33162 Federal Register / Vol. 75, No. 112 / Friday, June 11, 2010 / Rules and Regulations 

FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5122, fax (817) 222–5961, for 

information about previously approved 

alternative methods of compliance. 

(f) The Joint Aircraft System/ 

Component (JASC) Code is 6410: Tail 

Rotor Blades. 

(g) This amendment becomes effective 

on July 16, 2010. 

Note 5: The subject of this AD is addressed 

in Transport Canada (Canada) AD CF–2004– 

21R3, dated April 23, 2008. 

Issued in Fort Worth, Texas, on April 28, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11071 Filed 6–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0512; Directorate 

Identifier 2010–NE–21–AD; Amendment 39– 

16332; AD 2010–13–01] 

RIN 2120–AA64 

Airworthiness Directives; Microturbo 

Saphir 20 Model 095 Auxiliary Power 

Units (APUs) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the European Aviation Safety 

Agency (EASA) to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The turbine wheel, part number (P/N) 095– 

01–015–03, of the SAPHIR 20 Model 095 

APU is a life-limited part. Microturbo had 

determined through ‘‘fleet leader’’ testing and 

inspection that the published life limit of this 

turbine wheel should be reduced to 9,000 

cycles. Use of the turbine wheel beyond 

9,000 cycles could lead to the release of high 

energy debris that could jeopardize aircraft 

safety. 

For the reasons described above, EASA AD 

2008–0084 required the implementation of 

the new life limit on the affected parts and 

the replacement parts that had exceeded the 

new life limit. 

Microturbo has now determined that the 

life limit of the turbine wheel should be 

further reduced to 4,225 cycles. Use of the 

turbine wheel beyond 4,225 cycles could 

lead to the release of high energy debris that 

could jeopardize aircraft safety. 

We are issuing this AD to prevent an 

uncontained burst of the APU turbine 

that could liberate high-energy 

fragments resulting in injury and 

damage to the aircraft. 

DATES: This AD becomes effective July 

16, 2010. 

We must receive comments on this 

AD by July 26, 2010. 

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: 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 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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

michaelschwetz@faa.gov; telephone 

(781) 238–7761; fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued AD 2010–0079, 

dated April 26, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The turbine wheel, part number (P/N) 095– 

01–015–03, of the SAPHIR 20 Model 095 

APU is a life-limited part. Microturbo had 

determined through ‘‘fleet leader’’ testing and 

inspection that the published life limit of this 

turbine wheel should be reduced to 9,000 

cycles. Use of the turbine wheel beyond 

9,000 cycles could lead to the release of high 

energy debris that could jeopardize aircraft 

safety. 

For the reasons described above, EASA AD 

2008–0084 required the implementation of 

the new life limit on the affected parts and 

the replacement parts that had exceeded the 

new life limit. 

Microturbo has now determined that the 

life limit of the turbine wheel should be 

further reduced to 4,225 cycles. Use of the 

turbine wheel beyond 4,225 cycles could 

lead to the release of high energy debris that 

could jeopardize aircraft safety. 

For the reasons described above, this AD, 

which supersedes EASA AD 2008–0084, 

requires the implementation of the new life 

limit on the affected parts and the 

replacement of parts that had exceeded this 

new limit. This AD also extends the scope to 

include the P/N 095–01–015–20 turbine 

wheel, which is physically identical to the P/ 

N 095–01–015–03 turbine wheel but is 

manufactured using a revised process 

(approved by EASA). 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Microturbo has issued Service 

Bulletin 095–49–17, dated March 16, 

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 AD 

This product has been approved by 

the aviation authority of EASA 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 

issuing 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. This 

AD requires removal of turbine wheels 

P/N 095–01–015–03 or P/N 095–01– 

015–20, before exceeding the new 

reduced life limit of 4,225 cycles-inservice, and replacement with a new or 

serviceable part. 

FAA’s Determination of the Effective 

Date 

Since no domestic operators use this 

product, notice and opportunity for 

public comment before issuing this AD 

are unnecessary. Therefore, we are 

adopting this regulation immediately. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

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Federal Register / Vol. 75, No. 112 / Friday, June 11, 2010 / Rules and Regulations 33163 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0512; 

Directorate Identifier 2010–NE–21–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 with FAA 

personnel concerning this 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). 

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 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 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); 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 AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 adding 

the following new AD: 

2010–13–01 Microturbo: Amendment 39– 

16332.; Docket No. FAA–2010–0512; 

Directorate Identifier 2010–NE–21–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 16, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Microturbo Saphir 

20 model 095 auxiliary power units (APUs). 

These APUs are installed on, but not limited 

to, Eurocopter EC225 and AS332 helicopters. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by the European Aviation Safety 

Agency (EASA) to identify and correct an 

unsafe condition on an aviation product. 

EASA AD 2010–0079 states: 

The turbine wheel, part number (P/N) 095– 

01–015–03, of the SAPHIR 20 Model 095 

APU is a life-limited part. Microturbo had 

determined through ‘‘fleet leader’’ testing and 

inspection that the published life limit of this 

turbine wheel should be reduced to 9,000 

cycles. Use of the turbine wheel beyond 

9,000 cycles could lead to the release of high 

energy debris that could jeopardize aircraft 

safety. 

For the reasons described above, EASA AD 

2008–0084 required the implementation of 

the new life limit on the affected parts and 

the replacement parts that had exceeded the 

new life limit. 

Microturbo has now determined that the 

life limit of the turbine wheel should be 

further reduced to 4,225 cycles. Use of the 

turbine wheel beyond 4,225 cycles could 

lead to the release of high energy debris that 

could jeopardize aircraft safety. 

We are issuing this AD to prevent an 

uncontained burst of the APU turbine that 

could liberate high-energy fragments 

resulting in injury and damage to the aircraft. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

(1) Remove turbine wheels P/N 095–01– 

015–03 or P/N 095–01–015–20, before 

exceeding the new reduced life limit of 4,225 

cycles-in-service, and replace it with a new 

or serviceable part. 

(2) Thereafter, remove turbine wheels P/N 

095–01–015–03 or P/N 095–01–015–20, 

before exceeding the new reduced life limit 

of 4,225 cycles-in-service, and replace it with 

a new or serviceable part. 

FAA AD Differences 

(f) The initial compliance time for the 

EASA AD is within one month after the 

effective date of the AD or upon 

accumulating 4,225 cycles-in-service, 

whichever occurs later. The initial 

compliance time for this AD is before 

exceeding the new reduced life limit of 4,225 

cycles-in-service. 

Alternative Methods of Compliance 

(g) The Manager, Boston Aircraft 

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 

(h) Refer to EASA AD 2010–0079, dated 

April 26, 2010, and Microturbo Service 

Bulletin No. 095–49–17, dated March 16, 

2010, for related information. Contact 

Microturbo, Technical Publications 

Department, 8 Chemin du pont de Rupe, BP 

62089, 31019 Toulouse Cedex, France; 

telephone 33 0 5 61 37 55 00; fax 33 0 5 61 

70 74 45 for a copy of this service bulletin. 

(i) Contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA 01803; e-mail: michaelschwetz@faa.gov; 

telephone (781) 238–7761; fax (781) 238- 

7170, for more information about this AD. 

Material Incorporated by Reference 

(j) None. 

Issued in Burlington, Massachusetts, on 

June 4, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–13928 Filed 6–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

WReier-Aviles on DSKGBLS3C1PROD with RULES