[Federal Register Volume 72, Number 91 (Friday, May 11, 2007)]
[Rules and Regulations]
[Pages 26711-26714]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-8991]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23809; Directorate Identifier 2005-NE-52-AD; 
Amendment 39-15048; AD 2007-10-07]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft 
Engines

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

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding an existing airworthiness directive (AD) by 
adopting a new 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:

    The deterioration of the splines on the HP/LP pump assembly 
drive shaft may eventually interrupt fuel supply and cause 
uncommanded in-flight engine shutdown. The result may be an 
emergency autorotation landing or, at worst, an accident.
    Two cases of in-flight shutdown resulting from splines 
deterioration have been reported for the ARRIUS 2B1 engine, which 
has the same HP/LP pump drive design as the ARRIEL 2. These cases 
prompted us to require the inspection at 500 hours and each time the 
HMU is removed/installed.
    This AD modifies the content of the previous DGAC France AD F-
2005-188 (EASA Approval Number 2005-6408) in adding a one time 
inspection within 30

[[Page 26712]]

operating hours from effective date of this AD as well as HMU re-
installation according to a maintenance task modified to avoid this 
kind of wrong assembly. This has been set up following one case of 
improper clipping of the coupling shaft onto the drive gear shaft, 
which resulted in an uncommanded in-flight engine shutdown (on a 
twin engine rotorcraft). This precaution measure has been taken only 
on engines powering single engine rotorcraft.

This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective May 29, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of Turbomeca Mandatory Service Bulletin No. 292 73 2812, 
Update No. 4, dated January 2, 2007, listed in the AD, as of May 29, 
2007.
    We must receive comments on this AD by June 11, 2007.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility 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 
Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: <a href="/cdn-cgi/l/email-protection#a7e4cfd5ced4d3c8d7cfc2d589d4d7cec9c9c2dee7c1c6c689c0c8d1"><span class="__cf_email__" data-cfemail="bbf8d3c9d2c8cfd4cbd3dec995c8cbd2d5d5dec2fbdddada95dcd4cd">[email protected]</span></a>; telephone (781) 238-7175; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This AD references the MCAI and related service information that we 
considered in forming the engineering basis to correct the unsafe 
condition. The AD contains text copied from the MCAI and for this 
reason might not follow our plain language principles.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
2007-0044, dated February 27, 2007 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    The deterioration of the splines on the HP/LP pump assembly 
drive shaft may eventually interrupt fuel supply and cause 
uncommanded in-flight engine shutdown. The result may be an 
emergency autorotation landing or, at worst, an accident.
    Two cases of in-flight shutdown resulting from splines 
deterioration have been reported for the ARRIUS 2B1 engine, which 
has the same HP/LP pump drive design as the ARRIEL 2. These cases 
prompted us to require the inspection at 500 hours and each time the 
HMU is removed/installed.
    This AD modifies the content of the previous DGAC France AD F-
2005-188 (EASA Approval Number 2005-6408) in adding a one time 
inspection within 30 operating hours from effective date of this AD 
as well as HMU re-installation according to a maintenance task 
modified to avoid this kind of wrong assembly. This has been set up 
following one case of improper clipping of the coupling shaft onto 
the drive gear shaft, which resulted in an uncommanded in-flight 
engine shutdown (on a twin engine rotorcraft). This precaution 
measure has been taken only on engines powering single engine 
rotorcraft.

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

    This AD supersedes AD 2006-21-10, Amendment 39-14795 (71 FR 61634, 
October 19, 2006), which we issued in response to DGAC France AD F-
2005-188.

Relevant Service Information

    Turbomeca has issued Mandatory Service Bulletin No. 292 73 2812, 
Update No. 4, dated January 2, 2007. 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 another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, 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 the information provided by the State of Design Authority 
and determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design. This AD requires the 
following:
    <bullet> Visually inspecting splines of the coupling shaft assembly 
and the HP pump drive gear shaft for wear, within 30 hours-in-service 
from the effective date of this AD for engines that were previously 
inspected using Update 2 of MSB 292 73 2812;
    <bullet> For engines that were not previously inspected using 
Update 2 of MSB 292 73 2812, visual inspection within 50 hours-in-
service after the effective date of this AD for hydraulic mechanical 
units (HMUs) that have accumulated 450 or more hours time-since-new 
(TSN) or time-since-overhaul (TSO) on the effective date of this AD;
    <bullet> For HMUs that have fewer than 450 hours TSN or TSO on the 
effective date of this AD, visual inspection after accumulating 450 
hours TSN or TSO, but before accumulating 500 hours TSN or TSO;
    <bullet> Repetitive inspections every time you remove or install 
the HMU.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies.

[[Page 26713]]

Any such differences are described in a separate paragraph of the AD. 
These requirements take precedence over the actions copied from the 
MCAI.

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 the 
compliance time required to correct the unsafe condition does not allow 
opportunity for prior public comment. 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.

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-2005-23809; Directorate 
Identifier 2005-NE-52-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://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive about this AD.

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, Incorporation by 
reference, 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 removing Amendment 39-14795 (71 FR 
61634, October 19, 2006) and by adding the following new AD:

2007-10-07 Turbomeca: Amendment 39-15048.; Docket No. FAA-2005-
23809; Directorate Identifier 2005-NE-52-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 29, 
2007.

Affected ADs

    (b) This AD supersedes AD 2006-21-10.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter AS350B3 and EC130B4 helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2007-0044, 
dated April 27, 2007, states:
    The deterioration of the splines on the HP/LP pump assembly 
drive shaft may eventually interrupt fuel supply and cause 
uncommanded in-flight engine shutdown. The result may be an 
emergency autorotation landing or, at worst, an accident.
    Two cases of in-flight shutdown resulting from splines 
deterioration have been reported for the ARRIUS 2B1 engine, which 
has the same HP/LP pump drive design as the ARRIEL 2. These cases 
prompted us to require the inspection at 500 hours and each time the 
HMU is removed/installed.
    This AD modifies the content of the previous DGAC France AD F-
2005-188 (EASA Approval Number 2005-6408) in adding a one time 
inspection within 30 operating hours from effective date of this AD 
as well as HMU re-installation according to a maintenance task 
modified to avoid this kind of wrong assembly. This has been set up 
following a one case of improper clipping of the coupling shaft onto 
the drive gear shaft, which resulted in an uncommanded in-flight 
engine shutdown (on a twin engine rotorcraft). This precaution 
measure has been taken only on engines powering single engine 
rotorcraft.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (f) Perform an initial visual inspection of the splines of the 
coupling assembly and the high pressure (HP) pump drive gear shaft 
for wear. Use 2.A. through 2.C.(2) of the Instructions to be 
Incorporated of Turbomeca Mandatory Service Bulletin (MSB) No. 292 
73 2812, Update No. 4, dated January 2, 2007, as follows:
    (1) Inspect within 30 hours-in-service from the effective date 
of this AD for engines that were previously inspected using Update 2 
of MSB 292 73 2812.
    (2) For engines that were not previously inspected using Update 
2 of MSB 292 73 2812, inspect as follows:
    (i) Inspect within 50 hours-in-service after the effective date 
of this AD for hydraulic mechanical units (HMUs) that have 
accumulated 450 or more hours time-since-new (TSN) or time-since-
overhaul (TSO) on the effective date of this AD. Replace the HMU if 
worn beyond limits.
    (ii) Inspect after accumulating 450 hours TSN or TSO, but before 
accumulating 500 hours TSN or TSO for HMUs that have fewer than 450 
hours TSN or TSO on the effective date of this AD. Replace the HMU 
if worn beyond limits.

Repetitive Visual Inspections

    (g) Thereafter, perform a visual inspection of the splines of 
the coupling shaft assembly and the HP pump drive gear shaft for 
wear every time you remove the HMU. Use 2.A. through 2.C.(2) of the 
Instructions to be Incorporated of Turbomeca MSB No. 292 73 2812, 
Update No. 4, dated January 2, 2007. Replace the HMU and coupling 
shaft assembly if worn beyond limits.

[[Page 26714]]

FAA AD Differences

    (h) None.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) 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.
    (2) Airworthy Product: For any requirement in this AD, to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (j) Refer to European Aviation Safety Agency AD 2007-0044, dated 
February 27, 2007, for related information.
    (k) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
<a href="/cdn-cgi/l/email-protection#612209130812150e110904134f1211080f0f0418210700004f060e17"><span class="__cf_email__" data-cfemail="1b58736972686f746b737e6935686b7275757e625b7d7a7a357c746d">[email protected]</span></a>; telephone (781) 238-7175; fax (781) 
238-7199, for more information about this AD.

Material Incorporated by Reference

    (l) You must use Turbomeca Mandatory Service Bulletin No. 292 73 
2812, Update No. 4, dated January 2, 2007, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos--France; Tel (33) 05 59 74 40 00; Telex 570 
042; Fax (33) 05 59 74 45 15.
    (3) 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/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on May 4, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-8991 Filed 5-10-07; 8:45 am]
BILLING CODE 4910-13-P


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