Airworthiness Directives; General Electric Company CF34-10E2A1; CF34-10E5, CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; and CF34-10E7-B Turbofan Engines, 27282-27284 [2011-11481]

Download as PDF 27282 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules inspections of the buttress threads in the propeller hub ports for cracks. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 2 propellers installed on one airplane of U.S. registry. We also estimate that it would take about 1 work-hour per propeller to comply with this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $20,000 per propeller. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $40,170. emcdonald on DSK2BSOYB1PROD with PROPOSALS 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 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 this 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. 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. VerDate Mar<15>2010 16:26 May 10, 2011 Jkt 223001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 AD: Dowty Propellers (formerly Dowty Aerospace; Dowty Rotol Limited; and Dowty Rotol): Docket No. FAA–2011– 0033; Directorate Identifier 2011–NE– 01–AD. Comments Due Date (a) We must receive comments by June 27, 2011. Affected Airworthiness Directives (ADs) (b) None. Applicability (c) This AD applies to Dowty Propellers type R212/4–30–4/22 propeller assemblies with hub and driving center assembly part number (P/N) 601022105, 601022211, 601022294, 601021426, 601021858, or 601021859 installed, and type R251/4–30–4/ 49 propeller assemblies with hub and driving center assembly P/N 660207202 or P/N 660207203 installed. Reason (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in damage to the airplane. Actions and Compliance (e) Unless already done, do the following: (1) Within 500 flight hours after the effective date of this AD, and thereafter at intervals not exceeding 500 flight hours, inspect the buttress threads in the propeller hub and driving center assembly, for cracks. (2) Use paragraphs 2.A.(1) through 2.A.(4)(a) of Accomplishment Instructions of Dowty Propellers Alert Service Bulletin No. 61–1043, Revision 6, dated January 5, 2011, and NDT Technique NDT 175U (Appendix A of Dowty Propellers Alert Service Bulletin No. 61–1043, Revision 6, dated January 5, 2011), to do the inspection. (3) If a crack is found, remove the propeller assembly from service before further flight. (4) After the effective date of this AD, do not install this propeller on any airplane PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 unless the propeller hub and driving center has passed the inspections required by this AD. FAA AD Differences (f) This AD differs from the service information as follows: (1) Although the service bulletin tells you to return the affected parts to the manufacturer, this AD does not require that action. (2) Although the service bulletin tells you to submit information to the manufacturer, this AD does not require that action. Alternative Methods of Compliance (AMOCs) (g) The Manager, Boston Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI European Aviation Safety Agency AD 2011–0012, dated January 20, 2011, and Dowty Propellers Alert Service Bulletin No. 61–1043, Revision 6, dated January 5, 2011, for related information. Contact Dowty Propellers, 114 Powers Court, Sterling, VA 20166, telephone (703) 421– 4434; fax (703) 450–0087, for a copy of this service information. (i) Contact Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: michael.schwetz@faa.gov; telephone (781) 238–7761; fax (781) 238– 7170, for more information about this AD. Issued in Burlington, Massachusetts, on April 28, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–11480 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0187; Directorate Identifier 2011–NE–07–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF34–10E2A1; CF34–10E5, CF34–10E5A1; CF34– 10E6; CF34–10E6A1; CF34–10E7; and CF34–10E7–B Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above with certain part number (P/N) fan rotor spinners SUMMARY: E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules installed. This proposed AD would require removing from service certain fan rotor blade retainers, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. This proposed AD was prompted by a fan rotor spinner support found cracked at the attachment lugs. We are proposing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by June 27, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact GE-Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 513– 552–3272; e-mail: geae.aoc@ge.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. emcdonald on DSK2BSOYB1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781– 238–7199; e-mail: john.frost@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Mar<15>2010 16:26 May 10, 2011 Jkt 223001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–0187; Directorate Identifier 2011– NE–07–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because 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 we receive about this proposed AD. Discussion Investigation of a General Electric Company (GE) CF34–10E turbofan engine experiencing high fan frame vibrations led to removal of the fan rotor spinner. Eight of the twelve attachment lugs on the fan rotor spinner support were found cracked. The cause of the vibration was determined to be a nonsynchronous vibration induced by a spinner redesign that removed an interference between the fan blade retainers and the spinner. This condition, if not corrected, could result in high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane. Relevant Service Information We reviewed GE Service Bulletin (SB) No. CF34–10E–S/B 72–0186, dated January 31, 2011. The SB describes procedures for replacement of the fan rotor blade retainers with redesigned retainers that reintroduce the interference between the fan blade retainers and the spinner. The SB also describes procedures for replacement of the fan rotor spinner support, with a new support of the same P/N. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require removing from service fan rotor blade PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 27283 retainers, P/N 2050M56P02, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. Costs of Compliance We estimate that this proposed AD would affect 164 engines installed on airplanes of U.S. registry. We also estimate that it would take about 2 work-hours per engine to perform the actions required by this proposed AD, and that the average labor rate is $85 per work-hour. If all removed parts get replaced, required parts would cost about $10,458 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $1,742,992. 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 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 this 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), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities E:\FR\FM\11MYP1.SGM 11MYP1 27284 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 (AD): General Electric Company: Docket No. FAA– 2011–0187; Directorate Identifier 2011– NE–07–AD. Comments Due Date (a) We must receive comments by June 27, 2011. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF34–10E2A1; CF34–10E5, CF34–10E5A1; CF34–10E6; CF34–10E6A1; CF34–10E7; and CF34–10E7–B turbofan engines, with a fan rotor spinner part number (P/N) 2050M34G03; 2050M34G04; 2050M34G05; 2050M34G06; 2437M60G01; or 2437M60G02, installed. Unsafe Condition (d) This AD was prompted by a fan rotor spinner support found cracked at the attachment lugs. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane. Compliance (e) Comply with this AD within 1,800 hours-in-service after the effective date of this AD, unless already done. emcdonald on DSK2BSOYB1PROD with PROPOSALS 16:26 May 10, 2011 Jkt 223001 Related Information (k) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238– 7199; e-mail: john.frost@faa.gov. (l) Refer to GE Service Bulletin No. CF34– 10E–S/B 72–0186, dated January 31, 2011, for related information. Contact GE-Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 513–552– 3272; e-mail: geae.aoc@ge.com, for a copy of this service information. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on April 28, 2011. Peter A. White, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–11481 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 100 [Docket No. USCG–2011–0211] RIN 1625–AA08 Special Local Regulation; Partnership in Education, Dragon Boat Race; Maumee River, Toledo, OH Coast Guard, DHS. ACTION: Notice of proposed rulemaking. The Coast Guard proposes establishing a permanent Special Local Regulation on the Maumee River, Toledo, Ohio. This regulation is intended to restrict vessels from portions of the Maumee River during the Dragon Boat Races which take place during the third or fourth weekend in July each year. This special local regulated area is necessary to protect race participants from other vessel traffic. SUMMARY: Removal of Fan Rotor Spinner Support (g) Remove from service the fan rotor spinner support that operated with the fan rotor blade retainers removed in paragraph (f) of this AD. VerDate Mar<15>2010 Alternative Methods of Compliance (AMOCs) (j) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. AGENCY: Removal of Fan Rotor Blade Retainers (f) Remove from service the 24 fan rotor blade retainers, P/N 2050M56P02. Installation Prohibition (h) After the effective date of this AD, do not install any fan rotor blade retainer, P/N 2050M56P02, into any engine. Do not attempt to repair, make serviceable, or reinstall, this part. (i) After the effective date of this AD, do not install any fan rotor spinner support removed in paragraph (g) of this AD, into any engine. Do not attempt to repair, make serviceable, or re-install, this part. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Comments and related material must be received by the Coast Guard on or before June 10, 2011. ADDRESSES: You may submit comments identified by docket number USCG– 2011–0211 using any one of the following methods: (1) Federal eRulemaking Portal: https://www.regulations.gov. (2) Fax: 202–493–2251. (3) Mail: Docket Management Facility (M–30), U.S. Department of Transportation, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590– 0001. (4) Hand delivery: Same as mail address above, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The telephone number is 202–366–9329. To avoid duplication, please use only one of these four methods. See the ‘‘Public Participation and Request for Comments’’ portion of the SUPPLEMENTARY INFORMATION section below for instructions on submitting comments. DATES: If you have questions on this proposed rule, call or e-mail BM1 Tracy Girard, Response Department, MSU Toledo, Coast Guard; telephone (419) 418–6036, e-mail Tracy.M.Girard@uscg.mil. If you have questions on viewing or submitting material to the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366–9826. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Public Participation and Request for Comments We encourage you to participate in this rulemaking by submitting comments and related materials. All comments received will be posted without change to https:// www.regulations.gov and will include any personal information you have provided. Submitting Comments If you submit a comment, please include the docket number for this rulemaking (USCG–2011–0211), indicate the specific section of this document to which each comment applies, and provide a reason for each suggestion or recommendation. You may submit your comments and material online (via https:// www.regulations.gov) or by fax, mail, or hand delivery, but please use only one of these means. If you submit a comment online via www.regulations.gov, it will be considered received by the Coast Guard when the comment is successfully E:\FR\FM\11MYP1.SGM 11MYP1

Agencies

[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Proposed Rules]
[Pages 27282-27284]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-11481]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0187; Directorate Identifier 2011-NE-07-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF34-10E2A1; 
CF34-10E5, CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; and CF34-
10E7-B Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above with certain part number (P/N) fan rotor spinners

[[Page 27283]]

installed. This proposed AD would require removing from service certain 
fan rotor blade retainers, and removing from service the fan rotor 
spinner support that was installed with those fan rotor blade 
retainers. This proposed AD was prompted by a fan rotor spinner support 
found cracked at the attachment lugs. We are proposing this AD to 
prevent high-cycle fatigue cracking of the fan rotor spinner support 
attachment lugs, leading to separation of the fan rotor spinner 
assembly, uncontained failure of the engine, and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by June 27, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact GE-
Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 
513-552-3272; e-mail: geae.aoc@ge.com. You may review copies of the 
referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
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 Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine 
Certification Office, FAA, 12 New England Executive Park, Burlington, 
MA 01803; phone: 781-238-7756; fax: 781-238-7199; e-mail: 
john.frost@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0187; 
Directorate Identifier 2011-NE-07-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because 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 we 
receive about this proposed AD.

Discussion

    Investigation of a General Electric Company (GE) CF34-10E turbofan 
engine experiencing high fan frame vibrations led to removal of the fan 
rotor spinner. Eight of the twelve attachment lugs on the fan rotor 
spinner support were found cracked. The cause of the vibration was 
determined to be a non-synchronous vibration induced by a spinner 
redesign that removed an interference between the fan blade retainers 
and the spinner. This condition, if not corrected, could result in 
high-cycle fatigue cracking of the fan rotor spinner support attachment 
lugs, leading to separation of the fan rotor spinner assembly, 
uncontained failure of the engine, and damage to the airplane.

Relevant Service Information

    We reviewed GE Service Bulletin (SB) No. CF34-10E-S/B 72-0186, 
dated January 31, 2011. The SB describes procedures for replacement of 
the fan rotor blade retainers with redesigned retainers that 
reintroduce the interference between the fan blade retainers and the 
spinner. The SB also describes procedures for replacement of the fan 
rotor spinner support, with a new support of the same P/N.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require removing from service fan rotor 
blade retainers, P/N 2050M56P02, and removing from service the fan 
rotor spinner support that was installed with those fan rotor blade 
retainers.

Costs of Compliance

    We estimate that this proposed AD would affect 164 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 2 work-hours per engine to perform the actions required by 
this proposed AD, and that the average labor rate is $85 per work-hour. 
If all removed parts get replaced, required parts would cost about 
$10,458 per engine. Based on these figures, we estimate the total cost 
of the proposed AD to U.S. operators to be $1,742,992.

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 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 this 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities

[[Page 27284]]

under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 (AD):

General Electric Company: Docket No. FAA-2011-0187; Directorate 
Identifier 2011-NE-07-AD.

Comments Due Date

    (a) We must receive comments by June 27, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF34-
10E2A1; CF34-10E5, CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; 
and CF34-10E7-B turbofan engines, with a fan rotor spinner part 
number (P/N) 2050M34G03; 2050M34G04; 2050M34G05; 2050M34G06; 
2437M60G01; or 2437M60G02, installed.

Unsafe Condition

    (d) This AD was prompted by a fan rotor spinner support found 
cracked at the attachment lugs. We are issuing this AD to prevent 
high-cycle fatigue cracking of the fan rotor spinner support 
attachment lugs, leading to separation of the fan rotor spinner 
assembly, uncontained failure of the engine, and damage to the 
airplane.

Compliance

    (e) Comply with this AD within 1,800 hours-in-service after the 
effective date of this AD, unless already done.

Removal of Fan Rotor Blade Retainers

    (f) Remove from service the 24 fan rotor blade retainers, P/N 
2050M56P02.

Removal of Fan Rotor Spinner Support

    (g) Remove from service the fan rotor spinner support that 
operated with the fan rotor blade retainers removed in paragraph (f) 
of this AD.

Installation Prohibition

    (h) After the effective date of this AD, do not install any fan 
rotor blade retainer, P/N 2050M56P02, into any engine. Do not 
attempt to repair, make serviceable, or re-install, this part.
    (i) After the effective date of this AD, do not install any fan 
rotor spinner support removed in paragraph (g) of this AD, into any 
engine. Do not attempt to repair, make serviceable, or re-install, 
this part.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (k) For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, 12 New England 
Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-
238-7199; e-mail: john.frost@faa.gov.
    (l) Refer to GE Service Bulletin No. CF34-10E-S/B 72-0186, dated 
January 31, 2011, for related information. Contact GE-Aviation, M/D 
Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 513-552-
3272; e-mail: geae.aoc@ge.com, for a copy of this service 
information. You may review copies of the referenced service 
information at the FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125.

    Issued in Burlington, Massachusetts, on April 28, 2011.
Peter A. White,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-11481 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P
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