[Federal Register Volume 86, Number 150 (Monday, August 9, 2021)]
[Notices]
[Pages 43555-43557]
[FR Doc No: 2021-16930]

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DEPARTMENT OF HEALTH AND HUMAN SERVICES

Food and Drug Administration

[Docket No. FDA-2015-D-0868]

Development and Submission of Near Infrared Analytical
Procedures; Guidance for Industry; Availability

AGENCY: Food and Drug Administration, Health and Human Services (HHS).

ACTION: Notice of availability.

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SUMMARY: The Food and Drug Administration (FDA or Agency) is announcing
the availability of a final guidance for industry entitled
``Development and Submission of Near Infrared Analytical Procedures.''
This guidance provides recommendations to applicants to aid the
development, validation, and use of near infrared (NIR)-based
analytical procedures in evaluating the identity, strength, quality,
purity, and potency of drug substances and drug products. The
recommendations apply to new drug applications (NDAs), abbreviated new
drug applications (ANDAs), and supplemental NDAs and ANDAs for small
molecule drugs. The principles in this guidance also apply to drug
substances and drug products covered in Type II drug master files. This
guidance finalizes the draft guidance of the same title issued on March
31, 2015.

DATES: The announcement of the guidance is published in the Federal
Register on August 9, 2021.

ADDRESSES: You may submit either electronic or written comments on
Agency guidances at any time as follows:

Electronic Submissions

    Submit electronic comments in the following way:
     Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments. Comments submitted
electronically, including attachments, to https://www.regulations.gov
will be posted to the docket unchanged. Because your comment will be
made public, you are solely responsible for ensuring that your comment
does not include any confidential information that you or a third party
may not wish to be posted, such as medical information, your or anyone
else's Social Security number, or confidential business information,
such as a manufacturing process. Please note that if you include your
name, contact information, or other information that identifies you in
the body of your comments, that information will be posted on https://www.regulations.gov.

     If you want to submit a comment with confidential
information that you do not wish to be made available to the public,
submit the comment as a written/paper submission and in the manner
detailed (see ``Written/Paper Submissions'' and ``Instructions'').

Written/Paper Submissions

    Submit written/paper submissions as follows:
     Mail/Hand Delivery/Courier (for written/paper
submissions): Dockets Management Staff (HFA-305), Food and Drug
Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852.
     For written/paper comments submitted to the Dockets
Management Staff, FDA will post your comment, as well as any
attachments, except for information submitted, marked and identified,
as confidential, if submitted as detailed in ``Instructions.''
    Instructions: All submissions received must include the Docket No.
FDA-2015-D-0868 for ``Development and Submission of Near Infrared
Analytical Procedures.'' Received comments will be placed in the docket
and, except for those submitted as ``Confidential Submissions,''
publicly viewable at https://www.regulations.gov or at the Dockets
Management Staff between 9 a.m. and 4 p.m., Monday through Friday, 240-
402-7500.
     Confidential Submissions--To submit a comment with
confidential information that you do not wish to be made publicly
available, submit your comments only as a written/paper submission. You
should submit two copies total. One copy will include the information
you claim to be confidential with a heading or cover note that states
``THIS DOCUMENT CONTAINS CONFIDENTIAL INFORMATION.'' The Agency will
review this copy, including the claimed confidential information, in
its consideration of comments. The second copy, which will have the
claimed confidential information redacted/blacked out, will be
available for public viewing and posted on https://www.regulations.gov.
Submit both copies to the Dockets Management Staff. If you do not wish
your name and contact information to be made publicly available, you
can provide this information on the cover sheet and not in the body of
your comments and you must identify this information as
``confidential.'' Any information marked as ``confidential'' will not
be disclosed except in accordance with 21 CFR 10.20 and other
applicable disclosure law. For more information about FDA's posting of
comments to public dockets, see 80 FR 56469, September 18, 2015, or
access the information at: https://www.govinfo.gov/content/pkg/FR-2015-09-18/pdf/2015-23389.pdf.
    Docket: For access to the docket to read background documents or
the electronic and written/paper comments received, go to https://www.regulations.gov and insert the docket number, found in brackets in
the heading of this document, into the ``Search'' box and follow the
prompts and/or go to the Dockets Management Staff, 5630 Fishers Lane,
Rm. 1061, Rockville, MD 20852,<PHONE_NUMBER>.
    You may submit comments on any guidance at any time (see 21 CFR
10.115(g)(5)).
    Submit written requests for single copies of this guidance to the
Division of Drug Information, Center for Drug Evaluation and Research,
Food and Drug Administration, 10001 New Hampshire Ave., Hillandale
Building, 4th Floor, Silver Spring, MD 20993-0002. Send one self-
addressed adhesive label to assist that office in processing your
requests. See the SUPPLEMENTARY INFORMATION section for electronic
access to the guidance document.

FOR FURTHER INFORMATION CONTACT: Eugenia Nashed, Center for Drug
Evaluation and Research, Food and Drug Administration, 10903 New
Hampshire Ave., Bldg. 51, Rm. 4154, Silver Spring, MD 20993-0002, 301-
796-1723.

SUPPLEMENTARY INFORMATION:

I. Background

    FDA is announcing the availability of a guidance for industry
entitled ``Development and Submission of Near Infrared Analytical
Procedures.'' This guidance provides recommendations to applicants to
aid the development, validation, and use of NIR-based analytical
procedures in evaluating the identity, strength, quality, purity, and
potency of drug substances and drug products. The recommendations apply
to NDAs, ANDAs, and supplemental NDAs and ANDAs for small molecule
drugs. The principles in this guidance also apply to drug substances
and drug products covered in Type II drug master files. FDA intends to
issue recommendations specific to NIR methods used for biological
products under biologics license applications in a future revision to
this guidance. Specifically, this guidance, among other things, (1)
addresses the development and submission of NIR analytical procedures
used during and for the manufacture and analysis of pharmaceuticals
(including raw materials, in-process materials and intermediates, drug
substances, and finished products); (2) provides recommendations to
manufacturers for applying the concepts described in the guidance for
industry entitled ``PAT--A Framework for Innovative Pharmaceutical
Development, Manufacturing, and Quality Assurance'' (https://www.fda.gov/media/71012/download) and the International Council for
Harmonisation guidance for industry entitled ``Q2(R1) Validation of
Analytical Procedures: Text and Methodology'' (https://www.fda.gov/regulatory-information/search-fda-guidance-documents/q2-r1-validation-analytical-procedures-text-and-methodology) to NIR analytical
procedures that use chemometric models; and (3) describes the type of
information that should be submitted about NIR analytical procedures in
applications.
    This guidance pertains only to the development and validation of
NIR analytical procedures and does not provide recommendations
concerning the setup, qualification, maintenance, or calibration of NIR
instruments. Although this guidance specifically addresses NIR
spectroscopy, this guidance's concepts of validation can be applied to
other multivariate analytical technics, including, for example, Raman.
    This guidance finalizes the draft guidance entitled ``Development
and Submission of Near Infrared Analytical Procedures'' issued on March
31, 2015 (80 FR 17057). FDA considered comments received on the draft
guidance as the guidance was finalized. Changes from the draft to the
final guidance include updates to reflect Agency regulatory experience
and technological advancements in the industry, as well as management
of NIR procedures over the life cycle of the products.
    This guidance is being issued consistent with FDA's good guidance
practices regulation (21 CFR 10.115). The guidance represents the
current thinking of FDA on the development and submission of NIR
analytical procedures. It does not establish any rights for any person
and is not binding on FDA or the public. You can use an alternative
approach if it satisfies the requirements of the applicable statutes
and regulations.

II. Paperwork Reduction Act of 1995

    While this guidance contains no collection of information, it does
refer to previously approved FDA collections of information. Therefore,
clearance by the Office of Management and Budget (OMB) under the
Paperwork Reduction Act of 1995 (PRA) (44 U.S.C. 3501-3521) is not
required for this guidance.

The previously approved collections of information are subject to
review by OMB under the PRA. The collections of information in 21 CFR
part 314 for NDAs and in 21 CFR parts 314 and 601 for annual reports,
ANDAs, and supplements to applications have been approved under OMB
control numbers 0910-0001 and 0910-0338, respectively. The collections
of information in 21 CFR part 211 for current good manufacturing
practices for finished pharmaceuticals and medical gases have been
approved under OMB control number 0910-0139.

III. Electronic Access

    Persons with access to the internet may obtain the guidance at
either https://www.fda.gov/drugs/guidance-compliance-regulatory-information/guidances-drugs or https://www.regulations.gov.

    Dated: August 2, 2021.
Lauren K. Roth,
Acting Principal Associate Commissioner for Policy.
[FR Doc. 2021-16930 Filed 8-6-21; 8:45 am]
BILLING CODE 4164-01-P


[Federal Register Volume 82, Number 40 (Thursday, March 2, 2017)]
[Proposed Rules]
[Pages 12301-12303]
[FR Doc No: 2017-03995]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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

========================================================================

Federal Register / Vol. 82, No. 40 / Thursday, March 2, 2017 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0125; Directorate Identifier 2016-NM-193-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Bombardier, Inc., Model DHC-8-401 and DHC-8-402 airplanes. This
proposed AD was prompted by a report that a pilot was unable to move
the rudder pedal due to an obstruction. This proposed AD would require
an inspection to determine if wiring shrouds are present, and modifying
the wiring shrouds if necessary. We are proposing this AD to address
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 17, 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
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone:<PHONE_NUMBER>; fax: 416-
375-4539; email<EMAIL_ADDRESS>Internet: http://www.bombardier.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<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0125; 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: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; 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-2017-0125;
Directorate Identifier 2016-NM-193-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

    Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2016-27, dated
September 14, 2016 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Bombardier, Inc., Model DHC-8-401 and DHC-8-402
airplanes. The MCAI states:

    An operator reported that the flying pilot was unable to move
the rudder pedal due to an obstruction caused by the non-flying
pilot's foot. The shoe belonging to the non-flying pilot was placed
between the rudder pedal and the newly installed wiring shroud and
prevented rudder pedal movement. The wiring shroud was installed to
support the wire harnesses installed below the cockpit instrument
panel.
    If not corrected, this condition could prevent rudder movement
during critical phases of flight or ground operation, and result in
loss of control of the aeroplane.
    This [Canadian] AD was issued to re-work the wiring shrouds to
eliminate potential for obstruction.

    Required actions include an inspection for the presence of wiring
shrouds and modification of any existing wiring shrouds. 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-
0125.

Related Service Information Under 1 CFR Part 51

    We reviewed Bombardier Service Bulletin 84-25-169, Revision A,
dated April 25, 2016. This service information describes procedures for
an inspection to verify if wiring shrouds are installed, and
modification of any existing wiring shrouds. 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.

Costs of Compliance

    We estimate that this proposed AD affects 82 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
            Action                         Labor cost               Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection...................  1 work-hour x $85 per hour = $85.              $0             $85          $6,970
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
these modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification of wiring shrouds.............  7 work-hours x $85 per hour = $595.             $71            $666
----------------------------------------------------------------------------------------------------------------

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 adding the following new airworthiness
directive (AD):

Bombardier, Inc.: Docket No. FAA-2017-0125; Directorate Identifier
2016-NM-193-AD.

(a) Comments Due Date

    We must receive comments by April 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model DHC-8-401 and DHC-8-
402 airplanes, certificated in any category, as identified in
Bombardier Service Bulletin 84-25-169, Revision A, dated April 25,
2016.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.

(e) Reason

    This AD was prompted by a report that a pilot was unable to move
the rudder pedal due to an obstruction caused by the non-flying
pilot's foot. We are issuing this AD to prevent an obstruction that
could prevent rudder pedal movement during critical phases of flight
or ground operations, potentially resulting in loss of control of
the airplane.

(f) Compliance

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

(g) Inspection and Modification of Wiring Shrouds

    Within 6 months after the effective date of this AD, do a one-
time inspection to determine if wiring shrouds are installed, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-25-169, Revision A, dated April 25, 2016.
    (1) If the airplane does not have wiring shrouds installed, no
further action is required by this AD.
    (2) If the airplane has wiring shrouds installed, before further
flight, modify the wiring shrouds in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-25-
169, Revision A, dated April 25, 2016.
    Note 1 to paragraph (g) of this AD: Wiring shrouds were
installed in accordance with Bombardier Modification Summary Package
(ModSum) IS4Q2500035-1, Revision A, dated July 26, 2011; Revision B,
dated October 10, 2013; Revision C, dated March 26, 2014; or
Revision D, dated February 26, 2016; or ModSum IS4Q2500035-2,
Revision A, dated July 26, 2011; Revision B, dated October 10, 2013;
Revision C, dated March

26, 2014; or Revision D, dated February 26, 2016.

(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170 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 ACO, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.
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, New York ACO,
ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2016-27, dated September 14, 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-2017-0125.
    (2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone: 416-375-
4000; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
Internet: http://www.bombardier.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 February 22, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03995 Filed 3-1-17; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)]
[Rules and Regulations]
[Pages 51456-51459]
[FR Doc No: 2015-20588]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2047; Directorate Identifier 2015-CE-013-AD;
Amendment 39-18243; AD 2015-17-10]
RIN 2120-AA64

Airworthiness Directives; SOCATA Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2007-04-13 for
certain SOCATA Model TBM 700 airplaness (type certificate previously
held by EADS SOCATA). This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as cracks
found on the main landing gear cylinders. We are issuing this AD to
require actions to address the unsafe condition on these products.

DATES: This AD is effective September 29, 2015.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
29, 2015.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of March
23, 2007 (72 FR 7576, February 16, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2047; or in person at the 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 service information identified in this AD, contact SOCATA,
Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33
(0)5 <IP_ADDRESS>; fax: 33 (0)5 <IP_ADDRESS>; or SOCATA North America,
North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023,
telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; Internet: http://www.socata.com. You may view this referenced service information at the
FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri
64106. 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 Docket No. FAA-2015-2047.

FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to
make changes to an NPRM (80 FR 8821, February 19, 2015), which would
amend 14 CFR part 39 to add an AD that would apply to certain SOCATA
Model TBM 700 airplaness (type certificate previously held by EADS
SOCATA). That SNPRM was published in the Federal Register on June 11,
2015 (80 FR 33208), and proposed to supersede

AD 2007-04-13, Amendment 39-14945, (72 FR 7576, February 16, 2007)
(``AD 2007-04-13'').
    Since we issued AD 2007-04-13, it has been determined that the time
between repetitive inspections should be extended and an optional
terminating action for the repetitive inspections is now available.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2006-0085R2, dated January 16, 2015 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:

    Cracks on several main landing gear (MLG) cylinders have been
reported in service.
    This condition, if not to detected and corrected, could lead to
fatigue cracks in the shock strut cylinder of the MLG, which could
result in a collapsed MLG during take-off or landing runs, and
possibly reduce the structural integrity of the aeroplane.
    To address this unsafe condition, EASA issued AD 2006-0085 to
require repetitive special detailed inspections (SDI) for cracks of
the MLG shock strut cylinder and, depending on findings, relevant
investigative and corrective actions.
    After that AD was issued, SOCATA performed an analysis to
demonstrate that the inspection interval could be extended, and
developed a reinforced MLG less prone to fatigue, which is embodied
in production through SOCATA modification (MOD) 70-0190-32 and can
be introduced in service through SOCATA Service Bulletin (SB) 70-
130-32 at Revision 03.
    Prompted by these developments, EASA issued AD 2006-0085R1 to
increase the inspection interval and to introduce the installation
of a reinforced MLG on the right hand (RH) side and left hand (LH)
side as an optional terminating action for the repetitive SDI
required by this AD.
    Since that AD was issued, it was found that aeroplanes MSN 639
to 683 (inclusive) are not affected by this AD. The applicability
has therefore been revised to remove those MSN.

The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.
    In addition, we have determined that airplanes with MLG with
forging body that had not reached 1,750 landings as of March 23, 2007
(the effective date of AD 2007-04-13) were not affected by the AD. This
is not the intent and allows airplanes to fly indefinitely with the
unsafe condition. This AD includes those airplanes with MLG with
forging body either at or under 1,750 landings as of March 23, 2007,
and extends the time between the repetitive inspections until a
reinforced landing gear is installed, which terminates the repetitive
inspections.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received one supportive comment to the NPRM (80 FR 8821,
February 19, 2015) and no comments on the SNPRM (80 FR 33208, June 11,
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and
the public interest require adopting the 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
SNPRM (80 FR 33208, June 11, 2015) for correcting the unsafe condition;
and
     Do not add any additional burden upon the public than was
already proposed in the SNPRM (80 FR 33208, June 11, 2015).

Related Service Information Under 1 CFR Part 51

    EADS SOCATA has issued TBM Aircraft Mandatory Service Bulletin SB
70-130, ATA No. 32, dated January 2006, and SOCATA has issued DAHER-
SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3,
dated December 2014. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
The DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014, incorporates procedures for replacing
cracked MLG with a reinforced MLG as a terminating action for the
repetitive inspections. 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 of this AD.

Costs of Compliance

    We estimate that this AD will affect 431 products of U.S. registry.
We also estimate that it will take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $109,905, or $255 per product.
    In addition, we estimate that any necessary follow-on actions will
take about 4 work-hours and require parts costing $6,000, for a cost of
$6,340 per product. We have no way of determining the number of
products that may need these actions.

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 above, I certify 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.

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-2015-
2047; 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 the SNPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Office
(telephone<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

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 removing Amendment 39-14945 (72 FR
7576, February 16, 2007), and adding the following new AD:

2015-17-10 SOCATA (type certificate previously held by EADS SOCATA):
Amendment 39-18243; Docket No. FAA-2015-2047; Directorate Identifier
2015-CE-013-AD.

(a) Effective Date

    This AD becomes effective September 29, 2015.

(b) Affected ADs

    This AD supersedes AD 2007-04-13, Amendment 39-14945, (72 FR
7576, February 16, 2007) (``AD 2007-04-13'').

(c) Applicability

    This AD applies to SOCATA Model TBM 700 airplanes, serial
numbers 1 through 638 and 687, that:
    (1) are not equipped with a left-hand main landing gear (MLG)
body part number (P/N) D68161 or D68161-1 and a right-hand MLG body
P/N D68162 or D68162-1; and
    (2) are certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 32: Landing
gear.

(e) Reason

    This AD was prompted from mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as cracks found on
the main landing gear cylinders. In addition, the FAA determined
that airplanes with MLG with forging body that had not reached 1,750
landings as of March 23, 2007 (the effective date of AD 2007-04-13)
were not affected by AD 2007-04-13. This is not the intent and
allows airplanes to fly indefinitely with the unsafe condition. This
AD increases the scope of the affected airplanes by including those
airplanes with MLG with forging body either at or under 1,750
landings as of March 23, 2007, increases the time between the
repetitive inspections, and incorporates a modification to terminate
the required repetitive inspections. We are issuing this AD to
detect and correct cracks in the shock strut cylinder of the MLG,
which could cause the MLG to fail. Failure of the shock strut
cylinder of the MLG could result in a collapsed MLG during takeoff
or landing and possible reduced structural integrity of the
airplane.

(f) Actions and Compliance for Airplanes Not Previously Affected by AD
2007-04-13

    Unless already done, do the actions in paragraphs (f)(1),
(f)(2), and (h) of this AD:
    (1) For MLG with forging body that were either at or under 1,750
landings as of March 23, 2007 (the effective date of (AD 2007-04-
13): Upon or before accumulating 1,750 landings on the MLG with
forging body since new or within the next 100 landings after
September 29, 2015 (the effective date of this AD), whichever occurs
later, inspect the forging body for cracks. Do the inspection
following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
    (2) If no cracks are detected during the inspection required in
paragraph (f)(1) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.

(g) Actions and Compliance for Airplanes Previously Affected by AD
2007-04-13

    Unless already done, do the actions in paragraphs (g)(1),
(g)(2), and (h) of this AD, including all subparagraphs:
    (1) As of March 23, 2007 (the effective date retained from AD
2007-04-13), for MLG with forging body totaling more than 1,750
landings but less than 3,501 landings since new:
    (i) Inspect the forging body for cracks within 100 landings
after March 23, 2007 (the effective date retained from AD 2007-04-
13), following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in
paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.
    (2) As of March 23, 2007 (the effective date retained from AD
2007-04-13), for MLG with forging body totaling more than 3,500
landings since new:
    (i) Inspect the forging body for cracks within 25 landings after
March 23, 2007 (the effective date retained from AD 2007-04-13),
following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in
paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.

(h) Actions and Compliance for All Affected Airplanes

    If any cracks are detected during any inspection required in
paragraphs (f)(1) through (g)(2) of this AD, including all
subparagraphs:
    (1) Before further flight, remove the affected landing gear leg
and confirm the presence of the crack with dye penetrant inspection
or fluorescent penetrant inspection.
    (2) If the crack is confirmed, before further flight, contact
SOCATA at the address in paragraph (l)(5) of this AD to coordinate
the FAA-approved landing gear repair/replacement and implement any
FAA-approved repair/replacement instructions obtained from SOCATA,
or replace the cracked landing gear with a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014. This replacement
terminates the repetitive inspections required by this AD.

(i) Calculating Unknown Number of Landings for Compliance

    The compliance times of this AD are presented in landings
instead of hours time-in-service (TIS). If the number of landings is
unknown, hours TIS may be used by dividing the number of hours TIS
by 1.35.

 (j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Albert J. Mercado, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2006-0085R2, dated January 16, 2015, for related information. You
may examine the MCAI on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.

(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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on
September 29, 2015.
    (i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, Revision 3, dated December 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on
March 23, 2007 (72 FR 7576, February 16, 2007).
    (i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, dated January 2006.
    (ii) Reserved.
    (5) For SOCATA service information identified in this AD,
contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9,
France; telephone: 33 (0)5 <IP_ADDRESS>; fax: 33 (0)5 <IP_ADDRESS>; or
SOCATA North America, North Perry Airport, 7501 S Airport Rd.,
Pembroke Pines, Florida 33023, telephone:<PHONE_NUMBER>; fax: (954)
964-4141; Internet: http://www.socata.com.
    (6) You may view this service information at FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148. In addition, you can access this service information
on the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2015-2047.
    (7) 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 Kansas City, Missouri, on August 14, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-20588 Filed 8-24-15; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Rules and Regulations]
[Pages 38959-38964]
[FR Doc No: 2018-16736]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0077; Product Identifier 2017-NM-126-AD; Amendment
39-19352; AD 2018-16-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A319 and A320 series airplanes; and A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes. This AD was prompted by
reports of battery retaining rod failures due to quality defects of the
material used during parts manufacturing. This AD requires a detailed
inspection of the battery support assemblies to identify the battery
retaining rod manufacturer, replacement of the battery retaining rods
with serviceable battery retaining rods if necessary, and the addition
of the applicable service information label on each battery retaining
rod if necessary. We are issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective September 12, 2018.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 12,
2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile
Dewoitine, 31700 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, 2200 South 216th St., Des
Moines, 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-2018-0077.

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-
0077; 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, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

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 A319
and A320 series airplanes; and Model A321-111, -112, -131, -211, -212,
-213, -231, and -232 airplanes. The NPRM published in the Federal
Register on February 12, 2018 (83 FR 5960) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0161R1, dated September 19, 2017; corrected September 20, 2017
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Airbus Model A319 and A320 series airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI
states:

    Several occurrences have been reported of battery rod failures
on certain Airbus aeroplanes. Subsequent examination of broken rod
parts determined that these failures were due to quality defects of
the material used during parts manufacturing. Each battery is
secured on an aeroplane by two rods. Failure of one rod, in case of
severe turbulence during flight or hard landing, could lead to
battery displacement, or roll on the remaining rod side, up to a
point where the remaining rod could be disengaged. The battery could
ultimately detach from its housing and damage relays, connectors,
contactor boxes, air ducts and surrounding structure.
    This condition, if not detected and corrected, could lead to the
loss of the normal electrical generation not followed by an
automatic recovery of essential network.
    To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A92N001-16 (later revised) and EASA
issued AD 2016-0204 [which corresponds to FAA AD 2016-25-24 (81 FR
90958, December 16, 2016) (``AD 2016-25-24'')] requiring repetitive
general visual inspections (GVI) of the four battery rods (two per
battery), and, in case of findings, replacement of battery rods.
    Since that [EASA] AD was issued, the manufacturer of the broken
battery retaining rods has been identified, which allows proper
identification of the affected parts and their withdrawal from
service. Consequently, Airbus issued [service bulletin] SB A320-92-
1116 and SB A320-92-1118 to provide the necessary instructions to
the affected operators. No rods delivered as spare parts are
affected by the manufacturing issue.
    For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2016-0204, which is superseded, and requires
replacement of battery retaining rods depending on manufacturer
identification. This [EASA] AD also provides a terminating action
for the repetitive inspections.

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-2018-
0077.

Comments

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

Request To Revise the Compliance Time

    Air Line Pilots Association, International (ALPA) requested that we
revise the compliance time. ALPA stated that the proposed AD specifies
a compliance time of within 24 months after the AD effective date. ALPA
commented that because the proposed AD is related to quality, it
believes this compliance time is insufficient. ALPA also commented that
since the issuance of the manufacturer's service information, operators
have had over 12 months to comply with the required corrective actions.
ALPA stated that, additionally, the time estimated to complete the
inspections and replacement of the affected parts is minimal. ALPA
recommended that we consider a compliance time of within 12 months
after the AD effective date.
    We disagree with the commenter. While some U.S. operators have had
time to plan and schedule the work contained in the Airbus service
information, there is no obligation for any U.S. operator to perform
those actions without a regulatory requirement. Therefore, we agree
with EASA's decision to allow a 24-month compliance time to plan,
schedule, and accomplish the actions necessary to remove the unsafe
condition. If additional data are presented that would justify a
shorter compliance time, we may consider further rulemaking on this
issue. We have not changed this AD in this regard.

Request To Revise the Definition of Serviceable Rod

    Delta Airlines (DAL) requested that we revise the definition of a
serviceable rod in paragraph (g) of the proposed AD. DAL stated to add
an additional paragraph that specifies:

    A battery retaining rod with an ISB [inspection service
bulletin] label installed in accordance with the accomplishment
instructions of Airbus Service Bulletin A320-92-1116, Revision 00,
dated January 31, 2017 (for Airbus Model A319 and A320 series
airplanes; and A321-111, -112, -131, -211, -212, -213, -231, and -
232 airplanes); or Airbus Service Bulletin A320-92-1118, Revision
00, dated January 31, 2017 (for Airbus Model A320-251N and -271N
airplanes).

    We partially agree with revising the definition of a serviceable
rod in paragraph (g) of this AD. We have determined that the
installation of the ISB label does not affect the unsafe condition and
have removed the requirement from this AD. We have coordinated this
changed with EASA. Furthermore, we have revised paragraph (g) of this
AD to clarify that the battery retaining rod used for replacement must
be positively identified as a serviceable battery retaining rod.

Request for Clarification Regarding Manufacturer Serial Numbers

    United Airlines (UAL) requested clarification regarding
manufacturer serial numbers in the proposed AD. UAL stated that the
manufacturer serial numbers are not applicable to the proposed AD as
identified in Airbus Service Bulletin A320-92-1116, Revision 00, dated
January 31, 2017, and Airbus Service Bulletin A320-92-1118, Revision
00, dated January 31, 2017. UAL stated that, although the machining
that caused the failure mode is identified in the service information,
the same battery retaining rod part number used in pre- and post-
service information remains unchanged. UAL commented that it is unclear
whether a serial number, batch number, or date exists for those battery
retaining rods. UAL also asked how were the battery

retaining rod spares deemed to be serviceable in paragraph (g)(1) of
the proposed AD?
    We agree to provide clarification for the commenter. According to
EASA AD 2017-0161R1, dated September 19, 2017; corrected September 20,
2017; no spares with manufacturing defects were delivered by Airbus.
Only a certain batch of defective parts were installed in production on
certain manufacturer serial numbers as specified in Airbus Service
Bulletin A320-92-1116, Revision 00, dated January 31, 2017; and Airbus
Service Bulletin A320-92-1118, Revision 00, dated January 31, 2017. If
an operator does not have an airplane affected as specified in the
service information, then there is no concern relative to defective
spare parts. We have not changed this AD in this regard.

Request To Clarify the Identification of Affected Parts

    DAL requested that we clarify the identification of the affected
parts in paragraph (h) of the proposed AD. DAL stated that the detailed
inspection to identify the battery retaining rod manufacturer should be
of the battery support assemblies and not the battery retaining rods.
    We agree with the commenter's request. We have revised paragraph
(h) of this AD to require a detailed inspection of the battery support
assemblies to identify the manufacturer of the battery retaining rods.

Request To Include an Additional Method of Compliance to the AD
Requirements

    DAL requested that we add an additional method of compliance for
paragraphs (h), (i), and (j) of the proposed AD. DAL stated that the
language, ``or using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
Design Organization Approval (DOA),'' should be included as an option
to using the service information. DAL also stated that this language
should be considered standard wording for future ADs as applicable.
    We disagree with the commenter's request. We have already provided
a method of compliance (MOC) for paragraphs (h), (i), and (j) of this
AD in accordance with the applicable service information. Any
deviations from the required MOC would need an evaluation in form of an
AMOC. DAL's proposed option is generally utilized in cases where no MOC
has been established or we have known information that the MOC may not
be applicable for all airplanes in the U.S fleet. We have not changed
the AD in this regard.

Request To Not Require Certain Service Information Labels on the
Battery Rod

    DAL and American Airlines (AA) requested that we not mandate that a
service information label be attached to each battery retaining rod as
required by the Airbus service information specified in paragraphs (j)
and (l) of the proposed AD. AA also requested that we not mandate
attachments of a service information label as part of the replacement
required by paragraph (i) of the proposed AD. DAL stated that it has 7
affected airplanes that would have a different final configuration than
the current and future fleet of 348 airplanes in its A320FAM fleet.
    AA stated that all battery retaining rods provided by Airbus post
August 2016 are marked and stamped with manufactures part number (MPN)
D8241023700000. AA commented that this marking of the new battery
retaining rods can be used in lieu of the information service bulletin
(ISB) label. AA also commented that it plans to replace all existing
battery retaining rods with the new battery retaining rods that are
marked with MPN D8241023700000.
    In addition, AA stated that installing the ISB label on the battery
retaining rods on 128 of its A319/A320 airplanes does not add a safety
value, but will put a burden on AA to maintain two different
configurations of battery retaining rod installation between 128
airplanes that are effected by the service information in the proposed
AD and 265 airplanes that are not affected by the service information
in the proposed AD.
    We agree with the commenters' request. We agree that the ISB label
is not necessary to mitigate the risk addressed in this AD. Therefore,
we have determined that the installation of ISB label should be
optional and not a required for compliance (RC) step.
    However, 14 CFR 39.9, specifies that operators have a continuing
obligation to maintain compliance with an AD, and the installation of
the ISB label or an equivalent method to identify a serviceable battery
retaining rod provides the operators with a simplified way to
demonstrate compliance with the AD requirements. We have removed
paragraph (j) of the proposed AD and revised paragraph (l) of this AD
to revise the terminating action requirements. We have also added
paragraph (j) of this AD to provide an exception to paragraph (i) of
this AD, which specifies that installing the ISB label is not a
requirement in this AD.

Request To Revise the Terminating Action Paragraph

    DAL requested that paragraph (l) of the proposed AD, ``Terminating
Action,'' be revised to read, ``Replacement of all battery retaining
rods,'' and not, ``Replacement of all battery retaining rods marked
`SA. . . .' '' DAL stated that the battery retaining rods are not
marked with ``SA,'' only the battery support assemblies.
    We agree with the commenter's request and have revised the AD
accordingly.

Request To Use Alternate Part Numbers

    Spirit Airlines requested that either the service information or
the proposed AD be revised to provide the use of alternate materials to
label part number (P/N) ASNE0248A1-4H9. Spirit Airlines stated that P/N
ASNE0248A1-4H9 is no longer available, and that alternate P/N E0248A1-
4H9P and P/N ASNE0248A1-4H9T may be obtained from Airbus. Spirit
Airlines believes that use of these alternate part numbers would
provide an equivalent level of safety as referenced in Airbus Dossier
Reference 80403684/003, dated January 8, 2018, and Airbus Retrofit
Information Letter SA92M16012714 R00, dated February 1, 2017.
    DAL requested that a previously approved AMOC be used in the
proposed AD. DAL stated that in paragraph (h) and (j) of the proposed
AD, Airbus Service Bulletin A320-92-1116, Revision 00, dated January
31, 2017, calls out a non-procurable part number for the identification
label. Therefore, DAL proposed that recognition of AMOC AIR-676-18-152,
issued against AD 2016-25-24, which allows an alternate label part
number, be added to paragraph (m) of the proposed AD as an acceptable
method of compliance to the proposed AD.
    We partially agree with the commenters request. As we stated
previously, we have determined that installation of an ISB label is not
an RC step. Therefore, a previously issued AMOC for allowing alternate
label part numbers is unnecessary. However, we would like to remind
operators that 14 CFR 39.9 specifies an operator's continuing
obligation to maintain compliance with an AD, and installation of an
ISB label or an equivalent method provides operators with a method to
demonstrate the affected battery retaining rods have been removed and
replaced with serviceable retaining rods in compliance with the AD
requirements.

Differences Between This AD and the MCAI

    The MCAI includes a requirement to install an ISB label. This AD
does not include that requirement. We have determined that the ISB
label is not necessary to mitigate the risk addressed in this AD.
However, 14 CFR 39.9, specifies that operators have a continuing
obligation to maintain compliance with an AD, and the installation of
the ISB label or an equivalent method to identify a serviceable battery
retaining rod provides the operators with a simplified way to
demonstrate compliance with the AD requirements.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-92-1116, Revision 00, dated
January 31, 2017; and Service Bulletin A320-92-1118, Revision 00, dated
January 31, 2017. This service information describes a detailed
inspection of the battery support assemblies to identify the battery
retaining rod manufacturer, replacement of the battery retaining rods
with serviceable battery retaining rods if necessary, and adding the
applicable service information label on each battery retaining rod if
necessary. These documents are distinct since they apply to different
airplane models. 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 330 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.........................  1 work-hour x $85 per hour               $0             $85         $28,050
                                      = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need this
replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  1 work-hour x $85 per hour = $85...              $0             $85
----------------------------------------------------------------------------------------------------------------

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):

2018-16-12 Airbus: Amendment 39-19352; Docket No. FAA-2018-0077;
Product Identifier 2017-NM-126-AD.

(a) Effective Date

    This AD is effective September 12, 2018.

(b) Affected ADs

    This AD affects AD 2016-25-24, Amendment 39-18750 (81 FR 90958,
December 16, 2016) (``AD 2016-25-24'').

(c) Applicability

    This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
216, -231, -232, -233, -251N, and -271N airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes,
certificated in any category, as identified in Airbus Service
Bulletin A320-92-1116, Revision 00, dated January 31, 2017; or
Airbus Service Bulletin A320-92-1118, Revision 00, dated January 31,
2017.

(d) Subject

    Air Transport Association (ATA) of America Code 92, Electrical
system installation.

(e) Reason

    This AD was prompted by reports of battery retaining rod
failures due to quality defects of the material used during parts
manufacturing. We are issuing this AD to detect and correct broken
battery retaining rods, which, in the event of a hard landing or
severe turbulence, could cause the battery to detach from its
housing, resulting in damage to other electrical equipment and
surrounding structure. This condition could lead to loss of normal
electrical power generation and subsequent inability to restore
electrical power to essential airplane systems.

(f) Compliance

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

(g) Definition of a Serviceable Rod

    For the purpose of this AD, a serviceable battery retaining rod
is defined in paragraphs (g)(1) or (g)(2) of this AD.
    (1) A battery retaining rod provided as a spare part by Airbus.
    (2) A battery retaining rod previously fitted on a battery
support assembly installed on an airplane manufacturer serial number
that is not specified in Airbus Service Bulletin A320-92-1116,
Revision 00, dated January 31, 2017 (for Airbus Model A319 and A320
series airplanes; and Model A321-111, -112, -131, -211, -212, -213,
-231, and -232 airplanes); or Airbus Service Bulletin A320-92-1118,
Revision 00, dated January 31, 2017 (for Airbus Model A320-251N and
-271N airplanes), provided the battery retaining rod used for
replacement can be positively identified as a serviceable battery
retaining rod.

(h) Identification of Affected Parts

    Within 24 months after the effective date of this AD: Accomplish
a detailed inspection of the battery support assemblies to identify
the battery retaining rod manufacturer, in accordance with the
Accomplishment Instructions of the Airbus Service Bulletin A320-92-
1116, Revision 00, dated January 31, 2017 (for Airbus Model A319 and
A320 series airplanes, and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes); or Airbus Service Bulletin A320-92-
1118, Revision 00, dated January 31, 2017 (for Airbus Model A320-
251N and -271N airplanes).

(i) Replacement of Affected Parts if Marking Is Found on Battery
Support Assembly

    If, during the inspection specified in paragraph (h) of this AD,
the quality stamp on any battery support assemblies are found marked
with an ``SA'' manufacturer identification, before further flight,
replace the battery retaining rods with serviceable battery
retaining rods, in accordance with the Accomplishment Instructions
of the Airbus Service Bulletin A320-92-1116, Revision 00, dated
January 31, 2017 (for Airbus Model A319 and A320 series airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes); or Airbus Service Bulletin A320-92-1118, Revision 00,
dated January 31, 2017 (for Airbus Model A320-251N and -271N
airplanes); except as provided by paragraph (j) of this AD.

(j) Exception to the Service Information

    Although Airbus Service Bulletin A320-92-1116, Revision 00,
dated January 31, 2017; and Airbus Service Bulletin A320-92-1118,
Revision 00, dated January 31, 2017; specify to install inspection
service bulletin (ISB) labels, this AD does not include that
requirement.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on
any airplane, a non-serviceable battery retaining rod.

(l) Terminating Action

    Replacement of all battery retaining rods with a serviceable
battery retaining rod as required by paragraph (i) of this AD
constitutes terminating action for all requirements of AD 2016-25-24
for that airplane.

(m) 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 International Section, send it to the attention of
the person identified in paragraph (n)(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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0161R1, dated September 19, 2017; corrected
September 20, 2017; 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-2018-0077.
    (2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>.

(o) 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 A320-92-1116, Revision 00, dated
January 31, 2017.
    (ii) Airbus Service Bulletin A320-92-1118, Revision 00, dated
January 31, 2017.
    (3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine,
31700 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, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (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 Des Moines, Washington, on July 27, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-16736 Filed 8-7-18; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: December 12, 2006 (Volume 71, Number 238)]
[Notices]
[Page 74497-74498]
[DOCID:fr12de06-48]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. RP07-91-000]

Enbridge Pipelines (KPC); Notice of Revenue Credit Report

December 5, 2006.
    Take notice that on November 30, 2006, Enbridge Pipelines (KPC)
(KPC) tendered for filing its Annual Interruptible Revenue Crediting
Report for the twelve (12) month period ending September 30, 2006.
    KPC states that copies of its transmittal letter and appendices
have been mailed to all affected customers and interested state
commissions.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211 and 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the date as indicated
below. Anyone filing an intervention or protest must serve a copy of
that document on the Applicant. Anyone filing an intervention or
protest on or before the intervention or protest date need not serve
motions to intervene or protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and

interventions in lieu of paper using the ``eFiling'' link at http://www.ferc.gov.
 Persons unable to file electronically should submit an

original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible on-line at http://www.ferc.gov, using the

``eLibrary'' link and is available for review in the Commission's
Public Reference Room in Washington, DC. There is an ``eSubscription''
link on the Web site that enables subscribers to receive e-mail
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please e-mail
<EMAIL_ADDRESS>or call<PHONE_NUMBER> (toll free). For

TTY, call<PHONE_NUMBER>.
    Comment Date: 5 p.m. Eastern Time December 12, 2006.

Magalie R. Salas,
Secretary.
[FR Doc. E6-21084 Filed 12-11-06; 8:45 am]

BILLING CODE 6717-01-P


TRIETHYLENE GLYCOL : INCIDENT REPORTS Triethylene glycol ( TEG) is used as an air sanitizer. In addition, TEG is an important industrial solvent. It is also useful in the dehydration of gasses, manufacturing of insecticides and in the synthesis of some organic derivatives. Pure TEG is useful in the production of plasticizer for cellophane, glue, cork, powder ceramics and some plastics. TEG is a component in the formulation of some pigments, printing dyes, inks and pastes. It is also used for air fumigation.

The major application for TEG is used as a drying agent for natural gas, as humectants, as a solvent and in the manufacture of vinyl plasticizers. The purpose of this chapter is to review the evidence of health effects in humans resulting from exposure to TEG. There is no published literature studies can be located associated with health effects chronic exposure to TEG. This reports summarized the potential acute health effects of TEG in humans, reported as incident reports from different sources.

DATA SOURCE There are many incident reports of health effects associated with acute TEG exposure. The following databases have been consulted for the poisoning incident data on the active ingredient TEG ( PC Code: 083501):

1. OPP Incident Data System ( IDS)  The Incident Data System of The Office of Pesticide Programs ( OPP) of the Environmental Protection Agency ( EPA) contains reports of incidents from various sources, including registrants, other federal and state health and environmental agencies and individual consumers, submitted to OPP since 1992. Reports submitted to the Incident Data System represent anecdotal reports or allegations only, unless otherwise stated. Typically no conclusions can be drawn implicating the pesticide as a cause of any of the reported health effects. Nevertheless, sometimes with enough cases and/ or enough documentation risk mitigation measures may be suggested.

2. Poison Control Centers  as the result of a data purchase by EPA, OPP received Poison Control Center data covering the years 1993 through 1996 for all pesticides. Most of the national Poison Control Centers ( PCCs) participate in a national data collection system, the Toxic Exposure Surveillance System, which obtains data from about 65 70 centers at hospitals and universities. PCCs provide telephone consultation for individuals and health care providers on suspected poisonings, involving drugs, household products, pesticides, etc.

3. California Department of Pesticide Regulation  California has collected uniform data on suspected pesticide poisonings since 1982. Physicians are required, by statute, to report to their local health officer all occurrences of illness suspected of being related to exposure to pesticides. The majority of the incidents involve workers. Information on exposure ( worker activity), type of illness ( systemic, eye, skin, eye/ skin and respiratory), likelihood of a causal relationship, and number of days off work and in the hospital are provided.

4. National Pesticide Telecommunications Network ( NPTN)  NPTN is a toll free information service supported by OPP. A ranking of the top 200 active ingredients for which telephone calls were received during calendar years 1984 1991, inclusive, has been prepared. The total number of calls was tabulated for the categories human incidents, animal incidents, calls for information, and others.

5. Published Incident Reports  Some incident reports associated with creosote related human health hazard are published in the scientific literature.

INCIDENT REPORT DATA ASSOCIATED WITH HEALTH EFFECTS OF TRIETHYLENE GLYCOL EXPOSURE OPP's Incident Data System ( IDS)

Please note that the following cases from the IDS do not have documentation confirming exposure or health effects. There are 269 incidents reports been recorded in the IDS are TEG related. Most of the incidences are related to inhalation irritation and/ or allergic type reaction. The reported symptoms include respiratory irritation, coughing, chest tightness, difficulty breathing, shortness of breath, wheezing. In some cases, dermal sensitization reactions were also noticed.

Poison Control Center All the incidences reported in the Poison Center Center data base were included in the OPP's IDS. No additional data were reported in the Poison Control Center database covering the years 1993 through 1996.

California Data  1982 through 1996 Detailed descriptions of two cases submitted to the California Pesticide Illness Surveillance Program ( 1982 1996) were reviewed. In both cases, after exposed to aerosol disinfectant, the individuals developed allergic respiratory symptoms. The reported symptoms included chest tightness, coughing, wheezing, short of breath, and mild bronchospasm. The involved aerosol disinfectant containing both TEG and propylene glycol as active ingredients.

National Pesticide Telecommunications Network ( NPTN)

There are no incidences reported in the NPTN database. Incident Reports Associated with Acute Toxic Effects of TEG Published in Scientific Literature.

There are no incidences located in published literature related to TEG.