81 FR 53908 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 157 (August 15, 2016)

We are superseding Airworthiness Directive (AD) 2016-13-10, for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2016-13-10 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. AD 2016-13-10 also required a preventive modification of the fuselage skin at crown stringers S-1 and S-2R. This AD requires the same actions as AD 2016-13-10, and clarifies certain regulatory text. This AD was prompted by the determination that certain regulatory text in AD 2016- 13-10 requires clarification. 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.

[Federal Register Volume 81, Number 157 (Monday, August 15, 2016)]
[Rules and Regulations]
[Pages 53908-53912]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-18952]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8841; Directorate Identifier 2016-NM-115-AD; 
Amendment 39-18611; AD 2016-16-13]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-13-10, 
for certain The Boeing Company Model 737-300, -400, and -500 series 
airplanes. AD 2016-13-10 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. AD 
2016-13-10 also required a preventive modification of the fuselage skin 
at crown stringers S-1 and S-2R. This AD requires the same actions as 
AD 2016-13-10, and clarifies certain regulatory text. This AD was 
prompted by the determination that certain regulatory text in AD 2016-
13-10 requires clarification. 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 15, 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 (81 FR 43483, July 5, 2016).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
23, 2012 (77 FR 36134, June 18, 2012).
    We must receive any comments on this AD by September 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 final rule, contact 
Boeing

[[Page 53909]]

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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-8841.

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-2016-
8841; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 21, 2016, we issued AD 2016-13-10, Amendment 39-18574 (81 
FR 43483, July 5, 2016) (``AD 2016-13-10''), for certain The Boeing 
Company Model 737-300, -400, and -500 series airplanes. AD 2016-13-10 
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 STA 400 and STA 460, and 
repair if necessary. AD 2016-13-10 also required a preventive 
modification of the fuselage skin at crown stringers S-1 and S-2R. AD 
2016-13-10 resulted from a determination that, for certain airplanes, 
the skin pockets adjacent to the Air Traffic Control (ATC) antenna are 
susceptible to widespread fatigue damage. We issued AD 2016-13-10 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.

Actions Since AD 2016-13-10 Was Issued

    Since we issued AD 2016-13-10, we have determined that certain 
regulatory text in AD 2016-13-10 requires clarification:
     We have revised paragraphs (h)(3) and (i) of this AD to 
refer to paragraph (l)(3) of this AD for the exception to the service 
information.
     We have also removed the sentence from paragraph (h)(3) of 
AD 2016-13-10 that provided existing repair information and instead we 
have included existing repair information in the introductory text of 
paragraph (h) of this AD.
     We have revised paragraph (j) of this AD to also refer to 
Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated January 
23, 2015, for locations for the modification of the chem-mill steps.
     We have revised paragraphs (j) and (l)(3) of this AD to 
refer to paragraph (n) of this AD for the appropriate procedures to 
request approval of an alternative method of compliance.
    We are issuing this AD to correct the unsafe condition on certain 
The Boeing Company Model 737-300, -400, and -500 series airplanes.

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

FAA's Determination

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

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously.

FAA's Justification and Determination of the Effective Date

    We are superseding AD 2016-13-10 to clarify certain regulatory 
text. We have made no other changes to the requirements published in AD 
2016-13-10. Therefore, we find that notice and opportunity for prior 
public comment are unnecessary and that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
Docket No. FAA-2016-8841; and Directorate Identifier 2016-NM-115-AD at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 186 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 53910]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost         Parts cost      Cost per product         operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD     Between 7 and 15                  $0  Between $595 and      Between $110,670
 2016-13-10.                      work-hours x $85                      $1,275 per            and $237,150 per
                                  per hour, depending                   inspection cycle.     inspection cycle.
                                  on airplane
                                  configuration =
                                  between $595 and
                                  $1,275 per
                                  inspection cycle.
Retained modification from AD    236 work-hours x $85           (\1\)  $20,060.............  $3,731,160.
 2016-13-10.                      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

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2016-13-10, Amendment 39-18574 (81 FR 43483, July 5, 2016), and adding 
the following new AD:

2016-16-13 The Boeing Company: Amendment 39-18611; Docket No. FAA-
2016-8841; Directorate Identifier 2016-NM-115-AD.

(a) Effective Date

    This AD is effective August 15, 2016.

(b) Affected ADs

    This AD replaces AD 2016-13-10, Amendment 39-18574 (81 FR 43483, 
July 5, 2016) (``AD 2016-13-10'').

(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 (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 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) Retained Inspections With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-13-10, with no changes. 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.
    (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.

[[Page 53911]]

(h) Retained Repair With Clarification of Repair Information and 
Service Information Exception

    This paragraph restates the requirements of paragraph (h) of AD 
2016-13-10, with clarification of repair information and service 
information exception. 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. 
Installation of a repair prior to August 9, 2016 (the effective date 
of AD 2016-13-10) that meets the conditions specified in Part 9 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1293, Revision 3, dated January 23, 2015, terminates the 
inspections required by paragraph (g) of this AD for the area 
covered by that repair only. Installation of a repair prior to 
August 9, 2016, that meets the conditions specified in Part 9 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, covers all eight chem-
mill step inspection areas between STA 410 and STA 450, and was done 
using a method approved in accordance with the procedures specified 
in paragraph (n) of this AD, terminates the inspections required by 
paragraph (g) of this AD for the area covered by that repair only, 
and terminates the preventive modification required by paragraph (i) 
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 (l)(3) of this AD. 
Installation of this repair terminates the repetitive inspections 
required by paragraph (g) of this AD for the area covered by that 
repair only.

(i) Retained Preventive Modification With Clarification of Service 
Information Exception and Method of Compliance Procedures

    This paragraph restates the requirements of paragraph (i) of AD 
2016-13-10, with clarification of service information exception and 
method of compliance procedures. 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 (l)(3) 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) Retained Optional Modification With Clarification of Service 
Information

    This paragraph restates the requirements of paragraph (j) of AD 
2016-13-10, with clarification of service information. Accomplishing 
a modification of the chem-mill steps at any location identified in 
Boeing Service Bulletin 737-53A1293, Revision 2, dated August 10, 
2011; or Boeing Alert Service Bulletin 737-53A1293, Revision 3, 
dated January 23, 2015; using a method approved in accordance with 
the procedures specified in paragraph (n) of this AD, terminates the 
repetitive inspections required by paragraph (g) of this AD for the 
modified area only.

(k) Retained Post-Repair/Post-Modification Inspections With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2016-13-10, with no changes. 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) Retained Exceptions to Service Bulletin Specifications With 
Clarification of Method of Compliance Procedures

    This paragraph restates the requirements of paragraph (l) of AD 
2016-13-10, With clarification of method of compliance procedures.
    (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 August 9, 2016 
(the effective date of AD 2016-13-10).
    (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 
August 9, 2016 (the effective date of AD 2016-13-10).
    (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) of this AD.

(m) Retained Credit for Previous Actions With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2016-13-10, with no changes.
    (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, Amendment 
39-17093 (77 FR 36134, June 18, 2012) (``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 August 9, 2016 (the effective date of AD 2016-13-10), using 
Boeing 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: [email protected].
    (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.

[[Page 53912]]

(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: 
[email protected].
    (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 (81 FR 43483, July 5, 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 https://www.myboeingfleet.com.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18952 Filed 8-12-16; 8:45 am]
 BILLING CODE 4910-13-P