61438 Federal Register / Vol. 62, No. 222 / Tuesday, November 18, 1997 / Rules and Regulations

Bulletin 600–0679, dated September 12,

1997.

(1) If no crack is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 600 landings.

(2) If any crack is detected and if all three

of the conditions specified in paragraphs

(a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD are

met, within 600 landings or 12 months after

the crack is detected, whichever occurs first,

repair the cracking in accordance with a

method approved by the Manager, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Until the

repair is accomplished, repeat the detailed

visual inspection at intervals not to exceed

100 landings.

(i) No more than one crack exists at each

corner radius, as specified in the service

bulletin; and

(ii) No crack extends under the angles

having P/N 600–32014–13 and P/N 600–

32014–15 on the aft side of the bulkhead

web; and

(iii) No crack exists in angles having P/N

600–32014–13 and P/N 600–32014–15 on the

aft side of the bulkhead web.

(3) If any cracking other than that

identified in paragraph (a)(2) of this AD is

detected, prior to further flight, repair it in

accordance with a method approved by the

Manager, New York ACO.

(b) For Model CL–600–2A12 (CL–601), CL–

600–2B16 (CL–601–3A/–3R), and CL–600–

2B16 (CL–604) series airplanes: Prior to the

accumulation of 1,100 total landings, or

within 100 landings after the effective date of

this AD, whichever occurs later, perform a

detailed visual inspection to detect cracks at

FS 409 of the bulkhead web (P/N 600–32014–

105/–137), in accordance with Canadair

Challenger Service Bulletin 601–0501, dated

September 12, 1997 [for Model CL–600–2A12

(CL–601) and CL–600–2B16 (CL–601–3A/–

3R) series airplanes); or Canadair Challenger

Service Bulletin 604–53–007, dated

September 30, 1997 [for Model CL–600–2B16

(CL–604) series airplanes]; as applicable.

(1) If no crack is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 600 landings.

(2) If any crack is detected and if all three

of the conditions specified in paragraphs

(b)(2)(i), (b)(2)(ii), and (b)(2)(iii) of this AD

are met, within 600 landings or 12 months

after the crack is detected, whichever occurs

first, repair the cracking in accordance with

a method approved by the Manager, New

York ACO. Until the repair is accomplished,

repeat the detailed visual inspection at

intervals not to exceed 100 landings.

(i) No more than one crack exists at each

corner radius, as specified in the service

bulletin; and

(ii) No crack extends under the angles

having P/N 600–32014–113 and P/N 600–

32014–115 on the aft side of the bulkhead

web; and

(iii) No crack exists in angles having P/N

600–32014–113 and P/N 600–32014–115 on

the aft side of the bulkhead web.

(3) If any cracking other than that

identified in paragraph (b)(2) of this AD is

detected, prior to further flight, repair it in

accordance with a method approved by the

Manager, New York ACO.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(e) The inspections shall be done in

accordance with Canadair Challenger Service

Bulletin 600–0679, dated September 12,

1997; Canadair Challenger Service Bulletin

601–0501, dated September 12, 1997; or

Canadair Challenger Service Bulletin 604–

53–007, dated September 30, 1997; 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 Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station Centre-ville,

Montreal, Quebec H3C 3G9, Canada. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Engine and Propeller Directorate, New York

Aircraft Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in Canadian airworthiness directive CF–97–

16, dated September 25, 1997.

(f) This amendment becomes effective on

December 3, 1997.

Issued in Renton, Washington, on

November 10, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30104 Filed 11–17–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–40–AD; Amendment

39–10162; AD 97–21–09]

RIN 2120–AA64

Airworthiness Directives; Allison

Engine Company Model 250–C47B

Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

existing airworthiness directive (AD)

96–24–09, applicable to Allison Engine

Company Model 250–C47B turboshaft

engines, that currently requires

replacing the engine main electrical

harness assembly with an improved

assembly, disabling the overspeed

solenoid, inspecting the engine control

unit (ECU) internal PW10 voltage to

determine electrical noise

characteristics, and replacing units not

considered serviceable. In addition, the

existing AD requires adding a placard to

the helicopter instrument panel

notifying the pilot that the overspeed

protection system is disabled and

removes a placard which was required

by priority letter AD 96–21–12; revises

the Bell Helicopter Textron, A Division

of Textron Canada Ltd. (BHTC) Model

407 Rotorcraft Flight Manual (RFM);

and requires maintenance actions to

clear the ECU of faults prior to each

flight. This amendment continues to

require replacing the engine main

electrical harness assembly with an

improved assembly, but adds the

requirements to install a new

hydromechanical unit (HMU) and ECU,

removing the placard notifying the pilot

that the overspeed protection system is

disabled, and revises the BHTC Model

407 RFM. This amendment is prompted

by the development of overspeed

protection system modifications to

reactivate the overspeed solenoid in

conjunction with raising the power

turbine overspeed trip point and

revising the overspeed system to default

to a minimum fuel flow in the event of

its activation. The actions specified by

this AD are intended to prevent

uncommanded inflight engine

shutdowns, which can result in

autorotation, forced landing, and

possible loss of the helicopter.

DATES: Effective December 3, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

3, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

January 20, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

97–ANE–40–AD, 12 New England

Executive Park, Burlington, MA 01803–

5299. Comments may also be sent via

the Internet using the following address:

‘‘9-ad-engineprop@faa.dot.gov’’.
Federal Register / Vol. 62, No. 222 / Tuesday, November 18, 1997 / Rules and Regulations 61439

Comments sent via the Internet must

contain the docket number in the

subject line.

The service information referenced in

this AD may be obtained from Allison

Engine Company, P.O. Box 420, Speed

Code P–40A, Indianapolis, IN 46206–

0420; telephone (317) 230–2720, fax

(317) 230–3381. This information may

be examined at the FAA, New England

Region, Office of the Assistant Chief

Counsel, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Patricia Bonnen, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, Small Airplane Directorate, 2300

East Devon Ave., Des Plaines, IL 60018;

telephone (847) 294–7134, fax (847)

294–7834.

SUPPLEMENTARY INFORMATION: On

October 11, 1996, the Federal Aviation

Administration (FAA) issued priority

letter airworthiness directive (AD) 96–

21–12, applicable to Bell Helicopter

Textron, A Division of Textron Canada

Ltd. (BHTC) Model 407 helicopters,

which prohibited further flight. That

action was prompted by reports of

uncommanded inflight engine

shutdowns on Allison Engine Company

Model 250–C47B turboshaft engines

installed in those helicopters. In each

case, the harness failed and caused the

electronic control unit (ECU) to go into

a fail fixed fuel flow condition.

Subsequent pilot action (reduction in

collective), caused the engine to reach

the overspeed trip point, with resultant

default to zero fuel flow and engine

shutdown. That condition, if not

corrected, could result in

uncommanded inflight engine

shutdowns, which can result in

autorotation, forced landing, and

possible loss of the helicopter.

Following issuance of priority letter

AD 96–21–12, the investigation revealed

that the cause of the uncommanded

inflight engine shutdowns was an ECU

fault to a fail fixed fuel flow condition,

and subsequent main rotor and power

turbine overspeed limit exceedances

coincident with pilot collective input.

These overspeed conditions activated

the analog overspeed trip, which

resulted in a command to zero fuel flow

and engine flameout. The ECU fault

resulted from a manufacturing defect in

the engine main electrical harness

assembly.

Additionally, in a related incident

involving another Allison Engine

Company engine model, an ECU fault to

fail fixed fuel flow was attributed to the

electrical noise characteristics of the

ECU internal PW10 voltage, as affected

by certain ECU power modulator

subcomponents. This same power

modulator Part Number (P/N) was in

use on the Allison Engine Company

Model 250–C47B engine application.

The noted ECU power modulator

problem could have also led to the

overspeed condition and uncommanded

engine shutdown described above, and

was therefore addressed in the following

AD action.

On November 15, 1996, the FAA

issued AD 96–24–09, Amendment 39–

9834 (61 FR 59828, November 25, 1996),

applicable to Allison Engine Company

Model 250-C47B turboshaft engines, to

require replacing the engine main

electrical harness assembly with an

improved assembly, disabling the

overspeed solenoid (thereby

deactivating the engine overspeed

protection system), inspecting the ECU

internal PW10 voltage to determine

electrical noise characteristics, and

replacing units not considered

serviceable due to excessive electrical

noise. In addition, AD 96–24–09

requires adding a helicopter instrument

panel placard notifying the pilot that the

overspeed protection system is disabled;

removes the placard required by AD 96–

21–12 which prohibited further flight;

and revises the BHTC Model 407

Rotorcraft Flight Manual (RFM) to

clarify emergency flight procedures and

to require maintenance actions to clear

Full Authority Digital Engine Control

(FADEC) fault annunciations prior to

each flight. That action was prompted

by investigation into the causes of the

inflight engine shutdowns.

The original decision to disconnect

the overspeed protection system was

arrived at by comparing the safety of

operating with the system enabled to the

safety of operating with the system

disabled. By operating with the system

enabled, there was a likely consequence

of other FADEC failures leading to an

overspeed trip and resulting in an

engine shutdown as had happened

previously. Disabling the overspeed

protection system eliminated the

possibility of inadvertent activation and

engine shutdown, but introduced new

risks associated with engine power

turbine shaft failure or rotorcraft drive

train failure leading to uncontained

blade shedding and hazards to the

aircraft. Based on service data for

comparable applications, and the

estimated length of time for a final fix

to be designed and tested, the FAA

considered operations with the

overspeed protection disabled

acceptable. The redesign of the system

has taken longer than estimated, which

now puts in question the original

analysis concerning operations with the

overspeed protection disabled. The FAA

has determined that immediate action is

necessary to prevent possible turbine

shaft failure, or rotorcraft drive train

failure, from leading to an uncontained

blade shedding due to the lack of

overspeed protection. For these reasons,

the FAA has determined that

implementation of the redesigned

overspeed system must proceed without

further delay.

Since the issuance of AD 96–24–09,

Allison Engine Company has developed

certain modifications that raise the

power turbine overspeed trip point, and

revise the overspeed system to default to

a minimum fuel flow in the event of its

activation. With these changes

incorporated, the overspeed solenoid

can be reactivated. Additionally, a

capacitor was added to the ECU PW10

circuit thereby eliminating the

problematic electrical noise

characteristic.

The FAA has reviewed and approved

the technical contents of: Allison Engine

Company Alert Commercial Engine

Bulletin (CEB) A–73–6015, Revision 1,

dated July 30, 1997, and Revision 2,

dated October 31, 1997, that describe

procedures for installing a new

hydromechanical unit (HMU) and ECU;

Allison Engine Company Alert CEB–A–

73–6010, dated October 15, 1996, that

describes replacing the engine main

electrical harness assembly with an

improved assembly; and BHTC RFM

BHT–407-FM–1, Revision 5, dated June

24, 1997, that adds new instructions for

the revised overspeed system.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD supersedes AD 96–

24–09 to continue to require replacing

the engine main electrical harness

assembly with an improved assembly,

and adds the requirements to install a

new HMU and ECU, to remove the

placard notifying the pilot that the

overspeed protection system is disabled,

and to revise the BHTC Model 407 RFM.

Installation of the new HMU and ECU

will reactivate the overspeed solenoid in

conjunction with raising the power

turbine overspeed trip point and

revising the overspeed system to default

to a minimum fuel flow in the event of

its activation. These actions must be

completed by January 31, 1998. This

calendar end-date was determined

based upon parts availability. The

requirements of paragraph (c) of this AD

have been coordinated with the

Rotorcraft Directorate. The actions are

required to be accomplished in

accordance with the service information

described previously.
61440 Federal Register / Vol. 62, No. 222 / Tuesday, November 18, 1997 / Rules and Regulations

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–ANE–40–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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 39–9834, (61 FR

59828, November 25, 1996), and by

adding a new airworthiness directive,

Amendment 39–10162, to read as

follows:

97–21–09 Allison Engine Company:

Amendment 39–10162. Docket 97–ANE–

40–AD. Supersedes AD 96–24–09,

Amendment 39–9834.

Applicability: Allison Engine Company

Model 250-C47B turboshaft engines, installed

on but not limited to Bell Helicopter Textron,

A Division of Textron Canada Ltd. (BHTC)

Model 407 helicopters.

Note 1: This airworthiness directive (AD)

applies to each engine identified in the

preceding applicability provision, regardless

of whether it has been modified, altered, or

repaired in the area subject to the

requirements of this AD. For engines that

have been modified, altered, or repaired so

that the performance of the requirements of

this AD is affected, the owner/operator must

request approval for an alternative method of

compliance in accordance with paragraph (d)

of this AD. The request should include an

assessment of the effect of the modification,

alteration, or repair on the unsafe condition

addressed by this AD; and, if the unsafe

condition has not been eliminated, the

request should include specific proposed

actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent uncommanded inflight engine

shutdowns, which can result in autorotation,

forced landing, and possible loss of the

helicopter, accomplish the following:

(a) Prior to further flight, replace the engine

main electrical harness assembly, Part

Number (P/N) 23062796, with an improved

assembly, P/N 23065805, in accordance with

Allison Engine Company Alert Commercial

Engine Bulletin (CEB) CEB–A–73–6010,

dated October 15, 1996.

(b) Prior to January 31, 1998, install a new

hydromechanical unit (HMU) and engine

control unit (ECU) in accordance with

Allison Engine Company Alert CEB–A–73–

6015, Revision 1, dated July 30, 1997, or

Revision 2, dated October 31, 1997.

(c) After completing the requirements of

paragraph (b) of this AD, and then prior to

further flight:

(1) Remove the ‘‘OVRSPD SYSTEM INOP’’

placard required by paragraph (d) of AD 96–

24–09, and

(2) Revise the FAA-approved Rotorcraft

Flight Manual (RFM) by removing the pages

added by paragraph (f) of AD 96–24–09, and

incorporate BHTC Flight Manual BHT–407–

FM–1, Revision 5, dated June 24, 1997.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Chicago

Aircraft Certification Office. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following

service documents:

Document No. Pages Revision Date

Allison Engine Company Alert, CEB–A–73–6010 .................................................................... 1–7 .............. Original ............. Oct. 15, 1996.

Total Pages: 7

Allison Engine Company Alert, CEB–A–73–6015 .................................................................... 1–4 .............. 1 ....................... July 30, 1997.
Federal Register / Vol. 62, No. 222 / Tuesday, November 18, 1997 / Rules and Regulations 61441

Document No. Pages Revision Date

Total Pages: 4

Allison Engine Company Alert, CEB–A–73–6015 .................................................................... 1–4 .............. 2 ....................... Oct. 31, 1997.

Total pages: 4

BHTC Flight Manual BHT–407–FM–1 ...................................................................................... Cover .......... 5 ....................... June 24, 1997.

NP ............... 3 ....................... July 30, 1996.

A,B .............. 5 ....................... June 24, 1997.

C/D .............. 5 ....................... June 24, 1997.

1–3 .............. 5 ....................... June 24, 1997.

1–4 .............. 4 ....................... Nov. 4, 1996.

1–7, 1–8 ...... 5 ....................... June 24, 1997.

1–13 ............ 4 ....................... Nov. 4, 1996.

1–14 ............ 5 ....................... June 24, 1997.

1–14A/14B .. 5 ....................... June 24, 1997.

1–19/1–20 ... 5 ....................... June 24, 1997.

2–3 .............. 5 ....................... June 24, 1997.

2–4 .............. 1 ....................... Mar. 8, 1996.

2–7—2–10 .. 5 ....................... June 24, 1997.

2–13, 2–14 .. 5 ....................... June 24, 1997.

3–3—3–5 .... 5 ....................... June 24, 1997.

3–6 .............. 2 ....................... May 9, 1996.

3–7, 3–8 ...... 5 ....................... June 24, 1997.

3–15 ............ 5 ....................... June 24, 1997.

3–16 ............ 2 ....................... May 9, 1996.

3–17—3–22 5 ....................... June 24, 1997.

4–5, 4–6 ...... 5 ....................... June 24, 1997.

4–9 .............. Original ............. Feb. 9, 1996.

4–10—4–12 5 ....................... June 24, 1997.

Total pages: 40

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 Allison Engine Company, P.O. Box 420,

Speed Code P–40A, Indianapolis, IN 46206–

0420; telephone (317) 230–2720, fax (317)

230–3381. Copies may be inspected at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(h) This amendment becomes effective on

December 3, 1997.

Issued in Burlington, Massachusetts, on

November 10, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–30201 Filed 11–17–97; 8:45 am]

BILLING CODE 4910–13–P

ENVIRONMENTAL PROTECTION

AGENCY

40 CFR Part 180

[OPP–300559; FRL 5753–5]

RIN 2070–AB78

Fenarimol; Pesticide Tolerances for

Emergency Exemptions

AGENCY: Environmental Protection

Agency (EPA).

ACTION: Final rule.

SUMMARY: This regulation establishes a

time-limited tolerance for residues of

fenarimol in or on filberts. This action

is in response to EPA’s granting of an

emergency exemption under section 18

of the Federal Insecticide, Fungicide,

and Rodenticide Act authorizing use of

the pesticide on filberts. This regulation

establishes a maximum permissible

level for residues of fenarimol in this

food commodity pursuant to section

408(l)(6) of the Federal Food, Drug, and

Cosmetic Act, as amended by the Food

Quality Protection Act of 1996. The

tolerance will expire and is revoked on

December 31, 1998.

DATES: This regulation is effective

November 18, 1997. Objections and

requests for hearings must be received

by EPA on or before January 20, 1998.

ADDRESSES: Written objections and

hearing requests, identified by the

docket control number, [OPP–300559],

must be submitted to: Hearing Clerk

(1900), Environmental Protection

Agency, Rm. M3708, 401 M St., SW.,

Washington, DC 20460. Fees

accompanying objections and hearing

requests shall be labeled ‘‘Tolerance

Petition Fees’’ and forwarded to: EPA

Headquarters Accounting Operations

Branch, OPP (Tolerance Fees), P.O. Box

360277M, Pittsburgh, PA 15251. A copy

of any objections and hearing requests

filed with the Hearing Clerk identified

by the docket control number, [OPP–

300559], must also be submitted to:

Public Information and Records

Integrity Branch, Information Resources

and Services Division (7502C), Office of

Pesticide Programs, Environmental

Protection Agency, 401 M St., SW.,

Washington, DC 20460. In person, bring

a copy of objections and hearing

requests to Rm. 1132, CM #2, 1921

Jefferson Davis Hwy., Arlington, VA.

A copy of objections and hearing

requests filed with the Hearing Clerk

may also be submitted electronically by

sending electronic mail (e-mail) to: oppdocket@epamail.epa.gov. Copies of

objections and hearing requests must be

submitted as an ASCII file avoiding the

use of special characters and any form

of encryption. Copies of objections and

hearing requests will also be accepted

on disks in WordPerfect 5.1/6.1 or

ASCII file format. All copies of

objections and hearing requests in

electronic form must be identified by

the docket control number [OPP–

300559]. No Confidential Business

Information (CBI) should be submitted

through e-mail. Electronic copies of

objections and hearing requests on this

rule may be filed online at many Federal

Depository Libraries.

FOR FURTHER INFORMATION CONTACT: By

mail: Olga Odiott, Registration Division

(7505C), Office of Pesticide Programs,

Environmental Protection Agency, 401

M St., SW., Washington, DC 20460.

Office location, telephone number, and

e-mail address: Rm. 268, Crystal Mall

#2, 1921 Jefferson Davis Hwy.,

Arlington, VA, (703) 308–9363; e-mail:

odiott.olga@epamail.epa.gov.