Airworthiness Directives; Turbomeca Arriel 1B, 1D, and 1D1 Turboshaft Engines, 14636-14638 [06-2760]

Download as PDF 14636 § 745.8 Federal Register / Vol. 71, No. 56 / Thursday, March 23, 2006 / Rules and Regulations [Amended] 9. Section 745.8 is amended by removing ‘‘$100,000’’ each time it appears and adding in its place ‘‘the SMSIA’’. I § 745.9–1 [Amended] 10. Section 745.9–1 is amended by removing ‘‘$100,000’’ and adding in its place ‘‘the SMSIA’’. I 11. Section 745.9–2 is revised to read as follows: I rmajette on PROD1PC67 with RULES § 745.9–2 Retirement and other employee benefit plan accounts. (a) Pass-through share insurance. Any shares of an employee benefit plan in an insured credit union shall be insured on a ‘‘pass-through’’ basis, in the amount of up to the SMSIA for the non-contingent interest of each plan participant, in accordance with § 745.2 of this part. An insured credit union that is not ‘‘well capitalized’’ or ‘‘adequately capitalized’’, as those terms are defined in 12 U.S.C. 1790d(c), may not accept employee benefit plan deposits. The terms ‘‘employee benefit plan’’ and ‘‘pass-through share insurance’’ are given the same meaning in this section as in 12 U.S.C. 1787(k)(4). (b) Treatment of contingent interests. In the event that participants’ interests in an employee benefit plan are not capable of evaluation in accordance with the provisions of this section, or an account established for any such plan includes amounts for future participants in the plan, payment by the NCUA with respect to all such interests shall not exceed the SMSIA in the aggregate. (c)(1) Certain retirement accounts. Shares in an insured credit union made in connection with the following types of retirement plans shall be aggregated and insured in the amount of up to $250,000 (which amount shall be subject to inflation adjustments as provided under section 11(a)(1)(F) of the Federal Deposit Insurance Act, except that $250,000 shall be substituted for $100,000 wherever such term appears in such section) per account: (i) Any individual retirement account described in section 408(a) (IRA) of the Internal Revenue Code (26 U.S.C. 408(a)) or similar provisions of law applicable to a U.S. territory or possession; (ii) Any individual retirement account described in section 408A (Roth IRA) of the Internal Revenue Code (26 U.S.C. 408A) or similar provisions of law applicable to a U.S. territory or possession; and (iii) Any plan described in section 401(d) (Keogh account) of the Internal Revenue Code (26 U.S.C. 401(d)) or VerDate Aug<31>2005 13:41 Mar 22, 2006 Jkt 208001 similar provisions of law applicable to a U.S. territory or possession. (2) Insurance coverage for the accounts enumerated in paragraph (c)(1) of this section is based on the present vested ascertainable interest of a participant or designated beneficiary. For insurance purposes, IRA and Roth IRA accounts will be combined together and insured in the aggregate up to $250,000 (which amount shall be subject to inflation adjustments as provided under section 11(a)(1)(F) of the Federal Deposit Insurance Act, except that $250,000 shall be substituted for $100,000 wherever such term appears in such section). A Keogh account will be separately insured from an IRA account, Roth IRA account or, where applicable, aggregated IRA and Roth IRA accounts. account and accumulates $250,000 in that account. Subsequently, A becomes selfemployed and establishes a Keogh account in the same credit union and accumulates $250,000 in that account. What is the insurance coverage? Answer: Each of A’s accounts would be separately insured as follows: The individual account for $100,000, the maximum for that type of account; the IRA account for $250,000, the maximum for that type of account; and the Keogh account for $250,000, the maximum for that type of account. (§§ 745.3(a)(1) and 745.9–2). § 745.9–3 Federal Aviation Administration [Removed] 12. Section 745.9–3 is removed. 13. Section 745.10 is amended by revising the section heading as set forth below and by removing ‘‘$100,000’’ each time it appears and adding in its place ‘‘the SMSIA’’. I I § 745.10 Accounts held by government depositors. * * * * * 14. The Appendix to Part 745 is amended as follows: I a. Section E is amended by removing the heading ‘‘How are Public Unit Accounts Insured?’’ and adding in its place ‘‘How are Accounts Held by Government Depositors Insured?’’ I b. The last sentence of the second paragraph of Section G is amended by removing the words ‘‘the basic insured amount of’’. I c. The seventh paragraph of Section G is amended by removing ‘‘$100,000’’ and adding in its place ‘‘$250,000’’. I d. Example 3(a) of Section G is amended by removing ‘‘(§ 745.9–1)’’ and adding in its place ‘‘(§ 745.9–2)’’. I e. Example 3(b) of Section G is amended by removing ‘‘(§ 745.9–1)’’ and adding in its place ‘‘(§ 745.9–2)’’. I f. Example 4 of Section G is revised to read as follows: I Appendix to Part 745—Examples of Insurance Coverage Afforded Accounts in Credit Unions Insured by the National Credit Union Share Insurance Fund * * * * * G. How are Trust Accounts and Retirement Accounts Insured? * * * * * Example 4 Question: Member A has an individual account of $100,000 and establishes an IRA PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 * * * * * [FR Doc. 06–2754 Filed 3–22–06; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2005–22364; Directorate Identifier 2005–NE–26–AD; Amendment 39– 14526; AD 2006–06–17] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 1B, 1D, and 1D1 Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines. This AD requires inspecting the 2nd stage nozzle guide vanes (NGV2) for wall thickness. This AD results from one instance of a fractured 2nd stage turbine blade followed by an uncommanded engine shutdown. We are issuing this AD to detect and prevent perforation of the NGV2 that could cause fracture of a turbine blade that could result in an uncommanded engine in-flight shutdown on a single-engine helicopter. DATES: This AD becomes effective April 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 27, 2006. ADDRESSES: You can get the service information identified in this AD from Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. E:\FR\FM\23MRR1.SGM 23MRR1 Federal Register / Vol. 71, No. 56 / Thursday, March 23, 2006 / Rules and Regulations FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; 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, 1D, and 1D1 turboshaft engines. We published the proposed AD in the Federal Register on November 4, 2005 (70 FR 67099). That action proposed to require inspecting the NGV2 for wall thickness. 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 comment received. Request To Include an End Date One commenter requests that we include an end date in the AD, of December 31, 2006. This end date would help manage the risk of failure, while causing the least amount of disruption in the form of helicopter grounding. We agree. We changed compliance paragraph (e) to read ‘‘You are responsible for having the actions required by this AD performed at the next shop visit or the next accessibility of the NGV2 after the effective date of this AD, whichever occurs first, but no later than December 31, 2006, unless the actions have already been done.’’ rmajette on PROD1PC67 with RULES Clarification of Unsafe Condition For clarification that the AD is applicable to only single-engine installations, we changed the unsafe condition in the AD to read ‘‘We are issuing this AD to detect and prevent perforation of the 2nd stage nozzle guide vanes (NGV2) that could cause fracture of a turbine blade that could result in an uncommanded engine in- VerDate Aug<31>2005 13:41 Mar 22, 2006 Jkt 208001 flight shutdown on a single-engine helicopter.’’ Conclusion We have carefully reviewed the available data, including the comment 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. Costs of Compliance We estimate that this AD will affect 571 engines installed on helicopters of U.S. registry. We also estimate that it will take about 0.5 work hours per engine to perform the actions, and that the average labor rate is $65 per work hour. No parts are required. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $18,558. 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 14637 (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 Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2006–06–17 Turbomeca: Amendment 39– 14526. Docket No. FAA–2005–22364; Directorate Identifier. 2005–NE–26–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 27, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Arriel 1B, 1D, and 1D1 certain turboshaft engines, modified to the TU 202 standard. These engines are installed on, but not limited to, Eurocopter France AS350BA, AS350B, AS350B1, and AS350B2 helicopters. Unsafe Condition (d) This AD results from one instance of a fractured 2nd stage turbine blade followed by an uncommanded engine shutdown. We are issuing this AD to detect and prevent perforation of the 2nd stage nozzle guide vanes (NGV2) that could cause fracture of a turbine blade that could result in an uncommanded engine in-flight shutdown on a single-engine helicopter. Compliance (e) You are responsible for having the actions required by this AD performed at the next shop visit or the next accessibility of the NGV2 after the effective date of this AD, whichever occurs first, but no later than December 31, 2006, unless the actions have already been done. E:\FR\FM\23MRR1.SGM 23MRR1 14638 Federal Register / Vol. 71, No. 56 / Thursday, March 23, 2006 / Rules and Regulations Inspect NGV2 DEPARTMENT OF TRANSPORTATION (f) Inspect the thickness of the material on each NGV2 using the Instructions to be Incorporated of Turbomeca Mandatory Service Bulletin (MSB) No. A292 72 0231, Update No. 5, dated July 22, 2004. Replace the NGV2 if the vane thickness is below the defined criteria. (g) Inspections carried out before the effective date of this AD, using an earlier update of MSB No. A292 72 0231, are acceptable alternatives to the requirements of this AD. (h) Information regarding NGV2s that have already had the actions required by this AD done and are exempt from the inspections using paragraph (e) of this AD can be found in MSB No. A292 72 0231, Update No. 5, dated July 22, 2004. Definitions (i) For the purposes of this AD the following definitions apply: (1) A shop visit is defined as introduction of the engine into a shop for the purposes of deep maintenance and the separation of a major mating flange. (2) Accessibility of the NGV2 is defined as removal of the NGV2 from the engine regardless of the location or reason for removal. 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 No. F– 2004–088 R1 also addresses the subject of this AD. Material Incorporated by Reference rmajette on PROD1PC67 with RULES (l) You must use Turbomeca Mandatory Service Bulletin No. A292 72 0231, Update No. 5, dated July 22, 2004, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin 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 https://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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on March 16, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–2760 Filed 3–22–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 13:41 Mar 22, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23269; Directorate Identifier 2005–NE–50–AD; Amendment 39– 14525; AD 2006–06–16] RIN 2120–AA64 Airworthiness Directives; Lycoming Engines (Formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, and LO–360 Series Reciprocating Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, and LO–360 series reciprocating engines. This AD requires replacing certain crankshafts. This AD results from a crankshaft failure in a Lycoming LO–360–A1H6 reciprocating engine. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the aircraft. DATES: This AD becomes effective April 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 27, 2006. ADDRESSES: You can get the service information identified in this AD from Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone (570) 323–6181; fax (570) 327–7101, or on the Internet at https:// www.Lycoming.Textron.com. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Norm Perenson, Aerospace Engineer, New York Aircraft Certification Office, FAA, Engine & Propeller Directorate, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7337; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to certain Lycoming Engines (formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, and LO–360 series reciprocating engines. We published the proposed AD in the Federal Register on December 27, 2005 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 (70 FR 76431). That action proposed to require replacing certain crankshafts within 50 hours time-in-service or 6 months after the effective date of this AD, whichever is earlier. 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 Offices 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 received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 282 engines installed on aircraft of U.S. registry. We estimate that it will take the following work hours to perform the inspection and crankshaft replacement: Type of application Constant-Speed Propeller ........ Fixed-Pitch Propeller ............. Work-hours per engine Number of engines affected 86 251 84.5 31 We estimate the average labor rate is $65 per work hour and that required parts for each engine will cost about $15,300. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $5,887,957. Lycoming Engines informed us that they intend to supply the new parts at no charge and reimburse labor costs when authorized, for engine removal and reinstallation, using the current revision of Lycoming’s Removal and Installation Labor Allowance Guidebook. These actions would substantially reduce the estimated cost of this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\23MRR1.SGM 23MRR1

Agencies

[Federal Register Volume 71, Number 56 (Thursday, March 23, 2006)]
[Rules and Regulations]
[Pages 14636-14638]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2760]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22364; Directorate Identifier 2005-NE-26-AD; 
Amendment 39-14526; AD 2006-06-17]
RIN 2120-AA64


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

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines. This AD requires 
inspecting the 2nd stage nozzle guide vanes (NGV2) for wall thickness. 
This AD results from one instance of a fractured 2nd stage turbine 
blade followed by an uncommanded engine shutdown. We are issuing this 
AD to detect and prevent perforation of the NGV2 that could cause 
fracture of a turbine blade that could result in an uncommanded engine 
in-flight shutdown on a single-engine helicopter.

DATES: This AD becomes effective April 27, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of April 27, 2006.

ADDRESSES: You can get the service information identified in this AD 
from Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 
33 05 59 74 45 15.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

[[Page 14637]]


FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
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, 1D, and 1D1 turboshaft engines. We published 
the proposed AD in the Federal Register on November 4, 2005 (70 FR 
67099). That action proposed to require inspecting the NGV2 for wall 
thickness.

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 comment received.

Request To Include an End Date

    One commenter requests that we include an end date in the AD, of 
December 31, 2006. This end date would help manage the risk of failure, 
while causing the least amount of disruption in the form of helicopter 
grounding.
    We agree. We changed compliance paragraph (e) to read ``You are 
responsible for having the actions required by this AD performed at the 
next shop visit or the next accessibility of the NGV2 after the 
effective date of this AD, whichever occurs first, but no later than 
December 31, 2006, unless the actions have already been done.''

Clarification of Unsafe Condition

    For clarification that the AD is applicable to only single-engine 
installations, we changed the unsafe condition in the AD to read ``We 
are issuing this AD to detect and prevent perforation of the 2nd stage 
nozzle guide vanes (NGV2) that could cause fracture of a turbine blade 
that could result in an uncommanded engine in-flight shutdown on a 
single-engine helicopter.''

Conclusion

    We have carefully reviewed the available data, including the 
comment 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.

Costs of Compliance

    We estimate that this AD will affect 571 engines installed on 
helicopters of U.S. registry. We also estimate that it will take about 
0.5 work hours per engine to perform the actions, and that the average 
labor rate is $65 per work hour. No parts are required. Based on these 
figures, we estimate the total cost of the AD to U.S. operators to be 
$18,558.

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:

2006-06-17 Turbomeca: Amendment 39-14526. Docket No. FAA-2005-22364; 
Directorate Identifier. 2005-NE-26-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
27, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 1B, 1D, and 1D1 certain 
turboshaft engines, modified to the TU 202 standard. These engines 
are installed on, but not limited to, Eurocopter France AS350BA, 
AS350B, AS350B1, and AS350B2 helicopters.

Unsafe Condition

    (d) This AD results from one instance of a fractured 2nd stage 
turbine blade followed by an uncommanded engine shutdown. We are 
issuing this AD to detect and prevent perforation of the 2nd stage 
nozzle guide vanes (NGV2) that could cause fracture of a turbine 
blade that could result in an uncommanded engine in-flight shutdown 
on a single-engine helicopter.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next shop visit or the next accessibility of the 
NGV2 after the effective date of this AD, whichever occurs first, 
but no later than December 31, 2006, unless the actions have already 
been done.

[[Page 14638]]

Inspect NGV2

    (f) Inspect the thickness of the material on each NGV2 using the 
Instructions to be Incorporated of Turbomeca Mandatory Service 
Bulletin (MSB) No. A292 72 0231, Update No. 5, dated July 22, 2004. 
Replace the NGV2 if the vane thickness is below the defined 
criteria.
    (g) Inspections carried out before the effective date of this 
AD, using an earlier update of MSB No. A292 72 0231, are acceptable 
alternatives to the requirements of this AD.
    (h) Information regarding NGV2s that have already had the 
actions required by this AD done and are exempt from the inspections 
using paragraph (e) of this AD can be found in MSB No. A292 72 0231, 
Update No. 5, dated July 22, 2004.

Definitions

    (i) For the purposes of this AD the following definitions apply:
    (1) A shop visit is defined as introduction of the engine into a 
shop for the purposes of deep maintenance and the separation of a 
major mating flange.
    (2) Accessibility of the NGV2 is defined as removal of the NGV2 
from the engine regardless of the location or reason for removal.

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 No. F-2004-088 R1 also 
addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Turbomeca Mandatory Service Bulletin No. A292 
72 0231, Update No. 5, dated July 22, 2004, to perform the actions 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin 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 https://
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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on March 16, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-2760 Filed 3-22-06; 8:45 am]
BILLING CODE 4910-13-P

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