AD 2016-13-10

[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)]
[Rules and Regulations]
[Pages 43483-43488]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-15291]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3628; Directorate Identifier 2015-NM-025-AD; 
Amendment 39-18574; AD 2016-13-10]
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 Airworthiness Directive (AD) 2012-12-04, 
for certain The Boeing Company Model 737-300, -400, and -500 series 
airplanes. AD 2012-12-04 required repetitive external detailed 
inspections and nondestructive inspections to detect cracks in the 
fuselage skin along the chem-mill steps at stringers S-1 and S-2R, 
between station (STA) 400 and STA 460, and repair if necessary. This 
new AD requires a preventive modification of the fuselage skin at crown 
stringers S-1 and S-2R. This new AD also reduces the inspection 
threshold for certain airplanes. This AD was prompted by a 
determination that, for certain airplanes, the skin pockets adjacent to 
the Air Traffic Control (ATC) antenna are susceptible to widespread 
fatigue damage. We are issuing this AD to detect and correct fatigue 
cracking of the fuselage skin panels at the chem-mill steps, which 
could result in sudden fracture and failure of the fuselage skin 
panels, and consequent rapid decompression of the airplane.

DATES: This AD is effective August 9, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 9, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in

[[Page 43484]]

this AD as of July 23, 2012 (77 FR 36134, June 18, 2012).

ADDRESSES: For service information identified in this final rule, 
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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
3628.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>. by searching for and locating Docket No. FAA-2015-
3628; 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: 800-647-
5527) is Docket 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: Jennifer Tsakoumakis, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: 
<a href="/cdn-cgi/l/email-protection#157f707b7b7c7370673b6166747e7a6078747e7c66557374743b727a63"><span class="__cf_email__" data-cfemail="6d07080303040b081f43191e0c060218000c06041e2d0b0c0c430a021b">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-12-04, Amendment 39-17083 (77 FR 36134, 
June 18, 2012) (``AD 2012-12-04''). AD 2012-12-04 applied to certain 
The Boeing Company Model 737-300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on September 14, 2015 (80 FR 
55045) (``the NPRM''). The NPRM was prompted by a determination that, 
for certain airplanes, the skin pockets adjacent to the ATC antenna are 
susceptible to widespread fatigue damage. The NPRM proposed to continue 
to require repetitive external detailed inspections and nondestructive 
inspections to detect cracks in the fuselage skin along the chem-mill 
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and 
repair if necessary. The NPRM also proposed to require a preventive 
modification of the fuselage skin at crown stringers S-1 and S-2R. In 
addition, the NPRM proposed to revise certain compliance times. We are 
issuing this AD to detect and correct fatigue cracking of the fuselage 
skin panels at the chem-mill steps, which could result in sudden 
fracture and failure of the fuselage skin panels, and consequent rapid 
decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Requests To Clarify Compliance Time Changes

    Boeing asked that we change the NPRM preamble, which stated that 
the proposed AD would reduce the inspection thresholds ``and repetitive 
intervals'' for certain airplanes. Boeing stated that the repetitive 
inspection intervals specified in Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, remain unchanged from the 
previous version of the service information, which was mandated by AD 
2012-12-04. Boeing added that Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, reduced only the 
inspection threshold for those airplanes.
    We agree with the commenter's request for the reason provided. We 
have changed the language in the SUMMARY of this final rule 
accordingly.

Request To Clarify Acceptable Previous Alternative Methods of 
Compliance (AMOCs)

    Boeing and Southwest Airlines (SWA) asked that we revise paragraph 
(l)(4) of the proposed AD. Boeing requested that we state that AMOCs 
approved for AD 2012-12-04 are approved as AMOCs for ``all 
corresponding requirements''--instead of just the requirements of 
paragraph (g)--of the proposed AD. Boeing stated that this proposed 
change matches the wording in paragraph (l)(4) of AD 2012-12-04. SWA 
added that paragraph (l)(4) of the proposed AD does not provide credit 
for AMOCs approved for the actions specified in paragraphs (f) and (g) 
of AD 2008-19-03, Amendment 39-15670 (73 FR 56958, October 1, 2008) 
(``AD 2008-19-03''). (AD 2008-19-03 was superseded by AD 2012-12-04.)
    We agree to revise paragraph (n)(4) of this AD (paragraph (l)(4) of 
the proposed AD) to specify that AMOCs approved for AD 2012-12-04 are 
approved as AMOCs for all the corresponding provisions of this AD.
    It is not necessary, however, to state that AMOCs approved for AD 
2008-19-03 are approved for the requirements of this AD. When AD 2008-
19-03 was superseded, the corresponding provisions of AD 2008-19-03 
were retained in AD 2012-12-04. Therefore, no change to this final rule 
is necessary in this regard.

Request To Separate Certain Actions for Clarification

    Boeing, ASL Airlines France, and SWA asked that we clarify the 
requirements of paragraph (h) of the proposed AD by separating the 
actions into two core paragraphs: One paragraph for ``Repairs'' and one 
paragraph for the ``Preventive Modification.'' Boeing stated that 
tables 1, 2, and 3 of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, address the repair and preventive 
modification instructions for Group 1 airplanes, and table 5 addresses 
repair instructions for Group 2 airplanes; therefore table 5 should not 
be included in paragraph (h)(2) of the proposed AD. Boeing also stated 
that Note (e) of tables 1, 2, and 3 of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015, provides a terminating 
action provision for the repetitive inspections under the installed 
preventive modification doubler; therefore a terminating action should 
be added to paragraph (h)(2) of the proposed AD. ASL Airlines France 
stated that, as written, paragraph (h) of the proposed AD is confusing 
because it would require the preventive modification specified in 
paragraph (h)(2) of the proposed AD to be installed only if cracking is 
found. SWA stated that Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, does not provide repair 
instructions for cracks found in four or more tear strap bays and 
certain other conditions, as specified in figure 6 or figure 8 of the 
Accomplishment Instructions. SWA asked that a provision be added to 
paragraph (h)(2) of the proposed AD to allow for both new and existing 
repairs to remain on the airplane if the repair covers all eight chem-
mill step inspection areas between STA 410 and STA 450, if approved by 
the FAA or a Boeing-approved representative.

[[Page 43485]]

    We agree with the commenters' requests for the reasons provided. We 
have separated paragraph (h) of the proposed AD into paragraphs (h) and 
(i) of this AD to clarify the actions identified by the commenters (and 
have redesignated subsequent paragraphs accordingly).

Request To Add Exception for the Preventive Modification

    Boeing asked that we add a new exception to address the preventive 
modification. Boeing stated that paragraph (j)(3) of the proposed AD 
addresses repairs, and a similar paragraph needs to be added to address 
the preventive modification specified in Part 9 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015; Part 9 specifies contacting Boeing for 
preventive modification instructions. Boeing added that the new 
exception should be done using a method approved by the FAA or a Boeing 
approved representative.
    We agree with the commenter's request. Part 9 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015, specifies contacting Boeing for modification 
instructions if an existing repair is installed that was not 
accomplished in accordance with Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015. We have revised paragraph 
(l)(3) of this AD (paragraph (j)(3) of the proposed AD) to include the 
exception to account for the preventive modification.

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 redesignated paragraph (c) of 
the proposed AD as (c)(1) and added new paragraph (c)(2) to this AD to 
state that installation of STC ST01219SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se</a>) 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'' AMOC approval request is not necessary to comply 
with the requirements of 14 CFR 39.17.

Request To Restate the Optional Modification in AD 2012-12-04

    Boeing and Al Nippon Airways (ANA) asked that the optional 
modification specified in paragraph (i) of AD 2012-12-04 be restated in 
this AD. The commenters stated that Section 1.F., ``Approval'' of 
Boeing Alert Service Bulletin 737-53A1305, Revision 1, dated September 
19, 2012, includes approval of the accomplishment of the inspections 
and modifications, in accordance with that service information for the 
modified area only, as a method of compliance with the modification 
specified in paragraph (i) of AD 2012-12-04. The commenters added that 
since the optional modification is not restated in the proposed AD, 
this approval is now eliminated.
    We agree with the commenters for the reasons provided. We have 
restated the optional modification in new paragraph (j) of this AD 
(paragraph (i) of AD 2012-12-04), and redesignated subsequent 
paragraphs accordingly.

Request To Clarify the Extent of AMOC Approvals

    Boeing asked whether AMOCs would be considered for ``preventive 
modifications,'' in addition to repairs, in paragraph (l)(3) of the 
proposed AD. Boeing stated that adding this would address the AMOC 
requirement for the mandatory preventive modification.
    We agree with the commenter's request because deviations to the 
mandated preventive modification are possible. Therefore, we have added 
``modification'' (as well as ``alteration'') to paragraph (n)(3) of 
this AD (paragraph (l)(3) of the proposed AD).

Request To Clarify Exception

    ASL Airlines France asked that we clarify the reference in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, specified in the 
``Condition'' columns. The commenter stated that the flight-cycle 
compliance time referred to in these columns specifies ``at the 
Revision 3 date of this service bulletin'' instead of ``as of the 
effective date of this AD.'' The commenter asked that we include a new 
paragraph to clarify that ``as of the effective date of this AD'' 
should be used for compliance throughout the proposed AD.
    We acknowledge the commenter's concern; however, paragraph (l)(1) 
of the proposed AD already addressed this difference; paragraph (j)(2) 
of this AD retains this provision. Therefore, no change to this AD is 
necessary in this regard.

Request To Correct Typographical Errors

    Boeing and ASL Airlines France asked that we correct the paragraph 
reference in Note 1 to paragraph (i) of the proposed AD and in 
paragraph (j)(3) of the proposed AD. The commenters stated that these 
are typographical errors.
    The information in Note 1 to paragraph (i) of the proposed AD has 
been included in paragraph (j) of this final rule (paragraph (i) of the 
proposed AD), therefore ``Note 1'' no longer exists. In light of this, 
the requested correction is not necessary in this regard. We have 
corrected the reference in paragraph (j)(3) of the proposed AD 
(paragraph (l)(3) of this AD) accordingly.

Change to Paragraph (k) of This AD

    We have revised the language in paragraph (k) of this AD (paragraph 
(i) in the proposed AD) to clarify that the post-repair/post-
modification inspections are airworthiness limitations that are 
required by maintenance and operational rules; therefore, these 
inspections are not required by this AD.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015. The service information describes procedures 
for repetitive external detailed inspections and non-destructive 
inspections to detect cracks in the fuselage skin along the chem-mill 
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and 
repair of any cracking. The service information also describes 
procedures for a modification of the chem-mill steps at the locations 
identified, including related investigative actions and corrective 
actions, and repetitive post-mod inspections. This service information 
is reasonably available

[[Page 43486]]

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

Costs of Compliance

    We estimate that this AD affects 186 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
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD 2012- Between 7 and 15                 $0  Between $595 and     Between $110,670
 12-04.                             work-hours x $85                     $1,275 per           and $237,150 per
                                    per hour,                            inspection cycle.    inspection cycle.
                                    depending on
                                    airplane
                                    configuration =
                                    between $595 and
                                    $1,275 per
                                    inspection cycle.
New modification.................  236 work-hours x                  1  $20,060............  $3,731,160.
                                    $85 per hour =
                                    $20,060.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the modification. We
  cannot determine the cost of the materials because the modification parts must be sized at the time the
  modification is installed, taking into account any existing repairs in the area.

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

Authority for This Rulemaking

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

Regulatory Findings

    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) 
2012-12-04, Amendment 39-17083 (77 FR 36134, June 18, 2012), and adding 
the following new AD:

2016-13-10 The Boeing Company: Amendment 39-18574; Docket No. FAA-
2015-3628; Directorate Identifier 2015-NM-025-AD.

(a) Effective Date

    This AD is effective August 9, 2016.

(b) Affected ADs

    This AD replaces AD 2012-12-04, Amendment 39-17083 (77 FR 36134, 
June 18, 2012) (``AD 2012-12-04'').

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-300, -400, 
and -500 series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se</a>) 
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 cracks found on the fuselage 
skin at the chem-mill steps, and the determination that, for certain 
airplanes, the skin pockets adjacent to the Air Traffic Control 
antenna are susceptible to widespread fatigue damage. We are issuing 
this AD to detect and correct fatigue cracking of the fuselage skin 
panels at the chem-mill steps, which could result in sudden fracture 
and failure of the fuselage skin panels, and consequent rapid 
decompression of the airplane.

(f) Compliance

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

(g) Inspections

    At the applicable time specified in tables 1, 2, 3, and 5 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015, except as required 
by paragraphs (l)(1) and (l)(2) of this AD: Do the actions specified 
in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, except as required by 
paragraph (l)(3) of this AD. Repeat the applicable inspections 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015.

[[Page 43487]]

    (1) Do an external detailed inspection for cracking of the 
fuselage skin chem-mill steps.
    (2) Do an external non-destructive (medium frequency eddy 
current, magneto optical imaging, C-Scan, or ultrasonic phased 
array) inspection for cracking of the fuselage skin chem-mill steps.

(h) Repair

    If any cracking is found during any inspection required by 
paragraph (g) of this AD, do the applicable actions specified in 
paragraph (h)(1), (h)(2), or (h)(3) of this AD.
    (1) Repair before further flight in accordance with Part 2 (for 
Group 1 airplanes) or Part 7 (for Group 2 airplanes) of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015; except as required by 
paragraph (l)(3) of this AD. Installation of a repair that meets the 
conditions specified in Note (a) of table 1, 2, 3, or 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, 
Revision 3, dated January 23, 2015, terminates the repetitive 
inspections required by paragraph (g) of this AD for the area 
covered by that repair only.
    (2) For Group 1 airplanes: Accomplishing the modification 
specified in paragraph (i) of this AD is a method of compliance with 
paragraph (h)(1) of this AD.
    (3) If any cracking is found in any area not covered by the 
preventive modification doubler during any inspection required by 
paragraph (g) of this AD: Repair before further flight, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23, 
2015, except as provided by paragraph (n)(4) of this AD. Both new 
and existing repairs are allowed if the repair covers all eight 
chem-mill step inspection areas between STA 410 and STA 450, and the 
repairs were done using a method approved in accordance with the 
procedures specified in paragraph (n)(1) of this AD.

(i) Preventive Modification

    For Group 1 airplanes: At the applicable time specified in 
tables 1, 2 and 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1293, Revision 3, dated January 23, 2015, 
except as required by paragraphs (l)(1) and (l)(2) of this AD, do a 
preventive modification of the fuselage skin at crown stringers S-1 
and S-2R, including all applicable related investigative actions in 
accordance with Part 9 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23, 
2015, except as provided by paragraph (n)(4) of this AD. Do all 
applicable related investigative actions concurrently with the 
modification. Installation of a preventive modification terminates 
the repetitive inspections required by paragraph (g) of this AD for 
the modified area only. Thereafter, repeat the inspections specified 
in Part 3 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1293, Revision 3, dated January 23, 2015.

(j) Optional Modification

    Accomplishing a modification of the chem-mill steps at any 
location identified in Boeing Service Bulletin 737-53A1293, Revision 
2, dated August 10, 2011, using a method approved in accordance with 
the procedures specified in paragraph (n)(1) of this AD, terminates 
the repetitive inspections required by paragraph (g) of this AD for 
the modified area only.

(k) Post-Repair/Post-Modification Inspections

    Tables 4 and 6 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23, 
2015, specify post-repair/post-modification airworthiness limitation 
inspections in compliance with 14 CFR 25.571(a)(3) at the modified 
locations, which support compliance with 14 CFR 121.1109(c)(2) or 
129.109(b)(2). As airworthiness limitations, these inspections are 
required by maintenance and operational rules. It is therefore 
unnecessary to mandate them in this AD. Deviations from these 
inspections require FAA approval, but do not require an alternative 
method of compliance.

(l) Exceptions to Service Bulletin Specifications

    (1) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015, specifies a compliance time ``after the 
Revision 3 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 737-53A1293, 
Revision 3, dated January 23, 2015, specifies a condition based on 
when an airplane has or has not been inspected, this AD bases the 
condition on whether an airplane has or has not been inspected on 
the effective date of this AD.
    (3) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015, specifies to contact Boeing for repair or 
preventive modification instructions: Before further flight, do the 
repair or preventive modification, as applicable, using a method 
approved in accordance with the procedures specified in paragraph 
(n)(1) of this AD.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before July 23, 2012 (the effective date of AD 2012-12-04), using 
Boeing Alert Service Bulletin 737-53A1293, Revision 1, dated July 7, 
2010, which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-53A1293, Revision 2, dated August 10, 2011, which was 
incorporated by reference in AD 2012-12-04.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (o)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#ba8397fbf4f797f6fbfbf9f597fbf7f5f997e8dfcbcfdfc9cec9fadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="350c18747b7818797474767a1874787a76186750444050464146755354541b525a43">[email&#160;protected]</span></a>.
    (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, modification, or alteration 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. To be approved, 
the repair method, modification deviation, or alteration deviation 
method must meet the certification basis of the airplane, and the 
approval must specifically refer to this AD.
    (4) AMOCs approved for AD 2012-12-04 are approved as AMOCs for 
the corresponding provisions of this AD.

(o) Related Information

    (1) For more information about this AD, contact Jennifer 
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; 
phone: 562-627-5264; fax: 562-627-5210; email: 
<a href="/cdn-cgi/l/email-protection#38525d5656515e5d4a164c4b5953574d555953514b785e5959165f574e"><span class="__cf_email__" data-cfemail="fa909f9494939c9f88d48e899b91958f979b919389ba9c9b9bd49d958c">[email&#160;protected]</span></a>.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(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 
August 9, 2016.
    (i) Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated 
January 23, 2015.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
July 23, 2012 (77 FR 36134, June 18, 2012).
    (i) Boeing Service Bulletin 737-53A1293, Revision 2, dated 
August 10, 2011.
    (ii) Reserved.
    (5) 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

[[Page 43488]]

    (6) You may view this 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.
    (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 202-741-6030, or go to <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on June 21, 2016.
Dorr Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15291 Filed 7-1-16; 8:45 am]
 BILLING CODE 4910-13-P