Gravimetric with drying  .....................  ..............  4500-SO4 2- D....  4500-SO4 2- D....  4500-SO4 2- D-97.
                                  of residue.
                                 Turbidimetric method...  .....................  D 516-07, 11,   4500-SO4 2- E....  4500-SO4 2- E....  4500-SO4 2- E-97.
                                                                                16.
                                 Automated methylthymol   .....................  ..............  4500-SO4 2- F....  4500-SO4 2- F....  4500-SO4 2- F-97.
                                  blue method.
Total Dissolved Solids.........  Total Dissolved Solids   .....................  ..............  2540 C...........  2540 C.
                                  Dried at 180 deg C.
Zinc...........................  Axially viewed           200.5, Revision
                                  inductively coupled      4.2.\2\
                                  plasma-atomic emission
                                  spectrometry (AVICP-
                                  AES).
                                 Atomic Absorption;       .....................  ..............  3111 B...........  3111 B.
                                  Direct Aspiration.
                                 Inductively Coupled      .....................  ..............  3120 B...........  3120 B.
                                  Plasma.
--------------------------------------------------------------------------------------------------------------------------------------------------------
 * * * * * * *
\1\ Standard Methods for the Examination of Water and Wastewater, 21st edition (2005). Available from American Public Health Association, 800 I Street
  NW, Washington, DC 20001-3710.
\2\ EPA Method 200.5, Revision 4.2. ``Determination of Trace Elements in Drinking Water by Axially Viewed Inductively Coupled Plasma-Atomic Emission
  Spectrometry.'' 2003. EPA/600/R-06/115. (Available at http://www.epa.gov/water-research/epa-drinking-water-research-methods.)
\3\ Standard Methods Online are available at http://www.standardmethods.org. The year in which each method was approved by the Standard Methods
  Committee is designated by the last two digits in the method number. The methods listed are the only online versions that may be used.
\4\ Available from ASTM International, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959 or http://astm.org. The methods listed are the only
  alternative versions that may be used.
 * * * * * * *
\6\ Standard Methods for the Examination of Water and Wastewater, 20th edition (1998). Available from American Public Health Association, 800 I Street
  NW, Washington, DC 20001-3710.
\7\ Method ME355.01, Revision 1.0. ``Determination of Cyanide in Drinking Water by GC/MS Headspace,'' May 26, 2009. Available at https://www.nemi.gov or
  from James Eaton, H & E Testing Laboratory, 221 State Street, Augusta, ME 04333.<PHONE_NUMBER>.
\8\ Systea Easy (1-Reagent). ``Systea Easy (1-Reagent) Nitrate Method,'' February 4, 2009. Available at https://www.nemi.gov or from Systea Scientific,
  LLC., 900 Jorie Blvd., Suite 35, Oak Brook, IL 60523.
\9\ EPA Method 524.3, Version 1.0. ``Measurement of Purgeable Organic Compounds in Water by Capillary Column Gas Chromatography/Mass Spectrometry,''
  June 2009. EPA 815-B-09-009. Available at https://www.nemi.gov.
\10\ Mitchell Method M5271, Revision 1.1. ``Determination of Turbidity by Laser Nephelometry,'' March 5, 2009. Available at https://www.nemi.gov or from
  Leck Mitchell, Ph.D., PE, 656 Independence Valley Dr., Grand Junction, CO 81507.
\11\ Mitchell Method M5331, Revision 1.1. ``Determination of Turbidity by LED Nephelometry,'' March 5, 2009. Available at https://www.nemi.gov or from
  Leck Mitchell, Ph.D., PE, 656 Independence Valley Dr., Grand Junction, CO 81507.
\12\ Orion Method AQ4500, Revision 1.0. ``Determination of Turbidity by LED Nephelometry,'' May 8, 2009. Available at https://www.nemi.gov or from
  Thermo Scientific, 166 Cummings Center, Beverly, MA 01915, http://www.thermo.com.
\13\ Modified ColitagTM Method. ``Modified ColitagTM Test Method for the Simultaneous Detection of E. coli and other Total Coliforms in Water (ATP D05-
  0035),'' August 28, 2009. Available at https://www.nemi.gov or from CPI International, 5580 Skylane Boulevard, Santa Rosa, CA 95403.
\14\ EPA Method 557. ``Determination of Haloacetic Acids, Bromate, and Dalapon in Drinking Water by Ion Chromatography Electrospray Ionization Tandem
  Mass Spectrometry (IC-ESI-MS/MS),'' September 2009. EPA 815-B-09-012. Available at https://www.nemi.gov.
\15\ AMI Turbiwell, ``Continuous Measurement of Turbidity Using a SWAN AMI Turbiwell Turbidimeter,'' August 2009. Available at https://www.nemi.gov or
  from Markus Bernasconi, SWAN Analytische Instrumente AG, Studbachstrasse 13, CH-8340 Hinwil, Switzerland.
\16\ EPA Method 334.0. ``Determination of Residual Chlorine in Drinking Water Using an On-line Chlorine Analyzer,'' September 2009. EPA 815-B-09-013.
  Available at https://www.nemi.gov.
\17\ ChloroSense. ``Measurement of Free and Total Chlorine in Drinking Water by Palintest ChloroSense,'' August 2009. Available at https://www.nemi.gov
  or from Palintest Ltd., 1455 Jamike Avenue (Suite 100), Erlanger, KY 41018.
\18\ EPA Method 302.0. ``Determination of Bromate in Drinking Water using Two-Dimensional Ion Chromatography with Suppressed Conductivity Detection,''
  September 2009. EPA 815-B-09-014. Available at https://www.nemi.gov.
\19\ EPA 415.3, Revision 1.2. ``Determination of Total Organic Carbon and Specific UV Absorbance at 254 nm in Source Water and Drinking Water,''
  September 2009. EPA/600/R-09/122. Available at http://www.epa.gov/water-research/epa-drinking-water-research-methods.
\20\ Readycult[supreg] Method, ``Readycult[supreg] Coliforms 100 Presence/Absence Test for Detection and Identification of Coliform Bacteria and
  Escherichia coli in Finished Waters,'' January, 2007. Version 1.1. Available from EMD Millipore (division of Merck KGaA, Darmstadt, Germany), 290
  Concord Road, Billerica, MA 01821.
\21\ Chromocult[supreg] Method, ``Chromocult[supreg] Coliform Agar Presence/Absence Membrane Filter Test Method for Detection and Identification of
  Coliform Bacteria and Escherichia coli in Finished Waters,'' November, 2000. Version 1.0. EMD Millipore (division of Merck KGaA, Darmstadt, Germany),
  290 Concord Road, Billerica, MA 01821.
\22\ Hach Company. ``Hach Company SPADNS 2 (Arsenite-Free) Fluoride Method 10225--Spectrophotometric Measurement of Fluoride in Water and Wastewater,''
  January 2011. 5600 Lindbergh Drive, P.O. Box 389, Loveland, Colorado 80539.
\23\ Hach Company. ``Hach Company TNTplus\TM\ 835/836 Nitrate Method 10206--Spectrophotometric Measurement of Nitrate in Water and Wastewater,'' January
  2011. 5600 Lindbergh Drive, P.O. Box 389, Loveland, Colorado 80539.
\24\ EPA Method 525.3. ``Determination of Semivolatile Organic Chemicals in Drinking Water by Solid Phase Extraction and Capillary Column Gas
  Chromatography/Mass Spectrometry (GC/MS),'' February 2012. EPA/600/R-12/010. Available at http://www.epa.gov/water-research/epa-drinking-water-research-methods.
\25\ EPA Method 536. ``Determination of Triazine Pesticides and their Degradates in Drinking Water by Liquid Chromatography Electrospray Ionization
  Tandem Mass Spectrometry (LC/ESI-MS/MS),'' October 2007. EPA 815-B-07-002. Available at the National Service Center for Environmental Publications
  (EPA Method 536).
\26\ EPA Method 523. ``Determination of Triazine Pesticides and their Degradates in Drinking Water by Gas Chromatography/Mass Spectrometry (GC/MS),''
  February 2011. EPA 815-R-11-002. Available at the National Service Center for Environmental Publications (EPA Method 523).
 * * * * * * *
\28\ Standard Methods for the Examination of Water and Wastewater, 22nd edition (2012). Available from American Public Health Association, 800 I Street
  NW, Washington, DC 20001-3710.
\29\ EPA Method 524.4, Version 1.0. ``Measurement of Purgeable Organic Compounds in Water by Gas Chromatography/Mass Spectrometry using Nitrogen Purge
  Gas,'' May 2013. EPA 815-R-13-002. Available at the National Service Center for Environmental Publications (EPA Method 524.4).

\30\ Charm Sciences Inc. ``Fast Phage Test Procedure. Presence/Absence for Coliphage in Ground Water with Same Day Positive Prediction''. Version 009.
  November 2012. 659 Andover Street, Lawrence, MA 01843. Available at www.charmsciences.com.
\31\ Hach Company. ``Hach Method 10260--Determination of Chlorinated Oxidants (Free and Total) in Water Using Disposable Planar Reagent-filled Cuvettes
  and Mesofluidic Channel Colorimetry,'' April 2013. 5600 Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\32\ ChlordioX Plus. ``Chlorine Dioxide and Chlorite in Drinking Water by Amperometry using Disposable Sensors,'' November 2013. Available from
  Palintest Ltd., 1455 Jamike Avenue (Suite 100), Erlanger, KY 41018.
\33\ Tecta EC/TC. ``Techta\TM\ EC/TC Medium and Techta\TM\ Instrument: A Presence/Absence Method for the Simultaneous Detection of Total Coliforms and
  Escherichia coli (E. coli) in Drinking Water,'' version 1.0, May 2014. Available from Pathogen Detection Systems, Inc., 382 King Street East,
  Kingston, Ontario, Canada, K7K 2Y2.
\34\ Hach Company. ``Hach Method 10241--Spectrophotometric Measurement of Free Chlorine (Cl2) in Drinking Water,'' November 2015. Revision 1.2. 5600
  Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\35\ Hach Company. ``Hach Method 8026--Spectrophotometric Measurement of Copper in Finished Drinking Water,'' December 2015. Revision 1.2. 5600
  Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\36\ Hach Company. ``Hach Method 10272--Spectrophotometric Measurement of Copper in Finished Drinking Water,'' December 2015. Revision 1.2. 5600
  Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\37\ Hach Company. ``Hach Method 10261--Total Organic Carbon in Finished Drinking Water by Catalyzed Ozone Hydroxyl Radical Oxidation Infrared
  Analysis,'' December 2015. Revision 1.2. 5600 Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\38\ Hach Company. ``Hach Method 10267--Spectrophotometric Measurement of Total Organic Carbon (TOC) in Finished Drinking Water,'' December 2015.
  Revision 1.2. 5600 Lindbergh Drive, P.O. Box 389, Loveland, CO 80539.
\39\ Hach Company. ``Hach Method 10258--Determination of Turbidity by 360[deg] Nephelometry,'' January 2016. Revision 1.0. 5600 Lindbergh Drive, P.O.
  Box 389, Loveland, CO 80539.
\40\ Nitrate Elimination Company Inc. (NECi). ``Method for Nitrate Reductase Nitrate-Nitrogen Analysis of Drinking Water,'' February 2016. Superior
  Enzymes Inc., 334 Hecla Street, Lake Linden, Michigan 49945.
\41\ Thermo Fisher. ``Thermo Fisher Scientific Drinking Water Orthophosphate Method for Thermo Scientific Gallery Discrete Analyzer,'' February 2016.
  Revision 5. Thermo Fisher Scientific, Ratastie 2, 01620 Vantaa, Finland.
\42\ Mitchell Method M5331, Revision 1.2. ``Determination of Turbidity by LED or Laser Nephelometry,'' February 2016. Available from Leck Mitchell,
  Ph.D., PE, 656 Independence Valley Dr., Grand Junction, CO 81507.
\43\ Tecta EC/TC. ``TectaTM EC/TC Medium and the TectaTM Instrument: A Presence/Absence Method for the Simultaneous Detection of Total Coliforms and
  Escherichia coli (E. coli) in Drinking Water,'' version 2.0, February 2017. Available from Pathogen Detection Systems, Inc., 382 King Street East,
  Kingston, Ontario, Canada, K7K 2Y2.
\44\ Lovibond PTV 1000. ``Continuous Measurement of Drinking Water Turbidity Using a Lovibond PTV 1000 White Light LED Turbidimeter,'' December 2016.
  Revision 1.0. Available from Tintometer, Inc., 6456 Parkland Drive, Sarasota, FL 34243.
\45\ Lovibond PTV 2000. ``Continuous Measurement of Drinking Water Turbidity Using a Lovibond PTV 2000 660-nm LED Turbidimeter,'' December 2016.
  Revision 1.0. Available from Tintometer, Inc., 6456 Parkland Drive, Sarasota, FL 34243.
\46\ Lovibond PTV 6000. ``Continuous Measurement of Drinking Water Turbidity Using a Lovibond PTV 6000 Laser Turbidimeter,'' December 2016. Revision
  1.0. Available from Tintometer, Inc., 6456 Parkland Drive, Sarasota, FL 34243.
\47\ Thermo Fisher. ``Thermo Fisher Method 557.1: Determination of Haloacetic Acids in Drinking Water using Two-Dimensional Ion Chromatography with
  Suppressed Conductivity Detection,'' January 2017. Version 1.0. Available from Thermo Fisher Scientific, 490 Lakeside Dr., Sunnyvale, CA 94085
  ([email protected]).
\48\ EPA Method 150.3. ``Determination of pH in Drinking Water,'' February 2017. EPA 815-B-17-001. Available at the National Service Center for
  Environmental Publications (EPA Method 150.3).
\49\ Standard Methods for the Examination of Water and Wastewater, 23rd edition (2017). Available from American Public Health Association, 800 I Street
  NW, Washington, DC 20001-3710.
\50\ EPA Method 900.0, Rev. 1.0. ``Determination of Gross Alpha and Gross Beta in Drinking Water,'' February 2018. EPA 815-B-18-002. Available at the
  National Service Center for Environmental Publications (EPA Method 900.0 Rev 1.0).
\51\ Hach Company. ``Hach Method 10258--Determination of Turbidity by 360[deg] Nephelometry,'' March 2018. Revision 2.0. 5600 Lindbergh Drive, P.O. Box
  389, Loveland, CO 80539.
\52\ Hach Company. ``Hach Method 8195--Determination of Turbidity by Nephelometry,'' March 2018. Revision 3.0. 5600 Lindbergh Drive, P.O. Box 389,
  Loveland, CO 80539.

[FR Doc. 2018-22162 Filed 10-11-18; 8:45 am]
 BILLING CODE 6560-50-P


[Federal Register Volume 76, Number 13 (Thursday, January 20, 2011)]
[Rules and Regulations]
[Page 3516]
[FR Doc No: 2011-1194]

=======================================================================
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DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 117

[Docket No. USCG-2010-1090]

Drawbridge Operation Regulations; Harlem River, New York City, NY

AGENCY: Coast Guard, DHS.

ACTION: Notice of temporary deviation from regulations.

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

SUMMARY: The Commander, First Coast Guard District, has issued a
temporary deviation from the regulation governing the operation of the
103rd Street (Wards Island) Bridge at mile 0.0, across the Harlem
River, New York City, New York. The deviation is necessary to
facilitate bridge rehabilitation maintenance. This deviation allows the
bridge to remain in the closed position for one hundred nineteen days.

DATES: This deviation is effective from January 10, 2011 through April
29, 2011.

ADDRESSES: Documents mentioned in this preamble as being available in
the docket are part of docket USCG-2010-1090 and are available online
at http://www.regulations.gov, inserting USCG-2010-1090 in the
``Keyword'' and then clicking ``Search''. They are also available for
inspection or copying at the Docket Management Facility (M-30), U.S.
Department of Transportation, West Building Ground Floor, Room W12-140,
1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: If you have questions on this rule,
call or e-mail Mr. Joe Arca, Project Officer, First Coast Guard
District<EMAIL_ADDRESS>telephone<PHONE_NUMBER>. If you have
questions on viewing the docket, call Renee V. Wright, Program Manager,
Docket Operations, telephone<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: The 103rd Street (Wards Island) Bridge
across the Harlem River at mile 0.0 has a vertical clearance in the
closed position of 55 feet at mean high water and 60 feet at mean low
water. The existing drawbridge operation regulations are listed at 33
CFR 117.789(b)(1).
    The waterway has seasonal recreational vessels, and commercial
vessels of various sizes.
    The owner of the bridge, New York City Department of
Transportation, requested a temporary deviation to facilitate
rehabilitation construction at the bridge.
    Under this temporary deviation the 103rd Street (Wards Island)
Bridge, may remain in the closed position from January 10, 2011 through
April 29, 2011. Vessels that can pass under the bridge without a bridge
opening may do so at all times.
    In accordance with 33 CFR 117.35(e), the bridge must return to its
regular operating schedule immediately at the end of the designated
time period. This deviation from the operating regulations is
authorized under 33 CFR 117.35.

    Dated: January 5, 2011.
Gary Kassof,
Bridge Program Manager, First Coast Guard District.
[FR Doc. 2011-1194 Filed 1-19-11; 8:45 am]
BILLING CODE 9110-04-P


[Federal Register: December 4, 2007 (Volume 72, Number 232)]
[Notices]
[Page 68228-68229]
[DOCID:fr04de07-117]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-56825; File No. SR-NASDAQ-2007-066]

Self-Regulatory Organizations; The NASDAQ Stock Market LLC;
Notice of Filing and Immediate Effectiveness of Proposed Rule Change To
Clarify the Applicability to Limited Partnerships of Nasdaq's Direct
Registration Program Requirements

November 20, 2007.
    Pursuant to Section 19(b)(1) of the Securities Exchange Act of 1934
(``Act''),\1\ notice is hereby given that on July 12, 2007, NASDAQ
Stock Market LLC (``Nasdaq'') filed with the Securities and Exchange
Commission (``Commission'') the proposed rule change described in Items
I, II, and III below, which items have been prepared primarily by
Nasdaq. The Commission is publishing this notice to solicit comments on
the proposed rule change from interested parties.
---------------------------------------------------------------------------

    \1\ 15 U.S.C. 78s(b)(1).
---------------------------------------------------------------------------

I. Self-Regulatory Organization's Statement of the Terms of Substance
of the Proposed Rule Change

    Nasdaq proposes to clarify that the requirement that all issuers be
eligible to participate in the Direct Registration Program (``DRS'')
also applies to issuers that are limited partnerships. The text of the
proposed rule change is below.\2\
---------------------------------------------------------------------------

    \2\ Changes are to the rule text that appears in the electronic
manual of Nasdaq found at http://www.complinet.com/nasdaq.

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

4360. Qualitative Listing Requirements for Nasdaq Issuers That Are
Limited Partnerships
    (a)-(i) No Change.
    (j) Each issuer that is a limited partnership must comply with the
requirements to be eligible for a Direct Registration Program, as
described in Rule 4350(l).
* * * * *

II. Self-Regulatory Organization's Statement of the Purpose of, and
Statutory Basis for, the Proposed Rule Change

    In its filing with the Commission, Nasdaq included statements
concerning the purpose of and basis for the proposed rule change and
discussed any comments it received on the proposed rule change. The
text of these statements may be examined at the places specified in
Item IV below. Nasdaq has prepared summaries, set forth in sections
(A), (B), and (C) below, of the most significant aspects of these
statements.\3\
---------------------------------------------------------------------------

    \3\ The Commission has modified the text of the summaries
prepared by the Nasdaq.
---------------------------------------------------------------------------

A. Self-Regulatory Organization's Statement of the Purpose of, and
Statutory Basis for, the Proposed Rule Change

1. Purpose
    In August 2006, the Commission approved changes to Nasdaq Rule
4350(l) to require that Nasdaq-listed securities be eligible to
participate in a direct registration program.\4\ This requirement is
currently applicable to newly listing companies and on January 1, 2008,
will be fully implemented when all Nasdaq-listed securities will be
required to be eligible. In proposing this requirement, Nasdaq intended
that the requirement apply to all listed securities except non-equity
securities which are book-entry-only.\5\ However, Rule 4350 does not
apply to Nasdaq issuers that are limited partnerships. This filing
addresses that oversight by adopting in Rule 4360, which does apply to
limited partnerships, the requirement that each issuer be eligible for
DRS, as described in Rule 4350(l).
---------------------------------------------------------------------------

    \4\ Securities Exchange Act Release No. 54288 (August 8, 2007),
71 FR 47276 (August 16, 2007) [File No. SR-NASDAQ-2006-008] (order
approving listing standards requiring DRS eligibility) (``Approval
Order'').
    \5\ The Approval Order states, ``In order to reduce the number
of transactions in securities for which settlement is effected by
the physical delivery of securities certificates and thereby reduce
the risks, costs, and delays associated with the physical delivery
of securities certificates, Nasdaq is proposing to add new Section
(l) to its rule 4350 to require that all listed securities be
eligible to participate in DRS.''
---------------------------------------------------------------------------

2. Statutory Basis
    Nasdaq believes that the proposed rule change is consistent with
the requirements of Section 6 of the Act \6\ in general and
particularly with Section 6(b)(5) of the Act \7\ in that it is designed
to promote just and equitable principles of trade, to foster
cooperation and coordination with persons engaged in regulating,
clearing, settling, processing information with respect to, and
facilitating transaction in securities, to remove impediments to and
perfect the mechanism of a free and open market and a national market
system, and, in general, to protect investors and the public interest
and is not designed to permit unfair discrimination between customers,
issuers, brokers, or dealers. Nasdaq believes that requiring securities
to be eligible to use DRS will make it easier to trade securities in
book-entry form, which will facilitate the settlement of securities
transactions.
---------------------------------------------------------------------------

    \6\ 15 U.S.C. 78o-3.
    \7\ 15 U.S.C. 78o-3(b)(6).
---------------------------------------------------------------------------

B. Self-Regulatory Organization's Statement on Burden on Competition

    Nasdaq does not believe that the proposed rule change will impose
any burden on competition that is not necessary or appropriate in
furtherance of the purposes of the Act.

C. Self-Regulatory Organization's Statement on Comments on the Proposed
Rule Change Received From Members, Participants, or Others

    No written comments relating to the proposed rule change have been
solicited or received. Nasdaq will notify the Commission of any written
comments received by Nasdaq.

III. Date of Effectiveness of the Proposed Rule Change and Timing for
Commission Action

    The foregoing rule change has become effective upon filing pursuant
to Section 19(b)(3)(A)(iii) of the Act \8\ and Rule 19b-4(f)(6) \9\
thereunder in that it (1) does not significantly affect the protection
of investors or the public interest; (ii) does not impose any
significant burden on competition; (iii) by its terms, does not become
operative for 30 days after the date of the filing. As such, this
proposed rule change is effective upon the Commission's receipt of this
filing pursuant to Section 19(b)(3) and rule 19b-4(f)(6) thereunder. At
any time within sixty days of the filing of such rule change, the
Commission may summarily abrogate such rule change if it appears to the
Commission that such action is necessary or appropriate in the public
interest, for the protection of investors, or otherwise in furtherance
of the purposes of the Act.
---------------------------------------------------------------------------

    \8\ 15 U.S.C. 78s(b)(3)(A)(iii).
    \9\ 17 CFR 240.19b-4(f)(6).
---------------------------------------------------------------------------

IV. Solicitation of Comments

    Interested persons are invited to submit written data, views, and
arguments concerning the foregoing, including whether the proposed rule
change is consistent with the Act. Comments may be submitted by any of
the following methods:

Electronic Comments

     Use the Commission's Internet comment form (http://www.sec.gov/rules/sro.shtml.
) or     Send an e-mail to<EMAIL_ADDRESS>Please include

File Number SR-NASDAQ-2007-066 on the subject line.

Paper Comments

     Send paper comments in triplicate to Nancy M. Morris,
Secretary, Securities and Exchange Commission, 100 F Street, NE.,
Washington, DC 20549-1090.
    All submissions should refer to File Number SR-Nasdaq-2007-066.
This file number should be included on the subject line if e-mail is
used. To help the Commission process and review your comments more
efficiently, please use only one method. The Commission will post all
comments on the Commission's Internet Web site (http://www.sec.gov/rules/sro.shtml
). Copies of the submission, all subsequent amendments,

all written statements with respect to the proposed rule change that
are filed with the Commission, and all written communications relating
to the proposed rule change between the Commission and any person,
other than those that may be withheld from the public in accordance
with the provisions of 5 U.S.C. 552, will be available for inspection
and copying in the Commission's Public Reference Room, 100 F Street,
NE., Washington, DC 20549, on official business days between the hours
of 10 a.m. and 3 p.m. Copies of such filings also will be available for
inspection and copying at the principal office of Nasdaq and on
Nasdaq's Web site, http://www.complinet.com/nasdaq. All comments

received will be posted without change; the Commission does not edit
personal identifying information from submissions. You should submit
only information that you wish to make available publicly. All
submissions should refer to File Number SR-NASDAQ-2007-066 and should
be submitted on or before December 26, 2007.

    For the Commission by the Division of Trading and Markets,
pursuant to delegated authority.\10\
---------------------------------------------------------------------------

    \10\ 17 CFR 200.30-3(a)(12).
---------------------------------------------------------------------------

Nancy M. Morris,
Secretary.
[FR Doc. E7-23397 Filed 12-3-07; 8:45 am]

BILLING CODE 8011-01-P


[Federal Register Volume 81, Number 12 (Wednesday, January 20, 2016)]
[Proposed Rules]
[Pages 3045-3051]
[FR Doc No: 2016-00634]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 95-21-09,
for all Airbus Model A300 series airplanes, and Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes). AD 95-21-09 currently requires repetitive inspections for
cracking of the No. 2 flap beams, and replacement of the flap beams, if
necessary; and provides optional modifications for extending certain
inspection thresholds, and an optional terminating modification for
certain inspections. Since we issued AD 95-21-09, we have determined
that the compliance times must be reduced. This proposed AD would
reduce the compliance times for inspections and also reduce the number
of airplanes affected. We are proposing this AD to detect and correct
cracking of the No. 2 flap beams, which could result in rupture of the
flap beams and reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by March 7, 2016.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 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_ADDRESS>Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8470; 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-8470;
Directorate Identifier 2013-NM-199-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    On October 3, 1995, we issued AD 95-21-09, Amendment 39-9395 (60 FR
53847, October 18, 1995). AD 95-21-09 requires actions intended to
address an unsafe condition on Airbus Model A300 and A300-600 series
airplanes.
    Since we issued AD 95-21-09, Amendment 39-9395 (60 FR 53847,
October 18, 1995), we have received a report that analyses showed a
need for reduced compliance times.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2013-0234R2, dated October 7, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A300 and A300-600
series airplanes. The MCAI states:

    Fatigue and ``fail safe'' tests developed on a test specimen
confirmed that cracks may appear and propagate from the bolt holes
of the base member and the side members of flap beam No. 2.
    The development of such cracks, if not detected, could result in
a rupture of flap beams No. 2, which could adversely affect the
structural integrity of the airframe.
    To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A300-57-0116 and SB A300-57-6005 and DGAC
France issued AD 1986-187-076(B) [available at http://ad.easa.europa.eu/blob/1986-187-076%28B%29R4en.pdf/AD_F-1986-187-076R4_1], later revised, to require a repetitive inspection
programme [and corrective action] for A300 and A300-600 aeroplanes.
[French AD 86-187-076(B)R3, dated March 2, 1994, corresponds to FAA
AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995),
which superseded FAA AD 85-07-04, Amendment 39-5027 (49 FR 45755,
April 2, 1985).]
    For A300 aeroplanes, and in the frame of the Extended Service
Goal (ESG) exercise, it was shown that design changes (Airbus Mod.
4740/Airbus SB A300-57-0128 or Airbus Mod. 5815/Airbus SB A300-57-
0141) were not sufficient to enable full ESG life without
inspections.
    For A300-600 aeroplanes, since DGAC France AD 1986-187-076(B)
was issued, a fleet survey and updated Fatigue and Damage Tolerance
analyses have been performed in order to substantiate the second
A300-600 ESG2 exercise. Airbus SB A300-57-6005 has been revised
accordingly to decrease the inspection thresholds and intervals.
    For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 1986-187-076(B)R4, which is
superseded, and requires those inspections to be accomplished at
reduced thresholds and intervals.
    This [EASA] AD has been revised to correct typographical errors
in some compliance times defined in Appendix 1, Tables 1 and 2.

    The MCAI also reduces the number of airplanes identified in the
applicability by exempting certain Model A300-600 airplanes on which
certain Airbus modifications have been embodied. 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-2015-8470.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A300-57-0116, Revision 07,
dated September 19, 2011; and A300-57-6005, Revision 06, dated November
14, 2013. This service information describes procedures for ultrasonic
inspections of the number 2 flap beam base and side members. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI. 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.

Differences Between This Proposed AD and the MCAI or Service
Information

    Although the MCAI or service information allows further flight
after cracks are found during compliance with the required action,
paragraph (m) of this proposed AD requires that you replace the flap
beam before further flight.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the
Airworthiness

Directive Implementation Aviation Rulemaking Committee (ARC), to
enhance the AD system. One enhancement was a new process for annotating
which procedures and tests in the service information are required for
compliance with an AD. Differentiating these procedures and tests from
other tasks in the service information is expected to improve an
owner's/operator's understanding of crucial AD requirements and help
provide consistent judgment in AD compliance. The procedures and tests
identified as Required for Compliance (RC) in any service information
have a direct effect on detecting, preventing, resolving, or
eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests that are identified
as RC in any service information must be done to comply with the
proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 49 airplanes of U.S.
registry.
    The actions that are required by AD 95-21-09, Amendment 39-9395 (60
FR 53847, October 18, 1995), and retained in this proposed AD take
about 6 work-hours per product, at an average labor rate of $85 per
work-hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the actions that were required by AD 95-
21-09 is $510 per product, per inspection cycle.
    We also estimate that it would take about 6 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $24,990 per
inspection cycle, or $510 per product, per inspection cycle.
    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.

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 removing Airworthiness Directive (AD)
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and adding
the following new AD:

Airbus: Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-
199-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847,
October 18, 1995).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category.
    (1) Model Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C,
B4-103, and B4-203 airplanes, all manufacturer serial numbers
(MSNs).
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
and B4-622R airplanes, all MSNs.
    (3) Airbus Model A300 F4-605R, all MSNs, except those airplanes
on which both Airbus Modifications 11133 and 12699 have been
embodied.
    (4) Airbus Model A300 F4-622R airplanes, all MSNs, except those
airplanes on which all Airbus Modifications 11133, 12047, 12048, and
12050 have been embodied, and except those airplanes on which both
Airbus Modifications 11133 and 12699 have been embodied.
    (5) Airbus Model A300 C4-605R Variant F airplanes, all MSNs.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the compliance
times must be reduced. We are issuing this AD to detect and correct
cracking of the No. 2 flap beams, which could result in rupture of
the flap beams and reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Inspection and Corrective Actions for Model A300 Series
Airplanes, With Note 3 of AD 95-21-09, Amendment 39-9395 (60 FR 53847,
October 18, 1995), Incorporated and Additional Terminating Provisions

    This paragraph restates the requirements of paragraph (a) of AD
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with
Note 3 of AD 95-21-09 incorporated and additional terminating
provisions. For Model A300 series airplanes: Prior to the
accumulation of 15,000 total landings, or within the next 120 days
after May 9, 1985 (the effective date of AD 85-07-04, Amendment 39-
5027 (49 FR 45755, April 2,

1985)), whichever occurs later, inspect for cracking of the base
steel member and light alloy side members of the No. 2 flap beams,
left hand and right hand, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-116, Revision 6,
dated July 16, 1993. Accomplishing the requirements of paragraph (h)
or (l) of this AD terminates the requirements of this paragraph.
Measurement of crack length is performed by measurement of the probe
displacement (perpendicular to symmetry plane of beam) between
defect indication appearance and its complete disappearance. The
bolt hole indication should not be interpreted as an indication of a
defect. These two indications appear very close together because the
defects originate from the bolt holes.
    (1) If no cracking is detected: Except as provided by paragraph
(i) of this AD, repeat the inspection at intervals not to exceed
1,700 landings until the requirements of paragraph (h) or (l) of
this AD are accomplished.
    (2) If any crack is detected that is less than or equal to 4 mm:
Repeat the inspection at intervals not to exceed 250 landings, until
the requirements of paragraph (h) or (l) of this AD are
accomplished.
    (3) If any crack is detected that exceeds 4 mm: Prior to further
flight, replace the flap beam in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-116, Revision 6,
dated July 16, 1993, and prior to the accumulation of 15,000 flight
cycles on the replaced flap beam, perform the ultrasonic inspection
as required by paragraph (h) or (l) of this AD.

(h) Retained Ultrasonic Inspection and Corrective Action for Model A300
Series Airplanes, With Additional Terminating Provisions

    This paragraph restates the requirements of paragraph (b) of AD
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with
additional terminating provisions. For Model A300 series airplanes:
Prior to the accumulation of 15,000 total landings, or within the
next 1,000 landings after November 17, 1995 (the effective date of
AD 95-21-09), whichever occurs later, perform an ultrasonic
inspection to detect cracking of the No. 2 flap beams, in accordance
with Airbus Service Bulletin A300-57-116, Revision 6, dated July 16,
1993. Accomplishment of this inspection terminates the inspections
required by paragraph (g) of this AD. Accomplishment of the
requirements of paragraph (l) of this AD terminates the requirements
of this paragraph.
    (1) If no cracking is detected: Except as provided by paragraph
(i) of this AD, repeat the ultrasonic inspections thereafter at
intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole, and that
crack is less than or equal to 4 mm in length: Repeat the ultrasonic
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack
is greater than 4 mm in length: Prior to further flight, replace the
flap beam in accordance with Airbus Service Bulletin A300-57-116,
Revision 6, dated July 16, 1993, and prior to the accumulation of
15,000 flight cycles on the replaced flap beam, perform the
ultrasonic inspection as required by this paragraph.

(i) Retained Modification of the No. 2 Track Beam for Model A300 Series
Airplanes, With Changes to Compliance Extension

    This paragraph restates the provisions of paragraph (c) of AD
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with
changes to compliance extension. For Model A300 series airplanes:
After accomplishing the initial inspection required by paragraph (h)
of this AD, accomplishment of either paragraph (i)(1) or (i)(2) of
this AD before the effective date of this AD extends the fatigue
life of the No. 2 flap track beam as specified in those paragraphs,
provided that no cracking is detected during any inspection required
by paragraph (g) or (h) of this AD.
    (1) Removal of any damage and the installation of larger
diameter bolts on the No. 2 flap track beam (Modification No. 4740),
in accordance with Airbus Service Bulletin A300-57-128, Revision 3,
dated January 26, 1990, extends the interval for the first
repetitive inspection required by paragraph (h) of this AD from
1,700 landings to 12,000 landings, provided that Modification No.
4740 is accomplished prior to the accumulation of 16,700 total
landings on the flap beams. Following accomplishment of the first
repetitive inspection, subsequent repetitive inspections shall be
performed at intervals not to exceed 1,700 landings. Or
    (2) Cold working of the bolt holes and the installation of
larger diameter bolts on the No. 2 flap track beam (Modification No.
5815), in accordance with Airbus Service Bulletin A300-57-141,
Revision 7, dated July 16, 1993, extends the interval for the first
repetitive inspection required by paragraph (h) of this AD from
1,700 landings to the interval specified in paragraph (i)(2)(i) or
(i)(2)(ii) of this AD.
    (i) If interference fit bolts that are 15/32-inch in diameter
are fitted, the interval for the first repetitive inspection
required by paragraph (h) of this AD is extended to 22,000 landings,
provided that Modification 5815 is accomplished prior to the
accumulation of 16,700 total landings on the flap beam. Following
accomplishment of the first repetitive inspection required by
paragraph (h) of this AD, subsequent repetitive inspections shall be
performed at intervals not to exceed 1,700 landings. Or
    (ii) If interference fit bolts that are 7/16- or 3/8-inch in
diameter are fitted, the interval for the first repetitive
inspection required by paragraph (h) of this AD is extended to
33,000 landings, provided that Modification 5815 is accomplished
prior to the accumulation of 16,700 total landings on the flap beam.
Following accomplishment of the first repetitive inspection required
by paragraph (h) of this AD, subsequent repetitive inspections shall
be performed at intervals not to exceed 1,700 landings.

(j) Retained Ultrasonic Inspection and Corrective Actions for Model
A300-600 Series Airplanes, With Terminating Provisions

    This paragraph restates the requirements of paragraph (d) of AD
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with
terminating provisions. For Model A300-600 series airplanes: Prior
to the accumulation of 15,000 total landings, or within the next
1,000 landings after November 17, 1995 (the effective date of AD 95-
21-09), whichever occurs later, perform an ultrasonic inspection to
detect cracking of the No. 2 flap track beams, in accordance with
Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16,
1993. Accomplishing the actions required by paragraph (l) of this AD
terminates the requirements of this paragraph.
    (1) If no cracking is detected, repeat the ultrasonic
inspections thereafter at intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole and that crack
is less than or equal to 4 mm in length: Repeat the ultrasonic
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack
is greater than 4 mm in length: Prior to further flight, replace the
flap beam in accordance with Airbus Service Bulletin A300-57-6005,
Revision 2, dated December 16, 1993, and prior to the accumulation
of 15,000 landings on the replaced flap beam, perform the ultrasonic
inspection required by paragraph (j) of this AD.

(k) Retained Optional Action With Note 5 of AD 95-21-09 Amendment 39-
9395 (60 FR 53847, October 18, 1995), Incorporated and Changes to
Terminating Action

    This paragraph restates the provisions of paragraph (e) of AD
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with
Note 5 of AD 95-21-09 incorporated and changes to terminating
action. For Model A300-600 series airplanes: Installation of
oversized transition fit bolts in cold-worked holes, in accordance
with Airbus Service Bulletin A300-57-6006 (Modification 5815),
Revision 4, dated July 25, 1994, constitutes terminating action for
the repetitive inspection requirements of paragraph (j) of this AD,
provided that no cracking is detected during any inspection required
by paragraph (j) of this AD, and provided that the installation is
accomplished prior to the accumulation of 15,000 total landings and
before the effective date of this AD. If any bolt requires
oversizing above 7/16-inch diameter during accomplishment of this
installation, prior to further flight, repair using a method
approved by the Manager, Standardization Branch, ANM-113, FAA,
Transport Airplane Directorate, or by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA. As of the
effective date of this AD, any new repair approval must be done
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin
A300-57-6005, Revision 2, dated December 16, 1993, is accomplished
concurrently with

Airbus Service Bulletin A300-57-6006, Revision 3, dated December 16,
1993 (Modification 5815), the ultrasonic inspection for cracking
required by paragraph (j) of this AD need not be performed since the
eddy current inspection detailed for Modification 5815 is more
comprehensive.

(l) New Requirement of This AD: Initial and Repetitive Ultrasonic
Inspections

    At the applicable time specified in paragraph (l)(1) or (l)(2)
of this AD and, thereafter at intervals not to exceed those defined
in table 3 to paragraph (l) of this AD, as applicable, accomplish an
ultrasonic inspection for cracking of the steel base member and the
aluminum side members' flap beam on the left-hand (LH) and right-
hand (RH) sides in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-57-0116, Revision 07, dated
September 19, 2011, including Appendixes A and B, undated; or Airbus
Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013;
as applicable. For the purposes of this AD, average flight time
(AFT) is considered to be the number of flight hours per flight
cycle. Doing the actions required by this paragraph terminates the
requirements of paragraphs (g) through (k) of this AD.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes (referred to as Model A300 series airplanes):
Within the applicable compliance time defined in table 1 to
paragraph (l) of this AD.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, F4-622R airplanes, and Model A300 C4-605R
Variant F airplanes (referred to as Model A300-600 series
airplanes): At the later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within the compliance time defined in table 2 to paragraph
(l) of this AD.
    (ii) Within 300 flight cycles or 640 flight hours after the
effective date of this AD, whichever occurs first.

  Table 1 to Paragraph (l) of This AD--Inspection Compliance Times for
                       Model A300 Series Airplanes
------------------------------------------------------------------------
                                                       Compliance times
                                   Compliance times   for airplanes with
     Airplane configuration       for airplanes with    an AFT of more
                                    an AFT of less     than or equal to
                                       than 1.5               1.5
------------------------------------------------------------------------
Model A300 B2-1A, B2-1C, B2K-3C,  Within 15,000       Within 15,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modifications 4740 and     16,900 flight       16,900 flight
 5815 have not been embodied.      hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B4-103 airplanes on    Within 15,000       Within 15,000
 which Airbus Modifications 4740   flight cycles or    flight cycles or
 and 5815 have not been embodied.  20,500 flight       20,500 flight
                                   hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B4-2C, and B4-203      Within 16,200       Within 15,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modifications 4740 and 5815       22,200 flight       34,000 flight
 have not been embodied.           hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 12,000       Within 12,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 4740 has      13,500 flight       13,500 flight
 been embodied.                    hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 12,000       Within 12,000
 which Airbus Modification 4740    flight cycles or    flight cycles or
 has been embodied.                16,400 flight       16,400 flight
                                   hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203      Within 12,900       Within 12,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 4740 has been        17,700 flight       27,200 flight
 embodied.                         hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 33,000       Within 33,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 5815 has      37,200 flight       37,200 flight
 been embodied and no bolt         hours since         hours since
 larger than 7/16-inch diameter    embodiment of       embodiment of
 is fitted.                        Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 33,000       Within 33,000
 which Airbus Modification 5815    flight cycles or    flight cycles or
 has been embodied and no bolt     45,200 flight       45,200 flight
 larger than 7/16-inch diameter    hours since         hours since
 is fitted.                        embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203      Within 35,600       Within 33,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 5815 has been        48,800 flight       74,900 flight
 embodied and no bolt larger       hours since         hours since
 than 7/16-inch diameter is        embodiment of       embodiment of
 fitted.                           Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 22,000       Within 22,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 5815 has      24,800 flight       24,800 flight
 been embodied and at least one    hours since         hours since
 bolt with a 15/32[dash]inch       embodiment of       embodiment of
 diameter is fitted.               Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 22,000       Within 22,000
 which Airbus Modification 5815    flight cycles or    flight cycles or
 has been embodied and at least    30,100 flight       30,100 flight
 one bolt with a 15/32[dash]inch   hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203,     Within 23,700       Within 22,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 5815 has been        32,500 flight       49,900 flight
 embodied and at least one bolt    hours since         hours since
 with a 15/32-inch diameter is     embodiment of       embodiment of
 fitted.                           Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
------------------------------------------------------------------------

Table 2 to Paragraph (l) of This AD--Compliance Times for Model A300-600
                            Series Airplanes
------------------------------------------------------------------------
                                                       Compliance times
                                   Compliance times   for airplanes with
     Airplane configuration       for airplanes with    an AFT of more
                                    an AFT of less     than or equal to
                                       than 1.5               1.5
------------------------------------------------------------------------
Model A300-600 series airplanes   Within 16,200       Within 15,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 and Airbus Modification      24,300 flight       32,400 flight
 11133 have not been embodied.     hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.

Model A300-600 series airplanes   Within 35,600       Within 33,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 has been embodied and no     53,400 flight       71,200 flight
 bolt larger than 7/16-inch        hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300-600 series airplanes   Within 23,700       Within 22,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 has been embodied and at     35,600 flight       47,500 flight
 least one bolt 15/32-inch         hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300-600 series airplanes   Within 35,600       Within 33,000
 on which Airbus Modification      flight cycles or    flight cycles or
 11133 has been embodied.          53,400 flight       71,200 flight
                                   hours since first   hours since first
                                   flight, whichever   flight, whichever
                                   occurs first.       occurs first.
------------------------------------------------------------------------

  Table 3 to Paragraph (l) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                      Repetitive          Repetitive
                                   interval (not to    interval (not to
                                      exceed) for         exceed) for
         Airplane models           airplanes with an   airplanes with an
                                   AFT of less than     AFT equal to or
                                          1.5            more than 1.5
------------------------------------------------------------------------
A300 B2-1A, B2-1C, B2K-3C, B2-    1,500 flight        1,500 flight
 203.                              cycles or 1,600     cycles or 1,600
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300B4-103 airplanes............  1,500 flight        1,500 flight
                                   cycles or 2,000     cycles or 2,000
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300 B4-2C, and B4-203..........  1,600 flight        1,500 flight
                                   cycles or 2,200     cycles or 3,400
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300-600 series airplanes.......  1,600 flight        1,500 flight
                                   cycles or 2,400     cycles or 3,200
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
------------------------------------------------------------------------

(m) New Requirement of This AD: Corrective Action

    If any crack is found during any inspection required by
paragraph (l) of this AD: Before further flight, replace the flap
beam using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus's EASA Design Organization
Approval (DOA). Replacement of the flap beam does not constitute
terminating action for the inspections required by paragraph (l) of
this AD.

(n) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by
paragraph (g) of this AD, if those inspections were performed before
November 17, 1995 (the effective date of AD 95-21-09, Amendment 39-
9395 (60 FR 53847, October 18, 1995)) using Airbus Service Bulletin
A300-57-116, Revision 1, dated August 27, 1983; Revision 2, dated
April 24, 1984; Revision 3, dated July 20, 1984; Revision 4, dated
August 13, 1986; or Revision 5, dated July 10, 1989; as applicable.
    (2) This paragraph provides credit for actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using the applicable service information
identified in paragraphs (n)(2)(i) through (n)(2)(x) of this AD.
    (i) Airbus Service Bulletin A300-57-6005, Revision 03, dated
November 25, 1997, which was not previously incorporated by
reference.
    (ii) Airbus Service Bulletin A300-57-6005, Revision 04, dated
October 25, 1999, which was not previously incorporated by
reference.
    (iii) Airbus Service Bulletin A300-57-6005, Revision 05, dated
April 25, 2013, which was not previously incorporated by reference.
    (iv) Airbus Service Bulletin A300-57-6005, Revision 2, dated
December 16, 1993, which was previously incorporated by reference on
November 17 1995 (60 FR 53847, October 18, 1995).
    (v) Airbus Service Bulletin A300-57-116, Revision 1, dated
August 27, 1983, which was not previously incorporated by reference.
    (vi) Airbus Service Bulletin A300-57-116, Revision 2, dated
April 24, 1984, which was not previously incorporated by reference.
    (vii) Airbus Service Bulletin A300-57-116, Revision 3, dated
July 20, 1984, which was not previously incorporated by reference.
    (viii) Airbus Service Bulletin A300-57-116, Revision 4, dated
August 13, 1986, which was not previously incorporated by reference.
    (ix) Airbus Service Bulletin A300-57-116, Revision 5, dated July
10, 1989, which was not previously incorporated by reference.
    (x) Airbus Service Bulletin A300-57-116, Revision 6, dated July
16, 1993, which was previously incorporated by reference on November
17, 1995 (60 FR 53847, October 18, 1995).

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>    (i) 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. The AMOC approval letter must specifically
reference this AD.
    (ii) AMOCs approved previously for AD 95-21-09, Amendment 39-
9395 (60 FR 53847, October 18, 1995), are approved as AMOCs for the
corresponding provisions of paragraphs (g) through (j) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (m) of this AD: 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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2013-0234R2, dated October 7, 2013, 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-2015-8470.
    (2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 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_ADDRESS>
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on January 6. 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-00634 Filed 1-19-16; 8:45 am]
BILLING CODE 4910-13-P