### 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 Initial Certificate Effective Date: June 13, 2011, superseded by Amendment Number 0, Revision 1, on April 25,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Amendment Number 1 Effective Date: December 17, 2014, superseded by Amendment.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


### 58225 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules

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 toprovide 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:


### 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.