39506 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 

that a violation of Loan Program 

Requirements constitutes default under 

their respective agreements with SBA. 

(1) Additional agreements by CDCs. 

By obtaining approval for 504 loans 

after October 20, 2017, a CDC consents 

to the remedies in § 120.1500(e)(3) and 

waives in advance any right it may have 

to contest the validity of the 

appointment of a receiver. The CDC 

agrees that its consent to SBA’s 

application to a Federal court of 

competent jurisdiction for appointment 

of a receiver of SBA’s choosing, an 

injunction or other equitable relief, and 

the CDC’s consent in advance to the 

court’s granting of SBA’s application, 

may be enforced upon any basis in law 

or equity recognized by the court. 

(2) Additional agreements by SBA 

Supervised Lenders (except Other 

Regulated SBLCs). By making SBA 7(a) 

guaranteed loans after October 20, 2017, 

an SBA Supervised Lender (except an 

Other Regulated SBLC) consents to the 

remedies in § 120.1500(c)(3) and waives 

in advance any right it may have to 

contest the validity of the appointment 

of a receiver. The SBA Supervised 

Lender agrees that its consent to SBA’s 

application to a Federal court of 

competent jurisdiction for appointment 

of a receiver of SBA’s choosing, an 

injunction or other equitable relief, and 

the SBA Supervised Lender’s consent in 

advance to the court’s granting of SBA’s 

application, may be enforced upon any 

basis in law or equity recognized by the 

court. 

* * * * * 

■ 47. Amend § 120.1500 by revising 

paragraph (c)(3) and adding paragraph 

(e)(3) to read as follows: 

§ 120.1500 Types of enforcement 

actions—SBA Lenders. 

* * * * * 

(c) * * * 

(3) Initiate request for appointment of 

receiver and/or other relief. The SBA 

may make application to any Federal 

court of competent jurisdiction for the 

court to take exclusive jurisdiction, 

without notice, of an SBA Supervised 

Lender, and SBA shall be entitled to the 

appointment of a receiver of SBA’s 

choosing to hold, administer, operate, 

and/or liquidate the SBA Supervised 

Lender; and to such injunctive or other 

equitable relief as may be appropriate. 

Without limiting the foregoing and with 

SBA’s written consent, the receiver may 

take possession of the portfolio of 7(a) 

loans and sell such loans to a third 

party, and/or take possession of 

servicing activities of 7(a) loans and sell 

such servicing rights to a third party. 

* * * * * 

(e) * * * 

(3) Apply to any Federal court of 

competent jurisdiction for the court to 

take exclusive jurisdiction, without 

notice, of the CDC, and SBA shall be 

entitled to the appointment of a receiver 

of SBA’s choosing to hold, administer, 

operate and/or liquidate the CDC; and to 

such injunctive or other equitable relief 

as may be appropriate. Without limiting 

the foregoing and with SBA’s consent, 

the receiver may take possession of the 

portfolio of 504 loans and/or pending 

504 loan applications, including for the 

purpose of carrying out an enforcement 

order under paragraph (e)(1) of this 

section. 

■ 48. Amend § 120.1600 by: 

■ a. Revising paragraph (a) introductory 

text; 

■ b. Adding paragraph (a)(6); and 

■ c. Revising paragraph (b)(4). 

The revisions and addition read as 

follows: 

§ 120.1600 General procedures for 

enforcement actions against SBA Lenders, 

SBA Supervised Lenders, Other Regulated 

SBLCs, Management Officials, Other 

Persons, Intermediaries, and NTAPs. 

(a) In general. Except as otherwise set 

forth for the enforcement actions listed 

in paragraphs (a)(6), (b) and (c) of this 

section, SBA will follow the procedures 

listed below. 

* * * * * 

(6) Receiverships of Certified 

Development Companies and/or other 

relief. If SBA undertakes the 

appointment of a receiver for a Certified 

Development Company and/or 

injunctive or other equitable relief, 

paragraphs (a)(1) through (5) of this 

section will not apply and SBA will 

follow the applicable procedures under 

Federal law to obtain such remedies and 

to enforce the Certified Development 

Company’s consent and waiver in 

advance to those remedies. 

(b) * * * 

(4) Receiverships, transfer of assets 

and servicing activities. If SBA 

undertakes the appointment of a 

receiver for, or the transfer of assets or 

servicing rights of an SBA Supervised 

Lender and/or injunctive or other 

equitable relief, SBA will follow the 

applicable procedures under Federal 

law to obtain such remedies and to 

enforce the SBA Supervised Lender’s 

consent and waiver in advance to those 

remedies. 

* * * * * 

■ 49. Amend § 120.1703 by revising 

paragraph (a)(4) to read as follows: 

§ 120.1703 Qualifications to be a Pool 

Originator. 

(a) * * * 

(4) Is in good standing with SBA (as 

the SBA determines), and is Satisfactory 

with the Office of the Comptroller of the 

Currency (OCC) if it is a national bank, 

the Federal Deposit Insurance 

Corporation if it is a bank not regulated 

by the OCC, the Financial Institutions 

Regulatory Authority if it is a member, 

the National Credit Union 

Administration if it is a credit union, as 

determined by SBA; and 

* * * * * 

■ 50. Amend § 120.1707 by revising the 

fifth sentence and adding a sixth 

sentence to read as follows: 

§ 120.1707 Seller’s retained Loan Interest. 

* * * In addition, in order to 

complete such sale, Seller must have the 

purchaser of its rights to the Pool Loan 

execute an allonge to the Seller’s First 

Lien Position 504 Loan Pool Guarantee 

Agreement in a form acceptable to SBA, 

acknowledging and accepting all terms 

of the Seller’s First Lien Position 504 

Loan Pool Guarantee Agreement, and 

deliver the executed original allonge 

and a copy of the corresponding First 

Lien Position 504 Loan Pool Guarantee 

Agreement to the CSA. All Pool Loan 

payments related to a Seller Receipt and 

Servicing Retention Amount proposed 

for sale will be withheld by the CSA 

pending SBA acknowledgement of 

receipt of all executed documents 

required to complete the transfer. 

Subpart K—[Removed] 

■ 51. Remove Subpart K, consisting of 

§§ 120.1800 through 120.1900. 

Dated: August 11, 2017. 

Linda E. McMahon, 

Administrator. 

[FR Doc. 2017–17447 Filed 8–18–17; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0419; Product 

Identifier 2015–SW–077–AD; Amendment 

39–18991; AD 2017–17–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters (Airbus) Model AS332L2 


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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39507 

and EC225LP helicopters. This AD 

requires inspections of the main rotor 

(M/R) blade attachment pins 

(attachment pins). This AD was 

prompted by a report of three cracked 

attachment pins. The actions of this AD 

are intended to detect and prevent an 

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 certain documents listed in this AD 

as of September 25, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0419. 

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– 

0419; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

David Hatfield, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5116; email 

david.hatfield@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 11, 2017, at 82 FR 21956, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Airbus Model AS332L2 helicopters with 

an attachment pin part number (P/N) 

332A31–2123–00 or P/N 332A31–2115– 

20 installed and Model EC225LP 

helicopters with an attachment pin P/N 

332A31–3204–20 installed. The NPRM 

proposed to require an initial and 

recurring inspection of each attachment 

pin for corrosion, a crack, and any 

pitting. If there is a crack or any pitting, 

the NPRM proposed to require replacing 

the attachment pin. If there is corrosion, 

the NPRM proposed to require removing 

the corrosion up to a maximum of four 

times. The NPRM also proposed to 

require performing these inspections 

prior to installing an attachment pin. 

The proposed requirements were 

intended to detect corrosion or a crack 

in an attachment pin and prevent loss 

of an M/R blade and subsequent loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2015–0016, dated January 30, 2015, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Airbus Model AS 332 L2 

and EC 225 LP helicopters with certain 

part-numbered attachment pins 

installed. EASA advises of three cracked 

attachment pins on a Model AS 332 L2 

helicopter, which resulted from a 

combination of factors including 

corrosion that had initiated in the inner 

diameter area of the attachment pin 

chamfer. EASA states that if this 

condition is not detected and corrected, 

it may lead to failure of the attachment 

pin with loss of control of the 

helicopter. Due to design similarity, 

Model EC225LP helicopters are also 

affected by this issue. 

For these reasons, EASA AD No. 

2015–0016 requires repetitive 

inspections of the attachment pins for 

corrosion. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are issuing this AD because we 

evaluated all information provided by 

EASA and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of these 

same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD does not require an 

inspection of the protective coating of 

each attachment pin for Model EC225LP 

helicopters. This AD requires inspecting 

the protective coating of each 

attachment pin for both model 

helicopters. The EASA AD requires 

ensuring there are no corrosion pits 

without a corresponding corrective 

action. This AD requires replacing an 

attachment pin that has any pitting. The 

EASA AD requires a non-destructive 

inspection if in doubt about whether 

there is a crack, while this AD does not. 

Lastly, the EASA AD requires contacting 

and returning to Airbus Helicopters any 

attachment pin with a crack, and this 

AD does not. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters Alert 

Service Bulletin (ASB) No. AS332– 

05.00.99, Revision 0, dated December 

22, 2014 (AS332–05.00.99), for Model 

AS332L2 helicopters and Airbus 

Helicopters ASB No. EC225–05A040, 

Revision 0, dated December 22, 2014 

(EC225–05A040), for Model EC225LP 

helicopters. Airbus Helicopters advises 

of cracks discovered in attachment pins 

that resulted from a combination of 

factors, but mainly corrosion which 

initiated in the inner diameter at the 

chamfer. This service information 

specifies repetitively inspecting for 

corrosion and cracks and ensuring there 

are no corrosion pits in the attachment 

pins. If there is corrosion, this service 

information allows an attachment pin to 

be reworked up to four times before 

removing it from service. If there is a 

crack, this service information specifies 

contacting and sending the attachment 

pin to Airbus Helicopters. 

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 5 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work-hour. 

For Model AS332L2 helicopters, there 

are no costs of compliance with this AD 

because there are no helicopters with 

this type certificate on the U.S. Registry. 

For Model EC225LP helicopters, 

which have ten attachment pins 


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installed, inspecting the attachment 

pins takes about 1 work-hour for a total 

cost of $85 per helicopter and $425 for 

the U.S. fleet. Removing corrosion takes 

about 1 work-hour for a total cost of $85 

per attachment pin. Replacing an 

attachment pin takes negligible 

additional labor time and required parts 

would cost about $5,720. 

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 

helicopters identified in this rulemaking 

action. 

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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2017–17–01 Airbus Helicopters: 

Amendment 39–18991; Docket No. 

FAA–2017–0419; Product Identifier 

2015–SW–077–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Model AS332L2 helicopters with a 

main rotor (M/R) blade attachment pin 

(attachment pin) part number (P/N) 332A31– 

2123–00 or P/N 332A31–2115–20 installed; 

and 

(2) Model EC225LP helicopters with an 

attachment pin P/N 332A31–3204–20 

installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion or a crack in an attachment pin. 

This condition could result in loss of an M/ 

R blade and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective September 25, 

2017. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) For Model AS332L2 helicopters, within 

410 hours time-in-service (TIS), and for 

Model EC225LP helicopters within 660 hours 

TIS, remove each attachment pin and inspect 

the protective coating on the inside of the 

attachment pin for scratches and missing 

protective coating. 

(i) If there is a scratch or any missing 

protective coating, sand the attachment pin 

to remove the varnish in the area depicted as 

‘‘Area A’’ in Figure 1 of Airbus Helicopters 

Alert Service Bulletin (ASB) No. AS332– 

05.00.99, Revision 0, dated December 22, 

2014 (AS332–05.00.99), or Airbus 

Helicopters ASB No. EC225–05A040, 

Revision 0, dated December 22, 2014 

(EC225–05A040), as applicable to your model 

helicopter. 

(ii) Using a 10X or higher power 

magnifying glass, inspect for corrosion and 

pitting at the chamfer. An example of pitting 

is shown in the Accomplishment 

Instructions, paragraph 3.B.3., Note 1, of 

AS332–05.00.99, and paragraph 3.B.2., Note 

1, of EC225–05A040. If there is any 

corrosion, remove the corrosion. If there is 

any pitting, replace the attachment pin. Do 

not sand the attachment pin to remove a 

corrosion pit. 

(iii) Using a 10X or higher power 

magnifying glass, inspect the inside and 

outside of the attachment pin for a crack in 

the areas depicted as ‘‘Area A’’ and ‘‘Area B’’ 

in Figure 1 of AS332–05.00.99 or EC225– 

05A040, as applicable to your model 

helicopter. Pay particular attention to the 

chamfer in ‘‘Area A.’’ If there is a crack, 

remove the attachment pin from service. 

(2) Thereafter, for Model AS332L2 

helicopters, at intervals not to exceed 825 

hours TIS or 26 months, whichever occurs 

first; and for Model EC225LP helicopters, at 

intervals not to exceed 1,320 hours TIS or 26 

months, whichever occurs first; perform the 

actions specified in paragraph (e)(1) of this 

AD. Corrosion may be removed from an 

attachment pin as specified in paragraph 

(e)(1)(ii) of this AD a maximum of four times. 

If there is a fifth occurrence of corrosion on 

an attachment pin, before further flight, 

remove the attachment pin from service. 

(3) Do not install an attachment pin P/N 

332A31–2123–00, P/N 332A31–2115–20, or 

P/N 332A31–3204–20 on any helicopter 

unless you have complied with the actions in 

paragraph (e)(1) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, FAA, may approve AMOCs for this 

AD. Send your proposal to: David Hatfield, 

Aviation Safety Engineer, Safety Management 

Section, Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5116; email 9– 

ASW–FTW–AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

No. 2015–0016, dated January 30, 2015. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2017–0419. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 


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(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