Federal Register / Vol. 82, No. 196 / Thursday, October 12, 2017 / Rules and Regulations 47367 

empennage SSIs E–19, E–21, E–29, E–30, and 

E–31. 

(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: 

jennifer.tsakoumakis@faa.gov. 

(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 D6–82669, 

‘‘Supplemental Structural Inspection 

Document, Models 737–300/400/500 

Airplanes,’’ Revision October 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 https://

www.myboeingfleet.com. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 27, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–21444 Filed 10–11–17; 8:45 am] 

BILLING CODE 4910–13–P 

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 

https://www.myboeingfleet.com. 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 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

0243. 

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–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: jennifer.tsakoumakis@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to 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 


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47368 Federal Register / Vol. 82, No. 196 / Thursday, October 12, 2017 / Rules and Regulations 

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: 

• 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 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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revision of maintenance or inspection program.1 work-hour × $85 per hour = $85 ................. $0 $85 $7,140 

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 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 196 / Thursday, October 12, 2017 / Rules and Regulations 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

Action Labor cost Parts cost Cost per 

product 

Reporting ...................................................................... 1 work-hour × $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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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’’). 

(c) Applicability 

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. 


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47370 Federal Register / Vol. 82, No. 196 / Thursday, October 12, 2017 / Rules and Regulations 

(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: 9-ANMLAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by 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: jennifer.tsakoumakis@faa.gov. 

(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 https://

www.myboeingfleet.com. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

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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