Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55517 

the meaning of section 654 of the 

Treasury and General Government 

Appropriations Act, 1999, Pub. L. 105–

277, 112 Stat. 2681 (1998). 

By the National Credit Union 

Administration Board on September 15, 

2005. 

Mary Rupp, 

Secretary of the Board. 

■ Accordingly, the NCUA amends 12 

CFR parts 703, 790, and 791 as follows: 

PART 703—INVESTMENT AND 

DEPOSIT ACTIVITIES 

■ 1. The authority citation for part 703 

continues to read as follows: 

Authority: 12 U.S.C. 1757(7), 1757(8), 

1757(15). 

§ 703.19 [Amended] 

■ 2. In 12 CFR 703.19(c) remove the 

words ‘‘Office of Strategic Program 

Support and Planning’’ and add, in their 

place, the words ‘‘Office of Capital 

Markets and Planning’’. 

PART 790—DESCRIPTION OF NCUA; 

REQUESTS FOR AGENCY ACTION 

■ 3. The authority citation for part 790 

continues to read as follows: 

Authority: 12 U.S.C. 1766, 1789, and 

1795f. 

§ 790.2 [Amended] 

■ 4. Amend § 790.2 as follows: 

■ a. In the table below, for 12 CFR 

790.2(b), remove the title indicated in 

the left column from wherever it 

appears in the section, and add the title 

indicated in the right column: 

Remove Add 

Office of Credit Union Development ........................................................ Office of Small Credit Union Initiatives. 

Office of Strategic Program Support and Planning .................................. Office of Capital Markets and Planning. 

■ b. Redesignate paragraph (b)(5)(i) as 

paragragh (b)(5), and paragraph (b)(5)(ii) 

as new paragraph (b)(15). 

■ c. Add the word ‘‘graphics;’’ in the 

last sentence of paragraph (b)(4) after 

the word ‘‘printing;’’ and remove the 

last sentence of paragraph (b)(11). 

PART 791—RULES OF NCUA BOARD 

PROCEDURE; PROMULGATION OF 

NCUA RULES AND REGULATIONS; 

PUBLIC OBSERVATION OF NCUA 

BOARD MEETINGS 

■ 5. The authority citation for part 791 

continues to read as follows: 

Authority: 12 U.S.C. 1766, 1789 and 5 

U.S.C. 552b. 

§ 791.4 [Amended] 

■ 6. In 12 CFR 791.4(b)(1), remove the 

word ‘‘routine’’ and add, in its place, 

the words ‘‘administrative or time 

sensitive, for example, enforcement or 

interagency actions requiring prompt 

Board action’’. 

[FR Doc. 05–18747 Filed 9–21–05; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22484; Directorate 

Identifier 2003–NM–270–AD; Amendment 

39–14286; AD 2005–19–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–202, –223, –243, and –343 

Airplanes; and Model A340–313 

Airplanes 

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 certain 

Airbus Model A330–202, –223, –243, 

and –343 airplanes; and certain Model 

A340–313 airplanes. This AD requires a 

one-time inspection for discrepancies of 

the attachment bolts of the windshield 

central retainer, and corrective actions if 

necessary. This AD results from a report 

indicating that, during production, the 

windshield central retainer may have 

been installed with attachment bolts 

that were too short, which prevented the 

thread of the bolt from fully engaging in 

the self-locking nut. We are issuing this 

AD to prevent loosened attachment 

bolts, which could result in loss of the 

windshield and consequent reduced 

structural integrity of the airplane. 

DATES: Effective October 7, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 7, 2005. 

We must receive comments on this 

AD by November 21, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments 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. 

• 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A330–

202, –223, –243, and –343 airplanes, 

and Model A340–313 airplanes. The 

windshield central retainer is attached 

with long-thread bolts of a certain 

length. During production on affected 

airplanes, the windshield central 

55518 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

retainer may have been installed with 

slightly shorter bolts having standard 

thread length. In that case, despite 

proper torquing, the bolt thread might 

not fully engage in the self-locking nut. 

Loosened attachment bolts, if not 

corrected, could result in loss of the 

windshield and consequent reduced 

structural integrity of the airplane. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A330–56–3006 and A340–56–4006, both 

Revision 01, dated March 24, 2003. The 

service bulletins describe procedures for 

inspecting the windshield central 

retainer to measure the protrusion of the 

attachment bolts, and replacing 

inadequate bolts and their 

corresponding nuts. Accomplishing the 

actions specified in the service 

information is intended to adequately 

address the unsafe condition. To ensure 

the continued airworthiness of these 

airplanes in France, the DGAC 

mandated the service information and 

issued French airworthiness directives 

2003–123(B) R1 and 2003–124(B) R1, 

both dated April 16, 2003. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for airplanes of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

prevent loosened attachment bolts of the 

windshield central retainer, which 

could result in loss of the windshield 

and reduced structural integrity of the 

airplane. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed below. 

Clarification of Inspection Terminology 

The service bulletins refer to a 

‘‘detailed visual inspection’’ for 

measuring the length of the attachment 

bolts. We have determined that the 

procedures in the service bulletins 

should be considered a ‘‘detailed 

inspection.’’ Note 1 in this AD defines 

this type of inspection. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

In that event, the required actions 

would take about 1 work hour per 

airplane, at an average labor rate of $65 

per work hour. Based on these figures, 

we estimate the cost of this AD to be $65 

per airplane. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to the address listed under 

the ADDRESSES section. Include ‘‘Docket 

No. FAA–2005–22484; Directorate 

Identifier 2003–NM–270–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD 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 that 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 Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System 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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55519 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–19–21 Airbus: Amendment 39–14286. 

Docket No. FAA–2005–22484; 

Directorate Identifier 2003–NM–270–AD. 

Effective Date 

(a) This AD becomes effective October 7, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Airbus airplanes, 

certificated in any category, listed in Table 1 

of this AD. 

TABLE 1.—APPLICABILITY

Airbus model— As identified in Airbus service bulletin— 

A330–202, –223, –243, and –343 airplanes .............................................................. A330–56–3006, Revision 01, dated March 24, 2003. 

A340–313 airplanes .................................................................................................... A340–56–4006, Revision 01, dated March 24, 2003. 

Unsafe Condition 

(d) This AD results from a report indicating 

that, during production, the windshield 

central retainer may have been installed with 

attachment bolts that were too short, which 

prevented the thread of the bolt from fully 

engaging in the self-locking nut. We are 

issuing this AD to prevent loosened 

attachment bolts, which could result in loss 

of the windshield and consequent reduced 

structural integrity 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. 

Inspection 

(f) Within 6 months after the effective date 

of this AD, perform a detailed inspection of 

the windshield central retainer for 

discrepancies of the attachment bolts, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

56–3006 or A340–56–4006, both excluding 

Appendix 01, Revision 01, dated March 24, 

2003; as applicable. If the protrusion of any 

attachment bolt is not within the limits 

specified in the service bulletin, replace the 

bolt and corresponding nut with new parts 

before further flight in accordance with the 

service bulletin. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Modification According to Previous Issue of 

Service Bulletin 

(g) Inspecting the windshield central 

retainer, and doing applicable corrective 

actions, is also acceptable for compliance 

with the requirements of paragraph (f) of this 

AD if done before the effective date of this 

AD in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

56–3006 or A340–56–4006, both dated March 

12, 2003; as applicable. 

No Reporting Requirement 

(h) Although Airbus Service Bulletins 

A330–56–3006 and A340–56–4006 specify 

sending an inspection report to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(j) French airworthiness directives 2003–

123(B) R1 and 2003–124(B) R1, both dated 

April 16, 2003, also address the subject of 

this AD. 

Material Incorporated by Reference 

(k) To perform the actions that are required 

by this AD, unless the AD specifies 

otherwise, you must use Airbus Service 

Bulletin A330–56–3006, excluding Appendix 

01, Revision 01, dated March 24, 2003; or 

Airbus Service Bulletin A340–56–4006, 

excluding Appendix 01, Revision 01, dated 

March 24, 2003; as applicable. The Director 

of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 13, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18782 Filed 9–21–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21355; Directorate 

Identifier 2005–NM–037–AD; Amendment 

39–14288; AD 2005–19–23] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F Series 

Airplanes Powered by General Electric 

or Pratt & Whitney Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

767 series airplanes. That AD currently 

requires repetitive inspections to detect 

discrepancies of the eight aft-most 

fastener holes in the horizontal tangs of 

the midspar fitting of the strut, and 

corrective actions if necessary. That AD 

also provides an optional terminating 

action for the repetitive inspections.