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PROPOSED AD AIRBUS HELICOPTERS: Docket No. FAA-2018-0019; Product Identifier 2017-SW-074-AD.
(a) APPLICABILITY

    This  AD  applies  to Airbus  Helicopters  Model  AS332L2 and  EC225LP
    helicopters, certificated in any  category, with a main  gearbox (MGB)
    suspension bar front attachment  bolt (bolt) part number  (P/N) 332A22
    -1613-21 or 332A22-1613-20,  MGB suspension bar  rear bolt P/N  332A22
    -1614-20, MGB  suspension bar  front attachment  fitting (fitting) P/N
    332A22-1623-01, MGB suspension bar  rear left hand fitting  P/N 332A22
    -1624-02  or 332A22-1624-04,  or MGB  suspension bar  rear right  hand
    fitting P/N 332A22-1624-03 or 332A22-1624-05 installed.

(b) UNSAFE CONDITION

    This AD defines the unsafe  condition as MGB suspension bar  bolts and
    fittings remaining in service beyond their fatigue life and loose  MGB
    suspension bar  bolts or  fittings, which  could result  in structural
    failure of the MGB suspension bar and loss of helicopter control.

(c) COMMENTS DUE DATE

    The FAA must receive comments by February 7, 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) Within 30 hours time-in-service (TIS), review records to determine the
    total hours TIS of each MGB suspension bar bolt.

(i) Determine the life limit of each bolt by applying the hours TIS by the
    add-on factor listed  in Table No.  1 of Airbus  Helicopters Emergency
    Alert Service Bulletin No. 01.00.86, Revision 1, dated August 25, 2017
    (EASB  01.00.86),  or  Airbus  Helicopters  Emergency  Alert   Service
    Bulletin No. 04A013, Revision 1, dated August 25, 2017, as  applicable
    to your model helicopter.

    Note 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters refers to
    bolts as "pins."

(A) Before further flight, remove  from service any bolt that  has reached
    or exceeded its life limit.

(B) For each bolt that has not exceeded its  life limit, continue to calc-
    ulate  and record  the life  limit on  its component  history card  or
    equivalent  record  by  applying  the  add-on  factor  each  time  the
    helicopter accumulates  hours TIS,  and remove  from service  any bolt
    before reaching its life limit.

(ii) Thereafter  following  paragraph (e)(1)(i)  of this  AD, continue  to
     calculate and  record the  life limit  of each  bolt on its component
     history card or equivalent record by applying the add-on factor  each
     time the helicopter accumulates hours TIS and remove from service any
     bolt before reaching its life limit.

(2) For Model AS332L2 helicopters, within 30 hours TIS, review records  to
    determine the total hours TIS of each MGB suspension bar fitting.

(i) Determine the life limit of each fitting by applying the hours TIS  by
    the add-on factor listed in Table No. 1 of EASB 01.00.86.

(A) Before further flight, remove from service any fitting that has reach-
    ed or exceeded its life limit.

(B) For each  fitting that has  not exceeded its  life limit, continue  to
    calculate and record the life  limit on its component history  card or
    equivalent  record  by  applying  the  add-on  factor  each  time  the
    helicopter accumulates hours TIS, and remove from service any  fitting
    before reaching its life limit.

(ii) Thereafter  following  paragraph (e)(2)(i)  of this  AD, continue  to
     calculate and record the life limit of each fitting on its  component
     history card or equivalent record by applying the add- on factor each
     time the helicopter accumulates hours TIS and remove from service any
     fitting before reaching its life limit.

(3) For Model AS332L2 helicopters,  within 150 hours TIS (without the add-
    on factor), inspect the torque  of each MGB suspension bar  attachment
    front and rear nut. The allowable torque for each front nut is 602-663
    lbf. in (6.8-7.5 daN.m) and the allowable torque for each rear nut  is
    337-398 lbf. in (3.8-4.5 daN.m).

(i) If the torque on any  nut is higher than the maximum  allowable torque
    stated in paragraph (e)(3) of  this AD, before further flight,  remove
    from service the bolt and nut.

(ii) If the torque on any  nut is lower than the minimum  allowable torque
     value stated in paragraph (e)(3)  of this AD, before further  flight,
     tighten the nut to the allowable torque stated in paragraph (e)(3) of
     this AD. Within  150 hours TIS  (without the add-  on factor), remove
     from service any bolt and nut that were tightened as required by this
     paragraph.

(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., 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.

(g) ADDITIONAL INFORMATION

    The subject of this AD is addressed in European Aviation Safety Agency
    (EASA) AD No.  2017-0189, dated September  22, 2017. 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:  6320,  Main  Rotor
    Gearbox.

Issued  in  Fort  Worth,  Texas, on  November  29,  2019.  Lance T.  Gant,
Director,  Compliance  &  Airworthiness  Division,  Aircraft Certification
Service.

DATES: The FAA must  receive comments on this  proposed AD by February  7,
2020.
PREAMBLE 
DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0019; Product Identifier 2017-SW-074-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus 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 Airbus Helicopters Model AS332L2 and EC225LP helicopters. This 
proposed AD would require determining the accumulated hours time-in-
service (TIS) of certain part-numbered main gearbox (MGB) suspension 
bar attachment bolts and fittings, applying a life limit add-on factor, 
and inspecting the torque of certain MGB suspension bar attachment 
nuts. This proposed AD is prompted by a report of torque loss on an MGB 
suspension bar bolt. The actions of this proposed AD are intended to 
address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by February 7, 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-2018-
0019; 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 Aviation Safety Agency (EASA) AD, the 
economic evaluation, 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 
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 
review 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 EASA AD No. 2017-0189, dated September 22, 
2017, to correct an unsafe condition for Airbus Helicopters (formerly 
Eurocopter, Eurocopter France, Aerospatiale) Model AS 332 L2 and EC 225 
LP helicopters. Following review of reported Model EC 225 LP data, EASA 
advises that the installation of the MGB upper deck fittings of the 
three MGB suspension bars could lead to tightening torque loss on the 
fittings' attachment pins (bolts). Due to design similarities, Model AS 
332 L2 helicopters could also be affected by the same installation 
condition. An investigation determined that the life limits in the 
Airworthiness Limitations Sections for the pins and fittings are valid 
if an "add-on penalty factor" is applied.

    EASA states that this condition, if not corrected, could lead to 
structural failure of the MGB suspension bar attachment pins or 
fittings. Accordingly, the EASA AD requires applying the add-on penalty 
factor to the flight hours to re-calculate the life limits and 
replacing an affected part before exceeding its life limit.

    EASA further advises that Airbus Helicopters' initial service 
information contained an error that may have resulted in the 
installation of pins or fittings using an incorrect torque value. As a 
result, the EASA AD also requires replacing pins if an incorrect torque 
value was applied and reporting the information to Airbus Helicopters.

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 proposing this AD 
after evaluating all known relevant information and determining that an 
unsafe condition is likely to exist or develop on other products of the 
same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Emergency Alert Service 
Bulletin (EASB) No. 01.00.86 for Model AS332 helicopters and Airbus 
Helicopters EASB No. 04A013 for Model EC225LP helicopters, both 
Revision 1 and dated August 25, 2017. This service information 
specifies applying an add-on factor to the flying hours logged by the 
pins and fittings and replacing them if the service life limit (SLL) is 
exceeded. If an incorrect tightening torque value was applied to the 
pins, the service information specifies replacing the pins and 
contacting Airbus Helicopters.

    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 for Airbus Helicopters Model AS332L2 
and EC225LP helicopters, within 30 hours time-in-service (TIS) and 
thereafter following each flight, re-calculating the life limit 
accumulated by each front bolt part number (P/N) 332A22-1613-21 or 
332A22-1613-20 and rear bolt P/N 332A22-1614-20 by applying an add-on 
factor listed in the applicable service information. If the bolt meets 
or exceeds its life limit, also known as SLL, this proposed AD would 
require removing the bolt from service before further flight.

    For Model AS332L2 helicopters, within 30 hours TIS and thereafter 
following each flight, this proposed AD would require re-calculating 
the life limit accumulated by the front attachment fitting P/N 332A22-
1623-01, rear left hand attachment fitting P/N 332A22-1624-02 or 
332A22-1624-04, and rear right hand attachment fitting P/N 332A22-1624-
03 or 332A22-1624-05 by applying an add-on factor listed in the 
applicable service information. If the fitting meets or exceeds its 
life limit, this proposed AD would require removing the fitting from 
service before further flight.

    For Model AS332L2 helicopters, within 150 hours TIS (without 
applying an add on-factor), this proposed AD would require inspecting 
the torque of each MGB suspension bar fitting front and rear nut. If 
the torque on any nut is higher than the maximum allowable limit, the 
proposed AD would require removing the nut and its bolt from service 
before further flight. If the torque on any nut is lower than the 
minimum allowable limit, this proposed AD would require tightening the 
nut before further flight and removing the nut and its bolt from 
service within 150 hours TIS.

Differences Between This Proposed AD and the EASA AD

    The EASA AD allows an optional 150 hours TIS extension to the life 
limit of an affected fitting for Model AS 332 L2 helicopters by 
performing dye-penetrant inspections. This AD does not allow this 
option. For Model AS 332 L2 helicopters, the EASA AD requires replacing 
pins (bolts) that are replacement pins installed before the AD's 
effective date with an incorrect torque value applied. This AD requires 
inspecting the torque for each nut for Model AS332L2 helicopters 
instead and depending on the outcome, removing the nut and its bolt 
from service.

Costs of Compliance

    The FAA estimates that this proposed AD affects 23 helicopters of 
U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this proposed AD.

    Determining the adjusted life limit for the bolts and fittings 
would take about 0.5 work-hour for an estimated cost of $43 per 
helicopter and $989 for the U.S. fleet. Replacing a bolt would take 
about 4 work-hours and parts would cost about $89 for an estimated cost 
of $429 per bolt.

    There are no costs of compliance for replacing a fitting and 
inspecting, and if necessary tightening, the torque for Model AS332L2 
helicopters by this proposed AD because there are no Model AS332L2 
helicopters on the U.S. Registry.

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.

    The FAA prepared an economic evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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):