Document ID: FAA-2009-0018-0014
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; General Electric Company CF6-80C2 Series Turbofan Engines; Correction
Posted Date: 2009-12-14T05:00Z

[Federal Register: December 14, 2009 (Volume 74, Number 238)]
[Rules and Regulations]               
[Page 66042]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14de09-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0018; Directorate Identifier 2009-NE-01-AD; 
Amendment 39-16044; AD 2009-21-07]
RIN 2120-AA64

 
Airworthiness Directives; General Electric Company CF6-80C2 
Series Turbofan Engines; Correction

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

ACTION: Final rule; correction.

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SUMMARY: The FAA is correcting airworthiness directive (AD) 2009-21-07, 
which published in the Federal Register. That AD applies to General 
Electric Company (GE) CF6-80C2 series turbofan engines with certain 
thrust reverser ballscrew gearbox assembly adjustable-length end 
actuators installed. The unsafe condition statement of ``We are issuing 
this AD to prevent loss of asymmetric thrust and thrust control'', and 
rod-end part number ``MS2124S06'' in paragraph (j) are incorrect. This 
document corrects the unsafe condition statement and the part number. 
In all other respects, the original document remains the same.

DATES: Effective December 14, 2009.

FOR FURTHER INFORMATION CONTACT: Christopher J. Richards, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (781) 238-7133; fax 
(781) 238-7199.

SUPPLEMENTARY INFORMATION: On October 27, 2009 (74 FR 55126), we 
published a final rule AD, FR Doc. E9-24391, in the Federal Register. 
That AD applies to GE CF6-80C2 series turbofan engines with certain 
thrust reverser ballscrew gearbox assembly adjustable-length end 
actuators installed. We need to make the following corrections:

Sec.  39.13  [Corrected]

    On page 55126, in the second column, in the last sentence of the 
Summary Section, ``We are issuing this AD to prevent loss of asymmetric 
thrust and thrust control.'' is corrected to read ``We are issuing this 
AD to prevent asymmetric thrust and loss of thrust control.''
    On page 55129, in the third column, in the last sentence of 
paragraph (d), ``We are issuing this AD to prevent loss of asymmetric 
thrust and thrust control.'' is corrected to read ``We are issuing this 
AD to prevent asymmetric thrust and loss of thrust control.''
    On page 55130, in the first column, in paragraph (j), in the third 
line, ``MS2124S06'' is corrected to read ``MS21242S06.''

    Issued in Burlington, Massachusetts, on December 4, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-29483 Filed 12-11-09; 8:45 am]

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