[Federal Register Volume 86, Number 175 (Tuesday, September 14, 2021)]
[Proposed Rules]
[Pages 51022-51026]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19607]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / 
Proposed Rules

[[Page 51022]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0283; Project Identifier 2018-SW-045-AD]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.a. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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

SUMMARY: The FAA is revising an earlier proposal for certain Leonardo 
S.p.a. Model AB139 and AW139 helicopters. This action revises the 
notice of proposed rulemaking (NPRM) by expanding the required actions. 
This proposed AD would require various inspections of certain main 
rotor (MR) dampers, as specified in a European Aviation Safety Agency 
(now European Union Aviation Safety Agency) (EASA) AD, which is 
proposed for incorporation by reference (IBR). This proposed AD would 
also require reducing the torque of the MR damper hub attachment bolts, 
installing a special washer, installing a certain part-numbered MR 
damper, and prohibit installing other part-numbered MR dampers. The FAA 
is proposing this airworthiness directive (AD) to address the unsafe 
condition on these products. Since these actions would impose an 
additional burden over those in the NPRM, the FAA is requesting 
comments on this SNPRM.

DATES: The comment period for the NPRM published in the Federal 
Register on March 31, 2020 (85 FR 17788), is reopened.
    The FAA must receive comments on this SNPRM by October 29, 2021.

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 https://www.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.
    For material that is proposed for IBR in this AD, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 
000; email <a href="/cdn-cgi/l/email-protection#ce8f8abd8eabafbdafe0abbbbca1beafe0abbb"><span class="__cf_email__" data-cfemail="1f5e5b6c5f7a7e6c7e317a6a6d706f7e317a6a">[email protected]</span></a>; internet www.easa.europa.eu. You may 
find this material on the EASA website at https://ad.easa.europa.eu. 
You may view this material 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 (817) 222-5110. It is also available in the AD docket on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2020-0283.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0283; 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 SNPRM, 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: Matt Fuller, AD Program Manager, 
General Aviation & Rotorcraft Unit, Airworthiness Products Section, 
Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#2944485d5d414c5e074f5c45454c5b694f4848074e465f"><span class="__cf_email__" data-cfemail="ed808c999985889ac38b988181889fad8b8c8cc38a829b">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2020-0283; Project Identifier 
2018-SW-045-AD'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this SNPRM 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 SNPRM, 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 SNPRM. Submissions containing CBI should 
be sent to Matt Fuller, AD Program Manager, General Aviation & 
Rotorcraft Unit, Airworthiness Products Section, Operational Safety 
Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 
(817) 222-5110; email <a href="/cdn-cgi/l/email-protection#bed3dfcacad6dbc990d8cbd2d2dbccfed8dfdf90d9d1c8"><span class="__cf_email__" data-cfemail="b1dcd0c5c5d9d4c69fd7c4ddddd4c3f1d7d0d09fd6dec7">[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 an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain serial-numbered Leonardo S.p.A. Model AB139 and 
AW139 helicopters with an MR damper part number (P/N) 3G6220V01351, 
3G6220V01352, or 3G6220V01353

[[Page 51023]]

installed. The NPRM published in the Federal Register on March 31, 2020 
(85 FR 17788). In the NPRM, the FAA proposed to require, for an 
affected helicopter with MR damper P/N 3G6220V01351, 3G6220V01352, or 
3G6220V01353 installed, reducing the installation torque of each hub 
attachment bolt for each MR damper. For an affected helicopter with MR 
damper P/N 3G6220V01351 or 3G6220V01352 installed, the NPRM proposed to 
require: Repetitively inspecting the MR damper rod end (rod end) and MR 
damper body end (body end) for a crack; dye penetrant inspecting or 
eddy current inspecting certain rod and body ends for a crack; 
repetitively inspecting the rod and body end bearings for rotation in 
the damper seat and for misaligned slippage marks; repetitively 
inspecting the rod end broached ring nut; and repetitively inspecting 
the bearing friction torque value of the body and rod ends, and the MR 
damper anti-rotation block. Depending on the results of the various 
inspections, the NPRM proposed to require removing a part from service 
or replacing a part. For an affected helicopter with MR damper P/N 
3G6220V01351 or 3G6220V01352 installed, the NPRM also proposed to 
require inspecting each rod end to determine if special washer P/N 
3G6220A05052 is installed, and depending on the results, aligning the 
rod ends and broached rings, replacing any broached ring that cannot be 
aligned, inspecting the broached rings for wear and damage, and 
replacing the broached ring and installing a special washer. Lastly, 
the NPRM proposed to require installing MR damper P/N 3G220V01353, 
prohibit installing MR damper P/N 3G6220V01351 and P/N 3G6220V01352 on 
any helicopter, and allow the installation of MR damper P/N 3G220V01353 
to constitute terminating action for all of the proposed repetitive 
required actions.
    The NPRM was prompted by EASA AD 2018-0112R1, dated June 4, 2018 
(EASA AD 2018-0112R1), which is the most recent of a series of ADs 
issued by EASA, the Technical Agent for the Member States of the 
European Union, to correct an unsafe condition for certain Leonardo 
S.p.A. Helicopters (formerly Finmeccanica S.p.A., Helicopter Division 
(FHD), AgustaWestland S.p.A., Agusta S.p.A.), AgustaWestland 
Philadelphia Corporation (formerly Agusta Aerospace Corporation) Model 
AB139 and AW139 helicopters. EASA advises of multiple failures of MR 
damper P/Ns 3G6220V01351 and 3G6220V01352. EASA states that in some 
cases these failures occurred at the eye end and body lugs resulting in 
disconnection of the MR damper in-flight. EASA further states that a 
combination of factors, including cracks on the MR damper rod end and 
body end and in-service failure of the eye end and body lugs may have 
contributed to the MR damper disconnections. Information issued by 
Leonardo Helicopters advises of MR damper cracking, loose rod ends, 
bearing rotation in the damper seat, and damage, incorrect engagement, 
and misalignment of the lag damper broached ring nut, particularly the 
broached ring teeth and the damper piston slots.
    EASA states that this condition could result in loss of the lead-
lag damping function of the MR blade, damage to adjacent critical rotor 
components, and subsequent reduced control of the helicopter. 
Accordingly, EASA AD 2018-0112R1 requires various one-time and 
repetitive inspections of the MR damper, a torque check of the damper 
body end, and replacing any MR damper with a crack or that fails the 
torque check. EASA AD 2018-0112R1 also requires replacing MR damper P/N 
3G6220V01351 and 3G6220V01352 with P/N 3G220V01353, as additional tests 
determined that MR damper P/N 3G220V01353 does not need to be subject 
to inspections for cracks, provided it is removed from service before 
it reaches its retirement life.

Actions Since the NPRM Was Issued

    Since the NPRM was issued, the FAA identified an action required by 
EASA AD 2018-0112R1 that was inadvertently omitted in the NPRM and 
incorrect thresholds for different actions proposed in the NPRM. The 
NPRM omitted the one-time dye penetrant inspection for any MR dampers 
that have accumulated 300 or more total hours time-in-service (TIS). 
The NPRM also stated incorrect thresholds to inspect each rod end 
bearing and body end bearing for rotation. The NPRM proposed to require 
those inspections based on the total hours TIS accumulated by the MR 
damper, when the thresholds for those inspections should have been 
based on the total hours TIS accumulated by the rod end and body end, 
independently. This SNPRM makes those updates.
    The NPRM also inadvertently omitted the option to accomplish an 
eddy current inspection for some inspections. This SNPRM adds that 
alternative for those inspections.
    Lastly, this SNPRM utilizes the FAA's new practice of proposing to 
incorporate EASA AD 2018-0112R1 by reference.

Comments

    The FAA gave the public the opportunity to participate in 
developing this proposed AD. The FAA has considered the comment 
received.

Request To Reduce the Applicability

    One commenter requested removing MR damper P/N 3G6220V01353 from 
the applicability. The commenter stated that the only requirement in 
this AD for that P/N is to reduce the torque on the body end of the MR 
damper and that procedures for this are available in the Interactive 
Electronic Technical Publications (IETP). The commenter asked if the 
intent is to capture any MR damper P/N 3G6220V01353 installed prior to 
the current IETP revisions with an incorrect torque. The commenter 
further stated that part II of Leonardo Helicopters Alert Service 
Bulletin No. 139-452, Revision B, dated April 10, 2018 (ASB 139-452 Rev 
B), is not applicable to MR damper P/N 3G6220V01353.
    The FAA disagrees. The commenter is correct that part II of ASB 
139-452 Rev B is not applicable to MR damper P/N 3G6220V01353; however, 
part I of ASB 139-452 Rev B, which specifies procedures to reduce the 
torque of the nut on the bolt attaching each MR damper to the MR hub, 
is applicable to MR damper P/N 3G6220V01353. Additionally, the FAA 
appreciates that while the procedures to reduce that torque may now be 
available in the IETP, not all operators are required to accomplish 
manufacturer's maintenance procedures. Where the FAA has determined 
that procedures, including manufacturer's maintenance procedures, are 
necessary to correct an unsafe condition, the FAA must issue an AD.

FAA's Determination

    These products have been approved by the aviation authority of 
another country, and are approved for operation in the United States. 
Pursuant to the bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in EASA AD 
2018-0112R1 referenced above. The FAA is proposing this AD after 
evaluating all the relevant information and determining the unsafe 
condition described previously is likely to exist or develop in other 
products of these same type designs.
    Certain changes described above expand the scope of the NPRM. As a 
result, the FAA has determined that it is necessary to reopen the 
comment period to provide additional opportunity for the public to 
comment on this SNPRM.

[[Page 51024]]

Related Service Information Under 1 CFR Part 51

    EASA AD 2018-0112R1 requires reducing the installation torque of 
the bolts affixing each affected MR damper to the MR hub. For certain 
affected MR dampers, EASA AD 2018-0112R1 requires a one-time dye 
penetrant inspection of the rod and body ends, and a repetitive 
detailed visual inspection of the rod and body ends. EASA AD 2018-
0112R1 allows an eddy current inspection as an alternative to those 
inspections. For certain affected MR dampers, EASA AD 2018-0112R1 also 
requires repetitively inspecting the rod and body end bearings for 
rotation, visually inspecting the rod end broached ring nut, 
accomplishing a bearing friction inspection of the body and rod end 
bearings, and a detailed inspection of the anti-rotation block. EASA AD 
2018-0112R1 also requires a one-time visual inspection of certain 
affected MR damper rod end installations and a torque check of the MR 
damper broached ring nut. For certain affected MR dampers, EASA AD 
2018-0112R1 requires replacing any special washer P/N 3G6220A05051 with 
a new washer P/N 3G6220A05052. If there is a crack or damage detected 
in any inspection, EASA AD 2018-0112R1 requires contacting Leonardo 
and, if the discrepancy is confirmed, replacing the MR damper. EASA AD 
2018-0112R1 also requires corrective actions if any discrepancy is 
detected in the inspections for rotation, friction, and torque. EASA AD 
2018-0112R1 allows installing MR damper P/N 3G6220V01353 on a 
helicopter, provided that it is installed using the correct torque 
values. Lastly, EASA AD 2018-0112R1 prohibits installing MR damper P/N 
3G6220V01351 and P/N 3G6220V01352 on any helicopter.
    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.

Proposed AD Requirements of This SNPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2018-0112R1, 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 Proposed AD and the EASA AD.''

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2018-0112R1 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2018-0112R1 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2018-0112R1 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 2018-
0112R1. Service information referenced in EASA AD 2018-0112R1 for 
compliance will be available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0283 after the FAA final 
rule is published.

Differences Between This Proposed AD and the EASA AD

    Where EASA AD 2018-0112R1 requires the compliance time of after the 
last flight (ALF) of the day inspection, this proposed AD would require 
the compliance time of before the first flight of the day. Some 
compliance times in EASA AD 2018-0112R1 are on condition of part 
removal or replacement, whereas this proposed AD would not include 
those compliance times. EASA AD 2018-0112R1 requires a torque check of 
the MR damper broached ring nut, whereas this proposed AD would require 
a torque inspection instead to clarify that the action must be 
accomplished by a mechanic that meets the requirements of 14 CFR part 
65 subpart D. EASA AD 2018-0112R1 requires making sure that there are 
no scratches or dents on the rod end, however it does not state 
corrective action for this requirement; this proposed AD would require 
removing the rod end from service if there is a scratch or dent on the 
rod end. Where EASA AD 2018-0112R1 requires contacting Leonardo and 
replacing the MR damper with a serviceable part, this proposed would 
require replacing or removing parts from service instead. Where EASA AD 
2018-0112R1 requires accomplishing applicable corrective action(s) as 
specified in, and in accordance with, the instructions in service 
information, this proposed AD would require removing parts from service 
for some of the corrective actions instead. Where EASA AD 2018-0112R1 
requires a one-time dye penetrant inspection of certain rod ends when 
installed, this proposed AD would not. Instead, this proposed AD would 
prohibit installing certain rod ends that are not marked with a black 
dot and therefore have not been inspected.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 126 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 proposed AD.
    Performing the MR damper inspections would take about 24 work-
hours, for an estimated cost of $2,040 per helicopter and $257,040 for 
the U.S. fleet, per inspection cycle.
    Replacing a rod end would take about 3 work-hours and parts would 
cost about $500, for an estimated cost of $755 per rod end. Replacing a 
broached ring and broached ring nut would take about 3 work-hours and 
parts would cost about $125, for an estimated cost of $380 per broached 
ring and broached ring nut. Replacing an anti-rotation block would take 
about 3 work-hours and parts would cost about $50, for an estimated 
cost of $305 per anti-rotation block. Replacing an MR damper would take 
about 2 work-hours and parts would cost about $18,000, for an estimated 
cost of $18,170 per MR damper.

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

[[Page 51025]]

that authority because it addresses an unsafe condition that is likely 
to exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
     For the reasons discussed above, I certify this proposed 
regulation:
     (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
     (2) Would not affect intrastate aviation in Alaska, and
     (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

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

    Leonardo S.p.a.: Docket No. FAA-2020-0283; Project Identifier 
2018-SW-045-AD.

(a) Comments Due Date

    The FAA must receive comments by October 29, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Leonardo S.p.a. Model AB139 and AW139 
helicopters, certificated in any category, as identified in European 
Aviation Safety Agency (now European Union Aviation Safety Agency) 
(EASA) AD 2018-0112R1, dated June 4, 2018 (EASA AD 2018-0112R1).

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

(e) Unsafe Condition

    This AD was prompted by reports of failed main rotor (MR) 
dampers. The FAA is issuing this AD to address a crack in an MR 
damper. The unsafe condition, if not addressed, could result in 
seizure of the MR damper, detachment of the MR damper in-flight, and 
subsequent loss of control of the helicopter.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2018-0112R1.

(h) Exceptions to EASA AD 2018-0112R1

    (1) Where EASA AD 2018-0112R1 requires compliance in terms of 
flight hours (FH), this AD requires using hours time-in-service 
(TIS).
    (2) Where EASA AD 2018-0112R1 refers to FH accumulated by a part 
since new (first installation on a helicopter) or since overhaul, 
this AD requires using total hours TIS.
    (3) Where EASA AD 2018-0112R1 refers to its effective date; May 
10, 2016 (the effective date of EASA AD 2016-0087, dated May 3, 
2016); July 28, 2016 (the effective date of EASA AD 2016-0140, dated 
July 14, 2016); or September 11, 2017 (the effective date of EASA AD 
2017-0160, dated August 28, 2017), this AD requires using the 
effective date of this AD.
    (4) Where EASA AD 2018-0112R1 requires the compliance time of 
during an ``after the last flight (ALF) of the day inspection,'' 
this AD requires the compliance time of before the first flight of 
the day.
    (5) Where the service information referenced in EASA AD 2018-
0112R1 specifies using a magnifying glass, this AD requires using a 
5X or higher power magnifying glass.
    (6) Where the service information referenced in EASA AD 2018-
0112R1 specifies discarding parts, this AD requires removing those 
parts from service.
    (7) Where paragraph (2) of EASA AD 2018-0112R1 requires 
compliance within 30 FH after 10 May 2016 (the effective date of 
EASA AD 2016-0087, dated May 3, 2016), or at the first MR damper 
removal, whichever occurs first, for a MR damper that has 
accumulated 300 or more FH, this AD requires compliance within 30 
hours TIS after the effective date of this AD for a MR damper that 
has accumulated 300 or more total hours TIS.
    (8) This AD does not require the actions required by paragraph 
(3) of EASA AD 2018-0112R1.
    (9) Where paragraph (8) of EASA AD 2018-0112R1 refers to having 
a serial number (S/N) specified in Part V of FHD BT 139-450, this AD 
requires the actions of that paragraph for helicopters with an MR 
damper part number (P/N) 3G6220V01351 or 3G6220V01352 with an S/N up 
to MCR8086 inclusive, installed, that has accumulated less than 600 
total hours TIS.
    (10) Where paragraph (10) of EASA AD 2018-0112R1 refers to 
having an S/N specified in in Part VII of FHD BT 139-450, this AD 
requires the actions of that paragraph for helicopters with:
    (i) MR damper P/N 3G6220V01351 or 3G6220V01352 with an S/N up to 
MCR8764 inclusive, and with rod end P/N M006-01H004-041, -045, or -
053, installed, except MR dampers confirmed of having 60-80 Nm 
applied and MR dampers marked with ``BT 139-446 Part II'' or ``BT 
139-446 Part III'' on the logcard; or
    (ii) MR damper P/N 3G6220V01351 or 3G6220V01352 that has had the 
damper rod end assembly removed before the issuance of ``BT 139-
446'' installed, even if it has an S/N higher than MCR8764 or it has 
been confirmed of having 60-80 Nm applied.

    Note 1 to paragraph (h)(10):  MR dampers confirmed of having 60-
80 Nm applied are listed in Table 1 (two pages) of Annex A, of 
Leonardo Helicopters Alert Service Bulletin No. 139-450, Revision D, 
dated May 28, 2019.

    (11) Where paragraph (10) of EASA AD 2018-0112R1 requires a 
torque check, this AD requires a torque inspection.
    (12) Where the service information referenced in paragraph (10) 
of EASA AD 2018-0112R1 specifies making sure that there are not 
scratches or dents on the rod end, this AD requires, before further 
flight, removing the rod end from service if there is a scratch or 
dent on the rod end.
    (13) Where paragraph (12) of EASA AD 2018-0112R1 requires 
contacting Leonardo and replacing the MR damper with a serviceable 
part, this AD does not. This AD requires the following:
    (i) If there is a crack in an MR damper body end, before further 
flight, replace the MR damper.
    (ii) If there is a crack in an MR damper rod end, before further 
flight, remove the MR damper rod end from service.
    (iii) If there is damage in any teeth of a rod end broached ring 
nut or damper piston slot, or if the engagement or alignment is not 
correct, before further flight, remove the rod end broached ring nut 
from service.
    (14) Paragraph (13) of EASA AD 2018-0112R1 requires 
accomplishing the applicable corrective action(s) as specified in, 
and in accordance with, the instructions of FHD BT 139-450 or FHD BT 
139-452, as applicable, except where:
    (i) If there is any bearing seat rotation or misaligned slippage 
mark in the MR damper rod end, this AD requires, before further 
flight, removing the MR damper rod end from service.
    (ii) If the MR damper rod end torque value is more than 30.0 Nm 
(265.5 in lb), this AD requires, before further flight, removing the 
MR damper rod end from service.
    (iii) If any MR damper anti-rotation block dimension measurement 
exceeds allowable limits, this AD requires, before further flight, 
removing the anti-rotation block from service.
    (15) This AD does not mandate compliance with the ``Remarks'' 
section of EASA AD 2018-0112R1.

(i) Parts Prohibition

    As of the effective date of this AD, do not install an MR damper 
rod end P/N M006-

[[Page 51026]]

01H004-041, M006-01H004-045, or M006-01H004-053 on any helicopter, 
unless it is marked with a black dot indicating that it has passed 
inspections specified by Leonardo Helicopters BT 139-450.

(j) No Reporting Requirement

    Although the service information referenced in EASA AD 2018-
0112R1 specifies to submit certain information to the manufacturer, 
this AD does not include that requirement.

(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)(2) of 
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#dfe6f29e898cf29e968df2e8eceff29e92909c9fb9bebef1b8b0a9"><span class="__cf_email__" data-cfemail="4b72660a1d18660a0219667c787b660a0604080b2d2a2a652c243d">[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) Related Information

    (1) For EASA AD 2018-0112R1, contact EASA, Konrad-Adenauer-Ufer 
3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
<a href="/cdn-cgi/l/email-protection#e7a6a394a782869486c9829295889786c98292"><span class="__cf_email__" data-cfemail="88c9ccfbc8ede9fbe9a6edfdfae7f8e9a6edfd">[email protected]</span></a>; internet www.easa.europa.eu. You may view this 
material 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 
(817) 222-5110. This material may be found in the AD docket at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2020-0283.
    (2) For more information about this AD, contact Matt Fuller, AD 
Program Manager, General Aviation & Rotorcraft Unit, Airworthiness 
Products Section, Operational Safety Branch, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
<a href="/cdn-cgi/l/email-protection#cea3afbabaa6abb9e0a8bba2a2abbc8ea8afafe0a9a1b8"><span class="__cf_email__" data-cfemail="87eae6f3f3efe2f0a9e1f2ebebe2f5c7e1e6e6a9e0e8f1">[email protected]</span></a>.

    Issued on September 7, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-19607 Filed 9-13-21; 8:45 am]
BILLING CODE 4910-13-P


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