[Federal Register Volume 85, Number 23 (Tuesday, February 4, 2020)]
[Notices]
[Pages 6252-6254]
[FR Doc No: 2020-02050]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-88077; File No. SR-FINRA-2020-003]

Self-Regulatory Organizations; Financial Industry Regulatory
Authority, Inc.; Notice of Filing and Immediate Effectiveness of
Proposed Rule Change To Extend the Effective Date for Eliminating
Computer-to-Computer Interface as a Technological Option for TRACE
Reporting

January 29, 2020.
    Pursuant to Section 19(b)(1) of the Securities Exchange Act of 1934
(``Act'') \1\ and Rule 19b-4 thereunder,\2\ notice is hereby given that
on January 28, 2020, Financial Industry Regulatory Authority, Inc.
(``FINRA'') filed with the Securities and Exchange Commission (``SEC''
or ``Commission'') the proposed rule change as described in Items I and
II below, which Items have been prepared by FINRA. FINRA has designated
the proposed rule change as constituting a ``non-controversial'' rule
change under paragraph (f)(6) of Rule 19b-4 under the Act,\3\ which
renders the proposal effective upon receipt of this filing by the
Commission. The Commission is publishing this notice to solicit
comments on the proposed rule change from interested persons.
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    \1\ 15 U.S.C. 78s(b)(1).
    \2\ 17 CFR 240.19b-4.
    \3\ 17 CFR 240.19b-4(f)(6).
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I. Self-Regulatory Organization's Statement of the Terms of Substance
of the Proposed Rule Change

    FINRA is proposing to provide members with additional time to
migrate their trade reporting processes to connect to TRACE through a
permissible means other than Computer-to-Computer Interface (``CTCI'').
    The text of the proposed rule change is available on FINRA's
website at http://www.finra.org, at the principal office of FINRA and
at the Commission's Public Reference Room.

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

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

and C below, of the most significant aspects of such statements.

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

1. Purpose
    On October 4, 2018, the SEC approved SR-FINRA-2018-030 which
amended FINRA Rule 7730 (Trade Reporting and Compliance Engine (TRACE))
to remove CTCI as a technological means of connectivity for reporting
transactions to TRACE.\4\ Since filing SR-FINRA-2018-030 (``CTCI
Elimination Filing''),\5\ FINRA has engaged in extensive outreach to
industry participants in connection with eliminating CTCI as a means of
connectivity, including direct outreach to the firms that used CTCI for
reporting, either directly or via a service bureau.
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    \4\ See Securities Exchange Act Release No. 84366, 83 FR 51514
(October 11, 2018) (Order Approving File No. SR-FINRA-2018-030).
    \5\ See Securities Exchange Act Release No. 83868 (August 17,
2018), 83 FR 42741 (August 23, 2018) (Notice of Filing of SR-FINRA-
2018-030).
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    FINRA recently has become aware that some firms have experienced
trade rejects after migrating from CTCI to FIX. FINRA understands that
the cause of these rejects is related to the validations done on a FIX
port to prevent duplicate trade reports from being submitted to the
system. These validations are specific to FIX messaging and, as such,
were not anticipated by certain firms migrating from CTCI to FIX. FINRA
understands that this issue is impacting the successful migration of
member firms whose activity, in the aggregate, account for a
significant percentage of TRACE reports (i.e., over 10 percent of
monthly trade reports). As a result, FINRA is filing the proposed rule
change to extend the effective date of the CTCI Elimination Filing
until March 16, 2020, which will allow firms adequate time to perform
the required coding changes and testing. FINRA will continue to work
closely with all firms that have not yet successfully migrated from
CTCI, and expects firms to ensure adequate testing and to continue to
work expeditiously to migrate as soon as possible in advance of the
March 16, 2020 date.
    FINRA has filed the proposed rule change for immediate
effectiveness and has requested that the SEC waive the requirement that
the proposed rule change not become operative for 30 days after the
date of the filing, so FINRA can implement the proposed rule change
immediately. The new operative date of the amendments adopted by SR-
FINRA-2018-030 will be March 16, 2020.
2. Statutory Basis
    FINRA believes that the proposed rule change is consistent with the
provisions of Section 15A(b)(6) of the Act,\6\ which requires, among
other things, that FINRA rules must be designed to prevent fraudulent
and manipulative acts and practices, to promote just and equitable
principles of trade, and, in general, to protect investors and the
public interest. Specifically, the proposed rule change provides
additional time for members who have not yet successfully migrated to a
permissible means of connectivity other than CTCI for reporting
transactions to TRACE. The proposed rule change will allow members to
continue to report transactions to TRACE through CTCI for a modest
additional period of time, which FINRA believes is reasonable in light
of technological difficulties identified recently. Thus, this extension
will facilitate efficient and uninterrupted trade reporting as firms
make coding refinements and complete a successful migration.
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    \6\ 15 U.S.C. 78o-3(b)(6).
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B. Self-Regulatory Organization's Statement on Burden on Competition

    FINRA does not believe that the proposed rule change will result in
any burden on competition that is not necessary or appropriate in
furtherance of the purposes of the Act. The proposed rule change would
provide additional time to all members who have not yet successfully
migrated to a permissible means of connectivity other than CTCI for
reporting transactions to TRACE. FINRA also notes that this extension
does not impact or require any changes by firms that already
successfully migrated to a permissible means of connectivity other than
CTCI for reporting transactions to TRACE.

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

    Written comments were neither solicited nor received.

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

    Because the foregoing proposed rule change does not: (i)
Significantly affect the protection of investors or the public
interest; (ii) impose any significant burden on competition; and (iii)
become operative for 30 days from the date on which it was filed, or
such shorter time as the Commission may designate, it has become
effective pursuant to Section 19(b)(3)(A) of the Act \7\ and Rule 19b-
4(f)(6) thereunder.\8\
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    \7\ 15 U.S.C. 78s(b)(3)(A).
    \8\ 17 CFR 240.19b-4(f)(6). In addition, Rule 19b-4(f)(6)(iii)
requires a self-regulatory organization to give the Commission
written notice of its intent to file the proposed rule change, along
with a brief description and text of the proposed rule change, at
least five business days prior to the date of filing of the proposed
rule change, or such shorter time as designated by the Commission.
The Commission is waiving the requirement in this case.
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    FINRA has asked the Commission to waive the 30-day operative delay
so that the proposal may become operative immediately upon filing. The
Commission believes that waiving the 30-day operative delay is
consistent with the protection of investors and the public interest. If
the proposed rule change did not become operative immediately, certain
member firms that currently report to TRACE using the CTCI protocol
might be unable to report successfully if CTCI were decommissioned on
February 3, 2020, as originally planned. This could result in
significant degradation of the TRACE information available to
regulators and the public. Allowing the proposal to become immediately
operative will enable these firms to continue reporting using the CTCI
protocol while the necessary technological changes continue to be made
for them to fully transition to other reporting protocols. For these
reasons, the Commission hereby waives the 30-day operative delay and
designates the proposed rule change as operative upon filing.\9\
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    \9\ For purposes only of waiving the 30-day operative delay, the
Commission also has considered the proposed rule's impact on
efficiency, competition, and capital formation. See 15 U.S.C.
78c(f).
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    At any time within 60 days of the filing of the proposed rule
change, the Commission summarily may temporarily suspend such rule
change if it appears to the Commission that such action is necessary or
appropriate in the public interest, for the protection of investors, or
otherwise in furtherance of the purposes of the Act. If the Commission
takes such action, the Commission shall institute proceedings to
determine whether the proposed rule change should be approved or
disapproved.

IV. Solicitation of Comments

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

Electronic Comments

     Use the Commission's internet comment form (http://www.sec.gov/rules/sro.shtml); or
     Send an email to<EMAIL_ADDRESS>Please include
File Number SR-FINRA-2020-003 on the subject line.

Paper Comments

     Send paper comments in triplicate to Secretary, Securities
and Exchange Commission, 100 F Street NE, Washington, DC 20549-1090.

All submissions should refer to File Number SR-FINRA-2020-003. This
file number should be included on the subject line if email is used. To
help the Commission process and review your comments more efficiently,
please use only one method. The Commission will post all comments on
the Commission's internet website (http://www.sec.gov/rules/sro.shtml).
Copies of the submission, all subsequent amendments, all written
statements with respect to the proposed rule change that are filed with
the Commission, and all written communications relating to the proposed
rule change between the Commission and any person, other than those
that may be withheld from the public in accordance with the provisions
of 5 U.S.C. 552, will be available for website viewing and printing in
the Commission's Public Reference Room, 100 F Street NE, Washington, DC
20549, on official business days between the hours of 10:00 a.m. and
3:00 p.m. Copies of such filing also will be available for inspection
and copying at the principal office of FINRA. All comments received
will be posted without change. Persons submitting comments are
cautioned that we do not redact or edit personal identifying
information from comment submissions. You should submit only
information that you wish to make available publicly. All submissions
should refer to File Number SR-FINRA-2020-003 and should be submitted
on or before February 25, 2020.

    For the Commission, by the Division of Trading and Markets,
pursuant to delegated authority.\10\
J. Matthew DeLesDernier,
Assistant Secretary.

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    \10\ 17 CFR 200.30-3(a)(12).
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[FR Doc. 2020-02050 Filed 2-3-20; 8:45 am]
 BILLING CODE 8011-01-P


[Federal Register Volume 78, Number 101 (Friday, May 24, 2013)]
[Rules and Regulations]
[Pages 31389-31394]
[FR Doc No: 2013-10797]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0855; Directorate Identifier 2011-NM-136-AD;
Amendment 39-17452; AD 2013-09-10]
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 an existing airworthiness directive (AD)
for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. That AD currently requires repetitive
inspections to detect cracking of the lower corners of the door frame
and cross beam of the forward cargo door, and corrective actions if
necessary. That AD also requires eventual modification of the outboard
radius of the lower corners of the door frame and reinforcement of the
cross beam of the forward cargo door, which terminates the existing
repetitive inspections. This new AD revises the compliance times for
the preventive modification; adds certain inspections for cracks in the
number 5 cross beam of the forward cargo door; and adds inspections of
the number 4 cross beam if cracks are found in the number 5 cross beam,
and corrective actions if necessary. For certain airplanes, this

new AD also adds a one-time inspection for airplanes previously
modified or repaired, and a one-time inspection of the reinforcement
angle for excessive shimming or fastener pull-up, and corrective
actions if necessary. This AD was prompted by additional reports of
fatigue cracking in the radius of the lower frames and in the lower
number 5 cross beam of the forward cargo door. We are issuing this AD
to prevent fatigue cracking of the lower corners of the door frame and
number 5 cross beam of the forward cargo door, which could result in
rapid depressurization of the airplane.

DATES: This AD is effective June 28, 2013.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 28, 2013.
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 16,
2000 (65 FR 19302, April 11, 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, Washington 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, 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 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6450; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness directive (AD) 2000-07-06, Amendment
39-11660 (65 FR 19302, April 11, 2000). That AD applies to the
specified products. The NPRM published in the Federal Register on
August 21, 2012 (77 FR 50407). The NPRM proposed to continue to require
repetitive inspections to detect cracking of the lower corners of the
door frame and cross beam of the forward cargo door, and corrective
actions if necessary. The NPRM also proposed to continue to require
eventual modification of the outboard radius of the lower corners of
the door frame and reinforcement of the cross beam of the forward cargo
door, which would constitute terminating action for the existing
repetitive inspections. Additionally, the NPRM proposed to revise the
compliance times for the preventive modification; add certain
inspections for cracks in the number 5 cross beam of the forward cargo
door; and add inspections of the number 4 cross beam if cracks are
found in the number 5 cross beam, and corrective actions if necessary.
For certain airplanes, the NPRM also proposed to add a one-time
inspection for airplanes previously modified or repaired, and a one-
time inspection of the reinforcement angle for excessive shimming or
fastener pull-up, and corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 50407, August 21, 2012) and the FAA's response to each comment.

Comment Regarding Winglet Supplemental Type Certificate (STC)

    Aviation Partners Boeing stated that 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 ability to accomplish the service information or the
NPRM (77 FR 50407, August 21, 2012).
    We have revised paragraph (c) in this final rule, by adding new
paragraph (c)(2), to state that installation of 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'' AMOC approval request is not necessary to comply
with the requirements of 14 CFR 39.17. For all other AMOC requests,
however, the operator must request approval for an AMOC in accordance
with the procedures specified in paragraph (n) of this AD.

Request To Add New Requirements

    Boeing asked that we add a new paragraph (k) to the NPRM (77 FR
50407, August 21, 2012) titled ``New Inspections and Corrective Actions
to Ensure Cross Beam Reinforcement,'' and suggested language for that
new requirement. Boeing stated that the intent of the NPRM and Boeing
Alert Service Bulletin 737-52A1100, Revision 5, dated February 14,
2011, is to ensure that all forward cargo doors have the reinforcing
modifications installed on both the beam and the frame at the forward
and aft lower corners of the door. Boeing added that the current
language in the NPRM and this service information leave open the
potential that some doors might not have the reinforcing modification
on the aft end of the cross beam, even though the doors were modified
as specified in Boeing Service Bulletin 737-52-1100, dated August 25,
1988, or Revision 1, dated July 20, 1989; or in accordance with the
requirements of AD 90-06-02, Amendment 39-6489 (55 FR 8372, March 7,
1990).
    We do not agree with the commenter's request to add a new
requirement to this AD. Boeing Service Bulletin 737-52-1100, dated
August 25, 1988; and Revision 1, dated July 20, 1989; includes
modifications of the forward corner of the door frame and forward end
of the lower cross beam, but no modifications of the aft end of the
door. Modifications of the aft corner of the door frame and aft end of
the lower cross beam were added in Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994. Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994, was required by paragraph (c) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), as
terminating action for the repetitive inspections. Paragraph (c) of AD
2000-07-06 is restated in paragraph (i) of this AD, and addresses
airplanes on which no modification was accomplished previously.
    The intent of paragraph (d) of AD 2000-07-06, Amendment 39-11660
(65 FR 19302, April 11, 2000), which is restated in paragraph (j) of
this AD, was to address airplanes on which a

modification was previously accomplished in accordance with Boeing
Service Bulletin 737-52-1100, dated August 25, 1988; or Revision 1,
dated July 20, 1989; and to ensure that both the forward and aft ends
of the lower beam of the door were modified, as well as the forward and
aft corners of the door frame. Therefore, Boeing Service Bulletin 737-
52-1100, Revision 2, dated March 31, 1994, was required by AD 2000-07-
06 for those modifications. However, paragraph (d) of AD 2000-07-06 and
paragraph (j) of this AD do not specify modifying the aft end of the
lower beam.
    We have made no change to the AD in regard to Boeing's request.
However, we are considering proposing additional rulemaking in the near
future to address this issue.

Explanation of Change to Final Rule

    We have changed paragraph (g) of this final rule to specify
performing the inspection in accordance with Boeing 737 Nondestructive
Test (NDT) Manual, D6-37239, Part 6, Section 51-00-00, Procedure 4 or
Procedure 23, Revision 108, dated November 15, 2012, as applicable. The
subject procedures were referred to as figures in the NPRM (77 FR
50407, August 21, 2012). Because of a publishing system change in this
revision of the NDT manual, the term ``figure'' was changed to
``procedure.'' The technical instructions in the NDT manual were not
changed.

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 change described previously. We also determined that
this change 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 581 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
----------------------------------------------------------------------------------------------------------------
Inspections retained from AD 2000- 1 work-hour x $85                $0  $85 per inspection   $49,385 per
 07-06, Amendment 39-11660 (65 FR   per hour = $85 per                   cycle.               inspection cycle.
 19302, April 11, 2000).            inspection cycle.
Modification retained from AD      18 work-hours x $85          $1,865  $3,395.............  $1,972,495.
 2000-07-06.                        per hour = $1,530.
Inspections, new action..........  9 work-hours x $85               $0  $765...............  $444,465.
                                    per hour = $765.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification..................................  84 work-hours x $85 per hour =           $12,395         $19,535
                                                 $7,140.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs/replacements 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

    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 the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD)
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), and
adding the following new AD:

2013-09-10 The Boeing Company: Amendment 39-17452; Docket No. FAA-
2012-0855; Directorate Identifier 2011-NM-136-AD.

(a) Effective Date

    This AD is effective June 28, 2013.

(b) Affected ADs

    This AD supersedes AD 2000-07-06, Amendment 39-11660 (65 FR
19302, April 11, 2000).

(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 52, Doors.

(e) Unsafe Condition

    This AD was prompted by additional reports of fatigue cracking
in the radius of the lower frames and in the lower number 5 cross
beam of the forward cargo door. We are issuing this AD to prevent
fatigue cracking of the lower corners of the door frame and number 5
cross beam of the forward cargo door, which could result in rapid
depressurization of the airplane.

(f) Compliance

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

(g) Retained High Frequency Eddy Current (HFEC) Initial/Repetitive
Inspections

    This paragraph restates the requirements of paragraph (a) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 1 year or 4,500 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, perform an HFEC inspection to detect cracking of the
lower corners (forward and aft) of the door frame of the forward
cargo door, in accordance with Figure 4 or Figure 23, of Section 51-
00-00, of Part 6, of Boeing 737 Nondestructive Test (NDT) Manual,
D6-37239, dated August 5, 1997, as applicable; or Procedure 4 or
Procedure 23, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, Revision 108, dated
November 15, 2012; as applicable.

    Note 1 to paragraphs (g), (h), (i), and (j) of this AD:
Accomplishment of Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994, does not supersede the requirements of AD 90-
06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990).

    (1) If no cracking is detected, repeat the HFEC inspection
thereafter at intervals not to exceed 4,500 flight cycles, until the
requirements of paragraph (i) of this AD have been accomplished.
    (2) If any cracking is detected during any inspection required
by paragraph (g) of this AD, prior to further flight, accomplish the
requirements of paragraphs (g)(2)(i) and (g)(2)(ii) of this AD,
which constitute terminating action for the repetitive inspections
required by paragraph (g)(1) of this AD.
    (i) Accomplish the requirements of paragraph (g)(2)(i)(A) or
(g)(2)(i)(B) of this AD, and install a cross beam repair and
reinforcement modification of the cross beam, in accordance with
Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31,
1994.
    (A) Repair the door frame of the forward cargo door in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), Transport Airplane Directorate, FAA; or
in accordance with data meeting the type certification basis of the
airplane approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make such findings. For a repair or
modification method to be approved by the Manager, Seattle ACO, as
required by this paragraph, and paragraphs (g)(2)(ii), (h)(2),
(h)(3)(ii), and (i)(2) of this AD, the Manager's approval letter
must specifically reference this AD.
    (B) Replace the door frame of the forward cargo door with a new
door frame, in accordance with Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994.
    (ii) Modify the repaired or replaced door frame of the forward
cargo door, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings.

(h) Retained Initial Detailed Inspection and Repetitive Inspections

    This paragraph restates the requirements of paragraph (b) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). Within
1 year or 4,500 flight cycles after May 16, 2000 (the effective date
of AD 2000-07-06), whichever occurs later, perform a detailed
inspection to detect cracking of the cross beam (i.e., upper and
lower chord and web sections) of the forward cargo door, in
accordance with Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994. For the purposes of this AD, a detailed
inspection is: An intensive examination of a specific item,
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.
Inspection aids such as mirror, magnifying lenses, etc., may be
necessary. Surface cleaning and elaborate procedures may be
required.
    (1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 4,500 flight cycles until the
requirements of paragraph (i) of this AD have been accomplished.
    (2) If any cracking is detected on the lower chord section of
the cross beam during any inspection required by paragraph (h) of
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Seattle ACO, or in accordance with data
meeting the type certification basis of the airplane approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings.
    (3) If any cracking is detected on any area excluding the lower
chord section of the cross beam (i.e., upper chord and web section)
during any inspection required by paragraph (h) of this AD, prior to
further flight, accomplish the requirements of paragraph (h)(3)(i)
or (h)(3)(ii) of this AD, as applicable, which constitutes
terminating action for the repetitive inspections required by
paragraph (h)(1) of this AD.
    (i) For airplanes with line numbers 1 through 1231 inclusive:
Install a cross beam repair and preventative modification of the
outboard radius of the lower corners (forward and aft) of the door
frame, in accordance with Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994.
    (ii) For airplanes with line numbers 1232 and subsequent:
Install a cross beam repair and preventative modification of the
outboard radius of the lower corners (forward and aft) of the door
frame, in accordance with a method approved by the Manager, Seattle
ACO, or in accordance with data meeting the type certification basis
of the airplane approved by the Boeing Commercial Airplanes ODA that
has been authorized by the Manager, Seattle ACO, to make those
findings.

(i) Retained Terminating Action

    This paragraph restates the requirements of paragraph (c) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later: Install the preventative modification of the outboard
radius of the lower corners (forward and aft) of the door frame and
the reinforcement modification of the cross beam of the forward
cargo door, in accordance with paragraph (i)(1) or (i)(2) of this
AD, as applicable. Accomplishment of paragraph (i)(1) or (i)(2) of
this AD, as applicable, constitutes terminating action for the
repetitive inspections required by paragraphs (g)(1) and (h)(1) of
this AD.

    (1) For airplanes with line numbers 1 through 1231 inclusive:
Accomplish the preventative modification and the reinforcement
modification, in accordance with Boeing Service Bulletin 737-52-
1100, Revision 2, dated March 31, 1994.
    (2) For airplanes with line numbers 1232 and subsequent:
Accomplish the preventative modification and the reinforcement
modification, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings; or in accordance with Boeing
Alert Service Bulletin 737-52A1100, Revision 5, dated February 14,
2011. As of the effective date of this AD, use only Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011,
to accomplish the modifications required by this paragraph.

(j) Retained Action for Airplanes on Which Modifications Were
Accomplished Previously

    This paragraph restates the requirements of paragraph (d) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). For
all airplanes on which modifications of the forward lower corner of
the door frame and the cross beam of the forward cargo door were
accomplished as specified in Boeing Service Bulletin 737-52-1100,
dated August 25, 1988, or Revision 1, dated July 20, 1989; or in
accordance with the requirements of AD 90-06-02, Amendment 39-6489
(55 FR 8372, March 7, 1990): Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, install the reinforcement modification of the aft
corner of the door frame of the forward cargo door, in accordance
with Boeing Service Bulletin 737-52-1100, Revision 2, dated March
31, 1994. Accomplishment of such modification constitutes
terminating action for the repetitive inspections required by
paragraphs (g)(1) and (h)(1) of this AD.

(k) New Inspections and Corrective Actions

    Except as provided by paragraphs (m)(1) and (m)(2) of this AD:
At the applicable time specified in paragraph 1.E, ``Compliance,''
of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011, do the inspections required by paragraphs (k)(1)
and (k)(2) of this AD, as applicable. Do all applicable related
investigative and corrective actions before further flight, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011;
except as required by paragraph (m)(3) of this AD. Accomplishment of
the inspections required by paragraph (k) of this AD terminates the
requirements of the repetitive inspections required by paragraphs
(g)(1) and (h)(1) of this AD. If any cracking is found in the number
4 cross beam, before further flight, repair in accordance with
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003.

    Note 2 to paragraph (k) of this AD:  Boeing Alert Service
Bulletin 737-52A1100, Revision 5, dated February 14, 2011, refers to
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003, as an additional source of guidance for the
inspection for cracks of the number 4 cross beam.

    (1) For airplanes identified in Tables 1 and 2 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time HFEC inspection
of the applicable location for cracks, in accordance with the Work
Instructions, Part I, of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011.
    (2) For airplanes identified in Table 3 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time general visual
inspection of the reinforcement angle for excessive shimming or
fastener pull-up, in accordance with the Work Instructions, Part
III, of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011.

(l) No Supplemental Structural Inspections Required by This AD

    (1) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' and Part 5 of the Accomplishment
Instructions, of Boeing Alert Service Bulletin 737-52A1100, Revision
5, dated February 14, 2011, are not required by this AD.
    (2) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1100, Revision 5, dated February 14, 2011, may be used in
support of compliance with section 121.1109(c)(2) or 129.109(b)(2)
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(b)(2)). The corresponding actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1100, Revision 5, dated February 14, 2011, are not required by
this AD.

(m) Exceptions to Certain Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011,
specifies a compliance time relative to the Revision 5 issue date of
that service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
    (2) Where Table 1, ``Condition'' column of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011, specifies ``airplanes without
either the repair or modification accomplished in accordance with
previous releases of this service bulletin,'' the corresponding
condition in this AD is for ``airplanes on which either a repair or
modification was not accomplished before the effective date of this
AD.''
    (3) Where Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011, specifies to contact Boeing for certain
actions: Before further flight, do the repair using a method
approved in accordance with the procedures specified in paragraph
(n)(1) of this AD.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, 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 AD 2000-07-06,
Amendment 39-11660 (65 FR 19302, April 11, 2000), are approved as
AMOCs for the corresponding requirements of this AD.

(o) Related Information

    (1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone (425)
917-6450; fax<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) 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>; 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>.

(p) 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 28, 2013.
    (i) Procedure 4, ``Surface Inspection of Aluminum Parts (Meter
Display),'' of Section 51-00-00, of Part 6, ``Eddy Current,'' of
Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, Revision 108,
dated November 15, 2012. The revision level of this document is
identified only in the letter of transmittal; no other page of this
document contains this information.

    (ii) Procedure 23, ``Aluminum Part Surface Inspection (Impedance
Plane Display),'' Section 51-00-00, of Part 6, ``Eddy Current,'' of
Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, Revision 108,
dated November 15, 2012. The revision level of this document is
identified only in the letter of transmittal; no other page of this
document contains this information.
    (iii) Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011.
    (iv) Boeing Special Attention Service Bulletin 737-52-1149,
dated December 11, 2003.
    (4) The following service information was approved for IBR on
May 16, 2000 (65 FR 19302, April 11, 2000).
    (i) Figure 4, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, dated August 5, 1997.
The revision level is not specified on the title page or list of
effective pages of this document. The title page of this document is
not dated. Pages 1 and 2 of the list of effective pages of this
document are dated August 5, 1997; page 2A is dated February 5,
1997.
    (ii) Figure 23, of Section 51-00-00, of Part 6, of Boeing 737
Nondestructive Test (NDT) Manual, D6-37239, dated August 5, 1997.
The revision level is not specified on the title page or list of
effective pages of this document. The title page of this document is
not dated. Pages 1 and 2 of the list of effective pages of this
document are dated August 5, 1997; page 2A is dated February 5,
1997.
    (iii) Boeing Service Bulletin 737-52-1100, Revision 2, dated
March 31, 1994.
    (5) For Boeing 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.
    (6) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, Washington 98057-3356. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.
    (7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on April 26, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10797 Filed 5-23-13; 8:45 am]
BILLING CODE 4910-13-P