Airworthiness Directives; General Electric Company CT64-820-4 Turboprop Engines, 35523-35525 [05-12173]

Download as PDF Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations What Are the Flight Restrictions Specified in Paragraphs (e)(3) and (e)(4) of This AD? (f) During the time allowed before compliance with the initial inspection required by paragraph (e)(1) of this AD, or for any approved special flight permit, you must adhere to the following limitations: (1) Acrobatic maneuvers are prohibited. (2) Flight into known or forecast moderate or severe turbulence is prohibited. (3) Day visual flight rules (VFR) operation only. (4) Single pilot operation only (Passengers prohibited). May I Request an Alternative Method of Compliance? (g) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: (562) 627–5232; facsimile: (562) 627–5210; e-mail: fred.guerin@faa.gov. Where Do I View the AD Docket? (h) To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http://dms.dot.gov. The docket number is FAA–2005–24163. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. Appendix to AD 2005–12–51 Wing Attachment Angle Inspection for: Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT– 6B, AT–6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, Harvard (Army AT–16), SNJ–7, and T–6G Airplanes Procedures: (1) Remove all outboard wing attach angle covers. (2) Support outboard wing on appropriate stands to relieve the weight on the wing attach bolts. (3) On the upper wing attach angles, except for the forward and aft five bolts on the angle, remove all of the through bolts that attach the outboard wing (Do not remove bolts in the nose angle). (4) Remove all paint down to the bare metal using solvent on outer surface of affected angles. Do not sand or use media blasting or use any method that would cover up or contaminate a crack. This means not using Scotchbrite or a similar abrasive, which can contaminate a crack for penetrant inspection. (5) Use the penetrant manufacturer’s cleaner, acetone, or 90-percent or more VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 alcohol solution to do a final surface cleaning preparation step before the fluorescent penetrant inspection. (6) Perform an inspection of the outboard and inboard wing attach angles using a high sensitivity fluorescent dye penetrant inspection procedure per the penetrant manufacturer’s instructions. Pay particular attention to cracks that may be present in the edge of the spot faces closest to the radius of the angle. Also pay attention to any small cracks that may be emanating from the edge of the fasteners in any row of installed fasteners. Choose a commercially available fluorescent inspection method that requires the use of an ultraviolet (black light) in a darkened environment. Do not use dye penetrant, which is read under normal lighting conditions. (7) Check the wing attachment angle for condition and for security of rivets and bolts. (8) If no cracks or major defects are found, replace nuts and bolts following directions in paragraphs (11) and (12) of this appendix of this AD, clean angle, and apply a corrosion protectant coating paint (Alodine alone is not acceptable). (9) On the upper wing, remove the forward and aft five bolts that were previously left in place, and inspect the remaining uninspected portion of the angles following the above procedure. (10) On the lower wings, repeat the inspection on the bottom two attach angles in the same sequence as on the top angles. (11) When replacing bolts in angles, use only nuts, bolts, and torque values as specified in ‘‘Erection and Maintenance No. AN01–60FFA–2’’ or ‘‘Erection and Maintenance No. AN01–60F–2’’ as applicable to the aircraft model. Bolts may be reused if upon inspection they are found to be in airworthy condition. Nuts may be reused as long as the nylon-locking feature is functional, and they cannot be turned onto the bolt with fingers. Torque values for 1⁄4inch bolts are 60–65 inch/lb, and for 5⁄16-inch bolts are 100–105 inch/lb. These torque values supersede those in the manuals. (12) To assure that the nuts do not contact the shoulder of the wing attach bolts and cause an under torque condition, assure that no more than two threads are protruding from nut after torquing. If more than two threads are protruding, replace with a bolt of the correct length. (13) If any cracks are found, replace the angle with a new part. Send all cracked angles to Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712. [FR Doc. 05–12151 Filed 6–20–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 35523 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21586; Directorate Identifier 2005–NE–16–AD; Amendment 39– 14148; AD 2005–13–11] RIN 2120–AA64 Airworthiness Directives; General Electric Company CT64–820–4 Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT64–820–4 turboprop engines with stage 1 turbine disk and shaft, part number (P/N) 6004T47P03 or 4921T10P02 installed. This AD requires removing from service these stage 1 turbine disk and shafts at reduced compliance times. This AD results from the discovery by the manufacturer of low-cycle-fatigue (LCF) cracks found in stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02. We are issuing this AD to prevent uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to the airplane. DATES: This AD becomes effective July 6, 2005. We must receive any comments on this AD by August 22, 2005. ADDRESSES: Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552–3272; fax (513) 552–3329; email address: GEAE.csc@ae.ge.com, for the service information identified in this AD. E:\FR\FM\21JNR1.SGM 21JNR1 35524 Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations FOR FURTHER INFORMATION CONTACT: Anthony W. Cerra Jr., Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone 781–238–7128; fax 781–238–7199; email address: anthony.cerra@faa.gov. GE has informed us that cracks have been found in some retired stage 1 disk and shafts which were removed from military T64 engines and are equivalent to the CT64– 820–4 P/Ns 6004T47P03 and 4921T10P02. The cracks were located at ‘‘small feature’’ locations. A ‘‘small feature’’ location is any rotating hardware feature with drawing radii less than 0.020-inch, that could become potentially life limiting. These cracks were difficult to find due to the nature of their geometry and location on the part. The cracks were confirmed upon metallurgical evaluation of cut-up sections of those parts. This condition, if not corrected, could result in an uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to the airplane. GE is aware of about 50 engines that are in service. Three of these engines have the affected parts. GE has coordinated the compliance plan with the operator of these three certain serial number engines. The specific compliance times for these engines minimize adverse operator impact, yet maintain the interests of safety. GE is aware of approximately 90 additional engines for which GE does not know if the engines are in service or if they have the affected parts. GE has established the additional removal-from-service compliance times for these other engines in the event that any are still in service. We are using GE’s compliance times in this AD. SUPPLEMENTARY INFORMATION: FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other CT64–820–4 turboprop engines of the same type design. We are issuing this AD to prevent uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to the airplane. This AD requires removing from service stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02 at reduced compliance times. VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. A situation exists that allows the immediate adoption of this regulation. 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–2005–21586; Directorate Identifier 2005–NE–16-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 DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647– 5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2005–13–11 General Electric Company: Amendment 39–14148. Docket No. FAA–2005–21586; Directorate Identifier 2005–NE–16–AD. E:\FR\FM\21JNR1.SGM 21JNR1 Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations Effective Date Definition (m) For the purpose of this AD, piece-part exposure is defined as the stage 1 disk and shaft is completely disassembled using the disassembly instructions of the manufacturer’s engine manual, or other FAAapproved engine manual. (a) This airworthiness directive (AD) becomes effective July 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT64–820–4 turboprop engines with stage 1 turbine disk and shaft, part number (P/N) 6004T47P03 or 4921T10P02 installed. These engines are installed on, but not limited to, DeHavilland DHC–5D Buffalo airplanes. Unsafe Condition (d) This AD results from the discovery by the manufacturer of low-cycle fatigue (LCF) cracks found in stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02. We are issuing this AD to prevent uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Engine Serial Numbers (SNs) 268537, 268565, and 268637 All Other Engines (i) For all other engines that have accumulated 590 CSN or more on the stage 1 turbine disk and shaft on the effective date of this AD, remove stage 1 turbine disk and shaft from service at or before accumulating an additional 10 cycles-in-service, at or before accumulating the service life limit of 1,700 CSN, or by December 31, 2005, whichever occurs first. (j) For all other engines that have accumulated fewer than 590 CSN on the stage 1 turbine disk and shaft on the effective date of this AD, remove stage 1 turbine disk and shaft from service at the next piece-partexposure, or before accumulating 600 CSN, or by December 31, 2005, whichever occurs first. (k) After the effective date of this AD, do not install any stage 1 turbine disk and shaft, P/N 6004T47P03 or 4921T10P02, into any engine. (l) After the effective date of this AD, do not install any engine with stage 1 turbine disk and shaft, P/N 6004T47P03 or 4921T10P02, into any airplane. 15:18 Jun 20, 2005 Jkt 205001 Related Information (o) Information on determining engine usage in cycles for comparison to CT64 service life limits can be found in GE Service Bulletin CEB No. 93, Revision 2, dated May 30, 1984. GE Alert Service Bulletin No. CT64 S/B 72–A0113, Revision 1, dated May 16, 2005, also pertains to the subject of this AD. Material Incorporated by Reference (p) None. Issued in Burlington, Massachusetts, on June 14, 2005. Robert Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–12173 Filed 6–20–05; 8:45 am] BILLING CODE 4910–13–P (f) For engine serial number (SN) 268537, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,700 cycles-since-new (CSN), or by December 31, 2005, whichever occurs first. (g) For engine SN 268565, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,585 CSN, or by December 31, 2005, whichever occurs first. (h) For engine SN 268637, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,345 CSN, or by December 31, 2005, whichever occurs first. VerDate jul<14>2003 Alternative Methods of Compliance (n) 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. 35525 History On April 27, 2005, a notice proposing to amend Part 71 of the Federal Aviation Regulations (14 CFR Part 71) by establishing a Class E airspace area at Sutton, WV, was published in the Federal Register (70 FR 21695–21696). The proposed action would provide controlled airspace to accommodate Standard Instrument Approach Procedures (SIAP), based on area navigation (RNAV), to Braxton County Airport. Interested parties were invited to participate in this rulemaking proceeding by submitting written comments on the proposal to the FAA on or before May 27, 2005. No comments to the proposal were received. The rule is adopted as proposed. The coordinates for this airspace docket are based on North America Datum 83. Class E airspace area designations for airspace extending upward from the surface of the earth are published in paragraph 6005 of FAA Order 7400.9M, dated August 30, 2004, and effective September 16, 2004, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document will be published in the Order. DEPARTMENT OF TRANSPORTATION The Rule Federal Aviation Administration This amendment to Part 71 of the Federal Aviation Regulations (14 CFR Part 71) provides controlled Class E airspace extending upward from 700 feet above the surface for aircraft conducting IFR operations within an 8mile radius of Braxton County Airport, Sutton, WV. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule will not have significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 14 CFR Part 71 [Docket No. FAA–2005–20931; Airspace Docket No. 95–AEA–08] Establishment of Class E Airspace; Sutton, WV Federal Aviation Administration (FAA) DOT. AGENCY: ACTION: Final rule. SUMMARY: This action establishes Class E airspace at Sutton, WV. Controlled airspace extending upward from 700 feet Above Ground Level (AGL) is needed to contain aircraft operating into Braxton County Airport, Sutton, WV, under Instrument Flight Rules (IR). DATES: Effective: 0901 UTC October 27, 2005. Mr. Francis Jordan, Airspace Specialist, Eastern Terminal Service Unit. Airspace and Operations, ETSU–520, Eastern Region, Federal Aviation Administration, 1 Aviation Plaza, Jamaica, New York 11434–4809, telephone: (718) 553–4521. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 List of Subjects in 14 CFR Part 71 Airspace, Incorporation by refernce, Navigation (air). E:\FR\FM\21JNR1.SGM 21JNR1

Agencies

[Federal Register Volume 70, Number 118 (Tuesday, June 21, 2005)]
[Rules and Regulations]
[Pages 35523-35525]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12173]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21586; Directorate Identifier 2005-NE-16-AD; 
Amendment 39-14148; AD 2005-13-11]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CT64-820-4 
Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) CT64-820-4 turboprop engines with stage 1 
turbine disk and shaft, part number (P/N) 6004T47P03 or 4921T10P02 
installed. This AD requires removing from service these stage 1 turbine 
disk and shafts at reduced compliance times. This AD results from the 
discovery by the manufacturer of low-cycle-fatigue (LCF) cracks found 
in stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02. We 
are issuing this AD to prevent uncontained failure of the stage 1 
turbine disk and shaft, resulting in damage to the airplane.

DATES: This AD becomes effective July 6, 2005.
    We must receive any comments on this AD by August 22, 2005.

ADDRESSES: Use one of the following addresses to comment on this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact GE Aircraft Engines Customer Support Center, M/D 285, 1 
Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513) 
552-3329; e-mail address: GEAE.csc@ae.ge.com, for the service 
information identified in this AD.

[[Page 35524]]


FOR FURTHER INFORMATION CONTACT: Anthony W. Cerra Jr., Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone 781-238-7128; fax 781-238-7199; e-mail address: 
anthony.cerra@faa.gov.

SUPPLEMENTARY INFORMATION: GE has informed us that cracks have been 
found in some retired stage 1 disk and shafts which were removed from 
military T64 engines and are equivalent to the CT64-820-4 P/Ns 
6004T47P03 and 4921T10P02. The cracks were located at ``small feature'' 
locations. A ``small feature'' location is any rotating hardware 
feature with drawing radii less than 0.020-inch, that could become 
potentially life limiting. These cracks were difficult to find due to 
the nature of their geometry and location on the part. The cracks were 
confirmed upon metallurgical evaluation of cut-up sections of those 
parts. This condition, if not corrected, could result in an uncontained 
failure of the stage 1 turbine disk and shaft, resulting in damage to 
the airplane.
    GE is aware of about 50 engines that are in service. Three of these 
engines have the affected parts. GE has coordinated the compliance plan 
with the operator of these three certain serial number engines. The 
specific compliance times for these engines minimize adverse operator 
impact, yet maintain the interests of safety. GE is aware of 
approximately 90 additional engines for which GE does not know if the 
engines are in service or if they have the affected parts. GE has 
established the additional removal-from-service compliance times for 
these other engines in the event that any are still in service. We are 
using GE's compliance times in this AD.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these engines, the possibility exists that the engines could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition described previously is likely to exist or develop on 
other CT64-820-4 turboprop engines of the same type design. We are 
issuing this AD to prevent uncontained failure of the stage 1 turbine 
disk and shaft, resulting in damage to the airplane. This AD requires 
removing from service stage 1 turbine disk and shafts, P/Ns 6004T47P03 
and 4921T10P02 at reduced compliance times.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. A situation exists that allows the immediate adoption 
of this regulation.

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-2005-21586; 
Directorate Identifier 2005-NE-16-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 DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the DMS receives them.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2005-13-11 General Electric Company: Amendment 39-14148. Docket No. 
FAA-2005-21586; Directorate Identifier 2005-NE-16-AD.

[[Page 35525]]

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 6, 
2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CT64-820-4 
turboprop engines with stage 1 turbine disk and shaft, part number 
(P/N) 6004T47P03 or 4921T10P02 installed. These engines are 
installed on, but not limited to, DeHavilland DHC-5D Buffalo 
airplanes.

Unsafe Condition

    (d) This AD results from the discovery by the manufacturer of 
low-cycle fatigue (LCF) cracks found in stage 1 turbine disk and 
shafts, P/Ns 6004T47P03 and 4921T10P02. We are issuing this AD to 
prevent uncontained failure of the stage 1 turbine disk and shaft, 
resulting in damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Engine Serial Numbers (SNs) 268537, 268565, and 268637

    (f) For engine serial number (SN) 268537, remove the stage 1 
turbine disk and shaft from service at or before accumulating 1,700 
cycles-since-new (CSN), or by December 31, 2005, whichever occurs 
first.
    (g) For engine SN 268565, remove the stage 1 turbine disk and 
shaft from service at or before accumulating 1,585 CSN, or by 
December 31, 2005, whichever occurs first.
    (h) For engine SN 268637, remove the stage 1 turbine disk and 
shaft from service at or before accumulating 1,345 CSN, or by 
December 31, 2005, whichever occurs first.

All Other Engines

    (i) For all other engines that have accumulated 590 CSN or more 
on the stage 1 turbine disk and shaft on the effective date of this 
AD, remove stage 1 turbine disk and shaft from service at or before 
accumulating an additional 10 cycles-in-service, at or before 
accumulating the service life limit of 1,700 CSN, or by December 31, 
2005, whichever occurs first.
    (j) For all other engines that have accumulated fewer than 590 
CSN on the stage 1 turbine disk and shaft on the effective date of 
this AD, remove stage 1 turbine disk and shaft from service at the 
next piece-part-exposure, or before accumulating 600 CSN, or by 
December 31, 2005, whichever occurs first.
    (k) After the effective date of this AD, do not install any 
stage 1 turbine disk and shaft, P/N 6004T47P03 or 4921T10P02, into 
any engine.
    (l) After the effective date of this AD, do not install any 
engine with stage 1 turbine disk and shaft, P/N 6004T47P03 or 
4921T10P02, into any airplane.

Definition

    (m) For the purpose of this AD, piece-part exposure is defined 
as the stage 1 disk and shaft is completely disassembled using the 
disassembly instructions of the manufacturer's engine manual, or 
other FAA-approved engine manual.

Alternative Methods of Compliance

    (n) 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

    (o) Information on determining engine usage in cycles for 
comparison to CT64 service life limits can be found in GE Service 
Bulletin CEB No. 93, Revision 2, dated May 30, 1984. GE Alert 
Service Bulletin No. CT64 S/B 72-A0113, Revision 1, dated May 16, 
2005, also pertains to the subject of this AD.

Material Incorporated by Reference

    (p) None.

    Issued in Burlington, Massachusetts, on June 14, 2005.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-12173 Filed 6-20-05; 8:45 am]
BILLING CODE 4910-13-P