81 FR 30166 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 94 (May 16, 2016)

Page Range		30166-30170
FR Document		2016-11200
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.
Federal Register, Volume 81 Issue 94 (Monday, May 16, 2016)
[Federal Register Volume 81, Number 94 (Monday, May 16, 2016)]
[Rules and Regulations]
[Pages 30166-30170]
From the Federal Register Online  [www.thefederalregister.org]
[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.

-----------------------------------------------------------------------

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: 
[email protected].

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: [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 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: 
[email protected].

(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
30166 Federal Register / Vol. 81, No. 94 / Monday, May 16, 2016 / Rules and Regulations

The Special Conditions (3) A battery failure sensing and by test or analysis, with the concurrence
■ Accordingly, pursuant to the authority warning system with a means for of the Wichita Aircraft Certification
delegated to me by the Administrator, automatically disconnecting the battery Office.
the following special conditions are from its charging source in the event of Issued in Kansas City, Missouri on May 9,
issued as part of the type certification battery failure. 2016.
basis for Cessna Aircraft Company, 208 h. Any lithium battery installation Pat Mullen,
and 208B Caravan airplanes modified by functionally required for safe operation
Acting Manager, Small Airplane Directorate,
Peregrine. of the airplane, must incorporate a Aircraft Certification Service.
monitoring and warning feature that
1. Installation of Lithium Battery [FR Doc. 2016–11502 Filed 5–13–16; 8:45 am]
will provide an indication to the
BILLING CODE 4910–13–P
The FAA states in this Notice that the appropriate flight crewmembers,
following special conditions be applied whenever the capacity and state of
to lithium battery installations on the charge of the batteries have fallen below
DEPARTMENT OF TRANSPORTATION
208 and 208B airplanes in lieu of the levels considered acceptable for
requirements § 23.1353(a)(b)(c)(d)(e), dispatch of the airplane. Federal Aviation Administration
amendment 49. i. The ICAW must contain
Lithium battery installations on the recommended manufacturer’s 14 CFR Part 39
208 and 208B airplanes must be maintenance and inspection
designed and installed as follows: requirements to ensure that batteries, [Docket No. FAA–2015–2462; Directorate
a. Safe cell temperatures and including single cells, meet a Identifier 2014–NM–224–AD; Amendment
functionally safe level essential to the 39–18515; AD 2016–10–04]
pressures must be maintained during
any probable charging or discharging aircraft’s continued airworthiness. RIN 2120–AA64
condition, or during any failure of the (1) The ICAW must contain operating
charging or battery monitoring system instructions and equipment limitations Airworthiness Directives; The Boeing
not shown to be extremely remote. The in an installation maintenance manual. Company Airplanes
lithium battery installation must be (2) The ICAW must contain
installation procedures and limitations AGENCY: Federal Aviation
designed to preclude explosion or fire in Administration (FAA), DOT.
the event of those failures. in a maintenance manual, sufficient to
ensure that cells or batteries, when ACTION: Final rule.
b. Lithium batteries must be designed
to preclude the occurrence of self- installed according to the installation
SUMMARY: We are adopting a new
sustaining, uncontrolled increases in procedures, still meet safety functional
levels essential to the aircraft’s airworthiness directive (AD) for certain
temperature or pressure. The Boeing Company Model 737–100,
c. No explosive or toxic gasses continued airworthiness. The
limitations must identify any unique –200, –200C, –300, –400, and –500
emitted by any lithium battery in series airplanes. This AD was prompted
normal operation or as the result of any aspects of the installation.
(3) The ICAW must contain corrective by reports of cracked antenna support
failure of the battery charging or channels, skin cracking underneath the
monitoring system, or battery maintenance procedures to check
battery capacity at manufacturer’s number 2 very high frequency (VHF)
installation not shown to be extremely antenna, and cracking in the frames
remote, may accumulate in hazardous recommended inspection intervals.
(4) The ICAW must contain scheduled attached to the internal support
quantities within the airplane. structure. This AD requires repetitive
d. Lithium batteries that contain servicing information to replace
batteries at manufacturer’s inspections to determine the condition
flammable fluids must comply with the of the skin and the internal support
flammable fluid fire protection recommended replacement time.
(5) The ICAW must contain structure, and follow-on actions
requirements of 14 CFR 23.863(a) including corrective action as necessary.
maintenance and inspection
through (d). We are issuing this AD to detect and
requirements how to check visually for
e. No corrosive fluids or gases that correct skin cracking of the fuselage.
battery and charger degradation.
may escape from any lithium battery j. Batteries in a rotating stock (spares) Such cracking could result in separation
may damage airplane structure or that have degraded charge retention of the number 2 VHF antenna from the
essential equipment. capability or other damage due to airplane and rapid depressurization of
f. Each lithium battery installation
prolonged storage must be checked at the cabin.
must have provisions to prevent any
manufacturer’s recommended DATES: This AD is effective June 20,
hazardous effect on structure or
inspection intervals. 2016.
essential systems that may be caused by k. If the lithium battery application
the maximum amount of heat the The Director of the Federal Register
contains software and/or complex approved the incorporation by reference
battery can generate during a short hardware, in accordance with AC 20–
circuit of the battery or of its individual of a certain publication listed in this AD
115 1 and AC 20–152,2 they should be as of June 20, 2016.
cells. developed to the standards of DO–178
g. Lithium battery installations must ADDRESSES: For service information
for software and DO–254 for complex identified in this final rule, contact
have— hardware.
(1) A system to control the charging Boeing Commercial Airplanes,
Compliance with the requirements of
rate of the battery automatically to Attention: Data & Services Management,
this Special Condition must be shown
prevent battery overheating or P.O. Box 3707, MC 2H–65, Seattle, WA
overcharging, or 98124–2207; telephone 206–544–5000,
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1 http://rgl.faa.gov/Regulatory_and_Guidance_
(2) A battery temperature sensing and Library/rgAdvisoryCircular.nsf/0/ extension 1; fax 206–766–5680; Internet
over-temperature warning system with a E35FBC0060E2159186257BBE00719FB3?Open https://www.myboeingfleet.com. You
means for automatically disconnecting Document&Highlight=ac%2020-115b. may view this referenced service
2 http://rgl.faa.gov/Regulatory_and_Guidance_
the battery from its charging source in Library/rgAdvisoryCircular.nsf/0/
information at the FAA, Transport
the event of an over-temperature 6D4AE0BF1BDE3579862570360055D119?Open Airplane Directorate, 1601 Lind Avenue
condition or, Document&Highlight=ac%2020-152. SW., Renton, WA. For information on

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Federal Register / Vol. 81, No. 94 / Monday, May 16, 2016 / Rules and Regulations 30167

the availability of this material at the received on the NPRM and the FAA’s Request To Add Terminating Action to
FAA, call 425–227–1221. It is also response to each comment. Boeing Paragraphs (h)(1) and (h)(2) of the
available on the Internet at http:// concurred with the NPRM. Proposed AD
www.regulations.gov by searching for British Airways asked why the
and locating Docket No. FAA–2015– Request To Correct a Typographical
Error in Paragraph (h)(4) of the terminating action specified in
2462. paragraph (k)(3) of the proposed AD is
Proposed AD
Examining the AD Docket not included in the text ‘‘until the
Southwest Airlines requested that we accomplishment of paragraphs’’
You may examine the AD docket on
correct a typographical error in references in paragraphs (h)(1) and
the Internet at http://
paragraph (h)(4) of the proposed AD, (h)(2) of the proposed AD. We infer
www.regulations.gov by searching for
which states that accomplishment of the British Airways is requesting that we
and locating Docket No. FAA–2015–
preventative modification terminates revise paragraphs (h)(1) and (h)(2) of the
2462; or in person at the Docket
the inspection required by ‘‘paragraphs proposed AD.
Management Facility between 9 a.m.
(g), (g)(1), and (h)(2) of the AD.’’ We agree with the commenter because
and 5 p.m., Monday through Friday,
Southwest Airlines noted that the installation of the preventive
except Federal holidays. The AD docket
NPRM does not contain paragraph modification in accordance with
contains this AD, the regulatory
(g)(1). Southwest Airlines concluded paragraph (k)(3) of this AD is acceptable
evaluation, any comments received, and
that this appears to be a typographical for terminating the repetitive
other information. The address for the
error and the references to paragraphs inspections. In addition, we note the
Docket Office (phone: 800–647–5527) is
(g) and (g)(1) of the proposed AD should reference to paragraph (k)(1) of this AD
Document Management Facility, U.S.
be to paragraphs (h) and (h)(1) of the in paragraph (h)(2) of this AD is
Department of Transportation, Docket
redundant. We have made the following
Operations, M–30, West Building proposed AD, similar to what is stated
changes to this AD:
Ground Floor, Room W12–140, 1200 in paragraph (k)(3) of the proposed AD.
• In paragraph (h)(1) of this AD, we
New Jersey Avenue SE., Washington, British Airways stated that it has specify to repeat the inspections ‘‘until
DC 20590. identified a potential contradiction the accomplishment of paragraph (k)(1),
FOR FURTHER INFORMATION CONTACT: between paragraphs (h)(4) and (k)(3) of (k)(2), or (k)(3) of this AD, as
Jennifer Tsakoumakis, Aerospace the proposed AD. British Airways stated applicable.’’
Engineer, Airframe Branch, ANM–120L, that paragraph (h)(4) of the proposed AD • In paragraph (h)(2) of this AD, we
FAA, Los Angeles Aircraft Certification refers to paragraph (h)(2), whereas specify to repeat the inspections ‘‘until
Office (ACO), 3960 Paramount paragraph (k)(3) of the proposed AD the accomplishment of paragraph (k)(2)
Boulevard, Lakewood, CA 90712–4137; refers to paragraphs (h), (h)(1), and or (k)(3) of this AD, as applicable.’’
phone: 562–627–5264; fax: 562–627– (h)(2) of the proposed AD.
5210; email: jennifer.tsakoumakis@ Request To Correct the Language in
faa.gov. We agree to revise paragraph (h)(4) of Paragraph (h)(2) of the Proposed AD
this AD because there is a typographical
SUPPLEMENTARY INFORMATION: Southwest Airlines requested a
error. We have changed the references
correction to the language in paragraph
Discussion in paragraph (h)(4) of this AD to specify (h)(2) of the proposed AD to add the
paragraphs (h), (h)(1), and (h)(2) of this term ‘‘as applicable’’ after the listed
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR AD. This change resolves the inspections. Southwest Airlines stated
part 39 by adding an AD that would contradiction noted by British Airways. that there are multiple sections of Part
apply to certain The Boeing Company Request a Provision To Terminate 2 of the Accomplishment Instructions of
Model 737–100, –200, –200C, –300, Inspections Required by Paragraph (h) Boeing Special Attention Service
–400, and –500 series airplanes. The of the Proposed AD Bulletin 737–53–1159, Revision 1, dated
NPRM published in the Federal October 20, 2014. Southwest Airlines
Register on July 20, 2015 (80 FR 42756) Southwest Airlines requested that we noted that each group/configuration has
(‘‘the NPRM’’). The NPRM was provide a provision to terminate the its own Part 2 instructions and that
prompted by reports of cracked antenna inspections required by paragraph (h) of Groups 3 through 6, Configurations 2
support channels, skin cracking the proposed AD for previously and 3, do not contain instructions for
underneath the number 2 VHF antenna, installed repairs that have received FAA internal detailed inspections or internal
and cracking in the frames attached to approval. The commenter stated that high frequency eddy current
the internal support structure. The these repairs would inhibit the inspections.
NPRM proposed to require repetitive inspections required by paragraph (h) of We agree with the commenter because
inspections to determine the condition this AD. certain inspections are applicable to
of the skin and the internal support only certain configurations. We have
We do not agree with the commenter’s added the language ‘‘as applicable’’ to
structure, and follow-on actions
request because previously installed paragraph (h)(2) of this AD.
including corrective action as necessary.
We are issuing this AD to detect and FAA-approved repairs may not have
been designed to address the specified Request To Revise Certain Paragraphs
correct skin cracking of the fuselage.
unsafe condition identified in this AD. To Include a Terminating Action for the
Such cracking could result in separation
We understand that some of these Preventive Modification
of the number 2 VHF antenna from the
airplane and rapid depressurization of repairs may not allow inspection of the Southwest Airlines requested that we
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the cabin. area specified in the AD; in those cases, revise paragraph (k)(2) of the proposed
the operator must request approval for AD to include a statement that
Comments an alternative method of compliance accomplishment of the repair specified
We gave the public the opportunity to (AMOC) according to paragraph (m) of in paragraph (h)(3) of the proposed AD
participate in developing this AD. The this AD. We have not revised this AD also terminates the preventive
following presents the comments in this regard. modification specified in paragraph

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30168 Federal Register / Vol. 81, No. 94 / Monday, May 16, 2016 / Rules and Regulations

(h)(4) of the proposed AD. Southwest We agree with the commenter’s required by maintenance and
Airlines stated that there is no language request because repairs installed in operational rules; therefore, these
in the NPRM or Boeing Special accordance with Part 3 of the inspections are not required by this AD.
Attention Service Bulletin 737–53– Accomplishment Instructions of Boeing
Conclusion
1159, Revision 1, dated October 20, Special Attention Service Bulletin 737–
2014, that states whether the 53–1159, Revision 1, dated October 20, We reviewed the relevant data,
preventative modification is required 2014, prior to the effective date of this considered the comments received, and
after the repair is installed. AD, will not allow accomplishment of determined that air safety and the
the initial inspections as specified in public interest require adopting this AD
We do not agree with the commenter’s
paragraph (h) of this AD. We revised with the changes described previously
request because, for some airplane
paragraph (k)(2) of this AD to specify and minor editorial changes. We have
configurations, the repair only installs
that accomplishment of the repair determined that these minor changes:
an external skin doubler and the
required by paragraph (h)(3) of this AD • Are consistent with the intent that
preventative modification includes
terminates the initial and repetitive was proposed in the NPRM for
replacement of the internal support
inspections required in paragraphs (h), correcting the unsafe condition; and
structure. For some airplane
(h)(1), and (h)(2) of this AD. • Do not add any additional burden
configurations, the preventive
upon the public than was already
modification specified in Part 4 of the Effect of Winglets on Accomplishment
proposed in the NPRM.
Accomplishment Instructions of Boeing of the Proposed Actions
We also determined that these
Special Attention Service Bulletin 737– Aviation Partners Boeing stated that changes will not increase the economic
53–1159, Revision 1, dated October 20, accomplishing Supplemental Type burden on any operator or increase the
2014, is required after installation of the Certificate (STC) ST01219SE (http:// scope of this AD.
repair specified in Part 3 of the rgl.faa.gov/Regulatory_and_Guidance_
Accomplishment Instructions of Boeing Library/rgstc.nsf/0/ Related Service Information Under 1
Special Attention Service Bulletin 737– be866b732f6cf31086257b9700692796/ CFR Part 51
53–1159, Revision 1, dated October 20, $FILE/ST01219SE.pdf) does not affect We reviewed Boeing Special
2014. We have not revised this AD in the actions specified in the NPRM. Attention Service Bulletin 737–53–
this regard. We concur with the commenter. We 1159, Revision 1, dated October 20,
Request To Provide Statement for have redesignated paragraph (c) of the 2014. The service information describes
Terminating Actions in Paragraph proposed AD as paragraph (c)(1) of this procedures for repetitive inspections to
(k)(2) of the Proposed AD AD and added new paragraph (c)(2) to determine the condition of the skin and
this AD to state that installation of STC the internal support structure, and
Southwest Airlines requested that we ST01219SE does not affect the ability to follow-on actions including corrective
revise paragraph (k)(2) of the proposed accomplish the actions required by this action as necessary. This service
AD to specify the repair also terminates AD. Therefore, for airplanes on which information is reasonably available
the initial inspections in paragraph (h) STC ST01219SE is installed, a ‘‘change because the interested parties have
of the proposed AD. Southwest Airlines in product’’ AMOC approval request is access to it through their normal course
stated that the current statement in not necessary to comply with the of business or by the means identified
paragraph (k)(2) of the proposed AD requirements of 14 CFR 39.17. in the ADDRESSES section.
does not address a terminating action
for the initial inspection specified in Change to Paragraph (j) of This AD Costs of Compliance
paragraphs (h)(1) and (h)(2) of the We have revised paragraph (j) of this We estimate that this AD affects 609
proposed AD for aircraft that have AD to clarify that the post-repair and airplanes of U.S. registry.
previously installed the repair specified post-modification inspections are We estimate the following costs to
in paragraph (h)(3) of the proposed AD. airworthiness limitations that are comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspections ..... 33 work-hours × $85 per hour = $0 $2,805 per inspection cycle ........... $1,708,245 per inspection cycle.
$2,805 per inspection cycle.

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

ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product

Repair and preventive modification .............................. 63 work-hours × $85 per hour = $5,355 ...................... $10,432 $15,787
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According to the manufacturer, some do not control warranty coverage for Authority for This Rulemaking
of the costs of this AD may be covered affected individuals. As a result, we
under warranty, thereby reducing the have included all costs in our cost Title 49 of the United States Code
cost impact on affected individuals. We estimate. specifies the FAA’s authority to issue

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Federal Register / Vol. 81, No. 94 / Monday, May 16, 2016 / Rules and Regulations 30169

rules on aviation safety. Subtitle I, 2016–10–04 The Boeing Company: applicable corrective actions, in accordance
section 106, describes the authority of Amendment 39–18515; Docket No. with Part 1 of the Accomplishment
the FAA Administrator. Subtitle VII: FAA–2015–2462; Directorate Identifier Instructions of Boeing Special Attention
2014–NM–224–AD. Service Bulletin 737–53–1159, Revision 1,
Aviation Programs, describes in more dated October 20, 2014. Thereafter, at the
detail the scope of the Agency’s (a) Effective Date applicable time specified in paragraph 1.E.,
authority. This AD is effective June 20, 2016. ‘‘Compliance,’’ of Boeing Special Attention
We are issuing this rulemaking under Service Bulletin 737–53–1159, Revision 1,
(b) Affected ADs
the authority described in Subtitle VII, dated October 20, 2014, except as required by
Part A, Subpart III, Section 44701: None. paragraph (l)(1) of this AD: Do all applicable
‘‘General requirements.’’ Under that (c) Applicability actions specified in paragraphs (h)(1) through
section, Congress charges the FAA with (h)(4) of this AD.
(1) This AD applies to The Boeing (1) Repeat the Part 1 inspections specified
promoting safe flight of civil aircraft in Company Model 737–100, –200, –200C, in paragraph (h) of this AD until the
air commerce by prescribing regulations –300, –400, and –500 series airplanes, accomplishment of paragraph (k)(1), (k)(2), or
for practices, methods, and procedures certificated in any category, as identified in (k)(3) of this AD, as applicable.
the Administrator finds necessary for Boeing Special Attention Service Bulletin (2) Inspect for cracking at the number 2
safety in air commerce. This regulation 737–53–1159, Revision 1, dated October 20, VHF antenna location using internal and
is within the scope of that authority 2014. external detailed inspections, internal and
(2) Installation of Supplemental Type external high frequency eddy current (HFEC)
because it addresses an unsafe condition Certificate (STC) ST01219SE (http://
that is likely to exist or develop on inspections, and an HFEC open-hole
rgl.faa.gov/Regulatory_and_Guidance_ inspection, as applicable, in accordance with
products identified in this rulemaking Library/rgstc.nsf/0/
action. Part 2 of the Accomplishment Instructions of
be866b732f6cf31086257b9700692796/$FILE/ Boeing Special Attention Service Bulletin
ST01219SE.pdf) does not affect the ability to
Regulatory Findings 737–53–1159, Revision 1, dated October 20,
accomplish the actions required by this AD.
2014. Repeat the inspections until the
This AD will not have federalism Therefore, for airplanes on which STC
accomplishment of paragraph (k)(2) or (k)(3)
implications under Executive Order ST01219SE is installed, a ‘‘change in
of this AD, as applicable.
13132. This AD will not have a product’’ alternative method of compliance
(3) Repair any crack found, in accordance
(AMOC) approval request is not necessary to
substantial direct effect on the States, on with Part 3 of the Accomplishment
comply with the requirements of 14 CFR
the relationship between the national 39.17.
Instructions of Boeing Special Attention
government and the States, or on the Service Bulletin 737–53–1159, Revision 1,
distribution of power and (d) Subject dated October 20, 2014, except as required by
responsibilities among the various Air Transport Association (ATA) of paragraph (l)(2) of this AD.
America Code 53, Fuselage. (4) Do a preventive modification, in
levels of government. accordance with Part 4 of the
For the reasons discussed above, I (e) Unsafe Condition Accomplishment Instructions of Boeing
certify that this AD: Special Attention Service Bulletin 737–53–
This AD was prompted by reports of
(1) Is not a ‘‘significant regulatory cracked antenna support channels, skin 1159, Revision 1, dated October 20, 2014,
action’’ under Executive Order 12866, cracking underneath the number 2 VHF except as specified in paragraph (l)(2) of this
(2) Is not a ‘‘significant rule’’ under antenna, and cracking in the frames attached AD. The accomplishment of this preventive
DOT Regulatory Policies and Procedures to the internal support structure. We are modification terminates the inspections
(44 FR 11034, February 26, 1979), issuing this AD to detect and correct skin required by paragraphs (h), (h)(1), and (h)(2)
(3) Will not affect intrastate aviation cracking of the fuselage. Such cracking could of this AD.
in Alaska, and result in separation of the number 2 VHF (i) Inspection and Follow-On Actions:
(4) Will not have a significant antenna from the airplane and rapid Groups 3 Through 6, Configuration 4
economic impact, positive or negative, depressurization of the cabin.
For airplanes identified as Groups 3
on a substantial number of small entities (f) Compliance through 6, Configuration 4, in Boeing Special
under the criteria of the Regulatory Comply with this AD within the Attention Service Bulletin 737–53–1159,
Flexibility Act. compliance times specified, unless already Revision 1, dated October 20, 2014: At the
done. applicable time specified in table 10 of
List of Subjects in 14 CFR Part 39 paragraph 1.E., ‘‘Compliance,’’ of Boeing
(g) Inspection and Follow-On Actions: Special Attention Service Bulletin 737–53–
Air transportation, Aircraft, Aviation
Group 1 1159, Revision 1, dated October 20, 2014,
safety, Incorporation by reference,
For airplanes identified as Group 1 in except as required by paragraph (l)(1) of this
Safety. AD, do an external detailed inspection for
Boeing Special Attention Service Bulletin
Adoption of the Amendment 737–53–1159, Revision 1, dated October 20, cracking at the outer row of fasteners
2014: Within 120 days after the effective date common to the internal repair doubler, and
Accordingly, under the authority of this AD, inspect for cracking at the number do an internal general visual inspection for
delegated to me by the Administrator, 2 VHF antenna location, and do all cracking on the modified internal support
the FAA amends 14 CFR part 39 as applicable follow-on actions, using a method structure of the number 2 VHF antenna, skin,
follows: approved in accordance with the procedures and surrounding stringers, channel, and
specified in paragraph (m) of this AD. frames, in accordance with the
PART 39—AIRWORTHINESS Accomplishment Instructions of Boeing
(h) Inspection and Follow-On Actions: Special Attention Service Bulletin 737–53–
DIRECTIVES
Groups 2 Through 6, Configurations 1 1159, Revision 1, dated October 20, 2014.
Through 3 (1) If any cracking is found, before further
■ 1. The authority citation for part 39
continues to read as follows: For airplanes identified as Groups 2 flight, repair using a method approved in
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through 6, Configurations 1 through 3 in accordance with the procedures specified in
Authority: 49 U.S.C. 106(g), 40113, 44701. Boeing Special Attention Service Bulletin paragraph (m) of this AD.
737–53–1159, Revision 1, dated October 20, (2) If no cracking is found, repeat the
§ 39.13 [Amended]
2014: Within 1,250 flight cycles after the inspections at the time specified in table 10
■ 2. The FAA amends § 39.13 by adding effective date of this AD, do an external of paragraph 1.E., ‘‘Compliance,’’ of Boeing
the following new airworthiness detailed inspection for cracking of the Special Attention Service Bulletin 737–53–
directive (AD): fuselage skin, as applicable, and do all 1159, Revision 1, dated October 20, 2014.

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Document Created: 2016-05-14 01:16:59
Document Modified: 2016-05-14 01:16:59
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective June 20, 2016.
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]
FR Citation		81 FR 30166
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 30166 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 94 (May 16, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
