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


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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.

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

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 http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the 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
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                                                               Life
                        Part No.                           limitation in
                                                           flight cycles
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2061M60G09..............................................          14,300
2061M60G22..............................................          14,300
2061M60G23..............................................          14,300
2061M60G24..............................................          14,300
2061M60G26..............................................          14,300
2061M60G27..............................................          14,300
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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]
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