
[Federal Register: July 1, 2009 (Volume 74, Number 125)]
[Rules and Regulations]               
[Page 31350-31351]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01jy09-3]                         


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0121; Directorate Identifier 2008-NE-36-AD; 
Amendment 39-15958; AD 2009-14-08]
RIN 2120-AA64

 
Airworthiness Directives; General Electric Company (GE) CF6-
80C2B5F Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
CF6-80C2B5F turbofan engines. This AD requires removing certain part 
number (P/N) high-pressure compressor rotor (HPCR) stages 11-14 spool/
shafts before they exceed a new, reduced life limit. This AD results 
from an internal GE audit that compared the life limited parts 
certification documentation to the airworthiness limitations section 
(ALS) of the instructions for continuing airworthiness (ICA). We are 
issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks 
caused by exceeding the life limit, which could result in a possible 
uncontained failure of the HPCR spool/shaft and damage to the airplane.

DATES: This AD becomes effective August 5, 2009.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Part, Burlington, MA 01803; e-mail: 
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-80C2B5F turbofan 
engines. We published the proposed AD in the Federal Register on 
February 20, 2009 (74 FR 7831). That action proposed to require 
removing certain P/N HPCR stages 11-14 spool/shafts before they exceed 
a new, reduced life limit.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter supports the proposal.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect one engine installed on an 
airplane of U.S. registry. We also estimate that the actions would 
require no work-hours per engine. No parts are required. Based on these 
figures, we estimate there is no cost of this AD to U.S. operators.

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 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
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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:

2009-14-08 General Electric Company: Amendment 39-15958. Docket No. 
FAA-2009-0121; Directorate Identifier 2008-NE-36-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
5, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2B5F 
turbofan engines with a high-pressure compressor rotor (HPCR) stages 
11-14 spool/shaft, part number (P/N) 1703M74G03, installed. These 
engines are installed on, but not limited to, Boeing 747 series 
airplanes.

Unsafe Condition

    (d) This AD results from an internal GE audit that compared the 
life limited parts certification documentation to the airworthiness 
limitations section (ALS) of the instructions for continuing 
airworthiness (ICA). We are issuing this AD to prevent HPCR stages 
11-14 spool/shaft fatigue cracks caused by exceeding the life limit, 
which could result in a possible uncontained failure

[[Page 31351]]

of the HPCR spool/shaft and damage to 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.

New Reduced Life Limit for the HPCR Stages 11-14 Spool/Shaft

    (f) Remove any CF6-80C2B5F turbofan engine that has an HPCR 
stages 11-14 spool/shaft, P/N 1703M74G03, before the spool/shaft 
meets or exceeds the new, reduced life cycle limit of 19,500 cycles.

Installation Prohibition

    (g) After the effective date of this AD, do not install any CF6-
80C2B5F turbofan engine that has an HPCR stages 11-14 spool/shaft, 
P/N 1703M74G03, that meets or exceeds 19,500 cycles.

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.

Special Flight Permits

    (i) Under 14 CFR part 39.23, we are prohibiting special flight 
permits for this AD.

Related Information

    (j) Robert Green, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Part, Burlington, MA 01803; e-mail: robert.green@faa.gov; 
telephone (781) 238-7754; fax (781) 238-7199.

Material Incorporated by Reference

    (k) None.

    Issued in Burlington, Massachusetts, on June 25, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-15513 Filed 6-30-09; 8:45 am]

BILLING CODE 4910-13-P
