[Federal Register Volume 88, Number 89 (Tuesday, May 9, 2023)]
[Notices]
[Pages 29926-29927]
[FR Doc No: 2023-09790]

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

DEPARTMENT OF HOMELAND SECURITY

Federal Emergency Management Agency

[Docket ID FEMA-2023-0002]

Final Flood Hazard Determinations

AGENCY: Federal Emergency Management Agency, Department of Homeland
Security.

ACTION: Notice.

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

SUMMARY: Flood hazard determinations, which may include additions or
modifications of Base Flood Elevations (BFEs), base flood depths,
Special Flood Hazard Area (SFHA) boundaries or zone designations, or
regulatory floodways on the Flood Insurance Rate Maps (FIRMs) and where
applicable, in the supporting Flood Insurance Study (FIS) reports have
been made final for the communities listed in the table below. The FIRM
and FIS report are the basis of the floodplain management measures that
a community is required either to adopt or to show evidence of having
in effect in order to qualify or remain qualified for participation in
the Federal Emergency Management Agency's (FEMA's) National Flood
Insurance Program (NFIP).

DATES: The date of September 21, 2023 has been established for the FIRM
and, where applicable, the supporting FIS report showing the new or
modified flood hazard information for each community.

ADDRESSES: The FIRM, and if applicable, the FIS report containing the
final flood hazard information for each community is available for
inspection at the respective Community Map Repository address listed in
the tables below and will be available online through the FEMA Map
Service Center at https://msc.fema.gov by the date indicated above.

FOR FURTHER INFORMATION CONTACT: Rick Sacbibit, Chief, Engineering
Services Branch, Federal Insurance and Mitigation Administration, FEMA,
400 C Street SW, Washington, DC 20472,<PHONE_NUMBER>, or (email)
[email protected]; or visit the FEMA Mapping and Insurance
eXchange (FMIX) online at https://www.floodmaps.fema.gov/fhm/fmx_main.html.

SUPPLEMENTARY INFORMATION: The Federal Emergency Management Agency
(FEMA) makes the final determinations listed below for the new or
modified flood hazard information for each community listed.
Notification of these changes has been published in newspapers of local
circulation and 90 days have elapsed since that publication. The Deputy
Associate Administrator for Insurance and Mitigation has resolved any
appeals resulting from this notification.
    This final notice is issued in accordance with section 110 of the
Flood Disaster Protection Act of 1973, 42 U.S.C. 4104, and 44 CFR part
67. FEMA has developed criteria for floodplain management in floodprone
areas in accordance with 44 CFR part 60.

    Interested lessees and owners of real property are encouraged to
review the new or revised FIRM and FIS report available at the address
cited below for each community or online through the FEMA Map Service
Center at https://msc.fema.gov.
    The flood hazard determinations are made final in the watersheds
and/or communities listed in the table below.

(Catalog of Federal Domestic Assistance No. 97.022, ``Flood
Insurance.'')

Nicholas A. Shufro,
Deputy Assistant Administrator for Risk Management, Federal Emergency
Management Agency, Department of Homeland Security.

------------------------------------------------------------------------
                                             Community map repository
               Community                             address
------------------------------------------------------------------------
               Benton County, Iowa and Incorporated Areas
                   Docket No.: FEMA-B-2126 and B-2261
------------------------------------------------------------------------
City of Vinton.........................  City Hall, 110 West 3rd Street,
                                          Vinton, IA 52349.
Unincorporated Areas of Benton County..  Benton County Courthouse, 111
                                          East 4th Street, Vinton, IA
                                          52349.
------------------------------------------------------------------------
            Olmsted County, Minnesota and Incorporated Areas
                         Docket No.: FEMA-B-2135
------------------------------------------------------------------------
Unincorporated Areas of Olmsted County.  Olmsted County Planning, Land
                                          Use, and Zoning Department,
                                          2122 Campus Drive SE, Suite
                                          100, Rochester, MN 55904.
------------------------------------------------------------------------
           Steele County, North Dakota and Incorporated Areas
                         Docket No.: FEMA-B-2240
------------------------------------------------------------------------
City of Finley.........................  City Hall, 208 4th Street West,
                                          Finley, ND 58230.
City of Hope...........................  City Hall, 107 Steele Avenue,
                                          Hope, ND 58046.
City of Sharon.........................  Steele County Courthouse, 201
                                          Washington Avenue West,
                                          Finley, ND 58230.
Unincorporated Areas of Steele County..  Steele County Courthouse, 201
                                          Washington Avenue West,
                                          Finley, ND 58230.
------------------------------------------------------------------------
                Union County, Ohio and Incorporated Areas
                         Docket No.: FEMA-B-2248
------------------------------------------------------------------------
City of Marysville.....................  City Hall, 209 South Main
                                          Street, Marysville, OH 43040.
Unincorporated Areas of Union County...  Union County Office Building,
                                          233 West 6th Street,
                                          Marysville, OH 43040.
Village of Richwood....................  Municipal Building, 153 North
                                          Franklin Street, Richwood, OH
                                          43344.
------------------------------------------------------------------------
              Johnson County, Texas and Incorporated Areas
                         Docket No.: FEMA-B-2200
------------------------------------------------------------------------
City of Cleburne.......................  City Hall, 10 North Robinson
                                          Street, Cleburne, TX 76031.
City of Mansfield......................  City Hall, 1200 East Broad
                                          Street, Mansfield, TX 76063.
City of Venus..........................  City Hall, 700 West US Highway
                                          67, Venus, TX 76084.
Unincorporated Areas of Johnson County.  Johnson County Public Works
                                          Department, 2 North Mill
                                          Street, Suite 305, Cleburne,
                                          TX 76033.
------------------------------------------------------------------------
             Somervell County, Texas and Incorporated Areas
                 Docket No.: FEMA-B-2057 and FEMA-B-2207
------------------------------------------------------------------------
City of Glen Rose......................  City Hall, Planning and
                                          Building Department, 201
                                          Northeast Vernon Street, Glen
                                          Rose, TX 76043.
Unincorporated Areas of Somervell        Somervell County Offices
 County.                                  Building, 107 Northeast Vernon
                                          Street, Glen Rose, TX 76043.
------------------------------------------------------------------------

[FR Doc. 2023-09790 Filed 5-8-23; 8:45 am]
BILLING CODE 9110-12-P


[Federal Register Volume 74, Number 120 (Wednesday, June 24, 2009)]
[Notices]
[Page 30203]
[FR Doc No: E9-14830]

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

DEPARTMENT OF TRANSPORTATION

Federal Railroad Administration

Notice of Application for Approval of Discontinuance or
Modification of a Railroad Signal System or Relief From the
Requirements of Title 49 Code of Federal Regulations Part 236

    Pursuant to Title 49 Code of Federal Regulations (CFR) Part 235 and
49 U.S.C. 20502(a), the following railroad has petitioned the Federal
Railroad Administration (FRA) seeking approval for the discontinuance
or modification of the signal system or relief from the requirements of
49 CFR Part 236, as detailed below.
    Docket Number FRA-2009-0052.
    Applicant: Norfolk Southern Corporation, Mr. Donald D. Graab,
Assistant Vice-President Mechanical, Mechanical Department, 1200
Peachtree Street, NE., Atlanta, Georgia 30309-3579.
    The Norfolk Southern Corporation (NS) seeks relief from the
requirements of the Rules, Standards, and Instructions, 49 CFR Part
236, Sec. Sec.  236.586 and 236.110. NS seeks a waiver from compliance
with Sec.  236.586 Daily or after trip test, in its entirety for
locomotives equipped with UltraCab equipment. NS seeks a waiver from
that portion of Sec.  236.110 that requires record-keeping and record
retention for tests performed under Sec.  236.586.
    The reason given for the proposed changes is that UltraCab
locomotive cab signal equipment is microprocessor-based, and it is
universally recognized that this technology has provided vast
breakthroughs in advanced train stop and train control equipment. These
systems offer improvements far superior to their predecessors in
performance, reliability, and safety. Equipment is now capable of
checking itself several times a second and verifying that the system is
functioning properly and that all external inputs are valid.
    Any interested party desiring to protest the granting of an
application shall set forth specifically the grounds upon which the
protest is made, and include a concise statement of the interest of the
party in the proceeding. Additionally, one copy of the protest shall be
furnished to the applicant at the address listed above.
    FRA expects to be able to determine these matters without an oral
hearing. However, if a specific request for an oral hearing is
accompanied by a showing that the party is unable to adequately present
his or her position by written statements, an application may be set
for public hearing.
    Interested parties are invited to participate in these proceedings
by submitting written views, data, or comments. FRA does not anticipate
scheduling a public hearing in connection with these proceedings since
the facts do not appear to warrant a hearing. If any interested party
desires an opportunity for oral comment, they should notify FRA, in
writing, before the end of the comment period and specify the basis for
their request.
    All communications concerning these proceedings should identify the
appropriate docket number (e.g., Waiver Petition Docket Number FRA-
2009-0052) and may be submitted by any of the following methods:
     Web site: http://www.regulations.gov. Follow the online
instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: Docket Operations Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., W12-140, Washington, DC
20590.
     Hand Delivery: 1200 New Jersey Avenue, SE., Room W12-140,
Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.
    Communications received within 45 days of the date of this notice
will be considered by FRA before final action is taken. Comments
received after that date will be considered as far as practicable. All
written communications concerning these proceedings are available for
examination during regular business hours (9 a.m.-5 p.m.) at the above
facility. All documents in the public docket are also available for
inspection and copying on the Internet at the docket facility's Web
site at http://www.regulations.gov.
    Anyone is able to search the electronic form of any written
communications and comments received into any of our dockets by the
name of the individual submitting the comment (or signing the comment,
if submitted on behalf of an association, business, labor union, etc.).
You may review DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (Volume 65, Number 70; Pages
19477-78).

    Issued in Washington, DC on June 17, 2009.
Grady C. Cothen, Jr.,
Deputy Associate Administrator for Safety Standards and Program
Development.
[FR Doc. E9-14830 Filed 6-23-09; 8:45 am]
BILLING CODE 4910-06-P


[Federal Register Volume 81, Number 208 (Thursday, October 27, 2016)]
[Notices]
[Pages 74798-74799]
[FR Doc No: 2016-25923]

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

ENVIRONMENTAL PROTECTION AGENCY

[EPA-HQ-OAR-2015-0216; FRL-9954-57-OAR]
RIN 2060-ZA22

Release of Final Control Techniques Guidelines for the Oil and
Natural Gas Industry

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice of availability.

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

SUMMARY: The Environmental Protection Agency (EPA) is announcing the
availability of a final document titled, ``Control Techniques
Guidelines for the Oil and Natural Gas Industry'' (EPA 453/B-16-001).
This Control Techniques Guidelines (CTG) document provides state,
local, and tribal air agencies (air agencies) information to assist
them in determining reasonably available control technology (RACT) for
volatile organic compound (VOC) emissions from select oil and natural
gas industry emission sources.

DATES: This CTG document is effective October 27, 2016.

ADDRESSES: The final ``Control Techniques Guidelines for the Oil and
Natural Gas Industry'' document is available primarily via the Internet
at http://www.epa.gov/airquality/oilandgas/index.html or https://www.epa.gov/laws-regulations/significant-guidance-documents-air or the
public docket at http://www.regulations.gov, Docket ID No. EPA-HQ-OAR-
2015-0216.

FOR FURTHER INFORMATION CONTACT: Ms. Charlene Spells, U.S.
Environmental Protection Agency, Office of Air Quality Planning and
Standards, Sector Policies and Programs Division (E143-05), Research
Triangle Park, NC 27711; telephone number:<PHONE_NUMBER>; fax number:
(919) 541-3470; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Information About the Document

    Section 172(c)(1) of the Clean Air Act (CAA) provides that State
Implementation Plans (SIP) for nonattainment areas must include RACT,
including RACT for existing sources of emissions. Section 182(b)(2)(A)
of the CAA requires that for areas designated nonattainment for an
ozone national ambient air quality standard (NAAQS) and classified as
Moderate, states must revise their SIP to include provisions to
implement RACT for each category of VOC sources covered by a CTG
document issued between November 15, 1990, and the date of attainment.
CAA section 182(c) through (e) applies this requirement to states with
areas designated nonattainment for an ozone NAAQS classified as
Serious, Severe, and Extreme.
    The CAA also imposes the same requirement on states in Ozone
Transport Regions (OTR). Specifically, CAA section 184(b) provides that
states in the OTR must revise their SIP to implement RACT with respect
to all sources of VOC in the state covered by a CTG document issued
before or after November 15, 1990. CAA section 184(a) establishes a
single OTR comprised of Connecticut, Delaware, Maine, Maryland,
Massachusetts, New Hampshire, New Jersey, New York, Pennsylvania, Rhode
Island, Vermont, and the Consolidated Metropolitan Statistical Area
(CMSA) that includes the District of Columbia.
    The EPA defines RACT as ``the lowest emission limitation that a
particular source is capable of meeting by the application of control
technology that is reasonably available considering technological and
economic feasibility'' (44 FR 53761, September 17, 1979). In subsequent
notices, the EPA has addressed how states can meet the RACT
requirements of the CAA. The EPA developed this CTG document to provide
air agencies information to assist them in determining what types of

control could constitute RACT for VOC emissions from select oil and
natural gas sources. In developing the final CTG document, the EPA
evaluated the sources of VOC emissions from the oil and natural gas
industry and the available control approaches for addressing these
emissions, including the costs of such approaches. Based on available
information and data, the EPA is providing final recommendations for
RACT for select oil and natural gas industry emission sources. The VOC
RACT recommendations contained in this final CTG document were made
based on a review of the 1983 CTG document on equipment leaks from
natural gas processing plants, the Oil and Natural Gas New Source
Performance Standards, existing state and local VOC emission reduction
approaches, and information on costs, emissions, and available emission
control technologies and in response to comments received on the draft
CTG document released for review on September 18, 2015 (80 FR 56577).
Also, the EPA released for external peer review five technical white
papers on potentially significant sources of emissions in the oil and
natural gas industry. We considered information included in these white
papers, along with the input we received from the peer reviewers and
the public, when evaluating and recommending a RACT level of control
for emission sources. Air agencies can use the recommendations in the
CTG document to inform their determinations as to what constitutes RACT
for VOC for those oil and natural gas industry emission sources in
their particular areas. The information contained in the CTG document
is provided only as guidance. This guidance does not change, or
substitute for, requirements specified in applicable sections of the
CAA or the EPA's regulations; nor is it a regulation itself. The RACT
recommendations, and corresponding model rule language, contained in
the CTG document do not impose any legally binding requirements on any
entity. The CTG document provides only recommendations for air agencies
to consider in determining RACT. Air agencies are free to implement
other technically-sound approaches that are consistent with the CAA and
the EPA's regulations.
    The recommendations contained in the CTG document are based on data
and information currently available to the EPA. These general
recommendations may not apply to a particular situation based on
circumstances not considered in the CTG document. Regardless of whether
an air agency chooses to implement the recommendations contained in
this CTG document, or to issue rules that adopt different approaches
for RACT for VOC from oil and natural gas industry emission sources,
air agencies must submit their RACT provisions to the EPA for review
and approval as part of the SIP submission process. The EPA will
evaluate the submissions and determine, through notice and comment
rulemaking in the SIP review process, whether the submissions meet the
RACT requirements of the CAA and the EPA's regulations. To the extent
an air agency adopts any of the recommendations in this CTG document
into its RACT provisions, interested parties can raise questions and
objections about the appropriateness of the application of this
guidance to a particular situation during the development of the rules
and the EPA's SIP review process. Such questions and objections can
relate to the substance of this guidance.
    Section 182(b)(2) of the CAA provides that a CTG document issued
after November 15, 1990, include the period for submitting SIP
revisions incorporating provisions to require RACT for the category of
VOC sources covered by the CTG document. The EPA is providing a 2-year
period, from the effective date included in this Notice, for the
required SIP submittal.
    The Tribal Authority Rule (63 FR 7254, February 12, 1998) (TAR)
identifies CAA provisions for which it is appropriate to treat Indian
tribes in the same manner as air agencies (TAS). Pursuant to the TAR,
tribes may apply for TAS for purposes of CAA section 110 and Part D
planning requirements in CAA section 182. As a result, tribes may, but
are not required to, apply for TAS for the purpose of developing a
tribal implementation plan (TIP) addressing RACT for sources located in
an area designated nonattainment for an ozone NAAQS with a
classification of Moderate, Serious, Severe or Extreme within the
tribe's jurisdiction. If the EPA grants that status and approves the
TIP, the tribe would implement RACT in the area within the geographic
scope of the TAS designation and the approved TIP. If a tribe does not
seek and obtain the authority from the EPA to establish a plan, the EPA
will be responsible for establishing CAA section 110 and 182 plans for
reservations and trust lands, and any other lands under tribal
jurisdiction, if the EPA determines that such a plan is necessary or
appropriate to protect air quality in such areas. See 40 CFR 49.4 and
49.11.
    A summary of the comments received on the draft CTG document and
responses can be found in the docket at http://www.regulations.gov
(Docket ID No. EPA-HQ-OAR-2015-0216).

    Dated: October 20, 2016.
Gina McCarthy,
Administrator.
[FR Doc. 2016-25923 Filed 10-26-16; 8:45 am]
 BILLING CODE 6560-50-P


[Federal Register: May 22, 2008 (Volume 73, Number 100)]
[Proposed Rules]
[Page 29716-29720]
[DOCID:fr22my08-13]

========================================================================
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.

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29227; Directorate Identifier 2007-NM-100-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-
200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes.
For certain airplanes, the original NPRM would have required a material
type inspection to determine if the lower forward corner reveal of the
number 3 main entry doors (MEDs) is a casting. If the reveals are
castings, the original NPRM would have required repetitive inspections
of the reveals for cracking, and corrective action if necessary. If the
reveals are not castings, the original NPRM would have required a
detailed inspection of the reveals for a sharp edge and repetitive
inspections of the reveals for cracking, and corrective action if
necessary. For certain other airplanes, the original NPRM would have
required only a detailed inspection of the reveals for a sharp edge and
repetitive inspections of the reveals for cracking, and corrective
action if necessary. For certain other airplanes, the original NPRM
would have required repetitive inspections of the reveals for cracking
only, and corrective action if necessary. The original NPRM resulted
from reports of cracking and/or a sharp edge in the lower forward
corner reveal of the number 3 MEDs. This action revises the original
NPRM by reducing the compliance times for doing certain inspections and
allowing a certain replacement as an optional action for the material
type inspection for certain airplanes. We are proposing this
supplemental NPRM to detect and correct fatigue cracking of the lower
forward corner reveal of the number 3 MEDs, which could lead to the
door escape slide departing the airplane when the door is opened and
the slide is deployed, and consequent injuries to passengers and crew
using the door escape slide during an emergency evacuation.

DATES: We must receive comments on this supplemental NPRM by June 16,
2008.

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 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; 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 Office (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 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-2007-
29227; Directorate Identifier 2007-NM-100-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 because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    We issued a notice of proposed rulemaking (NPRM) (the ``original
NPRM'') to amend 14 CFR part 39 to include an airworthiness directive
(AD) that would apply to certain Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
series airplanes. That original NPRM was published in the Federal
Register on September 19, 2007 (72 FR 53498). For certain airplanes,
that original NPRM proposed to require a material type inspection to
determine if the lower forward corner reveal of the number 3 main entry
doors (MEDs) is a casting. If the reveals are castings, that original
NPRM proposed to require repetitive inspections of the reveals for
cracking, and corrective action if necessary. If the reveals are not
castings, that original NPRM proposed to require a detailed inspection
of the reveals for a sharp edge and repetitive inspections of the
reveals for cracking, and corrective action if necessary. For certain
other airplanes, that original NPRM proposed to require only a detailed
inspection of the reveals for a sharp edge and repetitive inspections
of the reveals for cracking, and corrective action if necessary. For
certain other airplanes,

that original NPRM proposed to require repetitive inspections of the
reveals for cracking only, and corrective action if necessary.

Comments

    We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the commenter.

Request To Clarify No Further Action Statement

    Boeing requests that we clarify the statement ``No further action
is required by this paragraph for that location only after the
replacement'' specified in paragraphs (g)(1), (j)(1), (j)(2)(i),
(j)(3)(i), (k)(2)(i), and (k)(2)(ii)(B) of the NPRM. Boeing suggests
that we add the phrase ``with a two-piece reveal'' to the statement.
Boeing states that the referenced service bulletin (Boeing Special
Attention Service Bulletin 747-53-2460, Revision 1, dated February 13,
2007) gives two options for the replacement, with either a one-piece
reveal or a two-piece reveal. Boeing states that only a replacement
with a two-piece reveal terminates the inspections for that location.
    We agree that only replacement with a two-piece reveal would
terminate the inspections for that location. However, we do not agree
that clarification is necessary for all paragraphs. In paragraphs
(j)(2)(i), (j)(3)(i), and (k)(2)(ii)(B) of the supplemental NPRM, we
specify replacing the reveal with a new or reworked two-piece reveal in
accordance with Part 2 of Boeing Special Attention Service Bulletin
747-53-2460, Revision 1. We do not mention installation of a one-piece
reveal as an option in these paragraphs. Part 2 of the service bulletin
describes procedures for installing two-piece reveals. Therefore, in
paragraphs (j)(2)(i), (j)(3)(i), and (k)(2)(ii)(B) of the supplemental
NPRM where we state that no further action is required after the
replacement, the replacement is the two-piece reveal replacement
specified in those paragraphs. No change is necessary for paragraphs
(j)(2)(i), (j)(3)(i), and (k)(2)(ii)(B) of this supplemental NPRM in
regard to this issue.
    Also, for paragraphs (g)(1) and (k)(2)(i) of this supplemental
NPRM, we specify to repeat inspections until a new or re-worked two-
piece reveal is installed. The replacement is the two-piece reveal
installation specified in those paragraphs. No change is necessary for
paragraphs (g)(1) and (k)(2)(i) of this supplemental NPRM in regard to
this issue.
    However, we have revised paragraph (j)(1) of this supplemental NPRM
for clarity as suggested by the commenter.

Request To Allow Optional Action for Material Type Inspection

    Boeing requests that we allow doing a replacement with a new two-
piece reveal as an optional action for the material type inspection
specified in paragraph (k) of the original NPRM. Boeing states that if
an existing reveal is to be reworked to a two-piece reveal, the
material type inspection is necessary; however, if the reveal is
replaced with a new two-piece reveal, a material type inspection is not
necessary. Boeing states if an operator replaces all the reveals with
new two-piece reveals, the original NPRM would still require that the
material type inspection be done.
    We agree to allow replacing the reveal with a new two-piece reveal
as an option for the reasons stated by the commenter. In addition, we
have determined it is acceptable to replace the reveal with a re-worked
reveal as an option to doing the material type inspection; re-worked
reveals are machined from 6061 aluminum. We have revised paragraph (k)
of this supplemental NPRM accordingly.

Request To Reduce Compliance Time in Paragraph (j)(1) of the Original
NPRM

    Boeing requests that we reduce the compliance time ``before the
accumulation of another 10,000 flight cycles on the lower forward
corner reveal'' to `` before the accumulation of 10,000 flight cycles
on the lower forward corner reveal since new (for Group 2 airplanes) or
since replacement (for Group 1 Configuration 2 airplanes).'' Boeing
states that the first inspection should be at 1,500 flight cycles and
then the interval should be 6,000 flight cycles.
    We agree with the commenter that the next repeat inspection after
the initial inspection done in accordance with paragraph (j) of the
supplemental NPRM should be reduced. We intended to match the
compliance times specified in the service bulletin but the compliance
times in the service bulletin are unclear. Figure 16 of the service
bulletin specifies a compliance time of ``10,000 flight cycles after
the reveal was last replaced'' but does not refer to a compliance time
of 10,000 flight cycles on the reveal since new. In addition, the
commenter gives conflicting statements. The commenter's statement that
the interval should be 6,000 flight cycles after the first 1,500 flight
cycle inspection conflicts with its statement that the compliance time
should be revised to state 10,000 flight cycles on the reveal since new
or replaced. We have revised paragraph (j)(1) to reduce the compliance
time as follows: Before the accumulation of 10,000 flight cycles on the
lower forward corner reveal since new, or within 6,000 flight cycles
after doing the inspection required by paragraph (j) of this AD,
whichever occurs later.
    In addition, we have revised paragraphs (g)(2)(ii), (j)(2)(ii),
(j)(3)(ii), and (k)(2)(ii)(C) of the supplemental NPRM to clarify the
10,000-flight-cycle compliance time is on the replacement reveal
instead of since replacement of the reveal.

Request To Revise Reference

    Boeing requests that we revise the reference for doing the detailed
inspection specified in paragraph (j)(1) of the original NPRM. Boeing
states that instead of doing the detailed inspection as specified in
paragraph (j) of the original NPRM, the paragraph should specify doing
the detailed inspection in accordance with Part 5 of the service
bulletin. Boeing notes that paragraph (j) refers to paragraphs (h) and
(i) of the original NPRM for compliance times. Boeing contends that
because paragraphs (h) and (i) include a compliance time of ``before
the accumulation of 1,500 total flight cycles'' operators may interpret
that the inspection interval is 1,500 flight cycles.
    We disagree with the commenter's assertion that the compliance time
interval can be interpreted as 1,500 flight cycles because the
compliance time is specified in paragraph (j)(1) of the supplemental
NPRM and the reference to paragraph (j) of the supplemental NPRM is for
the details of how to do the inspection. However, we have revised
paragraph (j)(1) of the supplemental NPRM for clarity. Although the
commenter suggests pointing to Part 5 of the service bulletin for doing
the inspection, Part 5 of the service bulletin refers to Part 8 of the
service bulletin for doing the inspection. Therefore, we have revised
paragraph (j)(1) of the supplemental NPRM to refer directly to Part 8
of the service bulletin. We have also revised paragraph (j)(1) of the
supplemental NPRM to refer to paragraph (j)(3) of the supplemental NPRM
for doing corrective action if any cracking is found.
    In addition, we have revised paragraphs (g)(2)(ii), (j)(2)(ii),
(j)(3)(ii), and (k)(2)(ii)(C) of the supplemental NPRM to clarify the
references for doing the inspections.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    We are proposing this supplemental NPRM 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.
Certain changes described above expand the scope of the original NPRM.
As a result, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for the public to
comment on this supplemental NPRM.

Costs of Compliance

    There are about 715 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this supplemental NPRM.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Number of U.S.-
            Action               Work hours     Average labor      Cost per        registered       Fleet cost
                                                rate per hour      airplane         airplanes
----------------------------------------------------------------------------------------------------------------
Inspections..................               4             $80  $320, per                    119  $38,080, per
                                                                inspection                        inspection
                                                                cycle.                            cycle.
----------------------------------------------------------------------------------------------------------------

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), and
    3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
    You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Boeing: Docket No. FAA-2007-29227; Directorate Identifier 2007-NM-
100-AD.

Comments Due Date

    (a) We must receive comments by June 16, 2008.

Affected ADs

    (b) Certain requirements of this AD terminate certain
requirements of AD 2007-12-11, amendment 39-15089.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
series airplanes, certificated in any category, as identified in
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1,
dated February 13, 2007, except airplanes that have been converted
to an all-cargo configuration. The requirements of this AD also
become applicable at the time when a converted airplane operating in
an all-cargo configuration is converted back to a passenger or
passenger/cargo configuration.

Unsafe Condition

    (d) This AD results from reports of cracking and/or a sharp edge
in the lower forward corner reveal of the number 3 main entry doors
(MEDs). We are issuing this AD to detect and correct fatigue
cracking of the lower forward corner reveal of the number 3 MEDs,
which could lead to the door escape slide departing the airplane
when the door is opened and the slide is deployed, and consequent
injuries to passengers and crew using the door escape slide during
an emergency evacuation.

Compliance

    (e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.

Actions for Group 3 Airplanes

    (g) For airplanes identified as Group 3 airplanes in the service
bulletin: Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, do a detailed inspection for cracking of the
lower forward corner reveals in accordance with Part 8 of the
service bulletin.
    (1) If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 6,000 flight cycles until a new or reworked
two-piece reveal is installed in accordance with Part 2 of the
service bulletin. No further action is required by this paragraph
for that location only after the replacement.

    Note 1: For the purpose of this AD, a one-piece machined
aluminum reveal may be reworked into a two-piece reveal in
accordance with Part 7 of the service bulletin after it was verified
to be crack free and without a sharp edge in accordance with Part 5
of the service bulletin, or after it was confirmed to be crack free
in accordance with Part 5 of the service bulletin and reworked to
remove a sharp edge in accordance with Part 6 of the service
bulletin.

    (2) If cracking is found, do the replacement specified in
paragraph (g)(2)(i) or (g)(2)(ii) of this AD.

    (i) Before further flight, replace the reveal with a new or
reworked two-piece reveal in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
    (ii) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge in
accordance with Part 3 of the service bulletin. Before the
accumulation of 10,000 flight cycles on the replacement reveal since
new, do the inspection for cracking specified in Part 8 of the
service bulletin and repeat the inspection thereafter at intervals
not to exceed 6,000 flight cycles until a new or reworked two-piece
reveal is installed in accordance with Part 2 of the service
bulletin. If any cracking is found during any inspection required by
this paragraph, before further flight, do the action specified in
paragraph (g)(2) of this AD. No further action is required by this
paragraph for that location only after the replacement with a two-
piece reveal.

    Note 2: For the purpose of this AD, a one-piece machined
aluminum reveal with a sharp edge may be reworked into a one-piece
machined aluminum reveal without a sharp edge in accordance with
Part 6 of the service bulletin after it is confirmed to be crack
free in accordance with Part 5 of the service bulletin. After the
sharp edge is removed, the one-piece machined aluminum reveal
without a sharp edge may be further reworked into a two-piece reveal
in accordance with Part 7 of the service bulletin.

Actions for Group 2 Airplanes and Group 1, Configuration 2 Airplanes

    (h) For airplanes identified as Group 2 airplanes in the service
bulletin: Before the accumulation of 1,500 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, do the inspection specified in paragraph (j)
of this AD.
    (i) For airplanes identified as Group 1, Configuration 2
airplanes in the service bulletin: Within 1,500 flight cycles after
the lower forward corner reveal was last replaced or 1,000 flight
cycles after the effective date of this AD, whichever occurs later,
do the inspection specified in paragraph (j) of this AD.
    (j) At the applicable times specified in paragraphs (h) and (i)
of this AD: Do a detailed inspection of the lower forward corner
reveals for cracking and a sharp edge in accordance with Part 5 of
the service bulletin.
    (1) If no cracking and no sharp edge are found, before the
accumulation of 10,000 flight cycles on the lower forward corner
reveal since new, or within 6,000 flight cycles after doing the
inspection required by paragraph (j) of this AD, whichever occurs
later, do the detailed inspection for cracking in accordance with
Part 8 of the service bulletin and inspect thereafter at intervals
not to exceed 6,000 flight cycles, until a new or reworked two-piece
reveal is installed in accordance with Part 2 of the service
bulletin. If any cracking is found during any inspection required by
this paragraph, before further flight, do the action specified in
paragraph (j)(3) of this AD. No further action is required by this
paragraph for that location only after the replacement with a two-
piece reveal.
    (2) If no cracking is found but a sharp edge is found, do the
action specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
    (i) Before further flight, replace the lower forward corner
reveal with a new or reworked two-piece reveal, in accordance with
Part 2 of the service bulletin. No further action is required by
this paragraph for that location only after the replacement.
    (ii) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge, in
accordance with Part 3 of the service bulletin. Before the
accumulation of 10,000 flight cycles on the replacement reveal since
new, do the inspection for cracking in accordance with Part 8 of the
service bulletin and inspect thereafter at intervals not to exceed
6,000 flight cycles, until a new or reworked two-piece reveal is
installed in accordance with Part 2 of the service bulletin. If any
cracking is found during any inspection required by this paragraph,
before further flight, do the action required by paragraph (j)(3) of
this AD. No further action is required by this paragraph for that
location only after the replacement with a two-piece reveal.
    (3) If cracking is found, do the action specified in paragraph
(j)(3)(i) or (j)(3)(ii) of this AD.
    (i) Before further flight, replace the reveal with a new or
reworked two-piece reveal, in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
    (ii) Before further flight, replace the lower forward corner
reveal with a new or reworked one-piece machined aluminum reveal
without a sharp edge, in accordance with Part 3 of the service
bulletin. Before the accumulation of 10,000 flight cycles on the
replacement reveal since new, do the inspection for cracking in
accordance with Part 8 of the service bulletin and inspect
thereafter at intervals not to exceed 6,000 flight cycles, until a
new or reworked two-piece reveal is installed in accordance with
Part 2 of the service bulletin. If any cracking is found during any
inspection required by this paragraph, before further flight, do the
action required by paragraph (j)(3) of this AD. No further action is
required by this paragraph for that location only after the
replacement with a two-piece reveal.

Actions for Group 1, Configuration 1 Airplanes

    (k) For airplanes identified as Group 1, Configuration 1
airplanes in the service bulletin: Before the accumulation of 1,500
total flight cycles, or within 1,000 flight cycles after the
effective date of this AD, whichever occurs later, do a material
type inspection to determine if the lower forward corner reveals are
castings, in accordance with the service bulletin. As an alternative
to the material type inspection, replacing a reveal with a new or
reworked two-piece lower forward corner reveal in accordance with
Part 2 of the service bulletin is terminating action for the
requirements of this paragraph for that location only.
    (1) If the forward corner reveal is not a casting: Before
further flight, do the actions specified in paragraph (j) of this AD
except for the inspection for a sharp edge.
    (2) If the forward corner reveal is a casting: Before the
accumulation of 7,000 total flight cycles, within 2,000 flight
cycles after the effective date of this AD, or within 3,000 flight
cycles since the forward corner reveal was inspected in accordance
with Boeing Service Bulletin 747-53A2378, whichever is latest, do a
detailed inspection for cracking of the lower forward corner reveal,
in accordance with Part 1 of Boeing Special Attention Service
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.
    (i) If no cracking is found: Repeat the inspection specified in
paragraph (k)(2) of this AD thereafter at intervals not to exceed
3,000 flight cycles until a new or reworked two-piece lower forward
corner reveal is installed in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
    (ii) If cracking is found: Do the actions specified in paragraph
(k)(2)(ii)(A), (k)(2)(ii)(B), or (k)(2)(ii)(C) of this AD.
    (A) Before further flight, weld repair the reveal in accordance
with Part 4 of the service bulletin. Repeat the inspection specified
in paragraph (k)(2) of this AD thereafter at intervals not to exceed
3,000 flight cycles until a new or reworked two-piece reveal is
installed in accordance with Part 2 of the service bulletin. No
further action is required by this paragraph for that location only
after the replacement.
    (B) Before further flight, replace the reveal with a new or
reworked two-piece reveal, in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
    (C) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge, in
accordance with Part 3 of the service bulletin. Before the
accumulation of 10,000 flight cycles on the replacement reveal since
new, do the inspection for cracking in accordance with Part 8 of the
service bulletin and inspect thereafter at intervals not to exceed
6,000 flight cycles, until a new or reworked two-piece reveal is
installed in accordance with Part 2 of the service bulletin. If any
cracking is found during any inspection required by this paragraph,
before further flight, do the action required by paragraph
(k)(2)(ii)(B) or (k)(2)(ii)(C) of this AD. No further action is
required by this paragraph for that location only after the
replacement with a two-piece reveal.

Operator's Equivalent Procedure

    (l) Although Step 5 of Figure 8 of the service bulletin
specifies that operators may accomplish the actions in accordance
with ``an operator's equivalent procedure,'' this AD requires
operators to accomplish Step 5 of Figure 8 in accordance with only
the procedures specified in Boeing Standard Overhaul Practices
Manual (SOPM) 20-20-

02 as given in the service bulletin. An ``operator's equivalent
procedure'' may be used only if approved as an alternative method of
compliance in accordance with paragraph (p) of this AD.

Compliance With AD 2007-12-11, Amendment 39-15089, for MED 3 Only

    (m) Accomplishment of the applicable repair required by this AD
constitutes compliance with the repair of the lower forward corner
casting (reveal) of the number 3 MEDs only, as required by paragraph
(q)(2)(ii) of AD 2007-12-11 (which specifies the actions be done in
accordance with Boeing Service Bulletin 747-53A2378, Revision 1,
dated March 10, 1994; or Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005). Accomplishment of the actions of
this AD does not terminate the remaining requirements of AD 2007-12-
11.

Parts Installation

    (n) As of the effective date of this AD, no person may install a
door lower forward corner reveal made of cast 356 aluminum on any
airplane at a location specified by this AD.
    (o) As of the effective date of this AD, no person may install a
door lower forward corner reveal made of machined 6061 aluminum on
any airplane at a location specified by this AD, unless it has been
confirmed/reworked to be without a sharp edge in accordance with the
service bulletin.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.

    Issued in Renton, Washington, on May 7, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-11474 Filed 5-21-08; 8:45 am]

BILLING CODE 4910-13-P