66250 Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Rules and Regulations 

Secretary, that determines that the 

second preceding school year 

requirement would otherwise have been 

met. 

Dated: October 20, 2005. 

Roberto Salazar, 

Administrator, Food and Nutrition Service. 

[FR Doc. 05–21785 Filed 11–1–05; 8:45 am] 

BILLING CODE 3410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22701; Directorate 

Identifier 2005–NE–37–AD; Amendment 39–

14356; AD 2005–22–12] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–80E1 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF6–80E1 series 

turbofan engines installed on Airbus 

Industrie A330 series airplanes. This AD 

requires a check of the holding torque 

of the thrust reverser actuation system 

(TRAS) locks, and if necessary a visual 

inspection of the TRAS lock flexible 

drive shafts, within 10 flight cycles after 

all aborted takeoffs in which the thrust 

reverser was deployed. This AD results 

from reports of operators finding several 

damaged TRAS lock flexible drive shafts 

during inspections and checks of the 

drive shafts. We are issuing this AD to 

prevent inadvertent in-flight 

deployment of the thrust reverser, 

which can result in loss of control of the 

airplane. 

DATES: This AD becomes effective 

December 2, 2005. 

We must receive any comments on 

this AD by January 3, 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. 

Contact Middle River Aircraft 

Systems, Mail Point 46, 103 Chesapeake 

Park Plaza, Baltimore, MD, 21220–4295, 

attn: Warranty Support, telephone: (410) 

682–0094, fax: (410) 682–0100 for the 

alert service bulletin identified in this 

AD. Contact General Electric Company 

via Lockheed Martin Technology 

Services, 10525 Chester Road, Suite C, 

Cincinnati, Ohio 45215, telephone (513) 

672–8400, fax (513) 672–8422, for the 

temporary revision identified in this 

AD. Contact Airbus, 1 Rond Point 

Maurice Bellionte, 31707 Blagnac 

Cedex, France, for the Airbus A330 

manual information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Karen Curtis, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Office Park; 

telephone (781) 238–7192; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

issued AD 2002–10–08 (67 FR 36090, 

May 23, 2002) on May 9, 2002. That AD 

requires initial and repetitive thrust 

reverser inspections and checks. That 

AD resulted from reports of serviceinduced hardware deterioration that 

reduces the overall thrust reverser 

system protection against inadvertent 

deployment, which can result in loss of 

control of the airplane. Since we issued 

that AD, we received reports of 

operators finding several damaged 

TRAS lock flexible drive shafts. The 

operators found these damaged shafts 

while complying with the torque check 

specified in AD 2002–10–08. 

Investigation and analysis by GE and the 

FAA revealed that high end-of-stroke 

impact caused the damage. End-ofstroke impact is highest when the thrust 

reverser is commanded to deploy during 

an aborted take-off. The TRAS lock 

flexible drive shaft attaches the upper 

end actuator to the TRAS lock. When 

the system is commanded to deploy, the 

TRAS lock rotates to allow movement of 

the thrust reverser. At the end of the 

deployment stroke, the actuation system 

end-actuator hits its hard stop, while the 

TRAS lock continues to rotate. The 

TRAS lock then transmits its rotating 

inertia to the TRAS lock flexible drive 

shafts. This transmission of inertia can 

cause twisting, shearing, or bird caging 

of the drive shafts, leading to loss of the 

holding torque in the TRAS lock. Loss 

of holding torque reduces the 

effectiveness of the lock and if not 

corrected, can increase the probability 

of an in-flight inadvertent deployment 

of the thrust reverser, which can result 

in loss of control of the airplane. 

FAA’s Determination and Requirements 

of This AD 

Although this affected engine model 

is not used on any airplanes that are 

registered in the United States, the 

possibility exists that this engine model 

could be used on airplanes registered in 

the United States in the future. We are 

issuing this AD to prevent inadvertent 

in-flight deployment of the thrust 

reverser, which can result in loss of 

control of the airplane. This AD requires 

performing a check of the holding 

torque of the TRAS locks, and if 

necessary a visual inspection of the 

TRAS lock flexible drive shafts, within 

10 flight cycles after all aborted takeoffs 

in which the thrust reverser was 

deployed. This AD also requires 

replacing any damaged flexible drive 

shafts or locks. 

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–2005–22701; Directorate Identifier 

2005–NE–37–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 

Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Rules and Regulations 66251 

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 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 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 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 

■ 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2005–22–12 General Electric Company: 

Amendment 39–14356. Docket No. 

FAA–2005–22701; Directorate Identifier 

2005–NE–37–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 2, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–80E1 series turbofan 

engines. These engines are installed on, but 

not limited to, Airbus Industrie A330 series 

airplanes. 

Unsafe Condition 

(d) This AD results from reports of 

operators finding several damaged thrust 

reverser actuation system (TRAS) lock 

flexible drive shafts during inspections and 

checks of the drive shafts. We are issuing this 

AD to prevent inadvertent in-flight 

deployment of the thrust reverser, which can 

result in 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. 

(f) Within 10 flight cycles after all aborted 

takeoffs in which the thrust reverser was 

deployed, do the following: 

(1) Perform a check of the holding torque 

of the TRAS locks. 

(2) Based on the results of the holding 

torque check, perform a visual inspection of 

the TRAS lock flexible drive shafts if 

necessary. 

(3) Replace any damaged flexible drive 

shafts or locks. 

(g) Information on performing a check of 

the holding torque of the TRAS locks, and a 

visual inspection of the TRAS lock flexible 

drive shafts, can be found in the Airbus A330 

Aircraft Maintenance Manual, Task 72–00–

00–200–850. 

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) Middle River Aircraft Systems Alert 

Service Bulletin No. CF6–80E1 S/B 78A5097, 

dated June 14, 2005, and General Electric 

CF6–80E1 Series Engine Manual Temporary 

Revision No. 05–0049, dated August 24, 

2005, pertain to the subject of this AD. 

Issued in Burlington, Massachusetts, on 

October 27, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21805 Filed 11–1–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–21694; Airspace 

Docket No. 04–ASO–16] 

RIN 2120–AA66 

Establishment of Area Navigation 

Instrument Flight Rules Terminal 

Transition Routes (RITTR); 

Jacksonville, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes five 

Area Navigation Instrument Flight Rules 

Terminal Transition Routes (RITTR) in 

the Jacksonville, FL terminal area. The 

FAA originally proposed to establish 

seven routes as part of this action, but 

decided not to implement routes T–206 

and T–210 at this time. RITTRs are low 

altitude Air Traffic Service (ATS) 

routes, based on area navigation 

(RNAV), for use by aircraft having 

instrument flight rules (IFR)-approved 

Global Positioning System (GPS)/Global 

Navigation Satellite System (GNSS) 

equipment. The purpose of RITTR is to 

expedite the handling of IFR overflight 

traffic through busy terminal airspace 

areas. The FAA is taking this action to 

enhance safety and the efficient use of 

the navigable airspace in the 

Jacksonville, FL, terminal area.