This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

21639 

Vol. 80, No. 75 

Monday, April 20, 2015 

NUCLEAR REGULATORY 

COMMISSION 

10 CFR Part 72 

[NRC–2014–0233] 

RIN 3150–AJ47 

List of Approved Spent Fuel Storage 

Casks: Holtec International HI–STORM 

100 Cask System, Certificate of 

Compliance No. 1014, Amendment No. 

8, Revision No. 1 

AGENCY: Nuclear Regulatory 

Commission. 

ACTION: Direct final rule; withdrawal. 

SUMMARY: The U.S. Nuclear Regulatory 

Commission (NRC) is withdrawing a 

direct final rule that would have 

amended the NRC’s spent fuel storage 

regulations by revising the Holtec 

International HI–STORM 100 Cask 

System listing within the ‘‘List of 

approved spent fuel storage casks’’ to 

add Amendment No. 8, Revision No. 1. 

This rule would have superseded 

Amendment No. 8 (effective May 2, 

2012, and corrected on November 16, 

2012), to the Certificate of Compliance 

(CoC) No. 1014. The NRC is taking this 

action because it has received at least 

one significant adverse comment in 

response to a companion proposed rule 

that was concurrently published with 

the direct final rule. 

DATES: Effective April 20, 2015, the NRC 

withdraws the direct final rule 

published at 80 FR 6430 on February 5, 

2015. 

ADDRESSES: Please refer to Docket ID 

NRC–2014–0233 when contacting the 

NRC about the availability of 

information for this action. You may 

obtain publicly-available information 

related to this action by any of the 

following methods: 

• Federal Rulemaking Web site: Go to 

http://www.regulations.gov and search 

for Docket ID NRC–2014–0233. Address 

questions about NRC dockets to Carol 

Gallagher; telephone: 301–415–3463; 

email: Carol.Gallagher@nrc.gov. For 

technical questions, contact the 

individual listed in the FOR FURTHER

INFORMATION CONTACT section of this 

document. 

• NRC’s Agencywide Documents 

Access and Management System 

(ADAMS): You may obtain publiclyavailable documents online in the 

ADAMS Public Documents collection at 

http://www.nrc.gov/reading-rm/

adams.html. To begin the search, select 

‘‘ADAMS Public Documents’’ and then 

select ‘‘Begin Web-based ADAMS 

Search.’’ For problems with ADAMS, 

please contact the NRC’s Public 

Document Room (PDR) reference staff at 

1–800–397–4209, 301–415–4737, or by 

email to pdr.resource@nrc.gov. 

• NRC’s PDR: You may examine and 

purchase copies of public documents at 

the NRC’s PDR, Room O1–F21, One 

White Flint North, 11555 Rockville 

Pike, Rockville, Maryland 20852. 

FOR FURTHER INFORMATION CONTACT: 

Gregory R. Trussell, Office of Nuclear 

Material Safety and Safeguards, U.S. 

Nuclear Regulatory Commission, 

Washington, DC 20555–0001; telephone: 

301–415–6445; email: Gregory.Trussell@

nrc.gov. 

SUPPLEMENTARY INFORMATION: On 

February 5, 2015 (80 FR 6430), the NRC 

published in the Federal Register a 

direct final rule amending its 

regulations in part 72 of Title 10 of the 

Code of Federal Regulations to amend 

the NRC’s spent fuel storage regulations 

by revising the Holtec International HI– 

STORM 100 Cask System listing within 

the ‘‘List of approved spent fuel storage 

casks’’ to add Amendment No. 8, 

Revision No. 1, which would have 

superseded Amendment No. 8 (effective 

May 2, 2012, and corrected on 

November 16, 2012), to the Certificate of 

Compliance (CoC) No. 1014. The direct 

final rule was to become effective on 

April 21, 2015. The NRC also 

concurrently published a companion 

proposed rule on February 5, 2015 (80 

FR 6466). 

In the February 5, 2015, proposed 

rule, the NRC stated that if any 

significant adverse comments were 

received, then the NRC would withdraw 

the direct final rule by publishing a 

document in the Federal Register. As a 

result, the direct final rule would not 

take effect. The NRC received 16 

comments from private citizens. The 

comments are available at 

www.regulations.gov by searching on 

Docket ID NRC–2014–0233. The NRC 

determined that at least one of the 

comments is significant and adverse as 

defined in Section II, ‘‘Procedural 

Background,’’ of the direct final rule, 

because the comment raises an issue 

serious enough to warrant a substantive 

response to clarify or complete the 

record. Therefore, the NRC is 

withdrawing the direct final rule. 

As stated in the February 5, 2015, 

proposed rule, the NRC will address the 

comments in a subsequent final rule. 

The NRC will not initiate a second 

comment period on this action. 

Dated at Rockville, Maryland, this 10th day 

of April, 2015. 

For the Nuclear Regulatory Commission. 

Mark A. Satorius, 

Executive Director for Operations. 

[FR Doc. 2015–09023 Filed 4–17–15; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0497; Directorate 

Identifier 2012–NM–192–AD; Amendment 

39–18128; AD 2015–06–10] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

ATR–GIE Avions de Transport Re ́gional 

Model ATR72–212A airplanes. This AD 

requires inspection of the shock mount 

pick-up fittings and cone bolts, and 

replacement of certain shock mount 

pick-up fittings if necessary. This AD 

was prompted by reports of several 

cases of engine shock mount pick-up 

fittings with cracks or failure on the 

engine left-hand (LH) aft side 

attachment. We are issuing this AD to 

detect and correct an aft side attachment 

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21640 Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 

pick-up fitting failure associated with a 

cone bolt failure that could reduce the 

structural integrity of the concerned 

engine nacelle, and possibly result in 

detachment of the engine and 

consequent reduced control of the 

airplane. 

DATES: This AD becomes effective May 

5, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 5, 2015. 

We must receive comments on this 

AD by June 4, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre 

Nadot, 31712 Blagnac Cedex, France; 

telephone +33 (0) 5 62 21 62 21; fax +33 

(0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 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–2015– 

0497. 

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–2015– 

0497; 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2012–0192, dated September 

21, 2012 (corrected September 24, 2012) 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain ATR–GIE Avions 

de Transport Re ́gional Model ATR72– 

212A airplanes. The MCAI states: 

Several cases of engine shock mount pickup fitting with crack or failure have been 

reported, always on engine Left Hand (LH) aft 

side attachment. Prompted by those reports, 

improved Part Number (P/N) S54210394200 

(Barry Control P/N 94423–05) fittings 

(machined radius modification) have been 

introduced in production, having serial 

number (s/n) 2451 and higher. No crack has 

been reported on aeroplanes equipped with 

those improved fittings. 

Two recent cases of failed cone bolt have 

been reported on ATR 72–212A aeroplanes, 

both on engine Right Hand (RH) aft side 

isolator. 

An aft side attachment pick-up fitting 

failure associated to a cone bolt failure, if not 

detected and corrected, could reduce the 

structural integrity of the concerned engine 

nacelle, possibly resulting in detachment of 

the engine and consequent reduced control of 

the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed] 

inspection [for cracks] of the shock mount 

pick-up fittings and cone bolts and, 

depending on findings, accomplishment of 

applicable repair. This AD also requires 

replacement of all LH shock mount pick-up 

fitting P/N S54210394200 having a s/n lower 

than 2451. 

* * * * * 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0497. 

Related Service Information Under 1 

CFR Part 51 

ATR–GIE Avions de Transport 

Re ́gional (ATR) has issued the following 

service information. The service 

information describes procedures for a 

detailed visual inspection of the engine 

shock mounts. The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

• ATR ATR72 airplane maintenance 

manual (AMM) Job Instruction Card 54– 

11–61 DVI 10000, Detailed Visual 

Inspection of Forward Engine Mount, 

dated March 1, 2012. 

• ATR ATR72 AMM Job Instruction 

Card 71–20–00 DVI 10000, Detailled 

(sic) Visual Inspec[tion] of Engine 

Shockmounts, dated March 1, 2012. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0497; 

Directorate Identifier 2012–NM–192– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

Currently, there are no affected 

airplanes on the U.S. Register. However, 

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Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 21641 

if an affected airplane is imported and 

placed on the U.S. Register in the future, 

we estimate that it will take about 3 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$255 per product. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave., SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that 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 the 

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): 

2015–06–10 ATR–GIE Avions de Transport 

Re ́gional: Amendment 39–18128. Docket 

No. FAA–2015–0497; Directorate 

Identifier 2012–NM–192–AD. 

(a) Effective Date 

This AD becomes effective May 5, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to ATR–GIE Avions de 

Transport Re ́gional Model ATR72–212A 

airplanes, certificated in any category, 

manufacturer serial numbers 468 through 719 

inclusive, 723, 776, 777, 779, 821, and 837. 

(d) Subject 

Air Transport Association (ATA) of 

America 54, Nacelles/Pylons. 

(e) Reason 

This AD was prompted by reports of 

several cases of engine shock mount pick-up 

fittings with cracks or failure on the engine 

left-hand (LH) aft side attachment. We are 

issuing this AD to detect and correct an aft 

side attachment pick up fitting failure 

associated with a cone bolt failure that could 

reduce the structural integrity of the 

concerned engine nacelle, and possibly result 

in detachment of the engine and consequent 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Engine Shock Mount Pick-up Fittings 

Inspection 

Within 6 months after the effective date of 

this AD, accomplish the actions specified by 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD 

concurrently. 

(1) Identify the serial number (S/N) of the 

part number (P/N) S54210394200 (Barry 

Control P/N 94423–05) LH and right-hand 

(RH) shock mount pick-up fittings installed 

on both engine nacelles. Figure 1 to 

paragraph (g)(1) of this AD identifies the 

fitting part number and serial number 

locations. 

BILLING CODE 4910–13–C 

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21642 Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 

(2) Do a detailed inspection of both LH and 

RH aft side isolator pick-up fittings on both 

engines to detect cracks, in accordance with 

paragraph 004.1 of ATR ATR72 Aircraft 

Maintenance Manual (AMM) Job Instruction 

Card (JIC) 54–11–61 DVI 10000, dated March 

1, 2012. Refer to figure 2 to paragraph (g)(2) 

of this AD for potential crack location. 


mstockstill on DSK4VPTVN1PROD with RULESER20AP15.002</GPH>
Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 21643 

(3) Do a detailed inspection of both LH and 

RH aft shock mount cone bolts on both 

engines to detect cracks, in accordance with 

paragraph 006.3.A. of ATR ATR72 AMM JIC 

71–20–00 DVI 10000. Refer to figure 3 to 

paragraph (g)(3) of this AD for potential crack 

location. 


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21644 Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 

(h) Corrective Actions 

(1) If any crack is found during any 

inspection required by paragraphs (g)(2) and 

(g)(3) of this AD: Before further flight, repair 

in accordance with a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or ATR’s EASA Design Organization 

Approval (DOA). 

(2) If the serial number of the LH shock 

mount pick-up fitting, identified during any 

inspection required by paragraph (g)(1) of 

this AD, is lower than 2451 or is unreadable, 

and no crack has been found during any 


mstockstill on DSK4VPTVN1PROD with RULESER20AP15.004</GPH>

Figure 3 to paragraph (g)(3) of this AD - Shock Mount Cone Bolt 
Federal Register / Vol. 80, No. 75 / Monday, April 20, 2015 / Rules and Regulations 21645 

inspection required by paragraphs (g)(2) and 

(g)(3) of this AD: Within 6 months after the 

inspection required by paragraph (g)(2) of 

this AD, replace the LH shock mount pickup fitting P/N S54210394200 with a 

serviceable LH shock mount pick-up fitting 

having a serial number equal to or higher 

than 2451, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or ATR—GIE 

Avions de Transport Re ́gional’s EASA DOA. 

(i) Parts Installation Limitation 

As of the effective date of this AD, do not 

install on any airplane a LH shock mount 

pick-up fitting P/N S54210394200, unless it 

is serviceable and has been determined to 

have an S/N equal to or higher than 2451, in 

accordance with the requirements of 

paragraph (g)(1) of this AD. 

(j) Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspections 

required by paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD to ATR at techdesk@atr.fr 

and continued.airworthiness@atr.fr at the 

applicable time specified in paragraph (j)(1) 

or (j)(2) of this AD. The report must include 

the airplane serial number, registration, 

inspection date, inspection results, and 

engine pick-up serial numbers. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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. The AMOC approval letter 

must specifically reference this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0192, dated 

September 21, 2012 (corrected September 24, 

2012), for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–0497. 

(2) 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) ATR ATR72 Airplane Maintenance 

Manual (AMM) Job Instruction Card 54–11– 

61 DVI 10000, Detailed Visual Inspection of 

Forward Engine Mount, dated March 1, 2012. 

(ii) ATR ATR72 AMM Job Instruction Card 

71–20–00 DVI 10000, Detailled (sic) Visual 

Inspec[tion] of Engine Shockmounts, dated 

March 1, 2012. 

(3) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

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/ibr-locations.html. 

Issued in Renton, Washington, on March 

19, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07162 Filed 4–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0475; Directorate 

Identifier 2010–NM–199–AD; Amendment 

39–18137; AD 2015–08–01] 

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 757–200, 

–200PF, –200CB, and –300 series 

airplanes. This AD was prompted by 

numerous reports of unintended lateral 

oscillations during final approach, just 

before landing. This AD requires, 

depending on airplane configuration, 

installing new relays and bracket 

assemblies, inspecting to ensure that the 

new relays do not contact adjacent wire 

bundles, torquing the bracket assembly 

installation nuts and ground stud nuts, 

doing bond resistance tests between the 

bracket assemblies and the terminal lugs 

on the ground studs, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

reduce the chance of unintended lateral 

oscillations near touchdown, which 

could result in loss of lateral control of 

the airplane, and consequent airplane 

damage or injury to flightcrew and 

passengers. 

DATES: This AD is effective May 26, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 26, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

mstockstill on DSK4VPTVN1PROD with RULES