Airworthiness Directives; General Electric Company (GE) GE90 Series Turbofan Engines, 26538-26540 [E7-8990]

Download as PDF 26538 Federal Register / Vol. 72, No. 90 / Thursday, May 10, 2007 / Rules and Regulations storage facilities, and NAC. The companies that own these plants do not fall within the scope of the definition of ‘‘small entities’’ set forth in the Regulatory Flexibility Act or the size standards established by the NRC (10 CFR 2.810). Backfit Analysis The NRC has determined that the backfit rule (10 CFR 72.62) does not apply to this direct final rule because this amendment does not involve any provisions that would impose backfits as defined in 10 CFR Chapter I. Therefore, a backfit analysis is not required. Congressional Review Act Under the Congressional Review Act of 1996, the NRC has determined that this action is not a major rule and has verified this determination with the Office of Information and Regulatory Affairs, Office of Management and Budget. List of Subjects in 10 CFR Part 72 Administrative practice and procedure, Criminal penalties, Manpower training programs, Nuclear materials, Occupational safety and health, Penalties, Radiation protection, Reporting and recordkeeping requirements, Security measures, Spent fuel, Whistleblowing. I For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; and 5 U.S.C. 552 and 553; the NRC is adopting the following amendments to 10 CFR part 72. PART 72—LICENSING REQUIREMENTS FOR THE INDEPENDENT STORAGE OF SPENT NUCLEAR FUEL, HIGH-LEVEL RADIOACTIVE WASTE, AND REACTOR-RELATED GREATER THAN CLASS C WASTE 1. The authority citation for part 72 continues to read as follows: cprice-sewell on PRODPC61 with RULES I Authority: Secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182, 183, 184, 186, 187, 189, 68 Stat. 929, 930, 932, 933, 934, 935, 948, 953, 954, 955, as amended; sec. 234, 83 Stat. 444, as amended (42 U.S.C. 2071, 2073, 2077, 2092, 2093, 2095, 2099, 2111, 2201, 2232, 2233, 2234, 2236, 2237, 2238, 2282); sec. 274, Pub. L. 86–373, 73 Stat. 688, as amended (42 U.S.C. 2021); sec. 201, as amended, 202, 206, 88 Stat. 1242, as amended; 1244, 1246 (42 U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec. 10, 92 Stat. 2951, as amended by Pub. L. 102– 486, sec. 7902, 106 Stat. 3123 (42 U.S.C. 5851); sec. 102, Pub. L. 91–190, 83 Stat. 853 (42 U.S.C. 4332); secs. 131, 132, 133, 135, 137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230, 2232, 2241; sec. 148, Pub. L. 100–203, 101 VerDate Aug<31>2005 14:29 May 09, 2007 Jkt 211001 Stat. 1330–235 (42 U.S.C. 10151, 10152, 10153, 10155, 10157, 10161, 10168); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note); sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10 (42 U.S.C. 2014, 2021, 2021b, 2111). Section 72.44(g) also issued under secs. 142(b) and 148(c), (d), Pub. L. 100–203, 101 Stat. 1330–232, 1330–236 (42 U.S.C. 10162(b), 10168(c),(d)). Section 72.46 also issued under sec. 189, 68 Stat. 955 (42 U.S.C. 2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230 (42 U.S.C. 10154). Section 72.96(d) also issued under sec. 145(g), Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10165(g)). Subpart J also issued under secs. 2(2), 2(15), 2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat. 2202, 2203, 2204, 2222, 2244 (42 U.S.C. 10101, 10137(a), 10161(h)). Subparts K and L are also issued under sec. 133, 98 Stat. 2230 (42 U.S.C. 10153) and sec. 218(a), 96 Stat. 2252 (42 U.S.C. 10198). 2. In § 72.214, Certificate of Compliance 1025 is revised to read as follows: I § 72.214 List of approved spent fuel storage casks. * * * * * Certificate Number: 1025. Initial Certificate Effective Date: April 10, 2000. Amendment Number 1 Effective Date: November 13, 2001. Amendment Number 2 Effective Date: May 29, 2002. Amendment Number 3 Effective Date: October 1, 2003. Amendment Number 4 Effective Date: October 27, 2004. Amendment Number 5 Effective Date: July 24, 2007. SAR Submitted by: NAC International, Inc. SAR Title: Final Safety Analysis Report for the NAC Multi-Purpose Canister System (NAC–MPC System). Docket Number: 72–1025. Certificate Expiration Date: April 10, 2020. Model Number: NAC–MPC. * * * * * Dated at Rockville, Maryland, this 24th day of April, 2007. For the Nuclear Regulatory Commission. Martin J. Virgilio, Acting Executive Director for Operations. [FR Doc. E7–9008 Filed 5–9–07; 8:45 am] BILLING CODE 7590–01–P PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27283; Directorate Identifier 2007–NE–05–AD; Amendment 39– 15046; AD 2007–10–05] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) GE90 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE GE90–110B1, –113B, and –115B series turbofan engines with certain Turbine Center Frames (TCFs) installed. This AD requires removing certain TCFs, listed by part number (P/N) in this AD, from service before exceeding 14,300 flight cycles. This AD results from a report that GE inadvertently omitted some TCF P/Ns from the Airworthiness Limitations Section (ALS) of the engine manual. We are issuing this AD to prevent structural failure of the TCF with uncontained failure of low pressure turbine (LPT) rotating parts. Uncontained failure of the LPT rotating parts could result in damage to the airplane and possible loss of control of the airplane. DATES: This AD becomes effective June 14, 2007. We must receive any comments on this AD by July 9, 2007. ADDRESSES: Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace Engineer, Engine Certification Office, E:\FR\FM\10MYR1.SGM 10MYR1 Federal Register / Vol. 72, No. 90 / Thursday, May 10, 2007 / Rules and Regulations FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7751; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On January 12, 2007, we received a report from GE that they had inadvertently omitted six TCFs P/Ns from the ALS of the engine manual. GE introduced an improved, redesigned TCF after the initial engine certification. GE identified the new designs with new P/Ns. The TCF is a life-limited part. Engine lifelimited parts are listed in the ALS of the Engine Manual and must be removed from service at or before reaching their life limit. Because GE has not included in the ALS all the TCF P/Ns that are currently in service, operators might not be tracking the accumulated flight cycles on those P/N TCFs. Exceeding the TCF life limit will exceed the lowcycle fatigue design capability of the material structure. If the TCF fails, the LPT structure could fail with rotating parts liberating and impacting the fuselage of the airplane. This condition, if not corrected, could result in loss of control of the airplane. 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 engines of the same type design. We are issuing this AD to prevent structural failure of the TCF with uncontained failure of LPT rotating parts. Uncontained failure of the LPT rotating parts could result in damage to the airplane and possible loss of control of the airplane. This AD requires removing from service certain TCFs, listed by P/N in this AD, at or before accumulating 14,300 flight cycles. cprice-sewell on PRODPC61 with RULES 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 VerDate Aug<31>2005 14:29 May 09, 2007 Jkt 211001 ADDRESSES. Include ‘‘AD Docket No. FAA–2007–27283; Directorate Identifier 2007–NE–05–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 https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this 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 https://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 Docket Management Facility 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. 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 this 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. 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 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 26539 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 2007–10–05 General Electric Company: Amendment 39–15046 Docket No. FAA– 2007–27283; Directorate Identifier 2007– NE–05–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 14, 2007. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) GE90–110B1, –113B, and –115B series engines with a Turbine Center Frame (TCF) that has a part number listed in the following Table 1 of this AD installed. These engines are installed on, but not limited to, Boeing 777–200LR and 777– 300ER series airplanes. E:\FR\FM\10MYR1.SGM 10MYR1 26540 Federal Register / Vol. 72, No. 90 / Thursday, May 10, 2007 / Rules and Regulations TABLE 1.—TURBINE CENTER FRAME LIFE LIMIT BY P/N Part No. 2061M60G09 2061M60G22 2061M60G23 2061M60G24 2061M60G26 2061M60G27 Life limitation in flight cycles ........................ ........................ ........................ ........................ ........................ ........................ 14,300 14,300 14,300 14,300 14,300 14,300 (d) This AD results from a report that GE inadvertently omitted some TCF P/Ns from the Airworthiness Limitations Section (ALS) of the engine manual. We are issuing this AD to prevent structural failure of the TCF with uncontained failure of low pressure turbine (LPT) rotating parts. Uncontained failure of the LPT rotating parts could result in damage to the airplane and possible loss of control of 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. Modify the Airworthiness Limitations Section of the Engine Manual (f) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations Section of the applicable Engine Manual to include the TCF P/Ns and flight cycle limitation specified in Table 1 of this AD. (g) After the effective date of this AD, except as provided in paragraph (h) of this AD, we will not approve any alternative replacement times for a TCF with a P/N listed in Table 1 of this AD. 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. Related Information (i) None. Issued in Burlington, Massachusetts, on May 3, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–8990 Filed 5–9–07; 8:45 am] cprice-sewell on PRODPC61 with RULES BILLING CODE 4910–13–P 14:29 May 09, 2007 Federal Aviation Administration 14 CFR Parts 121 and 135 [Docket No. FAA–2002–6717; Amendment Nos. 121–329, 135–108] RIN 2120–AI03 Extended Operations (ETOPS) of MultiEngine Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: Unsafe Condition VerDate Aug<31>2005 DEPARTMENT OF TRANSPORTATION Jkt 211001 SUMMARY: The Federal Aviation Administration is correcting a final rule published in the Federal Register on January 16, 2007 (72 FR 1808). That final rule applied to air carrier (part 121), commuter, and on-demand (part 135) turbine powered multi-engine airplanes used in passenger-carrying, and some all-cargo, extended-range operations. This amendment adds the Office of Management and Budget (OMB) Information Collection Control Number indicating approval of the information collection requirements of the final rule. This amendment also makes three corrections: In part 135, it corrects the dual maintenance paragraph to conform to part 121 and deletes a redundant defining of ‘‘adequate airport’’; in part 121 it corrects the rule language applicable to those persons who must accomplish and certify by signature the completion of ETOPS tasks; and in parts 121 and 135 it corrects the hours required for notification of maintenance problems based on an earlier FAA rulemaking. None of these changes is substantive, but will clarify the final rule for the affected public. DATES: These amendments become effective May 10, 2007. FOR FURTHER INFORMATION CONTACT: For technical information on operational issues, contact Robert Reich, Flight Standards Service, Federal Aviation Administration, 800 Independence Ave., SW, Washington, DC 20591; telephone (202) 267–8166; facsimile (202) 267–5229; e-mail Robert.Reich@faa.gov. SUPPLEMENTARY INFORMATION: Background The final rule, Extended Operations (ETOPS) of Multi-engine Airplanes, applied to air carrier (part 121), commuter, and on-demand (part 135) turbine powered multi-engine airplanes used in passenger-carrying, extendedrange operations. (January 16, 2007; 72 FR 1808) All-cargo operations in PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 airplanes with more than two engines of both part 121 and part 135 were exempted from the majority of this rule. The rule established regulations governing the design, operation and maintenance of certain airplanes operated on flights that fly long distances from an adequate airport. It codified current FAA policy, industry best practices and recommendations, as well as international standards designed to ensure long-range flights will continue to operate safely. To ease the transition for current operators, the rule included delayed compliance dates for certain ETOPS requirements. Information Collection Requirements Control Number As required by the Paperwork Reduction Act of 1995 (44 U.S.C. 3507(d)), the FAA submitted a copy of the new information collection requirements in this final rule to the Office of Management and Budget for its review. OMB approved the collection of this information and assigned OMB Control Number 2120–0718. Explanation of Corrections Part 135 Conforming Changes for Appendix G Following publication of the final rule, it was brought to the attention of the FAA that the concept of ‘‘dual maintenance’’ in the final rule did not codify existing FAA ETOPS guidance as published in the notice of proposed rulemaking. Essentially, the final rule would have prohibited the maintenance of more than one ETOPS significant system during the same maintenance visit. The FAA published a correction to the final rule on February 15, 2007, revising this language for part 121. (See 72 FR 7346; 15 February, 2007.) Today’s amendment makes the same change for 14 CFR 135 in appendix G, section G135.2.8 (c). Section G135.2.8 (c) is changed to read: ‘‘(c) Limitations on dual maintenance. (1) Except as specified in paragraph G135.2.8 (c) (2) of this appendix, the certificate holder may not perform scheduled or unscheduled dual maintenance during the same maintenance visit on the same or a substantially similar ETOPS Significant System listed in the ETOPS maintenance document, if the improper maintenance could result in the failure of an ETOPS Significant System. (2) In the event dual maintenance as defined in paragraph G135.2.8 (c) (1) of this appendix can not be avoided, the certificate holder may perform maintenance provided: (i) The maintenance action on each affected ETOPS Significant System is performed by a different technician, or (ii) The maintenance action on each affected ETOPS Significant System is E:\FR\FM\10MYR1.SGM 10MYR1

Agencies

[Federal Register Volume 72, Number 90 (Thursday, May 10, 2007)]
[Rules and Regulations]
[Pages 26538-26540]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-8990]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27283; Directorate Identifier 2007-NE-05-AD; 
Amendment 39-15046; AD 2007-10-05]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) GE90 
Series Turbofan Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
GE90-110B1, -113B, and -115B series turbofan engines with certain 
Turbine Center Frames (TCFs) installed. This AD requires removing 
certain TCFs, listed by part number (P/N) in this AD, from service 
before exceeding 14,300 flight cycles. This AD results from a report 
that GE inadvertently omitted some TCF P/Ns from the Airworthiness 
Limitations Section (ALS) of the engine manual. We are issuing this AD 
to prevent structural failure of the TCF with uncontained failure of 
low pressure turbine (LPT) rotating parts. Uncontained failure of the 
LPT rotating parts could result in damage to the airplane and possible 
loss of control of the airplane.

DATES: This AD becomes effective June 14, 2007.
    We must receive any comments on this AD by July 9, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office,

[[Page 26539]]

FAA, Engine and Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; telephone (781) 238-7751; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On January 12, 2007, we received a report 
from GE that they had inadvertently omitted six TCFs P/Ns from the ALS 
of the engine manual. GE introduced an improved, redesigned TCF after 
the initial engine certification. GE identified the new designs with 
new P/Ns. The TCF is a life-limited part. Engine life-limited parts are 
listed in the ALS of the Engine Manual and must be removed from service 
at or before reaching their life limit. Because GE has not included in 
the ALS all the TCF P/Ns that are currently in service, operators might 
not be tracking the accumulated flight cycles on those P/N TCFs. 
Exceeding the TCF life limit will exceed the low-cycle fatigue design 
capability of the material structure. If the TCF fails, the LPT 
structure could fail with rotating parts liberating and impacting the 
fuselage of the airplane. This condition, if not corrected, could 
result in loss of control of the airplane.

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 engines of the same type design. We are issuing this AD to 
prevent structural failure of the TCF with uncontained failure of LPT 
rotating parts. Uncontained failure of the LPT rotating parts could 
result in damage to the airplane and possible loss of control of the 
airplane. This AD requires removing from service certain TCFs, listed 
by P/N in this AD, at or before accumulating 14,300 flight cycles.

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-2007-27283; 
Directorate Identifier 2007-NE-05-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 https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this 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 
https://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 Docket Management 
Facility 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 this 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. 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:

2007-10-05 General Electric Company: Amendment 39-15046 Docket No. 
FAA-2007-27283; Directorate Identifier 2007-NE-05-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 14, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) GE90-110B1, 
-113B, and -115B series engines with a Turbine Center Frame (TCF) 
that has a part number listed in the following Table 1 of this AD 
installed. These engines are installed on, but not limited to, 
Boeing 777-200LR and 777-300ER series airplanes.

[[Page 26540]]



            Table 1.--Turbine Center Frame Life Limit by P/N
------------------------------------------------------------------------
                                                               Life
                        Part No.                           limitation in
                                                           flight cycles
------------------------------------------------------------------------
2061M60G09..............................................          14,300
2061M60G22..............................................          14,300
2061M60G23..............................................          14,300
2061M60G24..............................................          14,300
2061M60G26..............................................          14,300
2061M60G27..............................................          14,300
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report that GE inadvertently omitted 
some TCF P/Ns from the Airworthiness Limitations Section (ALS) of 
the engine manual. We are issuing this AD to prevent structural 
failure of the TCF with uncontained failure of low pressure turbine 
(LPT) rotating parts. Uncontained failure of the LPT rotating parts 
could result in damage to the airplane and possible loss of control 
of 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.

Modify the Airworthiness Limitations Section of the Engine Manual

    (f) Within 30 days after the effective date of this AD, revise 
the Airworthiness Limitations Section of the applicable Engine 
Manual to include the TCF P/Ns and flight cycle limitation specified 
in Table 1 of this AD.
    (g) After the effective date of this AD, except as provided in 
paragraph (h) of this AD, we will not approve any alternative 
replacement times for a TCF with a P/N listed in Table 1 of this AD.

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.

Related Information

    (i) None.

    Issued in Burlington, Massachusetts, on May 3, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-8990 Filed 5-9-07; 8:45 am]
BILLING CODE 4910-13-P
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