[Federal Register Volume 84, Number 236 (Monday, December 9, 2019)]
[Proposed Rules]
[Pages 67246-67248]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-26428]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-1015; Product Identifier 2018-SW-104-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. This proposed AD would require determining the accumulated 
hours time-in-service (TIS) of certain part-numbered main gearbox (MGB) 
suspension bar attachment fittings (fittings) and bolts, and would 
establish new life limits. This proposed AD is prompted by the outcome 
of tests and analyses performed by Airbus Helicopters. 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-2019-
1015; 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 [email protected].

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 that the FAA receives, 
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 the FAA receives 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 the FAA receives.

[[Page 67247]]

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2018-0260, dated December 3, 
2018 (EASA AD 2018-0260), to correct an unsafe condition for Airbus 
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale) 
Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters.
    From 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 
screws (bolts). Due to design similarities, Model AS332L2 helicopters 
could also be affected by the same installation condition. 
Investigations determined that the life limits in the Airworthiness 
Limitations Sections for the screws and fittings are valid if an ``add-
on penalty factor'' is applied. Based on these findings, EASA issued 
EASA AD No. 2017-0133 dated July 27, 2017, and then superseded that AD 
with EASA AD No. 2017-0189, dated September 22, 2017, for Model AS 332 
L2 and EC 225 LP helicopters to address this condition.
    Airbus Helicopter subsequently performed testing on Model AS 332 C, 
AS 332 C1, AS 332 L, and AS 332 L1 helicopters due to design 
similarities, and determined a life limit reduction of the MGB 
suspension bar fittings and screws was necessary for these model 
helicopters. Accordingly, EASA AD 2018-0260 was issued for these model 
helicopters to require determining the accumulated service life of the 
affected parts and to introduce new life limits.
    EASA states that this condition, if not corrected, could lead to 
structural failure of the MGB suspension bar fittings and screws, 
possibly resulting in detachment of the MGB suspension bars.

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

    The FAA reviewed Airbus Helicopters Alert Service Bulletin No. 
AS332-01.00.90, Revision 0, dated November 11, 2018. This service 
information specifies determining the accumulated hours TIS of certain 
part-numbered rear MGB suspension bar fittings and screws. This service 
information further specifies criteria to determine the initial 
replacement compliance time of those parts and a new life limit for 
those parts thereafter. This service information also establishes a 
life limit for the front MGB attachment screws.

Proposed AD Requirements

    This proposed AD would require, within 50 hours TIS, reviewing the 
helicopter records to determine the total hours TIS of the MGB 
suspension bar right-hand side (RH) rear fitting part number (P/N) 
330A22-2702-07 and of the MGB suspension bar left-hand side (LH) rear 
fitting P/N 330A22-2702-06. This proposed AD would initially require 
removing from service the RH rear fitting and its bolts P/N 330A22-
0135-20 and the LH rear fitting and its bolts P/N 330A22-0135-20 based 
on the accumulated total hours TIS of the fittings and other 
conditions. Thereafter, this proposed AD would require removing from 
service the RH rear fitting and its bolts at intervals not to exceed 
1,470 hours TIS, removing from service the LH rear fitting at intervals 
not to exceed 13,600 hours TIS, and removing from service the LH rear 
bolts during each Major Inspection ``G.'' This proposed AD would also 
require removing from service the front bolts P/N 330A22-0134-20 during 
each Major Inspection ``G.''

Differences Between This Proposed AD and the EASA AD

    The EASA AD allows an option for the first MGB RH rear attachment 
fitting replacement to inspect torque and specifies different 
replacement compliance times based on the torque inspection results, 
whereas this proposed AD does not.

Interim Action

    The FAA considers this proposed AD to be an interim action. The 
design approval holder is currently developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA might 
consider additional rulemaking.

Costs of Compliance

    The FAA estimates that this proposed AD affects 14 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 total hours TIS of the rear MGB fittings would take 
about 0.5 work-hour for an estimated cost of $43 per helicopter and 
$602 for the U.S. fleet.
    Replacing a rear MGB fitting and its set of four bolts would take 
about 8 work-hours and parts would cost about $12,937, for an estimated 
cost of $13,617 per replacement cycle.
    Replacing a set of four MGB attachment bolts would take about 4 
work-hours and parts would cost about $224, for an estimated cost of 
$564 per replacement cycle.
    Replacing a LH rear MGB fitting would take about 8 work-hours and 
parts would cost about $12,713, for an estimated cost of $13,393 per 
replacement cycle.

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.

[[Page 67248]]

    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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus Helicopters: Docket No. FAA-2019-1015; Product Identifier 
2018-SW-104-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category, with 
a main gearbox (MGB) suspension bar right-hand side (RH) rear 
attachment fitting (fitting) part number (P/N) 330A22-2702-07 and 
bolt P/N 330A22-0135-20, MGB suspension bar left-hand side (LH) rear 
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB 
suspension bar front bolt P/N 330A22-0134-20 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as MGB suspension bar 
fittings and bolts remaining in service beyond their fatigue life. 
This condition could result in failure of an MGB attachment 
assembly, detachment of an MGB suspension bar, and subsequent 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 50 hours time-in-service (TIS), review records to 
determine the total hours TIS of each MGB suspension bar RH and LH 
rear fitting.
    (i) For any RH rear fitting that has accumulated 1,470 or more 
total hours TIS, before further flight, remove from service the RH 
rear fitting and its bolts.
    (ii) For any RH rear fitting that has accumulated less than 
1,470 total hours TIS, remove from service the RH rear fitting and 
its bolts before the fitting accumulates 1,470 total hours TIS.
    (iii) For any LH rear fitting that has accumulated 13,600 or 
more total hours TIS, before further flight, remove from service the 
LH rear fitting and its bolts.
    (iv) For any LH rear fitting that has accumulated less than 
13,600 total hours TIS:
    (A) If a Major Inspection ``G'' has not been completed since the 
LH rear fitting has been installed, remove from service the LH rear 
bolts during the next Major Inspection ``G'' inspection; or
    Note 1 to paragraph (e)(iv)(A) of this AD: Major Inspection 
``G'' (7,500 hours TIS between overhauls) is defined in Maintenance 
Manual MET 05-29-00-601.
    (B) If a Major Inspection ``G'' has been completed since the LH 
rear fitting has been installed, before further flight, remove from 
service the LH rear bolts; and
    (C) Remove from service the LH rear fitting before the fitting 
accumulates 13,600 total hours TIS.
    (2) Thereafter following paragraph (e)(1) of this AD, remove 
from service any RH rear fitting and its bolts at intervals not to 
exceed 1,470 hours TIS, remove from service any LH rear fitting at 
intervals not to exceed 13,600 hours TIS, and remove from service 
any LH rear bolts during each Major Inspection ``G.''
    (3) During the next Major Inspection ``G,'' remove from service 
the MGB suspension bar front bolts. Thereafter, remove from service 
the front bolts during each Major Inspection ``G.''

(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 [email protected].
    (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

    (1) Airbus Helicopters Alert Service Bulletin No. AS332-
01.00.90, Revision 0, dated November 11, 2018, which is not 
incorporated by reference, contains additional information about the 
subject of this AD. For service information identified in this AD, 
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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2018-0260, dated December 3, 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: 6320, Main Rotor 
Gearbox.

    Issued in Fort Worth, Texas, on November 29, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-26428 Filed 12-6-19; 8:45 am]
 BILLING CODE 4910-13-P