[Federal Register Volume 83, Number 11 (Wednesday, January 17, 2018)]
[Proposed Rules]
[Pages 2378-2382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00109]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9523; Product Identifier 2016-NM-134-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: We are revising an earlier proposal to supersede Airworthiness 
Directive (AD) 2014-12-13, which applies to all The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
first SNPRM proposed to revise the proposal by expanding the inspection 
area, and terminating, rather than superseding, the requirements of AD 
2014-12-13, after accomplishment of the initial inspections. This 
action proposes to again revise the proposal by requiring the 
installation of standard-size fasteners for a certain configuration. We 
are proposing this AD to address the unsafe condition on these 
products. Since these actions impose an additional burden over that 
proposed in the first SNPRM, we are reopening the comment period to 
allow the public the chance to comment on these proposed changes.

DATES: The comment period for the SNPRM published in the Federal 
Register on August 11, 2017 (82 FR 37549), is reopened.
    We must receive comments on this SNPRM by March 5, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this SNPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 
562-797-1717; internet https://www.myboeingfleet.com. You may view this 
referenced service information at the FAA, Transport Standards Branch, 
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-2016-9523.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9523; 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 SNPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-
5210; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-9523; 
Product Identifier 2016-NM-134-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this SNPRM. We will consider all 
comments received by the closing date and may amend this SNPRM because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2014-12-13, Amendment 39-17874 (79 FR 39300, July 10, 
2014) (``AD 2014-12-13''). AD 2014-12-13 requires actions to address an 
unsafe condition on all The Boeing Company Model 737-100, -200, -200C,

[[Page 2379]]

-300, -400, and -500 series airplanes. AD 2014-12-13 requires 
repetitive inspections for cracking of the aft support fitting for the 
main landing gear (MLG) beam, and the rear spar upper chord and rear 
spar web; and repair if necessary.
    We issued an NPRM to amend 14 CFR part 39 by adding an AD to 
supersede AD 2014-12-13 that would apply to all The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on January 5, 2017 (82 FR 1254) 
(``the NPRM''). The NPRM was prompted by reports of cracking in 
locations outside the inspection area identified in AD 2014-12-13, in 
the inspar upper skin at Wing Buttock Line (WBL) 157 and in the skin at 
two holes common to the rear spar in the same area, and in the rear 
spar web on both wings. Subsequent inspections revealed that the right 
rear spar upper chord was almost completely severed and the left rear 
spar upper chord was completely severed. The NPRM proposed to expand 
the inspection area and add applicable related investigative and 
corrective actions.
    We subsequently issued an SNPRM, which was published in the Federal 
Register on August 11, 2017 (82 FR 37549) (``the first SNPRM''). The 
first SNPRM was prompted by reports of additional cracking in the 
inspar upper skin at WBL 157 and in the skin at two holes common to the 
rear spar in the same area, and rear spar web cracks were also noted on 
both wings. The first SNPRM proposed to expand the inspection area and 
terminate (rather than supersede) the requirements of AD 2014-12-13, 
after accomplishment of the initial inspections.

Actions Since the First SNPRM Was Issued

    Since we issued the first SNPRM, we have determined that standard-
size fasteners are required for installation for a certain 
configuration, as explained below under ``Request to Install Standard-
Size Fasteners.''

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-57A1318, Revision 1, 
dated July 22, 2016. The service information describes procedures for 
repetitive high frequency eddy current (HFEC) open hole inspections for 
any cracking in the forward support fitting, the aft support fitting, 
the rear spar upper chord, and the rear spar web at the 12 fastener 
holes (locations 1-12). The service information also describes 
procedures for optional HFEC open hole inspections for any cracking in 
the forward support fitting, the aft support fitting, the rear spar 
upper chord, and the rear spar web, and HFEC surface inspections for 
any cracking in the rear spar upper chord and rear spar upper web, as 
applicable. The service information also describes procedures for 
related investigative and corrective actions.
    We also reviewed Boeing Alert Service Bulletin 737-57A1328, dated 
July 22, 2016. The service information describes procedures for 
repetitive eddy current inspections of the left and right wing for any 
cracking in the inspar upper skin and at the repair parts if 
applicable, and related investigative and corrective actions.
    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.

Comments

    We gave the public the opportunity to comment on the first SNPRM. 
The following presents the comments received on the first SNPRM and the 
FAA's response to each comment.

Request To Install Standard-Size Fasteners

    Boeing requested that standard-size fasteners be used for 
installation on the airplane instead of same-type and same-size 
fasteners. Boeing stated that for Group 7, Configuration 1 airplanes 
specified in Boeing Alert Service Bulletin 737-57A1318, Revision 1, 
dated July 22, 2016, the service information specifies to install 
standard-size fasteners (not oversize) and specifies a loose-fit design 
feature common to the aft fitting at fastener #5. Boeing commented that 
the loose-fit design feature is consistent with the type design and 
decreases the potential for future cracking. Boeing also stated that if 
the actions of Boeing Special Attention Service Bulletin 737-57-1318, 
dated May 15, 2013, have been done, it is possible that the fasteners 
have already been oversized and the loose-fit design feature has 
already been eliminated. Boeing commented that this recommendation will 
allow the opportunity to restore the fastener #5 location to the 
intended fastener fit (i.e., loose fit in the aft fitting and tight fit 
in the forward fitting, web and chord).
    We agree with the commenter for the reasons provided above. We have 
revised paragraph (h)(2) of this proposed AD to require the 
installation of standard-size fasteners, and if the existing fastener 
holes exceed the permitted hole diameter, operators must do a repair 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this proposed AD.

Request for Credit for Previous Actions

    All Nippon Airlines (ANA) requested credit for previous actions 
specified in paragraph (h) of the proposed AD (in the first SNPRM). ANA 
stated that credit should be provided if those actions were performed 
before the effective date of the AD using option 1 or 2 of Boeing 
Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, and 
the HFEC open hole inspection for the forward support fitting should be 
done at the same time as the existing inspection within a shortened 
inspection interval.
    ANA commented that based on the current descriptions of the 
proposed AD (in the first SNPRM), all operators must do the initial 
inspection even if they have chosen option 1 or 2 of Boeing Special 
Attention Service Bulletin 737-57-1318, dated May 15, 2013. Since AD 
2014-12-13 has been effective since July 25, 2014, ANA believes many 
operators have already completed the initial inspection and started the 
repetitive inspection in accordance with Boeing Special Attention 
Service Bulletin 737-57-1318, dated May 15, 2013. ANA questioned the 
reasonableness of the requirement for operators who have chosen option 
1 or 2 of Boeing Special Attention Service Bulletin 737-57-1318, dated 
May 15, 2013, to do the initial inspection again within the compliance 
time specified in table 2 through table 9 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, Revision 
1, dated July 22, 2016.
    We disagree with the commenter's request. Paragraph (h) of the 
proposed AD (in the first SNPRM) includes a requirement to do the HFEC 
open hole inspection of the forward fitting in addition to the 
inspections that were previously required by AD 2014-12-13 with updated 
service information, Boeing Alert Service Bulletin 737-57A1318, 
Revision 1, dated July 22, 2016. Since AD 2014-12-13 was issued, there 
have been reports of cracks found in the forward fitting. Therefore, 
Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 
2016, has added an inspection of the forward fitting. Paragraph (l) of 
this proposed AD would allow operators to request approval of an 
alternative method of compliance (AMOC) if they previously performed 
the HFEC open hole inspection of this stack up, including the forward 
fitting, and they have documentation that the inspection of

[[Page 2380]]

the forward fitting was done. We have not changed this proposed AD 
regarding this issue.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
Certain changes described above expand the scope of the first SNPRM. As 
a result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this second SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would require accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between this Proposed AD and the Service Information.'' 
For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-9523.
    The phrase ``related investigative actions'' is used in this SNPRM. 
Related investigative actions are follow-on actions that (1) are 
related to the primary action, and (2) further investigate the nature 
of any condition found. Related investigative actions in an AD could 
include, for example, inspections.
    The phrase ``corrective actions'' is used in this SNPRM. Corrective 
actions correct or address any condition found. Corrective actions in 
an AD could include, for example, repairs.

Differences Between This SNPRM and the Service Information

    Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 
22, 2016; and Boeing Alert Service Bulletin 737-57A1328, dated July 22, 
2016; specify to contact the manufacturer for certain instructions, but 
this proposed AD would require accomplishment of repair methods, 
modification deviations, and alteration deviations in one of the 
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 471 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
HFEC open hole inspections.....  82 work-hours x $85 per              $0  $6,970 per          $3,282,870 per
                                  hour = $6,970 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Eddy current inspection........  14 work-hours x $85 per               0  $1,190 per          $560,490 per
                                  hour = $1,190 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
               Action                          Labor cost             Parts cost          Cost per product
----------------------------------------------------------------------------------------------------------------
Inspection..........................  Up to 41 work-hours x $85                 $0  Up to $1,641,435 per
                                       per hour = $3,485 per                         inspection cycle.
                                       inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this SNPRM.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 2381]]

the FAA proposes to amend 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):

The Boeing Company: Docket No. FAA-2016-9523; Product Identifier 
2016-NM-134-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by March 5, 
2018.

(b) Affected ADs

    This AD affects AD 2014-12-13, Amendment 39-17874 (79 FR 39300, 
July 10, 2014) (``AD 2014-12-13''), and AD 2015-21-08, Amendment 39-
18301 (80 FR 65921, October 28, 2015) (``AD 2015-21-08'').

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in 
any category.
    (2) Installation of Supplemental Type Certificate (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'' 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 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of additional cracking in the 
inspar upper skin at Wing Buttock Line (WBL) 157 and in the skin at 
two holes common to the rear spar in the same area, and rear spar 
web cracks were also noted on both wings. Subsequent inspections 
revealed that the right rear spar upper chord was almost completely 
severed and the left rear spar upper chord was completely severed. 
We are issuing this AD to detect and correct cracking of the forward 
and aft support fittings for the main landing gear (MLG) beam, and 
the rear spar upper chord and rear spar web in the area of rear spar 
station (RSS) 224.14, which could grow and result in a fuel leak and 
possible fire.

(f) Compliance

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

(g) Required Actions for Group 1 Airplanes (MLG Support Fittings and 
Rear Spar)

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the 
applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, 
Revision 1, dated July 22, 2016, do applicable inspections and 
corrective actions using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(h) Required Actions for Groups 2-7 Airplanes (MLG Support Fittings and 
Rear Spar)

    For airplanes identified as Groups 2-7 in Boeing Alert Service 
Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the 
applicable time specified in table 2 through table 9 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, 
Revision 1, dated July 22, 2016, except as required by paragraph 
(j)(3) of this AD, do high frequency eddy current (HFEC) open hole 
inspections for any cracking in the forward support fitting, the aft 
support fitting, the rear spar upper chord, and the rear spar web at 
the 12 fastener holes (locations 1-12); or HFEC open hole 
inspections for any cracking in the forward support fitting, the aft 
support fitting, the rear spar upper chord, and the rear spar web, 
and an HFEC surface inspection for any cracking in the rear spar 
upper chord and rear spar upper web; as applicable; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, 
except as provided by paragraph (h)(1) of this AD, and except as 
required by paragraphs (h)(2) and (j)(1) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Thereafter, repeat the HFEC inspection at the 
applicable time specified in table 2 through table 9 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, 
Revision 1, dated July 22, 2016.
    (1) Options provided in Boeing Alert Service Bulletin 737-
57A1318, Revision 1, dated July 22, 2016, for accomplishing the 
inspection are acceptable for the corresponding requirements in the 
introductory text of paragraph (h) of this AD, provided that the 
inspections are done at the applicable times in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318, 
Revision 1, dated July 22, 2016.
    (2) For Group 7, Configuration 1, airplanes identified in Boeing 
Alert Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016: 
Install standard-size fasteners in accordance with figures 29 and 30 
of Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 
22, 2016. If the existing fastener holes exceed the permitted hole 
diameter, repair before further flight using a method approved in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(i) Eddy Current Inspection (Inspar Upper Skin)

    For airplanes identified in Boeing Alert Service Bulletin 737-
57A1328, dated July 22, 2016: At the applicable time specified in 
table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-57A1328, dated July 22, 2016, except as 
required by paragraph (j)(2) of this AD, do an eddy current 
inspection of the left and right wings for any cracking in the 
inspar upper skin, and at the repair parts if installed, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-57A1328, dated July 22, 2016, except as 
required by paragraph (j)(1) of this AD. Do all related 
investigative and corrective actions before further flight. 
Thereafter, repeat the eddy current inspection at the applicable 
time specified in table 1 and table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1328, dated 
July 22, 2016.

(j) Exceptions to the Service Information

    (1) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 737-57A1318, Revision 1, 
dated July 22, 2016; or Boeing Alert Service Bulletin 737-57A1328, 
dated July 22, 2016; specifies to contact Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (l) of this 
AD.
    (2) Where Boeing Alert Service Bulletin 737-57A1328, dated July 
22, 2016, specifies a compliance time ``after the Original Issue 
date of this service bulletin,'' this AD requires compliance within 
the specified compliance time after the effective date of this AD.
    (3) Where Boeing Alert Service Bulletin 737-57A1318, Revision 1, 
dated July 22, 2016, specifies a compliance time ``after the 
Revision 1 date of this service bulletin, whichever occurs later,'' 
this AD requires compliance within the specified compliance time 
after the effective date of this AD.

(k) Terminating Action

    (1) Accomplishing the initial inspections and applicable related 
investigative and corrective actions required by paragraphs (g), 
(h), and (i) of this AD, as applicable, terminates all requirements 
of AD 2015-21-08.
    (2) Accomplishing the initial inspections and applicable related 
investigative and corrective actions required by paragraphs (g) and 
(h) of this AD, as applicable, terminates all requirements of AD 
2014-12-13.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (m)(1) of this AD. Information 
may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager

[[Page 2382]]

of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO Branch, 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) AMOCs approved previously for AD 2014-12-13 are approved as 
AMOCs for the corresponding provisions of paragraphs (g) and (h) of 
this AD.
    (5) Except as required by paragraph (j)(1) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (l)(5)(i) and 
(l)(5)(ii) of this AD 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. If a step or sub-step is labeled ``RC Exempt,'' then 
the RC requirement is removed from that step or sub-step. 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.

(m) Related Information

    (1) For more information about this AD, contact Payman Soltani, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; 
telephone 562-797-1717; internet https://www.myboeingfleet.com. You 
may view this referenced service information at the FAA, Transport 
Standards Staff, 1601 Lind Avenue SW, Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on December 28, 2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-00109 Filed 1-16-18; 8:45 am]
 BILLING CODE 4910-13-P