[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:
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: 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:
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
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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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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