Document ID: FAA-2015-3984-0005
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Co. Airplanes
Posted Date: 2016-11-14T05:00Z

[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)]
[Proposed Rules]
[Pages 79395-79400]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-22699]

[[Page 79395]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3984; Directorate Identifier 2015-NM-033-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

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

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SUMMARY: We are revising an earlier proposal to supersede Airworthiness 
Directive (AD) 2008-13-12 R1, for certain The Boeing Company Model 737-
100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-13-12 
R1 requires various repetitive inspections for cracking of the upper-
frame-to-side-frame splice of the fuselage, and other specified and 
corrective actions if necessary; and also provides for an optional 
preventive modification, which would terminate the repetitive 
inspections. This action revises the notice of proposed rulemaking 
(NPRM) by adding post-repair/post-modification inspections. We are 
proposing this SNPRM to detect and correct fatigue cracking of the 
upper-frame-to-side-frame splice of the fuselage, which could result in 
reduced structural integrity of the frame and adjacent lap joint, 
causing increased loading in the fuselage skin, which will accelerate 
skin crack growth and result in decompression of the airplane. Since 
these actions impose an additional burden over that proposed in the 
NPRM, we are reopening the comment period to allow the public the 
chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by December 29, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this SNPRM, 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 206-766-5680; Internet https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-3984.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3984; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 
425-917-6590; email: wayne.lockett@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3984; 
Directorate Identifier 2015-NM-033-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued an NPRM to amend 14 CFR part 39 to supersede AD 2008-13-
12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008) (``AD 2008-
13-12 R1''). AD 2008-13-12 R1 applied to certain The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 
2008-13-12 R1 requires various repetitive inspections for cracking of 
the upper-frame-to-side-frame splice of the fuselage, and other 
specified and corrective actions if necessary. AD 2008-13-12 R1 also 
provides for an optional preventive modification, which terminates the 
repetitive inspections. AD 2008-13-12 R1 resulted from a report that 
the upper frame of the fuselage was severed between stringers (S) S-13L 
and S-14L at station (STA) 747, and the adjacent frame at STA 767 had a 
1.3-inch-long crack at the same stringer location. The NPRM published 
in the Federal Register on October 9, 2015 (80 FR 61133) (``The 
NPRM''). The NPRM was prompted by reports of additional fatigue 
cracking of the upper-frame-to-side-frame splice of the fuselage, and 
one report of a severed frame. The NPRM proposed to add, for certain 
airplanes, an inspection to determine if the existing frame repair 
meets all specified requirements, and for certain other airplanes, a 
new modification of the upper-frame-to-side-frame splice, which would 
terminate the repetitive inspections. The NPRM also proposed to reduce 
certain inspection thresholds and repetitive intervals.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM, we have determined that it is necessary 
to require post-repair/post-modification inspections that were not 
included in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015. The service information describes procedures 
for various repetitive inspections for cracking of the upper-frame-to-
side-frame splice of the fuselage, a preventive modification to prevent 
WFD, an inspection to determine if the existing frame repair meets all 
specified requirements, and corrective actions. This service 
information is reasonably available because the interested parties

[[Page 79396]]

have access to it through their normal course of business or by the 
means identified in the ADDRESSES section.

Comments

    We gave the public the opportunity to comment on the NPRM. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment. One commenter supported the actions specified 
in the NPRM.

Request To Require Post-Repair/Post-Modification Inspections

    Boeing asked that we change paragraph (j) of the proposed AD (in 
the NPRM) to require the post-repair/post-modification inspections that 
are not required in that paragraph. Boeing stated that the WFD 
evaluation of the frame repair/modification specified in Boeing Alert 
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, 
indicated the need for reduced repetitive inspection intervals from 
those provided in Boeing Damage Tolerance Inspection Data Service 
Bulletin 737-00-1006, dated March 12, 2010. Boeing added that since the 
inspections specified in Boeing Service Bulletin 737-00-1006, dated 
March 12, 2010, are not to be used for the post-repair/post-
modification inspections required by 14 CFR 121.1109(c)(2) or 
129.109(c)(2), they should be required by paragraph (j) of the proposed 
AD.
    We agree with the commenter for the reasons provided. We have 
changed paragraph (j) of this SNPRM to require that post-repair/post-
modification inspections be done in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing the Supplemental 
Type Certificate (STC) ST01219SE does not affect the actions specified 
in the NPRM.
    We agree with the commenter. We have changed paragraph (c) of this 
proposed AD to state that installation of STC ST01219SE does not affect 
the ability to accomplish the actions required by this final rule. 
Therefore, for airplanes on which STC ST01219SE is installed, a 
``change in product'' alternative methods of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Request To Clarify That the NPRM Addresses WFD

    Boeing asked that we update the language in ``Actions Since AD 
2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008) Was 
Issued'' section of the NPRM to clarify that this action is intended to 
address WFD by supporting the airplane's limit of validity (LOV). 
Boeing noted that a recently issued WFD-related AD action used 
different language regarding WFD. Boeing stated that Boeing Alert 
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, was 
released in support of the requirements of 14 CFR 26.21(b) and (c) and 
provides additional service action required to support LOV.
    We agree to provide clarification. The NPRM addressed WFD in 
several locations in the preamble. To clarify, this action is intended 
to address WFD by supporting the airplane's LOV, as stated by Boeing. 
However, we have not updated the language in that section of the NPRM 
because that section of the NPRM is not carried over to this SNPRM. 
Therefore, no change to this SNPRM is necessary in this regard.

Request To Clarify Certain Procedures in the Related Service 
Information Section

    Boeing asked that we change the ``Related Service Information under 
1 CFR part 51'' section in the NPRM to clarify the description of the 
modification procedures in the service information. Boeing asked that 
the proposed language ``. . . a new preventive modification, which 
would eliminate the need for the repetitive inspections'' be changed to 
``. . . a preventive modification to prevent the WFD.'' Boeing stated 
that Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated 
January 30, 2015, retains all inspections specified in Boeing Alert 
Service Bulletin 737-53A1261, dated January 19, 2006, and mandates the 
previously optional preventive modification to mitigate the WFD 
concern.
    We agree with the commenter for the reasons provided. We have 
clarified the ``Related Service Information under 1 CFR part 51'' 
section of this SNPRM accordingly.

Request To Clarify Reason for Supersedure

    Boeing asked that we clarify in the SUMMARY section of the NPRM the 
events that prompted the proposed supersedure of AD 2008-13-12 R1. 
Boeing stated that instead of two reports of severed frames, as 
specified in the NPRM, there was just one report of a severed frame.
    We agree to provide clarification. We agree that the commenter's 
statement is accurate. However, we have removed details relating to the 
NPRM from the SUMMARY section of this SNPRM; therefore, no change is 
necessary to this SNPRM in this regard.

Request To Clarify Provisions Related to Repetitive Actions

    Boeing asked that we clarify paragraph (g)(1)(ii) of the proposed 
AD (in the NPRM) to state that the actions are to be repeated until the 
preventive modification in paragraph (k) or the terminating action in 
paragraph (l) of the proposed AD has been accomplished. Boeing added 
that this change is consistent with the provisions of Boeing Alert 
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, and 
the requirements of AD 2008-13-12 R1.
    We agree with the commenter for the reasons provided. We have 
clarified paragraph (g)(1)(ii) of this proposed AD accordingly.

Request To Clarify Inspection Locations

    Boeing asked that we change paragraph (g)(2)(i) of the proposed AD 
(in the NPRM) to clarify that the inspections are for ``existing frame 
repairs,'' instead of ``frames.'' Boeing requested that we change 
``frame'' to ``frame repairs,'' and ``tied frames'' to ``existing frame 
repairs.''
    We agree with the commenter. We have revised paragraph (g)(2)(i) of 
this proposed AD accordingly.

Request To Revise Inspection Type

    Boeing asked that we revise paragraphs (k) and (l) of the proposed 
AD (in the NPRM) by changing ``detailed and HFEC inspections'' to just 
``HFEC inspections.'' Boeing stated that detailed inspections are not 
specified during accomplishment of the preventive modification in 
Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 
30, 2015.
    We agree with the commenter for the reason provided. We have 
removed ``detailed'' inspections from paragraphs (k) and (l) of this 
proposed AD.

Request To Change Certain Language in Paragraph (l)(2) of the Proposed 
AD

    Boeing asked that we change paragraph (l)(2) of the proposed AD (in 
the NPRM), which stated that the repair would terminate the repetitive 
inspections required by paragraph (g)(1) of this AD. Boeing requested 
that the proposed AD instead state that the repair would terminate not 
only the repetitive inspections, but also the preventive modification 
required by

[[Page 79397]]

paragraph (k) of the proposed AD. Boeing added that Boeing Alert 
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, 
provides a terminating action provision for the repetitive inspections 
and the preventive modification under the repair. Boeing stated that 
accomplishment of the repair removes the WFD, and therefore the 
preventive modification is not required for repaired frames.
    We agree with the commenter for the reasons provided. We have 
clarified the language in paragraph (l)(2) of this proposed AD 
accordingly.

Request To Move Terminating Action in Paragraph (l)(3) of the Proposed 
AD to the Credit Paragraph

    Boeing asked that we move the terminating action specified in 
paragraph (l)(3) of the proposed AD (in the NPRM) into the credit for 
previous actions specified in paragraph (m) of the proposed AD (in the 
NPRM) for clarification. Boeing stated that accomplishment of the 
repair or preventive modification, as specified in Boeing Message M-
7200-02-1294, dated August 20, 2002, is a ``previous action'' similar 
to accomplishment of the repair or preventive modification specified in 
Boeing Alert Service Bulletin 737-53A1261, dated January 19, 2006. 
Boeing added that paragraph (l)(3) of the proposed AD (in the NPRM) 
stated that the repair or preventive modification done before the 
effective date of the AD terminates the repetitive inspection 
requirements of paragraph (g)(1) of the proposed AD (in the NPRM). 
Boeing also asked that we revise the proposed AD (in the NPRM) to state 
that accomplishment of the repair or preventive modification in 
accordance with Boeing Message M-7200-02-1294, dated August 20, 2002, 
if performed before the effective date of the AD, would also terminate 
the preventive modification required by paragraph (k) of the proposed 
AD (in the NPRM).
    We agree to revise paragraph (l)(3) of this proposed AD to state 
that a repair or preventive modification done in accordance with Boeing 
Message M-7200-02-1294, dated August 20, 2002, is acceptable for 
terminating both the inspections and the preventive modification 
requirements in paragraphs (g)(1) and (k) of this proposed AD 
respectively. We have changed paragraph (l)(3) of this proposed AD 
accordingly.
    We do not agree to move paragraph (l)(3) of the proposed AD (in the 
NPRM) into the credit for previous actions specified in paragraph (m) 
of this proposed AD. Paragraph (m) of this proposed AD is intended to 
give credit for actions accomplished using previous revisions of 
service information for accomplishing corresponding actions prior to 
the effective date of the AD; it does not terminate any actions and 
does not address future actions.

Request To Provide Credit for Certain Repairs

    Boeing asked that we change paragraph (m) of the proposed AD (in 
the NPRM) to provide credit for repairs that were accomplished before 
the effective date of the AD, in accordance with Boeing Alert Service 
Bulletin 737-53A1261, dated January 19, 2006. Boeing stated that the 
repair procedures are the same as those in Boeing Alert Service 
Bulletin 737-53A1261, Revision 1, dated January 30, 2015 (as specified 
in paragraph (l)(2) of the proposed AD (in the NPRM)).
    We agree with the commenter for the reason provided. We have added 
a new paragraph (m)(3) to this proposed AD to give credit for repairs 
specified in paragraph (l)(2) of the this proposed AD that are 
accomplished before the effective date of this proposed AD.

Request To Remove Repairs as Terminating Action Under Certain 
Conditions

    Boeing asked that we change paragraph (l)(4) of the proposed AD (in 
the NPRM) to remove repairs as acceptable terminating action. Boeing 
stated that paragraph (l)(4) of the proposed AD (in the NPRM) would 
provide a terminating action provision for the repetitive inspections 
required by paragraph (g)(2) of the proposed AD (in the NPRM) if a 
repair or preventive modification is accomplished that is different 
from the one provided in Boeing Alert Service Bulletin 737-53A1261, 
Revision 1, dated January 30, 2015, provided it has been approved by 
the Manager, Los Angeles Aircraft Certification Office. Boeing added 
that there have been repairs performed in the past that involve 
trimming the production upper frame web near S-11 and replacing it with 
an identical replacement frame web without additional reinforcement 
similar to the preventive modification or repair. Boeing noted that the 
repair is structurally acceptable; however, it does not sufficiently 
reinforce the frame to provide terminating action for the inspections, 
and would require further service actions, including inspections and a 
preventive modification. Boeing added that the additional inspection 
requirements should be specified in the AMOC approval, and noted that a 
preventive modification would not necessarily be required since prior 
approvals would not have taken the WFD requirements into account.
    We agree with the commenter for the reasons provided. All 
previously installed repairs or modifications installed in accordance 
with Boeing Alert Service Bulletin 737-53A1261, dated January 19, 2006, 
must be reevaluated or replaced to ensure that all WFD requirements are 
met. Therefore, we have removed paragraph (l)(4) of the proposed AD (in 
the NPRM) from this proposed AD.

FAA's Determination

    We are proposing this SNPRM because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would require accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Difference Between this AD and the Service Information.'' Refer to 
this service information for information on the procedures and 
compliance times.

Difference Between This SNPRM and the Service Information

    Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated 
January 30, 2015, specifies to contact the manufacturer for certain 
repair instructions, but this proposed AD would require repair methods, 
modification deviations, and alteration deviations in one of the 
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 391 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 79398]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                     Parts
          Action                 Labor cost           cost        Cost per product       Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from  Between 18 and 38 work-        $0  Between $1,530 and        Between $598,230 and
 AD 2008-13-12 R1.          hours x $85 per hour,              $3,230 per inspection     $1,262,930, per
                            depending on airplane              cycle.                    inspection cycle.
                            configuration =
                            between $1,530 and
                            $3,230 per inspection
                            cycle.
New proposed inspections.  213 work[dash]hours x          $0  $18,105 per inspection    $7,079,055, per
                            $85 per hour, $18,105              cycle.                    inspection cycle.
                            per inspection cycle.
New proposed modification  256 work-hours x $85     ([sup1])  $21,760.................  $8,508,160
                            per hour = $21,760.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the proposed
  modification.

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008), and 
adding the following new AD.

The Boeing Company: Docket No. FAA-2015-3984; Directorate Identifier 
2015-NM-033-AD.

(a) Comments Due Date

    We must receive comments by December 29, 2016.

(b) Affected ADs

    This AD replaces AD 2008-13-12 R1, Amendment 39-15719 (73 FR 
67383, November 14, 2008) (``AD 2008-13-12 R1'').

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?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

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

(e) Unsafe Condition

    This AD was prompted by reports of additional fatigue cracking 
of the upper-frame-to-side-frame splice of the fuselage, and one 
report of a severed frame due to susceptibility to widespread 
fatigue damage (WFD). We are issuing this AD to detect and correct 
fatigue cracking of the upper-frame-to-side-frame splice of the 
fuselage, which could result in reduced structural integrity of the 
frame and adjacent lap joint, causing increased loading in the 
fuselage skin, which will accelerate skin crack growth and result in 
decompression of the airplane.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions for Certain Airplanes

    (1) For Groups 1 through 3, Configurations 1, 3, 4, and 5 
airplanes; Group 7, Configurations 1, 3, 4, and 5 airplanes; Groups 
4 through 6, Configurations 1, 3, 4, and 6 airplanes; and Groups 8 
through 11, Configurations 1, 3, 4, and 6 airplanes; as identified 
in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated 
January 30, 2015: Do the actions specified in paragraphs (g)(1)(i) 
and (g)(1)(ii) of this AD, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, 
except as required by paragraph (i)(3) of this AD. Do all applicable 
corrective actions before further flight.
    (i) At the applicable time specified in Tables 1, 2, 3, 5, 6, 
and 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as 
required by paragraphs (i)(1) and (i)(2) of this AD: Do medium 
frequency eddy current inspections for cracking of the upper-frame-
to-side-frame splice of the fuselage.
    (ii) Repeat the inspections specified in paragraph (g)(1)(i) of 
this AD at the applicable time specified in Tables 1, 2, 3, 5, 6, 
and 8 of paragraph 1.E., ``Compliance,'' of

[[Page 79399]]

Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 
30, 2015, until the preventive modification required by paragraph 
(k) of this AD, or a terminating action specified in paragraph (l) 
of this AD, has been accomplished. The inspections are terminated 
for the repaired or modified areas only.
    (2) For Groups 4 through 6, Configurations 2 and 5 airplanes; 
and Groups 8 through 11, Configurations 2 and 5 airplanes; as 
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015: Do the actions specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD, and all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 
30, 2015, except as required by paragraph (i)(3) of this AD. Do all 
applicable corrective actions before further flight.
    (i) At the applicable time specified in Tables 4 and 7 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1261, Revision 1, dated January 30, 2015, except as required 
by paragraphs (i)(1) and (i)(2) of this AD: Do a detailed inspection 
to determine if the existing frame repair meets all requirements 
specified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015, and for any frame repair that does meet all 
requirements, do detailed and high frequency eddy current (HFEC) 
inspections for cracking of the existing frame repairs.
    (ii) Repeat the inspections for cracking specified in paragraph 
(g)(2)(i) of this AD at the applicable time specified in Tables 4 
and 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1261, Revision 1, dated January 30, 2015.

(h) Post-Repair and Post-Modification Actions for Certain Airplanes

    For Group 1, Configurations 2 and 6 airplanes; Group 2, 
Configurations 2 and 6 airplanes; Group 3, Configurations 2 and 6 
airplanes; and Group 7, Configurations 2 and 6 airplanes; as 
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015: Within 120 days after the effective date of 
this AD, do post-repair and post-modification actions using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(i) Exceptions to Service Bulletin Specifications

    (1) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where the ``Condition'' column of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, 
Revision 1, dated January 30, 2015, specifies a condition based on 
whether an airplane has or has not been inspected, this AD bases the 
condition on whether an airplane has or has not been inspected as of 
the effective date of this AD.
    (3) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015, specifies to contact Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (n) of this 
AD.

(j) Post-Repair/Post-Modification Inspections

    For Groups 4 through 6, Configurations 1, 3, 4, 6, 7, 8, 9, and 
10 airplanes; and Groups 8 through 11, Configurations 1, 3, 4, 6, 7, 
8, 9, and 10 airplanes; as identified in Boeing Alert Service 
Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Except as 
provided by paragraphs (i)(1) and (i)(2) of this AD, at the 
applicable time specified in Tables 12 through 17 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, 
Revision 1, dated January 30, 2015; do the post-repair/post-
modification inspections, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 
1, dated January 30, 2015, except as required by paragraph (i)(3) of 
this AD. Do all applicable corrective actions before further flight.

(k) Preventive Modification for Certain Airplanes

    For Groups 4 through 6, Configurations 1, 3, 4, and 6 airplanes; 
and Groups 8 through 11, Configurations 1, 3, 4, and 6 airplanes; as 
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015: Except as provided by paragraphs (i)(1) and 
(i)(2) of this AD, at the applicable time specified in Tables 3, 5, 
6, and 8 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1261, Revision 1, dated January 30, 2015, do the 
preventive modification, including HFEC inspections for cracking and 
applicable corrective actions, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015, except as required by 
paragraph (i)(3) of this AD. Do all applicable corrective actions 
before further flight. Accomplishing the modification required by 
this paragraph terminates the inspections required by paragraph 
(g)(1) of this AD for the modified area only.

(l) Terminating Action

    (1) For Groups 4 through 6, Configurations 1, 3, 4, and 6 
airplanes; and Groups 8 through 11, Configurations 1, 3, 4, and 6 
airplanes; as identified in Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015: Accomplishing the 
preventive modification, including HFEC inspections for cracking and 
applicable corrective actions, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015, except as required by 
paragraph (i)(3) of this AD, terminates the inspections required by 
paragraph (g)(1) of this AD for the modified area only.
    (2) For Groups 4 through 6, Configurations 3 and 6 airplanes; 
and Groups 8 through 11, Configurations 3 and 6 airplanes; as 
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, 
dated January 30, 2015: Accomplishing the repair, including HFEC 
inspections for cracking and applicable corrective actions, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 
2015, except as required by paragraph (i)(3) of this AD, terminates 
the repetitive inspections required by paragraph (g)(1) of this AD, 
and the preventive modification required by paragraph (k) of this 
AD, for the repaired area only.
    (3) Accomplishment of the repair or the preventive modification 
specified in Boeing Message M-7200-02-1294, dated August 20, 2002, 
before the effective date of this AD terminates the repetitive 
inspections required by paragraph (g)(1) of this AD and the 
preventive modification required by paragraph (k) of this AD for the 
repaired or modified area only.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for the inspections required 
by paragraph (g) of this AD, if those inspections were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-53A1261, dated January 19, 2006, which was incorporated 
by reference in AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 
8, 2008) (``AD 2008-13-12'').
    (2) This paragraph provides credit for the modification 
specified in paragraphs (k) and (l)(1) of this AD, if performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-53A1261, dated January 19, 2006.
    (3) This paragraph provides credit for repairs specified in 
paragraphs (l)(2) of this AD, if performed before the effective date 
of this AD using Boeing Alert Service Bulletin 737-53A1261, dated 
January 19, 2006.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the ACO, send it to the attention of the person 
identified in paragraph (o)(1) of this AD. Information may be 
emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Los Angeles 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 for AD 2008-13-12, and AD 2008-13-12 R1; are 
approved as AMOCs for the corresponding provisions of paragraph (g) 
of this AD.

[[Page 79400]]

(o) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 
fax: 425-917-6590; email: wayne.lockett@faa.gov.
    (2) 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 206-766-5680; Internet https://www.myboeingfleet.com. You may view this 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 425-227-1221.

    Issued in Renton, Washington, on September 12, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-22699 Filed 11-10-16; 8:45 am]
BILLING CODE 4910-13-P