[Federal Register: May 22, 2006 (Volume 71, Number 98)]
[Notices]
[Page 29326]
[DOCID:fr22my06-40]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. RP06-357-000]

Gulf States Transmission Corporation; Notice of Proposed Changes
In FERC Gas Tariff

May 12, 2006.
    Take notice that on May 9, 2006, Gulf States Transmission
Corporation (Gulf States) tendered for filing as part of its FERC Gas
Tariff, Original Volume No. 1, the tariff sheets listed on Attachment A
to the filing, to become effective June 1, 2006.
    Gulf States copies of this filing are being served on all customers
of Gulf States and applicable state regulatory agencies.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211 and 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed in accordance with the provisions of
Sec.  154.210 of the Commission's regulations (18 CFR 154.210). Anyone
filing an intervention or protest must serve a copy of that document on
the Applicant. Anyone filing an intervention or protest on or before
the intervention or protest date need not serve motions to intervene or
protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://www.ferc.gov.
 Persons unable to file electronically should submit an

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

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

TTY, call<PHONE_NUMBER>.

Magalie R. Salas,
Secretary.
 [FR Doc. E6-7705 Filed 5-19-06; 8:45 am]

BILLING CODE 6717-01-P


[Federal Register Volume 79, Number 135 (Tuesday, July 15, 2014)]
[Rules and Regulations]
[Pages 41120-41125]
[FR Doc No: 2014-16381]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD;
Amendment 39-17898; AD 2014-14-03]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-07-01,
for certain The Boeing Company Model 747 airplanes. AD 2014-07-01
required repetitive inspections for cracking in certain bulkhead
structure; inspections of certain fasteners and support frame
modifications on certain airplanes; related investigative and
corrective actions, if necessary; and an interim modification that
would terminate certain repetitive inspections. This AD clarifies
certain paragraph references and revises a compliance time. This AD was
prompted by a determination that certain paragraph references are in
error. We are issuing this AD to detect and correct fatigue cracking of
the BS 2598 bulkhead structure, which could adversely affect the
structural integrity of the bulkhead and the horizontal stabilizer
support structure, and result in loss of controllability of the
airplane.

DATES: This AD is effective July 15, 2014.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 3, 2014
(79 FR 23893, April 29, 2014).
    We must receive any comments on this AD by August 29, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: 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, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone<PHONE_NUMBER>,
extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0432; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>; fax:
425-917-6590; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On March 17, 2014, we issued AD 2014-07-01, Amendment 39-17815 (79
FR 23893, April 29, 2014), for certain The Boeing Company Model 747
airplanes. AD 2014-07-01 required repetitive inspections, including
post-repair and post-modification inspections, for cracking in the
bulkhead structure at body station (BS) 2598; certain one-time
inspections of certain fasteners and support frame modifications on
certain airplanes; related investigative and corrective

actions, if necessary; and an interim modification that would terminate
certain repetitive inspections.
    AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
resulted from reports of cracking in the forward and aft inner chord of
the BS 2598 bulkhead near the upper corners of the cutout for the
horizontal stabilizer rear spar, and cracking in the bulkhead upper and
lower web panels near the inner chord to shear deck connection. We
issued AD 2014-07-01 to detect and correct fatigue cracking of the BS
2598 bulkhead structure, which could adversely affect the structural
integrity of the bulkhead and the horizontal stabilizer support
structure, and result in loss of controllability of the airplane.

Actions Since AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29,
2014), Was Issued

    Paragraph (o)(1) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893,
April 29, 2014), terminated the actions in certain paragraphs of AD
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010). AD 2014-07-
01, however, incorrectly terminated ``paragraphs (k) and (l),'' which
should have been ``paragraph (k)(1).'' Paragraph (o)(1) of this AD
corrects that reference to ``paragraph (k)(1).'' All provisions of AD
2010-14-07 that are not specifically referenced in paragraph (o)(1) of
this AD remain fully applicable and must be complied with, including
paragraph (k)(2) of AD 2010-14-07.
    We also found an additional incorrect paragraph reference. The
first sentence of paragraph (p) of AD 2014-07-01 provides credit for
the actions required by paragraphs (g), (h), (i), and (n)(2) of that
AD. Paragraph (n)(2) of AD 2014-07-01 does not exist. The text of
paragraph (p) of this AD has been revised to refer to paragraphs (g),
(h), and (i) of this AD.
    We have also clarified that the airplanes affected by paragraph (i)
of this AD include airplanes on which an interim modification, aft
inner chord repair, or upper web repair has been previously
accomplished as specified in Boeing Alert Service Bulletin 747-53A2427.

Compliance Time Change for Airplanes in Groups 4 and 5

    We have moved the compliance time specified in paragraph (j) of
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), into new
paragraphs (j)(1) and (j)(2) of this AD. Paragraph (j)(1) of this AD
restates the compliance times for airplanes in Groups 1, 2, and 3.
Paragraph (j)(2) of this AD provides a new compliance time for
airplanes in Groups 4 and 5. We have added a compliance time (grace
period) of ``18 months after the effective date of this AD'' for
airplanes in Groups 4 and 5. We have determined that this new grace
period will provide an acceptable level of safety.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires repetitive inspections, including post-repair and
post-modification inspections, for cracking in the bulkhead structure
at BS 2598; certain one-time inspections of certain fasteners and
support frame modifications on certain airplanes; related investigative
and corrective actions, if necessary; and an interim modification that
would terminate certain repetitive inspections. This AD provides
clarification of certain paragraph references and revises a compliance
time.

FAA's Justification and Determination of the Effective Date

    Since this AD merely corrects incorrect paragraph references and
includes a relieving grace period for certain airplanes, notice and
opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 184 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Bulkhead (support frame)           49 work-hours x $85            $0  $4,165 per            $766,360 per
 inspection.                        per hour = $4,165                  inspection cycle.     inspection cycle.
                                    per inspection
                                    cycle.
Support frame modification.......  315 work-hours x $85            0  $26,775.............  Up to $4,926,600.
                                    per hour = $26,775.
Support frame upper corner         16 work-hours x $85             0  $1,360..............  Up to $250,240.
 fastener inspection.               per hour = $1,360.
Support frame post-modification/   200 work hours x $85            0  $17,000.............  $3,128,000.
 post repair inspection.            per hour = $17,000.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary interim
modification that would be required based on the results of the
inspections of the bulkhead specified in paragraph (g) of this AD. We
have no way of determining the number of aircraft that might need this
interim modification:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Interim modification.........................  4 work-hours x $85 per hour =                $0             $340
                                                $340.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
a cost estimate for the corrective actions specified in this 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

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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)
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014) and adding
the following new AD:

2014-14-03 The Boeing Company: Amendment 39-17898; Docket No. FAA-
2014-0432; Directorate Identifier 2014-NM-099-AD.

(a) Effective Date

    This AD is effective July 15, 2014.

(b) Affected ADs

    This AD supersedes AD 2014-07-01, Amendment 39-17815 (79 FR
23893, April 29, 2014).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes, certificated in
any category, as identified in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in particular areas
of the bulkhead structure at body station (BS) 2598. We are issuing
this AD to detect and correct fatigue cracking of the BS 2598
bulkhead structure, which could adversely affect the structural
integrity of the bulkhead and the horizontal stabilizer support
structure, and result in loss of controllability of the airplane.

(f) Compliance

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

(g) Retained Inspections of the Bulkhead (Support Frame) With No
Changes

    This paragraph restates the actions required by paragraph (g) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. For airplanes on which the bulkhead (support frame)
modification specified in Boeing Service Bulletin 747-53A2473 or
Boeing Alert Service Bulletin 747-53A2837 has not been done, and on
which an interim modification or aft inner chord repair specified in
Boeing Alert Service Bulletin 747-53A2427 has not been done: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013, except as provided by paragraph (m)(1), (m)(2), or (m)(3)
of this AD, as applicable, do an open-hole and surface high
frequency eddy current (HFEC) inspection for cracking in the
bulkhead (support frame), which includes the bulkhead splice
fitting, frame supports, forward and aft inner chords, floor
supports, and upper and lower web panels; do a surface HFEC
inspection for cracking in the bulkhead upper web assembly; do an
open-hole and surface HFEC inspection for cracking in the bulkhead
lower web assembly; and do all applicable corrective actions; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013,
except as required by paragraphs (h), (m)(4), (m)(5), and (m)(6) of
this AD. Do all applicable corrective actions before further flight.
Repeat the applicable inspections, thereafter, at the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013. Doing
the modification required by paragraph (j) of this AD terminates the
repetitive inspections required by this paragraph.

(h) Retained Interim Modification With No Changes

    This paragraph restates the actions required by paragraph (h) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. For airplanes in Groups 1 and 2, as identified in
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013, on which no cracking was found during any inspection
required by paragraph (g) of this AD: At the applicable times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, except as
provided by paragraph (m)(2) of this AD, do the interim
modification, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013. Doing the interim modification terminates the repetitive

inspections required by paragraph (g) of this AD in the area of the
modification only. The repetitive inspections of the bulkhead lower
web, as specified in paragraph (g) of this AD, must be done. If the
aft inner chord repair or upper web repair specified in Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, has
been accomplished, an interim modification on the side of the
airplane that has the repair is not required by this paragraph.

(i) Retained Post-Repair Inspection or Post-Interim Modification
Inspection With a Clarification

    This paragraph restates the actions required by paragraph (i) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a clarification of the affected airplanes. For airplanes on
which an interim modification, aft inner chord repair, or upper web
repair has been done as specified in paragraph (g) or (h) of this
AD, or has been previously accomplished as specified in Boeing Alert
Service Bulletin 747-53A2427: At the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as specified in
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do
the actions specified in paragraphs (i)(1) and (i)(2) of this AD,
and all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, except as required by
paragraph (m)(4) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspections thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013. Doing the modification required by paragraph (j) of this
AD terminates the repetitive inspections required by this paragraph.
    (1) Do forward side surface HFEC inspections for cracking of the
bulkhead forward inner chord, splice fitting, and frame support.
    (2) Do surface and open-hole HFEC inspections for cracking in
the repaired and modified areas of the bulkhead, as applicable.

(j) Retained Bulkhead (Support Frame) Modification and Inspections With
a Revised Compliance Time

    This paragraph restates the actions required by paragraph (j) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a revised compliance time. For airplanes on which the bulkhead
(support frame) modification, as specified in Boeing Service
Bulletin 747-53A2473 has not been done as of June 3, 2014 (the
effective date of AD 2014-07-01): At the applicable time specified
in paragraph (j)(1) or (j)(2) of this AD, do the bulkhead (support
frame) modification and inspections, and all applicable related
investigative and corrective actions; in accordance with steps
3.B.3., 3.B.4., and 3.B.5. of the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011, except as required by paragraph (m)(4) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Doing the modification in this paragraph terminates
the inspections required by paragraphs (g) and (i) of this AD.
    (1) For Groups 1, 2, and 3 airplanes identified in Boeing
Service Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At
the time specified in table 2 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
    (2) For Groups 4 and 5 airplanes identified in Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At the
earlier of the times specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD,
    (i) Before the accumulation of 20,000 total flight cycles or
within 18 months after August 5, 2010 (the effective date of AD
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010),
whichever occurs later.
    (ii) Before the accumulation of 12,000 total flight cycles or
within 18 months after the effective date of this AD, whichever
occurs later.

(k) Retained Post-Modification Inspections With No Changes

    This paragraph restates the actions required by paragraph (k) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes.
    (1) For airplanes on which the bulkhead (support frame)
modification, as specified in Boeing Service Bulletin 747-53A2473
has been done: Except as provided by paragraphs (m)(7) and (m)(8) of
this AD, at the applicable time specified in tables 6, 7, 8, and 9
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do support frame post-
modification inspections, and open-hole HFEC inspections for
cracking in the hinge support, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, except as required by paragraph
(m)(4) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspections
thereafter at the applicable times specified in tables 6, 7, 8, and
9 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011.
    (2) For airplanes on which the support frame modification, as
specified in Boeing Service Bulletin 747-53A2473, Revision 1, dated
February 20, 2007 (which is not incorporated by reference in this
AD), has been done : Except as specified in paragraphs (m)(7) and
(m)(8) of this AD, at the applicable time specified in tables 4 and
5 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do a one-time general
visual inspection of the frame web and upper shear deck (floor
support) chord aft side for fasteners that were installed as part of
an inner chord repair removal; and a one-time general visual
inspection of the upper forward inner chord, frame support fitting,
and splice fitting for the installation of certain fasteners; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, except as
required by paragraph (m)(4) of this AD. Do all applicable related
investigative and corrective actions at the applicable times
specified in tables 4 and 5 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
    (3) For airplanes on which the support frame modification, as
specified in Boeing Service Bulletin 747-53A2473, dated March 24,
2005 (which was incorporated by reference in AD 2006-05-06,
Amendment 39-14503 (71 FR 12125, March 9, 2006)), has been done:
Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at
the applicable time specified in tables 5 and 10 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do a one-time general visual inspection of
the upper forward inner chord, frame support fitting, and splice
fitting for the installation of certain fasteners; a one-time
general visual inspection for any repair installed on the left and
right side of the aft inner chord; and do all applicable related
investigative and corrective actions; in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, except as required by paragraph
(m)(4) of this AD. Do all applicable related investigative and
corrective actions at the applicable times specified in tables 5 and
10 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2473, Revision 4, dated December 1, 2011.
    (4) For airplanes on which a post-modification inspection was
done using paragraph 3.B.8. of Part 1 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2473, Revision 3,
dated July 14, 2011 (which is not incorporated by reference in this
AD): Except as required by paragraphs (m)(7) and (m)(8) of this AD,
at the applicable time in table 11 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do a one-time surface HFEC inspection of the
support frame outer chord for cracking, in accordance with Part 1 of
the Accomplishment Instructions of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011. If any cracking is
found, repair before further flight, using a method approved in
accordance with the procedures specified in paragraph (q) of this
AD.

(l) Retained Post-Modification and Post-Repair Inspections With No
Changes

    This paragraph restates the actions required by paragraph (l) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. For airplanes on which cracking was found during a
post-modification inspection and was repaired by doing the
installation of an upper or lower corner post-modification web crack
repair, as specified in Boeing Service Bulletin 747-

53A2473, Revision 4, dated December 1, 2011: At the applicable times
specified in tables 6 and 8 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011, do a bulkhead (support frame) post-repair inspection, and do
all applicable corrective actions, in accordance with paragraph a.,
b., or c. of Part 4 of paragraph 3.B.8 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, as applicable, except as required by
paragraph (m)(4) of this AD. Repeat the inspection, thereafter, at
the applicable times specified in tables 6 and 8 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011.

(m) Retained Exceptions to Service Information With No Changes

    This paragraph restates the exceptions specified in paragraph
(m) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29,
2014), with no changes.
    (1) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after ``the date on
Revision 2 of this service bulletin,'' this AD requires compliance
within the specified compliance time after August 28, 2001 (the
effective date of AD 2001-15-03, Amendment 39-12337 (66 FR 38365,
July 24, 2001)).
    (2) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after ``the date on
Revision 4 of this service bulletin,'' this AD requires compliance
within the specified compliance time after August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
    (3) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time ``after the date on
the respective service bulletin revision'' this AD requires
compliance within the specified compliance time after June 3, 2014
(the effective date of AD 2014-07-01 Amendment 39-17815 (79 FR
23893, April 29, 2014)).
    (4) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013; or Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011; specifies to contact Boeing for
appropriate action: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (q) of this AD.
    (5) If, during any inspection required by paragraph (g) of this
AD, any cracking is found in the bonded web doubler, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (q) of this AD.
    (6) Where Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013,
specifies accomplishing inspections for cracking in the forward and
aft inner chords, splice fittings, floor supports, and upper and
lower web panels, this AD also requires doing an open-hole HFEC
inspection of the bonded web doubler if present.
    (7) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time ``after the date on
Revision 2 of this service bulletin,'' this AD requires compliance
within the specified compliance time as of August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
    (8) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time ``after the date on
Revision 3 of this service bulletin,'' or ``after the date on
Revision 4 of this service bulletin,'' this AD requires compliance
within the specified compliance time after June 3, 2014 (the
effective date of AD 2010-14-07, Amendment 39-17815 (79 FR 23893,
April 29, 2014)).

(n) Retained Optional Terminating Modification With No Changes

    This paragraph restates the actions required by paragraph (n) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. Accomplishing the modification of the bulkhead at
BS 2598 in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2837, dated July 13, 2012, terminates
the requirements of paragraphs (g), (h), (i), (j), (k), and (l) of
this AD, except where Boeing Alert Service Bulletin 747-53A2837,
dated July 13, 2012, specifies to contact Boeing for appropriate
action: Before further flight, repair the crack using a method
approved in accordance with the procedures specified in paragraph
(q) of this AD.

(o) Retained Terminating Action for Certain Requirements of AD 2010-14-
07, Amendment 39-16352 (75 FR 38001, July 1, 2010), With Revised
Terminating Action

    This paragraph restates the terminating actions specified in
paragraph (o) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893,
April 29, 2014), with revised terminating action within paragraph
(o)(1) of this AD.
    (1) Accomplishing the inspections, repairs, and modification in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, is an
acceptable terminating action for the corresponding inspections,
repairs, and modification at the BS 2598 support frame required by
paragraphs (i), (j), (k)(1), (m), (n), (o), (p), (q), (r), (s), (t),
(u), and (v) of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July
1, 2010). Where Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, specifies to contact Boeing for repair
instructions, the repair instructions must be approved in accordance
with the procedures specified in paragraph (q) of this AD. All
provisions of AD 2010-14-07 that are not specifically referenced in
this paragraph remain fully applicable and must be complied with,
including paragraph (k)(2) of AD 2010-14-07.
    (2) Accomplishing the inspections, repairs, and interim
modification in accordance with Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, is an acceptable
terminating action for the corresponding inspections, repairs and
interim modification at the BS 2598 bulkhead required by paragraphs
(i), (j), (o), (s), (t), (u), and (v) of AD 2010-14-07, Amendment
39-16352 (75 FR 38001, July 1, 2010). Where Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, specifies to
contact Boeing for repair data, the repair data must be approved in
accordance with the procedures specified in paragraph (q) of this
AD. All provisions of AD 2010-14-07 that are not specifically
referenced in this paragraph remain fully applicable and must be
complied with.

(p) Retained Credit for Previous Actions With Change to Paragraph
Reference

    This paragraph restates the credit specified in paragraph (p) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a change to a paragraph reference. This paragraph provides
credit for the actions required by paragraphs (g), (h), and (i) of
this AD, if those actions were performed before June 3, 2014 (the
effective date of AD 2014-07-01) using Boeing Alert Service Bulletin
747-53A2427, Revision 6, dated July 14, 2011, provided that the
additional actions added in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, are done within the
applicable compliance times specified in paragraphs (g), (h), and
(i) of this AD. Boeing Alert Service Bulletin 747-53A2427, Revision
6, dated July 14, 2011, is not incorporated by reference in this AD.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (r)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (2) 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.
    (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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
    (4) Related portions or applicable paragraphs of AMOCs approved
previously for AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July
1, 2010), are approved as AMOCs for the corresponding provisions of
paragraphs (g), (h), (i), (j), (k), and (l) of this AD. All new
actions specified in paragraphs

(g), (h), (i), (j), (k), and (l) of this AD that are not identified
in a previously approved AMOC must still be done.
    (5) AMOCs approved for AD 2014-07-01, Amendment 39-17815 (79 FR
23893, April 29, 2014), are approved as AMOCs for the corresponding
provisions of this AD.

(r) Related Information

    (1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) Service information identified in this AD that is not
incorporated by reference in this AD may be viewed at the addresses
specified in paragraphs (s)(4) and (s)(5) of this AD.

(s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on
June 3, 2014 (79 FR 23893).
    (i) Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated
July 19, 2013.
    (ii) Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011.
    (iii) Boeing Alert Service Bulletin 747-53A2837, dated July 13,
2012.
    (4) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (5) You may view this service information at 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.
    (6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 3, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-16381 Filed 7-14-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 83, Number 111 (Friday, June 8, 2018)]
[Rules and Regulations]
[Pages 26598-26599]
[FR Doc No: 2018-12388]

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ENVIRONMENTAL PROTECTION AGENCY

40 CFR Part 52

[EPA-R07-OAR-2018-0319; FRL-9979-11--Region 7]

Adequacy Determination for the St. Louis Area 2008 8-Hour Ozone
Redesignation Request and Maintenance State Implementation Plan, Motor
Vehicle Emissions Budgets for Transportation Conformity Purposes; State
of Missouri

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notification of adequacy determination.

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

SUMMARY: In this document, the EPA is notifying the public that the St.
Louis area 2008 8-hour ozone redesignation request and maintenance plan
motor vehicle emission budgets (MVEBs) for volatile organic compounds
(VOCs) and nitrogen oxides (NOX) are adequate for
transportation conformity purposes. As a result, these budgets must be
used by the State of Missouri for future transportation conformity
determinations for the St. Louis area.

DATES: This finding is effective June 22, 2018.

FOR FURTHER INFORMATION CONTACT: Heather Hamilton, at<PHONE_NUMBER>,
by email at [email protected], or by mail at U.S. Environmental
Protection Agency, Air Planning and Development Branch, 11201 Renner
Boulevard, Lenexa, Kansas 66219.

SUPPLEMENTARY INFORMATION: Throughout this document ``we,'' ``us,'' or
``our'' refer to EPA. The word ``budget(s)'' refers to the motor
vehicle emission budgets (MVEBs) for volatile organic compounds and
nitrogen oxides. For the purposes of this document, ``SIP'' refers to
the St. Louis Area 2008 8-Hour Ozone Redesignation Request and
Maintenance State Implementation Plan, submitted by Missouri Department
of Natural Resources to EPA as a SIP revision on September 12, 2016.
The Plan was revised on February 16, 2018.
    This document is an announcement of a finding that EPA has already
made. EPA Region 7 sent a letter to Missouri Department of Natural
Resources on May 15, 2018, stating that the MVEBs contained in the
Redesignation Request and Maintenance Plan are adequate for
transportation conformity purposes. As a result of EPA's finding, the
State of Missouri must use the MVEBs from the February 16, 2018,
Redesignation Request and Maintenance Plan for

future transportation conformity determinations for the St. Louis area.
The finding is available at EPA's conformity website: https://www.epa.gov/state-and-local-transportation.
    Transportation conformity is required by section 176(c) of the
Clean Air Act, as amended in 1990. EPA's conformity rule requires that
transportation plans, programs and projects conform to state air
quality implementation plans and establishes the criteria and procedure
for determining whether or not they do. Conformity to a SIP means that
transportation activities will not produce new air quality violations,
worsen existing violations, or delay timely attainment of the national
ambient air quality standards.
    The criteria by which we determine whether a SIP's motor vehicle
emission budgets are adequate for conformity purposes are outlined in
40 CFR 93.118(e)(4). Please note that an adequacy review is separate
from EPA's completeness review, and it should not be used to prejudge
EPA's ultimate approval of the SIP. EPA plans to take action on the SIP
at a later date. We have described our process for determining the
adequacy of submitted SIP budgets in 40 CFR 93.118(f), and have
followed this rule in making our adequacy determination.

    Authority:  42 U.S.C. 7401-7671q.

    Dated: May 25, 2018.
James B. Gulliford,
Regional Administrator, Region 7.
[FR Doc. 2018-12388 Filed 6-7-18; 8:45 am]
 BILLING CODE 6560-50-P


[Federal Register Volume 76, Number 170 (Thursday, September 1, 2011)]
[Proposed Rules]
[Pages 54399-54403]
[FR Doc No: 2011-22370]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0914; Directorate Identifier 2010-NM-166-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Model 737-200, -
200C, -300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Model 737-300,

-400, and -500 series airplanes. The existing AD currently requires
repetitive external non-destructive inspections to detect cracks in the
fuselage skin along the chem-mill step at stringers S-1 and S-2 right,
between station (STA) 827 and STA 847, and repair if necessary. Since
we issued that AD, we have received reports of additional crack
findings of the fuselage crown skin at the chem-milled steps. This
proposed AD would add inspections for cracking in additional fuselage
crown skin locations, and repair if necessary. This proposed AD would
also reduce the inspection thresholds for certain airplanes, extend
certain repetitive inspection intervals, and add airplanes to the
applicability of the existing AD. We are proposing this AD to detect
and correct fatigue cracking of the fuselage skin panels at the chem-
milled steps, which could result in sudden fracture and failure of the
fuselage skin panels, and consequent rapid decompression of the
airplane.

DATES: We must receive comments on this proposed AD by October 17,
2011.

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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone<PHONE_NUMBER>,
extension 1; fax<PHONE_NUMBER>; e-mail<EMAIL_ADDRESS>Internet
https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 425-917-
6447; fax:<PHONE_NUMBER>; e-mail<EMAIL_ADDRESS>
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-2011-0914;
Directorate Identifier 2010-NM-166-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

    On December 21, 2009, we issued AD 2010-01-09, Amendment 39-16167
(75 FR 1527, January 12, 2010), for certain Model 737-300, -400, and -
500 series airplanes. That AD requires repetitive external non-
destructive inspections to detect cracks in the fuselage skin along the
chem-mill step at stringers S-1 and S-2 right, between STA 827 and STA
847, and repair if necessary. That AD resulted from a report of a hole
in the fuselage skin common to stringers S-1 and S-2 left, between STA
827 and STA 847, on an airplane that diverted to an alternate airport
due to cabin depressurization and subsequent deployment of the oxygen
masks. We issued that AD to detect and correct fatigue cracking of the
fuselage skin panels at the chem-milled steps, which could result in
sudden fracture and failure of the fuselage skin panels, and consequent
rapid decompression of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2010-01-09, we have received reports of new
findings of cracking in the fuselage crown skin at the horizontal chem-
milled steps at locations between body stations 259.5 and 1016 and
between stringers S-10L and S-10R. The cause of the cracking is under
investigation.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-53A1301, Revision 2,
dated April 25, 2011. Boeing Alert Service Bulletin 737-53A1301, dated
September 3, 2009, was referred to for accomplishing the actions in the
existing AD. We also reviewed Boeing Alert Service Bulletin 737-
53A1301, Revision 1, dated June 7, 2010. Revision 1 of this service
bulletin adds inspections for cracking in additional fuselage crown
skin locations, and repair if necessary; it reduces the inspection
threshold for certain airplanes; extends certain repetitive inspection
intervals; and adds airplanes to the effectivity (Model 737-200 and -
200C series airplanes, and Model 737-300, -400, and -500 series without
ELT antenna provisions). The new inspection types specified in Revision
1 of this service bulletin are detailed inspections, and optional
external nondestructive: ultrasonic phased array inspections. Revision
1 of this service bulletin also recommends contacting Boeing for
inspection instructions for Group 26 airplanes. Revision 2 of this
service bulletin specifies that no more work is necessary on airplanes
changed as specified in Revision 1 of this service bulletin. Revision 2
of this service bulletin only includes minor editorial changes.
    Boeing Alert Service Bulletin 737-53A1301, Revision 2, dated April
25, 2011; and Boeing Alert Service Bulletin 737-53A1301, Revision 1,
dated June 7, 2010; specify that the compliance times for the initial
inspections for Groups 2, 8, and 10 airplanes at the ELT antenna
provision at stringers S-1 and S-2R between BS 827 and BS 847, are at
the latest of the following: Prior to the accumulation of 35,000 total
flight cycles, or, depending on inspection locations, within 1,800
flight cycles after the issue date of the original issue or Revision 1
of this service bulletin, or within 1,800 flight cycles after the most
recent inspection done in accordance with Boeing Alert Service Bulletin
737-53A1301, dated September 3, 2009. For Groups 1 through 12
airplanes, at the new inspection locations, the compliance times are
prior to the accumulation of 35,000 total flight

cycles, or within 1,800 flight cycles after the issue date of Revision
1 of this service bulletin. For groups 1 through 12, the repetitive
inspection interval is 1,800 flight cycles (for Option 1 inspections)
and 2,400 flight cycles (for Option 2 inspections). For airplanes on
which the inspection procedure is changed from Option 2 to Option 1,
the first Option 1 inspection must be done within 2,400 flight cycles
after doing the Option 2 inspection. For airplanes on which the
inspection procedure is changed from Option 1 to Option 2, the first
two Option 2 inspections must be done within 1,800 flight cycles.
    Boeing Alert Service Bulletin 737-53A1301, Revision 2, dated April
25, 2011; specifies that the compliance times for the initial
inspections for Groups 13 through 18 and 21 through 25 airplanes at the
ELT antenna provision at stringers S-1 and S-2R, between BS 827 and BS
847, are as follows:
     For airplanes on which the inspections specified in Boeing
Alert Service Bulletin 737-53A1301, dated September 3, 2009; or
Revision 1, dated June 7, 2010; have been done: At the latest of the
following, prior to the accumulation of 33,000 total flight cycles, or
within 500 flight cycles after the most recent inspection done in
accordance with Boeing Alert Service Bulletin 737-53A1301, dated
September 3, 2009; or Revision 1, dated June 7, 2010.
     For airplanes on which the inspections specified in Boeing
Alert Service Bulletin 737-53A1301, dated September 3, 2009; or
Revision 1, dated June 7, 2010; have not been done: Prior to the
accumulation of 33,000 total flight cycles, or within 500 flight cycles
after the issue date of Revision 2 of this service bulletin, whichever
occurs later.
    For Groups 13 through 25, Boeing Alert Service Bulletin 737-
53A1301, Revision 2, dated April 25, 2011; specifies that the
compliance times for the initial inspections for Groups 13 through 25
airplanes at the new inspection locations are as follows: Prior to the
accumulation of 33,000 total flight cycles, or within 500 flight cycles
after the issue date of Revision 1 of Boeing Alert Service Bulletin
737-53A1301, whichever occurs later.
    For Groups 13 through 25, Boeing Alert Service Bulletin 737-
53A1301, Revision 2, dated April 25, 2011; specifies that the
repetitive inspection interval is 500 flight cycles (for Option 1) and
1,000 flight cycles (for Option 2). For airplanes on which the
inspection procedure is changed from Option 2 to Option 1, the first
Option 1 inspection must be done within 1,000 flight cycles after doing
the Option 2 inspection. For airplanes on which the inspection
procedure is changed from Option 1 to Option 2, the first two Option 2
inspections must be done within 500 flight cycles.
    For Group 26 airplanes, Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, specifies contacting Boeing to obtain
engineering and accomplishment instructions for certain inspections.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2010-01-09,
and would add inspections for cracking in additional fuselage crown
skin locations, and repair if necessary. This proposed AD would also
reduce the inspection thresholds for certain airplanes, extend certain
repetitive inspection intervals, and add airplanes to the applicability
of AD 2010-01-09. This proposed AD would require accomplishing the
actions specified in the service information described previously.

Interim Action

    We consider this proposed AD interim action. If final action is
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD affects 654 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Number of U.S.-
            Action                Work hours     Average labor      Cost per       registered       Fleet cost
                                                 rate per hour      product         airplanes
----------------------------------------------------------------------------------------------------------------
Inspection in AD 2010-01-09..  2..............             $85  $170 per                    135  $22,950 per
                                                                 inspection                       inspection
                                                                 cycle.                           cycle.
New inspection in this         Between 2 and                85  Between $170                654  Between
 proposed AD.                   30.                              and $2,550 per                   $111,180 and
                                                                 inspection                       $1,667,700 per
                                                                 cycle.                           inspection
                                                                                cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
a cost estimate 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 have 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 that the proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
    (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

    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 removing airworthiness directive
(AD) 2010-01-09, Amendment 39-16167 (75 FR 1527, January 12, 2010), and
adding the following new AD:

The Boeing Company: Docket No. FAA-2011-0914; Directorate Identifier
2010-NM-166-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October
17, 2011.

Affected ADs

    (b) This AD supersedes AD 2010-01-09, Amendment 39-16167.

Applicability

    (c) This AD applies to all The Boeing Company Model 737-200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 53, Fuselage.

Unsafe Condition

    (e) This AD was prompted by reports of additional crack findings
of the fuselage crown skin at the chem-milled steps. We are issuing
this AD to detect and correct fatigue cracking of the fuselage skin
panels at the chem-milled steps, which could result in sudden
fracture and failure of the fuselage skin panels, and consequent
rapid decompression of the airplane.

Compliance

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

Restatement of Requirements of AD 2010-01-09, Amendment 39-16167

Initial and Repetitive Inspections

    (g) For airplanes identified in Boeing Alert Service Bulletin
737-53A1301, dated September 3, 2009: Before the accumulation of
35,000 total flight cycles, or within 500 flight cycles after
February 16, 2010 (the effective date of AD 2010-01-09), whichever
occurs later, except as provided by paragraph (i) of this AD, do an
external non-destructive inspection (NDI) to detect cracks in the
fuselage skin along the chem-mill steps at stringers S-1 and S-2
right, between station (STA) 827 and STA 847, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1301, dated September 3, 2009; or Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011. If no cracking is
found, repeat the inspection thereafter at intervals not to exceed
500 flight cycles; except as provided by paragraphs (i) and (n) of
this AD. Accomplishing the inspections required by paragraph (j) of
this AD terminates the inspections required by this paragraph.

Repair

    (h) If any crack is found during any inspection required by
paragraph (g) of this AD, and Boeing Alert Service Bulletin 737-
53A1301, dated September 3, 2009; or Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011; specifies to contact
Boeing for repair instructions: Before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (q) of this AD.

Optional Terminating Action for Repetitive Inspections in Paragraph (g)
of This AD

    (i) Installing an external repair doubler along the chem-milled
steps at stringers S-1 and S-2 right, between STA 827 and STA 847,
constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD for the repaired area only,
provided all of the conditions specified in paragraphs (i)(1),
(i)(2), and (i)(3) of this AD are met.
    (1) The repair is installed after September 3, 2009;
    (2) The repair was approved by the FAA or by a Boeing Company
Authorized Representative or the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft Certification Office
(ACO) to make such findings; and
    (3) The repair extends a minimum of three rows of fasteners on
each side of the chem-mill line in the circumferential direction.

New Inspections Including Additional Locations and Reduced Inspection
Intervals

Groups 1 Through 25: Initial and Repetitive Inspections

    (j) For Groups 1 through 25 airplanes identified in Boeing Alert
Service Bulletin 737-53A1301, Revision 2, dated April 25, 2011:
Except as provided by paragraph (k) of this AD, at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1301, Revision 2, dated April 25, 2011, do
the applicable inspections required by paragraphs (j)(1) and (j)(2)
of this AD, in accordance with paragraphs 3.B.1 through 3.B.25 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011. If no cracking is
found, repeat the applicable inspections thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1301, Revision 2, dated April
25, 2011; except as provided by paragraphs (m) and (n) of this AD.
Doing the inspections required by this paragraph terminates the
inspections required by paragraph (g) of this AD.
    (1) For Groups 2, 8, 10, 13 through 18, and 21 through 25
airplanes: Do a detailed inspection and an external non-destructive
inspection (NDI) (medium frequency eddy current inspection, magneto
optical imaging inspection, c-scan inspection, or ultrasonic phased
array inspection) for cracking in the fuselage skin at the chem-mill
steps at S-1 and S-2R between STA 827 and STA 847, as identified in
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011.
    (2) For Groups 1 through 25 airplanes: Do a detailed inspection
and an external NDI (medium frequency eddy current inspection;
magneto optical imaging inspection, c-scan inspection, or ultrasonic
phased array inspection) for cracking in the fuselage skin at the
chem-mill steps at the specified locations other than at S-1 and S-
2R between STA 827 and STA 847, as identified in the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1301, Revision
2, dated April 25, 2011.

    Note 1: Option 1 of Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, specifies a detailed inspection,
and one additional inspection (external NDI, medium frequency eddy
current inspection, magneto optical imaging inspection, or c-scan
inspection). Option 2 specifies a detailed inspection and an
external ultrasonic phased array inspection. These options have
different compliance times after the initial inspection.

    (k) Where Boeing Alert Service Bulletin 737-53A1301, Revision 2,
dated April 25, 2011, specifies a compliance time after ``the date
of Revision 1,'' or ``the date of Revision 2'' of that service
bulletin, this AD requires compliance within the specified time
after the effective date of this AD.

Repair

    (l) If any crack is found during any inspection required by
paragraph (j) of this AD: Before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (q) of this AD. Doing the repair ends the repetitive
inspections required by paragraph (j) for the repaired area only.

Optional Terminating Action for Repetitive Inspections

    (m) Installing an external repair doubler along the chem-milled
steps at any location identified in Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011, constitutes
terminating action for the repetitive inspections required by
paragraph (j) of this AD for the repaired area only, provided all of
the conditions specified in

paragraphs (m)(1), (m)(2), and (m)(3) of this AD are met.
    (1) The repair is installed after the applicable date specified
in paragraph (m)(1)(i) and (m)(1)(ii) of this AD.
    (i) For repairs at S-1 and S-2R between STA 827 and STA 847:
Installed after September 3, 2009.
    (ii) For repairs at locations other than at S-1 and S-2R between
STA 827 and STA 847: Installed after June 7, 2010.
    (2) The repair was approved by the FAA or by a Boeing Company
Authorized Representative or the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft Certification Office
(ACO) to make such findings; and
    (3) The repair extends a minimum of three rows of fasteners on
each side of the chem-mill line in the circumferential direction.
    (n) Accomplishing a modification of the chem-milled steps at any
location identified in Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, using a method approved in
accordance with the procedures specified in paragraph (q)(1) of this
AD, terminates the repetitive inspections required by paragraphs (g)
and (j) of this AD for the modified area only.

Group 26 Airplanes

    (o) For Group 26 airplanes identified in Boeing Alert Service
Bulletin 737-53A1301, Revision 2, dated April 25, 2011: Within 1,800
flight cycles after the effective date of this AD, accomplish
applicable inspections and corrective action, as identified in the
service bulletin, using a method approved in accordance with the
procedures specified in paragraph (q)(1) of this AD.

Credit for Actions Accomplished in Accordance With Previous Service
Information

    (p) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 737-53A1301, Revision
1, dated June 7, 2010, are acceptable for compliance with the
corresponding requirements of this AD.

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
Information may be e-mailed to<EMAIL_ADDRESS>    (2) 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.
    (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 the
Boeing Commercial Airplanes ODA that 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.

Related Information

    (r) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; e-mail:
<EMAIL_ADDRESS>    (s) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax<PHONE_NUMBER>; e-mail
<EMAIL_ADDRESS>Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on August 25, 2011.
Ali Bahrami,
Manager Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-22370 Filed 8-31-11; 8:45 am]
BILLING CODE 4910-13-P