[Federal Register Volume 84, Number 139 (Friday, July 19, 2019)]
[Proposed Rules]
[Pages 34816-34819]
[FR Doc No: 2019-15413]

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 84, No. 139 / Friday, July 19, 2019 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0260; Product Identifier 2017-NE-13-AD]
RIN 2120-AA64

Airworthiness Directives; Ipeco Pilot and Co-Pilot Seats

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede airworthiness directive (AD)
2017-22-02, which applies to certain Ipeco Holdings Limited (Ipeco)
pilot and co-pilot seats. AD 2017-22-02 requires modification and re-
identification of the affected seats. Since the FAA issued AD 2017-22-
02, Ipeco has received reports that the tracklock spring modification
required by AD 2017-22-02 does not adequately address the issue of
unexpected seat movement during takeoff and landing and the FAA also
determined the need to add additional seat part numbers (P/Ns) to the
applicability. This proposed AD would continue to require modification
and re-identification of the affected seats. This proposed AD would
also require initial and repetitive inspections of the affected
tracklock springs and, depending on the findings, replacement of the
tracklock springs with a part eligible for installation. The FAA is
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by September
3, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Ipeco
Holdings Limited, Aviation Way, Southend-on-Sea, SS2 6UN, United
Kingdom; phone: 44 1702 549371; fax: 44 1702 540782; email:
<EMAIL_ADDRESS>You may view this service information at the FAA,
Engine & Propeller Standards Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0260; 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 NPRM, the mandatory continuing airworthiness information, the
regulatory 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 FURTHER INFORMATION CONTACT: Neil Doh, Aerospace Engineer, Boston
ACO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
781-238-7757; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2019-0260;
Product Identifier 2017-NE-13-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
    The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this proposed AD.

Discussion

    The FAA issued AD 2017-22-02, Amendment 39-19082 (82 FR 51552,
November 7, 2017), (``AD 2017-22-02''), for Ipeco pilot and co-pilot
seats. AD 2017-22-02 requires modification and re-identification of the
affected seats. AD 2017-22-02 resulted from reports of unexpected
movement of pilot and co-pilot seats during takeoff and landing. The
FAA issued AD 2017-22-02 to prevent unexpected movement of pilot and
co-pilot seats during takeoff and landing.

Actions Since AD 2017-22-02 Was Issued

    Since the FAA issued AD 2017-22-02, Ipeco has received reports that
the tracklock spring modification required by AD 2017-22-02 does not
adequately address the issue of unexpected seat movement during takeoff
and landing. As a result, Ipeco published Ipeco Service Bulletin (SB)
063-25-14, Revision 00, dated August 14, 2018, providing instructions
to inspect and replace, if necessary, affected tracklock springs. Also,
since the FAA issued AD 2017-22-02, the European Union Aviation Safety
Agency (EASA) has issued AD 2018-0262, dated December 6, 2018, which
retains the requirements of EASA AD 2016-0256, dated December 16, 2016,
and also requires repetitive inspection of seats and, depending on
findings, replacement of affected tracklock springs. Based on
discussions with Ipeco and EASA, the FAA also determined the need to
add additional seat part numbers (P/Ns) to the applicability. These
seat P/Ns are included in the applicability of EASA AD 2018-0262.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Ipeco Service Bulletin (SB) Number 063-25-08,
Revision 00; SB Number 063-25-09, Revision 00; and SB Number 063-25-10,
Revision 00; all dated May 31, 2016.

The SBs provide instructions, differentiated by the part numbers of the
affected pilot and co-pilot seats, for the modification and re-
identification of these seats. The FAA also reviewed Ipeco SB Number
063-25-14, Revision 00, dated August 14, 2018. This SB provides
instructions for inspection and replacement, if necessary, of affected
tracklock springs. 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.

FAA's Determination

    The FAA is proposing this AD because it evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2017-
22-02. This proposed AD would add additional seat P/Ns to the
applicability. This proposed AD would also require initial and
repetitive inspections of the affected tracklock springs and, depending
on the findings, replacement of the tracklock springs with a part
eligible for installation.

Differences Between the Proposed AD and MCAI or Service Information

    This proposed AD and EASA AD 2018-0262, dated December 6, 2018,
include pilot seat P/N 3A063-0099-01-1 and co-pilot seat P/N 3A063-
0100-01-1in their respective applicability sections, while Ipeco SB
Number 063-25-14, Revision 00, dated August 14, 2018, does not.

Costs of Compliance

    The FAA estimates that this proposed AD affects 110 pilot and co-
pilot seats installed on, but not limited to, ATR-GIE Avions de
Transport Regional (ATR) 42 and ATR 72 airplanes of U.S. registry. The
FAA estimates that seats installed on 34 ATR 42 airplanes and seats
installed on 21 ATR 72 airplanes will require modification and
inspection. The FAA is revising the estimated number of affected seats
in this cost estimate to include two affected seats per airplane.
    The FAA estimates the following costs to comply with this proposed
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect ATR 42 flight crew seats......  0.1 work-hours x $85 per              $0           $8.50            $289
                                         hour = $8.50.
Modify ATR 42 flight crew seats.......  2 work-hours x $85 per                56             226           7,684
                                         hour = $170.
Report results of ATR 42 inspection...  1.0 work-hours x 85 per                1              86           2,924
                                         hour = $85.
Inspect ATR 72 flight crew seats......  0.1 work-hours x 85 per                0            8.50             179
                                         hour = $8.50.
Modify ATR 72 flight crew seats.......  2 work-hours x 85 per                 56             226           4,746
                                         hour = $170.
Report results of ATR 72 inspection...  1.0 work-hours x 85 per                1              86           1,806
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The FAA has no way of determining the number of
aircraft that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Remove seat and replace ATR 42 tracklock        1.4 work-hours x $85 per hour =              $28            $147
 spring.                                         $119.
Remove seat and replace ATR 72 tracklock        1.4 work-hours x $85 per hour =               28             147
 spring.                                         $119.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all costs in
our cost estimate.

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 a 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 currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, 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.
    This AD is issued in accordance with authority delegated by the
Executive

Director, Aircraft Certification Service, as authorized by FAA Order
8000.51C. In accordance with that order, issuance of ADs is normally a
function of the Compliance and Airworthiness Division, but during this
transition period, the Executive Director has delegated the authority
to issue ADs applicable to engines, propellers, and associated
appliances to the Manager, Engine and Propeller Standards Branch,
Policy and Innovation Division.

Regulatory Findings

    The FAA has 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 above, I certify that the 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

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 removing airworthiness directive (AD)
2017-22-02, Amendment 39-19082 (82 FR 51552, November 7, 2017), and
adding the following new AD:

Ipeco Holdings Limited: Docket No. FAA-2019-0260; Product Identifier
2017-NE-13-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 3,
2019.

(b) Affected ADs

    This AD replaces AD 2017-22-02, Amendment 39-19082 (82 FR 51552,
November 7, 2017).

(c) Applicability

    (1) This AD applies to:
    (i) Ipeco Holdings Limited (Ipeco) pilot and co-pilot seats with
a part number (P/N) listed in Paragraph 1.A., Planning Information,
Tables 1 and 2, of Ipeco Service Bulletin (SB) Number 063-25-14,
Revision 00, dated August 14, 2018, and
    (ii) Ipeco pilot seat P/N 3A063-0099-01-1 and Ipeco co-pilot
seat P/N 3A063-0100-01-1.
    (2) These seats are installed on, but not limited to, ATR-GIE
Avions de Transport Regional ATR 42 and ATR 72 airplanes.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2510, Flight
Compartment Equipment.

(e) Unsafe Condition

    This AD was prompted by reports of tracklock spring failures
occurring on affected seats, including those seats already modified
by AD 2017-22-02. The FAA is issuing this AD to prevent unexpected
movement of pilot and co-pilot seats on takeoff and landing. The
unsafe condition, if not addressed, could result in reduced control
of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Required Action

    (1) For seats that have not installed the tracklock spring
modification kit, within two years after December 12, 2017 (the
effective date of AD 2017-22-02), modify and re-identify each
affected pilot and co-pilot seat. Use the Accomplishment
Instructions of Ipeco SB Number 063-25-08, Revision 00; Ipeco SB
Number 063-25-09, Revision 00; or Ipeco SB Number 063-25-10,
Revision 00; all dated May 31, 2016, as appropriate, to do the
modification and re-identification.
    (2) For all affected seats, within 750 flight hours (FHs) after
the effective date of this AD, and, thereafter at intervals not to
exceed 750 FHs, inspect the tracklock spring of each seat in
accordance with the Accomplishment Instructions, paragraph 3.2, of
the Ipeco SB Number 063-25-14, Revision 00, dated August 14, 2018.
    (i) If, during any inspection as required by paragraph (g)(2) of
this AD, any damage on, or incorrect installation of, any tracklock
spring is found on the pilot or co-pilot seat, before further
flight, replace both tracklock springs of the affected seat with a
part eligible for installation using the Accomplishment
Instructions, paragraphs <IP_ADDRESS> or <IP_ADDRESS>, as applicable, of the
Ipeco SB Number 063-25-14, Revision 00, dated August 14, 2018.
    (ii) [Reserved]
    (3) Within 30 days after the initial and repetitive inspections,
and thereafter for two years after the effective date of this AD,
send the inspection results, including no findings, to Ipeco at
<EMAIL_ADDRESS>
(h) Installation Prohibition

    After the effective date of this AD, do not install any pilot or
co-pilot seat identified in paragraph (c)(1)(i) of this AD unless
the seat is modified and re-identified as specified in paragraph
(g)(1) of this AD.

(i) Definition

    (1) For the purpose of this AD, ``damage'' can include cracks,
breaks, corrosion, or deformation of the tracklock spring.
    (2) For the purpose of this AD, ``incorrect installation'' is
installing the tracklock spring at an angle or position at odds with
Figures 6 and 7 of Ipeco SB Number 063-25-14, Revision 00, dated
August 14, 2018.
    (3) For the purpose of this AD, a ``part eligible for
installation'' is:
    (i) A modified seat provided, before installation, it has passed
an inspection (no damage or defect found).
    (ii) a tracklock spring provided that it passed an inspection
(no damage or defect found).

 (j) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a 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 currently valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, searching existing data sources,
gathering and maintaining the data needed, completing and reviewing
the collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden
estimate or any other aspect of this collection of information,
including suggestions for reducing this burden to: Information
Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston ACO 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 certification office, send it to the attention of the
person identified in paragraph (l)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.

(l) Related Information

    (1) For more information about this AD, contact Neil Doh,
Aerospace Engineer, Boston ACO Branch, FAA, 1200 District

Avenue, Burlington, MA 01803; phone:<PHONE_NUMBER>; fax: 781-238-
7199; email<EMAIL_ADDRESS>    (2) Refer to European Union Aviation Safety Agency AD 2018-0262,
dated December 6, 2018, for more information. You may examine the
EASA AD in the AD docket on the internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA-2019-0260.
    (3) For service information identified in this AD, contact Ipeco
Holdings Limited, Aviation Way, Southend-on-Sea, SS2 6UN, United
Kingdom; phone: 44 1702 549371; fax: 44 1702 540782; email:
<EMAIL_ADDRESS>You may view this referenced service information at
the FAA, Engine & Propeller Standards Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Burlington, Massachusetts, on July 12, 2019.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019-15413 Filed 7-18-19; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 83, Number 178 (Thursday, September 13, 2018)]
[Rules and Regulations]
[Pages 46384-46386]
[FR Doc No: 2018-19432]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0418; Product Identifier 2017-SW-016-AD; Amendment
39-19390; AD 2018-18-11]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model AS-365N2 and AS 365 N3 helicopters with a lower
strobe light installed. This AD requires installing a cable mount,
inspecting the lower strobe light wiring harness, and re-routing the
wiring harness. This AD was prompted by reports of interference between
the lower strobe light wiring harness and the helicopter structure. The
actions of this AD are intended to prevent an unsafe condition on these
helicopters.

DATES: This AD is effective October 18, 2018.
    The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of October 18,
2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.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. It is also available
on the internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0418.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0418; 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 AD, the European Aviation Safety Agency (EASA) AD, any
incorporated-by-reference service information, the economic evaluation,
any comments received, and other information. The street address for
Docket Operations (phone:<PHONE_NUMBER>) 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: George Schwab, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone<PHONE_NUMBER>;
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On May 11, 2018, at 83 FR 21964, the Federal Register published our
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR
part 39 by adding an AD that would apply to Airbus Helicopters Model
AS-365N2 and AS 365 N3 helicopters with a lower strobe light installed.
    The NPRM proposed to require installing a cable mount on the
helicopter structure and inspecting the lower strobe light electrical
harness and the electrical harness between the cut-off connector and
Frame 2000 for torn spiral tape and for any chafing on the harness
cables. If the spiral tape is torn, the NPRM proposed to require
replacing the spiral tape. If there is any chafing on the cable, the
NPRM proposed to require replacing the harness. The proposed
requirements were intended to prevent interference between the lower
strobe light electrical harness wiring and the helicopter structure,
which could result in chafing of an electrical harness adjacent to the
inboard fuel tank vapor space, a fuel tank fire, and subsequent loss of
control of the helicopter.
    The NPRM was prompted by AD No. 2016-0258, dated December 16, 2016,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters Model AS 365 N2 and AS 365 N3 helicopters with certain
serial numbers and configurations. EASA advises of in-production
helicopters with lower strobe light wiring harnesses that were
interfering with either the helicopter structure or the adjacent fuel
tank support. EASA further states that an investigation determined that
the electrical harnesses of these lower strobe lights were manufactured
with additional length to facilitate removal and installation of the
lower strobe light assembly. However, the additional length of wiring
in the harness was not properly secured to the helicopter structure.
According to EASA, this could result in chafing of the harness on the
helicopter structure, creating an ignition source adjacent to the
inboard fuel tank vapor space, and result in a fuel tank fire.
    To address this unsafe condition, the EASA AD requires installing a
cable mount, inspecting the lower strobe light electrical harness for
damage, and re-routing the electrical harness.

Comments

    We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed.

Differences Between This AD and the EASA AD

    The EASA AD limits the applicability to helicopters with a lower
strobe light installed and with certain serial numbers or that are in a
configuration based upon a modification, service information, or
engineering drawings. This AD applies to all Model AS-365N2 and AS 365
N3 helicopters with a lower strobe light installed.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin No. AS365-
05.00.73, Revision 1, dated December 12, 2016, which specifies
procedures for inspecting the lower strobe light electrical harness for
interference and chafing with the helicopter structure and also
specifies procedures for installing a cable mount to secure the
electrical harness. These procedures correspond to Airbus Helicopters
modification (MOD) 365P084778.00.
    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.

Costs of Compliance

    We estimate that this AD affects 30 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD.
    At an average labor rate of $85 per work-hour, installing a cable
mount and inspecting the strobe light wiring harnesses requires about 1
work-hour, and required parts cost about $50, for a cost of $135 per
helicopter and a total cost of $4,050 to all U.S. operators.
    If required, replacing torn spiral tape requires about 1 work-hour,
and required parts cost $45, for a cost of $130 per helicopter.
    If required, replacing a chafed wiring harness between the cut-off
connector and Frame 2000 requires about 3 work-hours, and required
parts cost $90, for a cost of $345 per helicopter.
    If required, replacing a chafed lower strobe light wiring harness
requires about 3 work-hours, and required parts cost $154, for a cost
of $409 per helicopter.

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.
    We are 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 helicopters 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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
    (4) 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.
    We prepared an economic evaluation of the estimated costs to comply
with this 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.

Adoption of 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

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):

2018-18-11 Airbus Helicopters: Amendment 39-19390; Docket No. FAA-
2018-0418; Product Identifier 2017-SW-016-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS-365N2 and AS 365
N3 helicopters, certificated in any category, with a lower strobe
light installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as interference between the
lower strobe light electrical harness wiring and the helicopter
structure. This condition could result in chafing of an electrical
harness adjacent to the inboard fuel tank vapor space, a fuel tank
fire, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective October 18, 2018.

(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

    Within 50 hours time-in-service:
    (1) Install cable mount part number (P/N) ASMS-A to the
helicopter structure as depicted in Figure 1, Detail A and Detail C,
of Airbus Helicopters Alert Service Bulletin No. AS365-05.00.73,
Revision 1, dated December 12, 2016 (ASB AS365-05.00.73).
    (2) Inspect the lower strobe light harness and the harness
between the cut-off connector and Frame 2000 for tears in the spiral
tape and for chafing of the harness wires. If there is a tear in the
spiral tape, before further flight, replace the spiral tape. If
there is any chafing, before further flight, replace the chafed
harness.
    (3) Route the lower strobe light harness and the harness between
the cut-off connector and Frame 2000 and secure as depicted in
Figure 1, Detail A and Section B-B, of ASB AS365-05.00.73.

    Note 1 to paragraph (e) of this AD: Airbus Helicopters
identifies the actions in ASB AS365-05.00.73 as Modification
365P084778.00.

(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:
George Schwab, Aviation Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone<PHONE_NUMBER>; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest 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. 2016-0258, dated December 30, 2016. You may
view the EASA AD on the internet at http://www.regulations.gov in
Docket No. FAA-2018-0418.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 3340, Lights.

(i) 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 the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin No. AS365-
05.00.73, Revision 1, dated December 12, 2016.
    (ii) Reserved.
    (3) For Airbus Helicopters service information identified in
this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax
(972) 641-3775; or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
    (4) You may view this service information at 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<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on August 28, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-19432 Filed 9-12-18; 8:45 am]
 BILLING CODE 4910-13-P