AD 2017-20-12

final rule

Airworthiness Directives; The Boeing Company Airplanes

AD Number: 2017-20-12
Status: final_rule
Effective Date: November 16, 2017
Product Category: aircraft
Docket: Docket No. FAA-2017-0243
FR Citation: 82 FR 47367

Applicability

Type	Manufacturer	Model	Details
aircraft	The Boeing Company	737-100 Series	Airworthiness Directives; The Boeing Company Airplanes
aircraft	The Boeing Company	737-200 Series	Airworthiness Directives; The Boeing Company Airplanes
aircraft	The Boeing Company	737-200C Series	Airworthiness Directives; The Boeing Company Airplanes

Unsafe Condition

Fatigue cracking in transport category airplanes approaching or exceeding their design service objective, as identified through a structural reevaluation conducted by the manufacturer.

AI-generated summary from the source AD text. Verify against the official source before acting.

Required Actions

Revise the maintenance or inspection program to add supplemental inspections. Inspect each structural significant item (SSI) for cracks and repair any cracked structure. Report SSI discrepancies as applicable.

AI-generated summary from the source AD text. Verify against the official source before acting.

Compliance Time

Before the accumulation of 66,000 total flight cycles, or within 12 months after the effective date of this AD, or at the next scheduled inspection as required by AD 98-11-04 R1 or AD 2008-08-23, whichever occurs later.

AI-generated summary from the source AD text. Verify against the official source before acting.

Affected Aircraft

The Boeing Company Model 737-100, -200, and -200C series airplanes.

AI-generated summary from the source AD text. Verify against the official source before acting.

Federal Register Abstract

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, and -200C series airplanes. This AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation that was conducted by the manufacturer. This AD requires revising the maintenance or inspection program, as applicable, to add supplemental inspections. This AD also requires inspections to detect cracks in each structural significant item (SSI), and repair of any cracked structure. We are issuing this AD to address the unsafe condition on these products.

Applicability Source Text

Show captured applicability text from the source AD

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, 
and -200C series airplanes, certificated in any category.

Document Text

Show stored source text (verify against official source)

[Federal Register Volume 82, Number 196 (Thursday, October 12, 2017)]
[Rules and Regulations]
[Pages 47367-47370]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-21445]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0243; Product Identifier 2016-NM-045-AD; Amendment
39-19069; AD 2017-20-12]
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 all The
Boeing Company Model 737-100, -200, and -200C series airplanes. This AD
was prompted by a report of incidents involving fatigue cracking in
transport category airplanes that are approaching or have exceeded
their design service objective and a structural reevaluation that was
conducted by the manufacturer. This AD requires revising the
maintenance or inspection program, as applicable, to add supplemental
inspections. This AD also requires inspections to detect cracks in each
structural significant item (SSI), and repair of any cracked structure.
We are issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective November 16, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 16,
2017.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may view this 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0243.

Examining the AD Docket

You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0243; 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 final rule, the regulatory evaluation, any comments
received, and other information. The address for the Docket Office
(phone: 800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-
5210; email: <a href="/cdn-cgi/l/email-protection#046e616a6a6d6261762a7077656f6b7169656f6d77446265652a636b72">[email&#160;protected]</a>.

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 all The Boeing Company
Model 737-100, -200, and -200C series airplanes. The NPRM published in
the Federal Register on March 27, 2017 (82 FR 15166) (``the NPRM'').
The NPRM was prompted by a report of incidents involving fatigue
cracking in transport category airplanes that are approaching or have
exceeded their design service objective and a structural reevaluation
that was conducted by the manufacturer. The NPRM proposed to require
revising the maintenance or inspection program, as applicable, to add
supplemental inspections and SSI discrepancy reporting. The NPRM also
proposed inspections to detect cracks in each SSI, and repair of any
cracked structure. We are issuing this AD to ensure the continued
structural integrity of all The Boeing Company Model 737-100, -200, and
-200C series airplanes.

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.

Support for the NPRM

An anonymous commenter expressed support for the NPRM.

Request To Revise Program Designation

Boeing requested that we revise ``maintenance or inspection
program'' to ``maintenance inspection program'' in the proposed AD.
Boeing stated that operators have a single program that relates to the
Supplemental Structural Inspection Document (SSID).
We do not agree with the commenter's request. Airplanes operating
under 14 CFR part 91 have ``inspection programs'' while airplanes
operating under 14 CFR part 121 have ``maintenance programs.'' The
decision to use the wording ``maintenance or inspection program'' is
intentional. We have not changed this AD in this regard.

Request To Revise Compliance Times

Boeing requested that we revise the compliance time for the initial
inspections in paragraphs (h)(1) and (h)(2) of the proposed AD from
``before the accumulation of 66,000 total flight cycles, or within 12
months after the effective date of this AD, whichever occurs later'' to
before the accumulation of 66,000 total flight cycles, or at the next
scheduled inspection as required

[[Page 47368]]

by AD 98-11-04 R1, Amendment 39-10984 (64 FR 987, January 7, 1999)
(``AD 98-11-04 R1''), whichever occurs later.
Boeing also requested that we revise the compliance time for the
initial inspections in paragraph (h)(3) of the proposed AD from
``before the accumulation of 46,000 total flight cycles, or within 12
months after the effective date of this AD, whichever occurs later'' to
before the accumulation of 46,000 total flight cycles, or at the next
scheduled inspection as required by AD 2008-08-23, Amendment 39-15477
(73 FR 21237, April 21, 2008) (``AD 2008-08-23''), whichever occurs
later.
We partially agree with the commenter's requests. We agree that a
compliance time option of at the next required inspection should be
added because operators who have airplanes with more than 66,000 total
flight cycles (or more than 46,000 total flight cycles for SSIs
affected by the 737-200C cargo configuration) and who have initiated
SSI inspections would be required to accomplish an inspection within 12
months in accordance with this AD, which may be earlier than the next
repeat inspection required by the existing ADs. We disagree with the
commenter's request to remove the 12 month grace period because
operators who are very close to accomplishing an initial or repeat
inspection required by AD 98-11-04 R1 or AD 2008-08-23 need time to
incorporate the revised service information in their maintenance or
inspection program. Because this AD is not superseding the existing
SSID ADs, any initial or repeat inspection required by AD 98-11-04 R1
or AD 2008-08-23 will still be required until the corresponding action
in this AD is accomplished. We have revised paragraphs (h)(1), (h)(2),
and (h)(3) of this AD to include a compliance time option of at the
next required inspection.

Request To Address Repaired or Altered SSIs

Boeing requested that we revise the proposed AD to include a
paragraph that addresses any repair installed on an SSI such that the
repair affects the operator's ability to accomplish inspections
required by the proposed AD. Boeing suggested that we include wording
similar to the wording in AD 2008-08-23, except that we make the
actions applicable to a repair installed on an SSI at any time and not
exclusive to repairs installed before the effective date of the AD.
We agree with the commenter's request to revise this AD to include
wording to address repairs or alterations on any SSI such that the
repair or alteration affects the operator's ability to accomplish the
inspections required by this AD. We have included paragraphs (i)(1) and
(i)(2) in this AD. Paragraph (i)(1) of this AD requires repairs to SSI
structure if cracks are found while accomplishing inspections in
accordance with this AD and is similar to paragraph (i) of the proposed
AD, except for the change described below under ``Change to Paragraph
(i) of the Proposed AD.'' Paragraph (i)(2) is added to this AD to
address repairs or alterations that affect the ability to inspect an
SSI as required by this AD. If an operator finds a repaired or altered
SSI such that the repair or alteration affects the operator's ability
to accomplish the inspections required by this AD and the repair or
alteration does not have alternative method of compliance (AMOC)
approval in accordance with paragraph (l) of this AD, then paragraph
(i)(2) of this AD will provide the operator an 18-month grace period
after the compliance time to request an AMOC.

Change to Paragraph (i) of the Proposed AD

Paragraph (i) of the proposed AD specifies to repair ``using a
method approved in accordance with the procedures specified in
paragraph (l) of this AD.'' We have changed the method of compliance
language in paragraph (i)(1) of this AD to specify to repair ``using an
FAA-approved method.'' Specifying an FAA-approved method will allow for
FAA Designated Engineering Representatives (DERs) to approve repairs in
addition to the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) and the Los Angeles ACO Branch as specified by the
procedures in paragraph (l) of this AD. If an FAA DER has the
appropriate structures delegation for major repairs on 14 CFR part 25
airplanes, then the DER has the authority to approve these types of
repairs.

Conclusion

We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described previously and minor
editorial changes. We have determined that these minor changes:
<bullet> Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
<bullet> 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 final
rule.

Related Service Information Under 1 CFR Part 51

We reviewed Boeing Document D6-37089, ``Supplemental Structural
Inspection Document for Model 737-100/200/200C Airplanes,'' Revision F,
dated November 2015. The service information identifies SSIs having
fatigue crack growth characteristics warranting special attention,
describes procedures for inspections to detect cracks of all structure
identified as SSIs, and provides corrective actions for cracked SSI
structure. 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 will affect 84 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revision of maintenance or inspection 1 work-hour x $85 per $0 $85 $7,140
program. hour = $85.
----------------------------------------------------------------------------------------------------------------

We have not specified cost estimates for the inspections and repair
specified in this AD. Compliance with this AD constitutes a method of
compliance with the FAA aging airplane safety final rule (AASFR) for
certain baseline

[[Page 47369]]

structure of Model 737-100, -200, and -200C series airplanes. The AASFR
requires certain operators to incorporate damage tolerance inspections
into their maintenance programs. These requirements are described in 14
CFR 121.1109(c)(1) and 14 CFR 129.109(b)(1). Accomplishment of the
actions specified in this AD will meet the requirements of these
regulations for certain baseline structure. The costs for accomplishing
the inspection portion of this AD were accounted for in the regulatory
evaluation of the AASFR for airplanes affected by that rule. For
airplanes not affected by the AASFR, we have received no definitive
data that would enable us to provide cost estimates for the inspection
portion of this AD.
We estimate the following costs to do any necessary reporting that
would be required based on the results of the inspections specified in
the revision of the maintenance or inspection program. We have no way
of determining the number of aircraft that might need this action:

On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Reporting..................................... 1 work-hour x $85 per hour = $85 $0 $85
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.

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 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

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):

2017-20-12 The Boeing Company: Amendment 39-19069; Docket No. FAA-
2017-0243; Product Identifier 2016-NM-045-AD.

(a) Effective Date

This AD is effective November 16, 2017.

(b) Affected ADs

This AD affects AD 98-11-04 R1, Amendment 39-10984 (64 FR 987,
January 7, 1999) (``AD 98-11-04 R1''); and AD 2008-08-23, Amendment
39-15477 (73 FR 21237, April 21, 2008) (``AD 2008-08-23'').

This AD applies to all The Boeing Company Model 737-100, -200,
and -200C series airplanes, certificated in any category.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage;
54, Nacelles/Pylons; 55, Stabilizers; 57, Wings.

(e) Unsafe Condition

This AD was prompted by a report of incidents involving fatigue
cracking in transport category airplanes that are approaching or
have exceeded their design service objective and a structural
reevaluation that was conducted by the manufacturer that identified
additional structural elements that qualify as structural
significant items (SSIs). We are issuing this AD to ensure the
continued structural integrity of all The Boeing Company Model 737-
100, -200, and -200C series airplanes.

(f) Compliance

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

[[Page 47370]]

(g) Revision of the Maintenance or Inspection Program for All Airplanes

Prior to reaching the compliance time specified in paragraph
(h)(1), (h)(2), or (h)(3) of this AD, as applicable: Incorporate a
revision into the maintenance or inspection program, as applicable,
that provides no less than the required damage tolerance rating
(DTR) for each SSI listed in Boeing Document D6-37089,
``Supplemental Structural Inspection Document for Model 737-100/200/
200C Airplanes,'' Revision F, dated November 2015 (``Document D6-
37089, Revision F''). The required DTR value for each SSI is listed
in Document D6-37089, Revision F. The revision to the maintenance or
inspection program must include, and must be implemented in
accordance with, the procedures in Section 5.0, ``Damage Tolerance
Rating (DTR) System Application,'' and Section 6.0, ``SSI
Discrepancy Reporting'' of Document D6-37089, Revision F.
Accomplishing the revision required by this paragraph terminates the
actions required by paragraphs (a) and (b) of AD 98-11-04 R1, and
paragraph (g) of AD 2008-08-23.

(h) Initial and Repetitive Inspections

Perform an inspection in accordance with Document D6-37089,
Revision F, to detect cracks of all structure identified in Document
D6-37089, Revision F, at the time specified in paragraph (h)(1),
(h)(2), or (h)(3) of this AD, as applicable. Repeat the inspection
thereafter at the intervals specified in Document D6-37089, Revision
F. Accomplishing an initial inspection required by this paragraph
terminates the corresponding inspection required by paragraph (c) of
AD 98-11-04 R1 and paragraph (h) of AD 2008-08-23.
(1) For SSIs on Model 737-100 and -200 series airplanes: Before
the accumulation of 66,000 total flight cycles, at the next
inspection required by Note 5 of AD 98-11-04 R1 (Note 5 of AD 98-11-
04 R1 follows paragraph (c)(2) of AD 98-11-04 R1), or within 12
months after the effective date of this AD, whichever occurs later.
(2) For SSIs on Model 737-200C series airplanes not affected by
cargo configuration: Before the accumulation of 66,000 total flight
cycles, at the next inspection required by paragraph (h) of AD 2008-
08-23, or within 12 months after the effective date of this AD,
whichever occurs later.
(3) For SSIs on Model 737-200C series airplanes affected by
cargo configuration: Before the accumulation of 46,000 total flight
cycles, at the next inspection required by paragraph (h) of AD 2008-
08-23, or within 12 months after the effective date of this AD,
whichever occurs later.

(i) Repairs and Alterations

(1) If any cracked SSI structure is found during any inspection
required by paragraph (h) of this AD, repair before further flight
using an FAA-approved method or using a method approved in
accordance with the procedures specified in paragraph (l) of this
AD. Within 18 months after repair, incorporate a revision into the
maintenance or inspection program, as applicable, to include a
damage-tolerance-based alternative inspection program for the
repaired structure. Thereafter, inspect the affected structure in
accordance with the alternative program. The inspection method and
compliance times (i.e., threshold and repetitive intervals) of the
alternative program must be approved in accordance with the
procedures specified in paragraph (l) of this AD.
(2) If any repair or alteration to an SSI is found during any
inspection required by paragraph (h) of this AD such that the repair
or alteration affects your ability to accomplish the inspections
required by paragraph (h) of this AD, within 18 months after the
inspection compliance time, incorporate a revision into the
maintenance or inspection program, as applicable, to include a
damage tolerance based alternative inspection program for each
affected SSI. Thereafter, inspect the affected structure in
accordance with the alternative inspection program. The inspection
method and compliance times (i.e., threshold and repetitive
intervals) of the alternative inspection program must be approved in
accordance with the procedures specified in paragraph (l) of this
AD. Accomplishing an initial inspection required by this paragraph
terminates the corresponding inspection required by paragraph (i) of
AD 2008-08-23.

(j) Terminating Action for Other ADs

Accomplishing the revision required by paragraph (g) of this AD
and all initial inspections required by paragraph (h) of this AD
terminates all requirements of AD 98-11-04 R1 and AD 2008-08-23.

(k) Paperwork Reduction Act Burden Statement

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.

(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) of this AD. Information may
be emailed to: <a href="/cdn-cgi/l/email-protection#82bbafc3cccfafcec3c3c1cdafc3cfcdc1afd0e7f3f7e7f1f6f1c2e4e3e3ace5edf4">[email&#160;protected]</a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO 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 for AD 98-11-04 R1 and AD 2008-08-23 are
approved as AMOCs for the corresponding provisions of paragraphs (g)
and (h) of this AD for the SSIs identified in the AMOC.

(m) Related Information

For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
<a href="/cdn-cgi/l/email-protection#b4ded1dadaddd2d1c69ac0c7d5dfdbc1d9d5dfddc7f4d2d5d59ad3dbc2">[email&#160;protected]</a>.

(n) 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 Document D6-37089, ``Supplemental Structural
Inspection Document for Model 737-100/200/200C Airplanes,'' Revision
F, dated November 2015.
(ii) Reserved.
(3) 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-
5600; telephone 562-797-1717; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) You may view this 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.
(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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

Issued in Renton, Washington, on September 27, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-21445 Filed 10-11-17; 8:45 am]
BILLING CODE 4910-13-P

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