Airworthiness Directives; General Electric Company (GE) CF6-80C2B5F Turbofan Engines, 7831-7833 [E9-3609]

Download as PDF Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules Pursuant to the Commodity Promotion, Research and Information Act of 1996 (7 U.S.C. 7411–7425) (Act), it is hereby directed that a referendum be conducted to ascertain whether continuance of the Order is favored by producers of peanuts covered under the program. The Order is authorized under the Act. The representative period for establishing voter eligibility for the referendum shall be the period from January 1, 2008, to December 31, 2008. Persons who are producers of peanuts and paid assessments at the time of the referendum and during the representative period are eligible to vote. Persons who received an exemption from assessments for the entire representative period are ineligible to vote. The referendum shall be conducted by mail from April 2, 2009, through April 30, 2009. Section 518 of the Act authorizes continuance referenda. Under section 1216.82 of the Order, the Department of Agriculture (Department) shall conduct a referendum every five years or when 10 percent or more of the eligible voters petition the Secretary of Agriculture to hold a referendum to determine if persons subject to assessment favor continuance of the Order. The Department would continue the Order if continuance of the Order is approved by a simple majority of the producers voting in the referendum. In accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. chapter 35), the referendum ballot has been approved by the Office of Management and Budget (OMB) and assigned OMB NO. 0581–0093. It has been estimated that there are approximately 10,840 producers who will be eligible to vote in the referendum. It will take an average of 15 minutes for each voter to read the voting instructions and complete the referendum ballot. SUPPLEMENTARY INFORMATION: Referendum Order Jeanette Palmer and Sonia Jimenez, RPB, FVP, AMS, USDA, Stop 0244, Room 0632–S, 1400 Independence Avenue, SW., Washington, DC 20250– 0244, are designated as the referendum agents to conduct this referendum. The referendum procedures 7 CFR 1216.100 through 1216.107, which were issued pursuant to the Act, shall be used to conduct the referendum. The referendum agents will mail the ballots to be cast in the referendum and voting instructions to all known producers prior to the first day of the voting period. Persons who are producers and paid assessments at the time of the referendum and during the VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 representative period are eligible to vote. Persons who received an exemption from assessments during the entire representative period are ineligible to vote. Any eligible producer who does not receive a ballot should contact the referendum agent no later than one week before the end of the voting period. Ballots must be received by the referendum agent by the April 30, 2009 deadline, in order to be counted. List of Subjects in 7 CFR Part 1216 Administrative practice and procedure, Advertising, Consumer information, Marketing agreements, Peanut promotion, Reporting and recordkeeping requirements. Authority: 7 U.S.C. 7411–7425 and 7 U.S.C. 7401. Dated: February 13, 2009. James E. Link, Administrator, Agricultural Marketing Service. [FR Doc. E9–3601 Filed 2–19–09; 8:45 am] BILLING CODE 3410–02–P 7831 DATES: We must receive any comments on this proposed AD by April 21, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Part, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238–7754; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0121; Directorate Identifier 2008–NE–36–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF6–80C2B5F Turbofan 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 GE CF6–80C2B5F turbofan engines. This proposed AD would require removing certain part number (P/N) high-pressure compressor rotor (HPCR) 11–14 spool/ shafts before they exceed a new, reduced life limit. This proposed AD results from an internal GE audit that compared the life limited parts certification documentation to the airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We are proposing this AD to prevent HPCR 11–14 spool/ shaft fatigue cracks caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and damage to the airplane. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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– 2009–0121; Directorate Identifier 2008– NE–36–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:// www.regulations.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 Web site, anyone can find and read the comments in any of our dockets, including, if provided, 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). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. E:\FR\FM\20FEP1.SGM 20FEP1 7832 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion The ALS in the ICA for CF6–80C2 series engines incorrectly cited a cyclic life of 20,000 cycles for the HPCR 11– 14 spool/shaft, P/N 1703M74G03, installed in CF6–80C2B5F engines. The certified life for this spool/shaft in CF6– 80C2B5F engines is 19,500 cycles. The HPCR 11–14 spool/shaft, P/N 1703M74G03, wasn’t originally certified for CF6–80C2B5F engines, but was included in the ALS under the CF6– 80C2B5F engine model listing with a 20,000 cycle limit. When the spool/shaft was certified for the CF6–80C2B5F, it was certified for 19,500 cycles. GE changed the ALS to 19,500 cycles. Exceeding the 19,500 cycle life limit could result in fatigue cracks starting and growing until the spool/shaft fails. This condition, if not corrected, could result in possible uncontained HPCR spool/shaft failure and damage to the airplane. 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 removing from service CF6–80C2B5F engines with HPCR 11–14 spool/shafts, P/N 1703M74G03, before they exceed 19,500 cycles. Costs of Compliance We estimate that this proposed AD would affect one engine installed on an airplane of U.S. registry. We also estimate that the proposed actions would require no work-hours per engine. No parts are required. Based on these figures, we estimate there is no cost of the proposed AD to U.S. operators. 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 Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 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 AD: 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. You may get a copy of this summary at the address listed under ADDRESSES. General Electric Company: Docket No. FAA– 2009–0121; Directorate Identifier 2008– NE–36–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by April 21, 2009. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–80C2B5F turbofan engines with a high-pressure compressor rotor (HPCR) 11–14 spool/shaft, part number (P/N) 1703M74G03, installed. These engines are installed on, but not limited to, Boeing 747 series airplanes. Unsafe Condition (d) This AD results from an internal GE audit that compared the life limited parts certification documentation to the airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We are issuing this AD to prevent HPCR 11–14 spool/shaft fatigue cracks caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and 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. New Reduced Life Limit for the HPCR 11– 14 Spool/Shaft (f) Remove any CF6–80C2B5F turbofan engine that has an HPCR 11–14 spool/shaft, P/N 1703M74G03, before the spool/shaft meets or exceeds the new, reduced life cycle limit of 19,500 cycles. Installation Prohibition Air transportation, Aircraft, Aviation safety, Safety. (g) After the effective date of this AD, do not install any CF6–80C2B5F turbofan engine that has an HPCR 11–14 spool/shaft, P/N 1703M74G03, that meets or exceeds 19,500 cycles. The Proposed Amendment Alternative Methods of Compliance List of Subjects in 14 CFR Part 39 Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: Special Flight Permits PART 39—AIRWORTHINESS DIRECTIVES (i) Under 14 CFR part 39.23, we are prohibiting special flight permits for this AD. 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 00003 Fmt 4702 Sfmt 4702 (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (j) Contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Part, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238–7754; fax (781) 238– 7199, for more information about this AD. E:\FR\FM\20FEP1.SGM 20FEP1 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules Issued in Burlington, Massachusetts, on February 12, 2009. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3609 Filed 2–19–09; 8:45 am] FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: terry.fahr@faa.gov; telephone (781) 238–7155; fax (781) 238–7170. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0113; Directorate Identifier 2008–NE–25–AD] RIN 2120–AA64 Airworthiness Directives; Hamilton Sundstrand Propellers Model 247F Propellers 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 Hamilton Sundstrand Propellers model 247F propeller assemblies with certain part number (P/N) and serial number (SN) blades. This proposed AD would require removing affected propeller blades from service. This proposed AD results from reports of blades with corrosion pits in the tulip area of the blades. We are proposing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control. DATES: We must receive any comments on this proposed AD by April 21, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. You can get the service information identified in this proposed AD from Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1–3–AB43, Windsor Locks, CT 06096–1010; fax (860) 654–5107. VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 7833 R817370–1, could result in corrosion pits developing in the tulip area of the propeller blade. This condition, if not corrected, could cause cracks in the tulip area, which could result in separation of the propeller blade and possible loss of airplane control. 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– 2009–0113; Directorate Identifier 2008– NE–25–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:// www.regulations.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 Web site, anyone can find and read the comments in any of our dockets, including, if provided, 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). We have reviewed and approved the technical contents of Hamilton Sundstrand Service Bulletin 247F–61– 54, Revision 1, dated January 12, 2004, that describes procedures for reworking and re-marking the blade with a new P/N. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion We have received reports of corrosion on 6 propeller blades. A lack of adhesive and primer beyond the end of the compression wrap during manufacturing of certain serialnumbered propeller blades, P/N PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Relevant Service Information 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 removing propeller blades, P/N R817370–1, with a SN listed in this proposed AD, within 30 days after the effective date of this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 25 propellers installed on airplanes of U.S. registry. We also estimate that it would take about 128 work-hours per propeller to perform the proposed actions, and that the average labor rate is $80 per work-hour. Required parts would cost about $50 per propeller. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $257,250. 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. E:\FR\FM\20FEP1.SGM 20FEP1

Agencies

[Federal Register Volume 74, Number 33 (Friday, February 20, 2009)]
[Proposed Rules]
[Pages 7831-7833]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3609]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0121; Directorate Identifier 2008-NE-36-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-
80C2B5F Turbofan 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 GE CF6-80C2B5F turbofan engines. This proposed AD would require 
removing certain part number (P/N) high-pressure compressor rotor 
(HPCR) 11-14 spool/shafts before they exceed a new, reduced life limit. 
This proposed AD results from an internal GE audit that compared the 
life limited parts certification documentation to the airworthiness 
limitations section (ALS) of the instructions for continuing 
airworthiness (ICA). We are proposing this AD to prevent HPCR 11-14 
spool/shaft fatigue cracks caused by exceeding the life limit, which 
could result in a possible uncontained failure of the HPCR spool/shaft 
and damage to the airplane.

DATES: We must receive any comments on this proposed AD by April 21, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Part, Burlington, MA 01803; e-mail: 
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.

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-2009-0121; Directorate 
Identifier 2008-NE-36-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://
www.regulations.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 Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, 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).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m.

[[Page 7832]]

and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Operations office (telephone (800) 647-5527) is the same as the 
Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    The ALS in the ICA for CF6-80C2 series engines incorrectly cited a 
cyclic life of 20,000 cycles for the HPCR 11-14 spool/shaft, P/N 
1703M74G03, installed in CF6-80C2B5F engines. The certified life for 
this spool/shaft in CF6-80C2B5F engines is 19,500 cycles. The HPCR 11-
14 spool/shaft, P/N 1703M74G03, wasn't originally certified for CF6-
80C2B5F engines, but was included in the ALS under the CF6-80C2B5F 
engine model listing with a 20,000 cycle limit. When the spool/shaft 
was certified for the CF6-80C2B5F, it was certified for 19,500 cycles. 
GE changed the ALS to 19,500 cycles. Exceeding the 19,500 cycle life 
limit could result in fatigue cracks starting and growing until the 
spool/shaft fails. This condition, if not corrected, could result in 
possible uncontained HPCR spool/shaft failure and damage to the 
airplane.

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 
removing from service CF6-80C2B5F engines with HPCR 11-14 spool/shafts, 
P/N 1703M74G03, before they exceed 19,500 cycles.

Costs of Compliance

    We estimate that this proposed AD would affect one engine installed 
on an airplane of U.S. registry. We also estimate that the proposed 
actions would require no work-hours per engine. No parts are required. 
Based on these figures, we estimate there is no cost of the proposed AD 
to U.S. operators.

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 AD:
    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. 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.

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:

General Electric Company: Docket No. FAA-2009-0121; Directorate 
Identifier 2008-NE-36-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 21, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2B5F 
turbofan engines with a high-pressure compressor rotor (HPCR) 11-14 
spool/shaft, part number (P/N) 1703M74G03, installed. These engines 
are installed on, but not limited to, Boeing 747 series airplanes.

Unsafe Condition

    (d) This AD results from an internal GE audit that compared the 
life limited parts certification documentation to the airworthiness 
limitations section (ALS) of the instructions for continuing 
airworthiness (ICA). We are issuing this AD to prevent HPCR 11-14 
spool/shaft fatigue cracks caused by exceeding the life limit, which 
could result in a possible uncontained failure of the HPCR spool/
shaft and 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.

New Reduced Life Limit for the HPCR 11-14 Spool/Shaft

    (f) Remove any CF6-80C2B5F turbofan engine that has an HPCR 11-
14 spool/shaft, P/N 1703M74G03, before the spool/shaft meets or 
exceeds the new, reduced life cycle limit of 19,500 cycles.

Installation Prohibition

    (g) After the effective date of this AD, do not install any CF6-
80C2B5F turbofan engine that has an HPCR 11-14 spool/shaft, P/N 
1703M74G03, that meets or exceeds 19,500 cycles.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (i) Under 14 CFR part 39.23, we are prohibiting special flight 
permits for this AD.

Related Information

    (j) Contact Robert Green, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Part, Burlington, MA 01803; e-mail: 
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199, 
for more information about this AD.


[[Page 7833]]


    Issued in Burlington, Massachusetts, on February 12, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-3609 Filed 2-19-09; 8:45 am]
BILLING CODE 4910-13-P
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