Airworthiness Directives; Turbomeca Astazou XIV B and XIV H Turboshaft Engines, 73581-73583 [05-23827]

Download as PDF 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 73582 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations • 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 Astazou XIV B and XIV H turboshaft engines that have operated with an air intake noise suppressor. The DGAC advises that several cases of failure of 2nd stage axial compressor wheel blades have occurred in service. An investigation revealed that these failures result from aerodynamicinduced stresses caused by improperly installed air intake noise suppressors. An improperly installed air intake noise suppressor has too great an angular position on the air intake casing. This in turn results in downstream airflow turbulence causing high stresses in the 2nd stage axial compressor wheel blades. Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Alert Service Bulletin (ASB) No. A283 72 0800, dated February 5, 2004, that describes instructions for ultrasonic inspection of 2nd stage axial compressor wheel blades. The DGAC classified this alert service bulletin as mandatory and issued AD F–2004–029, dated February 18, 2004, in order to ensure the airworthiness of these Astazou XIV B and XIV H turboshaft engines in France. Bilateral Airworthiness Agreement These Astazou XIV B and XIV H 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 Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 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 Astazou XIV B and XIV H turboshaft engines of the same type design. We are issuing this AD to prevent failure of 2nd stage axial compressor wheel blades, leading to inflight engine shutdown and autorotation landing. This AD requires: • Before further flight, ensuring proper installation of air intake noise suppressors; and • For engines operated with improperly installed air intake noise suppressors, removing the engine and performing an ultrasonic inspection of 2nd stage axial compressor wheel blades, within 50 flight hours or 6 months after the effective date of this AD, whichever occurs first, and replacing blades that fail inspection. You must use the service information described previously to perform the removals, blade inspections, replacements, and installations 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–2005–23004; Directorate Identifier 2005–NE–42–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:// PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 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 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. 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. E:\FR\FM\13DER1.SGM 13DER1 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations 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: § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2005–25–12 Turbomeca: Amendment 39– 14405. Docket No. FAA–2005–23004; Directorate Identifier 2005–NE–42–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Astazou XIV B and XIV H turboshaft engines that have operated with air intake noise suppressors. These engines are installed on, but not limited to, single-engine Aerospatiale AS319B ‘‘Alouette III’’ and AS342J ‘‘Gazelle’’ helicopters. Unsafe Condition (d) 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 in-flight engine shutdown and autorotation landing. Compliance (e) You are responsible for having the actions required by this AD performed within VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 the compliance times specified unless the actions have already been done. DEPARTMENT OF TRANSPORTATION Ensure Proper Installation of Air Intake Noise Suppressors Federal Aviation Administration (f) Before further flight, ensure proper installation of air intake noise suppressors. (g) You can find information on doing this in aircraft maintenance manual (AMM) section 71–30–41 for Aerospatiale AS319B helicopters, and in AMM section 71–61–401 for Aerospatiale AS342J helicopters. Engines That Operated With Improperly Installed Air Intake Noise Suppressors (h) For engines that operated with improperly installed air intake noise suppressors: (1) Perform an ultrasonic inspection of 2nd stage axial compressor wheel blades, within 50 flight hours or 6 months after the effective date of this AD, whichever occurs first, and replace blades that fail inspection. (2) Use 2.B.(1) through 2.B.(2)(b) of Turbomeca Alert Service Bulletin No. A283 72 0800, dated February 5, 2004, to do the inspection. Alternative Methods of Compliance (i) 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 Authority: 49 U.S.C. 106(g), 40113, 44701. 73583 (j) Direction Generale de L’Aviation Civile airworthiness directive F–2004–029, dated February 18, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Turbomeca Alert Service Bulletin No. A283 72 0800, dated February 5, 2004, to perform the removals, blade inspections, replacements, and installations 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/federalregister/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. 05–23827 Filed 12–12–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2005–22290; Directorate Identifier 2005–NM–129–AD; Amendment 39–14407; AD 2005–25–14] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. This AD requires modifying the wiring of the starter-generator terminal block. This AD results from a report of total electrical failure just as the airplane landed. We are issuing this AD to prevent total electrical failure and consequent reduced controllability of the airplane. DATES: This AD becomes effective January 17, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 17, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC. Contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at E:\FR\FM\13DER1.SGM 13DER1

Agencies

[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73581-73583]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23827]


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

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

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 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 in-flight 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.

[[Page 73582]]

     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 Astazou XIV B and XIV 
H turboshaft engines that have operated with an air intake noise 
suppressor. The DGAC advises that several cases of failure of 2nd stage 
axial compressor wheel blades have occurred in service. An 
investigation revealed that these failures result from aerodynamic-
induced stresses caused by improperly installed air intake noise 
suppressors. An improperly installed air intake noise suppressor has 
too great an angular position on the air intake casing. This in turn 
results in downstream airflow turbulence causing high stresses in the 
2nd stage axial compressor wheel blades.

Relevant Service Information

    We have reviewed and approved the technical contents of Turbomeca 
Alert Service Bulletin (ASB) No. A283 72 0800, dated February 5, 2004, 
that describes instructions for ultrasonic inspection of 2nd stage 
axial compressor wheel blades. The DGAC classified this alert service 
bulletin as mandatory and issued AD F-2004-029, dated February 18, 
2004, in order to ensure the airworthiness of these Astazou XIV B and 
XIV H turboshaft engines in France.

Bilateral Airworthiness Agreement

    These Astazou XIV B and XIV H 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 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 Astazou XIV B and XIV H turboshaft engines 
of the same type design. We are issuing this AD to prevent failure of 
2nd stage axial compressor wheel blades, leading to in-flight engine 
shutdown and autorotation landing. This AD requires:
     Before further flight, ensuring proper installation of air 
intake noise suppressors; and
     For engines operated with improperly installed air intake 
noise suppressors, removing the engine and performing an ultrasonic 
inspection of 2nd stage axial compressor wheel blades, within 50 flight 
hours or 6 months after the effective date of this AD, whichever occurs 
first, and replacing blades that fail inspection.

You must use the service information described previously to perform 
the removals, blade inspections, replacements, and installations 
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-2005-23004; 
Directorate Identifier 2005-NE-42-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 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.

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.

[[Page 73583]]

    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

    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:

2005-25-12 Turbomeca: Amendment 39-14405. Docket No. FAA-2005-23004; 
Directorate Identifier 2005-NE-42-AD.

Effective Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Astazou XIV B and XIV H 
turboshaft engines that have operated with air intake noise 
suppressors. These engines are installed on, but not limited to, 
single-engine Aerospatiale AS319B ``Alouette III'' and AS342J 
``Gazelle'' helicopters.

Unsafe Condition

    (d) 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 in-
flight engine shutdown and autorotation landing.

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.

Ensure Proper Installation of Air Intake Noise Suppressors

    (f) Before further flight, ensure proper installation of air 
intake noise suppressors.
    (g) You can find information on doing this in aircraft 
maintenance manual (AMM) section 71-30-41 for Aerospatiale AS319B 
helicopters, and in AMM section 71-61-401 for Aerospatiale AS342J 
helicopters.

Engines That Operated With Improperly Installed Air Intake Noise 
Suppressors

    (h) For engines that operated with improperly installed air 
intake noise suppressors:
    (1) Perform an ultrasonic inspection of 2nd stage axial 
compressor wheel blades, within 50 flight hours or 6 months after 
the effective date of this AD, whichever occurs first, and replace 
blades that fail inspection.
    (2) Use 2.B.(1) through 2.B.(2)(b) of Turbomeca Alert Service 
Bulletin No. A283 72 0800, dated February 5, 2004, to do the 
inspection.

Alternative Methods of Compliance

    (i) 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

    (j) Direction Generale de L'Aviation Civile airworthiness 
directive F-2004-029, dated February 18, 2004, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (k) You must use Turbomeca Alert Service Bulletin No. A283 72 
0800, dated February 5, 2004, to perform the removals, blade 
inspections, replacements, and installations 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. 05-23827 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P