Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52835 

Section, Transport Standards 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 International Section, send it 

to the attention of the person identified in 

paragraph (l)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i) of this AD, if any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0023, dated February 10, 2017, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2017–0710. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–57–6118, 

Revision 01, dated January 31, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.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 

November 3, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–24501 Filed 11–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0715; Product 

Identifier 2017–NM–073–AD; Amendment 

39–19096; AD 2017–23–02] 

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 737–200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the 

fuselage crown skin panels are subject 

to widespread fatigue damage (WFD). 

This AD requires repetitive inspections, 

replacement, and applicable oncondition actions for certain fuselage 

crown skin panels. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective December 

20, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 20, 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 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–2017– 

0715. 

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– 

0715; 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 certain The Boeing Company 

Model 737–200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

August 10, 2017 (82 FR 37366). The 

NPRM was prompted by an evaluation 

by the DAH indicating that the fuselage 

crown skin panels are subject to WFD. 

The NPRM proposed to require 

repetitive inspections, replacement, and 

applicable on-condition actions for 

certain fuselage crown skin panels. 

We are issuing this AD to detect and 

correct cracking in the fuselage crown 

skin panels. Multiple adjacent cracks in 

the fuselage crown skin could link up 

and lead to decompression or loss of 

structural integrity of the airplane. 


sradovich on DSK3GMQ082PROD with RULES
52836 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comments 

received. 

Support for the NPRM 

Boeing concurred with the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing Supplemental Type 

Certificate (STC) ST01219SE does not 

affect the ability to accomplish the 

actions specified in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) and 

added 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’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

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 Alert Service 

Bulletin 737–53A1358, dated April 27, 

2017. This service information describes 

procedures for repetitive inspections, 

replacement, and applicable oncondition actions for certain fuselage 

crown skin panels. 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 200 

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 

Inspection ......... Up to 507 work-hours × $85 per hour = $43,095 

per inspection cycle.

$0 Up to $43,095 per inspection cycle.Up to $8,619,000 per inspection cycle. 

Replacement ..... 304 work-hours × $85 per hour = $25,840 per skin 

panel.

95,000 $120,840 per skin panel Up to $24,168,000. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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): 

2017–23–02 The Boeing Company: 

Amendment 39–19096; Docket No. 

FAA–2017–0715; Product Identifier 

2017–NM–073–AD. 

(a) Effective Date 

This AD is effective December 20, 2017. 

(b) Affected ADs 

None. 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52837 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–200, –200C, –300, 

–400, and –500 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/EBD1CEC7B301293E

86257CB30045557A?OpenDocument&

Highlight=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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the fuselage crown skin panels are subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct cracking in the 

fuselage crown skin panels. Multiple 

adjacent cracks in the fuselage crown skin 

could link up and lead to decompression or 

loss of structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as required by paragraph (h) of this 

AD: At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1358, dated 

April 27, 2017, do all applicable actions 

identified as ‘‘RC’’ (required for compliance) 

in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017. 

(h) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD, 

the phrase ‘‘the effective date of this AD’’ 

may be substituted for ‘‘the original issue 

date of this service bulletin,’’ as specified in 

Boeing Alert Service Bulletin 737–53A1358, 

dated April 27, 2017. 

(2) Where Boeing Alert Service Bulletin 

737–53A1358, dated April 27, 2017, specifies 

contacting Boeing, and specifies that action 

as RC: This AD requires using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(3) Part 7 of Boeing Alert Service Bulletin 

737–53A1358, dated April 27, 2017, specifies 

post-modification airworthiness limitation 

inspections in compliance with 14 CFR 

25.571(a)(3) at the modified locations to 

support compliance with 14 CFR 

121.1109(c)(2) or 129.109(b)(2). Although 

Part 7 is identified as RC, this AD does not 

require accomplishment of Part 7. 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 approval of an alternative method of 

compliance. 

(i) Terminating Action for Repetitive 

Inspections 

(1) Replacement of a skin panel, in 

accordance with Part 8 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017, except as required by paragraph 

(h)(2) of this AD, terminates the actions 

specified in Parts 1, 4, and 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017, as required by paragraph (g) of this 

AD, for that replaced skin panel only. To be 

acceptable as terminating action, the 

replacement may not be done prior to the 

applicable time specified in Table 4 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1358, dated 

April 27, 2017. 

(2) Completion of a structural repair 

manual repair to repair cracking, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017, except as required by paragraph 

(h)(2) of this AD, terminates the repetitive 

inspections specified in Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017, as required by paragraph (g) of this 

AD, for that repair location only. 

(3) Completion of a ‘‘Category C repair’’ to 

repair cracking, in accordance with Part 3 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1358, dated 

April 27, 2017, except as required by 

paragraph (h)(2) of this AD, terminates the 

repetitive inspections specified in Part 1 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1358, dated 

April 27, 2017, as required by paragraph (g) 

of this AD, for that repair location only. 

(4) Completion of a ‘‘Change Category C 

Repair to SB Repair,’’ in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1358, 

dated April 27, 2017, except as required by 

paragraph (h)(2) of this AD, terminates the 

inspections specified in Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1358, dated April 

27, 2017, as required by paragraph (g) of this 

AD, for that repair location only. 

(j) 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 (k) 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) Except as required by paragraphs (h)(2) 

and (h)(3) of this AD: For service information 

that contains steps that are labeled as RC, the 

provisions of paragraphs (j)(4)(i) and (j)(4)(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 substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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. 

(k) 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. 

(l) 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 Alert Service Bulletin 737– 

53A1358, dated April 27, 2017. 

(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 


sradovich on DSK3GMQ082PROD with RULES
52838 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 

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 October 

27, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–24164 Filed 11–14–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0772; Product 

Identifier 2017–NM–075–AD; Amendment 

39–19099; AD 2017–23–05] 

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, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by 

reports of crack indications in the right 

wing upper aft skin, originating from 

fastener holes common to the rear spar 

upper chord. This AD requires 

repetitive inspections for cracking of the 

wing upper aft skin, and applicable oncondition actions. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective December 

20, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 20, 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– 

0772. 

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– 

0772; 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: 

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: payman.soltani@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, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

August 15, 2017 (82 FR 38632). The 

NPRM was prompted by a report of 

crack indications in the right wing 

upper aft skin, originating from fastener 

holes common to the rear spar upper 

chord at wing buttock line (WBL) 172.30 

and WBL 197.38. The cracks were found 

on airplanes with 58,148 to 64,204 total 

flight hours and 45,512 to 51,409 total 

flight cycles. This cracking, if not 

corrected, could result in the inability of 

a principal structural element to sustain 

flight load, which could adversely affect 

the structural integrity of the airplane. 

The NPRM proposed to require 

repetitive inspections for cracking of the 

wing upper aft skin at and forward of 

the rear spar upper chord, and 

applicable on-condition actions. 

We are issuing this AD to detect and 

correct cracking of the wing upper aft 

skin, which can lead to the inability of 

a principal structural element to sustain 

flight load, and adversely affect the 

structural integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comments 

received. 

Support for the NPRM 

The Boeing Company supported the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the Supplemental Type 

Certificate (STC) ST01219SE 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 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’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

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 change 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 Alert Service 

Bulletin 737–57A1335, dated May 24, 

2017. The service information describes 

procedures for repetitive inspections for 

cracking of the wing upper aft skin at 

and forward of the rear spar upper 

chord, and applicable on-condition 

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. 

Costs of Compliance 

We estimate that this AD affects 160 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 


sradovich on DSK3GMQ082PROD with RULES