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ADs updated daily at www.Tdata.com
PROPOSED AD LEONARDO S.P.A.: Docket No. FAA-2020-0283; Product Identifier 2018-SW-045-AD.
(a) APPLICABILITY

    This AD applies to Leonardo S.p.A. Model AB139 and AW139  helicopters,
    certificated in any  category, all serial  numbers (S/Ns) except  S/Ns
    31004, 31007, and  41237, with a  main rotor (M/R)  damper part number
    (P/N) 3G6220V01351, 3G6220V01352, or 3G6220V01353 installed.

(b) UNSAFE CONDITION

    This AD  defines the  unsafe condition  as a  crack in  an M/R damper,
    which if not  detected and corrected,  could result in  seizure of the
    M/R damper,  detachment of  the M/R  damper in-flight,  and subsequent
    loss of control of the helicopter.

(c) COMMENTS DUE DATE

    The FAA must receive comments by June 1, 2020.

(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) For helicopters with M/R damper P/N 3G6220V01351 or 3G6220V01352 with-
    in  5  hours time-in-service  (TIS)  and thereafter  before  the first
    flight of each day:

(i) For helicopters with an M/R damper rod end (rod end)  that has accumu-
    lated 300  or more  hours TIS  since new  or since  the last overhaul,
    using a  mirror and  a 5X  or higher  power magnifying glass, visually
    inspect each rod end  for a crack in  the areas shown in  Figure 19 of
    Leonardo Helicopters Alert Service  Bulletin No. 139-450, Revision  C,
    dated  April 10, 2018  (ASB  139-450).  If  there is  a crack,  before
    further flight, remove from service the rod end.

(ii) For  helicopters  with an M/R damper body end  (body end)  that  have
     accumulated  more  than 1,200  hours  TIS since  new,  before further
     flight, remove from service the body end.

(iii) For  helicopters  with  a body end  that has accumulated 300 or more
      hours TIS and less than 1,200 hours TIS since new or since the  last
      overhaul, using a mirror and a 5X or higher power magnifying  glass,
      inspect each body end for a crack in the areas shown in Figure 19 of
      ASB 139-450. If there is a crack, before further flight, replace the
      M/R damper.

(2) For all helicopters, within 10 hours TIS, reduce the torque of the nut
    on the  bolt attaching  each M/R  damper to  the M/R  hub. Using  as a
    reference Figure 1 of Leonardo Helicopters Alert Service Bulletin  No.
    139-452, Revision B, dated April  10, 2018 (ASB 139-452), on  the body
    end of each M/R damper, remove the cotter pin from service, remove the
    nut from the bolt, and clean the threads of the bolt. Install the  nut
    and apply a torque  of 74.6 Nm to  88 Nm (55 lbf  ft to 64.9 lbf  ft).
    Install  a  new cotter  pin  and apply  corrosion  inhibitor (C002  or
    equivalent) to the cotter pin, nut, and washer.

(3) For  helicopters  with  M/R  damper  P/N 3G6220V01351 or 3G6220V01352,
    within 30 hours TIS, before the M/R damper accumulates 300 hours  TIS,
    or within  300 hours  TIS since  the last  overhaul, whichever  occurs
    later, inspect  each rod  end and  body end  for a  crack in the areas
    shown in Figures 1 through 6 of ASB 139-450 by either performing a dye
    penetrant inspection using  a 5X or  higher power magnifying  glass or
    using  an  eddy  current  inspection  method  performed  by  personnel
    qualified to at least Level 2 per the National Aerospace Standard  410
    or equivalent requirements.

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

(ii) If there is a crack on the rod end,  before  further  flight,  remove
     from service the rod end.

(iii) If there is no crack,  before further flight,  mark the rod end  and
      body  end with  a dot  of black  polyurethane paint  as depicted  in
      Figure 7 of ASB 139-450.

(4) For helicopters with M/R damper P/N 3G6220V01351 or 3G6220V01352, per-
    form the  inspection in  paragraph (e)(4)(iii)  of this  AD within the
    compliance times listed in paragraphs (e)(4)(i) and (ii) of this AD:

(i) For M/R 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 until the M/R damper  accumulates
    up to 300 hours TIS; or

(ii) For M/R 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:

(iii) Inspect each rod end bearing  and  body end bearing  for rotation in
      the damper seat and for misaligned slippage marks as shown in Figure
      9  of  ASB  139-450.  If  there  is  any  bearing  seat  rotation or
      misaligned  slippage mark  in the  rod end,  before further  flight,
      remove  from service  the rod  end.  If  there is  any bearing  seat
      rotation or misaligned slippage mark in the body end, before further
      flight, replace the M/R damper.

(5) For  helicopters  with  M/R  damper  P/N 3G6220V01351 or 3G6220V01352,
    within 30 hours TIS and thereafter at intervals not to exceed 20 hours
    TIS  until  the  M/R damper  has accumulated  600 hours  TIS, visually
    inspect  each  rod end  broached  ring nut  for  broken teeth,  proper
    engagement, and alignment as depicted in Figure 11 and shown in Figure
    12 of ASB 139-450. If there is a broken tooth, improper engagement, or
    misalignment of the broached ring nut, before next flight, remove from
    service the broached ring nut.

(6) For  helicopters  with  M/R  damper  P/N 3G6220V01351 or 3G6220V01352,
    within 50  hours TIS  and thereafter  at intervals  not to  exceed 100
    hours TIS:

(i) Inspect the bearing friction torque value of each body end as depicted
    in "View G" of Figure 18 of ASB 139-450.

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

(B) If the torque value of the body end is 30.0 Nm (265.5 in lb)  or less,
    inspect the bearing friction torque  value of the rod end  as depicted
    in "View H" of  Figure 18 of ASB  139-450. If the torque  value of the
    rod end is  more than 30.0  Nm (265.5 in  lb), before further  flight,
    remove from service the rod end.

(ii) Inspect each M/R damper anti-rotation block  for  wear  by  following
     paragraphs 4.3 through 4.3.7 of the Accomplishment Instructions, Part
     VI, of ASB 139-450. If  there is wear, before further  flight, remove
     from service the M/R damper anti-rotation block.

(7) For  helicopters  with  M/R  damper  P/N 3G6220V01351 or 3G6220V01352,
    within 50  hours TIS,  inspect each  rod end  to determine  if special
    washer P/N 3G6220A05052 is installed:

(i) If special washer P/N 3G6220A05052 is installed,  align  each  rod end
    and broached ring by applying a torque  of 63 Nm (558 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.

(ii) If special washer P/N 3G6220A05052 is not installed:

(A) Inspect each broached ring for wear and damage.  Pay particular atten-
    tion 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 ASB 139-450.

(B) Install special washer P/N 3G6220A05052 before further flight.

(8) For helicopters with M/R damper P/N 3G6220V01351 or 3G6220V01352,  and
    with M/R body end P/N M006-01H002-041or P/N M006-01H002-047 installed,
    within 30 hours  TIS, or before  the body end  accumulates 1,200 hours
    TIS, whichever occurs  later, replace the  M/R damper with  M/R damper
    P/N 3G6220V01353.

(9) After the effective date of this AD,  do not install an M/R damper P/N
    3G6220V01351 or P/N 3G6220V01352 on any helicopter.

(10) Replacing  each  M/R damper P/N 3G6220V01351 or P/N 3G6220V01352 with
     an M/R damper P/N 3G6220V01353 in accordance with the instructions of
     Part  II  of  ASB 139-452,  constitutes  terminating  action for  all
     repetitive actions required by this AD for that helicopter.

(f) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The  Manager,  Safety Management Section,  Rotorcraft Standards Branch
    FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller
    Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft
    Standards Branch, FAA, 10101 Hillwood Pkwy, Ft. Worth, TX 76177; tele-
    phone 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.

(g) ADDITIONAL INFORMATION

    The subject of this AD is addressed  in European Union Aviation Safety
    Agency (previously European Aviation Safety Agency) (EASA) AD No. 2018
    -0112R1, dated June 4, 2018.  You may view the EASA AD on the internet
    at https://www.regulations.gov in the AD Docket.

(h) SUBJECT

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

Issued  on  March 25,  2020.  Gaetano A.  Sciortino,  Deputy Director  for
Strategic  Initiatives,  Compliance  &  Airworthiness  Division,  Aircraft
Certification Service.

DATES: The FAA must receive comments on this proposed AD by June 1, 2020.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

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

Airworthiness Directives; Leonardo S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Leonardo S.p.A. (Leonardo) Model AB139 and AW139
helicopters. This proposed AD would require various inspections of the
main rotor (M/R) damper, and depending on the inspection results,
removing from service or replacing certain parts. This proposed AD
would also require reducing the torque of the M/R damper hub attachment
bolts, marking parts, installing a special washer, and installing a
certain part-numbered M/R damper and prohibit installing other part-
numbered M/R dampers. This proposed AD is prompted by reports of failed
M/R dampers. The proposed actions are intended to address the unsafe
condition on these products.

DATES: The FAA must receive comments on this proposed AD by June 1,
2020.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.

Fax: 202-493-2251.

Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.

Hand Delivery: Deliver to the "Mail" address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 proposed AD, the European Union Aviation Safety Agency (previously
European Aviation Safety Agency) (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 service information identified in this proposed 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.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110;
email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.

The FAA will file in the docket all comments received, as well as a
report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal,
the FAA will consider all comments received on or before the closing
date for comments. The FAA will consider comments filed after the
comment period has closed if it is possible to do so without incurring
expense or delay. The FAA may change this proposal in light of the
comments received.

Discussion

EASA, which is the Technical Agent for the Member States of the
European Union, has issued a series of superseded and revised ADs to
correct an unsafe condition for 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, all
serial numbers (S/Ns) except S/Ns 31004, 31007, and 41237. EASA advises
of multiple failures of M/R dampers part number (P/N) 3G6220V01351 and
3G6220V01352. EASA states that in some cases these failures occurred at
the eye end and body lugs resulting in disconnection of the M/R damper
in-flight. EASA further states that a combination of factors, including
cracks on the M/R damper rod end and body end and in-service failure of
the eye end and body lugs may have contributed to the M/R damper
disconnections. Information issued by Leonardo advises of M/R 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 M/R blade, damage to adjacent critical
rotor components, and subsequent reduced control of the helicopter.
EASA AD No. 2018-0112R1, dated June 4, 2018 (EASA AD 2018-0112R1),
which is the most recent EASA AD, requires various one-time and
repetitive inspections of the M/R damper, a torque check of the damper
body end, and replacing any M/R damper with a crack or that fails the
torque check. EASA AD 2018-0112R1 also requires replacing M/R damper P/N
3G6220V01351 and 3G6220V01352 with P/N 3G220V01353, as additional
tests determined that M/R 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.

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 about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other helicopters of
the same type designs.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Leonardo Helicopters Alert Service Bulletin No.
139-450, Revision C, dated April 10, 2018, which contains procedures
for visual and dye penetrant inspections of the M/R damper for cracks
and for verifying the torque of the M/R damper body ends (body ends).

The FAA also reviewed Leonardo Helicopters Alert Service Bulletin
No. 139-452, Revision B, dated April 10, 2018, which contains
procedures for reducing the body end nut torque.

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.

Proposed AD Requirements

This proposed AD would require compliance with certain procedures
described in the manufacturer's service bulletin. Based on the
helicopter's S/N and the M/R damper P/N installed, this proposed AD
would require within 5 hours time-in-service (TIS) and thereafter
before the first flight of each day:

A repetitive visual inspection using a magnifying glass of
the M/R damper rod end (rod end) and body ends for a crack, and
depending on the inspection results, removing the rod end from service
or replacing the M/R damper.

A repetitive inspection of the rod and body end bearings
for rotation in the damper seat and for misaligned slippage marks, and
depending on the inspection results, removing from service the rod end
or replacing the M/R damper.

This proposed AD would also require within 10 hours TIS:

Reducing the installation torque of each hub attachment
bolt for each M/R damper.

This proposed AD would also require within 30 hours TIS, before the
M/R damper accumulates 300 hours TIS, or within 300 hours TIS since
last overhaul, whichever occurs later:

A dye penetrant inspection using a magnifying glass or
eddy current inspection of the rod and body ends for a crack, and
depending on the inspection results, removing from service the rod end
and replacing the M/R damper, or marking the rod and body ends.

This proposed AD would require within 30 hours TIS and thereafter
at intervals not to exceed 20 hours TIS until the M/R damper has
accumulated 600 hours TIS:

A repetitive visual inspection of the rod end broached
ring nut for broken teeth, improper engagement, and misalignment, and
depending on the inspection results, removing from service the broached
ring nut.

This AD would require within 50 hours TIS and thereafter at
intervals not to exceed 100 hours TIS:

A repetitive inspection of the bearing friction torque
value of the body and rod ends, and depending on the inspection
results, removing from service the rod end or replacing the M/R damper.

A repetitive inspection the M/R damper anti-rotation block
(block), and depending on the inspection results, removing the block
from service.

This AD would also require, within 50 hours TIS:

If special washer P/N 3G6220A05052 is installed, aligning
the rod ends and broached rings, and replacing any broached ring that
cannot be aligned.

If special washer P/N 3G6220A05052 is not installed,
inspecting the broached rings for wear and damage, and depending on the
inspection results, replacing the broached ring and installing a
special washer.

This proposed AD would also require installing M/R damper P/N
3G220V01353, prohibit installing M/R damper P/N 3G6220V01351 and P/N
3G6220V01352 on any helicopter, and allow the installation of M/R
damper P/N 3G220V01353 to serve as terminating action for all the
repetitive requirements of this proposed AD.

Differences Between This Proposed AD and the EASA AD

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

Costs of Compliance


The FAA estimates that this proposed AD would affect 123
helicopters of U.S. Registry. The FAA estimates that operators may
incur the following costs in order to comply with this proposed AD.
Labor costs are estimated at $85 per work-hour.

Performing the M/R damper inspections would take about 24 work-
hours, for an estimated cost of $2,040 per helicopter and $250,920 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 M/R damper would take about 2 work-hours and parts
would cost about $18,000, for an estimated cost of $18,170 per M/R
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 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, I certify this proposed regulation:

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 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

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 (AD):