Airworthiness Directives; Turbomeca Turmo IV A and IV C Series Turboshaft Engines, 6691-6693 [E6-1768]

Download as PDF Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Proposed Rules with the Accomplishment Instructions of the service bulletin. Do the initial replacement at the applicable compliance time specified in Notes (c) and (d), as applicable, of Table 7 in paragraph 1.E., ‘‘Compliance,’’ of the service bulletin, except as provided by paragraph (g) of this AD. Repeat the replacement thereafter at the applicable interval specified in Notes (c) and (d), as applicable, of Table 7 under paragraph 1.E., ‘‘Compliance,’’ of the service bulletin. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. Issued in Renton, Washington, on January 31, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1767 Filed 2–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–NE–12–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca Turmo IV A and IV C Series Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). wwhite on PROD1PC61 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. That AD currently requires borescope and eddy current inspections or ultrasonic inspections of centrifugal compressor intake wheel blades for cracks and evidence of corrosion pitting, and replacement with serviceable parts. This proposed AD would require the VerDate Aug<31>2005 20:19 Feb 08, 2006 Jkt 208001 same actions, but would require borescope inspections at more frequent intervals for certain engines. This proposed AD results from Turbomeca’s review of the engines’ service experience that determined more frequent borescope inspections are required on engines not modified to the TU 191, TU 197, or TU 224 standard. We are proposing this AD to prevent centrifugal compressor intake wheel blade cracks, which can result in engine in-flight power loss, engine shutdown, or forced landing. DATES: We must receive any comments on this proposed AD by April 10, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 99–NE–12– AD, 12 New England Executive Park, Burlington, MA 01803–5299. • By fax: (781) 238–7055. • By e-mail: 9-aneadcomment@faa.gov. You can get the service information identified in this proposed 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, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 99– NE–12–AD’’ in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. If a person contacts us verbally, and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 6691 will consider all comments received by the closing date and may amend the proposed AD in light of those comments. Examining the AD Docket You may examine the AD Docket (including any comments and serviceinformation), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. Discussion On May 20, 2003, the FAA issued AD 2003–11–09, Amendment 39–13168 (68 FR 31970, May 29, 2003). That AD requires initial and repetitive borescope and eddy current inspections or ultrasonic inspections of centrifugal compressor intake wheel blades for cracks and evidence of corrosion pitting, and, if found cracked or if there is evidence of corrosion pitting, replacement with serviceable parts. The Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Turbomeca Turmo IV A and IV C series turboshaft engines. The DGAC advises that they have received reports of cracked centrifugal compressor intake wheel blades. The phenomena of blade cracking occurs in two phases; initiation after a single event, such as foreign object damage or surge, and crack propagation due to operating at a gas generator speed, between 80 percent and 83 percent, which sets up a vibration. Although the exact cause of the initiation of cracks has not yet been identified, cracks could initiate at corrosion pits. The investigation is continuing. This condition, if not corrected, could result in centrifugal compressor intake wheel blade cracks, which can result in engine in-flight power loss, engine shutdown, or forced landing. Since AD 2003–11–09 required the removal of the TU 197 standard within 6 months after the AD’s effective date of July 3, 2003, the TU 197 standard is no longer allowed. The compliance time in this proposed AD requires removing the TU 197 standard before further flight. Actions Since AD 2003–11–09 Was Issued Since AD 2003–11–09 was issued, Turbomeca reevaluated the engines’ service experience and reduced the borescope inspection interval for engines not modified to the TU 191, TU 197, or TU 224 standard, from 250 flight hours-since-last inspection to 200 flight hours-since-last inspection. Also, E:\FR\FM\09FEP1.SGM 09FEP1 6692 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Proposed Rules Turbomeca eliminated the TU 197 standard as a valid modification. Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Mandatory Service Bulletin (MSB) A249 72 0100, Update No. 5, dated February 25, 2005, that describes procedures for the centrifugal compressor intake wheel blade borescope inspections. The DGAC classified this MSB as mandatory and issued AD F–2005–037, dated March 2, 2005, in order to ensure the airworthiness of these engines in France. Bilateral Agreement Information This engine model is manufactured in France and is type certificated for operation in the United States under the provisions of Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. In keeping with this bilateral airworthiness agreement, the DGAC has 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. wwhite on PROD1PC61 with PROPOSALS FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Therefore, we are proposing this AD, which would require: • For engines modified to the TU 197 standard but not to the TU 191 standard or TU 224 standard, before further flight, removing the TU 197 standard and installing the TU 224 standard. • Initial and repetitive borescope and eddy current or ultrasonic inspections of centrifugal compressor intake wheel blades for cracks and evidence of corrosion pitting. • Removing centrifugal compressor intake wheel blades confirmed cracked or pitted. The proposed AD would require that you do these actions using the service information described previously. Costs of Compliance We estimate that this proposed AD would affect 36 Turbomeca Turmo IV A and IV C series turboshaft engines installed on helicopters of U.S. registry. We also estimate that it would take about 41 work hours per engine to perform the proposed inspections, VerDate Aug<31>2005 20:19 Feb 08, 2006 Jkt 208001 including disassembling and assembling engines, and that the average labor rate is $65 per work hour. A replacement centrifugal compressor assembly costs about $21,651. Based on these figures, the cost per inspection and replacement is estimated to be $24,316. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $875,390. Special Flight Permits Paragraph Removed Paragraph (e) of the current AD, AD 2003–11–09, contains a paragraph pertaining to special flight permits. Even though this proposed AD does not contain a similar paragraph, we have made no changes with regard to the use of special flight permits to operate the helicopter to a repair facility to do the work required by this AD. In July 2002, we published a new Part 39 that contains a general authority regarding special flight permits and airworthiness directives; see Docket No. FAA–2004– 8460, Amendment 39–9474 (69 FR 47998, July 22, 2002). Thus, when we now supersede ADs we will not include a specific paragraph on special flight permits unless we want to limit the use of that general authority granted in section 39.23. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this proposal 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. Include ‘‘AD Docket No. 99– NE–12–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–13168 (68 FR 31970, May 29, 2003) and by adding a new airworthiness directive, to read as follows: Turbomeca: Docket No. 99–NE–12–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by April 10, 2006. Affected ADs (b) This AD supersedes AD 2003–11–09, Amendment 39–39–13168. Applicability (c) This AD applies to Turbomeca Turmo IV A and IV C series turboshaft engines. These engines are installed on but not limited to Aerospatiale SA 330—PUMA helicopters. Unsafe Condition (d) This AD results from Turbomeca’s review of the engines’ service experience that determined more frequent borescope inspections are required on engines not modified to the TU 191, TU 197, or TU 224 standard. The actions specified in this AD are E:\FR\FM\09FEP1.SGM 09FEP1 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Proposed Rules intended to prevent centrifugal compressor intake wheel blade cracks, which can result in engine in-flight power loss, engine shutdown, or forced 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. Engine Modification Before Further Flight (f) For engines modified to the TU 197 standard but not to the TU 191 or TU 224 standard, before further flight, remove the TU 197 standard and install the TU 224 standard. Initial Inspections (g) For all engines, borescope-inspect, and either eddy current-inspect (ECI) or 6693 ultrasonic-inspect (UI) the centrifugal compressor intake wheel blades using paragraphs 2.B.(1)(a) through 2.B.(1)(g) of Turbomeca Mandatory Service Bulletin A249 72 0100, Update No. 5, dated February 25, 2005, and the criteria in the following Table 1: TABLE 1.—INSPECTION CRITERIA Then borescope-inspect centrifugal compressor intake wheel blades: If engine modification level is: (1) Pre TU 191 and Pre TU 224 .... Were traces of corrosion found at borescope-inspection? Then confirm corrosion by performing ECI or UI within: Within 200 flight hours-since-last inspection. (i) Yes ........................................... Six months-or 50 flight hourssince-borescope inspection, whichever occurs first. Two hundred flight hours-sinceborescope inspection. Six months-or 50 flight hourssince-borescope inspection, whichever occurs first. One thousand flight hours-sinceborescope inspection. (ii) No ............................................ (2) Post TU 191 or Post TU 224 ... Within 1,000 flight hours-since-last inspection. (i) Yes ........................................... (ii) No ............................................ (h) Thereafter, perform repetitive inspections using the criteria in Table 1 of this AD. (i) Remove centrifugal compressor intake wheel blades confirmed cracked or pitted. DEPARTMENT OF ENERGY Alternative Methods of Compliance 18 CFR Part 40 (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. [Docket Nos. RM06–8–000 and AD05–7–000] Related Information (k) Direction Generale de L’Aviation Civile airworthiness directive F–2005–037, dated March 2, 2005, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on February 3, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–1768 Filed 2–8–06; 8:45 am] wwhite on PROD1PC61 with PROPOSALS BILLING CODE 4910–13–P VerDate Aug<31>2005 20:19 Feb 08, 2006 Jkt 208001 Federal Energy Regulatory Commission Long-Term Firm Transmission Rights in Organized Electricity Markets; LongTerm Transmission Rights in Markets Operated by Regional Transmission Organizations and Independent System Operators February 2, 2006. Federal Energy Regulatory Commission. ACTION: Notice of Proposed Rulemaking. AGENCY: SUMMARY: The Federal Energy Regulatory Commission is proposing to amend its regulations to require transmission organizations that are public utilities with organized electricity markets to make available long-term firm transmission rights that satisfy certain guidelines established in this proceeding. The Commission is taking this action pursuant to section 1233(b) of the Energy Policy Act of 2005, Public Law No. 109–58, section 1233(b), 119 Stat. 594, 960 (2005). DATES: Comments are due March 13, 2006. Reply comments are due March 27, 2006. FOR FURTHER INFORMATION CONTACT: Udi E. Helman (Technical Information), Office of Energy Markets and Reliability, Federal Energy Regulatory Commission, 888 First Street, NE., PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Washington, DC 20426, (202) 502– 8080. Roland Wentworth (Technical Information), Office of Energy Markets and Reliability, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, (202) 502–8262. Wilbur C. Earley (Technical Information), Office of Energy Markets and Reliability, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, (202) 502–8087. Harry Singh (Technical Information), Office of Market Oversight and Investigations, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, (202) 502–6341. Jeffery S. Dennis (Legal Information), Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, (202) 502–6027. SUPPLEMENTARY INFORMATION: I. Introduction 1. On August 8, 2005, the Energy Policy Act of 2005 (EPAct 2005) 1 became law. Pursuant to the requirement in section 1233 of EPAct 2005,2 which added a new section 217 to the Federal Power Act (FPA), the Commission is proposing to amend its regulations to require each transmission organization that is a public utility with one or more organized electricity markets to make available long-term 1 Pub. 2 Pub. E:\FR\FM\09FEP1.SGM L. 109–58, 119 Stat. 594 (2005). L. 109–58, § 1233(b), 119 Stat. 594, 960. 09FEP1

Agencies

[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Proposed Rules]
[Pages 6691-6693]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1768]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-12-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Turmo IV A and IV C Series 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft 
engines. That AD currently requires borescope and eddy current 
inspections or ultrasonic inspections of centrifugal compressor intake 
wheel blades for cracks and evidence of corrosion pitting, and 
replacement with serviceable parts. This proposed AD would require the 
same actions, but would require borescope inspections at more frequent 
intervals for certain engines. This proposed AD results from 
Turbomeca's review of the engines' service experience that determined 
more frequent borescope inspections are required on engines not 
modified to the TU 191, TU 197, or TU 224 standard. We are proposing 
this AD to prevent centrifugal compressor intake wheel blade cracks, 
which can result in engine in-flight power loss, engine shutdown, or 
forced landing.

DATES: We must receive any comments on this proposed AD by April 10, 
2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 99-NE-12-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: 9-ane-adcomment@faa.gov.
    You can get the service information identified in this proposed 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, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 99-NE-12-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. If a person contacts us verbally, and that contact relates to a 
substantive part of this proposed AD, we will summarize the contact and 
place the summary in the docket. We will consider all comments received 
by the closing date and may amend the proposed AD in light of those 
comments.

Examining the AD Docket

    You may examine the AD Docket (including any comments and 
serviceinformation), by appointment, between 8 a.m. and 4:30 p.m., 
Monday through Friday, except Federal holidays. See ADDRESSES for the 
location.

Discussion

    On May 20, 2003, the FAA issued AD 2003-11-09, Amendment 39-13168 
(68 FR 31970, May 29, 2003). That AD requires initial and repetitive 
borescope and eddy current inspections or ultrasonic inspections of 
centrifugal compressor intake wheel blades for cracks and evidence of 
corrosion pitting, and, if found cracked or if there is evidence of 
corrosion pitting, replacement with serviceable parts. The Direction 
Generale de L'Aviation Civile (DGAC), which is the airworthiness 
authority for France, notified the FAA that an unsafe condition may 
exist on Turbomeca Turmo IV A and IV C series turboshaft engines. The 
DGAC advises that they have received reports of cracked centrifugal 
compressor intake wheel blades.
    The phenomena of blade cracking occurs in two phases; initiation 
after a single event, such as foreign object damage or surge, and crack 
propagation due to operating at a gas generator speed, between 80 
percent and 83 percent, which sets up a vibration. Although the exact 
cause of the initiation of cracks has not yet been identified, cracks 
could initiate at corrosion pits. The investigation is continuing. This 
condition, if not corrected, could result in centrifugal compressor 
intake wheel blade cracks, which can result in engine in-flight power 
loss, engine shutdown, or forced landing.
    Since AD 2003-11-09 required the removal of the TU 197 standard 
within 6 months after the AD's effective date of July 3, 2003, the TU 
197 standard is no longer allowed. The compliance time in this proposed 
AD requires removing the TU 197 standard before further flight.

Actions Since AD 2003-11-09 Was Issued

    Since AD 2003-11-09 was issued, Turbomeca reevaluated the engines' 
service experience and reduced the borescope inspection interval for 
engines not modified to the TU 191, TU 197, or TU 224 standard, from 
250 flight hours-since-last inspection to 200 flight hours-since-last 
inspection. Also,

[[Page 6692]]

Turbomeca eliminated the TU 197 standard as a valid modification.

Relevant Service Information

    We have reviewed and approved the technical contents of Turbomeca 
Mandatory Service Bulletin (MSB) A249 72 0100, Update No. 5, dated 
February 25, 2005, that describes procedures for the centrifugal 
compressor intake wheel blade borescope inspections. The DGAC 
classified this MSB as mandatory and issued AD F-2005-037, dated March 
2, 2005, in order to ensure the airworthiness of these engines in 
France.

Bilateral Agreement Information

    This engine model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. In keeping with this 
bilateral airworthiness agreement, the DGAC has 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 the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would require:
     For engines modified to the TU 197 standard but not to the 
TU 191 standard or TU 224 standard, before further flight, removing the 
TU 197 standard and installing the TU 224 standard.
     Initial and repetitive borescope and eddy current or 
ultrasonic inspections of centrifugal compressor intake wheel blades 
for cracks and evidence of corrosion pitting.
     Removing centrifugal compressor intake wheel blades 
confirmed cracked or pitted.
    The proposed AD would require that you do these actions using the 
service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 36 Turbomeca Turmo 
IV A and IV C series turboshaft engines installed on helicopters of 
U.S. registry. We also estimate that it would take about 41 work hours 
per engine to perform the proposed inspections, including disassembling 
and assembling engines, and that the average labor rate is $65 per work 
hour. A replacement centrifugal compressor assembly costs about 
$21,651. Based on these figures, the cost per inspection and 
replacement is estimated to be $24,316. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$875,390.

Special Flight Permits Paragraph Removed

    Paragraph (e) of the current AD, AD 2003-11-09, contains a 
paragraph pertaining to special flight permits. Even though this 
proposed AD does not contain a similar paragraph, we have made no 
changes with regard to the use of special flight permits to operate the 
helicopter to a repair facility to do the work required by this AD. In 
July 2002, we published a new Part 39 that contains a general authority 
regarding special flight permits and airworthiness directives; see 
Docket No. FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 
2002). Thus, when we now supersede ADs we will not include a specific 
paragraph on special flight permits unless we want to limit the use of 
that general authority granted in section 39.23.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this proposal 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. Include 
``AD Docket No. 99-NE-12-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-13168 (68 FR 
31970, May 29, 2003) and by adding a new airworthiness directive, to 
read as follows:

Turbomeca: Docket No. 99-NE-12-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 10, 
2006.

Affected ADs

    (b) This AD supersedes AD 2003-11-09, Amendment 39-39-13168.

Applicability

    (c) This AD applies to Turbomeca Turmo IV A and IV C series 
turboshaft engines. These engines are installed on but not limited 
to Aerospatiale SA 330--PUMA helicopters.

Unsafe Condition

    (d) This AD results from Turbomeca's review of the engines' 
service experience that determined more frequent borescope 
inspections are required on engines not modified to the TU 191, TU 
197, or TU 224 standard. The actions specified in this AD are

[[Page 6693]]

intended to prevent centrifugal compressor intake wheel blade 
cracks, which can result in engine in-flight power loss, engine 
shutdown, or forced 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.

Engine Modification Before Further Flight

    (f) For engines modified to the TU 197 standard but not to the 
TU 191 or TU 224 standard, before further flight, remove the TU 197 
standard and install the TU 224 standard.

Initial Inspections

    (g) For all engines, borescope-inspect, and either eddy current-
inspect (ECI) or ultrasonic-inspect (UI) the centrifugal compressor 
intake wheel blades using paragraphs 2.B.(1)(a) through 2.B.(1)(g) 
of Turbomeca Mandatory Service Bulletin A249 72 0100, Update No. 5, 
dated February 25, 2005, and the criteria in the following Table 1:

                                          Table 1.--Inspection Criteria
----------------------------------------------------------------------------------------------------------------
                                        Then borescope-inspect       Were traces of       Then confirm corrosion
   If engine modification level is:     centrifugal compressor     corrosion found at    by performing ECI or UI
                                         intake wheel blades:    borescope-inspection?           within:
----------------------------------------------------------------------------------------------------------------
(1) Pre TU 191 and Pre TU 224........  Within 200 flight hours- (i) Yes................  Six months-or 50 flight
                                        since-last inspection.                            hours-since-borescope
                                                                                          inspection, whichever
                                                                                          occurs first.
                                                                (ii) No................  Two hundred flight
                                                                                          hours-since-borescope
                                                                                          inspection.
(2) Post TU 191 or Post TU 224.......  Within 1,000 flight      (i) Yes................  Six months-or 50 flight
                                        hours-since-last                                  hours-since-borescope
                                        inspection.                                       inspection, whichever
                                                                                          occurs first.
                                                                (ii) No................  One thousand flight
                                                                                          hours-since-borescope
                                                                                          inspection.
----------------------------------------------------------------------------------------------------------------

    (h) Thereafter, perform repetitive inspections using the 
criteria in Table 1 of this AD.
    (i) Remove centrifugal compressor intake wheel blades confirmed 
cracked or pitted.

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) Direction Generale de L'Aviation Civile airworthiness 
directive F-2005-037, dated March 2, 2005, also addresses the 
subject of this AD.

    Issued in Burlington, Massachusetts, on February 3, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-1768 Filed 2-8-06; 8:45 am]
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