[Federal Register Volume 70, Number 123 (Tuesday, June 28, 2005)]
[Proposed Rules]
[Pages 37063-37065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-12692]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21242; Directorate Identifier 2005-NE-09-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1 and 1S1 
Turboshaft Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a 
new airworthiness directive (AD) that is applicable to certain 
Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines. This proposal 
would require initial and repetitive position checks of the gas 
generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1 
and 1S1 turboshaft engines, and replacement of 2nd stage turbines on 1B 
and 1D1 engines only. This proposal is prompted by the release of gas 
generator 2nd stage turbine blades while in service, with full 
containment of debris. We are proposing this AD to prevent an 
uncommanded engine in flight shutdown.

DATES: We must receive any comments on this proposed AD by August 29, 
2005.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     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.
    Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 
00, fax +33 05 59 74 45 15, for the service information identified in 
this proposed AD.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7175, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-21242; 
Directorate Identifier 2005-NE-09-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light 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 with FAA 
personnel concerning this proposed AD. Using the search function of the 
DMS 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) or you 
may visit http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is on the plaza 
level of the Department of Transportation Nassif Building at the street 
address stated in ADDRESSES. Comments will be available in the AD 
docket shortly after the DMS receives them.

Discussion

    The Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition might exist on Turbomeca, Arriel 1B (modified per TU 148), 
1D, 1D1 and 1S1 turboshaft engines. The DGAC advises that sixteen cases 
of release of gas generator 2nd stage turbine blades occurred in 
service, with full containment of debris. These events resulted in 
uncommanded engine in flight shutdown. Although terminating action is 
still unavailable, mandatory checks of the turbine blades and 
replacement of the turbine are being required in order to reduce the 
probability of an uncommanded engine in flight shutdown.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following Turbomeca Alert Service Bulletins (ASBs), all dated March 24, 
2004: ASB A292 72 0807, for Arriel 1B post TU 148; ASB A292 72 0808, 
for Arriel 1D; ASB A292 72 0809, for Arriel 1D1; and ASB A292 72 0810, 
for Arriel 1S1, that describe procedures for initial and repetitive 
position checks of the 2nd stage turbine blades, and replacement of 2nd 
stage turbines on 1B and 1D1 engines only. The DGAC classified these 
ASBs as mandatory and issued airworthiness directive F-2004-047, dated 
March 31, 2004, in order to ensure the airworthiness of these Turbomeca 
Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines in France.

FAA's Determination and Requirements of the Proposed AD

    These engines, manufactured in France, are 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. In keeping with this bilateral 
airworthiness agreement, the DGAC kept us informed of the situation 
described above. We have examined the DGAC'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. For this reason, we are proposing this AD, which would 
require initial and repetitive position checks of the 2nd stage turbine 
blades on Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines, and 
replacement of 2nd stage turbines on 1B and 1D1 engines only. The 
proposed AD would require you to

[[Page 37064]]

use the service information described previously to perform these 
actions.

Interim Action

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

Costs of Compliance

    There are about 2,557 Turbomeca Arriel 1B, 1D, 1D1 and 1S1 
turboshaft engines of the affected design in the worldwide fleet. We 
estimate that this proposed AD would affect 721 engines installed on 
helicopters of U.S. registry. We also estimate that it would take about 
2 work hours per engine to inspect all 721 engines and 40 hours per 
engine to replace about 571 2nd stage turbines on 1B and 1D1 engines, 
and that the average labor rate is $65 per work hour. Required parts 
would cost about $3,200 per engine. Based on these figures, we estimate 
the total cost of the proposed AD to U.S. operators to be $3,405,530.

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 have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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. Would 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 proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

Turbomeca: Docket No. FAA-2005-21242; Directorate Identifier 2005-
NE-09-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 29, 
2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 1B engines fitted with 
2nd stage turbine modification TU 148, and Arriel 1D, 1D1 and 1S1 
engines. Arriel 1B engines are installed on but not limited to 
Eurocopter France AS-350B and AS-350A ``Ecureuil'' helicopters; 1D 
engines are installed on but not limited to Eurocopter France AS-
350B1 ``Ecureuil'' helicopters; 1D1 engines are installed on but not 
limited to Eurocopter France AS-350B2 ``Ecureuil'' helicopters; and 
Arriel 1S1 engines are installed on but not limited to Sikorsky 
Aircraft S-76A and S-76C helicopters.

Unsafe Condition

    (d) This AD results from the release of gas generator 2nd stage 
turbine blades while in service, with full containment of debris. We 
are issuing this AD to prevent an uncommanded engine in flight 
shutdown.

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.

Initial Relative Position Check of 2nd Stage Turbine Blades

    (f) Do an initial relative position check of the 2nd stage 
turbine blades using the Turbomeca service bulletins (SBs) specified 
in the following Table 1 before reaching any of the intervals 
specified in Table 1 or within 50 hours time-in-service after the 
effective date of this AD, whichever occurs later.

          Table 1.--Initial and Repetitive Relative Position Check Intervals of 2nd Stage Turbine Blade
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                         Initial relative position check
Turbomeca engine model              interval                    Repetitive interval           Service bulletin
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Arriel 1B (modified     Within 1,200 hours time-since-    Within 200 hours time-in-        A292 72 0807, dated
 per TI 148).            new (TSN) or time-since-          service-since-last-relative-     March 24, 2004.
                         overhaul (TSO) or 3,500 cycles-   position check (TSLRPC)
                         since-new (CSN) or cycles--
                         since-overhaul (CSO), whichever
                         occurs earlier.
Arriel 1D.............  Within 1,200 hours TSN or TSO or  Within 200 hours TSLRPC........  A292 72 0808, dated
                         3,500 hours CSN or CSO,                                            March 24, 2004.
                         whichever occurs earlier.
Arriel 1D1............  Within 1,200 hours TSN or TSO or  Within 150 hours TSLRPC........  A292 72 0809, dated
                         3,500 hours CSN or CSO,                                            March 24, 2004.
                         whichever occurs earlier.
Arriel 1S1............  Within 1,200 hours TSN or TSO or  Within 150 hours TSLRPC........  A292 72 0810, dated
                         3,500 hours CSN or CSO,                                            March 24, 2004.
                         whichever occurs earlier.
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Credit for Previous Relative Position Checks

    (g) Relative position checks of 2nd stage turbine blades done 
using Turbomeca SB A292 72 0263, update 1, 2, 3, or 4, may be used 
to show compliance with the initial requirements of paragraph (f) of 
this AD.

Repetitive Relative Position Check of 2nd Stage Turbine Blades

    (h) Recheck the relative position of 2nd stage turbine blades at 
the TSLRPC intervals specified in Table 1 of this AD, using the 
service bulletins indicated.

Replace 2nd Stage Turbines on 1B and 1D1 Engines

    (i) Replace 2nd stage turbine with a new or overhauled 2nd stage 
turbine before accumulating 1,500 hours TSN or TSO for Arriel 1D1 
engines, and 2,200 hours TSN or TSO for Arriel 1B engines, or by 
August 31, 2006, whichever occurs later. Overhauled Arriel 1D1 2nd 
stage turbines must be fitted with new blades; overhauled Arriel 1B 
2nd stage turbines may be fitted with overhauled or new blades. 
Because this is an interim action, all turbines, including those 
that are new or overhauled, must continue to comply with relative 
position check requirements of paragraphs (f) and (h).

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) DGAC airworthiness directive F-2004-047, dated March 31, 
2004, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on June 15, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-12692 Filed 6-27-05; 8:45 am]
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