This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

67901 

Vol. 70, No. 216 

Wednesday, November 9, 2005 

FARM CREDIT ADMINISTRATION 

12 CFR Parts 611, 612, 614, 615, and 

620 

RIN 3052–AC21 

Organization; Standards of Conduct 

and Referral of Known or Suspected 

Criminal Violations; Loan Policies and 

Operations; Funding and Fiscal 

Affairs, Loan Policies and Operations, 

and Funding Operations; Disclosure to 

Shareholders; Preferred Stock; 

Effective Date 

AGENCY: Farm Credit Administration. 

ACTION: Notice of effective date. 

SUMMARY: The Farm Credit 

Administration (FCA) published a final 

rule under parts 611, 612, 614, 615, and 

620 on September 13, 2005 (70 FR 

53901). This final rule amends our 

regulations governing preferred stock 

issued by Farm Credit System (FCS or 

System) banks, associations, and service 

corporations. This final rule requires 

greater board involvement and oversight 

in the retirement of preferred stock, 

enhances FCA’s current standards of 

conduct regulations to specifically 

address insider preferred stock 

transactions, modifies and streamlines 

the FCA review and clearance process, 

and requires disclosure of senior officer 

and director preferred stock 

transactions. Lastly, we add a new 

provision to require FCA prior approval 

of investments by FCS banks, 

associations, and service corporations in 

preferred stock of other System 

institutions, including the Federal 

Agricultural Mortgage Corporation. In 

accordance with 12 U.S.C. 2252, the 

effective date of the final rule is 30 days 

from the date of publication in the 

Federal Register during which either or 

both Houses of Congress are in session. 

Based on the records of the sessions of 

Congress, the effective date of the 

regulation is November 3, 2005. 

EFFECTIVE DATE: The regulation 

amending 12 CFR parts 611, 612, 614, 

615, and 620 published on September 

13, 2005 (70 FR 53901) is effective 

November 3, 2005, except for the 

amendments to §§ 612.2165(b)(12)–(15), 

615.5245(a), and 615.5270(d). An 

announcement of an effective date for 

these sections will be published at a 

later date. 

FOR FURTHER INFORMATION CONTACT: 

Dennis K. Carpenter, Senior Policy 

Analyst, Office of Regulatory Policy, 

Farm Credit Administration, McLean, 

VA 22102–5090, (703) 883–4498, TTY 

(703) 883–4434; or Howard Rubin, 

Senior Attorney, Office of General 

Counsel, Farm Credit Administration, 

McLean, VA 22102–5090, (703) 883– 

4020, TTY (703) 883–4020. 

Authority: 12 U.S.C. 2252(a)(9) and (10). 

Dated: November 3, 2005. 

Jeanette C. Brinkley, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 05–22276 Filed 11–8–05; 8:45 am] 

BILLING CODE 6705–01–P 

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. 

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 

67902 Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Rules and Regulations 

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 

■ 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: 

2005–23–09 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. 

Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Rules and Regulations 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. 

BILLING CODE 4910–13–P 

BILLING CODE 4910–13–C 

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] 

BILLING CODE 4910–13–P 


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