Federal Register / Vol. 69, No. 192 / Tuesday, October 5, 2004 / Proposed Rules 59559

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 proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this proposed 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) if 

promulgated, 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 copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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 39–12481 (66 FR 

54416, October 29, 2001), and by adding 

a new airworthiness directive (AD), to 

read as follows:

Airbus: Docket 2003–NM–16–AD. 

Supersedes AD 2002–08–13, 

Amendment 39–12481.

Applicability: Model A300 B2 and B4 

series airplanes, certificated in any category; 

except those airplanes modified by Airbus 

Modification 12656. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of both spring boxes of 

the variable lever arm (VLA) due to corrosion 

damage, which could result in loss of rudder 

control and consequent reduced 

controllability of the airplane, accomplish 

the following: 

Restatement of the Requirements of AD 

2001–22–02 

(a) Within 10 days after November 13, 2001 

(the effective date of AD 2001–22–02, 

amendment 39–12481): Determine the part 

and amendment numbers of the VLA of the 

rudder control system to verify the parts were 

installed using the correct standard, in 

accordance with Airbus All Operators Telex 

(AOT) A300–27A0196, dated September 20, 

2001; or in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–27–0196, Revision 01, 

dated November 13, 2002. 

(1) If the part and amendment numbers 

shown are not correct, as specified in the 

AOT or the service bulletin, before further 

flight, do a detailed inspection of the VLA tie 

rod for damage (bent or ruptured rod) in 

accordance with the AOT or the service 

bulletin. 

(i) If the tie rod is damaged, replace the 

VLA with a new VLA in accordance with the 

AOT or the service bulletin. Such 

replacement ends the requirements of this 

paragraph. 

(ii) If the tie rod is not damaged, no further 

action is required by this paragraph. 

(2) If the part and amendment numbers 

shown are correct, no further action is 

required by this paragraph.

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.’’

New Requirements of This AD 

(b) For airplanes having a VLA with any 

part number (P/N) other than 418473–20 or 

418473–200: Within 500 flight hours after the 

effective date of this AD, do a detailed 

inspection of the tie rod for damage (bent or 

ruptured rod), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–27–0196, Revision 01, 

dated November 13, 2002. Repeat the 

inspection thereafter at intervals not to 

exceed 1,000 flight hours, until paragraph (f) 

of this AD has been accomplished. 

Replacement or Repair 

(c) If any damage is found to the VLA or 

the rudder control system during any 

inspection required by paragraph (a)(1) or (b) 

of this AD, before further flight, replace the 

VLA with a new VLA (including a follow-up 

test) in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300–

27–0196, Revision 01, dated November 13, 

2002. 

Actions Accomplished in Accordance With 

Previous Issue of the Service Bulletin 

(d) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A300–27–0196, 

dated September 20, 2002, are considered 

acceptable for compliance with the 

corresponding actions specified in 

paragraphs (a), (b), and (c) of this AD. 

No Reporting/Parts Return Requirements 

(e) Although Airbus Service Bulletin 

A300–27–0196, Revision 01, dated November 

13, 2002, describes procedures for submitting 

certain information to the manufacturer, and 

for returning certain parts to the 

manufacturer, this AD does not require those 

actions. 

Terminating Modification 

(f) Within 24 months after the effective 

date of this AD: Modify the applicable VLA, 

as required by either paragraph (f)(1) or (f)(2) 

of this AD, by doing all the applicable actions 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300–

27–0198, dated December 1, 2003. 

Accomplishing this modification ends the 

repetitive inspections required by paragraph 

(b) of this AD. 

(1) For any VLA having a spring box with 

P/N 418473–20 or 418473–200: Install a new 

identification plate and re-identify the VLA. 

(2) For any VLA having a spring box with 

P/N 418473 or 418473–100: Modify the 

spring box and re-identify the VLA.

Note 2: Airbus Service Bulletin A300–27–

0198, dated December 1, 2003, references 

Goodrich Actuation Systems Service Bulletin 

27–21–1H, Revision 3, dated December 8, 

2003, as an additional source of service 

information for accomplishing the 

modification.

Alternative Methods of Compliance 

(g) In accordance with 14 CFR 39.19, the 

Manager, International Branch, FAA, ANM–

116, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 3: The subject of this AD is addressed 

in French airworthiness directive F–2004–

091(B), dated June 23, 2004.

Issued in Renton, Washington, on 

September 29, 2004. 

Kalene C. Yanamura, 

Acting Manager, , Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22356 Filed 10–4–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION 

(DOT) 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19245; Directorate 

Identifier 2004–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300, –400, –500, –600, –700, 

–700C, –800 and –900 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

59560 Federal Register / Vol. 69, No. 192 / Tuesday, October 5, 2004 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 737–300, –400, 

–500, –600, –700, –700C, –800 and –900 

series airplanes. This proposed AD 

would require modifying the wiring for 

the master dim and test system. For 

certain airplanes, this proposed AD 

would also require related concurrent 

actions as necessary. This proposed AD 

is prompted by a report that the master 

dim and test system circuit does not 

have wiring separation of the test 

ground signal for redundant equipment 

in the flight compartment. We are 

proposing this AD to prevent a single 

fault failure inflight from simulating a 

test condition and showing test patterns 

instead of the selected radio frequencies 

on the communications panels, which 

could inhibit communication between 

the flightcrew and the control tower, 

affecting the continued safe flight of the 

airplane.

DATES: We must receive comments on 

this proposed AD by November 19, 

2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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. 

sbull By 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 service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Binh Tran, 

Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6485; fax (425) 917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19245; Directorate Identifier 

2004–NM–108–AD’’ in the subject line 

of your comments. We specifically 

invite comments on the overall 

regulatory, economic, environmental, 

and energy aspects of the proposed AD. 

We will consider all comments 

submitted by the closing date and may 

amend the proposed AD in light of those 

comments. 

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 proposed AD. 

Using the search function of that 

website, 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 can 

review DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you can visit http://

dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the Docket 

You can 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 DMS 

receives them. 

Discussion 

We have received a report indicating 

that the master dim and test system 

circuit does not have wiring separation 

of the test ground signal for redundant 

equipment in the flight compartment on 

certain Boeing Model 737–300, –400, 

–500, –600, –700, –700C, –800 and –900 

series airplanes. This condition could 

allow a single fault to simulate a test 

condition in the annunciators, switches, 

and displays in the flight compartment. 

A single fault failure could also simulate 

a test condition on the communications 

panels and show test patterns instead of 

the selected radio frequencies. The 

flightcrew needs to know the selected 

radio frequencies so they can 

communicate with the control tower. In 

flight, if test patterns appear instead of 

the selected radio frequencies on the 

communications panels, 

communication between the flightcrew 

and the control tower could be 

inhibited, and the continued safe flight 

of the airplane could be affected. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 737–33–

1132, Revision 1, dated March 4, 2004 

(for Model 737–300, –400, and–500 

series airplanes). We have also reviewed 

Boeing Service Bulletin 737–33–1133, 

Revision 2, dated December 4, 2003 (for 

Model 737–600, –700, –700C, –800, and 

–900 series airplanes). These service 

bulletins describe procedures for 

modifying the wiring for the master dim 

and test system. The modification 

includes re-routing existing wiring, 

creating splices, and performing 

operational testing. 

For certain airplanes, Service Bulletin 

737–33–1132 specifies prior or 

concurrent accomplishment of Boeing 

Service Bulletin 737–77–1022, currently 

at Revision 1, dated October 26, 1989. 

Service Bulletin 737–77–1022 describes 

procedures for installing an engine 

instrument system (EIS), and specifies 

prior or concurrent accomplishment of 

Boeing Service Bulletin 737–77–1023, 

Federal Register / Vol. 69, No. 192 / Tuesday, October 5, 2004 / Proposed Rules 59561

currently at Revision1, dated November 

9, 1989. Service Bulletin 737–77–1023 

describes procedures for modifying the 

advisory system for the EIS. Boeing 

Service Bulletin 737–77–1023 

references Smiths Industries Service 

Bulletin 311EDP–77–348 as an 

additional source of service information 

for modifying the existing EIS unit. 

For certain other airplanes, Service 

Bulletin 737–33–1133 specifies prior or 

concurrent accomplishment of Boeing 

Service Bulletin 737–26A1083, 

currently at Revision 1, dated November 

15, 2001; and Boeing Service Bulletin 

737–33–1121, currently at Revision 1, 

December 19, 2002. Service Bulletin 

737–26A1083 describes procedures for 

installing a smoke detection and fire 

extinguishing system in the cargo 

compartment. Service Bulletin 737–33–

1121 describes procedures for installing 

wiring for the test system for the audio 

control panel lamp. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. Therefore, we are 

proposing this AD, which would require 

modifying the wiring for the master dim 

and test system. The proposed AD 

would require you to use the service 

information described previously to 

perform these actions. 

Costs of Compliance 

This proposed AD would affect about 

2,868 airplanes worldwide, and 1,181 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this 

proposed AD.

ESTIMATED COSTS

Boeing service bulletin Work

hours 

Average

labor rate

per hour 

Parts Cost per

airplane 

737–33–1132, Revision 1 ........................................................... 14 $65 Nominal .................................... $910 

737–33–1133, Revision 2 ........................................................... 3 65 Nominal .................................... 195 

ESTIMATED CONCURRENT SERVICE BULLETIN COSTS

Boeing service bulletin Work

hours 

Average

labor rate

per hour 

Parts Cost per

airplane 

737–26A1083, Revision 1 (Only one airplane affected).185 ..................... $65 Between $30,000 and $36,400 ..... Between $42,025 and 

$48,425. 

737–33–1121, Revision 1 ............................ Between 5 and 6 65 Between $200 and $340 ............... Between $525 and $730. 

737–77–1022, Revision 1 (Only four airplanes affected).72 ....................... 65 No charge ...................................... $4,680. 

737–77–1023, Revision 1 ............................ Between 1 and 3 65 Nominal ......................................... Between $65 and $195. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed 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 proposed AD. See the ADDRESSES

section for a location to examine the 

regulatory evaluation.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 (AD):

Boeing: Docket No. FAA–2004–19245; 

Directorate Identifier 2004–NM–108–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by November 19, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

300, –400, and –500 series airplanes listed in 

Boeing Special Attention Service Bulletin 

737–33–1132, Revision 1, dated March 4, 

2004; and Model 737–600, –700, –700C, 

–800, and –900 series airplanes listed in 

Boeing Service Bulletin 737–33–1133, 

Revision 2, dated December 4, 2003; 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report that 

the master dim and test system circuit does 

not have wiring separation of the test ground 

signal for redundant equipment in the flight 

compartment. We are issuing this AD to 

prevent a single fault failure inflight from 

simulating a test condition and showing test 

patterns instead of the selected radio 

frequencies on the communications panels, 

which could inhibit communication between 

the flightcrew and the control tower, 

affecting the continued safe flight of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

59562 Federal Register / Vol. 69, No. 192 / Tuesday, October 5, 2004 / Proposed Rules 

the compliance times specified, unless the 

actions have already been done. 

Modification 

(f) Within 30 months after the effective 

date of this AD: Modify the wiring for the 

master dim test system in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–33–

1132, Revision 1, dated March 4, 2004 (for 

Model 737–300, –400, –500 series airplanes); 

and Boeing Service Bulletin 737–33–1133, 

Revision 2, dated December 4, 2003 (for 

Model 737–600, –700, –700C, –800, and –900 

series airplanes); as applicable. 

Actions Required To Be Accomplished Prior 

to or Concurrently With Paragraph (f) of 

This AD 

(g) Prior to or concurrently with 

accomplishment of paragraph (f) of this AD, 

do the actions specified in Table 1 of this AD, 

as applicable.

TABLE 1—PRIOR/CONCURRENT ACTIONS

For— Accomplish all actions associated with— According to the Accomplishment Instructions 

of—

Group 57 airplanes identified in Boeing Service 

Bulletin 737–33–1132, Revision 1, dated 

March 4, 2004.

Installing an engine instrument system (EIS) 

and.

Boeing Service Bulletin 737–77–1022, Revision 1, dated October 26, 1989. 

Modifying the advisory system for the EIS ...... Boeing Service Bulletin 737–77–1023, Revision 1, dated November 9, 1989. 

Group 4, 5, 7, 15, 16, 20, 24, 25, 29, 30, 33, 

37, 39, 40, 41, and 46 airplanes identified in 

Boeing Service Bulletin 737–33–1133, Revision 2, dated December 4, 2003.

Installing wiring for the test system for the 

audio control panel lamp.

Boeing Service Bulletin 737–33–1121, Revision 1, dated December 19, 2002. 

Group 2 airplanes identified in Boeing Service 

Bulletin 737–33–1121, Revision 1, dated December 19, 2002.

Installing splice SP896 ..................................... Boeing Service Bulletin 737–26A1083, Revision 1, dated November 15, 2001. 

Group 39 airplanes identified in Boeing Service 

Bulletin 737–33–1133, Revision 2, dated December 4, 2003.

Installing a smoke detection and fire extinguishing system in the cargo compartment.Boeing Service Bulletin 737–26A1083, Revision 1, dated November 15, 2001. 

Actions Accomplished per Previous Issue of 

Service Bulletins 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Special Attention Service Bulletin 

737–33–1132, dated March 20, 2003; Boeing 

Service Bulletin 737–33–1133, dated 

December 19, 2002; or Boeing Service 

Bulletin 737–33–1133, Revision 1, dated 

April 17, 2003, as applicable, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19.

Issued in Renton, Washington, on 

September 27, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–22355 Filed 10–4–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF HOMELAND 

SECURITY 

Bureau of Customs and Border 

Protection 

19 CFR 133 

RIN 1505–AB51 

Recordation of Copyrights and 

Enforcement Procedures To Prevent 

the Importation of Piratical Articles

AGENCY: Bureau of Customs and Border 

Protection, Department of Homeland 

Security.

ACTION: Proposed rule.

SUMMARY: As a result of technological 

advances available to those pirating 

copyrighted works, there has been a 

global increase in the importation of 

piratical works. Because of this 

increased risk to owners of protected 

copyrighted works and because most 

owners of copyrights in non-U.S. works 

do not register their copyrights as a 

matter of course, the Bureau of Customs 

and Border Protection (CBP) is 

proposing regulations that allow CBP to 

be more responsive to claims of piracy. 

The CBP Regulations currently 

require that in order to be eligible for 

border protection all claims to 

copyright, foreign and domestic, be 

registered with the U.S. Copyright 

Office. This document proposes to allow 

sound recordings and motion pictures 

or similar audio-visual works to be 

recorded with CBP while pending 

registration with the U.S. Copyright 

Office. This document also proposes to 

amend the CBP Regulations to enhance 

the protection of all non-U.S. works by 

allowing recordation without requiring 

registration with the U.S. Copyright 

Office. Lastly, the proposed regulations 

set forth changes to CBP’s enforcement 

procedures, including, among other 

things, enhanced disclosure provisions, 

protection for live musical performances 

and provisions to enforce the Digital 

Millennium Copyright Act.

DATES: Written comments must be 

submitted on or before November 4, 

2005.

ADDRESSES: You may submit comments, 

identified by RIN 1505–AB51, by either 

of the following methods: 

• Federal eRulemaking Portal: http://

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Regulations Branch, Office of 

Regulations and Rulings, Bureau of 

Customs and Border Protection, 1300 

Pennsylvania Avenue, NW. (Mint 

Annex), Washington, DC 20229. 

Comments submitted may be 

inspected at the Regulations Branch, 

Office of Regulations and Rulings, 

Bureau of Customs and Border 

Protection, 799 9th Street, NW., 5th 

Floor, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul 

Pizzeck, Esq. or George F. McCray, Esq., 

Intellectual Property Rights Branch, 

Office of Regulations and Rulings, (202) 

572–8710.

SUPPLEMENTARY INFORMATION: