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[Federal Register: September 27, 2010 (Volume 75, Number 186)]
[Rules and Regulations]               
[Page 59060-59062]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27se10-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21624; Directorate Identifier 2005-NE-17-AD; 
Amendment 39-16439; AD 2010-20-05]
RIN 2120-AA64

 
Airworthiness Directives; Turbom[eacute]ca S.A. ARRIEL 2B 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Turbom[eacute]ca S.A. ARRIEL 2B turboshaft engines. That AD 
currently requires initial and repetitive inspections, cleaning, 
lubrication, and checks for proper operation of the hydro-mechanical 
unit (HMU) acceleration controller axle except on engines that 
incorporate modification TU 132. That AD also provides an optional 
terminating action for the repetitive inspections. This AD requires the 
same actions, but expands the applicability to include all engines that 
do not incorporate modification TU 149. This AD results from reports of 
engines with modification TU 132 incorporated experiencing stuck 
controller axles in the metering valve body. We are issuing this AD to 
prevent loss of control of engine fuel flow in manual control mode or 
mixed control mode, which can lead to engine overspeed, and in-flight 
engine shutdown resulting in a forced autorotation landing or accident.

DATES: Effective October 12, 2010. The Director of the Federal Register 
approved the incorporation by reference of a certain publication listed 
in the AD as of October 12, 2010.
    We must receive any comments on this AD by October 27, 2010.

ADDRESSES: Use one of the following addresses to comment on this 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

[[Page 59061]]

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 Turbom[eacute]ca, 40220 Tarnos, France; telephone 33 05 59 
74 40 00; fax 33 05 59 74 45 15, for the service information identified 
in this AD.

FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and 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: On April 9, 2007, the FAA issued AD 2005-13-
25R1, Amendment 39-15028 (72 FR 19110, April 17, 2007). That AD 
requires initial and repetitive inspections, cleaning, lubrication, and 
checks for proper operation of the HMU acceleration controller axle on 
engines that incorporate modification TU 62A, unless the engine 
incorporates modification TU 132. That AD was the result of several 
reports of the HMU acceleration controller axle sticking. The stuck 
acceleration controller axle resulted in engine overspeed and commanded 
and uncommanded in-flight engine shutdowns. That condition, if not 
corrected, could result in loss of control of engine fuel flow in 
manual control mode or mixed control mode, which can lead to engine 
overspeed, and in-flight engine shutdown resulting in a forced 
autorotation landing or accident.

Actions Since AD 2005-13-25R1 Was Issued

    Since we issued AD 2005-13-25R1, the European Aviation Safety 
Authority (EASA), which is the airworthiness agent for the Member 
States of the European Union, has informed us that the manufacturer, 
Turbom[eacute]ca S.A., has reported additional occurrences of stuck 
controller axles in the metering valve body. Some of these occurrences 
occurred on engines that incorporated modification TU 132. 
Turbom[eacute]ca S.A. introduced modification TU 149 to eliminate the 
cause of the unsafe condition on the ARRIEL 2B turboshaft engines. This 
AD requires inspecting and lubricating the P3 cover and HMU 
acceleration control axle on HMUs that are not modified to TU 149. It 
also approves incorporating modification TU 149 to eliminate the cause 
of the unsafe condition and the repetitive inspections required by this 
AD. We are issuing this AD to prevent loss of control of engine fuel 
flow in the manual or mixed control modes, which can lead to engine 
overspeed, and in-flight engine shutdown resulting in a forced 
autorotation landing or accident.

Relevant Service Information

    Turbom[eacute]ca has issued Mandatory Service Bulletin A292 73 
2814, Version D, dated October 16, 2009, that describes procedures for 
inspecting, lubricating, and checking for proper operation of the HMU 
acceleration controller axle. EASA classified this service bulletin as 
mandatory and issued AD 2009-0246, dated November 10, 2009, in order to 
assure the airworthiness of these ARRIEL 2B turboshaft engines in the 
European Union.

Bilateral Airworthiness Agreement

    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 that agreement, 
EASA has kept us informed of the situation described above. We have 
examined EASA's findings, 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 This AD

    The unsafe condition described previously is likely to exist or 
develop on other Turbom[eacute]ca S.A. ARRIEL 2B turboshaft engines of 
the same type design. We are issuing this AD to prevent loss of control 
of engine fuel flow in the manual control mode or mixed control mode, 
which can lead to engine overspeed, and in-flight engine shutdown 
resulting in a forced autorotation landing or accident. This AD 
requires initial and repetitive inspections, cleaning, lubrication, and 
checks for proper operation of the HMU acceleration controller axle. 
You must use the service information described previously to perform 
the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-21624; 
Directorate Identifier 2005-NE-17-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    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 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 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.

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

[[Page 59062]]

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 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 that 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (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 removing Amendment 39-15028 (72 FR 
19110, April 17, 2007), and by adding a new airworthiness directive, 
Amendment 39-16439, to read as follows:
2010-20-05 Turbom[eacute]ca S.A.: Amendment 39-16439. Docket No. 
FAA-2005-21624; Directorate Identifier 2005-NE-17-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
12, 2010.

Affected ADs

    (b) This AD supersedes AD 2005-13-25R1, Amendment 39-15028.

Applicability

    (c) This AD applies to Turbom[eacute]ca S.A. ARRIEL 2B 
turboshaft engines that do not have Modification TU 149 
incorporated. These engines are installed on, but not limited to, 
Eurocopter AS350B3 helicopters.

Unsafe Condition

    (d) This AD results from reports of engines with modification TU 
132 incorporated experiencing stuck acceleration control axles in 
the hydromechanical unit (HMU) metering valve body. We are issuing 
this AD to prevent loss of control of engine fuel flow in manual 
control mode or mixed control mode, which can lead to engine 
overspeed, and in-flight engine shutdown resulting in a forced 
autorotation landing or accident.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

HMUs Without Modification TU 149

    (f) Within 20 operating hours of the effective date of this AD, 
check the fuel metering system and perform maintenance procedures in 
accordance with Paragraph 2 of Turbom[eacute]ca MSB A292 73 2814, 
Version D, dated October 16, 2009.
    (g) Repeat the maintenance procedures of paragraph (f) of this 
AD within every 210 operating hours.

Optional Terminating Action

    (h) Modifying the HMU to Modification TU 149 terminates the 
repetitive inspection requirements specified in paragraph (g) of 
this AD. You can find guidance on modifying the HMU to Modification 
TU 149 in Turbom[eacute]ca Service Bulletin 292 73 2149, Version C, 
dated August 10, 2009.

Previous Credit

    (i) Maintenance performed prior to the effective date of this AD 
using Turbom[eacute]ca MSB A292 73 2814, Version C, dated December 
19, 2006, or an earlier version of this MSB, satisfies the 
maintenance requirements of paragraph (f) of this AD.

Alternative Methods of Compliance

    (j) 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

    (k) EASA airworthiness directive 2009-00246, dated November 10, 
2009, also addresses the subject of this AD.
    (l) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and 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

    (m) You must use Turbom[eacute]ca Mandatory Service Bulletin 
(MSB) A292 73 2814, Version D, dated October 16, 2009, to perform 
the actions required by this AD. The Director of the Federal 
Register approved the incorporation by reference of MSB A292 73 
2814, Version D, dated October 16, 2009, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Contact Turbom[eacute]ca S.A., 40220 
Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, 
for a copy of this service information. You may review copies at the 
FAA, New England Region, Office of the Regional Counsel, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Burlington, Massachusetts, on September 15, 2010.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-23581 Filed 9-24-10; 8:45 am]
BILLING CODE 4910-13-P
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