Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60809

paragraphs (e)(1) and (e)(2) of this AD, except 

as provided by paragraph (f) of this AD. 

(1) Deactivate the Lucas humidifier, part 

number (P/N) M01AA0101, M01AB0101, 

M01AB0102, or M01AB0103, in accordance 

with the service bulletin. 

(2) Before further flight following the 

deactivation specified in paragraph (e)(1) of 

this AD, replace all APU and engine fire 

shutoff switches with new or serviceable 

switches in accordance with the service 

bulletin. 

Reactivation of Lucas Humidifier 

(f) For any airplanes on which Lucas 

humidifier, P/N M01AA0101, M01AB0101, 

M01AB0102, or M01AB0103 is reactivated 

after the effective date of this AD: Do the 

requirements of paragraphs (f)(1) and (f)(2) of 

this AD at the times specified in those 

paragraphs. 

(1) Within 18 months after reactivating the 

humidifier, and thereafter at intervals not to 

exceed 18 months, do the functional test 

required by paragraph (b) of this AD. 

(2) Within 36 months after reactivating the 

humidifier, and thereafter at intervals not to 

exceed 36 months, replace all APU and 

engine fire shutoff switches that have not 

been previously replaced per paragraph (c) of 

this AD. Do the replacements per paragraph 

(d) of this AD. 

Actions Accomplished Per Previous Issue of 

Service Bulletin 

(g) Unless otherwise specified in this AD, 

actions accomplished before the effective 

date of this AD per Boeing Alert Service 

Bulletin 747–26A2274, dated August 29, 

2002, are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

Alternative Methods of Compliance 

(h) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance for this AD. 

Incorporation by Reference 

(i) The actions shall be done in accordance 

with Boeing Alert Service Bulletin 747–

26A2274, Revision 1, dated January 9, 2003. 

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 Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. 

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.

Effective Date 

(j) This amendment becomes effective on 

November 17, 2004.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22563 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–211–AD; Amendment 

39–13819; AD 2004–20–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4 Series Airplanes and Model 

A300 B4–600, A300 B4–600R, and A300 

F4–600R (Collectively Called A300–

600) Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Airbus Model A300 B4 

series airplanes and all Airbus Model 

A300–600 series airplanes. That AD 

currently requires a one-time high 

frequency eddy current inspection to 

detect cracking of the splice fitting at 

fuselage frame (FR) 47 between stringers 

24 and 25; and corrective actions if 

necessary. This amendment requires 

new repetitive inspections of an 

expanded area and adds airplanes to the 

applicability in the existing AD. The 

actions specified by this AD are 

intended to detect and correct cracking 

of the splice fitting at fuselage FR 47, 

which could result in reduced structural 

integrity of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

17, 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, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

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) 

by superseding AD 2001–03–14, 

amendment 39–12118 (66 FR 10957, 

February 21, 2001), was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on August 4, 2004 (69 FR 

47035). The proposal is applicable to all 

Airbus Model A300 series airplanes and 

all Airbus Model A300–600 series 

airplanes. The action proposed to 

require new repetitive high frequency 

eddy current inspections to detect 

cracking of an expanded area, and 

corrective actions, if necessary; and to 

add airplanes to the applicability in the 

existing AD. 

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.

Clarification of Service Information 

Requirements for Paragraph (b) of This 

AD 

In our response to comments in the 

Preamble of the supplemental NPRM, 

we stated our intent to revise paragraphs 

(a), (b), and (c) of the supplemental 

NPRM to refer to Revision 02 of the 

referenced Airbus service bulletins as 

the appropriate sources of service 

information for accomplishment of the 

required actions. (Revision 01 of those 

service bulletins was referenced in the 

original NPRM for accomplishment of 

the required actions.) However, while 

we revised paragraphs (a) and (c) of the 

supplemental NPRM, we inadvertently 

omitted the revision to paragraph (b). 

Therefore, we have revised paragraph 

(b) of this final rule to reference 

Revision 02 of Airbus Service Bulletin 

A300–53–6123 as the appropriate 

source of service information for the 

required actions in that paragraph. 

Conclusion 

After careful review of the available 

data, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the change 

60810 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

described previously. The FAA has 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Cost Impact 

There are approximately 92 airplanes 

of U.S. registry that will be affected by 

this AD. 

The inspection of an expanded area 

that is required in this AD will take 

approximately 29 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. Based 

on these figures, the cost impact of the 

required inspection on U.S. operators is 

estimated to be $173,420, or $1,885 per 

airplane, per inspection cycle. 

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 

removing amendment 39–12118 (66 FR 

10957, February 21, 2001), and by adding 

a new airworthiness directive (AD), 

amendment 39–13819, to read as 

follows:

2004–20–14 Airbus: Amendment 39–13819. 

Docket 2002–NM–211–AD. Supersedes 

AD 2001–03–14, Amendment 39–12118.

Applicability: All Model A300 B4–600, 

B4–600R, and F4–600R (collectively called 

A300–600) series airplanes; and all Model 

A300 B4 series airplanes; certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct cracking of the splice 

fitting at fuselage frame (FR) 47, which could 

result in reduced structural integrity of the 

airplane, accomplish the following: 

Repetitive Inspections 

(a) For airplanes defined in Airbus Service 

Bulletin A300–53–0350, Revision 02, dated 

November 12, 2002: Do a high frequency 

eddy current (HFEC) inspection to detect 

cracking of the splice fitting at fuselage FR 

47 between stringers 24 and 26 (left- and 

right-hand sides), at the applicable times 

specified in paragraph (a)(1) or (a)(2) of this 

AD. Repeat the inspection thereafter at the 

earlier of the flight-cycle/flight-hour intervals 

specified in the applicable column in Table 

2 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of the service 

bulletin. Do the inspections in accordance 

with the service bulletin, excluding 

Appendix 01. 

(1) For airplanes that have accumulated 

20,000 or more total flight cycles as of the 

effective date of this AD: Do the initial 

inspection at the later of the times specified 

in paragraphs (a)(1)(i) and (a)(1)(ii) of this 

AD: 

(i) At the earlier of the flight-cycle/flighthour intervals after the effective date of this 

AD, as specified in the applicable column in 

Table 1 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of the service 

bulletin. 

(ii) Within 750 flight cycles or 1,500 flight 

hours after the effective date of this AD, 

whichever is first. 

(2) For airplanes that have accumulated 

fewer than 20,000 total flight cycles as of the 

effective date of this AD: Do the initial 

inspection at the later of the times specified 

in paragraphs (a)(2)(i) and (a)(2)(ii) of this 

AD. 

(i) At the earlier of the flight-cycle/flighthour intervals after the effective date of this 

AD, as specified in the applicable column in 

Table 1 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of the service 

bulletin. 

(ii) Within 1,800 flight cycles or 3,000 

flight hours after the effective date of this AD, 

whichever is first. 

(b) For airplanes defined in Airbus Service 

Bulletin A300–53–6123, Revision 02, dated 

November 12, 2002: Do the HFEC inspection 

required by paragraph (a) of this AD at the 

applicable times specified in paragraph (b)(1) 

or (b)(2) of this AD. Repeat the inspection 

thereafter at the earlier of the flight-cycle/

flight-hour intervals specified in the 

applicable column in Table 2 of Figure 1 and 

Sheet 1 of the Accomplishment Instructions 

of the service bulletin. Do the inspections in 

accordance with the service bulletin, 

excluding Appendix 01. 

(1) For airplanes that have accumulated 

10,000 or more total flight cycles as of the 

effective date of this AD: Do the initial 

inspection within 750 flight cycles or 1,900 

flight hours after the effective date of this AD, 

whichever is first.

(2) For airplanes that have accumulated 

fewer than 10,000 total flight cycles as of the 

effective date of this AD: Do the initial 

inspection at the later of the times specified 

in paragraphs (b)(2)(i) and (b)(2)(ii) of this 

AD. 

(i) At the earlier of the flight-cycle/flighthour intervals after the effective date of this 

AD, as specified in the applicable column in 

Table 1 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of the service 

bulletin. 

(ii) Within 1,500 flight cycles or 3,800 

flight hours after the effective date of this AD, 

whichever is first. 

Repair 

(c) Repair any cracking found during any 

inspection required by this AD before further 

flight, in accordance with Airbus Service 

Bulletin A300–53–0350 or A300–53–6123, 

both Revision 02, both excluding Appendix 

01, both dated November 12, 2002; as 

applicable. Where the service bulletins 

specify to contact Airbus in case of certain 

crack findings, this AD requires that a repair 

be accomplished before further flight in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent). 

Credit for Previous Issues of Airbus Service 

Bulletin 

(d) Accomplishment of the actions before 

the effective date of this AD in accordance 

with Airbus Service Bulletin A300–53–0350 

or A300–53–6123, Revision 01, dated 

December 18, 2001; is considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD. 

Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60811

Incorporation by Reference 

(f) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002; and Airbus Service 

Bulletin A300–53–6123, Revision 02, 

excluding Appendix 01, dated November 12, 

2002; as applicable. 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–

184(B), dated April 3, 2002.

Effective Date 

(g) This amendment becomes effective on 

November 17, 2004.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22564 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 510

New Animal Drugs; Change of 

Sponsors’ Addresses

AGENCY: Food and Drug Administration, 

HHS.

ACTION: Final rule.

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

changes of address for Alpharma Inc.; 

Intervet Inc.; and Ve`toquinol N.-A., Inc.

DATES: This rule is effective October 13, 

2004.

FOR FURTHER INFORMATION CONTACT:

David R. Newkirk, Center for Veterinary 

Medicine (HFV–100), Food and Drug 

Administration, 7500 Standish Pl., 

Rockville, MD 20855, 301–827–6967; email: david.newkirk@fda.gov.

SUPPLEMENTARY INFORMATION: Alpharma 

Inc., One Executive Dr., P.O. Box 1399, 

Fort Lee, NJ 07024, has informed FDA 

of a change of address to One Executive 

Dr., Fort Lee, NJ 07024. Intervet, Inc., 

P.O. Box 318, 405 State St., Millsboro, 

DE 19966, has informed FDA of a 

change of address to 29160 Intervet 

Lane, P.O. Box 318, Millsboro, DE 

19966. Ve`toquinol N.-A., Inc., 2000 

chemin Georges, Lavaltrie (PQ), Canada 

J0K 1H0, has informed FDA of a change 

of address to 2000 chemin Georges, 

Lavaltrie (PQ), Canada J5T 3S5. 

Accordingly, the agency is amending 

the regulations in 21 CFR 510.600 to 

reflect these changes of sponsors’

addresses.

This rule does not meet the definition 

of ‘‘rule’’ in 5 U.S.C. 804(3)(A), because 

it is a rule of ‘‘particular applicability.’’

Therefore, it is not subject to 

congressional review requirements in 5 

U.S.C. 801–808.

List of Subjects in 21 CFR Part 510

Administrative practice and 

procedure, Animal drugs, Labeling, 

Reporting and recordkeeping 

requirements.

■ Therefore, under the Federal Food, 

Drug, and Cosmetic Act and under 

authority delegated to the Commissioner 

of Food and Drugs and redelegated to the 

Center for Veterinary Medicine, 21 CFR 

part 510 is amended as follows:

PART 510—NEW ANIMAL DRUGS

■ 1. The authority citation for 21 CFR 

part 510 continues to read as follows:

Authority: 21 U.S.C. 321, 331, 351, 352, 

353, 360b, 371, 379e.

§ 510.600 [Amended]

■ 2. Section 510.600 is amended:

a. In the table in paragraph (c)(1) in 

the entry for ‘‘Alpharma Inc.’’, by 

removing ‘‘P.O. Box 1399,’’;

b. In the table in paragraph (c)(1) in 

the entry for ‘‘Intervet, Inc.’’, by 

removing ‘‘Intervet, Inc., P.O. Box 318, 

405 State St.’’ and by adding in its place 

‘‘Intervet Inc., P.O. Box 318, 29160 

Intervet Lane’’;

c. In the table in paragraph (c)(1) in 

the entry for ‘‘Ve`toquinol N.-A., Inc.’’, 

by removing ‘‘J0K 1H0’’ and by adding 

in its place ‘‘J5T 3S5’’;

d. In the table in paragraph (c)(2) in 

the entry for ‘‘046573’’, by removing 

‘‘P.O. Box 1399’’;

e. In the table in paragraph (c)(2) in 

the entry for ‘‘057926’’ by removing 

‘‘Intervet, Inc., P.O. Box 318, 405 State 

St.’’ and by adding in its place ‘‘Intervet 

Inc., P.O. Box 318, 29160 Intervet 

Lane’’; and

f. In the table in paragraph (c)(2) in 

the entry for ‘‘059320’’, by removing 

‘‘J0K 1H0’’ and by adding in its place 

‘‘J5T 3S5’’.

Dated: September 16, 2004.

Bernadette A. Dunham,

Deputy Director, Office of New Animal Drug 

Evaluation, Center for Veterinary Medicine.

[FR Doc. 04–22915 Filed 10–12–04; 8:45 am]

BILLING CODE 4160–01–S

DEPARTMENT OF STATE

22 CFR Part 51 

RIN 1400–ZA07 

[Public Notice 4859] 

Passport Procedures—Amendment to 

Passport Regulations

AGENCY: State Department.

ACTION: Interim rule.

SUMMARY: This interim rule amends the 

regulation implementing the statutory 

requirement that both parents consent to 

issuance of a passport for children 

under 14 years to require that a 

statement of consent submitted in 

support of a minor’s application be 

notarized. The rule will ensure that the 

individual providing the signature is 

properly identified.

DATES: The effective date is November 1. 

The Department will accept comments 

from the public up to 30 days from 

November 12, 2004.

ADDRESSES: Written comments should 

be addressed to: Chief, Legal Division, 

Office of Passport Policy, Planning and 

Advisory Services, 2100 Pennsylvania 

Ave., NW., 3rd Floor, Washington, DC 

20037. E-mail for comments: 

PassportRules@state.gov.

Persons with access to the internet 

may also view this notice and provide 

comment by going to the regulations.gov 

Web site at: http://www.regulations.gov/

index.cfm.

FOR FURTHER INFORMATION CONTACT:

Sharon Palmer-Royston, Office of 

Passport Policy, Planning and Advisory 

Services, Bureau of Consular Affairs, 

Department of State 202–663–2662; Fax 

202–663–2654.

SUPPLEMENTARY INFORMATION: 22 U.S.C. 

213 provides that before a U.S. passport 

can be issued the applicant ‘‘shall 

subscribe to and submit a written 

application which shall contain a true 

recital of each and every matter of fact 

which may be required by law or by any 

rules authorized by law.’’ Section 236 of 

the Admiral James W. Nance and Meg 

Donovan Foreign Relations 

Authorization Act, Public Law 106–113, 

113 Stat. 1501A–420 (22 U.S.C. 213n) 

(‘‘2-Parent Consent Statute’’) provides 

that the Secretary shall require 

documentary proof of both parents’ or