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2022-13-14 AIRBUS HELICOPTERS: Amendment 39-22100; Docket No. FAA-2022-0295; Project Identifier MCAI-2021-00840-R.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective August 15, 2022.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD  applies to all Airbus Helicopters Model AS-365N2,  AS 365 N3,
    EC 155B, EC155B1, and SA-365N1 helicopters,  certificated in any cate-
    gory.

(d) SUBJECT

    Joint Aircraft Service Component (JASC)  Code  6500,  Tail Rotor Drive
    System.

(e) UNSAFE CONDITION

    This AD was prompted  by  a  large amount  of critical scale particles
    found on the tail rotor gearbox (TGB) chip detector magnetic plug dur-
    ing an unscheduled check of the TGB.  The  particles  belonged  to the
    double bearing  (pitch control rod bearing)  installed inside the TGB.
    The FAA is issuing  this AD  to prevent bearing degradation and subse-
    quent failure. The unsafe condition, if not addressed, could result in
    loss of yaw control of the helicopter.

(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 2021-0170, dated
    July 19, 2021 (EASA AD 2021-0170).

(h) EXCEPTIONS TO EASA AD 2021-0170

(1) Where EASA AD 2021-0170  requires compliance  in terms of flight hours
    (FH), this AD requires using hours time-in-service (TIS).

(2) Where EASA AD 2021-0170  refers  to  the  effective dates specified in
    paragraphs (h)(2)(i) through (iii) of this AD,  this AD requires using
    the effective date of this AD.

(i) October 28, 2019  (the  effective  date  of EASA AD 2019-0267-E, dated
    October 25, 2019).

(ii) November 19, 2019  (the effective date of EASA AD 2019-0267R1,  dated
     November 12, 2019, and corrected November 13, 2019).

(iii) The effective date of EASA AD 2021-0170.

(3) Where EASA  AD 2021-0170  requires  actions  during  each  "after last
    flight (ALF) of the day inspection"  or "ALF,"  this AD requires those
    actions before the first flight of each day.

(4) Where paragraph (7) of EASA AD 2021-0170  specifies "any discrepancy,"
    for this AD discrepancies  include the presence of particles and other
    conditions such as abrasions,  particles  that  consist  of any scale,
    chip, flake, splinter, M50 particles, magnetic abrasion dust, or other
    particles other than cotter pin fragments, pieces of lock wire, swarf,
    or miscellaneous non-metallic waste.

(5) Where paragraph (8)  of EASA AD 2021-0170  specifies for Group 2 heli-
    copters,  the  first  replacement  of the affected part must be accom-
    plished not later than December 31, 2021,  this AD requires, for Group
    2 helicopters,  the first replacement  of the affected part as defined
    in EASA AD 2021-0170 must be accomplished  within 5 months  after  the
    effective date of this AD.

(6) Where any work card  referenced in the service information  referenced
    in EASA AD 2021-0170  specifies "if there is an anomaly,  replace  the
    chip detector," or "if there is an anomaly, replace the TGB electrical
    magnetic plug," for this AD an anomaly may be indicated by the magnet-
    ic component  of the TGB chip detector  or the TGB electrical magnetic
    plug not being magnetized.  If there is an anomaly,  this  AD requires
    before further flight,  removing from service the TGB chip detector or
    the TGB electrical magnetic plug as applicable  to your model helicop-
    ter.

(7) Where any work card  referenced in the service information  referenced
    in EASA AD 2021-0170 specifies "make sure that the chip detector is in
    good condition," or "make sure  that the TGB electrical magnetic  plug
    is in  good condition,"  as applicable  to your  model helicopter, for
    this AD "good condition" is indicated when there are no signs of  wear
    on the locking  systems (including wear  on the bayonets,  and slotted
    tubes). If there are any signs of wear on the locking systems, this AD
    requires before  further flight,  removing from  service the  TGB chip
    detector or the TGB magnetic electrical magnetic plug as applicable to
    your model helicopter.

(8) Where any work card  referenced in the service information  referenced
    in EASA AD 2021-0170  specifies  "if necessary,  replace the O-rings,"
    this AD requires  before further flight,  removing any affected O-ring
    from service.

(9) Where the service information  referenced in EASA AD  2021-0170 speci-
    fies to return certain parts  to the manufacturer,  including  for re-
    pair,  this AD  does not require  returning parts to the manufacturer,
    however,  this AD does require  before further flight,  repair done in
    accordance with a method approved by the Manager, General Aviation and
    Rotorcraft Section,  International Validation Branch, FAA; or EASA; or
    Airbus  Helicopters'  EASA  Design  Organization  Approval  (DOA).  If
    approved by the DOA, the approval must include the DOA-authorized sig-
    nature.

(10) Where the service information  referenced in EASA AD 2021-0170 speci-
     fies to remove the TGB as per technical documentation,  or remove the
     concerned module(s), this AD requires before further flight, removing
     the TGB and replacing it with an airworthy part, or repairing the TGB
     in accordance with a method approved by the Manager, General Aviation
     & Rotorcraft Section,  International Validation Branch, FAA; or EASA;
     or Airbus Helicopters' EASA DOA. If approved by the DOA, the approval
     must include the DOA-authorized signature.

(11) Where the service information  referenced in EASA AD 2021-0170 speci-
     fies if the collected particles cannot be clearly defined,  perform a
     metallurgical analysis and contact Airbus Helicopters, before contin-
     uing flights, this AD does require before further flight, characteri-
     zation of the particles collected,  and  performing  a  metallurgical
     analysis for any particles  collected  using  a  method in accordance
     with FAA-approved procedures.  However, this AD does not require con-
     tacting the  manufacturer to  determine the  characterization of  the
     particles collected.

(12) Where the service information  or any work card referenced in EASA AD
     2021-0170 specifies to do the actions  identified  in  paragraphs (h)
     (12)(i) through (v) of this AD,  this  AD  does not include those re-
     quirements.

(i) Complete Appendix 4.A and 4.B.

(ii) Comply with paragraph 2.D.

(iii) Send all collected particles  and  metallurgical  analysis report to
      depot level maintenance facility with the concerned module.

(iv) Inform EST using chip detection tracking sheet.

(v) Complete the "Particle Detection" follow up sheet.

(13) Where a work card referenced in the service information referenced in
     EASA AD 2021-0170  specifies "send all oversized particles for analy-
     sis and wait for results before continuing flight,"  this AD does not
     require sending particles for analysis,  however this AD does require
     before further flight,  analyzing  the  particles  using  a method in
     accordance with FAA-approved procedures.

(14) This AD does not mandate  compliance  with  the  "Remarks" section of
     EASA AD 2021-0170.

(15) Where paragraph (7) of EASA AD 2021-0170  specifies to accomplish the
     applicable corrective actions  "within the compliance time as identi-
     fied in the applicable ASB,"  this AD  requires accomplishing correc-
     tive actions before further flight.

(16) Where paragraph (1)  of  EASA  AD  2021-0170  specifies  "within  the
     applicable compliance time  as identified in the close monitoring and
     until completion of the close monitoring,"  this AD  requires a close
     monitoring compliance time of a total of 25 hours TIS.

(i) NO REPORTING REQUIREMENT

    Although the service information referenced in EASA AD 2021-0170 spec-
    ifies to submit certain information to the manufacturer,  this AD does
    not include that requirement.

(j) SPECIAL FLIGHT PERMIT

    Special flight permits  may be issued in accordance with 14 CFR 21.197
    and 21.199, provided no passengers are onboard.

(k) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, International Validation Branch,  FAA,  has the authority
    to approve AMOCs for this AD,  if requested using the procedures found
    in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to
    your principal inspector or local Flight Standards District Office, as
    appropriate.  If  sending  information  directly to the manager of the
    International Validation Branch,  send it to the attention of the per-
    son identified in paragraph (l) 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.

(l) 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.

(m) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the service information listed  in this paragraph under 5
    U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless this AD specifies otherwise.

(i) European Union Aviation Safety Agency (EASA) AD 2021-0170,  dated July
    19, 2021.

(ii) [Reserved]

(3) For EASA AD 2021-0170,  contact  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  the EASA material on the
    EASA website 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  at https://www.regulations.gov  by searching for and
    locating Docket No. FAA-2022-0295.

(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 June 16, 2022.  Christina Underwood, Acting Director, Compliance
& Airworthiness Division, Aircraft Certification 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-2022-0295; Project Identifier MCAI-2021-00840-R;
Amendment 39-22100; AD 2022-13-14]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, and SA-
365N1 helicopters. This AD was prompted by a large amount of critical
scale particles found on the tail rotor gearbox (TGB) chip detector
magnetic plug during an unscheduled check of the TGB. The particles
belonged to the double bearing (pitch control rod bearing) installed
inside the TGB. This AD requires repetitive inspections of the TGB chip
detector for particles, analyzing any particles collected, performing a
double bearing washing, repetitive replacements of certain part-
numbered double bearings, and corrective actions if necessary, as
specified in a European Union Aviation Safety Agency (EASA) AD, which
is incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective August 15, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 15,
2022.

ADDRESSES: For EASA material incorporated by reference (IBR) in this
final rule, contact 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 the EASA material on the EASA website
at https://ad.easa.europa.eu. For Airbus Helicopters service
information identified in this final rule, contact Airbus Helicopters,
2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000
or (800) 232-0323; fax (972) 641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. 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.
Service information that is IBRed is also available in the AD docket at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2022-0295.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2022-0295; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, the
EASA AD, any comments received, and other information. The 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

EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0170, dated July 19, 2021 (EASA
AD 2021-0170), to correct an unsafe condition for all Airbus
Helicopters (AH), formerly Eurocopter, Eurocopter France, Aerospatiale,
Sud Aviation, Model AS 365 N2, AS 365 N3, EC 155 B, EC 155 B1 and SA
365 N1 helicopters.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus Helicopters
Model AS-365N2, AS 365 N3, EC 155B, EC155B1, and SA-365N1 helicopters.
The NPRM published in the Federal Register on April 11, 2022 (87 FR
21052). The NPRM was prompted by a large amount of critical scale
particles found on the TGB chip detector magnetic plug during an
unscheduled check of a Model AS 365 N2 helicopter. The NPRM proposed to
require repetitive inspections of the TGB chip detector for particles,
analyzing any particles collected, performing a double bearing washing,
repetitive replacements of certain part-numbered double bearings, and
corrective actions if necessary, as specified in EASA AD 2021-0170.
The FAA is issuing this AD to prevent bearing degradation and
subsequent failure. The unsafe condition, if not addressed, could
result in loss of yaw control of the helicopter. See EASA AD 2021-0170
for additional background information.

Discussion of Final Airworthiness Directive

Comments

The FAA received a comment from an anonymous commenter. The
commenter did not request any changes to the NPRM or to the
determination of costs.

Conclusion

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 reviewed the relevant
data, considered the comments received, and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these helicopters. This AD
is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

EASA AD 2021-0170 requires analyzing any particles collected during
close monitoring or during any required inspections, repetitive
inspections of the TGB chip detector for particles, performing a double
bearing washing, and corrective actions. Corrective actions include
removing an affected TGB and repairing or replacing that TGB, sending
affected parts and certain information to the manufacturer, replacing a
TGB chip detector or TGB electrical magnetic plug, and replacing an
affected O-ring and double bearing. EASA AD 2021-0170 also requires
performing a double bearing washing or performing a metallurgical
analysis based on inspection results.
EASA AD 2021-0170 also requires for any double bearing part number
(P/N) 704A33-651-245 or 704A33-651-246, installed on any TGB P/N
365A33-6005-09, before exceeding 610 flight hours (FH) since first
installation, or within 110 FH after October 28, 2019 (the effective
date of EASA AD 2019-0267-E, dated October 25, 2019), whichever occurs
later, and thereafter at intervals not to exceed 500 FH, replacing the
affected double bearing with a serviceable one. EASA AD 2021-0170
allows double bearing part number P/N 704A33-651-245 or 704A33-651-246
to be installed, provided it has never been installed on a helicopter
and it is inspected as required by EASA AD 2021-0170. Finally, EASA AD
2021-0170 allows TGB P/N 365A33-6005-09 to be installed, provided it
has a serviceable double bearing installed that is inspected as
required by EASA AD 2021-0170.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.

Other Related Service Information

The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin (EASB) No. 01.00.24 for non FAA-type certificated military
Model AS565MA, MB, MBe, SA, SB, and UB helicopters; EASB No. 01.00.71
for Model AS365N1, N2, and N3 helicopters, and non FAA-type
certificated military Model AS365F, Fi, K, and K2 helicopters; EASB No.
01.31 for non FAA-type certificated military Model SA366GA helicopters;
and EASB No. 04A016 for Model EC155B and B1 helicopters, each Revision
3 and dated June 14, 2021 (co-published as one document).
This service information specifies procedures to inspect the TGB
chip detector for particles, analyze and define the particles by
performing a metallurgical analysis, perform a washing of the double
bearing, replace the double bearing, and send certain information and
affected parts to the manufacturer.

Interim Action

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

Differences Between This AD and EASA AD 2021-0170

Service information referenced in EASA AD 2021-0170 specifies
sending compliance forms, and certain parts to the manufacturer; this
AD does not. Service information referenced in EASA AD 2021-0170
specifies contacting Airbus Helicopters for approved repairs or
corrective actions if certain discrepancies are found, whereas this AD
requires accomplishing repairs or corrective actions using a method
approved by the Manager, General Aviation and Rotorcraft Section,
International Validation Branch, FAA; or EASA; or Airbus Helicopters'
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.

Costs of Compliance

The FAA estimates that this AD affects 53 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Analyzing any particles collected during close monitoring takes
about 1 work-hour for an estimated cost of $85 per inspection and up to
$4,505 for the U.S. fleet.
Replacing a double bearing takes about 16 work-hours and parts cost
about $1,620 for an estimated cost of $2,980 per replacement and
$157,940 for the U.S. fleet.
Inspecting the TGB chip detector for particles takes about 1 work-
hour for an estimated cost of $85 per inspection and $4,505 for the
U.S. fleet.
Performing a double bearing washing takes about 8 work-hours for an
estimated cost of $680 per helicopter.

The FAA estimates the following costs to do any necessary on-
condition replacements that are required based on the results of the
inspection. The agency has no way of determining the number of aircraft
that might need these on-condition replacements:
Analyzing collected particles takes about 1 work-hour for an
estimated cost of $85 per helicopter.
Replacing a double bearing takes about 16 work-hours and parts cost
about $1,620 for an estimated cost of $2,980 per bearing.
Replacing a TGB chip detector or TGB electrical magnetic plug takes
about 1 work-hour and parts cost about $900 for an estimated cost of
$985 per part replacement.
Replacing an O-ring takes about 1 work-hour and parts cost about
$100 for an estimated cost of $185 per O-ring.
Replacing a TGB takes about 8 work-hours and parts cost about
$155,302 for an estimated cost of $155,982 per replacement.
The FAA has received no definitive data for the repair cost of a
TGB.

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: