[Federal Register Volume 88, Number 248 (Thursday, December 28, 2023)]
[Rules and Regulations]
[Pages 89568-89572]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-28720]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2396; Project Identifier MCAI-2023-01147-R; 
Amendment 39-22641; AD 2023-25-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-27-
09, which applied to certain Airbus Helicopters Model EC130T2 
helicopters. AD 2022-27-09 required repetitively inspecting the 
vibration level on the tail rotor drive shaft and, depending on the 
results, taking corrective action. AD 2022-27-09 also required 
reporting information and prohibited installing certain rotor drive 
shafts unless the inspection was done. Since the FAA issued AD 2022-27-
09, Airbus Helicopters revised its service information to update the 
procedures for inspecting that vibration level, reduce an allowable 
vibration level, and clarify when a balance correction may be 
accomplished. This AD was prompted by the determination that a certain 
vibration measurement tool was providing unexpected results and 
therefore the threshold must be revised. This AD continues to require 
certain actions in AD 2022-27-09 and also revises the procedures for 
inspecting the vibration level on the tail rotor drive shaft and 
depending on these results, requires replacing certain parts, as 
specified in a European Union Aviation Safety Agency (EASA) AD, which 
is incorporated by reference. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective January 12, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 28, 
2023.
    The FAA must receive comments on this AD by February 12, 2024.

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 regulations.gov. 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.
    Material Incorporated by Reference:
    <bullet> For EASA material identified in this final rule, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email <a href="/cdn-cgi/l/email-protection#bbfaffc8fbdedac8da95decec9d4cbda95dece"><span class="__cf_email__" data-cfemail="ca8b8eb98aafabb9abe4afbfb8a5baabe4afbf">[email protected]</span></a>; You may find this material on the 
website ad.easa.europa.eu.
    <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.
    Other Related Service Information:
    <bullet> For Airbus Helicopters service information identified in 
this final rule, contact Airbus Helicopters, 2701 North Forum Drive, 
Grand Prairie, TX 75052; phone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at airbus.com/en/products-services/helicopters/hcare-services/airbusworld. You may also view this service information 
at the FAA contact information under Material Incorporated by Reference 
above.

Examining the AD Docket

    You may examine the AD docket at regulations.gov by searching for 
and locating Docket No. FAA-2023-2396; 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 EASA AD, 
any comments received, and other information. The street address for 
Docket Operations is listed above. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer, 
FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (404) 
474-5548; email <a href="/cdn-cgi/l/email-protection#5d2a343131343c3073303e3e283131241d3b3c3c733a322b"><span class="__cf_email__" data-cfemail="384f51545451595516555b5b4d545441785e5959165f574e">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2023-2396; Project Identifier MCAI-
2023-01147-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 
this final rule 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 final rule.

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

[[Page 89569]]

(FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your 
comments responsive to this AD 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 AD, 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 AD. 
Submissions containing CBI should be sent to Dan McCully, Aviation 
Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; 
telephone (404) 474-5548; email <a href="/cdn-cgi/l/email-protection#7e09171212171f1350131d1d0b1212073e181f1f50191108"><span class="__cf_email__" data-cfemail="7106181d1d18101c5f1c1212041d1d08311710105f161e07">[email protected]</span></a>. Any commentary 
that the FAA receives that is not specifically designated as CBI will 
be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2022-27-09, Amendment 39-22294 (88 FR 2199, 
January 13, 2023) (AD 2022-27-09), for certain Airbus Helicopters Model 
EC130T2 helicopters. AD 2022-01-05 was prompted by EASA Emergency AD 
2022-0251-E, dated December 14, 2022 (EASA AD 2022-0251-E), originated 
by EASA, which is the Technical Agent for the Member States of the 
European Union. EASA AD 2022-0251-E was issued to correct an unsafe 
condition on Airbus Helicopters Model EC 130 T2 helicopters with 
modification 079809 incorporated in production. AD 2022-27-09 required 
repetitively inspecting the balancing of the tail rotor drive shaft by 
measuring the vibration level. Depending on the results, AD 2022-27-09 
required accomplishing corrective action in accordance with a method 
approved by the FAA, EASA, or Airbus Helicopters' EASA Design 
Organization Approval, and reporting the results to Airbus Helicopters. 
Lastly, AD 2022-27-09 prohibited installing certain part-numbered tail 
rotor drive shafts on any helicopter unless its requirements were met. 
The FAA issued AD 2022-27-09 to address an excessive vibration level on 
the tail rotor drive shaft, which could result in failure of the tail 
rotor drive shaft and subsequent loss of yaw control of the helicopter.

Actions Since AD 2022-27-09 Was Issued

    Since the FAA issued AD 2022-27-09, EASA superseded EASA AD 2022-
0251-E by issuing EASA Emergency AD 2023-0190-E, dated November 2, 2023 
(EASA AD 2023-0190-E), to correct an unsafe condition on Airbus 
Helicopters Model EC 130 T2 helicopters with modification 079809 
incorporated in production. EASA AD 2023-0190-E states that it was 
identified that one of the vibration measurement tools was providing 
different results than expected and therefore it was determined that 
the threshold must be revised. Consequently, Airbus Helicopter revised 
its service information to provide updated vibration inspection 
instructions, reduce an allowable vibration level, and clarify when a 
balance correction may be accomplished. Accordingly, EASA AD 2023-0190-
E retains the requirements of EASA AD 2022-0251-E and depending on the 
results of the updated vibration inspection, requires replacing certain 
parts with new (zero total hours time-in-service) parts. Additionally, 
EASA AD 2023-0190-E prohibits performing a balance correction unless it 
is performed concurrently with replacement of certain parts by 
following certain procedures. However, if a balance correction has 
already been performed independent of replacing the sliding flange and 
the splined sleeve equipped, EASA AD 2023-0190-E requires contacting 
Airbus Helicopter for further approved instructions. EASA considers its 
AD an interim action and states that further AD action may follow. See 
EASA AD 2023-0190-E for additional background information.
    Additionally, the FAA discovered that an incorrect U.S. fleet count 
was provided in the Costs of Compliance section of AD 2022-27-09. This 
AD corrects that count.

Related Service Information Under 1 CFR Part 51

    EASA AD 2023-0190-E requires repetitively checking the balancing of 
the tail rotor drive shaft by measuring the vibration level. Depending 
on the results, EASA AD 2023-0190-E requires replacing certain parts 
with new parts. EASA AD 2023-0190-E also prohibits performing a balance 
correction unless this action is performed concurrently with replacing 
certain parts. If a balance correction has already been performed 
independently of replacing those parts, EASA AD 2023-0190-E requires 
contacting Airbus Helicopters to obtain approved instructions and 
accomplishing those instructions. EASA AD 2023-0190-E also requires 
reporting the vibration measurements to Airbus Helicopters. Lastly, 
EASA AD 2023-0190-E prohibits installing certain part-numbered tail 
rotor drive shafts on any helicopter unless its requirements are met.
    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.

Other Related Service Information

    The FAA reviewed Airbus Helicopters Emergency Alert Service 
Bulletin No. EC130-05A042, Revision 1, dated November 2, 2023 (EASB 
EC130-05A042 Rev 1). This service information specifies procedures for 
measuring the vibration level on the tail rotor drive shaft, reporting 
the results to Airbus Helicopters, and replacing the sliding flange and 
the splined sleeve equipped.
    The FAA also reviewed AMM Task 65-11-01,5-1A, Adjustment--Balancing 
of the tail rotor drive line (with the STEADY Control tuning 
equipment)--Tail Drive Line POST MOD 079809 and AMM Task 65-11-01,5-1B, 
Adjustment--Balancing of the tail rotor drive shaft (with the VIBREX 
2000 adjustment equipment)--Tail Drive Line POST MOD 079809, both 
Update 2 and dated July 3, 2022. This service information specifies 
procedures for measuring the vibration level on the tail rotor drive 
shaft, analyzing the results, and balancing the tail rotor drive line 
or shaft.

FAA's Determination

    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 emergency AD. The FAA is issuing this 
AD after evaluating all pertinent information and determining that the 
unsafe condition exists and is likely to exist or develop on other 
helicopters of the same type design.

AD Requirements

    This AD retains certain requirements of AD 2022-27-09. This AD also 
requires accomplishing the actions specified in EASA AD 2023-0190-E, 
described previously, as incorporated by reference, except for any 
differences identified as exceptions in the regulatory text of this AD 
and except as discussed under ``Differences Between this AD and the 
EASA Emergency AD.''
    EASA AD 2023-0190-E refers to EASB EC130-05A042 Rev 1, for 
compliance times to replace the spline sleeve equipped and sliding 
flange. This AD requires those compliance times, as incorporated by 
reference, and are as follows:

[[Page 89570]]



------------------------------------------------------------------------
                                    Vibration
          Task used            measurement result      Compliance time
------------------------------------------------------------------------
The maintenance task A: AH    If the vibration      Within 30 hours time-
 EC130 Aircraft Maintenance    level is equal to     in-service (TIS)
 Manual (AMM) Task 65-11-      or more than 1.4      after the last
 01,5-1A (``Balancing of the   and less than 1.8     inspection.
 tail rotor drive line'').     IPS.                 Within 15 hours TIS
                              If the vibration       after the last
                               level is equal to     inspection.
                               or more than 1.8
                               and less than 2.6
                               IPS.
                              If the vibration      Before further
                               level is equal to     flight.
                               or more than 2.6
                               IPS.
The maintenance task B: AH    If the vibration      Within 30 hours TIS
 EC130 AMM Task 65-11-01,5-    level is equal to     after the last
 1B (``Balancing of the tail   or more than 0.7      inspection; or, if
 rotor drive shaft'').         and less than 0.9     the last inspection
                               IPS.                  was done before the
                                                     effective date of
                                                     this AD and more
                                                     than 30 hours TIS
                                                     have passed since
                                                     that inspection,
                                                     before further
                                                     flight.
                              If the vibration      Within 15 hours TIS
                               level is equal to     after the last
                               or more than 0.9      inspection; or, if
                               and less than 1.3     the last inspection
                               IPS.                  was done before the
                                                     effective date of
                                                     this AD and more
                                                     than 15 hours TIS
                                                     have passed since
                                                     that inspection,
                                                     before further
                                                     flight.
                              If the vibration      Before further
                               level is equal to     flight.
                               or more than 1.3
                               IPS.
------------------------------------------------------------------------

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, 
EASA AD 2023-0190-E will be incorporated by reference in this FAA final 
rule. This AD would, therefore, require compliance with EASA AD 2023-
0190-E in its entirety through that incorporation, except for any 
differences identified as exceptions in the regulatory text of this AD. 
Using common terms that are the same as the heading of a particular 
section in EASA AD 2023-0190-E 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 2023-0190-E. Service information 
referenced in EASA AD 2023-0190-E for compliance will be available at 
regulations.gov by searching for and locating Docket No. FAA-2023-2396 
after the FAA final rule is published.

Differences Between This AD and the EASA Emergency AD

    EASA AD 2023-0190-E requires tail rotor drive shaft checks, whereas 
this AD requires tail rotor drive shaft inspections because those 
actions must be accomplished by persons authorized under 14 CFR 43.3.
    For helicopters that accomplished a balance correction in 
accordance with the instructions of the applicable AMM before the 
effective date of EASA AD 2023-0190-E, except if this balance 
correction was accomplished before next flight after replacing the 
sliding flange and the splined sleeve equipped, EASA AD 2023-0190-E 
requires contacting AH [Airbus Helicopters] to obtain approved 
instructions, and within the compliance time(s) specified therein, 
accomplishing those instructions accordingly. Whereas, for helicopters 
that accomplished a balance correction in accordance with the 
instructions of the applicable AMM before the effective date of this 
AD, except not those that only accomplished a balance correction before 
the next flight after installing a new (zero total hours time-in-
service) sliding flange and a new (zero total hours time-in-service) 
splined sleeve equipped, this AD requires corrective action 
accomplished in accordance with a method approved by the FAA, EASA, or 
Airbus Helicopters' EASA Design Organization Approval.
    EASA AD 2023-0190-E requires reporting information to AH [Airbus 
Helicopters], whereas this AD does not.
    EASA AD 2023-0190-E allows credit for the initial instance of the 
vibration measurements accomplished before its effective date, whereas 
this AD allows credit for any instance of the vibration measurements 
accomplished before the effective date of this AD.
    EASA AD 2023-0190-E prohibits performing a balance correction, 
except if it is accomplished as part of its requirements. This AD does 
not, because such a compliance time would be difficult to enforce.

Interim Action

    The FAA considers this AD interim action. If final action is later 
identified, the FAA might consider further rulemaking then.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies foregoing notice and comment prior to adoption of this rule 
because the tail rotor drive shaft is critical to the control of a 
helicopter and a failure of the tail rotor drive shaft could occur 
during any phase of flight without previous indication. The FAA also 
has no information pertaining to how quickly the condition may 
propagate to failure. In light of this and, depending how many hours 
the helicopter has accumulated, for some operators the initial 
inspection must be accomplished before further flight. For other 
operators, the initial inspection must be accomplished before 
accumulating 50 total hours time-in-service or within three months, 
whichever occurs first, which is shorter than the time necessary for 
the public to comment and for publication of the final rule. 
Accordingly, notice and opportunity for prior public comment are 
impracticable and contrary to the public interest pursuant to 5 U.S.C. 
553(b)(3)(B).

[[Page 89571]]

    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 117 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.
    Inspecting the tail rotor drive shaft takes approximately 4 work-
hours for an estimated cost of $340 per helicopter and $39,780 for the 
U.S. fleet, per inspection cycle.
    If required, replacing the sliding flange and the splined sleeve 
equipped takes approximately 40 work-hours and parts cost $3,420 for an 
estimated cost of $6,820, per replacement cycle.
    For helicopters that accomplished a balance correction in 
accordance with the instructions of the applicable AMM before the 
effective date of this AD, except not those that only accomplished a 
balance correction before the next flight after installing a new (zero 
total hours time-in-service) sliding flange and a new (zero total hours 
time-in-service) splined sleeve equipped, the corrective action that 
may be needed could vary significantly from helicopter to helicopter. 
The FAA has no data to determine the costs to accomplish the corrective 
action or the number of helicopters that may require corrective action.

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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2022-27-09, Amendment 39-22294 (88 
FR 2199, January 13, 2023); and
0
b. Adding the following new airworthiness directive:

2023-25-14 Airbus Helicopters: Amendment 39-22641; Docket No. FAA-
2023-2396; Project Identifier MCAI-2023-01147-R.

(a) Effective Date

    This airworthiness directive (AD) is effective January 12, 2024.

(b) Affected ADs

    This AD replaces AD 2022-27-09, Amendment 39-22294 (88 FR 2199, 
January 13, 2023) (AD 2022-27-09).

(c) Applicability

    This AD applies to Airbus Helicopters Model EC130T2 helicopters, 
certificated in any category, as identified in European Union 
Aviation Safety Agency (EASA) Emergency AD 2023-0190-E, dated 
November 2, 2023 (EASA AD 2023-0190-E).

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor 
Drive Shaft.

(e) Unsafe Condition

    This AD was prompted by a report of a crack in the tailboom. The 
FAA is issuing this AD to address an excessive vibration level on 
the tail rotor drive shaft. The unsafe condition, if not addressed, 
could result in failure of the tail rotor drive shaft and subsequent 
loss of yaw 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, EASA AD 2023-0190-E.

(h) Exceptions to EASA AD 2023-0190-E

    (1) Where EASA AD 2023-0190-E requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) Where EASA AD 2023-0190-E refers to the effective date of 
December 16, 2022 (the effective date of EASA AD 2022-0251-E, dated 
December 14, 2022), this AD requires using the effective date of 
January 30, 2023 (the effective date of AD 2022-27-09).
    (3) Where EASA AD 2023-0190-E refers to its effective date, this 
AD requires using the effective date of this AD.
    (4) Where EASA AD 2023-0190-E refers to tail rotor drive shaft 
checks, this AD requires tail rotor drive shaft inspections.
    (5) Where Note 1 of EASA AD 2023-0190-E states, ``Unless 
indicated otherwise, the FH specified in Table 1 of this AD are 
those accumulated by the helicopter since first flight, or since the 
installation of the new spline sleeve equipped and sliding flange;'' 
for this AD, replace that text with ``Unless indicated otherwise, 
the hours time-in-service specified in Table 1 of this AD are those 
accumulated by the helicopter since first flight, or since the 
installation of the new spline sleeve equipped and sliding flange, 
as applicable to your helicopter.''
    (6) This AD does not allow the provisions in Note 2 of EASA AD 
2023-0190-E or Note 2 in the ASB referenced in EASA AD 2023-0190-E. 
Refer to paragraph (j) of this AD for special flight permit 
information.
    (7) Where paragraphs (2) and (3) of EASA AD 2023-0190-E require 
removing parts, this AD requires removing those parts from service.
    (8) Where paragraph (4) of EASA AD 2023-0190-E specifies to 
``contact AH [Airbus Helicopters] to obtain approved instructions, 
and within the compliance time(s) specified therein, accomplish 
those instructions accordingly;'' for this AD, replace that text 
with ``accomplish corrective action in accordance with a method 
approved by the Manager, International Validation Branch, FAA; or 
EASA; or Airbus Helicopters' EASA

[[Page 89572]]

Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.''
    (9) This AD does not require compliance with paragraph (5) of 
EASA AD 2023-0190-E.

    Note 1 paragraph (h)(9): Accomplishing a balance correction 
other than with the replacement of tail rotor drive line parts could 
interfere with subsequent tail rotor drive line balancing 
inspections. Airbus Helicopters Emergency Alert Service Bulletin No. 
EC130-05A042, Revision 1, dated November 2, 2023, contains 
additional information regarding balance corrections.

    (10) This AD does not require compliance with paragraph (6) of 
EASA AD 2023-0190-E.
    (11) Instead of the credit allowed in paragraph (7) of EASA AD 
2023-0190-E, you may take credit for the vibration measurements 
required by paragraph (1) of EASA AD 2023-0190-E that have been 
accomplished before the effective date of this AD using Airbus 
Helicopters Emergency Alert Service Bulletin No. EC130-05A042, 
Revision 0, dated December 14, 2022.
    (12) Instead of the credit allowed in paragraph (8) of EASA AD 
2023-0190-E, you may take credit for accomplishing ``maintenance 
task B,'' as defined in EASA AD 2023-0190-E and required by 
paragraph (3) of EASA AD 2023-0190-E, to satisfy the initial 
instance of ``maintenance task B,'' as defined in EASA AD 2023-0190-
E and required by paragraph (2) of EASA AD 2023-0190-E.
    (13) This AD does not adopt the ``Remarks'' section of EASA AD 
2023-0190-E.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2023-
0190-E specifies to submit certain information to the manufacturer, 
this AD does not include that requirement.

(j) Special Flight Permit

    Special flight permits may be issued in accordance with 14 CFR 
21.197 and 21.199 only to operate the helicopter to a maintenance 
location for the initial tail rotor drive shaft inspection, provided 
no passengers are onboard.

(k) 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 (l)(1) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#bb8296faede896faf2e9968c888b96faf6f4f8fbdddada95dcd4cd"><span class="__cf_email__" data-cfemail="60594d2136334d2129324d5753504d212d2f23200601014e070f16">[email protected]</span></a>.
    (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.

(l) Additional Information

    (1) For more information about this AD, contact Dan McCully, 
Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, 
Westbury, NY 11590; telephone (404) 474-5548; email 
<a href="/cdn-cgi/l/email-protection#83f4eaefefeae2eeadeee0e0f6efeffac3e5e2e2ade4ecf5"><span class="__cf_email__" data-cfemail="5126383d3d38303c7f3c3232243d3d28113730307f363e27">[email protected]</span></a>.
    (2) For Airbus Helicopters service information 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; 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 
Parkway, Room 6N-321, Fort Worth, TX 76177. For information on the 
availability of this material at the FAA, call (817) 222-5110.

(m) 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 this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) Emergency AD 
2023-0190-E, dated November 2, 2023.
    (ii) [Reserved]
    (3) For EASA material, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 8999 000; email 
<a href="/cdn-cgi/l/email-protection#a5e4e1d6e5c0c4d6c48bc0d0d7cad5c48bc0d0"><span class="__cf_email__" data-cfemail="37767344775256445619524245584756195242">[email protected]</span></a>; website easa.europa.eu. You may find the EASA 
material on the EASA website ad.easa.europa.eu.
    (4) You may view this service information 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 <a href="/cdn-cgi/l/email-protection#771105591e1904071214031e1819371916051659101801"><span class="__cf_email__" data-cfemail="4325316d2a2d30332620372a2c2d032d2231226d242c35">[email protected]</span></a>.

    Issued on December 22, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2023-28720 Filed 12-26-23; 11:15 am]
BILLING CODE 4910-13-P


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