42610 Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

In June of 1971, the FAA Engine & 

Propeller Directorate issued AD 71–13– 

01. That AD requires a one-time visual 

inspection of external fuel injector lines 

on Lycoming Engines model TIO 540– 

A series reciprocating engines for fuel 

stains, cracks, dents, and bend radii 

under 5⁄8 inch and, if necessary, removal 

from service and replacement with 

serviceable parts. That AD also requires 

installing if necessary, fuel injector line 

support clamps in accordance with 

Lycoming Engines SB No. 335 or later 

version of that SB. 

Since we issued AD 71–13–01, 

Lycoming Engines has informed us that 

it no longer supports SB No. 335A. They 

also pointed out that Lycoming Engines 

Mandatory SB No. 342F, dated June 4, 

2010, or the Instructions for Continued 

Airworthiness section of the Engine 

Overhaul Manual is the service 

information the owners, operators, and 

certificated repair facilities must use for 

initial and repetitive visual inspections 

of external fuel lines, on all affected 

Lycoming Engines reciprocating 

engines. 

We incorporated by reference 

Lycoming Engines Mandatory SB No. 

342E, dated May 18, 2004, in AD 2008– 

14–07 (73 FR 39574, July 10, 2008). We 

are in the process of issuing a 

supersedure to that AD, which will 

incorporate by reference Lycoming 

Engines Mandatory SB No. 342F, dated 

June 4, 2010. 

FAA’s Determination and Requirements 

of This Proposed AD Rescission 

We are proposing this AD rescission 

of AD 71–13–01 because we evaluated 

all information and determined that the 

requirements of that AD are no longer 

supported by Lycoming Engines SB No. 

335A, but are supported by Mandatory 

SB No. 342E, Mandatory SB 342F, and 

the Instructions for Continued 

Airworthiness section of the Engine 

Overhaul Manual. 

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 

rescission would not have federalism 

implications under Executive Order 

13132. This proposed AD rescission 

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 rescission of a 

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 rescission and placed 

it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 

rescinding airworthiness directive (AD) 

71–13–01, Amendment 39–1231: 

Lycoming Engines (formerly Textron 

Lycoming Division, AVCO Corporation): 

Docket No. FAA–2011–0691; Directorate 

Identifier 2011–NE–26–AD. 

(a) Comments Due Date 

We must receive comments by September 

2, 2011. 

(b) Affected ADs 

This AD rescinds AD 71–13–01. 

(c) Applicability 

This AD applies to Lycoming Engines 

model TIO 540–A series reciprocating 

engines, with serial numbers lower than 

1931–61. 

Issued in Burlington, Massachusetts, on 

July 13, 2011. 

Colleen M. D’Alessandro, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–18170 Filed 7–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0710; Directorate 

Identifier 2010–NE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 1 Series Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

The existing AD currently requires 

removing from service certain gas 

generator second stage turbine discs, 

part number (P/N) 0 292 25 040 0, that 

are not marked with ‘‘CFR’’ before the 

discs exceed 2,500 cycles-in-service 

(CIS) since-new or within 20 CIS from 

the effective date of the AD, whichever 

occurs later. That AD also requires 

removing from service certain gas 

generator second stage turbine discs, 

P/N 0 292 25 040 0, that are marked 

with ‘‘CFR’’ before the discs exceed 

3,500 CIS since-new. Since we issued 

that AD, Turbomeca has restored all or 

part of the life limits of the affected 

discs, and the European Aviation Safety 

Agency (EASA) issued AD 2010– 

0101R2, dated March 24, 2011 to do the 

same. This proposed AD would still 

prevent disc failure but extends the life 

limits of the affected discs. We are 

proposing this AD to prevent failure of 

the gas generator second stage turbine 

disc which could result in the release of 

high energy debris and damage to the 

helicopter. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules 42611 

DATES: We must receive comments on 

this proposed AD by September 2, 2011. 

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: 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 AD, contact Turbomeca, 40220 

Tarnos, France; phone: 33 05 59 74 40 

00, fax: 33 05 59 74 45 15. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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: Rose 

Len, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7772; fax: 781– 

238–7199; e-mail: rose.len@faa.gov. 

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–2010–0710; Directorate Identifier 

2010–NE–26–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 

On September 10, 2010, we issued AD 

2010–19–06, Amendment 39–16434 (75 

FR 57371, September 21, 2010), for 

Turbomeca Arriel 1 series turboshaft 

engines. That AD requires removing 

from service gas generator second stage 

turbine discs, P/N 0 292 25 040 0 that 

do not have the ‘‘CFR’’ marking, before 

exceeding 2,500 CIS since-new or 

within 20 CIS from the effective date of 

the AD, whichever occurs later. That AD 

also requires removing from service gas 

generator second stage turbine discs, P/ 

N 0 292 25 040 0 that have the ‘‘CFR’’ 

marking, before exceeding 3,500 CIS 

since-new. Discs that have the ‘‘CFR’’ 

marking have been inspected using a 

‘‘reinforced’’ eddy-current inspection 

(ECI). Discs that do not have the ‘‘CFR’’ 

marking have not been inspected using 

the ‘‘reinforced’’ ECI. Based on the 

‘‘reinforced’’ ECI and additional 

analysis finding performed by 

Turbomeca, the discs with the ‘‘CFR’’ 

marking are compliant with their 

original published life limit of 6,500 CIS 

since-new, and the life limit of discs 

with no ‘‘CFR’’ marking can be 

increased to 4,000 CIS since-new. AD 

2010–19–06 resulted from Mandatory 

Continuing Airworthiness Information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. We issued that AD to 

prevent failure of the gas generator 

second stage turbine disc which could 

result in the release of high energy 

debris and damage to the helicopter. 

Actions Since Existing AD Was Issued 

Since we issued AD 2010–19–06, 

Turbomeca has restored all or part of the 

life limits of the affected discs, based on 

the reinforced eddy current inspection 

that provides an improved detection 

threshold of any metallurgical nonconformities in the discs, in 

combination with additional testing and 

analysis. 

Also since we issued AD 2010–19–06, 

EASA has issued MCAI AD 2010– 

0101R2, dated March 24, 2011, which, 

for gas generator second stage turbine 

discs, P/N 0 292 25 040 0 that do not 

have the ‘‘CFR’’ marking, increases the 

life limit to 4,000 cycles, and for gas 

generator second stage turbine discs, 

P/N 0 292 25 040 0 that have the ‘‘CFR’’ 

marking, returns the life limit to the 

original published life limit of 6,500 

cycles. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

removing gas generator second stage 

turbine discs, P/N 0 292 25 040 0 that 

do not have the ‘‘CFR’’ marking, from 

service before exceeding 4,000 CIS 

since-new. This proposed AD would 

also require removing gas generator 

second stage turbine discs, P/N 0 292 25 

040 0 that have the ‘‘CFR’’ marking, 

from service before exceeding 6,500 CIS 

since-new. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 203 Turbomeca Arriel 1 

series turboshaft engines on helicopters 

of U.S. registry. We estimate that no 

additional labor costs would be incurred 

to return part of the life limit of the 

discs that do not have the ‘‘CFR’’ 

marking, to the original published life 

limit. Based on these figures, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $0. 

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 have 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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
42612 Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules 

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 the 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, 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 

removing airworthiness directive (AD) 

2010–19–06, Amendment 39–16434 (75 

FR 57371 September 21, 2010), and 

adding the following new AD: 

Turbomeca: Docket No. FAA–2010–0710; 

Directorate Identifier 2010–NE–26–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by September 2, 2011. 

(b) Affected ADs 

This AD revises AD 2010–19–06, 

Amendment 39–16434. 

(c) Applicability 

This AD applies to Turbomeca Arriel 1A, 

1A1, 1B, 1C, 1C1, 1C2, 1D, 1D1, and 1S1 

turboshaft engines that have incorporated 

Modification TU347. 

(d) Unsafe Condition 

This AD was prompted by Turbomeca 

restoring all or part of the life limits of the 

affected discs. We are issuing this AD to 

prevent failure of the gas generator second 

stage turbine disc which could result in the 

release of high energy debris and damage to 

the helicopter. 

(e) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) Remove from service gas generator 

second stage turbine discs, part number (P/ 

N) 0 292 25 040 0 that do not have the ‘‘CFR’’ 

marking, before exceeding 4,000 cycles-inservice (CIS) since-new. 

(3) Remove from service gas generator 

second stage turbine discs, P/N 0 292 25 040 

0 that have the ‘‘CFR’’ marking, before 

exceeding 6,500 CIS since-new. 

(4) Gas Generator Second Stage Turbine 

Installation Prohibition 

(i) After the effective date of this AD, do 

not install into any engine gas generator 

second stage turbine discs, P/N 0 292 25 040 

0 that do not have the ‘‘CFR’’ marking, and 

have 4,000 or more CIS since-new. 

(ii) After the effective date of this AD, do 

not install into any engine gas generator 

second stage turbine discs, P/N 0 292 25 040 

0 that have the ‘‘CFR’’ marking, and have 

6,500 or more CIS since-new. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. 

(g) Related Information 

(1) Refer to Turbomeca Alert Mandatory 

Service Bulletin No. A292 72 0831, Version 

C, dated March 3, 2011, for related 

information. Contact Turbomeca, 40220 

Tarnos, France; phone: 33 05 59 74 40 00, 

fax: 33 05 59 74 45 15, for a copy of this 

service information. 

(2) You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(3) For more information about this AD, 

contact Rose Len, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7772; fax: 781–238– 

7199; e-mail: rose.len@faa.gov. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

July 13, 2011. 

Colleen M. D’Alessandro, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–18171 Filed 7–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R01–OAR–2008–0905 ; A–1–FRL– 

9439–6] 

Approval and Promulgation of Air 

Quality Implementation Plans; 

Vermont; Reasonably Available 

Control Technology (RACT) for the 

1997 8-Hour Ozone Standard 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: EPA is proposing to approve 

State Implementation Plan (SIP) 

revisions submitted by the State of 

Vermont (VT) on November 22, 2006, 

and November 14, 2008. These SIP 

revisions consist of a demonstration that 

VT meets the requirements of 

reasonably available control technology 

(RACT) for oxides of nitrogen (NOX) and 

volatile organic compounds (VOCs) set 

forth by the Clean Air Act (CAA) with 

respect to the 1997 8-hour ozone 

standard; minor revisions to Vermont’s 

bulk gasoline plants regulation; and new 

requirements for wood furniture 

manufacturing operations. Additionally, 

EPA is proposing to approve VT’s 

negative declarations for several 

categories of VOC sources. EPA is 

proposing full approval all of the 

submitted items, with two exceptions. 

EPA is proposing a conditional approval 

of the RACT determinations for two 

major VOC sources (Churchill Coatings 

Corporation and H.B.H Prestain). This 

action is being taken in accordance with 

the CAA. 

DATES: Written comments must be 

received on or before August 18, 2011. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R01– 

OAR–2008–0905 by one of the following 

methods: 

1. http://www.regulations.gov: Follow 

the on-line instructions for submitting 

comments. 

2. E-mail: arnold.anne@epa.gov. 

3. Fax: (617) 918–0047. 

4. Mail: ‘‘EPA–R01–OAR–2008– 

0905’’, Anne Arnold, U.S. 

Environmental Protection Agency, EPA 

New England Regional Office, 5 Post 

Office Square, Suite 100 (mail code: 

OEP05–2), Boston, MA 02109–3912. 

5. Hand Delivery or Courier. Deliver 

your comments to: Anne Arnold, 

Manager, Air Quality Planning Unit, 

Office of Ecosystem Protection, U.S. 

Environmental Protection Agency, EPA 

New England Regional Office, 5 Post 

Office Square, 5th Floor, Boston, MA 

02109–3912. Such deliveries are only 


srobinson on DSK4SPTVN1PROD with PROPOSALS