Document ID: FAA-2010-0512-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Microturbo Saphir 20 Model 095 Auxiliary Power Units (APUs)
Posted Date: 2010-06-11T04:00Z

[Federal Register: June 11, 2010 (Volume 75, Number 112)]
[Rules and Regulations]               
[Page 33162-33163]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11jn10-2]                         

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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.

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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-in-service, 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

[[Page 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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