### 36387 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules

commercial distribution of byproduct material to allow recipients of exempt quantities of PCTE/MFP to commercially redistribute the material without a license. The petitioner states that once GE obtains an exempt quantity distribution license from the NRC, there should be no significant health, safety or common defense and security concerns that would preclude its customers from further redistribution of the material without a license.

The NRC has determined that the petition meets the threshold sufficiency requirements for a petition for rulemaking under Title 10 of the Code of Federal Regulations (10 CFR), 2.802, and the petition has been docketed as PRM–30–65. The NRC is requesting public comment on the petition for rulemaking.

Discussion of the Petition

The petitioner states that under current NRC regulations (and with a specific license, if approved), it is able to manufacture and commercially distribute PCTE/MFP membranes to that segment of its customers that will not be further distributing the product for commercial purposes. However, current regulations at 10 CFR 30.18(c) and (d) prohibit the petitioner from distribution of the material to a substantial portion of its customer base that would commercially redistribute the material if authorized to do so.

The petitioner proposes that 10 CFR 30.18 be modified as follows:

(c) This section does not authorize for purposes of commercial distribution the production, packaging, repackaging, or transfer of byproduct material or the incorporation of byproduct material into products intended for commercial distribution, except as provided in § 30.18(f).

(d) Except as provided in § 30.18(f), no person may, for purposes of commercial distribution, transfer byproduct material in the individual quantities set forth in § 30.71 Schedule B, knowing or having reason to believe that such quantities of byproduct material will be transferred to persons exempt under this section or equivalent regulations of an Agreement State, except in accordance with a license issued under § 32.18 of this chapter, which license states that the byproduct material may be transferred by the licensee to persons exempt under this section or the equivalent regulations of an Agreement State.

(f) Polymer track etch membrane containing mixed fission products in individual quantities, each of which does not exceed the applicable quantity set forth in § 30.71 Schedule B, may be redistributed commercially to any person without the redistributor obtaining a specific license under § 32.18, so long as the person who initially manufactures, processes, produces, packages, repackages, or transfers quantities of byproduct material for commercial distribution obtains a specific license under § 32.18.

The petitioner has separately requested an NRC exempt distribution license under 10 CFR 32.18 to authorize it to commercially distribute the PCTE/ MFP membranes to its customers, and believes that once it obtains the license, there should be no significant health, safety or common defense and security concerns that would preclude its customers from further redistribution without a license. The petitioner included an analysis in the petition for rulemaking document to support its belief. The petitioner states that PCTE/ MFP membranes are used in a wide variety of research, medical, academic, scientific and industrial applications. In particular, PCTE/MFP membranes are used in pharmaceutical, medical device, and water filtration applications. The petitioner believes that the amendments are necessary to allow it to distribute the PCTE/MFP membranes to the full range of its customers.

Dated at Rockville, Maryland this 16th day of June, 2011.

For the Nuclear Regulatory Commission. Annette Vietti-Cook, Secretary of the Commission.
[FR Doc. 2011–15593 Filed 6–21–11; 8:45 am]

**BILLING CODE 7590–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0570; Directorate Identifier 2011–NM–014–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A300 Series Airplanes; Model A310**  **Series Airplanes; and Model A300 B4– 600, B4–600R, and F4–600R Series**  **Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–**  **600 Series Airplanes)**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

* * * * * A recent analysis conducted by the manufacturer showed a particular risk for explosive failure of the * * * hydraulic accumulator.

This condition, if not detected and corrected, might, for some aeroplane installations, lead to damage to all three hydraulic circuits, possibly resulting in loss of control of the aeroplane or could, for certain other aeroplane installations, lead to an undetected fire in the wheel bay.
* * * * *

The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  We must receive comments on this proposed AD by August 8, 2011.

**ADDRESSES :**  You may send comments 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 SAS— EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; 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 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 :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116,


### 36388 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules

Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; 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–2011–0570; Directorate Identifier 2011–NM–014–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 Community, has issued EASA Airworthiness Directive 2011–0006, dated January 17, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Since 1984, the design of the hydraulic accumulator installed on all the affected Airbus types has changed. The Part Number (P/N) remained the same, but the manufacturer did not record the serial number of the part that was the first to be manufactured to the changed design specification.

The new design hydraulic accumulator is manufactured with 2 pieces unit welded, instead of 4 pieces unit with 3 welds (old design) as pictured in Appendix 1 of this [EASA] AD. The welding process of the new design hydraulic accumulator provides a higher strength shell material and more reliability.

A recent analysis conducted by the manufacturer showed a particular risk for explosive failure of the old design hydraulic accumulator. This condition, if not detected and corrected, might, for some aeroplane installations, lead to damage to all three hydraulic circuits, possibly resulting in loss of control of the aeroplane or could, for certain other aeroplane installations, lead to an undetected fire in the wheel bay.

For the reasons explained above, this [EASA] AD requires a one time detailed visual inspection to identify the old designed accumulators installed on certain hydraulic systems, the replacement of those accumulators by new designed accumulators and, irrespective of findings, the installation of warning placards to avoid installation of old designed accumulators on the affected hydraulic systems.

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued the service bulletins identified in the following table. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.



### TABLE 

### —S ERVICE INFORMATION

Airbus mandatory service bulletin— Revision— Dated—

A300–29–0126, including Appendices 01 and 02 ............................................................................ 01 ................................. October 12, 2010. A300–29–0127 ................................................................................................................... ............... Original ......................... August 12, 2010. A300–29–6063, including Appendix 01 ............................................................................................. Original ......................... August 12, 2010. A300–29–6064 ................................................................................................................... ............... Original ......................... August 12, 2010. A310–29–2099, including Appendix 01 ............................................................................................. Original ......................... August 12, 2010. A310–29–2100 ................................................................................................................... ............... Original ......................... August 12, 2010.

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.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 184 products of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $197 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $145,728, or $792 per product.

In addition, we estimate that any necessary follow-on actions would take about 5 work-hours and require parts costing $10,700, for a cost of $11,125 per product. We have no way of determining the number of products that may need these actions. 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


### 36389 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules

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); and

3. 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 a regulatory evaluation of the estimated costs to comply with this proposed 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. 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 AD:

Airbus: Docket No. FAA–2011–0570; Directorate Identifier 2011–NM–014–AD.

Comments Due Date

(a) We must receive comments by August 8, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the products identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers.

(1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes.

(2) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes.

(3) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; A300 B4–605R and B4–622R airplanes; A300 F4–605R and F4– 622R airplanes; and A300 C4–605R Variant F airplanes.
Subject

(d) Air Transport Association (ATA) of America Code 29: Hydraulic power.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states: A recent analysis conducted by the manufacturer showed a particular risk for explosive failure of the * * * hydraulic accumulator.

This condition, if not detected and corrected, might, for some aeroplane installations, lead to damage to all three hydraulic circuits, possibly resulting in loss of control of the aeroplane or could, for certain other aeroplane installations, lead to an undetected fire in the wheel bay.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Inspection, Replacement, and Placard Installation

(g) Within 30 months or 6,000 flight hours after the effective date of this AD, whichever occurs first: Do a detailed inspection of each type 5 hydraulic accumulator, part number (P/N) 3059103–1, P/N 3059103–2, P/N 3059103–8, and P/N 3059103–9, to determine if an old design accumulator (i.e., pre-1984) is installed on any affected hydraulic circuit indicated in table 1 of this AD, as applicable, in accordance with the Accomplishment Instructions of the applicable Airbus mandatory service bulletin identified in table 2 of this AD.



### T ABLE 

### 1—A PPLICABLE HYDRAULIC
CIRCUITS

Airbus model Hydraulic circuit

A300 airplanes pre-modification 02447. Blue and Green.

A300 airplanes post-modification 02447. Blue.

A300–600 airplanes ........... Blue. A310 airplanes ................... Green.



### T ABLE 

### 2—A PPLICABLE SERVICE INFORMATION

Airbus mandatory service bulletin— Revision — Dated —

A300–29–0126 (for Model A300 airplanes) ..................................................................................... 01 .................................... October 12, 2010. A300–29–6063 (for Model A300–600 airplanes) ............................................................................. Original ........................... August 12, 2010. A310–29–2099 (for Model A310 airplanes) ..................................................................................... Original ........................... August 12, 2010.

(h) If, during any detailed inspection required by paragraph (g) of this AD, an old design hydraulic accumulator ( i.e., pre-1984) is found installed on any affected hydraulic circuit as indicated in table 1 of this AD, as applicable to airplane model, before further flight replace each affected old design accumulator with a new design accumulator, in accordance with the Accomplishment Instructions of the applicable Airbus mandatory service bulletin identified in table 2 of this AD.

(i) Before further flight after accomplishing the inspection required by paragraph (g) of this AD: Install a placard at the designated location of any affected hydraulic circuit indicated in table 1 of this AD, as applicable to airplane model, in accordance with the Accomplishment Instructions of the applicable Airbus mandatory service bulletin identified in table 3 of this AD.



### TABLE 

### 3—O THER APPLICABLE SERVICE
INFORMATION

Airbus Mandatory Service Bulletin— Dated—

A300–29–0127 ................. August 12, 2010. A300–29–6064 ................. August 12, 2010. A310–29–2100 ................. August 12, 2010. FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(j) The following provisions also apply to this AD:

(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


### 36390 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules

appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(k) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0006, dated January 17, 2011; and the service bulletins identified in table 4 of this AD; for related information.



### T ABLE 

### 4—R ELATED SERVICE INFORMATION

Airbus Mandatory Service Bulletin— Revision— Dated—

A300–29–0126 ............................................................................................ 01 ..................... .................................................... October 12, 2010. A300–29–0127 ............................................................................................ Original ............... ................................................. August 12, 2010. A300–29–6063 ............................................................................................ Original ............... ................................................. August 12, 2010. A300–29–6064 ............................................................................................ Original ............... ................................................. August 12, 2010. A310–29–2099 ............................................................................................ Original ............... ................................................. August 12, 2010. A310–29–2100 ............................................................................................ Original ............... ................................................. August 12, 2010.

Issued in Renton, Washington, on June 10,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–15535 Filed 6–21–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0571; Directorate Identifier 2010–NM–263–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747SP Series**  **Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require replacing or modifying the upper and lower rudder power control modules (PCM). This proposed AD was prompted by a report of a rudder hard-over event on a Model 747–400 series airplane, caused by a rudder PCM manifold cracking and separating in the area of the yaw damper cavity end-cap. We are proposing this AD to prevent a failure of the lower or upper rudder PCM manifold, which could result in a hard-over of the rudder surface leading to an increase in pilot workload and a possible high-speed runway excursion upon landing. **DATES :**  We must receive comments on this proposed AD by August 8, 2011.

**ADDRESSES :**  You may send comments 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; 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 Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Marie Hogestad, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 917–6418; fax: 425–917–6590; e-mail: marie.hogestad@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2011–0571; Directorate Identifier 2010– NM–263–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 because of 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

We received a report from an operator of a Model 747–400 series airplane of a lower rudder hard-over event caused by a lower rudder PCM manifold cracking and separating in the area of the yaw damper cavity end-cap. This allowed the yaw damper sleeve to shift, giving the system a lower rudder left input (beyond the yaw damper authority).