 350A41-0082-0101, or P/N
350A41-0082-0102 installed, except those having a date of first
installation on a helicopter of February 16, 2022 or later; and for
helicopters with a landing gear assembly having a P/N specified in
this paragraph, with an unknown installation date, do the following:
    (i) Remove the landing gear fairing from the rear crossbeam and
clean the external areas of each of the landing gear tubes item a,
item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F,
and M as depicted in Detail A, Figure 3, and Details B and C, Figure
4 of Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014 (ASB EC120-32A014 Rev 1), or as depicted in Detail A, Figure
4, and Details B and C, Figure 5 of Airbus Helicopters ASB No.
EC130-32A013 (ASB EC130-32A013 Rev 1), both Revision 1, and both
dated October 17, 2022, as applicable to your model helicopter.
    (ii) Visually inspect the external areas of each of the landing
gear tubes item a, item c, item d, and item e, including Zones B1,
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack or leafing or exfoliant corrosion is detected,
before further flight, remove the affected part from service and
replace it with an airworthy part.
    (B) If any corrosion is detected in Zone C1, C2, or E, other
than leafing or exfoliant corrosion, before further flight,
disassemble the landing gear and remove all corrosion from all
zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or
M, other than leafing or exfoliant corrosion, before further flight,
remove all corrosion from all zones.
    (iii) Borescope inspect the internal side of each of the landing
gear tubes item a, item c, item d, and item e, including Zones B1,
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack, leafing corrosion, or exfoliant corrosion is
detected, before further flight, remove the affected part from
service and replace it with an airworthy part.
    (B) If any corrosion is detected in Zone C1, C2, or E, other
than leafing or exfoliant corrosion, before further flight,
disassemble the landing gear and remove all corrosion from all
zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or
M, other than leafing or exfoliant corrosion, before further flight,
remove all corrosion from all zones.
    (iv) Before further flight after performing the inspections
required by paragraphs (g)(1)(ii) and (iii) of this AD, if any
corrosion was detected during any inspection required by paragraphs
(g)(1)(ii) and (iii) of this AD other than leafing or exfoliant
corrosion, using an ultrasonic thickness gauge, measure the
remaining thickness of the landing gear tubes in the zones where any
corrosion was removed. Interpret the results of the measurement
using the criteria specified in Table 3 of ASB EC120-32A014 Rev 1 or
Table 3 of ASB EC130-32A013 Rev 1, as applicable to your model
helicopter. If the remaining thickness does not meet the permitted
criteria as specified, before further flight, remove each affected
sub-assembly from service and replace it with an airworthy part. If
the remaining thickness meets the permitted criteria as specified,
before further flight, accomplish the actions required by paragraph
(g)(1)(v) of this AD.
    (v) Apply a chemical conversion coating (Alodine 1200) or
equivalent, and a double layer of chromate Primer P05 and Primer
P20, or equivalent, below the collar in Zones F and M and to any
reworked zone.
    (2) For Model EC120B helicopters, as of the effective date of
this AD, do not install landing gear assembly P/N C321A2106102, P/N
C321A2501101, P/N C321A2501102, P/N C321A2601051AA, P/N
C321A2601051CA, or P/N C321A2601052, previously installed with an
unknown installation date or a date of first installation on a
helicopter before February 16, 2022; and do not install a front
crossbeam, rear crossbeam, left-hand (LH) skid assembly, or right-
hand (RH) skid

assembly having a P/N identified in Table 2 of ASB EC120-32A014 Rev
1, previously installed with an unknown installation date, or a date
of first installation on a helicopter before February 16, 2022, on
any helicopter; unless the actions required by paragraphs (g)(1)(i)
through (v) of this AD, as applicable, have been accomplished on the
part.
    (3) For Model EC130B4 and EC130T2 helicopters, as of the
effective date of this AD, do not install landing gear assembly P/N
350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-0080-1103, P/N
350A41-0081-0201, P/N 350A41-0082-0101, or P/N 350A41-0082-0102,
previously installed with an unknown installation date or a date of
first installation on a helicopter before February 16, 2022, and do
not install a front crossbeam, rear crossbeam, LH skid assembly, or
RH skid assembly, having a P/N identified in Table 2 of ASB EC130-
32A013 Rev 1, previously installed with an unknown installation
date, or a date of first installation on a helicopter before
February 16, 2022, on any helicopter, unless the actions required by
paragraphs (g)(1)(i) through (v) of this AD, as applicable, have
been accomplished on the part.

(h) 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 (i)(2) 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.

(i) Additional Information

    (1) Refer to European Union Aviation Safety Agency (EASA) AD
2022-0053, dated March 23, 2022, for related information. This EASA
AD may be found in the AD docket at regulations.gov under Docket No.
FAA-2023-0016.
    (2) For more information about this AD, contact Stephanie
Sunderbruch, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite
410, Westbury, NY 11590; telephone<PHONE_NUMBER>; email:
[email protected].

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014, Revision 1, dated October 17, 2022.
    (ii) Airbus Helicopters ASB No. EC130-32A013, Revision 1, dated
October 17, 2022.
    (3) For service information identified in this AD, contact
Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052;
telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or
at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
    (4) You may view this service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 12, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-16555 Filed 8-3-23; 8:45 am]
BILLING CODE 4910-13-P