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: 


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Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52839 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection ......... 4 work-hours × $85 per hour = $340 per inspection 

cycle.

$0 $340 per inspection cycle $54,400 per inspection 

cycle. 

We have received no definitive data 

that would 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): 

2017–23–05 The Boeing Company: 

Amendment 39–19099; Docket No. 

FAA–2017–0772; Product Identifier 

2017–NM–075–AD. 

(a) Effective Date 

This AD is effective December 20, 2017. 

(b) Affected ADs 

None. 

(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 (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ebd1cec7b301293e

86257cb30045557a/$FILE/ST01219SE.pdf) 

does not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

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. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For airplanes identified as Group 2 in 

Boeing Alert Service Bulletin 737–57A1335, 

dated May 24, 2017: Except as required by 

paragraph (h) of this AD, at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1335, dated May 24, 2017, 

do all applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1335, dated May 24, 2017. 

(2) For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 737–57A1335, 

dated May 24, 2017: Within 120 days after 

the effective date of this AD, inspect the 

airplane and do all applicable corrective 

actions using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(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 737–57A1335, 

dated May 24, 2017. 

(2) Where Boeing Alert Service Bulletin 

737–57A1335, dated May 24, 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 (i) of this AD. 

(i) 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 (j) of this 


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52840 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 

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 paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (i)(4)(i) and (i)(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. 

(j) Related Information 

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: 

payman.soltani@faa.gov. 

(k) 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– 

57A1335, dated May 24, 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 

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. 2017–24624 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–2016–9568; Product 

Identifier 2016–NM–150–AD; Amendment 

39–19077; AD 2017–21–06] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

328 Support Services GmbH Model 

328–100 and Model 328–300 airplanes. 

This AD was prompted by reports of 

broken bonding wires of certain fuel 

line clamps. This AD requires repetitive 

inspections of certain fuel line clamps 

for discrepancies; repetitive inspections 

of certain parts for chafing marks; and 

replacement of any discrepant parts. 

This AD also includes an optional 

modification, which is a terminating 

action for the inspections. 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 certain publications listed in this AD 

as of December 20, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 328 

Support Services GmbH, Global Support 

Center, P.O. Box 1252, D–82231 

Wessling, Federal Republic of Germany; 

telephone +49 8153 88111 6666; fax +49 

8153 88111 6565; email gsc.op@

328support.de; Internet http://

www.328support.de. 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– 

9568. 

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– 

9568; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 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: 

Todd Thompson, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1175; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to certain 328 Support 

Services GmbH Model 328–100 and 

Model 328–300 airplanes. The SNPRM 

published in the Federal Register on 

June 30, 2017 (82 FR 29786) (‘‘the 

SNPRM’’). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on January 11, 2017 (82 FR 

3217) (‘‘the NPRM’’). The NPRM 

proposed to require a one-time 

inspection of certain fuel line clamps for 

discrepancies, and replacement of any 

discrepant clamps. The NPRM was 

prompted by reports of broken bonding 

wires of certain fuel line clamps. The 

SNPRM proposed to expand the 

applicability and require repetitive 

inspections of certain fuel line clamps 

for discrepancies; repetitive inspections 

of certain jet fuel pumps, connection 

parts, and fuel lines for chafing marks; 

a measurement of the depth of the 

chafing marks on affected parts; and 

replacement of any discrepant parts. We 

are issuing this AD to prevent the loss 

of bonding function, which, in 


sradovich on DSK3GMQ082PROD with RULES