[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27010-27015]
[FR Doc No: 2013-10006]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1068; Directorate Identifier 2011-NM-073-AD;
Amendment 39-17443; AD 2013-09-02]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding two existing airworthiness directives (AD)
that apply to certain The Boeing Company Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes. Those ADs, for certain airplanes,
currently require repetitive inspections of the flap track of the wing
outboard flap, and corrective actions if necessary; and eventual rework
of the flap track assembly and rear spar attachments. For certain
airplanes, this new AD adds repetitive inspections, scheduled
overhauls, correct alignment during installation, and repetitive
maintenance of the flap track, and corrective actions if necessary.
This new AD also adds airplanes to the applicability. This AD was
prompted by reports that the work sequence and procedures used during
installation of replacement tracks could cause loose or cracked tracks.
We are issuing this AD to detect and correct cracking and damage in the
flap track, which could cause loss of the outboard trailing edge flap
and consequent reduced controllability of the airplane.

DATES: This AD is effective June 13, 2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 13,
2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of April
22, 2002 (67 FR 11891, March 18, 2002).
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
January 2, 2001 (65 FR 78913, December 18, 2000).

ADDRESSES: 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. You may review copies of the 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; 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 address for the
Docket Office (phone:<PHONE_NUMBER>) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, 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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2000-25-07, Amendment 39-12041 (65 FR 78913,
December 18, 2000); and AD 2002-05-07, Amendment 39-12675 (67 FR 11891,
March 18, 2002). Those ADs apply to the specified products, and require
repetitive inspections of the flap track of the wing outboard flap, and
corrective actions if necessary; and eventual rework of the flap track
assembly and rear spar attachments. The NPRM published in the Federal
Register on October 10, 2012 (77 FR 61542). The NPRM proposed to retain
all requirements of AD 2000-25-07 and AD 2002-05-07. For certain
airplanes, the NPRM proposed to add repetitive inspections, scheduled
overhauls, correct alignment during installation, and repetitive
maintenance of the flap track, and corrective actions if necessary.
This new AD also adds airplanes to the applicability.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 61542, October 10, 2012) and the FAA's response to each comment.

Concurrence

    Boeing and United concurred with the content of the NPRM (77 FR
61542, October 10, 2012).

Request To Change Text of Paragraph (p)(3) of the NPRM (77 FR 61542,
October 10, 2012)

    Alaska Airlines requested that we change the text of paragraph
(p)(3) of the NPRM (77 FR 61542, October 10, 2012) to revise the
descriptions of the inspection locations to be similar to the
instructions included in Boeing 737 Non Destructive Test (NDT) Manual
Part 6, 57-50-06. The commenter suggested that the existing wording in
paragraph (p)(3) of the NPRM contradicts the instructions specified in
Boeing 737 NDT Manual Part 6, 57-50-06.
    We disagree with the request to change the text of paragraph (p)(3)
of this AD. The inspections specified in paragraph (p)(3) of this AD
must be done in accordance with paragraph 3.B.3., ``Inspection--Track
Webs and Flanges,'' of the Accomplishment Instructions of Boeing
Service Bulletin 737-57A1271, Revision 3, dated February 13, 2012. The
instructions for accomplishing the eddy current inspection required by
paragraph (p)(3) of this AD are detailed in Boeing 737 NDT Manual Part
6, 57-50-06, which is an additional source of guidance. There is no
contradiction in the instructions. No change has been made to the AD in
this regard.

Request for Revised Service Information

    Southwest Airlines requested that Boeing Service Bulletin 737-
57A1271, Revision 3, dated February 13, 2012, be revised to add missing
necessary data to support the rework requirements of paragraphs (s) and
(t) of the NPRM (77 FR 61542, October 10, 2012) for flap track part
number (P/N) 65C34809-3. The commenter stated that paragraphs (s) and
(t) of the NPRM require doing the corrective actions in accordance with
Boeing Service Bulletin 737-57A1271, Revision 3, dated February 13,
2012. The commenter also stated that Boeing Service Bulletin 737-
57A1271, Revision 3, dated February 13, 2012, provides repair data, but
the commenter noted that not all repair data are provided for flap
track P/N 65C34809-3. The commenter added that Boeing

Overhaul Manual 57-53-15, Figure 614, ``Supplemental Track Overhaul
Instructions,'' should be revised to add minimum allowable dimensions
T1 through T4, W, and maximum allowable hole diameters d1, d2, and d3
for flap track P/N 65C34809-3.
    We disagree that any revised service information is necessary to
comply with the requirements of this AD. While the repair data for flap
track P/N 65C34809-3 is less extensive than for other tracks, the
information provided in Boeing Service Bulletin 737-57A1271, Revision
3, dated February 13, 2012, is adequate for this part. Since that flap
track has improved finishes, it is not expected to wear in the same way
as the other parts. If this flap track requires repair or rework that
exceeds the data currently provided, then operators may request
approval of new repair and rework limits in accordance with paragraph
(y) of this AD. No change has been made to the AD in this regard.

Request To Extend Compliance Time

    Sky King, Inc. requested that we extend the compliance time from
180 days to 24 months for airplanes with flap tracks that are
undocumented or did not previously require inspection by AD 2000-25-07,
Amendment 39-12041 (65 FR 78913, December 18, 2000); or AD 2002-05-07,
Amendment 39-12675 (67 FR 11891, March 18, 2002). The commenter stated
that extending the compliance time as requested will allow the operator
to inspect the flap tracks at a more convenient interval, such as a
scheduled ``C-check'' maintenance interval.
    We disagree with the request to extend the compliance time. The
initial inspection compliance time of 180 days was selected to address
potential safety issues on flap tracks that have not been inspected in
accordance with AD 2000-25-07, Amendment 39-12041 (65 FR 78913,
December 18, 2000); or AD 2002-05-07, Amendment 39-12675 (67 FR 11891,
March 18, 2002). The commenter provided no data to support a request to
extend the compliance time for these airplanes.
    In developing an appropriate compliance time for this AD, we
considered not only the safety implications, but the manufacturer's
recommendations and the practical aspect of accomplishing the
inspection within an interval of time that corresponds to typical
scheduled maintenance for affected operators. We consider that U.S.
operators have had ample time to consider initiating the actions
specified in Boeing Service Bulletin 737-57A1271, Revision 3, dated
February 13, 2012, cited in the NPRM (77 FR 61542, October 10, 2012),
which this AD ultimately requires. Under the provisions of paragraph
(y) of this AD, however, we will consider requests for adjustments to
the compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. No change has
been made to the AD in this regard.

Effect of Supplemental Type Certificate (STC) for Winglet

    Aviation Partners Boeing stated that the installation of winglets
per STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) does
not affect the accomplishment of the manufacturer's service
instructions.
    We have added paragraph (c)(2) to this AD to state that
installation of STC ST01219SE does not affect the ability to accomplish
the actions required by this AD. Therefore, for airplanes on which STC
ST01219SE is installed, a ``change in product'' alternative method of
compliance (AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17. For all other AMOC requests, the operator
must request approval in accordance with the procedures specified in
paragraph (y) of this AD.

Other Changes to the AD

    We have removed table 1 to paragraph (g) from this AD; instead, we
have included the subject part numbers in paragraphs (g)(4)(i) through
(g)(4)(x) of this AD. This change does not affect the intent of that
paragraph.
    We have revised the second to last sentence in paragraph (p) of
this AD to add references to paragraphs (l) and (m) of this AD.
Performing the inspections required by paragraph (p) of this AD
terminates the requirements of paragraphs (g), (j), (l), (m), and (n)
of this AD.
    We have revised paragraph (s) of this AD to clarify the
requirements for a damaged or corroded anti-fret strip.
    We have revised paragraph (x)(3) of this AD to correct the service
bulletin citation to Boeing Service Bulletin 737-57A1271, Revision 2,
dated January 17, 2011.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (77 FR 61542, October 10, 2012) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 61542, October 10, 2012).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 570 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                Cost per        Number of
                    Action                                Labor cost               Parts cost        product        airplanes     Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed visual inspection [retained actions   6 work-hours x $85 per hour =                 $0            $510             290                $147,900.
 from existing AD 2000-25-07, Amendment 39-     $510.
 12041 (65 FR 78913, December 18, 2000)].
Detailed visual, HFEC, and ultrasonic          4 work-hours x $85 per hour =                  0            $340           1,100                $374,000.
 inspections [retained actions from existing    $340.
 AD 2002-05-07, Amendment 39[dash]12675 (67
 FR 11891, March 18, 2002)].

Detailed and eddy current inspections [new     82 work-hours x $85 per hour =                 0      $6,970 per             570           $3,972,900 per
 actions].                                      $6,970 per inspection cycle.                         inspection                        inspection cycle.
                                                                                cycle
Overhaul [new action]........................  70 work-hours x $85 per hour =            20,000     $25,950 per             570          $14,791,500 per
                                                $5,950 per overhaul cycle.                       overhaul cycle                          overhaul cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for labor cost for repair, and parts cost for repair and
replacement for the on-condition actions specified in this AD. The
labor cost of the replacement is $1,360 (16 work-hours x $85 per hour).
We have no way of determining the number of aircraft that might need
these repairs/replacements.

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 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 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)
2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000); and AD
2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002); and
adding the following new AD:

2013-09-02 The Boeing Company: Amendment 39-17443; Docket No. FAA-
2012-1068; Directorate Identifier 2011-NM-073-AD.

(a) Effective Date

    This AD is effective June 13, 2013.

(b) Affected ADs

    This AD supersedes ADs 2000-25-07, Amendment 39-12041 (65 FR
78913, December 18, 2000); and 2002-05-07, Amendment 39-12675 (67 FR
11891, March 18, 2002).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
    (2) Installation of Supplemental Type Certificate (STC)
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports that the work sequence and
procedures used during installation of replacement tracks installed
in accordance with AD 2000-25-07, Amendment 39-12041 (65 FR 78913,
December 18, 2000); or AD 2002-05-07, Amendment 39-12675 (67 FR
11891, March 18, 2002); could cause loose or cracked tracks. We are
issuing this AD to detect and correct cracking and damage in the
flap track, which could cause loss of the outboard trailing edge
flap and consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections

    This paragraph restates the inspections required by paragraph
(a) of AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18,
2000), with added references to a terminating action. For Model 737-
100, -200, and -200C series airplanes on which the left- or right-
hand inboard flap tracks of the wing outboard flap have a part
number (P/N) listed in paragraphs (g)(4)(i) through (g)(4)(x) of
this AD: Do a detailed visual inspection to detect damage
(corrosion, cracking) of the aft end of the left- and right-hand
inboard flap tracks of the wing outboard flap, per Boeing All
Operator Message (AOM) M-7200-00-01854, dated July 27, 2000, at the
latest of the times specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD. Repeat the inspection thereafter at intervals not
to exceed 1,200 flight cycles. Accomplishing the requirements of
paragraph (p) of this AD terminates the requirements of this
paragraph.
    (1) Within 30 days after January 2, 2001 (the effective date of
AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000)).
    (2) Within 1,200 flight cycles after the last documented
inspection or overhaul of the aft end of each flap track.
    (3) Before the accumulation of 15,000 total flight cycles.

    (4) Boeing flap tracks subject to this AD are identified in
paragraphs (g)(4)(i) through (g)(4)(x) of this AD.
    (i) P/N 65-46428-9.
    (ii) P/N 65-46428-15.
    (iii) P/N 65-46428-17.
    (iv) P/N 65-46428-19.
    (v) P/N 65-46428-21.
    (vi) P/N 65-46428-23.
    (vii) P/N 65-46428-25.
    (viii) P/N 65-46428-27.
    (ix) P/N 65-46428-33.
    (x) P/N 65-46428-35.

(h) Retained Definition

    This paragraph restates the definition specified by Note 2 of AD
2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000). For
the purposes of this AD, a detailed visual inspection is defined as:
``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at an intensity deemed appropriate by
the inspector. Inspection aids such as a mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''

(i) Retained Corrective Actions

    This paragraph restates the corrective actions required by
paragraph (b) of AD 2000-25-07, Amendment 39-12041 (65 FR 78913,
December 18, 2000), with added reference to the Boeing Commercial
Airplanes Organization Designation Authorization (ODA). If any
damage (corrosion, cracking) is detected during any inspection
required by paragraph (g) of this AD, before further flight, repair
or rework the flap track per the ``Repair and Rework Instructions''
specified in Boeing AOM M-7200-00-01854, dated July 27, 2000. Where
that AOM specifies that the manufacturer may be contacted for
disposition of certain corrective actions (i.e., repair and/or
rework of the flaps), this AD requires such repair and/or rework to
be done using a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using data meeting the type
certification basis of the airplane approved by a Boeing Company
designated engineering representative (DER) or the Boeing Commercial
Airplanes ODA that has been authorized by the Manager, Seattle ACO,
to make such findings. For a repair method to be approved by the
ODA, the repair must meet the certification basis of the airplane,
and the approval must specifically refer to this AD. For a repair
method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the Manager's approval letter must specifically
reference this AD.

(j) Retained Initial Inspections

    This paragraph restates the initial inspections required by
paragraph (a) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891,
March 18, 2002), with added references to terminating action. For
Model 737-100, -200, and -200C series airplanes with line numbers
(L/N) 1 through 869 inclusive, and those airplanes with L/Ns 870
through 1585 inclusive, which either still have their original flap
tracks or which have had the original flap tracks replaced with
certain tracks as specified in Boeing Service Bulletin 737-57A1249,
Revision 1, including Appendix A, dated June 1, 2000; except
airplanes on which any replacement flap tracks were installed as
specified in Boeing Service Bulletin 737-57-1203, dated November 15,
1990, or production equivalent: Within 6 months after April 22, 2002
(the effective date of AD 2002-05-07, Amendment 39-12675 (67 FR
11891, March 18, 2002)), accomplish the requirements of paragraphs
(j)(1) and (j)(2) of this AD, according to Boeing Service Bulletin
737-57A1249, Revision 1, including Appendix A, dated June 1, 2000.
Accomplishing the requirements of paragraph (p) of this AD
terminates the requirements of this paragraph.
    (1) Perform a detailed visual inspection for discrepancies
(e.g., corrosion, or missing, damaged, or migrated anti-fret strips
and tapered shims) of the rear spar attachments of the flap tracks.
    (2) Perform detailed visual, high frequency eddy current (HFEC),
and ultrasonic inspections for cracking in the upper flange of the
inboard track of each outboard flap at the rear spar attachments.

(k) Retained Credit for Certain Previous Actions

    This paragraph restates the credit for certain previously
accomplished actions specified by Note 3 of AD 2002-05-07, Amendment
39-12675 (67 FR 11891, March 18, 2002). This paragraph provides
credit for the actions specified in paragraphs (j), (l), (m), and
(n) of this AD, if those actions were performed before the effective
date of this AD using Boeing Alert Service Bulletin 737-57A1249,
including Appendix A, dated December 16, 1999, which is not
incorporated by reference in this AD.

(l) Retained Repetitive Inspections of the Rear Spar Attachment of the
Flap Tracks and Upper Flange of the Inboard Track of Each Outboard Flap
at the Rear Spar Attachments

    This paragraph restates the repetitive inspections required by
paragraph (b) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891,
March 18, 2002). For airplanes subject to the requirements of
paragraph (j) of this AD: If no discrepancy is found during any
inspection required by paragraph (j) of this AD, thereafter, repeat
the inspections specified in paragraph (j) of this AD at intervals
not to exceed 9 months, until the actions required by paragraph (m)
or (p) of this AD have been accomplished.

(m) Retained Rework

    This paragraph restates the rework required by paragraph (c) of
AD 2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002). For
airplanes subject to the requirements of paragraph (j) of this AD:
At the applicable time specified in paragraph (m)(1) or (m)(2) of
this AD, accomplish rework of the flap track assembly and aft flap
track attachments (including removal of the flap track; a detailed
visual inspection for a missing, damaged, or migrated anti-fret
strip and tapered shim of the rear spar attachments of the flap
track; replacement of the anti-fret strip with a new aluminum anti-
fret strip (or installation of an aluminum strip if no strip is
installed), as applicable; replacement of the tapered shim with a
new shim (or installation of a shim if no shim is installed); eddy
current and ultrasonic inspections for fatigue cracking of the flap
tracks; a detailed visual inspection for corrosion of the flap
tracks; and rework of attachment holes), including replacement of
the flap tracks, as applicable, by accomplishing all actions
specified in Part II of the Accomplishment Instructions of Boeing
Service Bulletin 737-57A1249, Revision 1, including Appendix A,
dated June 1, 2000. Do these actions according to the Accomplishment
Instructions of Boeing Service Bulletin 737-57A1249, Revision 1,
including Appendix A, dated June 1, 2000, except as provided by
paragraph (o) of this AD. Accomplishment of the actions required by
this paragraph terminates the repetitive inspections required by
paragraph (l) of this AD. Accomplishing the requirements of
paragraph (p) of this AD terminates the requirements of this
paragraph.
    (1) If no discrepancy is found during any inspection required by
paragraph (j) or (l) of this AD: Do the rework within 24 months
after April 22, 2002 (the effective date of AD 2002-05-07, Amendment
39-12675 (67 FR 11891, March 18, 2002)).
    (2) If any discrepancy is found during any inspection required
by paragraph (j) or (l) of this AD: Do the rework prior to further
flight.

(n) Retained Repetitive Inspections of the Upper Flange of the Inboard
Track of Each Outboard Flap at the Rear Spar Attachments

    This paragraph restates the repetitive inspections required by
paragraph (d) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891,
March 18, 2002). For Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes, except airplanes on which any replacement flap
tracks were installed as specified in Boeing Service Bulletin 737-
57-1203, dated November 15, 1990, or production equivalent: At the
applicable time specified in paragraph (n)(1) or (n)(2) of this AD,
and thereafter at least every 24 months, perform detailed visual,
HFEC, and ultrasonic inspections for cracking in the upper flange of
the inboard track of each outboard flap at the rear spar
attachments, according to Part I of the Accomplishment Instructions
of Boeing Service Bulletin 737-57A1249, Revision 1, including
Appendix A, dated June 1, 2000. Accomplishing the requirements of
paragraph (p) of this AD terminates the requirements of this
paragraph.
    (1) For airplanes subject to paragraph (m) of this AD, do the
inspections within 10 years after accomplishment of the rework
according to paragraph (m) of this AD.
    (2) For airplanes other than those identified in paragraph
(n)(1) of this AD, do the inspections within 10 years since the
airplane's date of manufacture, or within 6 months after April 22,
2002 (the effective date of AD 2002-05-07, Amendment 39-12675 (67 FR
11891, March 18, 2002)), whichever occurs later.

(o) Retained Repair Instructions and Exception to Procedures in Service
Information

    This paragraph restates the repair instructions and exception to
procedures required by paragraph (e) of AD 2002-05-07, Amendment 39-
12675 (67 FR 11891, March 18, 2002). If any discrepancy is found
during any action required by paragraph (j), (l), or (m) of this AD,
and Boeing Service Bulletin 737-57A1249, Revision 1, including
Appendix A, dated June 1, 2000, specifies to contact Boeing for
appropriate action; or if any discrepancy is found during
inspections according to paragraph (n) of this AD: Prior to further
flight, repair according to a method approved by the Manager,
Seattle ACO, FAA; or according to data meeting the type
certification basis of the airplane approved by a Boeing DER or
Boeing Company ODA, that has been authorized by the Manager, Seattle
ACO, to make such findings. For a repair method to be approved by
the ODA, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD. For a
repair method to be approved by the Manager, Seattle ACO, as
required by this paragraph, the approval letter must specifically
reference this AD.

(p) New Inspection of Flap Track Web and Flanges

    For all airplanes: At the times specified in paragraph (q) of
this AD, do the inspections specified in paragraphs (p)(1), (p)(2),
(p)(3), and (p)(4) of this AD, and do all applicable corrective
actions, in accordance with paragraph 3.B.3., ``Inspection--Track
Webs and Flanges,'' of the Accomplishment Instructions of Boeing
Service Bulletin 737-57A1271, Revision 3, dated February 13, 2012,
except as required by paragraphs (r) and (v) of this AD. Performing
these inspections terminates the requirements of paragraphs (g),
(j), (l), (m), and (n) of this AD. Do all applicable corrective
actions before further flight.
    (1) Detailed inspection for damage (cracks, nicks, corrosion
pits, galling, pieces broken off) and stop-drill repairs along the
full length of the upper and lower flanges of the flap track.
    (2) Detailed inspection for damage, cracking, and stop-drill
repairs along the full length of the track webs.
    (3) Eddy current inspection for damage (including cracking) of
the flap track web and flanges.
    (4) Inspection to determine the part number of the flap track
assembly.

(q) New Compliance Time

    At the latest of the applicable times specified in paragraphs
(q)(1), (q)(2), and (q)(3) of this AD, do the actions required by
paragraph (p) of this AD.
    (1) Within 96 months since the flap track was new or overhauled,
or prior to the accumulation of 15,000 flight cycles on the flap
track since new or overhauled, whichever occurs first.
    (2) Within 180 days after the effective date of this AD.
    (3) Within 24 months after the most recent inspection was
performed using Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-57A1249, including Appendix A, dated
December 16, 1999; or Boeing Service Bulletin 737-57A1249, Revision
1, including Appendix A, dated June 1, 2000.

(r) New Replacement

    If, during any inspection required by paragraph (p) of this AD,
any flap track assembly having P/N 65-46428-31 or 65-46428-33 is
found, before further flight, replace the flap track assembly with a
new or serviceable flap track assembly, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 737-57A1271,
Revision 3, dated February 13, 2012, except as required by paragraph
(v) of this AD.

(s) New Inspections of Flap-to-Wing Attachment if Repairs Are Done or
if No Damage Is Found in Flap Track Web and Flanges

    For airplanes on which no damage is found in the flanges or the
web during any inspection required by paragraph (p) of this AD; and
for airplanes on which a repair is done during any corrective action
required by paragraph (p) of this AD: Before further flight, do the
inspections specified in paragraphs (s)(1) through (s)(4) of this
AD, and do all applicable related investigative and corrective
actions, in accordance with paragraphs 3.B.4., ``Inspection--With
Track-to-Wing Attachment Assembled,'' and 3.B.5., ``Inspection--With
Track-to-Wing Attachment Disassembled,'' of the Accomplishment
Instructions of Boeing Service Bulletin 737-57A1271, Revision 3,
dated February 13, 2012, except as required by paragraph (v) of this
AD. If, during the inspection required by paragraph (s)(1) of this
AD, an anti-fret strip is not found installed, before further
flight, do the related investigative actions specified in the
Accomplishment Instructions of Boeing Service Bulletin 737-57A1271,
Revision 3, dated February 13, 2012. If, during the inspection
required by paragraph (s)(1) of this AD, an anti-fret strip is found
with signs of damage or corrosion, before further flight, do all
applicable corrective actions, including making and installing a new
anti-fret strip, in accordance with paragraph 3.B.5., ``Inspection--
With Track-to-Wing Attachment Disassembled,'' of the Accomplishment
Instructions of Boeing Service Bulletin 737-57A1271, Revision 3,
dated February 13, 2012, except as required by paragraph (v) of this
AD. Do all applicable related investigative and corrective actions
before further flight.
    (1) Detailed inspection for signs of movement between the
tapered shim and anti-fret strip, installation of the anti-fret
strip, and corrosion of the tapered shim and anti-fret strip.
    (2) Detailed inspection for signs of movement, cracks and
corrosion of the area where the track is attached to the wing rear
spar.
    (3) High frequency eddy current inspection for cracking of the
outboard edge of the track adjacent to the outboard attach bolt.
    (4) Ultrasonic inspection for cracking of the inner edge of the
track adjacent to the outboard attach bolt.

(t) New Overhaul

    Within 10,000 flight cycles on the flap track or 48 months,
whichever occurs first, after accomplishing the inspection required
by paragraph (p) of this AD: Do an overhaul of the flap track, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-57A1271, Revision 3, dated February 13, 2012, except as
required by paragraph (v) of this AD. Repeat the overhaul thereafter
at intervals not to exceed 20,000 flight cycles on the flap track or
96 months, whichever occurs first.

(u) New Post-Overhaul Inspections

    For airplanes on which any overhaul required by paragraph (t) of
this AD is done: Do the inspections specified in paragraph (p) of
this AD within 10,000 flight cycles on the flap track or 48 months
after the most recent overhaul, whichever occurs first. Repeat the
inspections specified in paragraph (p) of this AD thereafter at
intervals not to exceed 10,000 flight cycles on the flap track or 48
months, whichever occurs first; except that if an overhaul required
by paragraph (t) of this AD is done, do the next inspection within
10,000 flight cycles or 48 months, whichever occurs first, after the
overhaul.

(v) Service Information Exception

    Where Boeing Service Bulletin 737-57A1271, Revision 3, dated
February 13, 2012, specifies to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (y) of this
AD.

(w) New Parts Installation Prohibition

    As of the effective date of this AD, no person may install a
flap track assembly, P/N 65-46428-31 or 65-46428-33, on any
airplane.

(x) New Credit for Previous Actions in Paragraphs (p) Through (t) of
This AD

    This paragraph provides credit for the actions specified in
paragraphs (p) through (t) of this AD, if those actions were
performed before the effective date of this AD using the service
bulletin specified in paragraph (x)(1), (x)(2), or (x)(3) of this
AD.
    (1) Boeing Alert Service Bulletin 737-57A1271, dated September
11, 2003, which is not incorporated by reference in this AD.
    (2) Boeing Service Bulletin 737-57A1271, Revision 1, dated July
30, 2008, which is not incorporated by reference in this AD.
    (3) Boeing Service Bulletin 737-57A1271, Revision 2, dated
January 17, 2011, which is not incorporated by reference in this AD.

(y) Alternative Methods of Compliance (AMOCs)

    (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 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 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) AMOCs approved previously in accordance with ADs 2000-25-07,
Amendment 39-12041 (65 FR 78913, December 18, 2000); and 2002-05-07,
Amendment 39-12675 (67 FR 11891, March 18, 2002); are approved as
AMOCs for the corresponding requirements of this AD.

(z) Related Information

    For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(aa) 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 13, 2013.
    (i) Boeing Service Bulletin 737-57A1271, Revision 3, dated
February 13, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on
April 22, 2002 (67 FR 11891, March 18, 2002).
    (i) Boeing Service Bulletin 737-57A1249, Revision 1, including
Appendix A, dated June 1, 2000.
    (ii) Reserved.
    (5) The following service information was approved for IBR on
January 2, 2001 (65 FR 78913, December 18, 2000).
    (i) Boeing All Operator Message M-7200-00-01854, dated July 27,
2000.
    (ii) Reserved.
    (6) 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.
    (7) 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.
    (8) 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 April 19, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10006 Filed 5-8-13; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 208 (Monday, October 30, 2017)]
[Notices]
[Pages 50125-50126]
[FR Doc No: 2017-23553]

=======================================================================
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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings #1

    Take notice that the Commission received the following electric
corporate filings:
    Docket Numbers: EC17-184-000.
    Applicants: Puget Sound Energy, Inc., Macquarie Infrastructure
Partners Inc.
    Description: Supplement to September 19, 2017 Application for
Authorization Under Section 203 of the Federal Power Act of Puget Sound
Energy, Inc., et al.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5173.
    Comments Due: 5 p.m. ET 10/30/17.

    Take notice that the Commission received the following electric
rate filings:

    Docket Numbers: ER08-1281-013.
    Applicants: New York Independent System Operator, Inc.
    Description: Motion to Terminate the Reporting Obligation of the
New York Independent System Operator, Inc.
    Filed Date: 3/27/2017.
    Accession Number: 20170327-5298.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER17-2027-001.
    Applicants: Southwest Power Pool, Inc.
    Description: Tariff Amendment: Deficiency Response--Integrated
Transmission Planning Process Tariff Revisions to be effective 10/1/
2017.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5477.
    Comments Due: 5 p.m. ET 11/13/17.

    Docket Numbers: ER17-2560-001.
    Applicants: Avista Corporation.
    Description: Tariff Amendment: Avista Corp NITSA BPA Kalispel SA T-
1140 Amendment to be effective 10/1/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5114.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-135-000.
    Applicants: AEP Texas Inc.
    Description: Sec.  205(d) Rate Filing: AEP TX-Oncor IA Second
Amended & Restated to be effective 9/26/2017.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5475.
    Comments Due: 5 p.m. ET 11/13/17.

    Docket Numbers: ER18-136-000.
    Applicants: Midcontinent Independent System Operator, Inc.
    Description: Sec.  205(d) Rate Filing: 2017-10-23_Revisions to
MISO-PJM JOA to address congestion overlap issues to be effective 3/1/
2018.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5483.
    Comments Due: 5 p.m. ET 11/13/17.

    Docket Numbers: ER18-137-000.
    Applicants: PJM Interconnection, L.L.C.
    Description: Sec.  205(d) Rate Filing: Revisions to MISO-PJM JOA
re: Overlapping Congestion Charges to be effective 3/1/2018.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5484.
    Comments Due: 5 p.m. ET 11/13/17.

    Docket Numbers: ER18-138-000.
    Applicants: First Solar Development, LLC.
    Description: Petition for Limited Waiver of Tariff Submission
Deadline of First Solar Development, LLC.
    Filed Date: 10/23/17.
    Accession Number: 20171023-5628.
    Comments Due: 5 p.m. ET 11/6/17.

    Docket Numbers: ER18-139-000.
    Applicants: PJM Interconnection, L.L.C.
    Description: Sec.  205(d) Rate Filing: Amendment to ISA No. 3198
and CSA Nos. 2642 and 2643; Queue No. T157/W4-037 to be effective 9/1/
2010.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5072.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-140-000.
    Applicants: Lackawanna Energy Center LLC.
    Description: Baseline eTariff Filing: Application for Market-Based
Rate Authorization to be effective 12/24/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5079.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-141-000.
    Applicants: Southern California Edison Company.
    Description: Sec.  205(d) Rate Filing: LGIA Alamitos Energy Center
Project SA No 197 to be effective 10/25/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5080.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-142-000.
    Applicants: Southern California Edison Company.
    Description: Sec.  205(d) Rate Filing: LGIA Huntington Beach Energy
Project SA No 196 to be effective 10/25/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5081.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-143-000.
    Applicants: PJM Interconnection, L.L.C.
    Description: Sec.  205(d) Rate Filing: Revisions to OATT 10.4 and
OA 15.6 RE: Limitation on Claims to be effective 12/23/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5084.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-144-000.
    Applicants: Southern California Edison Company.
    Description: Sec.  205(d) Rate Filing: Interconnection Agreement
Bob Switch-Eldorado 220-kV Transmission Line to be effective 10/25/
2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5112.
    Comments Due: 5 p.m. ET 11/14/17.

    Docket Numbers: ER18-145-000.
    Applicants: Midcontinent Independent System Operator, Inc.
    Description: Sec.  205(d) Rate Filing: 2017-10-24_SA 2637 Border
Winds-NSP E&P (J290) Termination to be effective 10/25/2017.
    Filed Date: 10/24/17.
    Accession Number: 20171024-5127.
    Comments Due: 5 p.m. ET 11/14/17.

    The filings are accessible in the Commission's eLibrary system by
clicking on the links or querying the docket number.
    Any person desiring to intervene or protest in any of the above
proceedings must file in accordance with Rules 211 and 214 of the
Commission's Regulations (18 CFR 385.211 and 385.214) on or before 5:00
p.m. Eastern time on the specified comment date. Protests may be
considered, but

intervention is necessary to become a party to the proceeding.
    eFiling is encouraged. More detailed information relating to filing
requirements, interventions, protests, service, and qualifying
facilities filings can be found at: http://www.ferc.gov/docs-filing/efiling/filing-req.pdf. For other information, call<PHONE_NUMBER>
(toll free). For TTY, call<PHONE_NUMBER>.

    Dated: October 24, 2017.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2017-23553 Filed 10-27-17; 8:45 am]
 BILLING CODE 6717-01-P