[Federal Register Volume 71, Number 15 (Tuesday, January 24, 2006)]
[Rules and Regulations]
[Pages 3754-3757]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-522]


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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; 
Amendment 39-14460; AD 2006-02-08]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, and 1S1 
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 adopting a new airworthiness directive (AD) for 
certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. This 
AD requires 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 initial and repetitive replacements of 2nd 
stage turbines on 1B, 1D, and 1D1 engines only. This AD results from 
reports of the release of gas generator 2nd stage turbine blades while 
in service, with full containment of debris. We are issuing this AD to 
prevent inflight engine shutdown and subsequent forced autorotation 
landing or accident.

DATES: This AD becomes effective February 28, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of February 28, 2006.
    We must receive any comments on this AD by March 27, 2006.

ADDRESSES: Use one of the following addresses to comment on this 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 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: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to Turbomeca Arriel 1B engines fitted with 2nd stage turbine 
modification TU 148, and Arriel 1D, 1D1, and 1S1 engines. We published 
the proposed AD in the Federal Register on June 28, 2005 (70 FR 37063). 
That action proposed to 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.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located 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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Change the Compliance Time

    One commenter, Turbomeca, requests we change the compliance time 
for replacing 2nd stage turbines to, immediately upon receipt of a 
replacement 2nd stage turbine from Turbomeca, and at least by August 
31, 2006. The commenter states that without this requirement, operators 
will incur unacceptable and unnecessary risk for engines operating past 
the

[[Page 3755]]

hourly life limit. The commenter further states that an unacceptable 
number of engines will require replacement 2nd stage turbines at the 
compliance end-date, causing grounding of aircraft because of a lack of 
replacement parts. We partially agree. There is a need to replace the 
2nd stage turbines as they reach the hourly life limit, and to strive 
to not allow them to stay installed until the compliance end-date. 
However, replacing them immediately upon receipt could unnecessarily 
create compliance problems for operators. An example would be if a 
helicopter is at a remote site the day an operator receives a 
replacement 2nd stage turbine. We changed the compliance to read 
``After accumulating 1,500 hours TSN or TSO for Arriel 1D and 1D1 
engines, and 2,200 hours TSN or TSO for Arriel 1B engines, initially 
replace the 2nd stage turbine with a new or overhauled 2nd stage 
turbine as soon as practicable, but no later than August 31, 2006.'' 
This change prevents compliance problems associated with the 
commenter's phrase ``immediately upon receipt'' yet still requires 
prompt replacement of 2nd stage turbines after one becomes available.

NPRM Not Clear About Ongoing Requirement

    The same commenter states that the NPRM is not clear that replacing 
the 2nd stage turbines is an ongoing requirement. We agree. We changed 
the compliance in this AD to address initial and repetitive 
replacements of 2nd stage turbines.

Inspection and Replacement Requirements Changed for Arriel 1D 
Turboshaft Engines

    The same commenter states that the requirements for inspecting and 
replacing Arriel 1D turboshaft engines have changed since we issued the 
NPRM. Those requirements are now the same as for Arriel 1D1 turboshaft 
engines. We agree. We changed the compliance in this AD to shorten the 
repetitive inspection interval and add the requirement to replace the 
2nd stage turbine. However, since many of the Arriel 1D turboshaft 
engines may be at or near the compliance time for replacing the 2nd 
stage turbine, we have found that notice and opportunity for further 
comment before issuing this AD, are impracticable. We are issuing this 
AD as a final rule; request for comments, allowing operators to comment 
after the AD publishes.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

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 AD will affect 721 engines installed on helicopters 
of U.S. registry. We estimate that it will 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 will cost about 
$3,200 per engine. Based on these figures, we estimate the total cost 
of the 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 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 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
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 airworthiness 
directive:

2006-02-08 Turbomeca: Amendment 39-14460; Docket No. FAA-2005-21242; 
Directorate Identifier. 2005-NE-09-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
28, 2006.

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 reports of the release of gas generator 
2nd stage turbine blades while in service, with full containment of 
debris. We are issuing this AD to prevent inflight engine shutdown 
and subsequent forced autorotation landing or accident.

[[Page 3756]]

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 mandatory alert service bulletins 
(ASBs) 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                               Mandatory alert
      Turbomeca engine model               check interval           Repetitive interval      service bulletin
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Arriel 1B (modified per TU 148)...  Within 1,200 hours time-      Within 200 hours time-  A292 72 0807, dated
                                     since-new (TSN) or time-      in-service-since-last-  March 24, 2004.
                                     since-overhaul (TSO) or       relative-position-
                                     3,500 cycles-since-new        check (TSLRPC).
                                     (CSN) or cycles-since-
                                     overhaul (CSO), whichever
                                     occurs earlier.
Arriel 1D1 and Arriel 1D..........  Within 1,200 hours TSN or     Within 150 hours        A292 72 0809, Update
                                     TSO or 3,500 hours CSN or     TSLRPC.                 No. 1, dated October
                                     CSO, whichever occurs                                 4, 2005.
                                     earlier.
Arriel 1S1........................  Within 1,200 hours TSN or     Within 150 hours        A292 72 0810, dated
                                     TSO or 3,500 hours CSN or     TSLRPC.                 March 24, 2004.
                                     CSO, whichever occurs
                                     earlier.
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Repetitive Relative Position Check of 2nd Stage Turbine Blades

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

Credit for Previous Relative Position Checks

    (h) Relative position checks of 2nd stage turbine blades done 
using Turbomeca Service Bulletin 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.

Initial Replacement of 2nd Stage Turbines on Arriel 1B, 1D, and 1D1 
Engines

    (i) After accumulating 1,500 hours TSN or TSO for Arriel 1D and 
1D1 engines, and 2,200 hours TSN or TSO for Arriel 1B engines, 
initially replace the 2nd stage turbine with a new or overhauled 2nd 
stage turbine as soon as practicable, but no later than August 31, 
2006.

Repetitive Replacements of 2nd Stage Turbines on Arriel 1B, 1D, and 1D1 
Engines

    (j) Thereafter, replace the 2nd stage turbine with a new or 
overhauled 2nd stage turbine within every 1,500 hours TSN or TSO for 
Arriel 1D and 1D1 engines, and within every 2,200 hours TSN or TSO 
for Arriel 1B engines.

Criteria for Overhauled 2nd Stage Turbines

    (k) Do the following to overhauled 2nd stage turbines, 
referenced in paragraphs (i) and (j) of this AD:
    (1) You must install new blades in the 2nd stage turbines of 
overhauled Arriel 1D and 1D1 engines.
    (2) You may install either overhauled or new blades in the 2nd 
stage turbines of overhauled Arriel 1B engines.

Relative Position Check Continuing Compliance Requirements

    (l) All 2nd stage turbines, including those that are new or 
overhauled, must continue to comply with relative position check 
requirements of paragraphs (f) and (j) of this AD.

Alternative Methods of Compliance

    (m) 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

    (n) DGAC airworthiness directive F-2004-047 R1, dated October 
26, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (o) You must use the service information specified in Table 2 of 
this AD to perform the actions required by this AD. The Director of 
the Federal Register approved the incorporation by reference of the 
documents listed in Table 2 of this AD in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Contact Turbomeca, 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 Docket 
Management Facility; U.S. Department of Transportation, 400 Seventh 
Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-
0001, on the Internet at http://dms.dot.gov, 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.

                                      Table 2.--Incorporation by Reference
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  Turbomeca mandatory alert
     service bulletin No.            Page             Update No.                         Date
----------------------------------------------------------------------------------------------------------------
A292 72 0807.................  ALL.............  Original...........  March 24, 2004.
  Total Pages: 17
A292 72 0809.................  ALL.............  1..................  October 4, 2005.
  Total Pages: 18
A292 72 0810.................  ALL.............  Original...........  March 24, 2004.
  Total Pages: 14
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[[Page 3757]]

    Issued in Burlington, Massachusetts, on January 12, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-522 Filed 1-23-06; 8:45 am]
BILLING CODE 4910-13-P