Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C30, 250-C40, and 250-C47 Series Turboshaft Engines, 4065-4067 [E6-898]

Download as PDF Federal Register / Vol. 71, No. 16 / Wednesday, January 25, 2006 / Proposed Rules 4065 TABLE 1.—COMPLIANCE TIMES TO REPLACE FACS—Continued Airplane model/series Required compliance time after the effective date of this AD Configuration And without accomplishment of Airbus Service Bulletin A310–22–2058, dated April 6, 2005, or Modification 12931. Part Installation (h) On or after the effective date of this AD, no person may install, on any airplane, any FAC having P/N B471AAM7 (for Model A300–600 series airplanes) or FAC P/N B471ABM4 (for Model A310 series airplanes), unless the FAC is in compliance with this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 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) The subject of this AD is addressed in French airworthiness directives F–2005–111 R1, dated December 21, 2005, and F–2000– 115–304 R5, dated July 6, 2005. Issued in Renton, Washington, on January 17, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–897 Filed 1–24–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23392; Directorate Identifier 2005–NE–47–AD] RIN 2120–AA64 cprice-sewell on PROD1PC66 with PROPOSALS Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250–C30, 250–C40, and 250– C47 Series Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for VerDate Aug<31>2005 15:04 Jan 24, 2006 Jkt 208001 Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) models 250–C30, 250– 40, and 250–C47 series turboshaft engines. This proposed AD would add an additional life limit for third- and fourth-stage turbine wheels. This proposed AD results from analysis by RRC of failures of third- and fourth-stage turbine wheels. We are proposing this AD to prevent loss of power, possible engine shutdown, or uncontained failure. DATES: We must receive any comments on this proposed AD by March 27, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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 Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206–0420; telephone (317) 230–6400; fax (317) 230–4243, for the service information identified in this proposed AD. You may examine the comments on this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; telephone (847) 294–8180; fax (847) 294–7834. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send us any written relevant data, views, or arguments PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–23392; Directorate Identifier 2005–NE–47–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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 proposed AD. Using the search function of the DOT 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 https:// dms.dot.gov. Examining the AD Docket You may examine the docket that contains the proposal, any comments received and, any final disposition in person at the DOT 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 Docket Management Facility receives them. Discussion Rolls-Royce Corporation investigated and analyzed nine failures of third- and fourth-stage turbine wheels, installed in models 250–C30, 250–40, and 250–C47 series turboshaft engines. The analysis revealed that third- and fourth-stage turbine wheels can prematurely fail if they are operated too many times in the E:\FR\FM\25JAP1.SGM 25JAP1 4066 Federal Register / Vol. 71, No. 16 / Wednesday, January 25, 2006 / Proposed Rules transient overspeed region. This condition, if not corrected, could result in loss of power, possible engine shutdown, or uncontained engine failure. Relevant Service Information We have reviewed and approved the technical contents of RRC Alert Commercial Engine Bulletins (CEBs) No. CEB A–72–3272 (250–C30 series engines), No. CEB A–72–5048 (250–C40 series engines), and No. CEB A–72–6054 (250–C47 series engines), all Revision 1, all dated July 1, 2005 (combined in one document). These Alert CEBs contain revised transient overspeed limit tables, and include the steady-state avoidance range and new transient event thresholds. These Alert CEBs also include requirements to record events exceeding the ‘‘Event Threshold’’. 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. We are proposing this AD, which would require recording the number of times the third- and fourthstage turbine wheels enter into the speed range between ‘‘Event Threshold’’ and ‘‘Maximum Overspeed Transient’’. This proposed AD would also require retiring and replacing third- and fourthstage turbine wheels that accumulate six transient overspeed events based on certain duration and speed parameters. The proposed AD would require you to use the service information described previously to perform these actions. cprice-sewell on PROD1PC66 with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect 1,300 engines installed on airplanes of U.S. registry. We also estimate that it would take about 42 work hours per engine to replace the third- and fourth-stage turbine wheels, and that the average labor rate is $65 per work hour. Required parts would cost about $25,000 per engine. We estimate that only 10% of all turbine wheel replacements would result from operators exceeding the new transient overspeed event limits. Based on these figures, we estimate the total potential maximum cost of the proposed AD to U.S. operators to be $3,604,900. 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 VerDate Aug<31>2005 15:04 Jan 24, 2006 Jkt 208001 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment 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 adding the following new airworthiness directive: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Rolls-Royce Corporation: Docket No. FAA– 2005–23392; Directorate Identifier 2005– NE–47–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by March 27, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) models 250– C30, 250–40, and 250–C47 series turboshaft engines. These engines are installed on, but not limited to, Bell 206L–3, Bell 206L–4, Bell 407, MDHI 369F, MDHI 369FF, MDHI 600N, and Sikorsky S–76A helicopters. Unsafe Condition (d) This AD results from analysis by RRC of failures of third- and fourth-stage turbine wheels. We are issuing this AD to prevent loss of power, possible engine shutdown, or uncontained failure. 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. (f) Within 30 days after the effective date of this AD, record each time the third- and fourth-stage turbine wheels enter into the speed range between ‘‘Event Threshold’’ and ‘‘Maximum Overspeed Transient’’. Use paragraph 2.A. through 2.A.(5) of the Accomplishment Instructions and the applicable Figures 1 through 5 of RRC Alert Commercial Engine Bulletins (CEBs) No. CEB A–72–3272, No. CEB A–72–5048, and No. CEB A–72–6054, all Revision 1, all dated July 1, 2005 (combined in one document) to determine the speed range. (g) Remove and retire any third-stage turbine wheel or fourth-stage turbine wheel after the sixth time the wheel enters into the speed range between ‘‘Event Threshold’’ and ‘‘Maximum Overspeed Transient’’. Third- and Fourth-Stage Turbine Wheel Life Limits (h) The retirement criteria in this AD are in addition to the existing third- and fourthstage turbine wheel hour and cycle life limits. You must retire the wheels when you exceed any published life limit (transient speed excursions, hours, or cycles). Alternative Methods of Compliance (i) The Manager, Chicago Aircraft 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) None. E:\FR\FM\25JAP1.SGM 25JAP1 Federal Register / Vol. 71, No. 16 / Wednesday, January 25, 2006 / Proposed Rules Issued in Burlington, Massachusetts, on January 18, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–898 Filed 1–24–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23673; Directorate Identifier 2005–NM–233–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 and EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). cprice-sewell on PROD1PC66 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all EMBRAER Model EMB–135 and EMB– 145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This proposed AD would require inspecting to determine the part number of the ailerons. For airplanes with affected aileron part numbers, this proposed AD would require reworking the aileron damper fitting. For certain airplanes, this proposed AD would also require replacing the rod end of the aileron damper assembly with an improved rod end. This proposed AD results from reports of structural failure of the rod end of the aileron damper, which was caused by insufficient clearance between the lugs of the aileron damper fitting and the rod end of the aileron damper. We are proposing this AD to prevent failure of the aileron damper, which could result in failure of the aileron actuator and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by February 24, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. VerDate Aug<31>2005 15:04 Jan 24, 2006 Jkt 208001 • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this proposed 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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–23673; Directorate Identifier 2005–NM–233–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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 proposed AD. Using the search function of that 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 https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 4067 Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The Departmento de Aviacao Civil (DAC), which is the airworthiness authority for Brazil, notified us that an unsafe condition may exist on all EMBRAER Model EMB–135 and EMB– 145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. The DAC advises of reports indicating structural failure of the rod ends of the aileron damper. This failure has been attributed to insufficient clearance between the lugs of the aileron damper fitting and the rod end of the aileron damper. The insufficient clearance is associated with improper clearance between the rod end and its bearing race. A failed rod end is a hidden failure of the aileron damper. Flutter caused by failure of the aileron damper could result in failure of the aileron actuator. This condition, if not corrected, could result in reduced controllability of the airplane. Relevant Service Information EMBRAER has issued Service Bulletin 145–27–0108, Revision 01, dated April 28, 2005, which is effective for airplanes that are equipped with an affected aileron. The service bulletin describes procedures for reworking the aileron damper fitting on the left- and righthand sides of the airplane. For aileron dampers with certain part numbers and serial numbers, the service bulletin also describes procedures for replacing the rod end of the aileron damper assembly with an improved rod end on the leftand right-hand sides of the airplane. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DAC mandated the service information and issued Brazilian airworthiness directive 2005–10–04, dated November 17, 2005, to ensure the continued airworthiness of these airplanes in Brazil. The EMBRAER service bulletin refers to Textron Service Bulletin 41012130– 27–02, dated July 12, 2004, as an additional source of service information for replacing the rod end of the aileron damper assembly. The Textron service bulletin is included within the pages of the EMBRAER service bulletin. E:\FR\FM\25JAP1.SGM 25JAP1

Agencies

[Federal Register Volume 71, Number 16 (Wednesday, January 25, 2006)]
[Proposed Rules]
[Pages 4065-4067]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-898]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23392; Directorate Identifier 2005-NE-47-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company, Allison Gas Turbine Division, and Detroit 
Diesel Allison) Models 250-C30, 250-C40, and 250-C47 Series Turboshaft 
Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Rolls-Royce Corporation (formerly Allison Engine Company, Allison 
Gas Turbine Division, and Detroit Diesel Allison) (RRC) models 250-C30, 
250-40, and 250-C47 series turboshaft engines. This proposed AD would 
add an additional life limit for third- and fourth-stage turbine 
wheels. This proposed AD results from analysis by RRC of failures of 
third- and fourth-stage turbine wheels. We are proposing this AD to 
prevent loss of power, possible engine shutdown, or uncontained 
failure.

DATES: We must receive any comments on this proposed AD by March 27, 
2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
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 Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 
46206-0420; telephone (317) 230-6400; fax (317) 230-4243, for the 
service information identified in this proposed AD.
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des 
Plaines, IL 60018-4696; telephone (847) 294-8180; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-23392; 
Directorate Identifier 2005-NE-47-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
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 proposed AD. Using the search function of the 
DOT 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 https://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received and, any final disposition in person at the DOT 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 Docket Management Facility receives 
them.

Discussion

    Rolls-Royce Corporation investigated and analyzed nine failures of 
third- and fourth-stage turbine wheels, installed in models 250-C30, 
250-40, and 250-C47 series turboshaft engines. The analysis revealed 
that third- and fourth-stage turbine wheels can prematurely fail if 
they are operated too many times in the

[[Page 4066]]

transient overspeed region. This condition, if not corrected, could 
result in loss of power, possible engine shutdown, or uncontained 
engine failure.

Relevant Service Information

    We have reviewed and approved the technical contents of RRC Alert 
Commercial Engine Bulletins (CEBs) No. CEB A-72-3272 (250-C30 series 
engines), No. CEB A-72-5048 (250-C40 series engines), and No. CEB A-72-
6054 (250-C47 series engines), all Revision 1, all dated July 1, 2005 
(combined in one document). These Alert CEBs contain revised transient 
overspeed limit tables, and include the steady-state avoidance range 
and new transient event thresholds. These Alert CEBs also include 
requirements to record events exceeding the ``Event Threshold''.

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. We are proposing this AD, which would require 
recording the number of times the third- and fourth-stage turbine 
wheels enter into the speed range between ``Event Threshold'' and 
``Maximum Overspeed Transient''. This proposed AD would also require 
retiring and replacing third- and fourth-stage turbine wheels that 
accumulate six transient overspeed events based on certain duration and 
speed parameters. The proposed AD would require you to use the service 
information described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 1,300 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 42 work hours per engine to replace the third- and fourth-
stage turbine wheels, and that the average labor rate is $65 per work 
hour. Required parts would cost about $25,000 per engine. We estimate 
that only 10% of all turbine wheel replacements would result from 
operators exceeding the new transient overspeed event limits. Based on 
these figures, we estimate the total potential maximum cost of the 
proposed AD to U.S. operators to be $3,604,900.

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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    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 adding the following new 
airworthiness directive:

Rolls-Royce Corporation: Docket No. FAA-2005-23392; Directorate 
Identifier 2005-NE-47-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by March 27, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Corporation (formerly Allison 
Engine Company, Allison Gas Turbine Division, and Detroit Diesel 
Allison) (RRC) models 250-C30, 250-40, and 250-C47 series turboshaft 
engines. These engines are installed on, but not limited to, Bell 
206L-3, Bell 206L-4, Bell 407, MDHI 369F, MDHI 369FF, MDHI 600N, and 
Sikorsky S-76A helicopters.

Unsafe Condition

    (d) This AD results from analysis by RRC of failures of third- 
and fourth-stage turbine wheels. We are issuing this AD to prevent 
loss of power, possible engine shutdown, or uncontained failure.

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.
    (f) Within 30 days after the effective date of this AD, record 
each time the third- and fourth-stage turbine wheels enter into the 
speed range between ``Event Threshold'' and ``Maximum Overspeed 
Transient''. Use paragraph 2.A. through 2.A.(5) of the 
Accomplishment Instructions and the applicable Figures 1 through 5 
of RRC Alert Commercial Engine Bulletins (CEBs) No. CEB A-72-3272, 
No. CEB A-72-5048, and No. CEB A-72-6054, all Revision 1, all dated 
July 1, 2005 (combined in one document) to determine the speed 
range.
    (g) Remove and retire any third-stage turbine wheel or fourth-
stage turbine wheel after the sixth time the wheel enters into the 
speed range between ``Event Threshold'' and ``Maximum Overspeed 
Transient''.

Third- and Fourth-Stage Turbine Wheel Life Limits

    (h) The retirement criteria in this AD are in addition to the 
existing third- and fourth-stage turbine wheel hour and cycle life 
limits. You must retire the wheels when you exceed any published 
life limit (transient speed excursions, hours, or cycles).

Alternative Methods of Compliance

    (i) The Manager, Chicago Aircraft 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) None.


[[Page 4067]]


    Issued in Burlington, Massachusetts, on January 18, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-898 Filed 1-24-06; 8:45 am]
BILLING CODE 4910-13-P

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