Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations 45243

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 

Federal Register / Vol. 69, No. 145 / Thursday, July 29, 2004 / Rules and Regulations 45245

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 the 

integrated 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