Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39509 

(i) Airbus Helicopters Alert Service 

Bulletin (ASB) No. AS332–05.00.99, Revision 

0, dated December 22, 2014. 

(ii) Airbus Helicopters ASB No. EC225– 

05A040, Revision 0, dated December 22, 

2014. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.helicopters.airbus.com/Website/en/ref/ 

Technical-Support_73.html. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on August 7, 

2017. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17084 Filed 8–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0335; Product 

Identifier 2017–NM–025–AD; Amendment 

39–18994; AD 2017–17–04] 

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 a 

report of cracks in the upper aft skin of 

the right wing at certain fastener holes 

along the rear spar upper chord. This 

AD requires repetitive inspections for 

cracking of the upper aft skin of the 

wings, and repair if necessary. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective September 

25, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 25, 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; 

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– 

0335. 

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– 

0335; 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 Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on May 17, 2017 (82 

FR 22619) (‘‘the NPRM’’). The NPRM 

was prompted by a report of cracks in 

the upper aft skin of the right wing at 

certain fastener holes along the rear spar 

upper chord. The NPRM proposed to 

require repetitive inspections for 

cracking of the upper aft skin of the 

wings, and repair if necessary. 

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 

Boeing and Robert Simpson 

concurred with the content of 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 compliance with the actions 

specified in the NPRM. 

We agree 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 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 737–57A1332, dated January 3, 

2017. This service information describes 

procedures for repetitive detailed 

inspections of the upper aft skin of the 

wings for cracking. 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 471 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 


sradovich on DSK3GMQ082PROD with RULES
39510 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 

ESTIMATED COSTS

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

operators 

Repetitive inspections .... 5 work-hours × $85 per hour = $425 

per inspection cycle.

$0 $425 per inspection cycle .. $200,175 per inspection 

cycle. 

We have received no definitive data 

that enables 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): 

2017–17–04 The Boeing Company: 

Amendment 39–18994; Docket No. 

FAA–2017–0335; Product Identifier 

2017–NM–025–AD. 

(a) Effective Date 

This AD is effective September 25, 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/0/312bc296830a925c86257

c85006d1b1f/$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 a report of 

cracks in the upper aft skin of the right wing 

at certain fastener holes along the rear spar 

upper chord. We are issuing this AD to detect 

and correct cracks in the upper aft skin of the 

wings, which could result in the inability of 

a principle structural element to sustain limit 

load, and consequent reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Group 2 Airplanes: Detailed Inspections 

and Repair 

For Group 2 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1332, dated 

January 3, 2017: At the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–57A1332, 

dated January 3, 2017, except as required by 

paragraph (i) of this AD, do a detailed 

inspection for cracking of the upper aft skin 

of the wings from wing buttock line (WBL) 

80 to WBL 155, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–57A1332, dated 

January 3, 2017. If any cracking is found, 

repair before further flight in accordance 

with the procedures specified in paragraph (j) 

of this AD. Although Boeing Alert Service 

Bulletin 737–57A1332, dated January 3, 

2017, specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair as specified in this paragraph. 

Repeat the inspection thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1332, dated January 3, 

2017. 

(h) Group 1 Airplanes: Inspection and 

Corrective Action 

For Group 1 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1332, dated 

January 3, 2017: Within 120 days after the 

effective date of this AD, inspect for cracking 

of the upper aft skin of the wings, and do all 

applicable corrective actions, using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(i) Exception to the Service Information 

Where Boeing Alert Service Bulletin 737– 

57A1332, dated January 3, 2017, specifies a 

compliance time ‘‘after the original issue date 

of this Service Bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 


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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39511 

(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 paragraph (g) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (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 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. 

(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– 

57A1332, dated January 3, 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; 

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 August 

8, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17204 Filed 8–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0131; Product 

Identifier 2016–NM–186–AD; Amendment 

39–18996; AD 2017–17–06] 

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 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by a report of fatigue 

cracking found in a certain fuselage 

frame common to the water tank 

support intercostal clip located between 

certain stringers. This AD requires 

inspections for any cracking of a certain 

fuselage frame, and repair if necessary. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective September 

25, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 25, 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– 

0131. 

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– 

0131; 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5324; fax: 562–627– 

5210; email: galib.abumeri@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 737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on March 23, 2017 (82 

FR 14835). The NPRM was prompted by 

a report of fatigue cracking found in a 

certain fuselage frame common to the 

water tank support intercostal clip 

located between certain stringers. The 

NPRM proposed to require inspections 

for any cracking of a certain fuselage 

frame, and repair if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking that could grow in size 

and result in a severed frame. Multiple 

adjacent severed frames would result in 

reduced structural integrity of the 

airplane. 

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 


sradovich on DSK3GMQ082PROD with RULES