### 45243 Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations about $140 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,845, or $205 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

– 12 Airbus: Amendment 39

– 13746. Docket 2003

–NM

– 272

–AD. Applicability: Model A330

– 202,

– 203,

– 223, and

– 243 airplanes, and A330

– 300 series airplanes; certificated in any category; on which Airbus Modification 50245 has not been done.

Compliance: Required as indicated, unless accomplished previously.

To prevent uncommanded in-flight shutdown of the auxiliary power unit (APU), which could result in loss of critical electrical systems when the airplane is operated in emergency electrical configuration, and consequent reduced controllability of the airplane, accomplish the following:

(a) Within 12 months after the effective date of this AD: Modify APU control box 5000VE by doing all the actions per the Accomplishment Instructions of Airbus Service Bulletin A330

– 49

– 3025, dated June 11, 2003. Alternative Methods of Compliance

(b) 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

(c) The actions shall be done in accordance with Airbus Service Bulletin A330

– 49

– 3025, dated June 11, 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 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 2003

– 350(B), dated September 17, 2003. Effective Date

(d) This amendment becomes effective on September 2, 2004.

Issued in Renton, Washington, on July 19, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04

– 16915 Filed 7

– 28

– 04; 8:45 am] **BILLING CODE 4910**
**– 13** 
**– P**  **DEPARTMENT OF TRANSPORTATION (DOT)**  **Federal Aviation Administration 14 CFR Part 39**  **[Docket No. FAA**
**– 2004** 
**– 18681; Directorate**  **Identifier 2004**
**– NM** 
**– 56** 
**– AD; Amendment 39** 
**– 13748; AD 2004** 
**– 15** 
**– 14]**  **RIN 2120**
**– AA64**  **Airworthiness Directives; Airbus Model A319** 
**– 131,** 
**– 132, and** 
**– 133; A320** 
**– 231,** 

**– 232, and** 
**– 233; and A321** 
**– 131 and** 

**– 231 Series Airplanes**  **AGENCY :**  Federal Aviation Administration (FAA), DOT. **ACTION :**  Final rule; request for comments. **SUMMARY :**  The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319

– 131,

– 132, and

– 133; A320

– 231,

– 232, and

– 233; and A321

– 131 and

– 231 series airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. This AD is prompted by reports of fretting and consequent arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. We are issuing this AD to prevent transient loss of certain systems and consequent reduced ability of the flightcrew to cope with adverse flight conditions. **DATES :**  Effective August 13, 2004.

The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of August 13, 2004.

We must receive comments on this AD by September 27, 2004. **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.


### 45244 Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations

• 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 the service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine this information 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. 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. Examining the Dockets

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 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. **FOR FURTHER INFORMATION CONTACT :**  Tim Dulin, Aerospace Engineer, International Branch, ANM

– 116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055

– 4056; telephone (425) 227

– 2141; fax (425) 227

– 1149. **SUPPLEMENTARY INFORMATION :**  The Direction Ge  ́ ne

 ́ rale de l ’ Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA of numerous reports of the intermittent interruption of the electrical power supply. The power interruption has been attributed to arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. The affected IDG connectors are installed on Airbus Model A319, A320, and A321 series airplanes equipped with International Aero Engines (IAE) Model V2500. In most of the incidents, the generator control unit (GCU) detected the arcing and shut down the associated IDG with only minor consequences. However, in some cases, the GCU

— because of intermittent arcing

— did not shut down the IDG. Investigation revealed that the arcing is due to fretting corrosion between the Cannon connector installed on the nacelle side of the firewall and the Souriau connector installed on the pylon side of the firewall. The following events have occurred or could occur during flight as a result of the intermittent loss of electrical power supply:

• Flickering cabin lights;
• Flickering primary flight and navigation displays;

• Transient disconnection of several systems (autopilot, yaw damper, auto throttle), triggering warnings from the electronic centralized aircraft monitoring (ECAM) displays and prompting diversions to the nearest available airport; and

• Loss of IDG power supply on the affected engine.

These conditions, if not corrected, could result in reduced ability of the flightcrew to cope with adverse flight conditions. Relevant Service Information

Airbus has issued Temporary Revision (TR) 4.02.00/20 to the A318/ 319/320/321 Airplane Flight Manual (AFM). The TR, dated May 3, 2004, provides background information and operational recommendations regarding the intermittent interruption of electrical power supply.

Airbus has also issued Service Bulletin A320

– 71

– 1030, dated February 27, 2003. The service bulletin describes procedures for replacing the IDG harness on the nacelle side of the firewall to eliminate the pin-to-socket arcing. Specifically, harnesses having Cannon connectors are replaced with harnesses having Souriau connectors. The Souriau connector provides a better connection of the IDG electrical harness at the firewall. Airbus Service Bulletin A320

– 71

– 1030 refers to International Aero Engines Information Bulletin V2500

–NAC

– 70

– 0736, dated January 28, 2003, as an additional source of information for the IDG harness/ connector replacement.

The DGAC approved these service documents. The DGAC has issued French airworthiness directive F

– 2004

– 074, dated May 26, 2004, to ensure the continued airworthiness of these airplanes in France. 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 AD action is necessary for products of this type design that are certificated for operation in the United States.

Therefore, we are issuing this AD to prevent transient loss of the systems connected to the affected arcing connector and consequent reduced ability of the flightcrew to cope with adverse flight conditions. This AD requires revising the AFM to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. The actions must be done in accordance with the service information described previously, except as described below. Differences Between FAA and DGAC Airworthiness Directive

The following differences have been coordinated between the FAA and the DGAC.

The French airworthiness directive does not require inspecting an IDG that has been shut down in accordance with the TR or that has been shut down automatically. We have determined that investigative and corrective actions (including an inspection for signs of arcing, and repair or replacement of any discrepant IDG harness/connector with a new harness/connector) are necessary due to the severity of the problem to prevent the unsafe condition from recurring. The inspections and corrective actions must be done in accordance with a method approved by the FAA.

The French airworthiness directive applies to all Model A319, A320, and A321 series airplanes equipped with IAE V2500 series engines

—regardless of the type of connector installed. This AD, however, applies to only those airplanes having Cannon connectors on the


### 45245 Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations
nacelle side of the firewall and Souriau connectors on the pylon side of the firewall. There have been no reported problems on airplanes equipped with Souriau connectors on both sides of the firewall. Therefore, the applicability of this AD excludes production airplanes that have been equipped with Souriau connectors on both sides of the firewall on both engines (accomplished via Airbus Modification 32943). This AD also includes a provision for replacing, on both engines, the IDG harnesses having Cannon connectors with IDG harnesses having Souriau connectors; this replacement would terminate the requirements of this AD. Interim Action

We consider this AD interim action. We may consider further rulemaking at a later date to mandate replacement of the subject connectors, as specified in Airbus Service Bulletin A320

– 71

– 1030. FAA ’ s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. 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 written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under **ADDRESSES .**  Include ‘‘ Docket No. FAA

– 2004

– 18681; Directorate Identifier 2004

–NM

– 56

–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 AD. Using the search function of our docket 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 can review the 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 with you. You can get more information about plain language at http://www/ faa.gov/language and http:// www.plainlanguage.gov

. 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. 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, 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2004

– 15

– 14 Airbus: Amendment 39

– 13748. Docket No. FAA

– 2004

– 18681; Directorate Identifier 2004

–NM

– 56

–AD. Effective Date (a) This AD becomes effective August 13, 2004. Affected ADs

(b) None. Applicability

(c) This AD applies to Airbus Model A319

– 131,

– 132, and

– 133; A320

– 231,

– 232, and

– 233; and A321

– 131 and ‘‘ 231 series airplanes; certificated in any category; except those airplanes on which Airbus Modification 32943 has been incorporated in production. Unsafe Condition

(d) This AD was prompted by reports of intermittent interruption of the electrical power supply due to fretting and consequent arcing of the electrical harness of theintegrated drive generator (IDG) at the pin-tosocket connector at the firewall. The FAA is issuing this AD to prevent the transient loss of certain systems and the consequent reduced ability of the flightcrew to cope with adverse flight conditions. 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. Revision of Airplane Flight Manual (AFM)

(f) Within 10 days after the effective date of this AD, revise the Limitations section of the Airbus A318/319/320/321 AFM to include the information in Temporary Revision (TR) 4.02.00/20, dated May 3, 2004. This may be done by inserting a copy of the TR into the AFM. When the TR has been included in general revisions of the AFM, those general revisions may be inserted into the AFM, provided the relevant information in the general revisions is identical to that in the TR. Post-IDG Shutdown Inspection

(g) If an IDG is shut down by the flightcrew in accordance with the TR procedures specified in paragraph (f) of this AD, or if an IDG is shut down automatically, do the actions specified in paragraph (g)(1) or (g)(2) of this AD.

(1) Before further flight, inspect the firewall connector of the affected IDG to detect signs of arcing, in accordance with a method approved by the Manager, International Branch, ANM

– 116, Transport Airplane Directorate, FAA. If any sign of arcing is detected: Before further flight, either repair the connector or replace the connector with a new connector, in accordance with a method approved by the Manager, International Branch, ANM

– 116.

(2) Operate the airplane with the affected IDG inoperative in accordance with the provisions and compliance periods specified in the FAA-approved Master Minimum Equipment List. Before further use of the affected IDG, do the actions specified in paragraph (g)(1) of this AD. Terminating Action

(h) Replacement of the IDG harnesses and connectors on both engines in accordance


### 45246 Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations
with Airbus Service Bulletin A320

– 71

– 1030, dated February 27, 2003, terminates the requirements of this AD.

Note 1: Airbus Service Bulletin A320

– 71

– 1030 refers to International Aero Engines Information Bulletin V2500

–NAC

– 70

– 0736, dated January 28, 2003, as an additional source of information for the harness/ connector replacement specified in paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs)

(i) The Manager, International Branch, ANM

– 116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference

(j) Unless this AD specifies otherwise, you must use Temporary Revision 4.02.00/20, dated May 3, 2004, to the Airbus A318/319/ 320/321 Airplane Flight Manual; and Airbus Service Bulletin A320

– 71

– 1030, dated February 27, 2003; as applicable; to perform the actions that are required by this AD. (Only page 1 of the temporary revision contains the date of the document.) The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the documents, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL

– 401, Nassif Building, Washington, DC; 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

. Related Information

(k) French airworthiness directive F

– 2004

– 074, dated May 26, 2004, also addresses the subject of this AD.

Issued in Renton, Washington, on July 16, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service [FR Doc. 04

– 16914 Filed 7

– 28

– 04; 8:45 am] **BILLING CODE 4910**
**– 13** 
**– P**  **DEPARTMENT OF TRANSPORTATION Federal Aviation Administration**  **14 CFR Part 39 [Docket No. 2003** 
**– NE** 
**– 12** 
**– AD; Amendment**  **39**
**– 13434; AD 2004** 
**– 01** 
**– 20]**  **RIN 2120**
**– AA64**  **Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines;**  **Correction AGENCY**  **:** Federal Aviation Administration, DOT. **ACTION :**  Final rule; correction **SUMMARY :**  This document makes a correction to Airworthiness Directive (AD) 2004

– 01

– 20, which is applicable to Rolls-Royce plc (RR) RB211

– 22B series, RB211

– 524B,

– 524C2,

– 524D4,

– 524G2,

– 524G3, and

– 524H series, and RB211

– 535C and

– 535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. That AD was published in the Federal Register on January 20, 2004 (69 FR 2661). The compliance information for the RB211

– 535C engine was inadvertently omitted from the AD. Also, under Related Information, the referenced service bulletin is not the latest revision. This document adds the omitted information and corrects the service bulletin reference. In all other respects, the original document remains the same. **EFFECTIVE DATE :**  Effective January 20, 2004. **FOR FURTHER INFORMATION CONTACT :**  Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238

– 7178; fax (781) 238

– 7199. **SUPPLEMENTARY INFORMATION :**  A final rule AD, FR Doc. 04

– 759, applicable to RR RB211

– 22B series, RB211

– 524B,

– 524C2,

– 524D4,

– 524G2,

– 524G3, and

– 524H series, and RB211

– 535C and

– 535E series turbofan engines with HPC stage 3 disc assemblies, P/Ns LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed, was published in the Federal Register on January 20, 2004 (69 FR 2661). The following corrections are needed: **§ 39.13 [Corrected]**  ■ On page 2663, in the first column, after paragraph (f)(4), add paragraph (f)(5) to read: ‘‘ (5) Discs in RB211

– 535C operation are unaffected by the interim rework cyclic band limits in Table 1 of this AD, but must meet the calendar life requirements of either paragraph (f)(1) or (f)(2) of this AD, as applicable. ’’ ■ On page 2663, in the second column, in paragraph (j), in the 4th and 5th lines, change ‘‘ RB.211

– 72

– 9661, Revision 3, dated December 20, 1999 ’’ to ‘‘ RB.211

– 72

– 9661, Revision 4, dated January 4, 2002 ’’

.

Issued in Burlington, MA, on July 21, 2004. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04

– 17283 Filed 7

– 28

– 04; 8:45 am] **BILLING CODE 4910**
**– 13** 
**– P** 
**DEPARTMENT OF THE TREASURY Office of Foreign Assets Control**  **31 CFR Part 541 Zimbabwe Sanctions Regulations**  **AGENCY :**  Office of Foreign Assets Control, Treasury. **ACTION :**  Interim final rule. **SUMMARY :**  The Office of Foreign Assets Control of the U.S. Department of the Treasury is adding new regulations to implement Executive Order 13288 of March 6, 2003, ‘‘ Blocking Property of Persons Undermining Democratic Processes or Institutions in Zimbabwe. ’’ **DATES :**  Effective Date: July 29, 2004.

Comments: Written comments must be received no later than September 27, 2004. **ADDRESSES :**  You may submit comments by any of the following methods:

• Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments.

• Agency Web Site: http:// www.treas.gov/offices/enforcement/ ofac/comment.html.

• Fax: Chief of Records, 202/622

– 1657.

• Mail: Chief of Records, ATTN: Request for Comments, Office of Foreign Assets Control, Department of the Treasury, 1500 Pennsylvania Avenue, NW., Washington, DC 20220.

Instructions: All submissions received must include the agency name and the FR Doc. number that appears at the end of this document. Comments received will be posted without change to http:/ /www.treas.gov/ofac, including any personal information provided. For detailed instructions on submitting comments and additional information on the rulemaking process, see the