[Federal Register Volume 70, Number 216 (Wednesday, November 9, 2005)]
[Rules and Regulations]
[Pages 67901-67903]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22207]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22712; Directorate Identifier 2005-NE-24-AD; 
Amendment 39-14367; AD 2005-23-09]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-
80E1A1, -80E1A2, -80E1A3, -80E1A4, and -80E1A4/B 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 
General Electric Company (GE) CF6-80E1A1, -80E1A2, -80E1A3, -80E1A4, 
and -80E1A4/B turbofan engines. This AD requires initial and repetitive 
fluorescent-penetrant inspections (FPI) of certain areas of high 
pressure compressor (HPC) cases, part number (P/N) 1509M97G07 and P/N 
2083M69G03. This AD results from the discovery that HPC cases, P/N 
1509M97G07 and P/N 2083M69G03, were inadvertently left out of the 
Airworthiness Limitations Section (ALS), Chapter 05-21-02, of GE Engine 
Manual, GEK 99376, Revision 17. We are issuing this AD to prevent 
failure of the HPC case aft mount flange, due to cracking.

DATES: This AD becomes effective November 25, 2005.
    We must receive any comments on this AD by January 9, 2006.

ADDRESSES: Use one of the following addresses to comment on this AD:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7176, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: In 2003, GE introduced a new stage 5 
variable stator vane system, through Service Bulletin (SB) No. CF6-80E1 
72-0237, dated January 21, 2003. To accommodate this system, GE SB No. 
CF6-80E1 72-0240, dated January 17, 2003, required reworking HPC case, 
P/N 1509M97G05, to P/N 2083M69G03. All HPC cases are supposed to have 
cyclic limits and inspection intervals specified in the ALS, Chapter 
05-21-02, of GE Engine Manual, GEK 99376, Revision 17. GE inadvertently 
left HPC cases P/N 1509M97G07 and P/N 2083M69G03 out of that GE Engine 
Manual ALS. GE's and FAA's intent is that all HPC cases must be 
inspected for cracking at the first hole in the aft flange above and 
below each horizontal split line flange. Currently, inspections of HPC 
cases P/N 1509M97G07 and P/N

[[Page 67902]]

2083M69G03 are not mandated. However, GE informed us that HPC case, P/N 
2083M69G03, is now included in the ALS, Chapter 05-21-02, of GE Engine 
Manual, GEK 99376, Revision 19, dated August 15, 2005, and, HPC case, 
P/N 1509M97G07, will be included in that Manual Chapter in Revision 20, 
to be issued in February 2006. This condition, if not corrected, could 
result in failure of the HPC case aft flange, due to cracking.

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 GE CF6-80E1A1, -80E1A2, -80E1A3, -80E1A4, and -80E1A4/B turbofan 
engines of the same type design. We are issuing this AD to prevent 
failure of the HPC case aft flange, due to cracking. For HPC cases, P/N 
1509M97G07 and P/N 2083M69G03, this AD requires:
    <bullet> Initial FPI of circumferential flange spotfaces at the 
first hole in the aft flange above and below each horizontal split line 
flange, at or before reaching 7,300 cycles-since-new; and
    <bullet> Repetitive FPI of circumferential flange spotfaces at the 
first hole in the aft flange above and below each horizontal split line 
flange, within 3,700 cycles-since-last-inspection.

FAA's Determination of the Effective Date

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

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-22712; 
Directorate Identifier 2005-NE-24-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 Docket 
Management System (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 (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:
2005-23-09 General Electric Company: Amendment 39-14367. Docket No. 
FAA-2005-22712; Directorate Identifier 2005-NE-24-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
25, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80E1A1, 
-80E1A2, -80E1A3, --80E1A4, and -80E1A4/B turbofan engines. These 
engines are installed on, but not limited to, Airbus Industrie A330 
series airplanes.

Unsafe Condition

    (d) This AD results from the discovery that high pressure 
compressor (HPC) cases, part number (P/N) 1509M97G07 and P/N 
2083M69G03, were inadvertently left out of the Airworthiness 
Limitations Section (ALS), Chapter 05-21-02, of GE Engine Manual GEK 
99376, Revision 17. We are issuing this AD to prevent failure of the 
HPC case aft flange, due to cracking.

[[Page 67903]]

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.

Initial Inspection

    (f) For HPC cases, P/N 1509M97G07 and P/N 2083M69G03, perform an 
initial fluorescent-penetrant inspection (FPI) of circumferential 
flange spotfaces at the first hole in the aft flange above and below 
each horizontal split line flange, at or before reaching 7,300 
cycles-since-new. See Figure 1 of this AD for reference. Information 
on inspecting these areas can be found in the ALS of GE Engine 
Manual GEK 99376, Revision 19, dated August 15, 2005.
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[GRAPHIC] [TIFF OMITTED] TR09NO05.011

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Repetitive Inspections

    (g) Perform repetitive FPI of circumferential flange spotfaces 
at the first hole in the aft flange above and below each horizontal 
split line flange, within 3,700 cycles-since-last-inspection. See 
Figure 1 of this AD for reference. Information on inspecting these 
areas can be found in the ALS of GE Engine Manual GEK 99376, 
Revision 19, dated August 15, 2005.

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 November 1, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-22207 Filed 11-8-05; 8:45 am]
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