Federal Register / Vol. 72, No. 10 / Wednesday, January 17, 2007 / Proposed Rules 1947 

performed at the time of scheduled 

engine overhaul. The financial burden 

to the operators (prorate) is about 

$140,080 per engine due to the 

reduction in the life limit. Based on 

these figures, and on the prorating for 

the usage of the combustor cases, we 

estimate the cost of the proposed AD on 

U.S. operators to be $5,886,720. 

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 

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); and 

3. Would 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. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

General Electric Company: Docket No. FAA–

2006–26585; Directorate Identifier 2006–

NE–44–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by March 

19, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF34–10E2A1, CF34–10E5, 

CF34–10E5A1, CF34–10E6, CF34–10E6A1, 

and CF34–10E7 turbofan engines. These 

engines are installed on, but not limited to, 

Embraer ERJ–190 and –195 airplanes. 

Unsafe Condition 

(d) This AD results from GE’s evaluation of 

the effects to the combustor case due to 

installing version 5.10 software in the fullauthority digital electronic control (FADEC), 

and revising the combustor case published 

life limit. We are issuing this AD to prevent 

uncontained combustor case failure resulting 

in an in-flight engine shutdown and possible 

damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

30 days after the effective date of this AD, 

unless the actions have already been done. 

(f) Revise the published life limit in the 

Airworthiness Limitations Section of the 

CF34–10E Engine Manual, for combustor 

cases, part number (P/N) 2070M47G02 and 

P/N 2070M47G03, from 39,600 cycles-sincenew (CSN) to 24,600 CSN. 

(g) Remove from service combustor cases, 

P/N 2070M47G02 and P/N 2070M47G03, 

before reaching 24,600 CSN. 

(h) The requirements of this AD have been 

met when the engine manual changes are 

made and operators have modified their 

continuous airworthiness maintenance plans 

to reflect the Engine Maintenance Program 

requirements specified in the GE CF34–10E 

Engine Manual. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) Contact Tara Chaidez, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7773, fax (781) 

238–7199; e-mail: tara.chaidez@faa.gov for 

more information about this AD. 

Issued in Burlington, Massachusetts, on 

January 10, 2007. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–499 Filed 1–16–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

RIN 2120–AA64 

[Docket No. FAA–2005–22430; Directorate 

Identifier 2005–NE–34–AD] 

Airworthiness Directives; Turbomeca 

Arrius 2 F Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for Turbomeca Arrius 2 F 

turboshaft engines. That AD currently 

requires removing from service certain 

serial number (SN) fuel control units 

(FCUs) or replacing the constant delta 

pressure diaphragm in those FCUs. This 

proposed AD would require replacing 

all FCUs not incorporating modification 

Tf 55 with FCUs that incorporate 

modification Tf 55. This proposed AD 

results from the European Aviation 

Safety Agency (EASA) and Turbomeca 

expanding the applicability to the full 

population of FCUs installed on Arrius 

2 F turboshaft engines. FCUs not 

incorporating modification Tf 55 are 

susceptible to having an improperly 

assembled constant delta pressure (delta 

P) diaphragm. We are proposing this AD 

to prevent an uncommanded engine inflight shutdown on a single-engine 

helicopter, resulting in a forced 

autorotation landing or an accident. 

DATES: We must receive any comments 

on this proposed AD by March 19, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

mstockstill on PROD1PC61 with PROPOSALS

1948 Federal Register / Vol. 72, No. 10 / Wednesday, January 17, 2007 / Proposed Rules 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Turbomeca, 40220 Tarnos, 

France; telephone +33 05 59 74 40 00, 

fax +33 05 59 74 45 15, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 

238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22430; Directorate Identifier 

2005–NE–34–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the DMS 

Web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the 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) or you may visit http:// 

dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the proposal, any comments 

received and any final disposition in 

person at the DMS Docket Office 

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

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647–

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Discussion 

On September 9, 2005, the FAA 

issued AD 2005–19–10, Amendment 

39–14275 (70 FR 54622, September 16, 

2005). That AD requires removing from 

service certain SN FCUs or replacing the 

constant delta P diaphragm in those 

FCUs. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, notified us that 

an unsafe condition may exist on 

Turbomeca Arrius 2 F turboshaft 

engines. EASA advises that the Arrius 2 

F engine fleet is susceptible to having an 

improperly assembled constant delta 

pressure (delta P) diaphragm (premodification Tf 55) in the FCU. 

Actions Since AD 2005–19–10 Was 

Issued 

Since AD 2005–19–10 was issued, 

EASA issued AD No. 2006–0237, dated 

August 9, 2006, which expands the 

applicability to the full population of 

FCUs installed on Arrius 2 F turboshaft 

engines that have not incorporated 

modification Tf 55. Also, Turbomeca 

issued Mandatory Service Bulletin No. 

319 73 4055, Update No. 1, dated March 

17, 2006, to introduce modification Tf 

55 to all Arrius 2 F FCUs. Modification 

Tf 55 upgrades the FCU with a constant 

delta P diaphragm that cannot be 

improperly assembled. 

Bilateral Agreement Information 

This engine model is manufactured in 

France and is type certificated for 

operation in the United States under the 

provisions of Section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Under this 

bilateral airworthiness agreement, EASA 

kept us informed of the situation 

described above. We have examined the 

findings of EASA, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require replacing FCUs 

that do not incorporate modification Tf 

55, with FCUs that do. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 46 Arrius 2 F turboshaft 

engines installed on helicopters of U.S. 

registry. We also estimate that it would 

take about 3 work-hours per engine to 

perform the proposed FCU replacement 

and that the average labor rate is $80 per 

work-hour. Required parts would cost 

about $25,480 per engine. Based on 

these figures, we estimate the total cost 

of the proposed AD to U.S. operators to 

be $1,183,120. 

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 

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); and 

mstockstill on PROD1PC61 with PROPOSALS

Federal Register / Vol. 72, No. 10 / Wednesday, January 17, 2007 / Proposed Rules 1949 

3. Would 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. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

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 Federal Aviation Administration 

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 Amendment 39–14275 (70 FR 

54622, September 16, 2005) and by 

adding a new airworthiness directive, to 

read as follows: 

Turbomeca: Docket No. FAA–2005–22430; 

Directorate Identifier 2005–NE–34–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by March 

19, 2007. 

Affected ADs 

(b) This AD supersedes AD 2005–19–10, 

Amendment 39–14275. 

Applicability 

(c) This AD applies to Turbomeca Arrius 

2 F turboshaft engines with fuel control units 

(FCUs) not incorporating modification Tf 55. 

These engines are installed on, but not 

limited to, Eurocopter EC120B helicopters. 

Unsafe Condition 

(d) This AD results from the European 

Aviation Safety Agency (EASA) and 

Turbomeca expanding the applicability to the 

full population of FCUs installed on Arrius 

2 F turboshaft engines. FCUs not 

incorporating modification Tf 55 are 

susceptible to having an improperly 

assembled constant delta pressure (delta P) 

diaphragm. We are issuing this AD to prevent 

an uncommanded engine in-flight shutdown 

on a single-engine helicopter, resulting in a 

forced autorotation landing or an accident. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed as 

soon as practicable after the effective date of 

this AD but no later than July 31, 2007, 

unless the actions have already been done. 

(f) Replace all FCUs not incorporating 

modification Tf 55 with FCUs that 

incorporate modification Tf 55. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(h) Contact Christopher Spinney, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine and Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 238–

7175, fax (781) 238–7199; e-mail: 

christopher.spinney@faa.gov for more 

information about this AD. 

(i) EASA AD No. 2006–0237, dated August 

9, 2006, addresses the subject of this AD. 

(j) Turbomeca Mandatory Service Bulletin, 

Update No. 1, dated March 17, 2006, pertains 

to the subject of this AD. 

Issued in Burlington, Massachusetts, on 

January 10, 2007. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–494 Filed 1–16–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

RIN 2120–AA64 

[Docket No. FAA–2006–25896; Directorate 

Identifier 2006–NE–33–AD] 

Airworthiness Directives; General 

Electric Company CF34–10E Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for General Electric 

Company (GE) CF34–10E series turbofan 

engines. That AD currently requires 

removing the fuel inlet strainer from 

main fuel pump (MFP) part number 

(P/N) 2043M12P03, installing a certain 

replacement flange as an interim repair, 

remarking the MFP to P/N 2043M12P04, 

and performing initial and repetitive 

visual inspections of the main fuel filter. 

This proposed AD would require 

removing MFPs, P/N 2043M12P03 and 

2043M12P04 from service and installing 

an improved MFP with a different P/N. 

This proposed AD results from GE 

determining that the cause of MFP fuel 

strainer failure is a design problem with 

the strainer. We are proposing this AD 

to prevent engine in-flight shutdown 

due to MFP malfunctions. 

DATES: We must receive any comments 

on this proposed AD by March 19, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact General Electric Company via 

Lockheed Martin Technology Services, 

10525 Chester Road, Suite C, Cincinnati, 

Ohio 45215, telephone (513) 672–8400, 

fax (513) 672–8422, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Tara 

Fitzgerald, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone: (781) 238–7130, fax: (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2006–25896; Directorate Identifier 

2006–NE–33–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

mstockstill on PROD1PC61 with PROPOSALS