Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines, 73579-73581 [05-23831]

Download as PDF Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane. 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. Determine Serial Number (S/N) and Inspect if Necessary (f) Within the applicable compliance time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD: Determine the serial number of the engines installed on the airplane, as identified in the table in paragraph 1.A., ‘‘Effectivity,’’ of Dassault Service Bulletin F2000–299, dated July 23, 2004; if any affected serial number is found on any engine, perform a borescope inspection to verify that a spherical bearing is installed on the attachment fitting of the front engine mount by doing all the applicable actions specified in the Accomplishment Instructions of the service bulletin. (1) For airplanes with any engine having 850 total landings or less as of the effective date of this AD: Before the accumulation of 880 total landings on the engine. (2) For airplanes with any engine having more than 850 total landings, but 1,000 total landings or less as of the effective date of this AD: Within 1 month after the effective date of this AD. (3) For airplanes with any engine having more than 1,000 total landings as of the effective date of this AD: Within 10 landings after the effective date of this AD. Corrective Action (g) If any spherical bearing is found missing during the inspection required by paragraph (f) of this AD: Before further flight, repair according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, ´ ´ FAA; or the Direction Generale de l’Aviation Civile (or its delegated agent). No Reporting Requirement (h) This AD does not require submitting reporting information to the manufacturer. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F–2004– 128, issued August 4, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Dassault Service Bulletin F2000–299, dated July 23, 2004, to perform VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, 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., room PL–401, Nassif Building, Washington, DC; 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 the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 2, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–23829 Filed 12–12–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22928; Directorate Identifier 2005–NE–43–AD; Amendment 39– 14406; AD 2005–25–13] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. This AD requires initial and repetitive visual checks of the free turbine shield for cracks. This AD results from reports of several free turbine shields found with large circumferential cracks. We are issuing this AD to prevent failure of the free turbine shield, leading to engine misalignment, in-flight engine shutdown, emergency autorotation landing, or accident. DATES: Effective December 28, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 28, 2005. We must receive any comments on this AD by February 13, 2006. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 73579 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 Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition might exist on Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. The DGAC advises that on several of these engines, large circumferential cracks were found in the free turbine shield at the blending radius between the containment shield and the rear flange. These cracks could cause a loss of engine alignment during maneuvering loads and lead to in-flight engine shutdown. ADDRESSES: Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Alert Mandatory Service Bulletin No. A292 72 2821, dated June 27, 2005, that describes procedures for visual checks of the free turbine shield for cracks. The DGAC classified this service bulletin as mandatory and issued AD F–2005–162, dated September 28, 2005, in order to ensure the airworthiness of these Arriel 2B and 2B1 engines in France. Bilateral Airworthiness Agreement These Turbomeca Arriel 2B and 2B1 turboshaft engines are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the E:\FR\FM\13DER1.SGM 13DER1 73580 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the DGAC kept the FAA informed of the situation described above. We have examined the findings of the DGAC, 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 Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated, of the same type design. We are issuing this AD to prevent failure of the free turbine shield, leading to engine misalignment, inflight engine shutdown, emergency autorotation landing, or accident. This AD requires initial visual checks of the free turbine shield for cracks within 10 operating hours of the effective date of the AD, repetitive visual checks at certain compliance intervals based on shield condition, and replacement if necessary. This AD also allows incorporation of Turbomeca modification TU22 as optional terminating action to the required repetitive visual checks. 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–2005–22928; Directorate Identifier 2005–NE–43–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. VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 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 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 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. 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 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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. 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 by sending a request to us 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 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: 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: 2005–25–13 Turbomeca: Amendment 39– 14406. Docket No. FAA–2005–22928; Directorate Identifier 2005–NE–43–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. These engines are installed on, but not limited to, Eurocopter France AS350B3 and EC130B4 helicopters. Unsafe Condition (d) This AD results from reports of several free turbine shields found with large circumferential cracks. We are issuing this AD to prevent failure of the free turbine shield, leading to engine misalignment, inflight engine shutdown, emergency autorotation landing, or accident. E:\FR\FM\13DER1.SGM 13DER1 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations 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. Visual Checks (f) Within 10 operating hours after the effective date of this AD: (1) Visually check the free turbine shield for cracks using 2.A. through 2.D.(2) of 73581 Turbomeca Mandatory Service Bulletin (MSB) A292 72 2821, dated June 27, 2005. (2) Replace the free turbine shield or establish a repetitive check interval using the criteria in the following Table 1: TABLE 1.—FREE TURBINE SHIELD CHECK, DISPOSITION CRITERIA Number of cracks: Crack locations using appendix 1 from MSB A292 72 2821: (i) 0 .............................. (ii) 1 ............................. Not Applicable ............ D–A ............................ (iii) 1 ............................. A–B ............................. (5:00 o’clock Area) ..... (iv) 1 ............................ C–D ............................ (8:00 o’clock Area) ..... (v) 2 ............................. One in A–B and one in C–D. (vi) 2 ............................ (vii) 2 ............................ (viii) 2 ........................... (ix) 3 or more ............... Either one or both in D–A. Both in A–B ................ Both in C–D ................ Any ............................. (3) You may treat multiple cracks adjacent to each other as a single crack by using the length measured between the two extremities of the cracks. (4) Single cracks that span two locations must use the location that yields the most conservative re-check interval or replacement requirement. Optional Terminating Action (g) Incorporation of Turbomeca modification TU22 terminates the repetitive visual checks required by this AD. Alternative Methods of Compliance (h) 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 (i) Direction Generale de L’Aviation Civile AD F–2005–162, dated September 28, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Mandatory Service Bulletin A292 72 2821, dated June 27, 2005, 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, VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 Re-check using paragraphs (f)(1) and (f)(2) of this AD, or replace: Crack length: Not Applicable ................................................. (A) Less than 170 mm .................................... (B) Between 170 mm and 200 mm ................ (C) Greater than 200 mm ............................... (A) Less than 201 mm .................................... (B) Between 201 mm and 248 mm ................ (C) Greater than 248 mm ............................... (A) Less than 297 mm .................................... (B) Between 297 mm and 366 mm ................ (C) Greater than 366 mm ............................... (A) Zone 1 using Appendix 3 of MSB A292 72 2821. (B) Zone 2 using Appendix 3 of MSB A292 72 2821. (C) Zone 3 using Appendix 3 of MSB A292 72 2821. Any .................................................................. Re-check shield within 500 N1 cycles. Re-check shield within 100 N1 cycles. Re-check shield daily. Replace shield before further flight. Re-check within 100 cycles. Re-check daily. Replace shield before further flight. Re-check within 100 cycles. Re-check daily. Replace shield before further flight. Re-check within 100 cycles. Any .................................................................. Any .................................................................. Any .................................................................. Replace shield before further flight. Replace shield before further flight. Replace shield before further flight. 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/ibrlocations.html. Issued in Burlington, Massachusetts, on December 5, 2005. Carlos Pestana, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–23831 Filed 12–12–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23004; Directorate Identifier 2005–NE–42–AD; Amendment 39– 14405; AD 2005–25–12] RIN 2120–AA64 Airworthiness Directives; Turbomeca Astazou XIV B and XIV H Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 Re-check daily. Replace shield before further flight. Replace shield before further flight. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Astazou XIV B and XIV H turboshaft engines that have operated with air intake noise suppressors. This AD requires ensuring proper installation of air intake noise suppressors, and ultrasonically inspecting 2nd stage axial compressor wheel blades operated in engines with improperly installed intake noise suppressors. This AD results from several reports of failure of 2nd stage axial compressor wheel blades. We are issuing this AD to prevent failure of 2nd stage axial compressor wheel blades, leading to inflight engine shutdown and autorotation landing. DATES: Effective December 28, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 28, 2005. We must receive any comments on this AD by February 13, 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. E:\FR\FM\13DER1.SGM 13DER1

Agencies

[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73579-73581]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23831]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22928; Directorate Identifier 2005-NE-43-AD; 
Amendment 39-14406; AD 2005-25-13]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft 
Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Turbomeca Arriel 2B and 2B1 turboshaft engines without modification 
TU22 incorporated. This AD requires initial and repetitive visual 
checks of the free turbine shield for cracks. This AD results from 
reports of several free turbine shields found with large 
circumferential cracks. We are issuing this AD to prevent failure of 
the free turbine shield, leading to engine misalignment, in-flight 
engine shutdown, emergency autorotation landing, or accident.

DATES: Effective December 28, 2005. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of December 28, 2005.
    We must receive any comments on this AD by February 13, 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 Direction Generale de L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified us 
that an unsafe condition might exist on Turbomeca Arriel 2B and 2B1 
turboshaft engines without modification TU22 incorporated. The DGAC 
advises that on several of these engines, large circumferential cracks 
were found in the free turbine shield at the blending radius between 
the containment shield and the rear flange. These cracks could cause a 
loss of engine alignment during maneuvering loads and lead to in-flight 
engine shutdown.

Relevant Service Information

    We have reviewed and approved the technical contents of Turbomeca 
Alert Mandatory Service Bulletin No. A292 72 2821, dated June 27, 2005, 
that describes procedures for visual checks of the free turbine shield 
for cracks. The DGAC classified this service bulletin as mandatory and 
issued AD F-2005-162, dated September 28, 2005, in order to ensure the 
airworthiness of these Arriel 2B and 2B1 engines in France.

Bilateral Airworthiness Agreement

    These Turbomeca Arriel 2B and 2B1 turboshaft engines are 
manufactured in France and are type certificated for operation in the 
United States under the provisions of section 21.29 of the

[[Page 73580]]

Federal Aviation Regulations (14 CFR 21.29) and the applicable 
bilateral airworthiness agreement. Under this bilateral airworthiness 
agreement, the DGAC kept the FAA informed of the situation described 
above. We have examined the findings of the DGAC, 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 Turbomeca Arriel 2B and 2B1 turboshaft engines without 
modification TU22 incorporated, of the same type design. We are issuing 
this AD to prevent failure of the free turbine shield, leading to 
engine misalignment, in-flight engine shutdown, emergency autorotation 
landing, or accident. This AD requires initial visual checks of the 
free turbine shield for cracks within 10 operating hours of the 
effective date of the AD, repetitive visual checks at certain 
compliance intervals based on shield condition, and replacement if 
necessary. This AD also allows incorporation of Turbomeca modification 
TU22 as optional terminating action to the required repetitive visual 
checks. 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-2005-22928; 
Directorate Identifier 2005-NE-43-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://
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 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 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.

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 the 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. 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 by 
sending a request to us 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]

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

2005-25-13 Turbomeca: Amendment 39-14406. Docket No. FAA-2005-22928; 
Directorate Identifier 2005-NE-43-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft 
engines without modification TU22 incorporated. These engines are 
installed on, but not limited to, Eurocopter France AS350B3 and 
EC130B4 helicopters.

Unsafe Condition

    (d) This AD results from reports of several free turbine shields 
found with large circumferential cracks. We are issuing this AD to 
prevent failure of the free turbine shield, leading to engine 
misalignment, in-flight engine shutdown, emergency autorotation 
landing, or accident.

[[Page 73581]]

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.

Visual Checks

    (f) Within 10 operating hours after the effective date of this 
AD:
    (1) Visually check the free turbine shield for cracks using 2.A. 
through 2.D.(2) of Turbomeca Mandatory Service Bulletin (MSB) A292 
72 2821, dated June 27, 2005.
    (2) Replace the free turbine shield or establish a repetitive 
check interval using the criteria in the following Table 1:

                            Table 1.--Free Turbine Shield Check, Disposition Criteria
----------------------------------------------------------------------------------------------------------------
                                    Crack locations using                              Re-check using paragraphs
         Number of cracks:           appendix 1 from MSB          Crack length:        (f)(1) and (f)(2) of this
                                        A292 72 2821:                                       AD, or replace:
----------------------------------------------------------------------------------------------------------------
(i) 0.............................  Not Applicable.......  Not Applicable............  Re-check shield within
                                                                                        500 N1 cycles.
(ii) 1............................  D-A..................  (A) Less than 170 mm......  Re-check shield within
                                                                                        100 N1 cycles.
                                                           (B) Between 170 mm and 200  Re-check shield daily.
                                                            mm.
                                                           (C) Greater than 200 mm...  Replace shield before
                                                                                        further flight.
(iii) 1...........................  A-B..................  (A) Less than 201 mm......  Re-check within 100
                                                                                        cycles.
                                    (5:00 o'clock Area)..  (B) Between 201 mm and 248  Re-check daily.
                                                            mm.
                                                           (C) Greater than 248 mm...  Replace shield before
                                                                                        further flight.
(iv) 1............................  C-D..................  (A) Less than 297 mm......  Re-check within 100
                                                                                        cycles.
                                    (8:00 o'clock Area)..  (B) Between 297 mm and 366  Re-check daily.
                                                            mm.
                                                           (C) Greater than 366 mm...  Replace shield before
                                                                                        further flight.
(v) 2.............................  One in A-B and one in  (A) Zone 1 using Appendix   Re-check within 100
                                     C-D.                   3 of MSB A292 72 2821.      cycles.
                                                           (B) Zone 2 using Appendix   Re-check daily.
                                                            3 of MSB A292 72 2821.
                                                           (C) Zone 3 using Appendix   Replace shield before
                                                            3 of MSB A292 72 2821.      further flight.
(vi) 2............................  Either one or both in  Any.......................  Replace shield before
                                     D-A.                                               further flight.
(vii) 2...........................  Both in A-B..........  Any.......................  Replace shield before
                                                                                        further flight.
(viii) 2..........................  Both in C-D..........  Any.......................  Replace shield before
                                                                                        further flight.
(ix) 3 or more....................  Any..................  Any.......................  Replace shield before
                                                                                        further flight.
----------------------------------------------------------------------------------------------------------------

    (3) You may treat multiple cracks adjacent to each other as a 
single crack by using the length measured between the two 
extremities of the cracks.
    (4) Single cracks that span two locations must use the location 
that yields the most conservative re-check interval or replacement 
requirement.

Optional Terminating Action

    (g) Incorporation of Turbomeca modification TU22 terminates the 
repetitive visual checks required by this AD.

Alternative Methods of Compliance

    (h) 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

    (i) Direction Generale de L'Aviation Civile AD F-2005-162, dated 
September 28, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin A292 72 
2821, dated June 27, 2005, 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 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.

    Issued in Burlington, Massachusetts, on December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-23831 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P