Federal Register / Vol. 74, No. 73 / Friday, April 17, 2009 / Proposed Rules 17797 

TABLE 1—COMPLIANCE TIMES—Continued 

If the gearbox accumulated time-since-new on the effective date of this 

AD is: Then: 

Repetitive Replacements 

(iii) After completing (i) or (ii) above ......................................................... Replace the propeller control valve at intervals not to exceed 300 FH. 

(2) If the engine is not installed with 

propeller control valve, P/N NM–0000– 

0124501, no action is required. 

Alternative Methods of Compliance 

(AMOCs) 

(f) 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. 

Related Information 

(g) Refer to MCAI EASA Airworthiness 

Directive 2008–0145, dated August 1, 2008. 

(h) Refer to Thielert Service Bulletin TM 

TAE 125–0018, dated June 19, 2008 (TAE 

125–01), and Thielert Service Bulletin TM 

TAE 125–1007 P1, dated July 11, 2008 (TAE 

125–02–99) for related information. 

(i) Contact Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, telephone: +49–37204–696–0; fax: 

+49–37204–696–55; e-mail: info@centurionengines.com, for a copy of this service 

information. 

(j) Contact Jason Yang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: jason.yang@faa.gov; telephone (781) 

238–7747; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

April 13, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8785 Filed 4–16–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0348; Directorate 

Identifier 2008–NE–39–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. ARRIUS 1A Turboshaft Engines 

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) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

We are proposing this AD to prevent 

failure of the balancing piston, which 

could result in an engine in-flightshutdown and the release of high-energy 

debris and damage to the helicopter. 

DATES: We must receive comments on 

this proposed AD by May 18, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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 the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

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–2009–0348; Directorate Identifier 

2008–NE–39–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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, 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). 

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 2008–0133, 

dated July 17, 2008, [(referred to after 

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

condition for the specified products]. 

The MCAI states: 

Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

As of the publication date of this 

Airworthiness Directive, no ARRIUS 1A 

engines in service are fitted with a balancing 

piston that has logged more than 16 000 

cycles, and the outlook for the consumption 


dwashington3 on PROD1PC60 with PROPOSALS
17798 Federal Register / Vol. 74, No. 73 / Friday, April 17, 2009 / Proposed Rules 

of cycles on the ARRIUS 1A fleet indicates 

that no balancing pistons will exceed this 

new limit for a few years’ time. 

Moreover, this new cycle life limit value 

for the balancing piston has been 

incorporated since the end of 2007 in 

ARRIUS 1A Maintenance documentation. 

Failure to comply with the new life limits 

provided in the Airworthiness Limitations 

Section of ARRIUS 1A Maintenance 

documentation could potentially result in an 

engine in-flight-shutdown and the release of 

high energy debris. 

You may obtain further information by 

examining the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of France, and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, they have 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

proposing this AD because we evaluated 

all information provided by EASA and 

determined the 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 

The MCAI requires modifying the 

cyclic life limit value of the balancing 

piston in the engine log book as 

specified in Turbomeca Mandatory 

Service Bulletin 319 72 0811, dated 

April 30, 2008, and updating the 

approved operator’s maintenance 

program. 

We are requiring removing the 

balancing piston, P/N 0 319 20 152 0, 

before it meets or exceeds the new, 

reduced cyclic life limit value of 16,000 

cycles-since-new. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 33 products of U.S. registry. 

We also estimate that it would take 

about 0.5 work-hour per product to 

comply with this proposed AD. The 

average labor rate is $80 per work-hour. 

Required parts would cost about $5,280 

per product. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $175,560. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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, 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: 

Turbomeca S.A.: Docket No. FAA–2009– 

0348; Directorate Identifier 2008–NE– 

39–AD. 

Comments Due Date 

(a) We must receive comments by May 18, 

2009. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca S.A. 

ARRIUS 1A turboshaft engines with 

balancing pistons, part number (P/N) 0 319 

20 152 0, installed. These engines are 

installed on, but not limited to, Eurocopter 

AS355N helicopters. 

Reason 

(d) Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

We are issuing this AD to prevent failure 

of the balancing piston, which could result 

in an engine in-flight-shutdown and the 

release of high-energy debris and damage to 

the helicopter. 

Actions and Compliance 

(e) Unless already done, for ARRIUS 1A 

engines with a balancing piston, P/N 0 319 

20 152 0, installed, remove the engine from 

service before the balancing piston 

accumulates 16,000 cycles-since-new (CSN). 

Installation Prohibition 

(f) After the effective date of this AD, don’t 

return to service any engine that has a 

balancing piston that has accumulated 16,000 

or more CSN. 

FAA AD Differences 

(g) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) or service information as follows: 

(1) This AD requires removing from 

service, any ARRIUS 1A engine that has a 

balancing piston, P/N 0 319 20 152 0, with 

16,000 CSN installed. 

(2) We prohibit returning to service 

ARRIUS 1A engine that has a balancing 

piston, P/N 0 319 20 152 0, with 16,000 or 

more CSN. 

Other FAA AD Provisions 

(h) 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. 

Related Information 

(i) Refer to MCAI Airworthiness Directive 

2008–0133, dated July 17, 2008 for related 

information. 

(j) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 


dwashington3 on PROD1PC60 with PROPOSALS
Federal Register / Vol. 74, No. 73 / Friday, April 17, 2009 / Proposed Rules 17799 

Issued in Burlington, Massachusetts, on 

April 9, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8786 Filed 4–16–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27687; Directorate 

Identifier 2000–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental Notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: This notice revises an earlier 

proposed airworthiness directive (AD), 

and supersedes an existing AD 

applicable to General Electric Company 

(GE) CF34–1A, –3A, –3A1, –3A2, –3B, 

and –3B1 turbofan engines. This 

proposed AD reopens the comment 

period, since we added additional 

requirements based on responses we 

received. This proposed AD would now 

require: 

• Inspecting certain fan disks for 

electrical arc-out indications, 

• Removing from service fan disks 

with electrical arc-out indications, 

• Performing tactile and enhanced 

visual (TEV) inspections, fluorescent 

penetrant inspections (FPI), and eddy 

current inspections (ECI) on certain 

disks that have already had a shop-level 

inspection, and 

• Repetitive FPI and ECI on certain 

fan disks. 

This proposed AD results from an 

updated risk analysis by GE that shows 

we need to take corrective action that is 

more stringent. We are proposing this 

AD to prevent an uncontained failure of 

the fan disk, which could result in 

damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by June 16, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2007–27687; Directorate Identifier 

2000–NE–42–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:// 

www.regulations.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 Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, 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). 

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 the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

Discussion 

We proposed to amend 14 CFR part 

39 by superseding AD 2007–07–07R1, 

Amendment 39–15179 (72 FR 49183, 

August 28, 2007). That AD requires a 

onetime inspection of certain fan disks 

for electrical arc-out indications, 

replacing fan disks with electrical arcout indications, and reducing the life 

limit of certain fan disks. That NPRM 

was prompted by us determining that 

we inadvertently left out an inspection 

requirement in Table C of AD 2007–07– 

07R1 to perform a shop inspection on 

disks that have greater than 6,000 flight 

hours and have already undergone a 

shop inspection. That condition, if not 

corrected, could result in an 

uncontained fan disk failure and 

airplane damage. On January 18, 2008, 

we published that proposal as an NPRM 

in the Federal Register (73 FR 3425). 

That NPRM would have required: 

• Replacing certain fan disks installed 

on regional jets within 15 days after the 

effective date of the proposed AD, and 

• On-wing and shop-level inspections 

of fan disks for electrical arc-out defects 

on fan disks installed on regional jets, 

and 

• Shop-level inspections of fan disks 

for electrical arc-out defects on fan disks 

installed on business jets. 

Since we issued that NPRM, GE 

performed an updated risk analysis that 

shows we need to take corrective action 

that is more stringent than that 

proposed in the NPRM. We also propose 

to amend 14 CFR part 39 by superseding 

AD 2007–05–16, Amendment 39–14977 

(72 FR 10054, March 7, 2007). That AD 

requires a onetime visual and tactile 

inspection of certain areas of certain 

P/N and SN fan disks for an arc-out 

defect, within 20 engine flight hours 

after the effective date of that AD. Since 

we issued that AD, GE has added those 

SN fan disks to the applicable service 

bulletins for the repetitive inspection 

requirements of this proposed AD. 

Since these changes expand the scope 

of the originally proposed rule, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for public 

comment. This condition, if not 

corrected, could result in an 

uncontained failure of the fan disk and 

damage to the airplane. 


dwashington3 on PROD1PC60 with PROPOSALS