preamble attached >>>
ADs updated daily at www.Tdata.com
2021-02-03 LEONARDO S.P.A: Amendment 39-21386; Docket No. FAA-2020-0503; Product Identifier 2018-SW-006-AD.
(a) APPLICABILITY

    This airworthiness  directive (AD)  applies to  Leonardo S.p.a.  Model
    AW189 helicopters,  certificated in  any category,  with a  main rotor
    (MR) damper part number (P/N) 4F6220V00251 installed.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as a crack in an MR damper, which
    if not detected  and  corrected,  could  lead to loss  of the lead-lag
    damping  function of  the MR  blade,  resulting  in damage  of the  MR
    damper, detachment of the MR damper in-flight, and subsequent loss  of
    control of the helicopter.

(c) EFFECTIVE DATE

    This AD becomes effective April 1, 2021.

(d) COMPLIANCE

    You are  responsible for  performing each  action required  by this AD
    within  the  specified  compliance time  unless  it  has already  been
    accomplished prior to that time.

(e) REQUIRED ACTIONS

(1) Within 10 hours time-in-service (TIS), reduce the torque of the nut on
    the  bolt  attaching  each  MR  damper  to  the  MR  hub  by following
    paragraphs 4 through 7 of the Accomplishment Instructions, Part I,  of
    Leonardo Helicopters Alert Service  Bulletin No. 189-102, Revision  A,
    dated December 21, 2017 (ASB 189-102).

(2) Within 30 hours TIS or before the MR damper body end (body end) accum-
    ulates  500  hours  TIS, whichever  occurs  later,  and thereafter  at
    intervals not to exceed 500 hours TIS, replace the MR damper.

(3) Within 30 hours TIS,  before the MR damper accumulates  300 hours TIS,
    or within  300 hours  TIS since  the last  overhaul, whichever  occurs
    later, dye penetrant inspect using a 5X power magnifying glass or eddy
    current inspect each MR  damper rod end (rod  end) and body end  for a
    crack in  the areas  depicted in  Figure 2  of Finmeccanica Bollettino
    Tecnico No. 189-080, Revision A, dated July 15, 2016 (BT 189-080).

(i) If there is a crack on the body end,  before  further  flight, replace
    the MR damper.

(ii) If there is a crack on the rod end,  before  further  flight, replace
     the rod end and, within 300 hours TIS, dye penetrant or eddy  current
     inspect the rod end for a  crack as described in paragraph (e)(3)  of
     this AD.

(iii) If there are no cracks, before further flight,  mark the rod end and
      body end  with a dot of black polyurethane paint as shown  in Figure
      13 of BT 189-080.

(iv) Thereafter, before the first flight of each day, using a mirror and a
     magnifying glass  visually inspect  each rod  end and  body end for a
     crack in the areas  shown in Figure 14  of BT 189-080. If  there is a
     crack in the rod end, before further flight, replace the rod end.  If
     there is a crack on the body end, before further flight, replace  the
     MR damper.

(4) Within the compliance times listed in paragraphs (e)(4)(i) and (ii) of
    this  AD,  inspect each  rod  end bearing  and  body end  for  bearing
    rotation  in  the  damper seat.  An  example  of rotation  (misaligned
    slippage marks) is shown  in Figure 4 of  BT 189-080. If there  is any
    bearing rotation in  the rod end,  before further flight,  replace the
    rod end.  If there  is any  bearing rotation  in the  body end, before
    further flight, replace the MR damper.

(i) For MR dampers that have accumulated less than 300 hours TIS since new
    or since  the last  overhaul, within  30 hours  TIS and  thereafter at
    intervals not to exceed 10 hours TIS.

(ii) For MR dampers that have accumulated 300  or more hours TIS since new
     or since the last overhaul, within 5 hours TIS and thereafter  before
     the first flight of each day.

(5) For helicopters  with an MR damper  with a serial number (S/N) MCR0001
    through MCR0154 and MCR0174 through  MCR0195, within 30 hours TIS  and
    thereafter at intervals not to exceed 20 hours TIS until the MR damper
    has  accumulated  600  hours  TIS,  visually  inspect  each  MR damper
    broached ring nut for  broken teeth, proper engagement,  and alignment
    as depicted in  Figure 5 and  shown in Figures  6, 7, and  8 of BT 189
    -080. If there is a broken tooth, improper engagement, or misalignment
    of the broached ring nut,  before further flight, remove from  service
    the rod end and broached ring nut.

(6) Within 50 hours TIS and thereafter  at  intervals  not  to  exceed 100
    hours TIS:

(i) Rotate the body end around the damper axis  to  put it near the middle
    position and determine the bearing  friction torque value of the  body
    end, using as a reference Figure 11 of BT 189-080.

Note 1 to Paragraph (e)(6)(i):  Applying too much force while rotating the
body end around the damper axis may cause damage.

(A) If the torque value of the body end is more than 30.0 Nm (265.5 in lb)
    before further flight, replace the MR damper.

(B) If the torque value of the body end is 30.0 Nm (265.5 in lb)  or less,
    determine the bearing friction torque value of each rod end, using  as
    a reference Figure 11  of BT 189-080. If  the torque value of  the rod
    end is more than 30.0 Nm (265.5 in lb), before further flight, replace
    the rod end.

(ii) Inspect each MR damper anti-rotation block for wear by following para
     -graphs 4.3 through 4.3.6 of the Compliance Instructions, Part VI, of
     BT 189-080. If there is  wear, before further flight, replace  the MR
     damper anti-rotation block.

(7) Within 50 hours TIS:

(i) On each MR damper replace special washer P/N 3G6220A05051 with special
    washer P/N 3G6220A05052.

(ii) For helicopters with an MR damper with a S/N MCR0001 through MCR0041,
     MCR0043,  MCR0045 through MCR0151,  MCR0153 through MCR0157,  MCR0159
     through MCR 0179 and MCR0185 through MCR0370; and for MR dampers with
     a rod end P/N M006-01H004-045  or  P/N M006-01H004-053 installed,  do
     the following:

(A) Inspect each broached ring for wear,  bent teeth,  missing teeth,  and
    stripped  threads.  Pay particular  attention  to the  four  pins that
    engage the  piston grooves.  If there  is any  wear or  damage to  the
    broached ring, before further flight, remove from service the broached
    ring.  An example of an acceptable broached ring is shown in Figure 4,
    Annex A, of BT 189-080.

(B) Align each rod end and broached ring  by  applying  a  torque of 60 Nm
    (531 in lb) to 80 Nm (708 in lb).  If  the  rod end  and broached ring
    cannot be aligned, before further flight, replace the broached ring.

(8) Except for MR dampers with a S/N MCR0042, MCR0044,  MCR0152,  MCR0158,
    and  MCR0180  through  MCR0184,  do  not  install  an  MR  damper  P/N
    4F6220V00251 on  any helicopter  unless the  MR damper  has passed the
    requirements in paragraph (e)(7)(ii) of this AD.

(f) CREDIT FOR PREVIOUS ACTIONS

(1) Actions accomplished  before the effective date of this AD  in accord-
    ance  with  the  Compliance  Instructions,  Part  II,  of Finmeccanica
    Bollettino Tecnico No. 189-069, dated February 12, 2016 (BT  189-069),
    are  considered  acceptable  for  compliance  with  the  corresponding
    actions in paragraph (e)(7)(i) of this AD.

(2) Actions accomplished  before the effective date of this AD  in accord-
    ance with the  Compliance Instructions, Part  III, of BT  189-069, are
    considered acceptable for compliance with the corresponding actions in
    paragraph (e)(7)(ii) of this AD.

(g) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Rotorcraft Standards Branch,  FAA,  may approve AMOCs for
    this AD. Send your proposal to: Matt Fuller, AD Program Manager, Oper-
    ational Safety Branch,  Airworthiness Products Section,  General Avia-
    tion & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177
    telephone 817-222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate
    or under 14 CFR part 91,  subpart K, the FAA suggests that  you notify
    your  principal  inspector,  or  lacking  a  principal  inspector, the
    manager of the local  flight standards district office  or certificate
    holding district office before  operating any aircraft complying  with
    this AD through an AMOC.

(h) ADDITIONAL INFORMATION

(1) Finmeccanica Bollettino Tecnico No. 189-069,  dated February 12, 2016,
    which is not incorporated  by reference,  contains additional informa-
    tion about the subject of this AD. For service information  identified
    in this AD, contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head
    of Airworthiness, Viale G.Agusta  520, 21017 C.Costa di  Samarate (Va)
    Italy;   telephone   +39-0331-225074;  fax   +39-0331-229046;   or  at
    https://www.leonardocompany.com/en/home. You  may view  the referenced
    service  information  at  the FAA,  Office  of  the Regional  Counsel,
    Southwest Region, 10101  Hillwood Pkwy., Room  6N-321, Fort Worth,  TX
    76177.

(2) The subject of this AD is addressed in European Aviation Safety Agency
    (now European Union  Aviation Safety Agency)  (EASA)  No. 2016-0145R1,
    dated  January 17, 2018.  You may view the EASA AD  on the internet at
    https://www.regulations.gov in Docket No. FAA-2020-0503.

(i) SUBJECT

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

(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) Finmeccanica Bollettino Tecnico No. 189-080 Revision A, dated July 15,
    2016.

(ii) Leonardo Helicopters Alert Service Bulletin No. 189-102,  Revision A,
     dated December 21, 2017.

(3) For service information identified in this AD, contact Leonardo S.p.a.
    Helicopters, Emanuele Bufano,  Head of Airworthiness,  Viale G. Agusta
    520, 21017 C. Costa di Samarate (Va) Italy; telephone +39-0331-225074;
    fax +39-0331-229046; or at https://www.leonardocompany.com/en/home.

(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 817-222-5110.

(5) You may view  this service information that is incorporated  by refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material at NARA, email fedreg
    .legal@nara.gov,  or go to: https://www.archives.gov/federal-register/
    cfr/ibr-locations.html.

Issued on January 6, 2021. Lance T. Gant, Director, Compliance & Airworth-
iness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Matt Fuller,  AD Program Manager,  Opera-
tional Safety Branch,  Airworthiness Products Section,  General Aviation &
Rotorcraft Unit, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone
817-222-5110; email matthew.fuller@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0503; Product Identifier 2018-SW-006-AD; Amendment
39-21386; AD 2021-02-03]
RIN 2120-AA64

Airworthiness Directives; Leonardo S.p.a. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Leonardo S.p.a. (Leonardo) Model AW189 helicopters. This AD
requires various repetitive inspections of the
main rotor (MR) damper. This AD was prompted by reports of in-service
MR damper failures and the development of an improved MR damper. This
condition, if not corrected, could lead to loss of the lead-lag damping
function of the MR blade, possibly resulting in damage to adjacent
critical rotor components and subsequent loss control of the
helicopter. The actions of this AD are intended to address the unsafe
condition on these products.

DATES: This AD is effective April 1, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of April 1, 2021.

ADDRESSES: For service information identified in this final rule
contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of
Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va)
Italy; telephone +39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view the referenced
service information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is
also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0503.

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-
0503; 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 AD, the European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD, any service information that is
incorporated by reference, any comments received, and other
information. The street 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.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager,
Operational Safety Branch, Airworthiness Products Section, General
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817-222-5110; email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Leonardo Model AW189
helicopters with MR damper part number (P/N) 4F6220V00251 installed.
The NPRM published in the Federal Register on May 20, 2020 (85 FR
30664). The NPRM proposed to require reducing the installation torque
of the nuts on the bolts attaching the MR damper to the MR hub. The
NPRM also proposed to require, at specified intervals, replacing the
affected MR damper; dye penetrant or eddy current inspecting the rod
end and body end of each MR damper for a crack, visually inspecting the
rod end and body end of each MR damper for a crack, and replacing any
cracked MR damper. For certain helicopters, the NPRM also proposed to
require inspecting each rod end and body end bearing for rotation, and
replacing the rod end or MR damper as applicable if there is any
rotation; inspecting the lag damper broached ring nut for damage,
correct engagement, and alignment and removing the rod end and broached
ring nut from service if any of those conditions exist. For all
helicopters, the NPRM proposed to require, at specified intervals,
inspecting the bearing friction torque of each MR damper body end and
rod end, and replacing the MR damper if the torque value exceeds 30.0
Nm (265.5 lb in); inspecting the MR damper anti-rotation block for wear
and replacing the anti-rotation block if there is wear beyond
acceptable limits; and replacing each special washer P/N 3G6220A05051
with special washer P/N 3G6220A05052. For certain MR dampers, the NPRM
proposed to require inspecting the broached ring for damage and
alignment, removing the broached ring from service if there is damage,
and replacing the broached ring if the rod end and broached ring cannot
be aligned. Finally, the NPRM proposed to require inspecting certain
serial-numbered MR dampers for correct torque of the broached ring
prior to installation on any helicopter. The proposed requirements were
intended to detect a crack in an MR damper, which if not detected and
corrected, could lead to loss of the lead-lag damping function of the
MR blade, resulting in damage of the MR damper, detachment of the MR
damper in-flight, and subsequent loss of control of the helicopter.
The NRPM was prompted by EASA AD No. 2016-0145R1, dated January 17,
2018 (EASA AD 2016-0145R1), issued by EASA, which is the Technical
Agent for the Member States of the European Union, to correct an unsafe
condition for Leonardo Model AW189 helicopters with MR damper P/N
4F6220V00251 installed. EASA advises that a MR damper failed, which
resulted in complete seizure of the body end lug and an in-flight
disconnection of the damper. EASA states that a combination of factors
may have contributed to the MR damper disconnection, and 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. The contributing factors include
cracks, slippage marks, damaged broach ring teeth, and loss of torque.
According to EASA, the AW189 MR damper is a similar design to the
MR dampers installed on Model AW139 helicopters, where multiple MR
damper failures have been reported involving the body end lug, the eye
end lug, and the rod end. To correct this condition, EASA issued a
series of superseded and revised ADs to require repetitive inspections
of certain MR dampers, and similar corrective actions as those for
Model AW139 helicopters. EASA AD 2016-0145R1 requires various one-time
and repetitive inspections of the MR damper, a torque check of the body
end, and replacing any MR damper with a crack or that fails the torque
check. EASA AD 2016-0145R1 also allows installation of a new MR damper,
P/N 8G6220V00151, as an optional terminating action for the repetitive
inspections.

Comments

The FAA gave the public the opportunity to participate in
developing this final rule, but the FAA did not receive any comments on
the NPRM or on the determination of the cost to the public.

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 AD. The FAA is issuing this AD after
evaluating all of the information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design and that air safety and the public
interest require adopting these AD requirements as proposed.

Differences Between This AD and the EASA AD

The EASA AD requires contacting the manufacturer under certain
conditions, while this AD does not.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Finmeccanica Bollettino Tecnico No. 189-080,
Revision A, dated July 15, 2016, which contains procedures for visual
and dye penetrant inspections of the MR damper for cracks and for
verifying the torque of the damper body ends.
The FAA also reviewed Leonardo Helicopters Alert Service Bulletin
No. 189-102, Revision A, dated December 21, 2017, which contains
procedures for installing an MR damper with reduced torque values and
specifies replacing MR damper P/N 4F6220V00251 with new MR damper P/N
8G6220V00151.
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 the ADDRESSES section.

Other Related Service Information

The FAA reviewed Finmeccanica Bollettino Tecnico No. 189-069, dated
February 12, 2016, which contains procedures for installing a special
washer on the MR damper rod end, modifying the installation torque of
the MR damper, and inspecting the rod end bearings.

Costs of Compliance

The FAA estimates that this AD affects 3 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Adjusting the tightening torque takes about 10 work-hours, for an
estimated cost of $850 per helicopter and $2,550 for the U.S. fleet.
Replacing an MR damper takes about 2 work-hours, and parts cost
about $18,000, for an estimated cost of $18,170 per MR damper.
Performing a dye penetrant or eddy current inspection of the MR
damper takes about 8 work-hours, for an estimated cost of $680 per
helicopter and $2,040 for the U.S fleet.
Visually inspecting the rod ends and body ends takes about 0.5
hour, for an estimated cost of $43 per helicopter and $129 for the U.S.
fleet, per inspection cycle.
Inspecting the rod ends and body ends for bearing rotation takes
about 0.5 hour, for an estimated cost of $43 per helicopter and $129
for the U.S. fleet, per inspection cycle.
Inspecting the broached ring nut takes about 0.5 hour, for an
estimated cost of $43 per helicopter and $129 for the U.S. fleet, per
inspection cycle.
Inspecting for bearing friction takes about 2 hours, for an
estimated cost of $170 per helicopter and $510 for the U.S fleet, per
inspection cycle.
Inspecting the broached ring teeth for proper alignment and
applying torque takes about 8 work-hours, for an estimated cost of $680
per helicopter and $2,040 for the U.S fleet.
Replacing a rod end takes about 3 work-hours and parts cost about
$500, for an estimated cost of $755 per rod end.
Replacing a broached ring takes about 3 work-hours and parts cost
about $100, for an estimated cost of $355 per broached ring.
Replacing a broached ring nut takes about 3 work-hours and parts
cost about $125, for an estimated cost of $380 per broached ring nut.
Replacing an anti-rotation block takes about 3 work-hours and parts
cost about $50, for an estimated cost of $305 per anti-rotation block.

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 helicopters 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.

Adoption of 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

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]

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