57484 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Rules and Regulations 

basis and do not need to comply with 

the requirements per 14 CFR 121.312, 

c. Airplanes exempted from smoke 

and heat release requirements. 

Definition of ‘‘non-traditional, large, 

nonmetallic panel’’—A non-traditional, 

large, nonmetallic panel, in this case, is 

defined as a panel with exposed surface 

areas greater than 1.5 square feet 

installed per seat place. The panel may 

consist of either a single component or 

multiple components in a concentrated 

area. Examples of parts of the seat where 

these non-traditional areas are installed 

include, but are not limited to, seat 

backs, bottoms and leg/foot rests, kick 

panels, back shells, credenzas, and 

associated furniture. Examples of 

traditional exempted areas are: arm 

caps, armrest close-outs such as end 

bays and armrest-styled center consoles, 

food trays, video monitors and shrouds. 

Clarification of ‘‘exposed’’—Exposed 

is considered to include panels that are 

directly exposed to the passenger cabin 

in the traditional sense, plus those 

panels enveloped, such as by a dress 

cover. Traditional fabrics or leathers 

currently used on seats are excluded 

from these special conditions. These 

materials must still comply with 

§§ 25.853(a) and 25.853(c) if used as a 

covering for a seat cushion, or 

§ 25.853(a) if installed elsewhere on the 

seat. Non-traditional large, nonmetallic 

panels covered with traditional fabrics 

or leathers will be tested without their 

coverings or covering attachments. 

Issued in Renton, Washington, on 

September 11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22831 Filed 9–17–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0671; Directorate 

Identifier 2011–NM–096–AD; Amendment 

39–17197; AD 2012–19–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Airbus Model A330–243, -341, -342 

and -343 airplanes. That AD currently 

requires modifying certain cowl 

assemblies of the left- and right-hand 

thrust reversers. This new AD requires 

removing certain C-duct assemblies of 

the left- and right-hand thrust reversers 

from service at certain designated life 

limits, and also adds airplanes to the 

applicability. This AD was prompted by 

new life limits on certain thrust reverser 

C-duct assemblies. We are issuing this 

AD to prevent fatigue cracking of the 

hinges integrated into the 12 o’clock 

beam of the thrust reversers, which 

could result in separation of a thrust 

reverser from the airplane, and 

consequent reduced controllability of 

the airplane. 

DATES: This AD becomes effective 

October 23, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 25, 2012 (77 FR 37829), 

and proposed to supersede AD 2005– 

25–21, Amendment 39–14414 (70 FR 

73919, December 14, 2005). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The life limits of the thrust reversers CDucts are not addressed by the definition of 

the structural life limits of Safe Life items as 

defined in the A330 Airworthiness 

Limitations Section—ALS Part 1. As a result, 

these life limits are covered by an 

Airworthiness Directive (AD). 

These life limits are due to unexpected 

high fatigue loads (measured during 

certification tests) on the hinges integrated 

into the 12 o’clock beam, which forms the 

upper extreme edge of the thrust reverser CDuct of Rolls Royce Trent 700 engines. 

The aim of the [Direction Ge ́ne ́rale de 

l’Aviation Civile] (DGAC) France AD F– 

2001–528 was to mandate the life limits, 

depending of the modifications applied to 

the C-Duct. 

Revision 1 of the DGAC France AD F– 

2001–528 deferred the accomplishment 

threshold of the modification to be applied 

in-service from 6,000 flight cycles (FC) to 

6,500 FC. 

Revision 2 of DGAC France AD F–2001– 

528 [which corresponds to FAA AD 2005– 

25–21, Amendment 39–14414 (70 FR 73919, 

December 14, 2005)] was issued to update 

again the accomplishment threshold from 

6,500 FC to 7,200 FC. 

This [European Aviation Safety Agency 

(EASA)] AD retains the requirements of 

DGAC France AD F–2001–528 R2, which is 

superseded, and adds [certain] life limits. 

The action required in this AD is 

removing certain C-duct assemblies of 

the left- and right-hand thrust reversers 

from service at certain designated life 

limits. This AD also adds Model A330– 

243F airplanes to the applicability, and 

revises the applicability to include all 

airplanes of the affected models. The 

unsafe condition is fatigue cracking of 

the hinges integrated into the 12 o’clock 

beam of the thrust reversers, which 

could result in separation of a thrust 

reverser from the airplane, and 

consequent reduced controllability of 

the airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR, 37829, June 25, 2012), or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

37829, June 25, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 37829, 

June 25, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 17 products of U.S. registry. 

We estimate that it will take about 48 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $69,360, or $4,080 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, 

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Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Rules and Regulations 57485 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 the NPRM (77 FR 37829, June 

25, 2012), 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2005–25–21, Amendment 39–14414 (70 

FR 73919, December 14, 2005), and 

adding the following new AD: 

2012–19–02 Airbus: Amendment 39–17197. 

Docket No. FAA–2012–0671; Directorate 

Identifier 2011–NM–096–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 23, 2012. 

(b) Affected ADs 

This AD supersedes AD 2005–25–21, 

Amendment 39–14414 (70 FR 73919, 

December 14, 2005). 

(c) Applicability 

This AD applies to all Airbus Model A330– 

243, –243F, –341, –342 and –343 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Reason 

This AD was prompted by new life limits 

on certain thrust reverser C-duct assemblies. 

We are issuing this AD to prevent fatigue 

cracking of the hinges integrated into the 12 

o’clock beam of the thrust reversers, which 

could result in separation of a thrust reverser 

from the airplane, and consequent reduced 

controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) C-duct Assembly Removal 

At the applicable compliance time 

specified in table 1 to paragraph (g) of this 

AD: Remove the applicable C-duct 

assemblies of the left- and right-hand thrust 

reversers, in accordance with 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). Thereafter, for any C-duct 

assembly of the left- and right-hand thrust 

reversers installed after the effective date of 

this AD, before the accumulation of the 

applicable total flight cycles specified in 

table 1 to paragraph (g) of this AD: Remove 

the C-duct assembly, in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

TABLE 1 TO PARAGRAPH (G) OF THIS AD—PART REMOVAL THRESHOLDS

Part No.— Compliance times at the later of the times specified— 

HDTR3410L, HDTR3410R, HDTR3411L, 

HDTR3411R, HDTR3412R, HDTR3413R.

Before the accumulation of 10,000 total flight 

cycles since the first installation of C-duct 

on the airplane.

Within 3 months after the effective date of this 

AD. 

HDTR3414L, HDTR3416R, HDTR3417R that 

have been modified in service as specified in 

Airbus Mandatory Service Bulletin 

A330-78-3010 or Rolls-Royce Service Bulletin RB.211–78–C899 at 7,200 total flight cycles or more since first installation on an airplane.

Before the accumulation of 10,000 total flight 

cycles since the first installation of C-duct 

on the airplane.

Within 3 months after the effective date of this 

AD. 

HDTR3414L, HDTR3416R, HDTR3417R that 

have been modified in production by Airbus 

Modification 47316 or that have been modified in service as specified in Airbus Mandatory Service Bulletin A330-78-3010 or RollsRoyce Service Bulletin RB.211–78–C899, before the accumulation of 7,200 total flight cycles since first installation on an airplane.

Before the accumulation of 25,000 total flight 

cycles since the first installation of C-duct 

on the airplane.

Within 3 months after the effective date of this 

AD. 

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57486 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (G) OF THIS AD—PART REMOVAL THRESHOLDS—Continued 

HDTR3412L, HDTR3416L, HDTR3417L, 

HDTR3414R, HDTR3419R, HDTR3420R.

Before the accumulation of 25,000 total flight 

cycles since the first installation of C-duct 

on the airplane.

Within 3 months after the effective date of this 

AD. 

HDTR3413L, HDTR3415R, HDTR3415L, 

HDTR3418R.

Before the accumulation of 40,000 total flight 

cycles since the C-duct was new.

Within 3 months after the effective date of this 

AD. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, WA 98057–3356; 

telephone (425) 227–1138; 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) 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. 

(i) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0018, dated February 3, 2011; 

for related information. 

(j) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on 

September 6, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22954 Filed 9–17–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Office of the Secretary 

32 CFR Part 233 

[DOD–2008–OS–0049] 

RIN 0790–AI27 

Federal Voting Assistance Program 

AGENCY: Office of the Under Secretary of 

Defense for Personnel and Readiness/ 

Federal Voting Assistance Program, 

DoD. 

ACTION: Interim final rule 

SUMMARY: This rule concerns the 

Federal Voting Assistance Program 

(FVAP). It provides direction and 

guidance to the Department of Defense 

and other Federal departments and 

agencies in establishing voting 

assistance programs for citizens covered 

by the Uniformed and Overseas Citizens 

Absentee Voting Act (UOCAVA) as 

modified by the Military and Overseas 

Voter Empowerment Act. The 2012 

election cycle starts with the January 10, 

2012 New Hampshire Presidential 

Preference Primary and continues 

through the November 6, 2012 General 

Election. This 2012 election schedule 

requires that the policies and 

procedures set forth in the rule must be 

in place to ensure that citizens voting 

under UOCAVA are fully guided and 

supported through established voting 

assistance programs within the Federal 

departments and agencies. Therefore, 

this rule is being established as an 

interim final rule to allow promulgation 

of appropriate direction and guidance 

prior to completion of a public comment 

period. 

DATES: Effective date: September 18, 

2012. 

Comment date: Comments must be 

received by November 19, 2012. 

ADDRESSES: You may submit comments, 

identified by docket number and or 

Regulatory Information Number (RIN) 

number and title, by any of the 

following methods: 

• Federal Rulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Federal Docket Management 

System Office, 4800 Mark Center Drive, 

2nd floor, East Tower, Suite 02G09, 

Alexandria, VA 22350–3100. 

Instructions: All submissions received 

must include the agency name and 

docket number or RIN for this Federal 

Register document. The general policy 

for comments and other submissions 

from members of the public is to make 

these submissions available for public 

viewing on the Internet at http:// 

www.regulations.gov as they are 

received without change, including any 

personal identifiers or contact 

information. 

FOR FURTHER INFORMATION CONTACT: John 

B. Godley, (703) 588–8108. 

SUPPLEMENTARY INFORMATION: 

Background 

Part 233 establishes policy and 

assigns responsibilities for the Federal 

Voting Assistance Program. It 

establishes policy and assigns 

responsibilities for the development and 

implementation of installation voter 

assistance (IVA) offices. This part 

establishes policy for the development 

and implementation, jointly with each 

State, of procedures for persons to apply 

to register to vote at recruitment offices 

of the Military Services. 

Executive Order 12866, ‘‘Regulatory 

Planning and Review’’ and Executive 

Order 13563, ‘‘Improving Regulation 

and Regulatory Review’’ 

It has been certified that 32 CFR part 

233 does not: 

(1) Have an annual effect on the 

economy of $100 million or more or 

adversely affect in a material way the 

economy; a section of the economy; 

productivity; competition; jobs; the 

environment; public health or safety; or 

State, local, or tribal governments or 

communities; 

(2) Create a serious inconsistency or 

otherwise interfere with an action taken 

or planned by another Agency; 

(3) Materially alter the budgetary 

impact of entitlements, grants, user fees, 

or loan programs, or the rights and 

obligations of recipients thereof; or 

(4) Raise novel legal or policy issues 

arising out of legal mandates, the 

President’s priorities, or the principles 

set forth in these Executive Orders. 

Sec. 202, Public Law 104–4, ‘‘Unfunded 

Mandates Reform Act’’ 

It has been certified that 32 CFR part 

233 does not contain a Federal mandate 

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