[Federal Register Volume 83, Number 48 (Monday, March 12, 2018)]
[Rules and Regulations]
[Pages 10563-10565]
[FR Doc No: 2018-04872]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0181; Product Identifier 2017-SW-085-AD; Amendment
39-19219; AD 2018-05-10]
RIN 2120-AA64

Airworthiness Directives; Agusta S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model AB412 and AB412 EP helicopters. This AD requires
removing each shoulder harness seat belt comfort clip (comfort clip)
and inspecting the seat belt shoulder harness. This AD is prompted by a
report of a comfort clip interfering with the seat belt inertia reel.
The actions of this AD are intended to prevent an unsafe condition on
these helicopters.

DATES: This AD becomes effective March 27, 2018.
    We must receive comments on this AD by May 11, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
     Fax:<PHONE_NUMBER>.

     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 http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0181; 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 comments
received, and other information. The street address for Docket
Operations (telephone<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
    For service information identified in this final rule, contact
Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness,
Viale G. Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone
+39-0331-711756; fax +39-0331-229046; or at http://www.leonardocompany.com/-/bulletins. 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<PHONE_NUMBER>;
email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, 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 them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.

Discussion

    EASA, which is the Technical Agent for the Member States of the
European Union, has issued AD No. 2016-0054, dated March 14, 2016, to
correct an unsafe condition for Finmeccanica S.p.A. (previously Agusta)
Model AB412 and AB412 EP helicopters. EASA advises that a design review
resulted in the determination that some passenger seat installations
allow the use of comfort clips on flight crew and passenger shoulder
harness seat belts to increase comfort to the occupant by locking the
seat belt position. These comfort clips could prevent the seat belt
inertia reel from retracting the shoulder harness during an emergency
landing. The EASA AD further advises that this could result in injury
to the seat occupant. To prevent this unsafe condition, the EASA AD
requires removal of all comfort clips from service and inspecting the
seat belt for wear from the comfort clip.
    The FAA is in the process of updating Agusta's name change to
Finmeccanica, and then to Leonardo Helicopters, on its FAA type
certificate. Because this name change is not yet effective, this AD
specifies Agusta.

FAA's Determination

    These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, 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.

Related Service Information

    Finmeccanica has issued Bollettino Tecnico No. 412-145, dated March
8, 2016, which specifies procedures for removing each comfort clip from
the crew and passenger shoulder harness seat belts and for inspecting
the seat belts for wear.

AD Requirements

    This AD requires, within 50 hours time-in-service, removing from
service any comfort clip installed on a crew or passenger shoulder
harness seat belt and inspecting the shoulder harness seat belt for
rips or abrasions. If there is a rip or any abrasion, the AD requires
replacing the seat belt. This AD also prohibits installing a comfort
clip on any shoulder harness seat belt.

Costs of Compliance

    There are no costs of compliance with this AD because there are no
helicopters with this type certificate on the U.S. Registry.

FAA's Justification and Determination of the Effective Date

    There are no helicopters with this type certificate on the U.S.
Registry. Therefore, we find good cause that notice and opportunity for
prior public comment are unnecessary. In addition, for the reason
stated above, we find that good cause exists for making this amendment
effective in less than 30 days.

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 products identified in this
rulemaking action.

Regulatory Findings

    We determined that 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, 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.

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):

2018-05-10 Agusta S.p.A.: Amendment 39-19219; Docket No. FAA-2018-
0181; Product Identifier 2017-SW-085-AD.

(a) Applicability

    This AD applies to Agusta S.p.A. Model AB412 and AB412 EP
helicopters with a seat belt comfort clip installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as a shoulder harness seat
belt comfort clip interfering with the seat belt inertia reel, which
could prevent the seatbelt from locking and result in injury to the
occupant during an emergency landing.

(c) Effective Date

    This AD becomes effective March 27, 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

    (1) Within 50 hours time-in-service:
    (i) Remove from service each seat belt comfort clip.
    (ii) Inspect each shoulder harness seat belt for a rip and
abrasion. If there is a rip or any abrasion, before further flight,
replace the shoulder harness seat belt.
    (2) After the effective date of this AD, do not install a
shoulder harness seat belt comfort clip on any helicopter.

(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<PHONE_NUMBER>; email; 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

    (1) Finmeccanica Bollettino Tecnico No. 412-145, dated March 8,
2016, which is not incorporated by reference, contains additional
information about the subject of this AD. For service information
identified in this AD, contact Leonardo S.p.A. Helicopters, Matteo
Ragazzi, Head of Airworthiness, Viale G. Agusta 520, 21017 C. Costa
di Samarate (Va) Italy; telephone +39-0331-711756; fax +39-0331-
229046; or at http://www.leonardocompany.com/-/bulletins. You may
review a copy of the 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. 2016-0054, dated March 14, 2016. You may
view the EASA AD on the internet at http://www.regulations.gov by
searching for and locating it in Docket No. FAA-2018-0181.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 2500 Cabin
Equipment/Furnishings.

    Issued in Fort Worth, Texas, on March 2, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2018-04872 Filed 3-9-18; 8:45 am]
 BILLING CODE 4910-13-P


claims agreement. The reciprocal waiver of claims must be in a form
acceptable to the Administrator.
* * * * *
    (f) The licensee or permittee and each space flight participant
must enter into a reciprocal waiver of claims agreement under which
each party waives and releases claims against the other party to the
waiver, and agrees to assume financial responsibility for property
damage it sustains and for bodily injury or property damage, and to
hold harmless and indemnify each other from bodily injury or property
damage, resulting from a licensed or permitted activity, regardless of
fault. This paragraph (f) shall cease to be effective as of September
30, 2025, unless public law modifies the limitation in section 50914 of
Title 51 of the U.S. Code.
    (g) Any waiver, release, assumption of responsibility or agreement
to hold harmless and indemnify pursuant to this section does not apply
to claims for

bodily injury or property damage resulting from willful misconduct of
any of the parties to the reciprocal waiver of claims, the contractors
and subcontractors of any of the parties to the reciprocal waiver of
claims, and in the case of licensee or permittee and customers and the
contractors and subcontractors of each of them, the directors,
officers, agents and employees of any of the foregoing, and in the case
of the United States, its agents.

Appendix B Through E to Part 440--[Removed]

0
34. Remove appendices B through E to part 440.

PART 450--LAUNCH AND REENTRY LICENSE REQUIREMENTS

0
35. The authority citation for part 450 continues to read as follows:

    Authority:  51 U.S.C. 50901-50923.
0
36. Amend Sec.  450.45 by revising paragraphs (e)(3)(ii)(E) and (e)(5)
to read as follows:

Sec.  450.45   Safety review and approval.

* * * * *
    (e) * * *
    (3) * * *
    (ii) * * *
    (E) For an unguided suborbital launch vehicle, the location of the
vehicle's center of pressure in relation to its center of gravity for
the entire flight profile.
* * * * *
    (5) Human space flight. For a proposed launch or reentry with a
human being on board a vehicle, an applicant must demonstrate
compliance with Sec. Sec.  460.5, 460.7, 460.11, 460.13, 460.15,
460.17, 460.51, 460.53, 460.59, 460.61, and 460.67 of this chapter.
* * * * *

PART 460--HUMAN SPACE FLIGHT REQUIREMENTS

0
37. The authority citation for part 460 continues to read as follows:

    Authority:  51 U.S.C. 50901-50923.

0
38. Add subpart C to read as follows:
Subpart C--Launch and Reentry With a Government Astronaut With a
Safety-Critical Role
Sec.
460.55 Scope.
460.57 Applicability.
460.59 Operator training of government astronauts with a safety-
critical role.
460.61 Environmental control and life support systems.

Subpart C--Launch and Reentry With a Government Astronaut With a
Safety-Critical Role

Sec.  460.55   Scope.

    This subpart establishes requirements for operators and applicants
whose licensed or permitted operations involve government astronauts on
board a vehicle.

Sec.  460.57   Applicability.

    This subpart applies to:
    (a) An applicant for a license or permit under this chapter who
proposes to have a government astronaut with a safety-critical role on
board a vehicle.
    (b) An operator licensed or permitted under this chapter who has a
government astronaut without a safety-critical role on board a vehicle.

Sec.  460.59   Operator training of government astronauts with a
safety-critical role.

    (a) An operator must train each government astronaut with a safety-
critical role on--
    (1) How to carry out their safety-critical role on board or on the
ground so that the vehicle will not harm the public; and
    (2) Their role in nominal and non-nominal conditions, including
abort scenarios and emergency operations, to the extent that
performance of their role could impact public safety.
    (b) An operator must ensure any government astronaut who has the
ability to control, in real time, a launch or reentry vehicle's flight
path during a phase of flight capable of endangering the public:
    (1) Receives vehicle and mission-specific training for each phase
of flight capable of endangering the public and over which the
government astronaut has the ability to control the vehicle by using
one or more of the following:
    (i) A method or device that simulates the flight;
    (ii) An aircraft whose characteristics are similar to the vehicle
or that has similar phases of flight to the vehicle;
    (iii) Flight testing; or
    (iv) An equivalent method of training approved by the FAA through
the license process.
    (2) Trains for each mode of control or propulsion, including any
transition between modes, such that the government astronaut is able to
control the vehicle.
    (3) Possesses aeronautical knowledge, experience, and skills
necessary to pilot and control the launch or reentry vehicle that will
operate in the National Airspace System (NAS). Aeronautical experience
may include hours in flight, ratings, and training.
    (c) With respect to training device fidelity, an operator must:
    (1) Ensure that any government astronaut training device used to
meet the training requirements realistically represents the vehicle's
configuration and mission; or,
    (2) Inform the government astronaut being trained of the
differences between the training device and the vehicle's configuration
and mission.
    (d) An operator must update the government astronaut training
continually to ensure that the training incorporates lessons learned
from training and operational missions including--
    (1) Tracking each revision and updating in writing; and
    (2) Documenting the completed training for each government
astronaut and maintaining the documentation for each active government
astronaut.
    (e) An operator must establish a recurrent training schedule and
ensure that all training of government astronauts performing safety-
critical roles is current before launch or reentry.

Sec.  460.61   Environmental control and life support systems.

    (a) An operator must provide atmospheric conditions adequate to
sustain life and consciousness for all inhabited areas within a vehicle
that house a government astronaut. The operator must monitor and
control the following atmospheric conditions in the inhabited areas or
demonstrate through the license or permit process that an alternate
means provides an equivalent level of safety--
    (1) Composition of the atmosphere, which includes oxygen and carbon
dioxide, and any revitalization;
    (2) Pressure, temperature and humidity;
    (3) Contaminants that include particulates and any harmful or
hazardous concentrations of gases, or vapors; and
    (4) Ventilation and circulation.
    (b) An operator must provide an adequate redundant or secondary
oxygen supply for any government astronaut with a safety-critical role.
    (c) An operator must provide a redundant means of preventing cabin
depressurization; or prevent incapacitation of any government astronaut
with a safety-critical role in the event of loss of cabin pressure.
0
39. Add subpart D to read as follows:
Subpart D--Launch and Reentry With a Government Astronaut Without a
Safety-Critical Role
Sec.
460.63 Scope.
460.65 Applicability.

460.67 Operator training of government astronauts without a safety-
critical role.

Subpart D--Launch and Reentry With a Government Astronaut Without a
Safety-Critical Role

Sec.  460.63   Scope.

    This subpart establishes requirements for operators and applicants
whose licensed or permitted operations involve government astronauts on
board a vehicle without a safety-critical role.

Sec.  460.65   Applicability.

    This subpart applies to:
    (a) An applicant for a license or permit under this chapter who
proposes to have a government astronaut without a safety-critical role
on board a vehicle.
    (b) An operator licensed or permitted under this chapter who has a
government astronaut without a safety-critical role on board a vehicle.

Sec.  460.67   Operator training of government astronauts without a
safety-critical role.

    An operator must train each government astronaut without a safety-
critical role on how to respond to emergency situations, including
smoke, fire, loss of cabin pressure, and emergency exit.
    Issued under authority provided by 49 U.S.C. 106(f) and 51 U.S.C.
Chapter 509 in Washington, DC.

Kelvin B. Coleman,
Associate Administrator, Office of Commercial Space Transportation.
[FR Doc. 2023-16858 Filed 8-17-23; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 77, Number 150 (Friday, August 3, 2012)]
[Rules and Regulations]
[Pages 46282-46283]
[FR Doc No: 2012-18921]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Docket No. FAA-2011-0829; Airspace Docket No. 11-ASW-9]

Amendment of Class E Airspace; Sweetwater, TX

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: This action amends Class E airspace at Sweetwater, TX.
Additional controlled airspace is necessary to accommodate new Area
Navigation (RNAV) Standard Instrument Approach Procedures at Avenger
Field Airport. The airport's geographic coordinates are adjusted and
the airport name changed. The FAA is taking this action to enhance the
safety and management of Instrument Flight Rule (IFR) operations at the
airport.

DATES: Effective date: 0901 UTC, November 15, 2012. The Director of the
Federal Register approves this incorporation by reference action under
1 CFR part 51, subject to the annual revision of FAA Order 7400.9 and
publication of conforming amendments.

FOR FURTHER INFORMATION CONTACT: Scott Enander, Central Service Center,
Operations Support Group, Federal Aviation Administration, Southwest
Region, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone 817-321-
7716.

SUPPLEMENTARY INFORMATION:

History

    On May 21, 2012, the FAA published in the Federal Register a notice
of proposed rulemaking (NPRM) to amend Class E airspace for the
Sweetwater, TX, area, creating additional controlled airspace at
Avenger Field Airport (77 FR 29917) Docket No. FAA-2011-0829.
Interested parties were invited to participate in this rulemaking
effort by submitting written comments on the proposal to the FAA. No
comments were received. Class E airspace designations are published in
paragraph 6005 of FAA Order 7400.9V dated August 9, 2011, and effective
September 15, 2011, which is incorporated by reference in 14 CFR 71.1.
The Class E airspace designations listed in this document will be
published subsequently in the Order.

The Rule

    This action amends Title 14 Code of Federal Regulations (14 CFR)
Part 71 by amending Class E airspace extending upward from 700 feet
above the surface to accommodate new standard instrument approach
procedures at Avenger Field Airport (formerly Avenger Field),
Sweetwater, TX. This action is necessary for the safety and management
of IFR operations at the airport. Geographic coordinates of the airport
are updated to coincide with the FAA's aeronautical database.
    The FAA has determined that this regulation only involves an
established body of technical regulations for which frequent and
routine amendments are necessary to keep them operationally current.
Therefore, this regulation: (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); and (3) does not warrant preparation of a regulatory evaluation
as the anticipated impact is so minimal. Since this is a routine matter
that will only affect air traffic procedures and air navigation, it is
certified that this rule, when promulgated, will not have a significant
economic impact on a substantial number of small entities under the
criteria of the Regulatory Flexibility Act.
    The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the U.S. Code. Subtitle 1, Section 106, describes
the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the agency's authority.
This rulemaking is promulgated under the authority described in
Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the
FAA is charged with prescribing regulations to assign the use of
airspace necessary to ensure the safety of aircraft and the efficient
use of airspace. This regulation is within the scope of that authority
as it amends controlled airspace at Avenger Field Airport, Sweetwater,
TX.

Environmental Review

    The FAA has determined that this action qualifies for categorical
exclusion under the National Environmental Policy Act in accordance
with FAA Order 1050.1E, ``Environmental Impacts: Policies and
Procedures,'' paragraph 311a. This airspace action is not expected to
cause any potentially significant environmental impacts, and no
extraordinary circumstances exist that warrant preparation of an
environmental assessment.

List of Subjects in 14 CFR Part 71

    Airspace, Incorporation by reference, Navigation (Air).

Adoption of the Amendment

    In consideration of the foregoing, the Federal Aviation
Administration amends 14 CFR part 71 as follows:

PART 71--DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR
TRAFFIC SERVICE ROUTES; AND REPORTING POINTS

0
1. The authority citation for 14 CFR part 71 continues to read as
follows:

    Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E.O. 10854, 24
FR 9565, 3 CFR, 1959-1963 Comp., p. 389.

Sec.  71.1  [Amended]

0
2. The incorporation by reference in 14 CFR 71.1 of the Federal
Aviation Administration Order 7400.9V, Airspace Designations and
Reporting Points, dated August 9, 2011, and effective September 15,
2011, is amended as follows:

Paragraph 6005 Class E airspace areas extending upward from 700
feet or more above the surface.

* * * * *

ASW TX E5 Sweetwater, TX [Amended]

Sweetwater, Avenger Field Airport, TX
    (Lat. 32[deg]28'03'' N., long. 100[deg]28'00'' W.)
Sweetwater RBN
    (Lat. 32[deg]27'42'' N., long. 100[deg]27'56'' W.)

    That airspace extending upward from 700 feet above the surface
within a 6.6-mile radius of Avenger Field Airport, and within 2.5
miles each side of the 348[deg] bearing from the Sweetwater RBN
extending from the 6.6-mile radius to 7.4 miles north of the
airport, and within 2 miles each side of the 174[deg] bearing from
the airport extending from the 6.6-mile radius to 12 miles south of
the airport.

    Issued in Fort Worth, Texas, on July 25, 2012.
David P. Medina,
Manager, Operations Support Group, ATO Central Service Center.
[FR Doc. 2012-18921 Filed 8-2-12; 8:45 am]
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[Federal Register Volume 82, Number 243 (Wednesday, December 20, 2017)]
[Rules and Regulations]
[Pages 60304-60306]
[FR Doc No: 2017-27388]

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DEPARTMENT OF COMMERCE

Bureau of Industry and Security

15 CFR Part 744

[Docket No. 140908761-7999-02]
RIN 0694--AG29

Addition of Certain Entities to the Entity List

AGENCY: Bureau of Industry and Security, Commerce.

ACTION: Final rule.

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SUMMARY: This rule amends the Export Administration Regulations (EAR)
by adding two entities to the Entity List. The two entities being added
to the Entity List have been determined by the U.S. Government to be
acting contrary to the national security or foreign policy interests of
the United States. These two entities will be listed on the Entity List
under the destination of Russia.

DATES: This rule is effective December 20, 2017.

FOR FURTHER INFORMATION CONTACT: Chair, End-User Review Committee,
Office of the Assistant Secretary, Export Administration, Bureau of
Industry and Security, Department of Commerce, Phone:<PHONE_NUMBER>,
Email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The Entity List (Supplement No. 4 to part 744 of the Export
Administration Regulations (EAR)) identifies entities and other persons
reasonably believed to be involved, or to pose a significant risk of
being or becoming involved, in activities contrary to the national
security or foreign policy interests of the United States. The EAR
imposes additional license requirements on, and limits the availability
of most license exceptions for, exports, reexports, and transfers (in-
country) to those listed. The ``license review policy'' for each listed
entity or other person is identified in the License Review Policy
column on the Entity List and the impact on the availability of license
exceptions is described in the Federal Register document adding
entities or other persons to the Entity List. BIS places entities and
other persons on the Entity List pursuant to sections of part 744
(Control Policy: End-User and End-Use Based) and part 746 (Embargoes
and Other Special Controls) of the EAR.
    The End-User Review Committee (ERC), composed of representatives of
the Departments of Commerce (Chair), State, Defense, Energy and, where
appropriate, the Treasury, makes all decisions regarding additions to,
removals from, or other modifications to the Entity List. The ERC makes
decisions to add an entry to the Entity List by majority vote and
decisions to remove or modify an entry by unanimous vote. The
Departments represented on the ERC have approved these changes to the
Entity List.

ERC Entity List Decisions

Additions to the Entity List

    This rule implements the decision of the ERC to add two entities to
the Entity List. These two entities are being added on the basis of
Sec.  744.11 (License requirements that apply to entities acting
contrary to the national security or foreign policy interests of the
United States) of the EAR. The two entries added to the Entity List
consist of two entities located in Russia.
    Under Sec.  744.11(b) (Criteria for revising the Entity List) of
the EAR, persons for whom there is reasonable cause to believe, based
on specific and articulable facts, that they have been involved, are
involved, or pose a significant risk of being or becoming involved in,
activities that are contrary to the national security or foreign policy
interests of the United States and those acting on behalf of such
persons may be added to the Entity List. Paragraphs (b)(1) through
(b)(5) of Sec.  744.11 provide an illustrative list of activities that
could be contrary to the national security or foreign policy interests
of the United States.
    BIS, pursuant to Section 744.11(b) of the EAR, and in consultation
with the Departments of State, Defense, Energy and the Treasury, has
designated the two persons, located in the Russian Federation, to be
added to the Entity List for actions contrary to the national security
or foreign policy interests of the United States. Specifically, these
entities produced, for the Russian Federation Ministry of Defense, a
ground-launched cruise missile system, and associated transporter-
erector-launcher, with a range prohibited by the Intermediate-Range
Nuclear Forces Treaty. Both the Russian Federation and the United
States are party to the INF Treaty. Therefore, there is reasonable
cause to believe, based on specific and articulable facts, that Joint
Stock Company Experimental Design Bureau Novator, and Joint Stock
Company Federal Scientific and Production Center Titan-Barrikady have
been involved in actions contrary to the national security or foreign
policy interests of the United States.
    The prior review of exports, reexports or transfers (in-country) of
all items subject to the EAR involving these persons, and the possible
imposition of license conditions or license denials on shipments to the
persons, will enhance BIS's ability to prevent use of items subject to
the EAR contrary to U.S. national security or foreign policy interests.
    For the two persons added to the Entity List, BIS imposes a license
requirement for all items subject to the EAR, and a license review
policy of presumption of denial. The license requirements apply to any
transaction in which items are to be exported, reexported, or
transferred (in-country) to either of the persons or in which such
persons act as purchaser, intermediate consignee, ultimate consignee,
or end-user. In addition, no license exceptions are available for
exports, reexports, or transfers (in-country) to the persons being
added to the Entity List in this rule. The acronym ``a.k.a.'' (also
known as) is used in entries on the Entity List to identify aliases and
help exporters, reexporters and transferors to better identify persons
on the Entity List.
    This final rule adds the following two entities to the Entity List:

Russia

    (1) Joint Stock Company Experimental Design Bureau Novator, a.k.a.,
the following two aliases:

--Novator Design Bureau; and
--JSC OKB Novator.

    18 Prospekt Kosmonavtov, 620017 Yekaterinburg, Russia; and
    (2) Joint Stock Company Federal Scientific and Production Center
Titan-Barrikady, a.k.a., the following three aliases:

--Federal Research and Production Center Titan Barrikady JSC;
--Titan Design Bureau; and
--JSC FNPTS Titan-Barrikady.

    Prospekt Imeni V.I. Lenina, b/n 400071, Volgograd, Russia.

Export Administration Act of 1979

    Although the Export Administration Act of 1979 expired on August
20, 2001, the President, through Executive Order 13222 of August 17,
2001, 3 CFR, 2001 Comp., p. 783 (2002), as amended by Executive Order
13637 of March 8, 2013, 78 FR 16129 (March 13, 2013) and as extended by
the Notice of August 15, 2017, 82 FR 39005 (August 16, 2017), has
continued the Export Administration Regulations in effect under the
International Emergency Economic Powers Act. BIS continues to carry out
the provisions of the Export Administration Act of 1979, as appropriate
and to the extent permitted by law, pursuant to Executive Order

13222, as amended by Executive Order 13637.

Rulemaking Requirements

    1. Executive Orders 13563 and 12866 direct agencies to assess all
costs and benefits of available regulatory alternatives and, if
regulation is necessary, to select regulatory approaches that maximize
net benefits (including potential economic, environmental, public
health and safety effects, distributive impacts, and equity). Executive
Order 13563 emphasizes the importance of quantifying both costs and
benefits, of reducing costs, of harmonizing rules, and of promoting
flexibility. This rule has been determined to be not significant for
purposes of Executive Order 12866. This rule is not an Executive Order
13771 regulatory action because this rule is not significant under
Executive Order 12866.
    2. Notwithstanding any other provision of law, no person is
required to respond to nor be subject to a penalty for failure to
comply with a collection of information, subject to the requirements of
the Paperwork Reduction Act of 1995 (44 U.S.C. 3501 et seq.) (PRA),
unless that collection of information displays a currently valid Office
of Management and Budget (OMB) Control Number. This regulation involves
collections previously approved by OMB under control number 0694-0088,
Simplified Network Application Processing System, which includes, among
other things, license applications, and carries a burden estimate of
43.8 minutes for a manual or electronic submission.
    Total burden hours associated with the PRA and OMB control number
0694-0088 are not expected to increase as a result of this rule. You
may send comments regarding the collection of information associated
with this rule, including suggestions for reducing the burden, to
Jasmeet K. Seehra, Office of Management and Budget (OMB), by email to
[email protected], or by fax to<PHONE_NUMBER>.
    3. This rule does not contain policies with Federalism implications
as that term is defined in Executive Order 13132.
    4. For the two persons added to the Entity List in this final rule,
the provisions of the Administrative Procedure Act (5 U.S.C. 553)
requiring notice of proposed rulemaking, the opportunity for public
participation and a 30-day delay in effective date are inapplicable
because this regulation involves a military or foreign affairs function
of the United States (5 U.S.C. 553(a)(1)). BIS implementation of this
rule is necessary to protect U.S. national security or foreign policy
interests by preventing items from being exported, reexported, or
transferred (in-country) to the persons being added to the Entity List.
If this rule were delayed to allow for notice and comment and a delay
in effective date, the entities being added to the Entity List by this
action would continue to be able to receive items without a license and
to conduct activities contrary to the national security or foreign
policy interests of the United States. In addition, publishing a
proposed rule would give these parties notice of the U.S. Government's
intention to place them on the Entity List, which could create an
incentive for these persons to accelerate receiving items subject to
the EAR to conduct activities that are contrary to the national
security or foreign policy interests of the United States, including
taking steps to set up additional aliases, change addresses, and other
measures to try to limit the impact of the listing on the Entity List
once a final rule is published. Further, no other law requires that a
notice of proposed rulemaking and an opportunity for public comment be
given for this rule. Because a notice of proposed rulemaking and an
opportunity for public comment are not required to be given for this
rule by 5 U.S.C. 553, or by any other law, the analytical requirements
of the Regulatory Flexibility Act, 5 U.S.C. 601 et seq., are not
applicable. Accordingly, no regulatory flexibility analysis is required
and none has been prepared.

List of Subjects in 15 CFR Part 744

    Exports, Reporting and recordkeeping requirements, Terrorism.

    Accordingly, part 744 of the Export Administration Regulations (15
CFR parts 730-774) is amended as follows:

PART 744--[AMENDED]

0
1. The authority citation for part 744 is revised to read as follows:

    Authority: 50 U.S.C. 4601 et seq.; 50 U.S.C. 1701 et seq.; 22
U.S.C. 3201 et seq.; 42 U.S.C. 2139a; 22 U.S.C. 7201 et seq.; 22
U.S.C. 7210; E.O. 12058, 43 FR 20947, 3 CFR, 1978 Comp., p. 179;
E.O. 12851, 58 FR 33181, 3 CFR, 1993 Comp., p. 608; E.O. 12938, 59
FR 59099, 3 CFR, 1994 Comp., p. 950; E.O. 12947, 60 FR 5079, 3 CFR,
1995 Comp., p. 356; E.O. 13026, 61 FR 58767, 3 CFR, 1996 Comp., p.
228; E.O. 13099, 63 FR 45167, 3 CFR, 1998 Comp., p. 208; E.O. 13222,
66 FR 44025, 3 CFR, 2001 Comp., p. 783; E.O. 13224, 66 FR 49079, 3
CFR, 2001 Comp., p. 786; Notice of January 13, 2017, 82 FR 6165
(January 18, 2017); Notice of August 15, 2017, 82 FR 39005 (August
16, 2017); Notice of September 18, 2017, 82 FR 43825 (September 19,
2017); Notice of November 6, 2017, 82 FR 51971 (November 8, 2017).

0
2. Supplement No. 4 to part 744 is amended by adding under Russia, two
Russian entities.
    The additions read as follows:

Supplement No. 4 to Part 744--Entity List

* * * * *

----------------------------------------------------------------------------------------------------------------
                                                                              License review    Federal Register
        Country                     Entity             License requirement        policy            citation
----------------------------------------------------------------------------------------------------------------

                                                  * * * * * * *
----------------------------------------------------------------------------------------------------------------
RUSSIA.................                                         * * * * * *
                        ----------------------------------------------------------------------------------------
                         Joint Stock Company           For all items        Presumption of     82 FR [INSERT FR
                          Experimental Design Bureau    subject to the       denial.            PAGE NUMBER],
                          Novator, a.k.a., the          EAR. (See Sec.                          December 12/20/
                          following two aliases:        744.11 of the                           17.
                         --Novator Design Bureau; and   EAR).
                         --JSC OKB Novator.
                         18 Prospekt Kosmonavtov,
                          620017 Yekaterinburg,
                          Russia.

                         Joint Stock Company Federal   For all items        Presumption of     82 FR [INSERT FR
                          Scientific and Production     subject to the       denial.            PAGE NUMBER], 12/
                          Center Titan-Barrikady,       EAR. (See Sec.                          20/17.
                          a.k.a., the following three   744.11 of the
                          aliases:                      EAR).
                         --Federal Research and
                          Production Center Titan
                          Barrikady JSC;
                         --Titan Design Bureau; and
                         --JSC FNPTS Titan-Barrikady.
                         Prospekt Imeni V.I. Lenina,
                          b/n 400071, Volgograd,
                          Russia.
----------------------------------------------------------------------------------------------------------------

                                                  * * * * * * *
----------------------------------------------------------------------------------------------------------------

    Dated: December 15, 2017.
Richard E. Ashooh,
Assistant Secretary for Export Administration.
[FR Doc. 2017-27388 Filed 12-19-17; 8:45 am]
 BILLING CODE 3510-33-P


[Federal Register: March 13, 2008 (Volume 73, Number 50)]
[Proposed Rules]
[Page 13513-13515]
[DOCID:fr13mr08-27]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-AD]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron, Inc. Model
214B and B-1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Bell Helicopter Textron, Inc. (BHTI) Model 214B and B-1
helicopters. The AD would require creating a component history card or
equivalent for each pylon support spindle assembly (spindle), and
inspecting certain spindles for any corrosion, or a nick, scratch,
dent, or crack, and replacing any unairworthy spindle before further
flight. This proposal is prompted by three in-flight failures of
spindles that resulted in forced landings. The actions specified by the
proposed AD are intended to detect damage in the radii or cracking of a
spindle, and to prevent failure of a spindle and subsequent loss of
control of the helicopter.

DATES: Comments must be received on or before May 12, 2008.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:

     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically;
     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 the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax:<PHONE_NUMBER>.
    You may get the service information identified in this proposed AD
from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas
76101, telephone<PHONE_NUMBER>, fax<PHONE_NUMBER>.
    You may examine the comments to this proposed AD in the AD docket
on the Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone<PHONE_NUMBER>, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2008-0288,
Directorate Identifier 2006-SW-25-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed rulemaking. Using the
search function of the docket Web site, you can find and read the
comments to any of our dockets, including the name of the individual
who sent or signed the comment. You may review the DOT's complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78).

Examining the Docket

    You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone<PHONE_NUMBER>) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.

Discussion

    This document proposes adopting a new AD for BHTI Model 214B and B-
1 helicopters. The AD would require, within 50 hours time-in-service
(TIS), creating a component history card or equivalent record for each
spindle, and begin recording the spindle's TIS and number of take-offs
and external load lifts accomplished with the spindle installed. It
would also require a one-time visual inspection of the outer radius of
the spindle for any corrosion or a nick, scratch, or dent, using a 3x-
power or higher magnifying glass, and a one-time magnetic particle
inspection of the spindles for a crack. The inspections would be
required within 100 hours TIS, or 325 hours TIS since the last overhaul
of the transmission assembly, whichever occurs later, for spindles with
5,000 or more hours TIS, or spindles for which the total number of
hours TIS is unknown and were installed before the last overhaul of the
transmission assembly. For spindles having 5,000 or more hours TIS, or
spindles for which the total number of hours TIS is unknown, that were
installed after the last overhaul of the transmission assembly, or the
installation history is unknown, the inspections would be required
within 100 hours TIS. The proposed AD would also require, before
further flight, replacing any spindle on which any corrosion or a crack
is discovered, and replacing any spindle that has a nick, scratch, or
dent, or repairing the spindle if the damage is within the repair
limits that are stated in the applicable component repair and overhaul
manual. This proposal is prompted by three in-flight failures of the
spindle, part number 214-030-606-005, which resulted in forced landings
and one serious injury. All three helicopters were involved in logging
operations, which put more torque cycles on the main rotor and
transmission systems. The failures occurred at 694, 810, and 1,928
hours TIS since the last overhaul of the transmission assembly on
helicopters having a total TIS of 3,500 to 17,000 hours. Currently, the
spindles do not have a retirement life on either the Model 214B or
214B-1 helicopters, and the number of hours TIS for the spindles is not
required to be tracked on a component history card or equivalent
record. The current inspections specified in the maintenance manuals
are a magnetic particle inspection at each 2,500 hours TIS transmission
overhaul, and a visual inspection for mechanical or corrosion damage,
using a 3x-power magnifying glass, at each main rotor tension-torsion
strap change. A magnetic particle inspection is also required following
the occurrence of a sudden stoppage of the main rotor system. The
actions specified by the proposed AD are intended to detect damage in
the radii or cracking of a spindle, and to prevent failure of a spindle
and subsequent loss of control of the helicopter. The actions of this
proposed AD are intended as interim actions until a retirement life for
these spindles can be developed and new replacement spindles become
available.
    This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, the proposed AD would
require creating a component history card or equivalent for each
spindle, inspecting certain spindles for any corrosion, or a nick,
scratch, dent, or crack, and replacing any unairworthy spindle before
further flight.
    We estimate that this proposed AD would affect 10 helicopters of
U.S. registry, and the proposed actions would take approximately:
     15 work hours to remove and replace a set of spindles for
inspecting;
     2 work hours to conduct a magnetic particle inspection;
and
     15 work hours to replace a set of spindles at an average
labor rate of $80 per work hour. Required parts would cost
approximately $10,735 for a set of spindles. Based on these figures,
the total cost impact of the proposed AD on U.S. operators would be
$25,535, assuming the inspections are performed once for each
helicopter and one set of spindles is replaced.

Regulatory Findings

    We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, 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. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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.
    We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. Go to the government-wide rulemaking Web
site at: http://www.regulations.gov to examine the draft economic
evaluation.

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 products identified in this
rulemaking action.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:

Bell Helicopter Textron, Inc.: Docket No. FAA-2008-0288; Directorate
Identifier 2006-SW-25-AD.

Applicability

    Model 214B and B-1 helicopters, with pylon support spindle
assembly (spindle), part number 214-030-606-005, installed,
certificated in any category.

Compliance

    Required as indicated, unless accomplished previously.
    To detect damage in the radii or cracking of a spindle, and to
prevent failure of a spindle and subsequent loss of control of the
helicopter, accomplish the following:
    (a) Within 50 hours time-in-service (TIS):
    (1) Create a component history card or equivalent record for
each spindle, stating the spindle's serial number. Begin recording
the number of hours TIS, and the number of take-offs and external
load lifts. An external load lift occurs when a load is picked up at
one location and is released at another location.
    (2) Review the helicopter records to determine if there has been
a sudden stoppage of the main rotor system, or any hard landing, on
a helicopter with any affected spindle installed and record any such
events on the component history card or equivalent record.
    (b) Record all conditional inspections of each spindle on the
component history card or equivalent record. A sudden stoppage of
the main rotor system is defined as any rapid deceleration of the
drive system, whether caused by seizure within the helicopter
transmission or by contact of a main rotor blade with the ground,
water, snow, dense vegetation, or other object of sufficient inertia
to cause rapid deceleration.
    (c) For each spindle with 5,000 or more hours TIS, or any
spindle for which the number of hours TIS is unknown, perform the
inspections in paragraphs (c)(1) and (c)(2) of this AD within the
hours TIS specified in Table 1 of this AD:

                                 Table 1
------------------------------------------------------------------------
 For spindles, part number 214-030-606-
    005, that were installed on the              Inspect within:
         transmission assembly:
------------------------------------------------------------------------
Before the last overhaul of the          100 hours TIS or 325 hours TIS
 transmission assembly.                   since the last overhaul of the
                                          transmission assembly,
                                          whichever occurs later.
After the last overhaul of the           100 hours TIS.
 transmission assembly or for which the
 installation history is unknown.
------------------------------------------------------------------------

    (1) Visually inspect each outer radius of the spindle for any
corrosion, or a nick, scratch, or dent, using a 3x-power or higher
magnifying glass; and
    (2) Conduct a magnetic particle inspection of the spindle for a
crack.
    (d) Before further flight, if a crack or any corrosion is found,
replace the spindle with an airworthy spindle.
    (e) Before further flight, replace any spindle that has a nick,
scratch, or dent with an airworthy spindle, or repair it if it is
within the repair limits.

    Note 2: The repair limits are specified in the applicable
component repair and overhaul manual.

    (f) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Rotorcraft Certification Office, FAA, ATTN:
Michael Kohner, Aviation Safety Engineer, Fort Worth, Texas 76193-
0170, telephone<PHONE_NUMBER>, fax<PHONE_NUMBER>, for information
about previously approved alternative methods of compliance.

    Issued in Fort Worth, Texas, on March 3, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-5060 Filed 3-12-08; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28020-28023]
[FR Doc No: 2017-12614]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0561; Directorate Identifier 2016-NM-141-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2001-16-
01, which applies to certain Airbus Model A330-301, -321, -322, -341,
and -342 airplanes, and certain Model A340 series airplanes; and AD
2014-17-06, which applies to all Airbus Model A330-200 series
airplanes, Model A330-200 Freighter series airplanes, and Model A330-
300 series airplanes. AD 2001-16-01 requires inspections for cracking
of the aft cargo compartment door, and corrective action if necessary.
AD 2014-17-06 requires revising the maintenance or inspection program,
as applicable, to incorporate structural inspection requirements. Since
we issued AD 2001-16-01 and AD 2014-17-06, we have determined that more
restrictive maintenance instructions and airworthiness limitations are
necessary. This proposed AD would require revising the maintenance or
inspection program, as applicable, to incorporate new or revised
airworthiness limitation requirements; and remove airplanes from the
applicability. We are proposing this AD to address the unsafe condition
on these products.

DATES: We must receive comments on this proposed AD by August 4, 2017.

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 Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45
80; email<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.

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-2017-
0561; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite 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-2017-0561;
Directorate Identifier 2016-NM-141-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    On July 26, 2001, we issued AD 2001-16-01, Amendment 39-12369 (66
FR 40874, August 6, 2001) (``AD 2001-16-01''), for certain Airbus Model
A330-301, -321, -322, -341, and -342 airplanes, and certain Model A340
series airplanes. AD 2001-16-01 was prompted by reports of cracking in
several structural parts of the aft cargo compartment door. AD 2001-16-
01 requires repetitive inspections to detect cracking of the aft cargo
compartment door, and corrective action if necessary; and also provides
optional terminating action for the repetitive inspections. We issued
AD 2001-16-01 to detect and correct cracking of the aft cargo
compartment door, which could result in reduced structural integrity of
the airplane.
    On August 15, 2014, we issued AD 2014-17-06, Amendment 39-17959 (79
FR 52181, September 3, 2014) (``AD 2014-17-06''), for all Airbus Model
A330-200 series airplanes, Model A330-200 Freighter series airplanes,
and Model A330-300 series airplanes. AD 2014-17-06 superseded AD 2011-
17-08, Amendment 39-16772 (76 FR 53303, August 26, 2011). AD 2014-17-06
was prompted by a revision of certain airworthiness limitations items
documents, which specifies more restrictive instructions and/or
airworthiness limitations. AD 2014-17-06 requires a revision to the
maintenance or inspection program, as applicable, to incorporate new or
revised structural inspection requirements. We issued AD 2014-17-06 to
detect and correct fatigue cracking, damage, and corrosion in certain
structure, which could result in reduced structural integrity of the
airplane.
    Since we issued AD 2001-16-01 and AD 2014-17-06, we have determined
that more restrictive maintenance instructions and airworthiness
limitations are necessary, and that Model A340 series airplanes should
be removed from the applicability as there are currently no Model A340
series airplanes on the U.S. register.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0152, dated July 27, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, -200, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:

    The airworthiness limitations are currently defined and
published in the Airbus A330 and A340 Airworthiness Limitations
Section (ALS) documents.
    The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI), which are approved by EASA,
are specified in Airbus A330 and A340 ALS Part 2. Failure to comply
with these instructions could result in an unsafe condition [fatigue
cracking, damage, and corrosion in a certain structure, which could
result in reduced structural integrity of the airplane].
    EASA issued AD 2012-0211 (for A330 aeroplanes) [which
corresponds to FAA AD 2014-17-06] and AD 2013-0127 (for A340
aeroplanes) [which corresponds to FAA AD 2001-16-01] to require the
actions as specified in Airbus A330 and A340 ALS Part 2 at original
issue and Revision 01, respectively.
    Since those [EASA] ADs were issued, Airbus issued Revision 01
and Revision 02, respectively, of Airbus A330 and A340 ALS Part 2,
to introduce more restrictive maintenance requirements and/or
airworthiness limitations.
    For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2012-0211 and AD 2013-0127, which are
superseded, and requires accomplishment of the actions specified in
Airbus A330 ALS Part 2 Revision 01 including Variation 1.1 and
Variation 1.2, or A340 ALS Part 2 Revision 02 including Variation
2.1 and Variation 2.2, as applicable (hereafter collectively
referred to as `the applicable ALS' in this [EASA] AD).
    In addition, this [EASA] AD also supersedes DGAC France AD 2001-
126(B), whose requirements applicable to A330 aeroplanes have been
transferred into Airbus A330 ALS Part 2, and supersedes DGAC
[Direction G[eacute]n[eacute]rale de l'Aviation Civile ] France AD
2001-124(B), EASA AD 2012-0031 and AD 2012-0167, whose requirements
applicable to A340 aeroplanes have been transferred into Airbus A340
ALS Part 2 [EASA ADs 2001-124(B) and 2001-126(B) correspond with FAA
AD 2001-16-01].

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0561.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information, which
describes airworthiness limitation requirements for damage-tolerant
airworthiness limitation items. These documents are distinct since they
provide different limitation requirements.
     Airbus A330 ALS Part 2, DT-ALI, Revision 01, issue 02,
dated November 30, 2015.
     Airbus 330 ALS Part 2, DT-ALI, Variation 1.1, dated
December 15, 2015.
     Airbus 330 ALS Part 2, DT-ALI, Variation 1.2, dated May
27, 2016.
    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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
    This proposed AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this proposed AD, the operator may not be able to accomplish the
actions described in the revisions. In this situation, to comply with
14 CFR 91.403(c), the operator must request approval for an AMOC
according to paragraph (l)(1) of this proposed AD. The request should
include a description of changes to the required actions that will
ensure the continued damage tolerance of the affected structure.

Differences Between This Proposed AD and the MCAI

    This proposed AD does not include the Model A340 airplanes that are
specified in the MCAI. We have added that MCAI to the required
airworthiness actions list (RAAL) for the Model A340 airplanes.
    The MCAI specifies that if there are findings from the ALS
inspection tasks, corrective actions must be accomplished in accordance
with Airbus maintenance documentation. However, this proposed AD does
not include that requirement. Operators of U.S.-registered airplanes
are required by general airworthiness and operational regulations to
perform maintenance using methods that are acceptable to the FAA. We
consider those methods to be adequate to address any corrective actions
necessitated by the findings of ALS inspections required by this
proposed AD.

Airworthiness Limitations Based on Type Design

    The FAA recently became aware of an issue related to the
applicability of ADs that require incorporation of an ALS revision into
an operator's maintenance or inspection program.
    Typically, when these types of ADs are issued by civil aviation
authorities of other countries, they apply to all airplanes covered
under an identified type certificate (TC). The corresponding FAA AD
typically retains applicability to all of those airplanes.
    In addition, U.S. operators must operate their airplanes in an
airworthy condition, in accordance with 14 CFR 91.7(a). Included in
this obligation is the requirement to perform any maintenance or
inspections specified in the ALS, and in accordance with the ALS as
specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been
approved by the FAA.
    When a TC is issued for a type design, the specific ALS, including
revisions, is a part of that type design, as specified in 14 CFR
21.31(c).
    The sum effect of these operational and maintenance requirements is
an obligation to comply with the ALS defined in the type design
referenced in the manufacturer's conformity statement. This obligation
may introduce a conflict with an AD that requires a specific ALS
revision if new airplanes are delivered with a later revision as part
of their type design.
    To address this conflict, the FAA has approved alternative methods
of compliance (AMOCs) that allow operators to incorporate the most
recent ALS revision into their maintenance/inspection programs, in lieu
of the ALS revision required by the AD. This eliminates the conflict
and enables the operator to comply with both the AD and the type
design.
    However, compliance with AMOCs is normally optional, and we
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection
programs, including those for new airplanes delivered with later ALS
revisions, to help standardize the maintenance of the fleet. To ensure
that operators comply with the applicable ALS revision for newly
delivered airplanes containing a later revision than that specified in
an AD, we plan to limit the applicability of ADs that mandate ALS
revisions to those airplanes that are subject to an earlier revision of
the ALS, either as part of the type design or as mandated by an earlier
AD.
    For purposes of this NPRM, in order to ensure that affected
airplanes are

maintained in accordance with mandatory instructions and airworthiness
limitations, this NPRM includes the limitations specified in Airbus 330
ALS Part 2, DT-ALI, Variation 1.1, dated December 15, 2015; and Airbus
330 ALS Part 2, DT-ALI, Variation 1.2, dated May 27, 2016. This NPRM,
therefore, applies to Model A330-200, -200 Freighter, and -300 series
airplanes with an original certificate of airworthiness or original
export certificate of airworthiness that was issued on or before May
27, 2016, the date of approval of Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2. Operators of airplanes with an original certificate of
airworthiness or original export certificate of airworthiness issued
after that date must comply with the airworthiness limitations
specified as part of the approved type design and referenced on the
type certificate data sheet.

Costs of Compliance

    We estimate that this proposed AD affects 101 airplanes of U.S.
registry.
    The actions required by AD 2014-17-06, and retained in this
proposed AD, take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Required parts cost about $0 per product.
Based on these figures, the estimated cost of the actions that are
required by AD 2014-17-06 is $85 per product.
    We also estimate that it would take about 1 work-hour per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $8,585, or $85 per product.

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 products identified in this
rulemaking action.

Regulatory Findings

    We 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 this proposed
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; 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.

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:
0
a. Removing Airworthiness Directives (AD) 2001-16-01, Amendment 39-
12369 (66 FR 40874, August 6, 2001); and AD 2014-17-06, Amendment 39-
17959 (79 FR 52181, September 3, 2014); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2017-0561; Directorate Identifier 2016-NM-
141-AD.

(a) Comments Due Date

    We must receive comments by August 4, 2017.

(b) Affected ADs

    This AD replaces AD 2001-16-01, Amendment 39-12369 (66 FR 40874,
August 6, 2001) (``AD 2001-16-01''); and AD 2014-17-06, Amendment
39-17959 (79 FR 52181, September 3, 2014) (``AD 2014-17-06'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
with an original certificate of airworthiness or original export
certificate of airworthiness issued on or before May 27, 2016.
    (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Airbus Model A330-223F and -243F airplanes.
    (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic
inspections.

(e) Reason

    This AD was prompted by a determination that more restrictive
maintenance instructions and airworthiness limitations are
necessary. We are issuing this AD to detect and correct fatigue
cracking, damage, and corrosion in a certain structure, which could
result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Requirement: Maintenance or Inspection Program Revision,
With a New Terminating Action

    This paragraph restates the requirements of paragraph (i) of AD
2014-17-06, with a new terminating action. Accomplishing the
revision required by paragraph (j) of this AD terminates the
requirements of this paragraph.
    (1) Within 3 months after October 8, 2014 (the effective date of
AD 2014-17-06): Revise the maintenance or inspection program, as
applicable, by incorporating Airbus Document AI/SE-M4/95A.0089/97,
``A330 Airworthiness Limitation Items,'' Issue 19, dated March 23,
2012; ``Variation to Issue 19 of ALI Document (referenced in ALS
Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),''
variation reference 0GVLG120018/C0S, dated October 24, 2012; and
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG130002/C01, dated March 26, 2013.
    (2) Comply with all applicable instructions and airworthiness
limitations included in Airbus Document AI/SE M4/95A.0089/97, ``A330
Airworthiness Limitation Items,'' Issue 19, dated March 23, 2012;
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG120018/C0S, dated October 24, 2012; and ``Variation
to Issue 19 of ALI Document (referenced in ALS Part 2) Damage
Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG130002/C01, dated March 26, 2013. The initial
compliance times for the actions specified in Airbus Document AI/SE-
M4/95A.0089/97, ``A330 Airworthiness Limitation Items,''

Issue 19, dated March 23, 2012; ``Variation to Issue 19 of ALI
Document (referenced in ALS Part 2) Damage Tolerant Airworthiness
Limitation Items (DT ALI),'' variation reference 0GVLG120018/C0S,
dated October 24, 2012; and ``Variation to Issue 19 of ALI Document
(referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation
Items (DT ALI),'' 0GVLG130002/C01, dated March 26, 2013; are at the
times specified in Airbus Document AI/SE-M4/95A.0089/97, ``A330
Airworthiness Limitation Items,'' Issue 19, dated March 23, 2012;
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
ref. 0GVLG120018/C0S, dated October 24, 2012; and ``Variation to
Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant
Airworthiness Limitation Items (DT ALI),'' variation ref.
0GVLG130002/C01, dated March 26, 2013; or within 3 months after
October 8, 2014 (the effective date of AD 2014-17-06), whichever
occurs later.

(h) Retained Provision: Optional Compliance, With a New Terminating
Action

    This paragraph restates the provision in paragraph (j) of AD
2014-17-06, with a new terminating action. Compliance with tasks
533021-02-01, 533021-02-02, and 533021-02-03, specified in
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
ref. 0GVLG120022/C0S, dated December 21, 2012, may be used as a
method of compliance to tasks 533021-01-01, 533021-01-02, 533021-01-
03 specified in Section 2.2.1 and 2.2.2 of Section 2,
``Airworthiness Limitations,'' of Airbus Document AI/SE M4/95A.0089/
97, ``A330 Airworthiness Limitation Items,'' Issue 19, dated March
23, 2012. Accomplishing the revision required by paragraph (j) of
this AD terminates the provision specified in this paragraph.

(i) Retained Requirement: No Alternative Intervals or Limits, With a
New Exception

    This paragraph restates the requirements of paragraph (k) of AD
2014-17-06, with a new exception. Except as provided by paragraph
(h) of this AD and as required by paragraph (j) of this AD, after
the maintenance or inspection program, as applicable, has been
revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) under the provisions of paragraph (l)(1) of this
AD.

(j) New Requirement: Maintenance or Inspection Program Revision

    Within 3 months after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, by incorporating
the service information specified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD. The initial compliance times for the actions
specified in the service information referenced in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD are the times specified in the
applicable service information, or within 3 months after the
effective date of this AD, whichever occurs later. Accomplishing the
revision specified in this paragraph terminates the requirements of
paragraph (g) of this AD and the provision specified in paragraph
(h) of this AD.
    (1) Airbus A330 Airworthiness Limitations Section (ALS) Part 2,
Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision
01, issue 02, dated November 30, 2015.
    (2) Airbus 330 ALS Part 2, DT-ALI, Variation 1.1, dated December
15, 2015.
    (3) Airbus 330 ALS Part 2, DT-ALI, Variation 1.2, dated May 27,
2016.

(k) New Requirement: No Alternative Actions or Intervals

    After the maintenance or inspection program, as applicable, has
been revised, as required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or intervals may be used
unless the actions or intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (l)(1) of this
AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to the attention of
the person identified in paragraph (m)(2) of this AD. Information
may be emailed to<EMAIL_ADDRESS>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.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0152, dated July 27, 2016,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0561.
    (2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email<EMAIL_ADDRESS>
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on June 9, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12614 Filed 6-19-17; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 81, Number 14 (Friday, January 22, 2016)]
[Notices]
[Pages 3788-3789]
[FR Doc No: 2016-01231]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings #1

    Take notice that the Commission received the following electric
corporate filings:

    Docket Numbers: EC16-11-000.
    Applicants: Greeley Energy Facility, LLC.
    Description: Supplement to October 13, 2015 Application for
Authorization Under Section 203 of the Federal Power Act and Request
for Expedited Action of Greeley Energy Facility, LLC.
    Filed Date: 1/4/16.
    Accession Number: 20160104-5540.
    Comments Due: 5 p.m. ET 1/22/16.

    Take notice that the Commission received the following electric
rate filings:

    Docket Numbers: ER12-161-014; ER12-645-016; ER14-25-011.
    Applicants: Bishop Hill Energy LLC, California Ridge Wind Energy
LLC, Prairie Breeze Wind Energy LLC.
    Description: Notice of Change in Status and Request for
Confidential Treatment of Bishop Hill Energy LLC, et al.
    Filed Date: 1/14/16.
    Accession Number: 20160114-5434.
    Comments Due: 5 p.m. ET 2/4/16.

    Docket Numbers: ER12-2068-010; ER15-1471-005; ER10-2460-010;

ER10-2461-010; ER12-2159-006; ER12-682-011; ER10-2463-010; ER15-1672-
004; ER11-2201-014; ER10-2464-007; ER10-1821-011; ER13-1139-013; ER13-
1585-007; ER12-2205-007; ER10-2465-006; ER11-2657-007; ER13-17-008;
ER14-2630-006; ER12-919-005; ER12-1311-010; ER10-2466-011; ER11-4029-
010.
    Applicants: Blue Sky East, LLC, Blue Sky West, LLC, Canandaigua
Power Partners, LLC, Canandaigua Power Partners II, LLC, Canadian Hills
Wind, LLC, Erie Wind, LLC, Evergreen Wind Power, LLC, Evergreen Wind
Power II, LLC, Evergreen Wind Power III, LLC, First Wind Energy
Marketing, LLC, Goshen Phase II LLC, Imperial Valley Solar 1, LLC,
Longfellow Wind, LLC, Meadow Creek Project Company LLC, Milford Wind
Corridor Phase I, LLC, Milford Wind Corridor Phase II, LLC, Niagara
Wind Power, LLC, Regulus Solar, LLC, Rockland Wind Farm LLC, Stetson
Holdings, LLC, Stetson Wind II, LLC, Vermont Wind, LLC.
    Description: Notice of Change in Status of Blue Sky East, LLC, et
al.
    Filed Date: 1/14/16.
    Accession Number: 20160114-5449.
    Comments Due: 5 p.m. ET 2/4/16.

    Docket Numbers: ER15-2483-002.
    Applicants: Emerald City Renewables LLC.
    Description: Notification of Non-Material Change in Status of
Emerald City Renewables LLC.
    Filed Date: 1/15/16.
    Accession Number: 20160115-5157.
    Comments Due: 5 p.m. ET 2/5/16.

    Docket Numbers: ER16-91-001.
    Applicants: Blythe Solar 110, LLC.
    Description: Amendment to December 18, 2015 Notification of Change
in Status of Blythe Solar 110, LLC.
    Filed Date: 1/14/16.
    Accession Number: 20160114-5447.
    Comments Due: 5 p.m. ET 2/4/16.

    The filings are accessible in the Commission's eLibrary system by
clicking on the links or querying the docket number.
    Any person desiring to intervene or protest in any of the above
proceedings must file in accordance with Rules 211 and 214 of the
Commission's Regulations (18 CFR 385.211 and 385.214) on or before 5:00
p.m. Eastern time on the specified comment date. Protests may be
considered, but intervention is necessary to become a party to the
proceeding.
    eFiling is encouraged. More detailed information relating to filing
requirements, interventions, protests, service, and qualifying
facilities filings can be found at: http://www.ferc.gov/docs-filing/efiling/filing-req.pdf. For other information, call<PHONE_NUMBER>
(toll free). For TTY, call<PHONE_NUMBER>.

     Dated: January 15, 2016.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2016-01231 Filed 1-21-16; 8:45 am]
BILLING CODE 6717-01-P


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P-23-0031 Sanitized Support Documents Index:
 P-23-0031 Sanitized Determination Document (linked)
 P-23-0031 Sanitized Premanufature Notice (attached)
 P-23-0031 Sanitized CHEM Report (attached)
 P-23-0031 Sanitized ECO Report (attached)
 P-23-0031 Sanitized ENG Report (attached)
 P-23-0031 Sanitized EXP Report (attached)
 P-23-0031 Sanitized Fate Report (attached)
 P-23-0031 Sanitized HLTH Report_POST-FOCUS FINAL (attached)