
[Federal Register Volume 81, Number 94 (Monday, May 16, 2016)]
[Rules and Regulations]
[Pages 30166-30170]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11200]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2462; Directorate Identifier 2014-NM-224-AD; 
Amendment 39-18515; AD 2016-10-04]
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 adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This AD was prompted by reports of cracked antenna 
support channels, skin cracking underneath the number 2 very high 
frequency (VHF) antenna, and cracking in the frames attached to the 
internal support structure. This AD requires repetitive inspections to 
determine the condition of the skin and the internal support structure, 
and follow-on actions including corrective action as necessary. We are 
issuing this AD to detect and correct skin cracking of the fuselage. 
Such cracking could result in separation of the number 2 VHF antenna 
from the airplane and rapid depressurization of the cabin.

DATES: This AD is effective June 20, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 20, 
2016.

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 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

[[Page 30167]]

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-2015-2462.

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-
2462; 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 Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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: 
jennifer.tsakoumakis@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on July 20, 2015 (80 FR 42756) 
(``the NPRM''). The NPRM was prompted by reports of cracked antenna 
support channels, skin cracking underneath the number 2 VHF antenna, 
and cracking in the frames attached to the internal support structure. 
The NPRM proposed to require repetitive inspections to determine the 
condition of the skin and the internal support structure, and follow-on 
actions including corrective action as necessary. We are issuing this 
AD to detect and correct skin cracking of the fuselage. Such cracking 
could result in separation of the number 2 VHF antenna from the 
airplane and rapid depressurization of the cabin.

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. Boeing concurred with the NPRM.

Request To Correct a Typographical Error in Paragraph (h)(4) of the 
Proposed AD

    Southwest Airlines requested that we correct a typographical error 
in paragraph (h)(4) of the proposed AD, which states that 
accomplishment of the preventative modification terminates the 
inspection required by ``paragraphs (g), (g)(1), and (h)(2) of the 
AD.'' Southwest Airlines noted that the NPRM does not contain paragraph 
(g)(1). Southwest Airlines concluded that this appears to be a 
typographical error and the references to paragraphs (g) and (g)(1) of 
the proposed AD should be to paragraphs (h) and (h)(1) of the proposed 
AD, similar to what is stated in paragraph (k)(3) of the proposed AD.
    British Airways stated that it has identified a potential 
contradiction between paragraphs (h)(4) and (k)(3) of the proposed AD. 
British Airways stated that paragraph (h)(4) of the proposed AD refers 
to paragraph (h)(2), whereas paragraph (k)(3) of the proposed AD refers 
to paragraphs (h), (h)(1), and (h)(2) of the proposed AD.
    We agree to revise paragraph (h)(4) of this AD because there is a 
typographical error. We have changed the references in paragraph (h)(4) 
of this AD to specify paragraphs (h), (h)(1), and (h)(2) of this AD. 
This change resolves the contradiction noted by British Airways.

Request a Provision To Terminate Inspections Required by Paragraph (h) 
of the Proposed AD

    Southwest Airlines requested that we provide a provision to 
terminate the inspections required by paragraph (h) of the proposed AD 
for previously installed repairs that have received FAA approval. The 
commenter stated that these repairs would inhibit the inspections 
required by paragraph (h) of this AD.
    We do not agree with the commenter's request because previously 
installed FAA-approved repairs may not have been designed to address 
the specified unsafe condition identified in this AD. We understand 
that some of these repairs may not allow inspection of the area 
specified in the AD; in those cases, the operator must request approval 
for an alternative method of compliance (AMOC) according to paragraph 
(m) of this AD. We have not revised this AD in this regard.

Request To Add Terminating Action to Paragraphs (h)(1) and (h)(2) of 
the Proposed AD

    British Airways asked why the terminating action specified in 
paragraph (k)(3) of the proposed AD is not included in the text ``until 
the accomplishment of paragraphs'' references in paragraphs (h)(1) and 
(h)(2) of the proposed AD. We infer British Airways is requesting that 
we revise paragraphs (h)(1) and (h)(2) of the proposed AD.
    We agree with the commenter because installation of the preventive 
modification in accordance with paragraph (k)(3) of this AD is 
acceptable for terminating the repetitive inspections. In addition, we 
note the reference to paragraph (k)(1) of this AD in paragraph (h)(2) 
of this AD is redundant. We have made the following changes to this AD:
     In paragraph (h)(1) of this AD, we specify to repeat the 
inspections ``until the accomplishment of paragraph (k)(1), (k)(2), or 
(k)(3) of this AD, as applicable.''
     In paragraph (h)(2) of this AD, we specify to repeat the 
inspections ``until the accomplishment of paragraph (k)(2) or (k)(3) of 
this AD, as applicable.''

Request To Correct the Language in Paragraph (h)(2) of the Proposed AD

    Southwest Airlines requested a correction to the language in 
paragraph (h)(2) of the proposed AD to add the term ``as applicable'' 
after the listed inspections. Southwest Airlines stated that there are 
multiple sections of Part 2 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, 
dated October 20, 2014. Southwest Airlines noted that each group/
configuration has its own Part 2 instructions and that Groups 3 through 
6, Configurations 2 and 3, do not contain instructions for internal 
detailed inspections or internal high frequency eddy current 
inspections.
    We agree with the commenter because certain inspections are 
applicable to only certain configurations. We have added the language 
``as applicable'' to paragraph (h)(2) of this AD.

Request To Revise Certain Paragraphs To Include a Terminating Action 
for the Preventive Modification

    Southwest Airlines requested that we revise paragraph (k)(2) of the 
proposed AD to include a statement that accomplishment of the repair 
specified in paragraph (h)(3) of the proposed AD also terminates the 
preventive modification specified in paragraph

[[Page 30168]]

(h)(4) of the proposed AD. Southwest Airlines stated that there is no 
language in the NPRM or Boeing Special Attention Service Bulletin 737-
53-1159, Revision 1, dated October 20, 2014, that states whether the 
preventative modification is required after the repair is installed.
    We do not agree with the commenter's request because, for some 
airplane configurations, the repair only installs an external skin 
doubler and the preventative modification includes replacement of the 
internal support structure. For some airplane configurations, the 
preventive modification specified in Part 4 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014, is required after installation of 
the repair specified in Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, 
dated October 20, 2014. We have not revised this AD in this regard.

Request To Provide Statement for Terminating Actions in Paragraph 
(k)(2) of the Proposed AD

    Southwest Airlines requested that we revise paragraph (k)(2) of the 
proposed AD to specify the repair also terminates the initial 
inspections in paragraph (h) of the proposed AD. Southwest Airlines 
stated that the current statement in paragraph (k)(2) of the proposed 
AD does not address a terminating action for the initial inspection 
specified in paragraphs (h)(1) and (h)(2) of the proposed AD for 
aircraft that have previously installed the repair specified in 
paragraph (h)(3) of the proposed AD.
    We agree with the commenter's request because repairs installed in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 737-53-1159, Revision 1, dated 
October 20, 2014, prior to the effective date of this AD, will not 
allow accomplishment of the initial inspections as specified in 
paragraph (h) of this AD. We revised paragraph (k)(2) of this AD to 
specify that accomplishment of the repair required by paragraph (h)(3) 
of this AD terminates the initial and repetitive inspections required 
in paragraphs (h), (h)(1), and (h)(2) of this AD.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing Supplemental 
Type Certificate (STC) ST01219SE (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) does not affect 
the actions specified in the NPRM.
    We concur with the commenter. We have redesignated paragraph (c) of 
the proposed AD as paragraph (c)(1) of this AD and added new paragraph 
(c)(2) to this AD to state that installation of STC ST01219SE does not 
affect the ability to accomplish the actions required by this AD. 
Therefore, for airplanes on which STC ST01219SE is installed, a 
``change in product'' AMOC approval request is not necessary to comply 
with the requirements of 14 CFR 39.17.

Change to Paragraph (j) of This AD

    We have revised paragraph (j) of this AD to clarify that the post-
repair and 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:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     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 Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014. The service information describes 
procedures for repetitive inspections to determine the condition of the 
skin and the internal support structure, and follow-on actions 
including corrective action as 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.

Costs of Compliance

    We estimate that this AD affects 609 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                 Labor cost          Parts cost       Cost per product           operators
----------------------------------------------------------------------------------------------------------------
Inspections..............  33 work-hours x $85                 $0  $2,805 per inspection   $1,708,245 per
                            per hour = $2,805 per                   cycle.                  inspection cycle.
                            inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair and preventive modification............  63 work-hours x $85 per hour =           $10,432         $15,787
                                                 $5,355.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 30169]]

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 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 adding the following new airworthiness 
directive (AD):

2016-10-04 The Boeing Company: Amendment 39-18515; Docket No. FAA-
2015-2462; Directorate Identifier 2014-NM-224-AD.

(a) Effective Date

    This AD is effective June 20, 2016.

(b) Affected ADs

    None.

(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 Special Attention Service Bulletin 
737-53-1159, Revision 1, dated October 20, 2014.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/be866b732f6cf31086257b9700692796/$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 cracked antenna support 
channels, skin cracking underneath the number 2 VHF antenna, and 
cracking in the frames attached to the internal support structure. 
We are issuing this AD to detect and correct skin cracking of the 
fuselage. Such cracking could result in separation of the number 2 
VHF antenna from the airplane and rapid depressurization of the 
cabin.

(f) Compliance

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

(g) Inspection and Follow-On Actions: Group 1

    For airplanes identified as Group 1 in Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: 
Within 120 days after the effective date of this AD, inspect for 
cracking at the number 2 VHF antenna location, and do all applicable 
follow-on actions, using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

(h) Inspection and Follow-On Actions: Groups 2 Through 6, 
Configurations 1 Through 3

    For airplanes identified as Groups 2 through 6, Configurations 1 
through 3 in Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014: Within 1,250 flight cycles after 
the effective date of this AD, do an external detailed inspection 
for cracking of the fuselage skin, as applicable, and do all 
applicable corrective actions, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014. 
Thereafter, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-
1159, Revision 1, dated October 20, 2014, except as required by 
paragraph (l)(1) of this AD: Do all applicable actions specified in 
paragraphs (h)(1) through (h)(4) of this AD.
    (1) Repeat the Part 1 inspections specified in paragraph (h) of 
this AD until the accomplishment of paragraph (k)(1), (k)(2), or 
(k)(3) of this AD, as applicable.
    (2) Inspect for cracking at the number 2 VHF antenna location 
using internal and external detailed inspections, internal and 
external high frequency eddy current (HFEC) inspections, and an HFEC 
open-hole inspection, as applicable, in accordance with Part 2 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014. Repeat the 
inspections until the accomplishment of paragraph (k)(2) or (k)(3) 
of this AD, as applicable.
    (3) Repair any crack found, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as 
required by paragraph (l)(2) of this AD.
    (4) Do a preventive modification, in accordance with Part 4 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as 
specified in paragraph (l)(2) of this AD. The accomplishment of this 
preventive modification terminates the inspections required by 
paragraphs (h), (h)(1), and (h)(2) of this AD.

(i) Inspection and Follow-On Actions: Groups 3 Through 6, Configuration 
4

    For airplanes identified as Groups 3 through 6, Configuration 4, 
in Boeing Special Attention Service Bulletin 737-53-1159, Revision 
1, dated October 20, 2014: At the applicable time specified in table 
10 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, 
except as required by paragraph (l)(1) of this AD, do an external 
detailed inspection for cracking at the outer row of fasteners 
common to the internal repair doubler, and do an internal general 
visual inspection for cracking on the modified internal support 
structure of the number 2 VHF antenna, skin, and surrounding 
stringers, channel, and frames, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
    (1) If any cracking is found, before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD.
    (2) If no cracking is found, repeat the inspections at the time 
specified in table 10 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 737-53-1159, Revision 1, dated 
October 20, 2014.

[[Page 30170]]

(j) Post Repair/Post Modification Inspections

    Tables 7 through 9 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 737-53-1159, Revision 1, dated 
October 20, 2014, specify post-repair and post-modification 
airworthiness limitation inspections in compliance with 14 CFR 
25.571(a)(3) at the repaired and 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.

(k) Terminating Action Provisions

    The following describes terminating action for the airplane 
groups and configurations, as identified in Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
    (1) For airplanes in Group 2, Configuration 2; and Groups 3 
through 6, Configuration 2: Accomplishment of the inspections 
specified in paragraph (h)(2) of this AD terminates the repetitive 
inspection requirements of paragraph (h)(1) of this AD.
    (2) For airplanes in Group 2, Configuration 1; and Groups 3 
through 6, Configurations 1, 2, and 3: Accomplishment of the repair 
specified in paragraph (h)(3) of this AD terminates the initial and 
repetitive inspections specified in paragraphs (h), (h)(1), and 
(h)(2) of this AD.
    (3) For airplanes in Group 2, Configuration 1; and Groups 3 
through 6, Configurations 1 and 3: Accomplishment of the preventive 
modification specified in paragraph (h)(4) of this AD terminates the 
initial and repetitive inspections specified in paragraphs (h), 
(h)(1), and (h)(2) of this AD.

(l) Exception to Service Bulletin Specifications

    (1) Where Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014, 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 Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014, specifies to contact Boeing for 
appropriate action, and specifies that action as ``RC'' (Required 
for Compliance): Before further flight, repair the cracking using a 
method approved in accordance with the procedures specified in 
paragraph (m) of 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) 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, modification, or alteration required by this AD 
if it is approved by 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 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) Except as required by paragraph (l)(2) of this AD, for 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (m)(4)(i) and 
(m)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    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: 
jennifer.tsakoumakis@faa.gov.

(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 Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (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 May 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-11200 Filed 5-13-16; 8:45 am]
 BILLING CODE 4910-13-P


