24832 Federal Register / Vol. 76, No. 85 / Tuesday, May 3, 2011 / Proposed Rules 

NRC–2011–0012. Address questions 

about NRC dockets to Carol Gallagher; 

telephone: 301–492–3668; e-mail: 

Carol.Gallagher@nrc.gov. 

• Mail comments to: Secretary, U.S. 

Nuclear Regulatory Commission, 

Washington, DC 20555–0001, Attn: 

Rulemakings and Adjudications Staff. 

• E-mail comments to: 

Rulemaking.Comments@nrc.gov. If you 

do not receive a reply e-mail confirming 

that we have received your comments, 

contact us directly at 301–415–1677. 

• Hand deliver comments to: 11555 

Rockville Pike, Rockville, Maryland 

20852, between 7:30 a.m. and 4:15 p.m. 

Federal workdays. (telephone: 301–415– 

1677). 

• Fax comments to: Secretary, U.S. 

Nuclear Regulatory Commission at 301– 

415–1101. 

You can access publicly available 

documents related to this proposed rule 

using the following methods: 

• NRC’s Public Document Room 

(PDR): The public may examine and 

have copied, for a fee, publicly available 

documents at the NRC’s PDR, O1–F21, 

One White Flint North, 11555 Rockville 

Pike, Rockville, Maryland 20852. 

• NRC’s Agencywide Documents 

Access and Management System 

(ADAMS): Publicly available documents 

created or received at the NRC are 

available online in the NRC Library at 

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

adams.html. From this page, the public 

can gain entry into ADAMS, which 

provides text and image files of the 

NRC’s public documents. If you do not 

have access to ADAMS or if there are 

problems in accessing the documents 

located in ADAMS, contact the NRC’s 

PDR reference staff at 1–800–397–4209, 

301–415–4737, or by e-mail to 

pdr.resource@nrc.gov. The preliminary 

proposed rule language is available 

electronically under ADAMS Accession 

Number ML111150205, the regulatory 

basis is available under ADAMS 

accession number ML111040419, and 

the ‘‘Technical Analysis Supporting 

Definition of Period of Performance for 

Low-Level Waste Disposal.’’ is available 

under ADAMS Accession Number 

ML111030586. 

• Federal Rulemaking Web site: 

Public comments and supporting 

materials related to this notice, 

including the preliminary proposed rule 

language and regulatory basis 

documents, can be found at http:// 

www.regulations.gov by searching on 

Docket ID NRC–2011–0012. 

FOR FURTHER INFORMATION CONTACT: 

Andrew Carrera, Office of Federal and 

State Materials and Environmental 

Management Programs, U.S. Nuclear 

Regulatory Commission, Washington, 

DC 20555–0001, telephone 301–415– 

1078, e-mail Andrew.Carrera@nrc.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The NRC is proposing to amend its 

regulations to require low-level 

radioactive waste disposal facilities to 

conduct site-specific analyses to 

demonstrate compliance with the 

performance objectives in Title 10 of the 

Code of Federal Regulations (10 CFR) 

part 61. The purpose of these 

amendments would be to enhance the 

safe disposal of low-level radioactive 

waste. The NRC is also proposing 

additional changes to the regulations in 

10 CFR part 61 to reduce ambiguity, 

facilitate implementation, and to better 

align the requirements with current 

health and safety standards. 

The NRC is making available a 

preliminary version of the proposed rule 

language and its associated regulatory 

basis documents to inform stakeholders 

of the current status of this proposed 

rulemaking. The NRC is inviting 

stakeholders to comment on the 

preliminary proposed rule language and 

its associated regulatory basis 

documents. The preliminary proposed 

rule language may be subject to 

additional significant revisions during 

the rulemaking process prior to 

publication for formal comment as a 

proposed rule. 

The NRC will review and consider 

any comments received on the 

preliminary proposed rule language and 

regulatory basis documents; however, 

the NRC will not formally respond to 

comments. As appropriate, the 

Statements of Consideration for the 

proposed rule may briefly discuss any 

substantive changes made to the 

proposed rule language as a result of 

comments received on this preliminary 

version. Stakeholders will also have an 

additional opportunity to comment on 

the rule language when it is published 

as a proposed rule in accordance with 

the provisions of the Administrative 

Procedures Act. The NRC will respond 

to any such comments in the Statements 

of Consideration for the final rule. 

The NRC may post updates to the 

preliminary rule language on the 

Federal rulemaking Web site under 

Docket ID NRC–2011–0012. The 

Regulations.gov Web site allows 

members of the public to set-up e-mail 

alerts so that they may be notified when 

documents are added to a docket. Users 

are notified via e-mail at an e-mail 

address provided at the time of 

registration for the notification. 

Directions for signing up for the e-mail 

alerts can be found at http:// 

www.regulations.gov. To do so, navigate 

to a docket folder you are interested in 

and then click the ‘‘Sign up for E-mail 

Alerts’’ link. 

Public Meeting 

The NRC plans to conduct a public 

meeting on May 18, 2011, to discuss the 

preliminary proposed rule language and 

the regulatory basis documents. The 

public meeting will be held from 8:30 

a.m. to 4:30 p.m. at The Legacy Hotel 

and Meeting Centre, 1775 Rockville 

Pike, Rockville, Maryland 20852. The 

meeting will provide an opportunity for 

stakeholders to ask clarifying questions 

to help formulate written comments. 

The meeting agenda can be viewed and 

downloaded electronically from the 

NRC’s Public Meeting Web site. 

Attendees are requested to notify Mr. 

Andrew Carrera at (301) 415–1078 or email Andrew.Carrera@nrc.gov of their 

planned attendance and if special 

services are necessary, such as for the 

hearing impaired. In addition, interested 

individuals may also request to 

participate via teleconference or 

Webinar by contacting Mr. Carrera prior 

to the meeting day. 

Dated at Rockville, Maryland, this 27th day 

of April, 2011. 

For the Nuclear Regulatory Commission. 

Deborah Jackson, 

Deputy Director, Division of 

Intergovernmental Liaison and Rulemaking, 

Office of Federal and State Materials and 

Environmental Management Programs. 

[FR Doc. 2011–10711 Filed 5–2–11; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0387; Directorate 

Identifier 2010–NM–222–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, and –243 

Airplanes, A330–300 Series Airplanes, 

A340–200 Series Airplanes, and A340– 

300 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 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 85 / Tuesday, May 3, 2011 / Proposed Rules 24833 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Surface defects were visually detected on 

the rudder of * * * [an] in-service aeroplane 

during scheduled maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

* * * * * 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

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 June 17, 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 

W12–40, 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— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330-A340@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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; 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–2011–0387; Directorate Identifier 

2010–NM–222–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 2010–0127, 

dated June 23, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of one A319 and one A321 inservice aeroplane during scheduled 

maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

Such reworks were also performed on 

some rudders fitted on A330 and A340–200/ 

–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

To address this unsafe condition, EASA 

issued AD 2010–0021, superseding EASA AD 

2009–0156, to require inspections of specific 

areas and, depending on findings, the 

accomplishment of corrective actions for 

those rudders where production reworks 

have been identified. 

In addition, this AD addresses the rudder 

population that has also been reworked in 

production but is not part of EASA AD 2010– 

0021 applicability. 

Required actions include vacuum loss 

and elasticity laminate checker 

inspections for damage including debonding between the skin and 

honeycomb core of the rudder on 

certain areas of the rudder, and repair if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A330–55–3042 and A340–55– 

4038, both dated April 22, 2010. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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 55 products of U.S. registry. 

We also estimate that it would take 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
24834 Federal Register / Vol. 76, No. 85 / Tuesday, May 3, 2011 / Proposed Rules 

about 6 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 the 

proposed AD on U.S. operators to be 

$28,050, or $510 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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); 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–2011–0387; 

Directorate Identifier 2010–NM–222–AD. 

Comments Due Date 

(a) We must receive comments by June 17, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; certificated 

in any category, all manufacturer serial 

numbers, if equipped with rudders having 

part numbers and serial numbers as 

identified in table 1, table 2, or table 3 of this 

AD. 

TABLE 1—RUDDER PART NUMBER

(P/N) AND AFFECTED RUDDER

SERIAL NUMBER (S/N) 

Rudder P/N 

Affected 

rudder 

S/N 

F554–70000–000–00 .................. TS–2045 

F554–70000–000–00 .................. TS–2046 

F554–71000–000–00–0000 ........ TS–3013 

F554–71000–000–00–0000 ........ TS–3014 

F554–71000–000–00–0000 ........ TS–3020 

F554–71000–000–00–0000 ........ TS–3022 

F554–71000–000–00–0000 ........ TS–3023 

F554–71000–000–00–0000 ........ TS–3027 

F554–71000–000–00–0000 ........ TS–3031 

F554–71000–000–00–0000 ........ TS–3034 

F554–71000–000–00–0000 ........ TS–3036 

F554–71000–000–00–0000 ........ TS–3038 

F554–71000–000–00–0000 ........ TS–3041 

F554–71000–000–00–0000 ........ TS–3046 

F554–71000–000–00–0000 ........ TS–3054 

F554–70005–000–00–0000 ........ TS–3102 

F554–71002–000–00–0002 ........ TS–4018 

F554–71002–000–00–0002 ........ TS–4022 

F554–71002–000–00–0002 ........ TS–4031 

TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N 

Rudder P/N 

Affected 

Rudder 

S/N 

A554–71500–024–00 ................. TS–1014 

TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N—Continued 

Rudder P/N 

Affected 

Rudder 

S/N 

A554–71500–030–00 ................. TS–1042 

F554–70000–000–00 .................. TS–2004 

F554–70000–000–00 .................. TS–2005 

F554–70000–000–00 .................. TS–2008 

F554–70000–000–00 .................. TS–2009 

F554–70000–000–00 .................. TS–2010 

F554–70000–000–00 .................. TS–2022 

F554–70000–000–00 .................. TS–2023 

F554–70000–000–00 .................. TS–2028 

F554–70000–000–00 .................. TS–2029 

F554–70000–000–00 .................. TS–2030 

F554–70000–000–00 .................. TS–2032 

F554–70000–000–00 .................. TS–2033 

F554–70000–000–00 .................. TS–2034 

F554–70000–000–00 .................. TS–2041 

F554–70000–000–00 .................. TS–2044 

F554–70000–000–00 .................. TS–2048 

F554–70000–000–00 .................. TS–2049 

F554–70000–000–00 .................. TS–2050 

F554–70000–000–00 .................. TS–2057 

F554–70000–000–00 .................. TS–2067 

F554–70000–002–00 .................. TS–2068 

F554–70000–002–00 .................. TS–2071 

F554–71000–000–00–0000 ........ TS–3001 

F554–71000–000–00–0000 ........ TS–3010 

F554–71000–000–00–0000 ........ TS–3012 

F554–71000–000–00–0000 ........ TS–3017 

F554–71000–000–00–0000 ........ TS–3018 

F554–71000–000–00–0000 ........ TS–3019 

F554–71000–000–00–0000 ........ TS–3021 

F554–71000–000–00–0000 ........ TS–3024 

F554–71000–000–00–0000 ........ TS–3025 

F554–71000–000–00–0000 ........ TS–3026 

F554–71000–000–00–0000 ........ TS–3028 

F554–71000–000–00–0000 ........ TS–3029 

F554–71000–000–00–0000 ........ TS–3030 

F554–71000–000–00–0000 ........ TS–3032 

F554–71000–000–00–0000 ........ TS–3035 

F554–71000–000–00–0000 ........ TS–3037 

F554–71000–000–00–0000 ........ TS–3039 

F554–71000–000–00–0000 ........ TS–3040 

F554–71000–000–00–0000 ........ TS–3042 

F554–71000–000–00–0000 ........ TS–3047 

F554–71000–000–00–0000 ........ TS–3049 

F554–71000–000–00–0000 ........ TS–3055 

F554–71000–000–00–0000 ........ TS–3058 

F554–71000–000–00–0000 ........ TS–3062 

F554–71000–000–00–0000 ........ TS–3063 

F554–71000–000–00–0000 ........ TS–3065 

F554–71000–000–00–0000 ........ TS–3067 

F554–71000–000–00–0000 ........ TS–3069 

F554–71000–000–00–0000 ........ TS–3070 

F554–71000–000–00–0000 ........ TS–3077 

F554–71000–000–00–0000 ........ TS–3078 

F554–71000–000–00–0000 ........ TS–3080 

F554–71000–000–00–0000 ........ TS–3081 

F554–71000–000–00–0000 ........ TS–3086 

F554–71000–000–00–0000 ........ TS–3089 

F554–71000–000–00–0000 ........ TS–3092 

F554–71000–000–00–0000 ........ TS–3093 

F554–71000–000–00–0000 ........ TS–3095 

F554–71000–000–00–0000 ........ TS–3096 

F554–70005–000–00–0000 ........ TS–3098 

F554–70005–000–00–0000 ........ TS–3099 

F554–70005–000–00–0000 ........ TS–3101 

F554–70005–000–00–0000 ........ TS–3103 

F554–70005–000–00–0000 ........ TS–3104 

F554–70005–000–00–0000 ........ TS–3105 

F554–70005–000–00–0000 ........ TS–3108 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
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TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N—Continued 

Rudder P/N 

Affected 

Rudder 

S/N 

F554–70005–000–00–0000 ........ TS–3109 

F554–70005–000–00–0000 ........ TS–3110 

F554–70005–000–00–0000 ........ TS–3111 

F554–70005–000–00–0000 ........ TS–3112 

F554–70005–000–00–0000 ........ TS–3114 

F554–70005–000–00–0000 ........ TS–3116 

F554–70005–000–00–0000 ........ TS–3117 

F554–70005–000–00–0000 ........ TS–3120 

F554–70005–000–00–0000 ........ TS–3131 

F554–70005–000–00–0000 ........ TS–3132 

F554–70005–000–00–0000 ........ TS–3212 

F554–70005–000–00–0002 ........ TS–3323 

F554–70005–000–00–0002 ........ TS–3330 

F554–71002–000–00–0002 ........ TS–4009 

F554–71002–000–00–0002 ........ TS–4010 

F554–71002–000–00–0002 ........ TS–4012 

F554–71002–000–00–0002 ........ TS–4013 

F554–71002–000–00–0002 ........ TS–4014 

F554–71002–000–00–0002 ........ TS–4015 

F554–71002–000–00–0002 ........ TS–4016 

F554–71002–000–00–0002 ........ TS–4017 

F554–71002–000–00–0002 ........ TS–4020 

F554–71002–000–00–0002 ........ TS–4023 

F554–71002–000–00–0002 ........ TS–4025 

F554–71002–000–00–0002 ........ TS–4026 

F554–71002–000–00–0002 ........ TS–4027 

F554–71002–000–00–0002 ........ TS–4029 

F554–71002–000–00–0002 ........ TS–4030 

F554–71002–000–00–0002 ........ TS–4038 

F554–71002–000–00–0002 ........ TS–4047 

F554–71002–000–00–0002 ........ TS–4049 

F554–71002–000–00–0002 ........ TS–4066 

F554–71002–000–00–0003 ........ TS–4083 

TABLE 3—RUDDER P/N AND

AFFECTED RUDDER S/N 

Rudder P/N 

Affected 

Rudder 

S/N 

F554–71000–000–00–0000 ........ TS–3060 

F554–71000–000–00–0000 ........ TS–3068 

F554–70005–000–00–0000 ........ TS–3128 

F554–71002–000–00–0002 ........ TS–4011 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of * * * [an] in-service aeroplane 

during scheduled maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

* * * * * 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

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. 

Inspections 

(g) For rudders identified in table 1 and 

table 2 of this AD, within the compliance 

time in paragraph (g)(1) or (g)(2) of this AD 

as applicable, do a vacuum loss inspection 

on the rudder non-ventilated area (Area 1) for 

damage including de-bonding between the 

skin and honeycomb core of the rudder, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3042 or A340–55–4038, 

both dated April 22, 2010, as applicable. 

(1) For rudders identified in table 1 of this 

AD: Within 1,800 flight hours after the 

effective date of this AD. 

(2) For rudders identified in table 2 of this 

AD: Within 21 months after the effective date 

of this AD. 

(h) For rudders identified in table 1 and 

table 2 of this AD, within 21 months after the 

effective date of this AD, do an elasticity 

laminate checker inspection on the trailing 

edge area (Area 2) for damage including debonding between the skin and honeycomb 

core of the rudder, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Thereafter, repeat the 

inspection two more times at intervals not to 

exceed 4,500 flight cycles but not less than 

4,000 flight cycles from the most recent 

inspection. 

(i) For rudders identified in table 3 of this 

AD, within 4,500 flight cycles but not less 

than 4,000 flight cycles from the date of the 

sampling inspection identified in table 4 of 

this AD, or within 30 days after the effective 

date of this AD, whichever occurs later, do 

an elasticity laminate checker inspection on 

the trailing edge area for damage including 

de-bonding between the skin and honeycomb 

core of the rudder, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Repeat the inspection once 

within 4,500 flight cycles after doing the 

inspection but not less than 4,000 flight 

cycles from the last inspection. 

TABLE 4—RUDDER P/N AND AFFECTED RUDDER S/N AND SAMPLING INSPECTION DATE

Rudder P/N Affected rudder S/N Date of sampling 

inspection 

F554–71000–000–00–0000 ................................................................................. TS–3060 ............................................... March 12, 2009. 

F554–71000–000–00–0000 ................................................................................. TS–3068 ............................................... April 27, 2009. 

F554–70005–000–00–0000 ................................................................................. TS–3128 ............................................... July 13, 2009. 

F554–71002–000–00–0002 ................................................................................. TS–4011 ............................................... February 12, 2009. 

Corrective Actions 

(j) If damage is found during any 

inspection required by paragraph (g), (h), (i), 

or (k)(1) of this AD, before further flight, 

repair the damage using a method approved 

by either the Manager, International Branch, 

ANM 116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Restoration 

(k) If no damage is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, restore the vacuum 

loss holes by doing a temporary restoration 

with self-adhesive disks or tapes, a temporary 

restoration with resin, or a permanent 

restoration with resin, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Do the applicable actions 

specified in paragraph (k)(1) or (k)(2) of this 

AD. 

(1) For airplanes on which a temporary 

restoration with self-adhesive disks or tapes 

is done, within 900 flight hours after doing 

the restoration, do a detailed inspection for 

loose or missing self-adhesive disks or tapes 

and repeat the inspection thereafter at 

intervals not to exceed 900 flight hours until 

the permanent restoration is done, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3042 or A340–55–4038, 

both dated April 22, 2010, as applicable. If 

any loose or missing self-adhesive disks or 

tapes are found during any inspection 

required by this AD, before further flight, 

close the holes, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Do the permanent restoration 

within 21 months after doing the temporary 

restoration, in accordance with the 

Accomplishment Instructions of Airbus 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
24836 Federal Register / Vol. 76, No. 85 / Tuesday, May 3, 2011 / Proposed Rules 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. 

(2) For airplanes on which a temporary 

restoration with resin is done: Within 21 

months after doing the temporary restoration, 

do the permanent restoration, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–55– 

3042 or A340–55–4038, both dated April 22, 

2010, as applicable. 

Reporting Requirements 

(l) Submit a report of the findings (positive 

and negative) of the first inspection required 

by paragraphs (g), (h), and (i) of this AD to 

Airbus, at the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(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. 

Parts Installation 

(m) As of the effective date of this AD, no 

person may install any affected rudder listed 

in table 1, table, 2, or table 3 of this AD, on 

any airplane, unless the rudder is inspected 

as specified in paragraphs (g), (h), and (i) of 

this AD, as applicable, and all applicable 

corrective actions specified in paragraph (j) 

of this AD and applicable restoration 

specified in paragraph (k) of this AD are 

done. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(n) 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 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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. 

(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. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2010–0127, dated June 23, 2010; 

Airbus Mandatory Service Bulletin A330–55– 

3042, dated April 22, 2010; and Airbus 

Mandatory Service Bulletin A340–55–4038, 

dated April 22, 2010; for related information. 

Issued in Renton, Washington, on April 20, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10624 Filed 5–2–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 460 

Regulatory Approach for Commercial 

Orbital Human Spaceflight 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of public meeting. 

SUMMARY: This notice announces a 

public meeting to solicit comments and 

information from the public on the 

regulatory approach to commercial 

orbital human spaceflight by the FAA. 

This public meeting is intended to aid 

the FAA in its regulatory effort by 

receiving early input from the affected 

community. 

DATES: The meeting is scheduled for 

Thursday, May 26, 2011, starting at 8:30 

a.m. Eastern Daylight Time. Written 

comments submitted to the docket must 

be received no later than June 9, 2011. 

ADDRESSES: DoubleTree by Hilton Hotel 

Cocoa Beach Oceanfront, 2080 North 

Atlantic Avenue, Cocoa Beach, FL 

32931. 

Persons who are unable to attend the 

meeting, or who otherwise wish to 

submit written comments, may send 

comments identified by Docket Number 

FAA–2011–0446 using any of the 

following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

FOR FURTHER INFORMATION CONTACT: 

Randy Repcheck, Deputy Division 

Manager, Regulations and Analysis 

Division, AST–300, Office of 

Commercial Space Transportation, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591, Telephone (202) 

267–8760, or e-mail at 

randy.repcheck@faa.gov; or Laura 

Montgomery, Senior Attorney for 

Commercial Space Transportation, 

Regulations Division, AGC–200, Office 

of the Chief Counsel, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591, 

Telephone (202) 267–3150, or e-mail at 

laura.montgomery@faa.gov. 

SUPPLEMENTARY INFORMATION: 51 U.S.C. 

Subtitle V, chapter 509 (Chapter 509) 

authorizes the Secretary of 

Transportation and, through 

delegations, the FAA’s Associate 

Administrator for Commercial Space 

Transportation, to oversee, license, and 

regulate both launches and reentries, 

and the operation of launch and reentry 

sites when carried out by U.S. citizens 

or within the United States. 51 U.S.C. 

50904, 50905. Chapter 509 directs the 

FAA to exercise this responsibility 

consistent with public health and safety, 

safety of property, and the national 

security and foreign policy interests of 

the United States, and to encourage, 

facilitate, and promote commercial 


emcdonald on DSK2BSOYB1PROD with PROPOSALS