preamble attached >>>
ADs updated daily at www.Tdata.com
2021-20-17 LEONARDO S.P.A.: Amendment 39-21755; FAA-2021-0612; Project Identifier MCAI-2021-00650-R.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective November 22, 2021.

(b) AFFECTED ADS

    This AD replaces Emergency AD 2018-23-52,  Product Identifier 2018-SW-
    093-AD, dated November 8, 2018 (Emergency AD 2018-23-52).

(c) APPLICABILITY

    This AD applies to all Leonardo S.p.a.  Model AW169 and AW189 helicop-
    ters, certificated in any category.

(d) SUBJECT

    Joint Aircraft Service Component (JASC) Code 6400, Tail Rotor System.

(e) UNSAFE CONDITION

    This AD was prompted by a report of an accident of a Model AW169 heli-
    copter, which was observed to have lost yaw control prior to the acci-
    dent.  The FAA is issuing this AD to address failure of the tail rotor
    servo-actuator (TRA)  feedback lever.  This condition  could result in
    loss of tail rotor control and subsequent loss of control of the heli-
    copter.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIREMENTS

    Except as specified in paragraph (h)  of this AD:  Comply with all re-
    quired actions and compliance times specified in,  and  in  accordance
    with, European Union Aviation Safety Agency (EASA) AD 2020-0197, dated
    September 10, 2020 (EASA AD 2020-0197).

(h) EXCEPTIONS TO EASA AD 2020-0197

(1) Where EASA AD 2020-0197 requires compliance in terms  of flight hours,
    this AD requires using hours time-in-service.

(2) This AD does not allow the compliance time tolerance specified in Note
    1 of EASA AD 2020-0197.

(3) The initial compliance time  for the inspection specified in paragraph
    (1) of EASA AD 2020-0197 is within  the  compliance time  specified in
    paragraph (1) of EASA AD 2020-0197,  except for Group 1 helicopters on
    which the inspection identified in paragraph (1)  of EASA AD 2020-0197
    has not been done,  the initial inspection is within 10 hours time-in-
    service after the effective date of this AD.

(4) The initial compliance time for the inspection  specified in paragraph
    (2) of EASA AD 2020-0197 is within  the compliance time  specified  in
    paragraph (2) of EASA AD 2020-0197,  except for Group 1 and 2 helicop-
    ters on which the inspection identified  in  paragraph (2)  of EASA AD
    2020-0197 has not been done,  the initial compliance time is within 50
    hours time-in-service after the effective date of this AD.

(5) The initial compliance time  for the installation  specified  in para-
    graph (3) of EASA AD 2020-0197 is within the compliance time specified
    in paragraph (3) of EASA AD 2020-0197,  except for Group 1 and 2 heli-
    copters on which the installation identified  in paragraph (3) of EASA
    AD 2020-0197 has not been done,  the initial compliance time is within
    20 hours time-in-service after the effective date of this AD.

(6) The initial compliance time  for the check (inspection)  specified  in
    paragraph (4) of EASA AD 2020-0197 is within the compliance time spec-
    ified in paragraph (4) of EASA AD 2020-0197,  except for Group 1 and 2
    helicopters on which the check (inspection)  identified  in  paragraph
    (4) of EASA AD 2020-0197  has not been done,  the  initial  compliance
    time is within 10 hours time-in-service  after  the  effective date of
    this AD.

(7) The initial compliance time  for  the  inspection / check specified in
    paragraph (5) of EASA AD 2020-0197 is within the compliance time spec-
    ified in paragraph (5)  of EASA AD 2020-0197  except for Group 1 and 2
    helicopters  on which the inspection identified  in  paragraph (5)  of
    EASA AD 2020-0197  has not been done,  the  initial compliance time is
    within 10 hours time-in-service after the effective date of this AD.

(8) Where paragraphs (6), (8), (9), and (11) of EASA AD 2020-0197  specify
    contacting Leonardo for corrective action instructions, the corrective
    action instructions  must  be  accomplished  in  accordance  with FAA-
    approved procedures.

(9) Where paragraphs (9) and (10) of EASA AD 2020-0197  use the term "dis-
    crepancy," for this AD,  discrepancies include roughness (meaning lack
    of free and easy rotation),  measured breakaway force(s)  outside  the
    allowed range specified in the service information identified in para-
    graphs (2) and (7) of EASA AD 2020-0197, any wear or other damage (in-
    cluding, but not limited to, broken seals), and the presence of parti-
    cles.

(10) Where paragraph (12) of EASA AD 2020-0197  requires reporting results
     to the  manufacturer  "as required by paragraphs (12.1) and (12.2) of
     this [EASA] AD",  for this AD,  only report  the inspection and check
     results specified in paragraph (12.1)  of  EASA AD 2020-0197.  Submit
     the report at the applicable time specified  in  paragraph (h)(10)(i)
     or (ii) of this AD.

(i) If the inspection or check was done on  or after the effective date of
    this  AD: Submit  the report  within 2  days after  the inspection  or
    check.

(ii) If the inspection or check was done before the effective date of this
     AD: Submit the report within 2 days after the effective date of  this
     AD.

(11) Where paragraph (13) of EASA AD 2020-0197,  and  the service informa-
     tion  specified in  EASA AD  2020-0197, specify  returning parts  and
     grease containers to the manufacturer, this AD does not include those
     requirements.

(12) Where EASA AD 2020-0197  requires compliance from March 20, 2020 (the
     effective date of EASA AD 2020-0048,  dated  March 6, 2020),  this AD
     requires using the effective date of this AD.

(13) Where EASA AD 2020-0197  requires compliance from its effective date,
     this AD requires using the effective date of this AD.

(14) This AD does not allow credit  for  the  actions specified in EASA AD
     2020-0197 if those actions were done  using  the  service information
     specified in paragraphs (h)(14)(i) through (ix) of this AD:

(i) Leonardo S.p.A. Emergency Alert Service Bulletin (EASB) 169-148, dated
    May 29, 2019;

(ii) Leonardo S.p.A. EASB 169-148, Revision A, dated September 5, 2019;

(iii) Leonardo S.p.A. EASB 169-148, Revision B, dated February 4, 2020;

(iv) Leonardo S.p.A. EASB 169-148, Revision C, dated April 6, 2020;

(v) Leonardo S.p.A. EASB 189-237, dated May 29, 2019;

(vi) Leonardo S.p.A. EASB 189-237, Revision A, dated September 5, 2019;

(vii) Leonardo S.p.A. EASB 189-237, Revision B, dated February 4, 2020;

(viii) Leonardo S.p.A. EASB 189-237,  Revision B,  dated February 4, 2020,
       with Errata Corrige;

(ix) Leonardo S.p.A. EASB 189-237, Revision C, dated April 6, 2020.

(15) This AD does not require the "Remarks" section of EASA AD 2020-0197.

(i) 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  (j) of  this AD.  Information may  be
    emailed to: 9-AVS-AIR-730-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards district office/certificate holding district office.

(j) RELATED INFORMATION

    For more information about this AD,  contact Andrea Jimenez, Aerospace
    Engineer,  COS Program Management Section,  Operational Safety Branch,
    Compliance & Airworthiness Division, FAA, 1600 Stewart Ave, Suite 410,
    Westbury, NY 11590; telephone (516) 228-7330; email andrea.jimenez@faa
    .gov.

(k) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference (IBR) 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) AD 2020-0197,  dated Sep-
    tember 10, 2020.

(ii) [Reserved]

(3) For EASA AD 2020-0197, contact the EASA, Konrad-Adenauer-Ufer 3, 50668
    Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu
    internet www.easa.europa.eu. You may find this EASA AD on the EASA web
    site at https://ad.easa.europa.eu.

(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.  This material may be found in
    the AD docket on the internet at https://www.regulations.gov by search
    -ing for and locating Docket No. FAA-2021-0612.

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

Issued on September 23, 2021.  Gaetano A. Sciortino,  Deputy Director  for
Strategic Initiatives,  Compliance & Airworthiness Division, Aircraft Cer-
tification Service.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez,  Aerospace Engineer,  COS
Program Management Section,  Operational Safety Branch,  Compliance & Air-
worthiness Division, FAA, 1600 Stewart Ave, Suite 410, Westbury, NY 11590;
telephone (516) 228-7330; email andrea.jimenez@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0612; Project Identifier MCAI-2021-00650-R;
Amendment 39-21755; AD 2021-20-17]
RIN 2120-AA64

Airworthiness Directives
; Leonardo S.p.a. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding emergency Airworthiness Directive (AD)
2018-23-52, which applied to all Leonardo S.p.a. Model AW169 and AW189
helicopters. AD 2018-23-52 required inspecting the nut, cotter pin,
lock-wire, and hinge bracket connected to the tail rotor servo-actuator
(TRA) feedback lever link, and each connection of the TRA feedback
lever link, and repair if necessary. AD 2018-23-52 also required
applying a paint stripe or torque seal on the nut and reporting certain
information. This AD requires repetitive inspections of the TRA,
repetitive inspections and checks of the tail rotor duplex bearings (TR
DB), installation of an improved TRA and TR DB, repetitive
installations and checks of thermal strips, replacement of the improved
TR DB (life limit), and applicable corrective actions, as specified in
a European Union Aviation Safety Agency (EASA) AD, which is
incorporated by reference. This AD was prompted by a report of an
accident of a Model AW169 helicopter, which was observed to have lost
yaw control prior to the accident and a determination that certain
inspections and checks of the TR DB, installation of an improved TRA
and TR DB, certain other actions, and applicable corrective actions are
necessary to address the unsafe condition. The FAA is issuing this AD
to address the unsafe condition on these products.

DATES: This AD is effective November 22, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 22,
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email ADs@easa.europa.eu; 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-2021-0612.

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-2021-
0612; 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, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email andrea.jimenez@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0197, dated September 10, 2020
(EASA AD 2020-0197), to correct an unsafe condition for all Leonardo
S.p.A. (formerly Finmeccanica S.p.A., AgustaWestland S.p.A.) Model
AW169 and AW189 helicopters.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede Emergency AD 2018-23-52, Product Identifier
2018-SW-093-AD, dated November 8, 2018 (Emergency AD 2018-23-52).
Emergency AD 2018-23-52 applied to all Leonardo S.p.a. Model AW169 and
AW189 helicopters. The NPRM published in the Federal Register on August
5, 2021 (86 FR 42754). The NPRM was prompted by a report of an accident
of a Model AW169 helicopter, which was observed to have lost yaw
control prior to the accident and a determination that certain
inspections and checks of the TR DB, installation of an improved TRA
and TR DB, certain other actions, and applicable corrective actions are
necessary to address the unsafe condition. The NPRM proposed to require
repetitive inspections of the TRA, repetitive inspections and checks of
the TR DB, installation of an improved TRA and TR DB, repetitive
installations and checks of thermal strips, replacement of the improved
TR DB (life limit), and applicable corrective actions, as specified in
an EASA AD.
The FAA is issuing this AD to address failure of the TRA feedback
lever. This condition could result in loss of tail rotor control and
subsequent loss of control of the helicopter. See the EASA AD 2020-0197
for additional background information.

Discussion of Final Airworthiness Directive

Comments

The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.

Conclusion

The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

EASA AD 2020-0197 requires the following actions:

--Repetitive inspections of the slippage marking of the castellated nut
installed on the back-end of the affected TRA.
--Repetitive inspections of the roughness and breakaway force of the
affected TR DB.
--Repetitive installations of a thermal strip on the spacer next to the
TR DB.
--Repetitive checks of the condition of the thermal strip and the
indicated temperature.
--Repetitive inspections/checks for particles and additional roughness
of the TR DB.
--Installation of an improved TRA.
--Installation of an improved TR DB.
--Repetitive replacements of the improved TR DB (life limit).
--An inspection of an affected TR DB if the thermal strip is detached,
partially detached, or unreadable.
--Reporting information to the manufacturer.
--Sending parts to the manufacturer.
--Applicable corrective actions.

Corrective actions include accomplishing instructions to address
the following findings: Evidence of rotation of an affected TRA nut;
thermal strip temperatures that exceed specified values; and any
discrepancies found during the inspection of an affected TR DB.
Discrepancies include roughness (meaning lack of free and easy
rotation), measured breakaway force(s) outside the allowed range, any
wear or other damage (including, but not limited to, broken seals), and
the presence of particles.
EASA AD 2020-0197 also prohibits (re)installation of an affected
TRA and an affected TR DB on a helicopter. EASA AD 2020-0197 also
specifies, for certain helicopters, terminating action for the
repetitive inspections of the slippage marking of the castellated nut.
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.

Differences Between This AD and EASA AD 2020-0197

EASA AD 2020-0197 requires sending parts to the manufacturer. This
AD does not require that action.
EASA AD 2020-0197 specifies the earlier revisions of Leonardo
S.p.A. Emergency Alert Service Bulletin (EASB) 169-148, Revision D,
dated August 4, 2020; and Leonardo S.p.A. EASB 189-237, Revision D,
dated August 4, 2020; are acceptable for compliance for certain
actions. This AD does not allow credit for the earlier revisions.
Where Note 1 of EASA AD 2020-0197 allows a non-cumulative tolerance
of 10 percent to be applied to the compliance times for the actions to
allow for synchronization of the required actions with other
maintenance tasks, this AD does not allow that tolerance.

Interim Action


The FAA considers this AD to be an interim action and further AD
action might follow.

Costs of Compliance

The FAA estimates that this AD affects 10 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections and checks Up to 9 work-hours x $85 per hour = $765, per inspection/check cycle $0 Up to $765, per inspection/check cycle Up to $7,650, per inspection/check cycle
Thermal strip installation 1 work-hour x $85 per hour = $85, per installation cycle $4 $89, per installation cycle $890, per installation cycle
Installation of improved TRA and TR DB Up to 18 work-hours x $85 per hour = $1,530 Up to $39,000 Up to $40,530 Up to $405,300
Replacement of improved TR DB 10 work-hours x $85 per hour = $850, per replacement cycle $1,500 $2,350, per replacement cycle $23,500, per replacement cycle

The FAA estimates that it would take about 1 hour per product to
comply with the on-condition reporting requirement in this AD. The
average labor rate is $85 per hour. Based on these figures, the FAA
estimates the cost of reporting the inspection and check results on
U.S. operators to be $85 per product.
The FAA estimates the following costs to do any necessary on-
condition inspections and thermal strip installations that would be
required based on the results of any required actions. The FAA has no
way of determining the number of helicopters that might need these on-
condition actions:

Estimated Costs of On-Condition Inspections and Installations

Labor cost
Parts cost
Cost per product
4 work-hours x $85 per hour = $340
$0
$340

The FAA has received no definitive data that would enable the
agency to provide cost estimates for the other on-condition actions
specified in this AD.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to
Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Pkwy., Fort Worth, TX 76177-1524.

Authority for This Rulemaking

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

Regulatory Findings


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

List of Subjects in 14 CFR Part 39

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

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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: