45578 Federal Register / Vol. 69, No. 146 / Friday, July 30, 2004 / Rules and Regulations 

levels of government. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to 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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–15–17 Fokker Services B.V.:

Amendment 39–13751. Docket 2002–

NM–302–AD.

Applicability: Model F27 Mark 100, 200, 

300, 400, 500, 600, and 700 series airplanes; 

certificated in any category; on which one or 

more of the modifications specified in 

paragraph 1.A.(1) of Fokker Service Bulletin 

F27/54–53, dated February 15, 2002, has 

been done. 

Compliance: Required as indicated, unless 

accomplished previously. 

To ensure the structural integrity of the 

engine-to-wing load path and prevent 

possible separation of the engine from the 

airplane, accomplish the following: 

One-Time Inspection 

(a) Within 24 months after the effective 

date of this AD: Do a one-time general visual 

inspection to determine the part numbers of 

the engine mounting frames, brace struts, and 

attachment fittings; per the Accomplishment 

Instructions of Fokker Service Bulletin F27/

54–53, dated February 15, 2002. Do the 

inspection and corrective action per the 

Accomplishment Instructions of the service 

bulletin. Do the related corrective action 

before further flight.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

Related Service Information

Note 2: Fokker Service Bulletin F27/54–53, 

dated February 15, 2002, references Fokker 

Service Bulletin 51–24, dated December 1, 

1971, as the appropriate source of service 

information for installing a new, improved 

engine mounting frame; and Fokker Service 

Bulletin F27/54–26, Revision 5, dated 

September 30, 2001, as the appropriate 

source of service information for installing 

new, improved, stronger brace struts and 

brackets.

Parts Installation 

(b) As of the effective date of this AD, no 

person may install on any airplane an engine 

mounting frame, brace strut, or attachment 

fitting unless that part has been identified as 

appropriate for the airplane configuration, as 

specified in the Accomplishment 

Instructions of Fokker Service Bulletin F27/

54–53, dated February 15, 2002. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Fokker Service Bulletin F27/54–53, 

dated February 15, 2002. This incorporation 

by reference was approved by the Director of 

the Federal Register in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Copies may 

be obtained from Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands. Copies may be inspected at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Note 3: The subject of this AD is addressed 

in Dutch airworthiness directive 2002–067, 

dated May 31, 2002.

Effective Date 

(e) This amendment becomes effective on 

September 3, 2004.

Issued in Renton, Washington, on July 19, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–17220 Filed 7–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–344–AD; Amendment 

39–13750; AD 2004–15–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A310 series airplanes, that requires 

modification of certain wires in the 

right-hand wing. This action is 

necessary to ensure that fuel quantity 

indication wires are properly separated 

from wires carrying 115-volt alternating 

current (AC). Improper separation of 

such wires, in the event of wire damage, 

could lead to a short circuit and a 

possible ignition source, which could 

result in a fire in the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective September 3, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

3, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

Federal Register / Vol. 69, No. 146 / Friday, July 30, 2004 / Rules and Regulations 45579

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Airbus 

Model A310 series airplanes was 

published in the Federal Register on 

May 17, 2004 (69 FR 27868). That action 

proposed to require modification of 

certain wires in the right-hand wing. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

The FAA estimates that 46 airplanes 

of U.S. registry will be affected by this 

AD, that it will take approximately 9 

work hours per airplane to accomplish 

the required actions, and that the 

average labor rate is $65 per work hour. 

Required parts will cost approximately 

$1,880 per airplane. Based on these 

figures, the cost impact of the AD on 

U.S. operators is estimated to be 

$113,390, or $2,465 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to 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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–15–16 Airbus: Amendment 39–13750. 

Docket 2002–NM–344–AD.

Applicability: Model A310 series airplanes 

on which neither Airbus Modification 12427 

nor 12435 has been accomplished, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To ensure that fuel quantity indication 

wires are properly separated from wires 

carrying 115-volt alternating current (AC), 

accomplish the following: 

Modification 

(a) Within 4,000 flight hours after the 

effective date of this AD: Modify the routing 

of wires in the right-hand wing by installing 

cable sleeves, per the Accomplishment 

Instructions of Airbus Service Bulletin A310–

28–2148, Revision 01, dated October 29, 

2002. 

Actions Accomplished Previously 

(b) Modification of the routing of wires 

accomplished before the effective date of this 

AD per Airbus Service Bulletin A310–28–

2148, dated January 23, 2002, is acceptable 

for compliance with the corresponding 

requirements of paragraph (a) of this AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A310–28–2148, 

Revision 01, dated October 29, 2002. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from Airbus, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2002–

578(B), dated November 27, 2002.

Effective Date 

(e) This amendment becomes effective on 

September 3, 2004.

Issued in Renton, Washington, on July 19, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–17221 Filed 7–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

Bureau of the Census 

15 CFR Part 50

[Docket No. 040408109–4209–02] 

RIN 0607–AA41

Amendment to the Age Search Fee 

Structure

AGENCY: Bureau of the Census, 

Department of Commerce.

ACTION: Final rule.

SUMMARY: The Bureau of the Census 

(Census Bureau) is amending the Code 

of Federal Regulations (CFR), to increase 

the fee for conducting an Age Search 

from $40.00 to $65.00. The Census 

Bureau also is adding an additional 

charge of $20.00 per case for expedited 

requests requiring search results within 

one day. These changes are being made 

to recover the increase in operating 

costs associated with processing an Age 

Search request.

EFFECTIVE DATE: This rule is effective on 

August 30, 2004.

FOR FURTHER INFORMATION CONTACT:

Eileen Little, Chief, Survey Processing