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[Federal Register Volume 80, Number 142 (Friday, July 24, 2015)]
[Rules and Regulations]
[Pages 43921-43925]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17977]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0572; Directorate Identifier 2014-NM-027-AD; 
Amendment 39-18214; AD 2015-15-05]
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) 98-22-10 for 
certain The Boeing Company Model 737-100, -200, -200C, and -300 series 
airplanes. AD 98-22-10 required repetitive inspections for cracking of 
the aft frame and frame support structure of the forward service 
doorway, and repair if necessary. AD 98-22-10 also provided an optional 
terminating action for the repetitive inspection requirements of that 
AD. This new AD requires new inspections and adds airplanes to the 
applicability; for certain airplanes, this new AD provides an optional 
preventive modification, which terminates the repetitive inspections. 
This AD was prompted by reports of fatigue cracking of the aft frame 
and frame support structure of the forward service doorway around the 
six doorstop fittings, and a determination that inspections are needed 
in additional locations and that additional airplanes might be subject 
to the identified unsafe condition. We are issuing this AD to detect 
and correct fatigue cracking of the aft frame and frame support 
structure of the forward service doorway around the six

[[Page 43922]]

doorstop fittings, which could result in door deflection and loss of 
pressurization.

DATES: This AD is effective August 28, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 28, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 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-2014-0572.

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-2014-
0572; 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: Nenita Odesa, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5234; fax: 562-627-5210; email: nenita.odesa@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 98-22-10, Amendment 39-10858 (63 FR 57240, 
October 27, 1998). AD 98-22-10 applied to certain The Boeing Company 
Model 737-100, -200, -200C, and -300 series airplanes. The NPRM was 
published in the Federal Register on August 26, 2014 (79 FR 50867). The 
NPRM was prompted by reports of cracking in the surround structure of 
the forward galley service doorway between body station (STA) 332.1 and 
STA 344, which are outside the inspection area of AD 98-22-10, and by 
reports that cracking has been discovered on airplanes outside the 
applicability of AD 98-22-10. We have determined that inspections are 
needed in additional locations, and that additional airplanes are 
subject to the identified unsafe condition.
    The NPRM (79 FR 50867, August 26, 2014) proposed to continue to 
require repetitive inspections for cracking of the aft frame and frame 
support structure of the forward service doorway, and repair if 
necessary. The NPRM also proposed to add inspections, add airplanes to 
the applicability, and for certain airplanes, provide an optional 
preventive modification, which would terminate the repetitive 
inspections. We are issuing this AD to detect and correct fatigue 
cracking of the aft frame and frame support structure of the forward 
service doorway around the six doorstop fittings, which could result in 
door deflection and loss of pressurization.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 50867, August 26, 2014) and the FAA's response to each comment.

Request To Clarify Wording in NPRM (79 FR 50867, August 6, 2014)

    Boeing stated paragraph 1.E, ``Compliance,'' of Boeing Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, provides actions 
for airplanes repaired or modified previously where the preventive 
modifications have been accomplished. Boeing stated that paragraph 
(l)(4) of the proposed AD reads: ``AMOCs approved for AD 98-22-10, 
Amendment 39-10858 (63 FR 57240, October 27, 1998), are approved as 
AMOCs for the corresponding provisions of this AD.'' Boeing interpreted 
the latter statement to mean that AMOCs approved for AD 98-22-10 do not 
supersede (or negate) the additional inspection requirements provided 
in Boeing Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, 
and requested concurrence with its interpretation of this language.
    We agree with Boeing's interpretation. Paragraph (m)(4) of this AD 
(paragraph (l)(4) of the proposed AD) establishes that an AMOC issued 
for actions performed in accordance with AD 98-22-10, Amendment 39-
10858 (63 FR 57240, October 27, 1998), satisfies the corresponding 
provisions, and only those corresponding provisions, of the this AD. 
All requirements of this AD must be satisfied, whether by previous 
AMOC, accomplishment of the specified AD actions, or a new AMOC. We 
have not changed this AD in this regard.

Request To Clarify Actions That Are Not Required

    Southwest Airlines (Southwest) noted that paragraph (h) of the 
proposed AD (79 FR 50867, August 26, 2014) would provide terminating 
action for the repetitive inspections required by paragraph (g) of this 
AD. Southwest requested that we revise the NPRM to state that the post 
preventive modification inspections specified in tables 9, 10, 11, and 
12 in paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1108, Revision 7, dated July 7, 2014, would not be required. 
Southwest also requested that this provision apply to paragraph (k) of 
the proposed AD (paragraph (l) of this AD), which specifies credit for 
actions done previously using Boeing Alert Service Bulletin 737-
53A1108, Revision 6, dated January 9, 2014.
    We agree with the requests. While the post-preventive modification 
inspections specified by tables 9 through 12 in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1108, Revision 
7, dated July 7, 2014, may be used in support of compliance with 
section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation 
Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)), those 
actions are not required by this AD. We have revised paragraph (g) of 
this AD by specifying the required parts of the service information: 
Parts 2 and 4. We have also added new paragraph (j) in this final rule 
to specify that post-preventive modification inspections (Part 6) are 
not required by this AD. We have redesignated subsequent paragraphs of 
this AD accordingly.

Effect of Winglets on This AD

    Aviation Partners Boeing stated that accomplishing the supplemental 
type certificate (STC) ST01219SE (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect 
accomplishment of the actions specified in the NPRM (79 FR 50867, 
August 26, 2014).
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD (79 FR 50867, August 26, 2014) as (c)(1) and added new 
paragraph (c)(2) to this AD to state that installation of STC ST01219SE 
(http://rgl.faa.gov/

[[Page 43923]]

Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) 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 method of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Explanation of Additional Changes Made to This AD

    We have updated the Costs of Compliance section to add existing 
inspection and repair costs from AD 98-22-10, Amendment 39-10858 (63 FR 
57240, October 27, 1998).
    We have changed paragraph (b) of this AD to add AD 90-06-02, 
Amendment 39-6489, (55 FR 8372, March 7, 1990), as an affected AD since 
accomplishment of the preventative modification required by paragraph 
(h) of this AD is an alternative method of compliance for paragraph A. 
of AD 90-06-02.
    In various locations, Boeing Alert Service Bulletin 737-53A1108, 
Revision 7, dated July 7, 2014, cites Boeing Alert Service Bulletin 
737-53A1108, Revision 6, dated January 9, 2014, instead of Revision 7 
of the service information. We have added a new paragraph (k)(3) in 
this AD to clarify that, where Revision 7 of the service information 
specifies accomplishment of a preventative modification be done using 
Revision 6 of the service information, this AD requires accomplishment 
of that preventative modification with Revision 7 of this service 
information.
    We also noted a discrepancy in table 4 of paragraph 1.E., 
``Compliance,'' in Boeing Alert Service Bulletin 737-53A1108, Revision 
7, dated July 7, 2014. Although the fourth action is an inspection of 
the intercostals ``and attaching stringers,'' the corresponding 
corrective action specified in table 4 is for only a crack in ``an 
intercostal.'' We have confirmed with Boeing that the ``attaching 
stringers'' were inadvertently omitted from this condition in table 4. 
Repair of a cracked attaching stringer, however, is described in PART 
4, paragraph 7, of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014. We have 
added a new paragraph (k)(4) in this AD to specify that cracking in the 
attaching stringers also requires repair.

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:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 50867, August 26, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 50867, August 26, 2014).
    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 737-53A1108, Revision 7, 
dated July 7, 2014. The service information describes procedures for 
inspections for cracking of the aft frame and frame support structure 
of the forward service doorway, and repair if necessary. 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 of this AD.

Costs of Compliance

    We estimate that this AD affects 419 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
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions      7 work-hours x $85  $0................  $595 per            $249,305 per
 from AD 98-22-10, Amendment 39-   per hour = $595                         inspection cycle.   inspection cycle.
 10858 (63 FR 57240, October 27,   per inspection
 1998)].                           cycle.
Inspection [new AD action]......  28 work-hours x     None..............  $2,380 per          $997,220 per
                                   $85 per hour =                          inspection cycle.   inspection cycle.
                                   $2,380 per
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

                                    Estimated Costs for On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                      Cost per
                     Action                                   Labor cost               Parts cost      product
----------------------------------------------------------------------------------------------------------------
Repair [retained actions from AD 98-22-10,        42 work-hours x $85 per hour =             $913        $4,483
 Amendment 39-10858 (63 FR 57240, October 27,      $3,570.
 1998)].
----------------------------------------------------------------------------------------------------------------

                                    Estimated Costs for Optional Modification
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair/preventive modification [new    Between 12 and 17 work-  Between $90 and $913...  Between $1,110 and
 AD action].                            hours x $85 per hour =                            $2,358.
                                        between $1,020 and
                                        $1,445.
----------------------------------------------------------------------------------------------------------------

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

[[Page 43924]]

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) 
98-22-10, Amendment 39-10858 (63 FR 57240, October 27, 1998), and 
adding the following new AD:

2015-15-05 The Boeing Company: Amendment 39-18214; Docket No. FAA-
2014-0572; Directorate Identifier 2014-NM-027-AD.

(a) Effective Date

    This AD is effective August 28, 2015.

(b) Affected ADs

    (1) This AD replaces AD 98-22-10, Amendment 39-10858 (63 FR 
57240, October 27, 1998).
    (2) This AD affects AD 90-06-02, Amendment 39-6489 (55 FR 8372, 
March 7, 1990).

(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-
53A1108, Revision 7, dated July 7, 2014.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) 
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 fatigue cracking of the aft 
frame and frame support structure of the forward service doorway 
around the six doorstop fittings, and a determination that 
inspections are needed in additional locations and that additional 
airplanes might be subject to the identified unsafe condition. We 
are issuing this AD to detect and correct fatigue cracking of the 
aft frame and frame support structure of the forward service doorway 
around the six doorstop fittings, which could result in door 
deflection and loss of pressurization.

(f) Compliance

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

(g) Inspections and Corrective Actions

    At the applicable times specified in tables 1 through 6 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1108, Revision 7, dated July 7, 2014, except as required by 
paragraph (k)(1) of this AD: Do detailed inspections of the frame 
web between body station (STA) 332.1 and STA 344, intercostal T-
brackets, intercostal T-chords, intercostals, and stringers, as 
applicable; do high frequency eddy current (HFEC) inspections for 
cracking of door stop intercostal T-brackets, intercostal web, door 
stop intercostal T-chords, intercostals, and stringers, as 
applicable; and do all applicable related investigative and 
corrective actions; in accordance with Parts 2 and 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1108, Revision 7, dated July 7, 2014, except as required by 
paragraphs (k)(2) through (k)(4) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Repeat the inspections at the applicable times specified in tables 1 
through 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, until the 
terminating action specified in paragraph (h) of this AD is done.

(h) Optional Terminating Action

    For Group 1, Configuration 1; Group 1, Configuration 2; Group 2; 
Group 3; Group 4, Configuration 1; and Group 4, Configuration 2 
airplanes identified in Boeing Alert Service Bulletin 737-53A1108, 
Revision 7, dated July 7, 2014: Accomplishment of a preventive 
modification in accordance with Part 5 of Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, terminates the 
repetitive inspections required by paragraph (g) of this AD.

(i) Inspections and Corrective Actions for Group 5 Airplanes

    For Group 5 airplanes identified in Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014: Within 120 
days after the effective date of this AD, inspect and repair any 
cracking using a method approved in accordance with the procedures 
specified in paragraph (m) of this AD. Repair any cracking, before 
further flight.

(j) Post Preventive Modification Inspections Not Required

    The post preventive modification inspections specified in tables 
9 through 12 in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1108, Revision 6, dated January 9, 2014; and 
Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 
2014; are not required by this AD.

    Note 1 to paragraph (j) of this AD: Tables 9 through 12 in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1108, Revision 6, dated January 9, 2014; and Boeing Alert 
Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014; 
specify that post preventive modification inspections may be used in 
support of compliance with section 121.1109(c)(2) or 129.109(b)(2) 
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 
129.109(b)(2)). The corresponding actions specified in the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014; are not 
required by this AD.

(k) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, specifies a compliance time ``after the issue 
date of Revision 6 of this service bulletin,'' this AD requires 
compliance within the specified time after the effective date of 
this AD.
    (2) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, specifies to contact Boeing for repair 
instructions: Before further flight, repair the cracking using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

[[Page 43925]]

    (3) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, specifies accomplishment of a preventative 
modification in accordance with ``Revision 6 of this service 
bulletin,'' this AD requires accomplishment of those actions to be 
done in accordance with Boeing Alert Service Bulletin 737-53A1108, 
Revision 7, dated July 7, 2014.
    (4) Where table 4 in paragraph 1.E, ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, 
specifies repairing a condition identified as any crack found in 
``an intercostal,'' this AD requires repairing a condition 
identified as any crack found in ``an intercostal or attaching 
stringers.''

(l) Credit for Previous Actions

    This paragraph provides credit for the 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 737-53A1108, Revision 6, dated January 9, 2014. This 
service information is not incorporated by reference in this AD.

(m) 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 (n)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-ACO-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 previously for AD 98-22-10, Amendment 39-
10858 (63 FR 57240, October 27, 1998), are approved as AMOCs for the 
corresponding provisions of this AD.
    (5) Accomplishment of the preventive modification in accordance 
with Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated 
July 7, 2014, as required by paragraph (h) of this AD, is an AMOC 
for the structural modification specified in Boeing Alert Service 
Bulletin 737-53A1108 that is required by paragraph A. of AD 90-06-
02, Amendment 39-6489, (55 FR 8372, March 7, 1990), for the 
airplanes identified in paragraph (h) of this AD.

(n) Related Information

    (1) For more information about this AD, contact Nenita Odesa, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; fax: 562-627-5210; email: nenita.odesa@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraph (o)(3) of this AD.

(o) 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.
    (i) Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated 
July 7, 2014. (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 
206-544-5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) 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 July 10, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17977 Filed 7-23-15; 8:45 am]
BILLING CODE 4910-13-P
```