Document ID: FAA-2010-0009-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Turbomeca Turmo IV A and IV C Turboshaft Engines
Posted Date: 2010-01-19T05:00Z

[Federal Register Volume 75, Number 11 (Tuesday, January 19, 2010)]
[Rules and Regulations]
[Pages 2787-2789]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-758]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0009; Directorate Identifier 2010-NE-01-AD; 
Amendment 39-16178; AD 2010-02-08]
RIN 2120-AA64

Airworthiness Directives; Turbomeca Turmo IV A and IV C 
Turboshaft Engines

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 an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During a maintenance inspection before the first flight of the 
day, an oil leak was found on an engine deck. A circumferential 
crack on the intermediate bearing return flexible pipe union (pipe 
part number 9 560 17 606 0) was identified as the origin of the 
leak. A similar oil pipe union crack was then reported at the same 
location on another engine, on the same pipe part number. This pipe 
part number was approved as Modification TU 233 in 2008.
    Although such cracks have been detected and did not lead to an 
in-service event, the possibility exists that some additional cracks 
could occur and may not be detected before the potential complete 
rupture of the union.

    We are issuing this AD to prevent a helicopter engine in-flight 
shutdown resulting in an emergency auto-rotation landing or accident.

DATES: This AD becomes effective February 3, 2010.
    We must receive comments on this AD by February 18, 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.

Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 
15, or go to: http://www.turbomeca-support.com, for a copy of the 
service information identified in this AD.

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: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

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 2009-0261-E, dated December 18, 2009 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During a maintenance inspection before the first flight of the 
day, an oil leak was found on an engine deck. A circumferential 
crack on the intermediate bearing return flexible pipe union (pipe 
part number 9 560 17 606 0) was identified as the origin of the 
leak. A similar oil pipe union crack was then reported at the same 
location on another engine, on the same pipe part number. This pipe 
part number was approved as Modification TU 233 in 2008.
    Although such cracks have been detected and did not lead to an 
in-service event, the possibility exists that some additional cracks 
could occur and may not be detected before the potential complete 
rupture of the union.

[[Page 2788]]

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Turbomeca has issued Alert Service Bulletin No. A249 72 0809, 
Version A, dated December 15, 2009. 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 EASA, 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, for Turmo IV A and Turmo IV C engines that have 
incorporated Turbomeca Modification TU 233, initial and repetitive 
visual inspections for the absence of oil leakage or seepage from the 
unions of the intermediate bearing return flexible pipes.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
failures of the flexible pipe unions, which if not corrected, could 
lead to an in-flight engine shutdown and a forced autorotation landing 
or accident. Therefore, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in fewer than 30 days.

Interim Actions

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and 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-2010-0009; Directorate 
Identifier 2010-NE-01-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:

2010-02-08 Turbomeca: Amendment 39-16178; Docket No. FAA-2010-0009; 
Directorate Identifier 2010-NE-01-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
3, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Turmo IV A and IV C turboshaft 
engines that have incorporated Turbomeca Modification TU 233. These 
engines are installed on, but not limited to, Eurocopter SA 330F, G, 
or J PUMA helicopters.

Reason

    (d) During a maintenance inspection before the first flight of 
the day, an oil leak was found on an engine deck. A circumferential 
crack on the intermediate bearing return flexible pipe union (pipe 
part number 9 560 17 606 0) was identified as the origin of the 
leak. A similar oil pipe union crack was then reported at the same 
location on another engine, on the same pipe part number. This pipe 
part number was approved as Modification TU 233 in 2008.
    Although such cracks have been detected and did not lead to an 
in-service event, the possibility exists that some additional cracks 
could occur and may not be detected before the potential complete 
rupture of the union.

This 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. We 
are issuing this AD to prevent a helicopter engine in-flight 
shutdown resulting in an emergency auto-rotation landing or 
accident.

[[Page 2789]]

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Before the next flight after the effective date of this AD, 
and thereafter daily after the last flight of the day until further 
notice, visually inspect for absence of oil leakage or seepage from 
both unions of the intermediate bearing return flexible pipes, part 
number 9 560 17 606 0.
    (2) If any oil leakage or seepage is found, disassemble the pipe 
and visually inspect the unions.
    (3) If no crack is found, re-install the pipe.
    (4) If any crack is found, remove the pipe from service and 
replace it.
    (5) The actions required by paragraph (e)(1) of this AD may be 
performed by the owner/operator holding at least a private pilot 
certificate, and must be entered into the aircraft records showing 
compliance with this AD in accordance with 14 CFR 43.9 and 
91.417(a)(2)(v).

FAA AD Differences

    (f) None.

Alternative Methods of Compliance (AMOCs)

    (g) 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

    (h) Refer to MCAI Airworthiness Directive 2009-0261-E, dated 
December 18, 2009, and Turbomeca Alert Mandatory Service Bulletin 
No. A249 72 0809, Version A, dated December 15, 2009, for related 
information. Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: 
noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 
59 74 45 15, or go to: http://www.turbomeca-support.com, for a copy 
of this service information.
    (i) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199, 
for more information about this AD.

Material Incorporated by Reference

    (j) None.

    Issued in Burlington, Massachusetts, on January 12, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-758 Filed 1-15-10; 8:45 am]
BILLING CODE 4910-13-P