58224 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 

of 1982, secs. 117(a), 132, 133, 134, 135, 137, 

141, 145(g), 148, 218(a) (42 U.S.C. 10137(a), 

10152, 10153, 10154, 10155, 10157, 10161, 

10165(g), 10168, 10198(a)); 44 U.S.C. 3504 

note. 

■ 2. In § 72.214, Certificate of 

Compliance No. 1032 is revised to read 

as follows: 

§ 72.214 List of approved spent fuel 

storage casks. 

* * * * * 

Certificate Number: 1032. 

Initial Certificate Effective Date: June 

13, 2011, superseded by Amendment 

Number 0, Revision 1, on April 25, 

2016. 

Amendment Number 0, Revision 1, 

Effective Date April 25, 2016. 

Amendment Number 1 Effective Date: 

December 17, 2014, superseded by 

Amendment. 

Number 1, Revision 1, on June 2, 

2015. 

Amendment Number 1, Revision 1, 

Effective Date: June 2, 2015. 

SAR Submitted by: Holtec 

International, Inc. 

SAR Title: Final Safety Analysis 

Report for the Holtec International HI– 

STORM FW System. 

Docket Number: 72–1032. 

Certificate Expiration Date: June 12, 

2031. 

Model Number: HI–STORM FW 

MPC–37, MPC–89. 

* * * * * 

Dated at Rockville, Maryland, this 18th day 

of September, 2015. 

For the Nuclear Regulatory Commission. 

Michael F. Weber, 

Acting, Executive Director for Operations. 

[FR Doc. 2015–24475 Filed 9–25–15; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3636; Directorate 

Identifier 2015–NM–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Defense and Space S.A. 

(formerly known as Construcciones 

Aeronauticas, S.A.) Model CN–235, CN– 

235–100, CN–235–200, and CN–235– 

300 airplanes. This proposed AD was 

prompted by a report of cracks on the 

lugs of the inboard and outboard control 

rod fittings of the right hand (RH) and 

left hand (LH) side ailerons. This 

proposed AD would require a one-time 

non-destructive test (NDT) inspection of 

the inboard and outboard control rod 

fittings of the RH and LH side ailerons 

for cracks and corrosion, and repair if 

necessary. We are proposing this AD to 

detect and correct cracks and corrosion 

on the lugs of the inboard and outboard 

control rod fittings of the RH and LH 

side ailerons, which could lead to 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

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 proposed AD, contact EADS–CASA, 

Military Transport Aircraft Division 

(MTAD), Integrated Customer Services 

(ICS), Technical Services, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; 

telephone: +34 91 585 55 84; fax: +34 91 

585 55 05; email: 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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. 

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– 

3636; 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 proposed 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone: 425–227– 

1112; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3636; Directorate Identifier 

2015–NM–043–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

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 2015–0040, dated March 6, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Defense and Space S.A. (formerly 

known as Construcciones Aeronauticas, 

S.A.) Model CN–235, CN–235–100, CN– 

235–200, and CN–235–300 airplanes. 

The MCAI states: 

A CN–235 operator recently reported 

finding, during scheduled maintenance tasks, 

cracks on the lugs of the control rod fittings 

(inboard and outboard) of the ailerons [Right 

Hand (RH) and Left Hand (LH) side] of two 

aeroplanes. At the time of the finding, the 

two affected aeroplanes had accumulated 

between 16,000 and 17,000 flight hours (FH), 

around 6,000 flight cycles and had been in 

service for 20 years. Following the 

investigation results, it was determined that 

these cracks were due to stress corrosion. 

This condition, if not detected and 

corrected, could lead to aileron fittings 


rmajette on DSK7SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 58225 

failure, possibly resulting in reduced control 

of the aeroplane. 

To address this unsafe condition and verify 

the integrity of the fittings, EADS–CASA 

(Airbus Military) issued Alert Operators 

Transmission (AOT) CN235–57–0001 to 

provide instructions for a one-time NonDestructive (NDT) inspection of the affected 

fittings for cracks and corrosion. 

For the reasons described above, this 

[EASA] AD requires a one-time NDT 

inspection of the affected aileron fittings and, 

if discrepancies are detected, 

accomplishment of applicable corrective 

action(s) [repair of any cracked or corroded 

parts]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3636. 

Related Service Information Under 1 

CFR part 51 

Airbus Defense and Space S.A. 

(formerly known as Construcciones 

Aeronauticas, S.A.) has issued Airbus 

Military Alert Operators Transmission 

(AOT) AOT–CN235–57–0001, Revision 

1, dated March 14, 2014. The service 

information describes procedures for a 

one-time NDT inspection of the inboard 

and outboard control rod fittings of the 

RH and LH side ailerons for cracks and 

corrosion, and repair if necessary. 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 of 

this NPRM. 

FAA’s Determination and Requirements 

of this Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 24 airplanes of U.S. registry. 

We also estimate that it would take 

about 30 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $61,200, or $2,550 per product. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus Defense and Space S.A. (Formerly 

Known as Construcciones Aeronauticas, 

S.A.): Docket No. FAA–2015–3636; 

Directorate Identifier 2015–NM–043–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Defense and 

Space S.A. (formerly known as 

Construcciones Aeronauticas, S.A.) Model 

CN–235, CN–235–100, CN–235–200, and 

CN–235–300 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report of 

cracks on the lugs of the inboard and 

outboard control rod fittings of the right hand 

(RH) and left hand (LH) side ailerons. We are 

issuing this AD to detect and correct cracks 

and corrosion on the lugs of the inboard and 

outboard control rod fittings of the RH and 

LH side ailerons, which could lead to 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Non-Destructive Test (NDT) 

Inspection 

(1) At the later of the compliance times 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD: Do a one-time NDT inspection of the 

inboard and outboard control rod fittings of 

the RH and LH side ailerons for cracks, and 

a one-time general visual inspection for 

corrosion, in accordance with Airbus 

Military Alert Operators Transmission (AOT) 

AOT–CN235–57–0001, Revision 1, dated 

March 14, 2014. 

(i) Before exceeding 8,000 flight hours or 

10 years since first flight of the airplane, 

whichever occurs first. 

(ii) Within 3 months after the effective date 

of this AD. 

(2) If any crack or corrosion is found 

during any inspection required by paragraph 

(g)(1) of this AD, before further flight, contact 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus Defense and Space S.A.’s 

(formerly known as Construcciones 

Aeronauticas, S.A.) EASA Design 

Organization Approval (DOA) for approved 

repair instructions, and before further flight, 

accomplish the repair accordingly. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 


rmajette on DSK7SPTVN1PROD with PROPOSALS
58226 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1112; 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 

the EASA; or Airbus Defense and Space 

S.A.’s (formerly known as Construcciones 

Aeronauticas, S.A.) EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0040, dated 

March 6, 2015, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–3636. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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. 

Issued in Renton, Washington, on 

September 16, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24424 Filed 9–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3635; Directorate 

Identifier 2015–NM–037–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by an evaluation by 

the design approval holder (DAH) 

indicating that the fuselage skin repairs 

are subject to widespread fatigue 

damage (WFD). This proposed AD 

would require an inspection to 

determine whether any fuselage external 

skin (doubler) repairs have been 

accomplished, an inspection for 

cracking of certain repaired external 

fuselage skin areas in the fuselage, and 

repair if necessary. We are proposing 

this AD to detect and correct fatigue 

cracking of the fuselage skin, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

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 proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

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– 

3635; 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 proposed 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3635; Directorate Identifier 

2015–NM–037–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 


rmajette on DSK7SPTVN1PROD with PROPOSALS