[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)]
[Rules and Regulations]
[Pages 57340-57343]
[FR Doc No: 2017-26037]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0709; Product Identifier 2016-NM-200-AD; Amendment
39-19115; AD 2017-25-01]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A318 series airplanes; Model A319 series airplanes; and
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. This
AD was prompted by a report indicating that the lower rib foot angle of
the center wing box did not match with the bottom skin panel inner
surface. This AD requires repetitive inspections for cracking of the
external bottom skin in certain areas on the left and right wings, and
corrective actions if necessary. We are issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective January 9, 2018.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 9,
2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0709.

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-
0709; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A318
and A319 series airplanes; and Model A320-211, -212, -214, -216, -231,
-232, and -233 airplanes. The NPRM published in the Federal Register on
July 25, 2017 (82 FR 34453) (``the NPRM''). The NPRM was prompted by a
report indicating that the lower rib foot angle of the center wing box
did not match with the bottom skin panel inner surface. The NPRM
proposed to require repetitive inspections for cracking of the external
bottom skin in certain areas on the left and right wings, and
corrective actions if necessary, and provided an optional terminating
modification for the repetitive inspections. We are issuing this AD to
detect and correct cracking of the external bottom skin in the area of
the rib 2 attachment of the wings, which could result in reduced
structural integrity of the wings.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0222, dated November 7, 2016 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A318 and A319
series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and
-233 airplanes. The MCAI states:

    During installation in production of new wing box ribs on post-
mod 39729 aeroplanes, it was discovered that the centre wing lower
rib foot angle was not matching with the bottom skin panel inner
surface.
    This condition, if not detected and corrected, could induce
fatigue cracking of the skin panel at the rib foot attachment, with
possible detrimental effect on wing structural integrity.
    This condition was initially addressed by Airbus on the
production line through adaptation mod 152155, then through mod
152200. For affected aeroplanes in service, Airbus issued Service
Bulletin (SB) A320-57-1205, providing instructions for repetitive
detailed inspections (DET) or special detailed inspections (SDI),
and SB A320-57-1207, providing modification instructions.
    For the reasons described above, this [EASA] AD requires
repetitive inspections (DET or SDI) of the wing bottom skin lower
surface for crack detection and, depending on findings, the
accomplishment of applicable corrective action(s). This [EASA] AD
also includes reference to an optional modification (Airbus SB A320-
57-1207), providing terminating action for the repetitive
inspections required by this [EASA] AD.

    The corrective action for cracking is to repair using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; EASA; or Airbus's EASA Design Organization Approval. 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-
0709.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response.

Request To Include Technical Adaptations

    Delta Airlines asked for another ``Contacting the Manufacturer''
subparagraph acknowledging Technical Adaptations from Airbus to be
added under paragraph (j) of the proposed AD, ``Other FAA AD
Provisions.'' Delta observed that the FAA provision for contacting the
manufacturer in paragraph (j) of the proposed AD would provide
allowances for corrective actions without alternative methods of
compliance (AMOCs). Delta noted that operators often receive Technical
Adaptations that include an EASA Design Organization Approval (DOA)

authorized signature for typographical, omitted instruction, and
technical errors, and that they should be included in the proposed AD.
    We disagree with the commenter. The ``Contacting the Manufacturer''
paragraph in ADs only addresses the requirement to contact the
manufacturer for corrective actions for the identified unsafe condition
and does not cover deviations from other AD requirements. This
paragraph states, in part, that for any requirement in an AD to obtain
corrective actions from a manufacturer, the actions must be
accomplished using a method approved by the FAA; or the EASA; or
Airbus's EASA DOA. We do not agree to extend this allowance to other AD
requirements. All deviations from the service information sections that
are marked ``RC'' (Required for Compliance) require AMOC approval
unless otherwise stated in the AD. We have not changed this AD in this
regard.

Conclusion

    We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:

     Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than
was already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-57-1205, dated May 26,
2016. This service information describes procedures for inspecting the
external bottom skin for cracking in the area of the rib 2 attachment
between stringer 8 and stringer 11 on both wings, and repairing any
cracks.
    Airbus has also issued Service Bulletin A320-57-1207, including
Appendix 01 and Appendix 02, dated May 26, 2016. This service
information describes procedures for inspecting the lower rib feet (rib
2) and the bottom skin upper surface on both wings for cracking,
modifying the wings by installing shims between the lower rib foot (rib
2) and the bottom skin upper surface, and repairing any cracks.
    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 10 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per  product         operators
----------------------------------------------------------------------------------------------------------------
Inspection....................  5 work-hours x $85                $0  $425 per inspection   $4,250 per
                                 per hour = $425 per                   cycle.                inspection cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification...............................  32 work-hours x $85 per hour =               $5,750          $8,470
                                              $2,720.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
    According to the manufacturer, some of the costs of the optional
modification of this AD may be covered under warranty, thereby reducing
the cost impact on affected individuals. We do not control warranty
coverage for affected individuals. As a result, we have included all
available costs in our cost estimate.

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.
    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 transport category airplanes to
the Director of the System Oversight Division.

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 above, I certify that this AD:
    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.

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):

2017-25-01 Airbus: Amendment 39-19115; Docket No. FAA-2017-0709;
Product Identifier 2016-NM-200-AD.

(a) Effective Date

    This AD is effective January 9, 2018.

(b) Affected ADs

    None.

 (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,
all manufacturer serial numbers on which Airbus Modification 39729
was embodied in production, except those airplanes on which Airbus
Modification 152155 or Modification 152200 was embodied in
production.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.

 (d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

 (e) Reason

    This AD was prompted by a report indicating that the lower rib
foot angle of the center wing box did not match with the bottom skin
panel inner surface. Misalignment of the lower rib foot angle of the
center wing box with the bottom skin panel inner surface could
induce fatigue cracking of the skin panel at the rib foot
attachment. We are issuing this AD to detect and correct cracking of
the external bottom skin in the area of the rib 2 attachment of the
wings, which could result in reduced structural integrity of the
wings.

 (f) Compliance

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

 (g) Repetitive Inspections

    Before exceeding the applicable compliance time specified in
table 1 to paragraph (g) of this AD, or within 3 months after the
effective date of this AD, whichever occurs later: Do a detailed
inspection or a special detailed inspection for cracking of the
external bottom skin in the area of the rib 2 attachment between
stringer 8 and stringer 11 of the left and right wings, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1205, dated May 26,
2016. Do all applicable corrective actions before further flight.
Repeat the inspection thereafter at the applicable intervals, based
on the method used for the most recent inspection, as specified in
table 2 to paragraph (g) of this AD.

      Table 1 to Paragraph (g) of This AD--Initial Inspection Times
------------------------------------------------------------------------
                                                   Compliance time--
                                                 whichever occurs first
       Airplane model and configuration        since first flight of the
                                                        airplane
------------------------------------------------------------------------
Model A318 series airplanes; Model A319        Before the accumulation
 series airplanes; and Model A320-211, -212, -  of 14,500 total flight
 214, -216, -231, -232, and -233 airplanes;     cycles or 29,000 total
 pre-Airbus Modification 155374; not used as    flight hours.
 VIP or Elite.
Model A318 series airplanes; Model A319        Before the accumulation
 series airplanes; and Model A320-211, -212, -  of 13,600 total flight
 214, -216, -231, -232, and -233 airplanes;     cycles or 27,300 total
 post-Airbus Modification 155374; not used as   flight hours.
 VIP or Elite.
Model A319 series airplanes; post-Airbus       Before the accumulation
 Modifications 28162, 28238, and 28342; used    of 7,400 total flight
 as VIP or CJ.                                  cycles or 32,000 total
                                                flight hours.
Model A318 series airplanes; post-Airbus       Before the accumulation
 Modification 39195; used as VIP or Elite.      of 14,500 total flight
                                                cycles or 43,500 total
                                                flight hours.
------------------------------------------------------------------------

  Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                       Detailed        Special detailed
                                     inspection--        inspection--
Airplane model and configuration   whichever occurs    whichever occurs
                                         first               first
------------------------------------------------------------------------
Model A318 series airplanes;      4,000 flight        5,000 flight
 Model A319 series airplanes;      cycles or 8,000     cycles or 10,000
 and Model A320-211, -212, -214,   flight hours.       flight hours.
 -216, -231, -232, and -233
 airplanes; not used as VIP or
 Elite.
Model A319 series airplanes;      2,000 flight        2,500 flight
 post-Airbus Modifications         cycles or 8,600     cycles or 11,000
 28162, 28238 and 28342; used as   flight hours.       flight hours.
 VIP or CJ.
Model A318 series airplanes;      4,000 flight        5,000 flight
 post-Airbus Modification 39195;   cycles or 12,000    cycles or 15,000
 used as VIP or Elite.             flight hours.       flight hours.
------------------------------------------------------------------------

    Note 1 to paragraph (g) of this AD: Airbus Modification 155374
defines the minimum airplane configuration for operation on
Commonwealth of Independent States runway profiles.

 (h) Terminating Action Limitation

    Repair of an airplane, as required by paragraph (g) of this AD,
does not constitute terminating action for the repetitive
inspections required by paragraph (g) of this AD unless otherwise
specified in the instructions obtained using the procedures
specified in paragraph (j)(2) of this AD.

 (i) Optional Terminating Action

    Modification of the wings including a detailed inspection of the
lower rib feet (rib 2) and bottom skin upper surface of the wings
for cracking and all applicable corrective actions, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-57-1207, including Appendix 01 and Appendix 02, dated May 26,
2016, constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD for that airplane. If, during
modification of an airplane as specified in this paragraph,
accomplishment of any modification instruction is not possible due
to configuration difficulties, accomplish the modification using the
procedures specified in paragraph (j)(1) of this AD.

 (j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this

AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the International
Branch, send it to the attention of the person identified in
paragraph (k)(2) of this AD. Information may be emailed to: [email protected]. 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: 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
Section, Transport Standards Branch, 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.
    (3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.

 (k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0222, dated November 7, 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-2017-0709.
    (2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax<PHONE_NUMBER>.
    (3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (l)(3) and (l)(4) of this AD.

 (l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-57-1205, dated May 26, 2016.
    (ii) Airbus Service Bulletin A320-57-1207, including Appendix 01
and Appendix 02, dated May 26, 2016.
    (3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. 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 Renton, Washington, on November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26037 Filed 12-4-17; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 86, Number 42 (Friday, March 5, 2021)]
[Rules and Regulations]
[Pages 12835-12836]
[FR Doc No: 2021-04576]

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DEPARTMENT OF TRANSPORTATION

Pipeline and Hazardous Materials Safety Administration

49 CFR Part 192

[Docket No. PHMSA-2018-0046; Amdt. No. 192-28]
RIN 2137-AF36

Pipeline Safety: Gas Pipeline Regulatory Reform; Correction

AGENCY: Pipeline and Hazardous Materials Safety Administration (PHMSA),
Department of Transportation (DOT).

ACTION: Final rule; correction.

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SUMMARY: PHMSA is correcting its Gas Pipeline Regulatory Reform final
rule that published in the Federal Register on January 11, 2021. The
rule makes miscellaneous changes to the regulatory requirements for gas
pipeline systems.

DATES: This correction is effective March 21, 2021.

FOR FURTHER INFORMATION CONTACT: Sayler Palabrica, Transportation
Specialist, by telephone at<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: PHMSA is correcting its Gas Pipeline
Regulatory Reform final rule that published in the Federal Register on
January 11, 2021 (86 FR 2210). PHMSA is correcting the amendatory
instructions to 49 CFR 192.281 and appendix B to part 192. PHMSA is
also correcting the new regulatory text at Sec.  192.507(d) to remove
the word ``hydrostatic,'' consistent with the unanimous recommendation
of the Gas Pipeline Advisory Committee and the stated intent in the
preamble of the final rule.\1\
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    \1\ See 86 FR 2210 at page 2234.
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List of Subjects in 49 CFR Part 192

    Fire prevention, Incorporation by reference, Pipeline safety,
Security measures.

Corrections

    In FR Doc. 2021-00208 that appears on page 2210 of the Federal
Register on Monday, January 11, 2021, the following corrections are
made:

Sec.  192.281  [Corrected]

0
1. On page 2240, in the second column, in part 192, in amendment 10,
the instruction ``In Sec.  192.281, revise paragraph (c) to read as
follow:'' is corrected to read ``In Sec.  192.281, revise paragraph (c)
introductory text to read as follows:''

0
2. On page 2241, in the third column, in amendatory instruction 17,
paragraph (d) is corrected to read as follows:

Sec.  192.507   [Corrected]

* * * * *
    (d) For fabricated units and short sections of pipe, for which a
post installation test is impractical, a preinstallation pressure test
must be conducted in accordance with the requirements of this section.

Appendix B to Part 192 [Corrected]

0
3. On page 2242, in the third column, in part 192 in amendment 25, the
instructions are corrected to read:
0
a. In section I.A., remove the term ``ASTM D2513-12ae1'' and add in its
place ``ASTM D2513''; and
0
b. In section I.B., remove the term ``ASTM D2513-12ae1'' and add in its
place ``ASTM D2513''.

    Issued in Washington, DC, on March 1, 2021, under authority
delegated in 49 CFR 1.97.
Tristan H. Brown,
Acting Administrator.
[FR Doc. 2021-04576 Filed 3-4-21; 8:45 am]
BILLING CODE 4910-60-P


[Federal Register Volume 83, Number 125 (Thursday, June 28, 2018)]
[Notices]
[Page 30446]
[FR Doc No: 2018-13945]

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ENVIRONMENTAL PROTECTION AGENCY

[EPA-HQ-OPPT-2003-0004; FRL-9979-45]

Access to Confidential Business Information by Industrial
Economics Incorporated

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice.

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SUMMARY: EPA has authorized its contractor, Industrial Economics
Incorporated of Cambridge, MA, to access information which has been
submitted to EPA under all sections of the Toxic Substances Control Act
(TSCA). Some of the information may be claimed or determined to be
Confidential Business Information (CBI).

DATES: Access to the confidential data will occur no sooner than July
5, 2018.

FOR FURTHER INFORMATION CONTACT:
    For technical information contact: Scott Sherlock, Environmental
Assistance Division (7408M), Office of Pollution Prevention and Toxics,
Environmental Protection Agency, 1200 Pennsylvania Ave. NW, Washington,
DC 20460-0001; telephone number:<PHONE_NUMBER>; email address:
[email protected].
    For general information contact: The TSCA-Hotline, ABVI-Goodwill,
422 South Clinton Ave., Rochester, NY 14620; telephone number: (202)
554-1404; email address: [email protected].

SUPPLEMENTARY INFORMATION:

I. General Information

A. Does this action apply to me?

    This action is directed to the public in general. This action may,
however, be of interest to all who manufacture, process, or distribute
industrial chemicals. Since other entities may also be interested, the
Agency has not attempted to describe all the specific entities that may
be affected by this action.

B. How can I get copies of this document and other related information?

    The docket for this action, identified by docket identification
(ID) number EPA-HQ-OPPT-2003-0004, is available at http://www.regulations.gov or at the Office of Pollution Prevention and Toxics
Docket (OPPT Docket), Environmental Protection Agency Docket Center
(EPA/DC), West William Jefferson Clinton Bldg., Rm. 3334, 1301
Constitution Ave. NW, Washington, DC. The Public Reading Room is open
from 8:30 a.m. to 4:30 p.m., Monday through Friday, excluding legal
holidays. The telephone number for the Public Reading Room is (202)
566-1744, and the telephone number for the OPPT Docket is (202) 566-
0280. Please review the visitor instructions and additional information
about the docket available at http://www.epa.gov/dockets.

II. What action is the Agency taking?

    Under EPA contract number GS-10F-0061N, order number 68HEOH18F1498,
contractor Industrial Economics Incorporated (IEI) of 2067
Massachusetts Ave, Suite 4, Cambridge, MA will assist the Office of
Enforcement and Compliance Assurance (OECA) in preparing financial
analysis of the firms, individuals, and organizations that are the
subject of EPA enforcement actions taken under TSCA.
    In accordance with 40 CFR 2.306(j), EPA has determined that under
EPA contract number GS-10F-0061N, order number 68HEOH18F1498, IEI will
require access to CBI submitted to EPA under all sections of TSCA to
perform successfully the duties specified under the contract. IEI
personnel will be given access to information submitted to EPA under
all sections of TSCA. Some of the information may be claimed or
determined to be CBI.
    EPA is issuing this notice to inform all submitters of information
under all sections of TSCA that EPA may provide IEI access to these CBI
materials on a need-to-know basis only. All access to TSCA CBI under
this contract will take place at EPA Headquarters IEI's site located in
Cambridge, MA, in accordance with EPA's TSCA CBI Protection Manual.
    Access to TSCA data, including CBI, will continue until March 31,
2023. If the contract is extended, this access will also continue for
the duration of the extended contract without further notice.
    IEI personnel will be required to sign nondisclosure agreements and
will be briefed on appropriate security procedures before they are
permitted access to TSCA CBI.

    Authority: 15 U.S.C. 2601 et seq.

    Dated: June 20, 2018.
Pamela S. Myrick,
Director, Information Management Division, Office of Pollution
Prevention and Toxics.
[FR Doc. 2018-13945 Filed 6-27-18; 8:45 am]
 BILLING CODE 6560-50-P