Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21083

dated April 27, 1984; certificated in any

category.

Note 1: This AD applies to each airplane

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

airplanes 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 (c) 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 damage to the windshield heat

wire bundle, which could cause arcing and

result in smoke and fire in the cockpit;

accomplish the following:

Inspection of Wiring and Clamps, and

Corrective Actions

(a) For airplanes listed in Lockheed Service

Bulletin 093–30–060, dated March 6, 2001:

Within 60 days after the effective date of this

AD, perform the detailed visual inspections

and repair or replacements specified in

paragraph (a)(1) and (a)(2) of this AD, per

Lockheed Service Bulletin 093–30–060,

dated March 6, 2001.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(1) Remove the C–38 wire harness clamps

and perform a detailed visual inspection of

the clamps and the conforming cushions for

any sign of deterioration, damage, or slippage

on the metal band of the clamp. Before

further flight, replace any clamp that does

not meet the specified criteria in the service

bulletin with a new or serviceable clamp, per

the service bulletin.

(2) Perform a detailed visual inspection of

the C–38 wire harness for any damage from

chafing or contamination (e.g., shavings,

moisture, deterioration, etc.). Before further

flight, repair, or replace any chafed or

damaged wiring per the service bulletin.

Rerouting the C–38 Harness

(b) For airplanes listed in Lockheed Service

Bulletin 093–30–057, dated April 27, 1984:

Within 60 days after the effective date of this

AD, reroute the C–38 harness and add one

additional clamp to secure the harness away

from the mounting brackets of the Flight

Officer’s chart light assembly, per the service

bulletin.

Alternative Methods of Compliance

(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, Atlanta

Aircraft Certification Office (ACO). Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Lockheed Service Bulletin 093–30–060,

dated March 6, 2001; and Lockheed Service

Bulletin 093–30–057, dated April 27, 1984,

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 Lockheed Martin & Logistics

Center, 120 Orion Street, Greenville, South

Carolina 29605. Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia 30349;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date

(f) This amendment becomes effective on

May 14, 2001.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10339 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–09–AD; Amendment

39–12212; AD 2001–09–07]

RIN 2120–AA64

Airworthiness Directives; Pratt and

Whitney PW4000 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule, request for

comments.

SUMMARY: This amendment supersedes

an emergency airworthiness directive

(AD) 2001–08–52 that was sent

previously to all known U.S. owners

and operators of Pratt and Whitney (PW)

model PW4050, PW4052, PW4056,

PW4060, PW4060A, PW4060C,

PW4062, PW4152, PW4156, PW4156A,

PW4158, PW4160, PW4460, PW4462,

and PW4650 turbofan engines by

individual letters. That emergency AD

requires limiting the number of PW4000

engines, listed by serial number (SN) in

that AD, with potentially reduced

stability to no more than one engine on

each airplane; removal of certain

PW4000 engines, listed by SN in this

AD, before exceeding cyclic limits that

are determined by airplane model;

removal of certain PW4000 engines,

listed by SN in this AD, that have a high

pressure compressor with 1,500 or more

cycles-since-overhaul (CSO) greater than

the high pressure turbine (HPT) CSO;

and requires a minimum rebuild

standard for engines that are returned to

service. This amendment supersedes

emergency AD 2001–08–52 to provide

clarifications and additions to the

compliance and applicability of certain

paragraphs of AD 2001–08–52. This AD

is prompted by a report of a dual-engine

surge event during take-off on an Airbus

Industrie A300 airplane. The actions

specified by this AD are intended to

prevent multiple-engine power losses

due to high pressure compressor (HPC)

surge at a critical phase of flight such as

takeoff or climb.

DATES: Effective May 14, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 26, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2001–NE–

09–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-aneadcomment@faa.gov.’’ Comments sent

via the Internet must contain the docket

number in the subject line.

FOR FURTHER INFORMATION CONTACT:

Peter White, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7128;

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: On April

13, 2001, the Federal Aviation

Administration (FAA) issued emergency

21084 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

AD 2001–08–52, applicable to PW

model PW4050, PW4052, PW4056,

PW4060, PW4060A, PW4060C,

PW4062, PW4152, PW4156, PW4156A,

PW4158, PW4160, PW4460, PW4462,

and PW4650 turbofan engines, which

requires:

• Limiting the number of PW4000

engines, listed by serial number (SN) in

that AD, to no more than one engine

with potentially reduced stability on

each airplane within 10 cycles after

receipt of that AD. AND

• Removal of certain PW4000

engines, listed by SN in that AD, before

exceeding cyclic limits that are

determined by airplane model, or

within 100 cycles-in-service (CIS) after

the receipt of that AD whichever occurs

later. AND

• Removal of certain PW4000

engines, listed by SN in that AD, within

100 cycles after the receipt of that AD,

that have an HPC with 1,500 or more

CSO greater than the HPT CSO. AND

• A minimum rebuild standard for

engines that are returned to service.

Since AD 2001–08–52 was issued, the

FAA has reevaluated those

requirements, and found that the

requirements of that AD need to be

clarified and changed to meet the

original safety intent of the emergency

AD. This amendment supersedes

emergency AD 2001–08–52 to provide

clarifications and additions to the

compliance and applicability of certain

paragraphs of AD 2001–08–52.

Significant changes to AD 2001–08–52

include:

• Minor modifications made to

engine serial number listings in Table 1

and Table 2 of this AD.

• Adding engines with the HPC

Cutback Stator (CBS) configuration to

the installation restrictions of paragraph

(c), to be consistent with the installation

restrictions of paragraph (b) of this AD.

• Editing paragraph (f) to clarify

applicability to all PW4000 series

engines defined in the applicability

section.

• Modifying paragraph (g) to clarify

applicability, and to specifically require

an HPC overhaul.

• Modifying paragraph (h) to alter

applicability to Table 2 engines only,

and to clarify applicability.

• Adding paragraph (i) to clarify

requirements for all PW4000 engines

included in the applicability section of

this AD.

• Clarifying the elimination of

installation restrictions in paragraphs (g)

and (h).

FAA’s Determination of an Unsafe

Condition and Proposed Actions

Since the unsafe condition described

is likely to exist or develop on other

PW4000 series turbofan engines of the

same type design, this AD is being

issued to prevent multiple-engine power

losses due to high pressure compressor

(HPC) surge at a critical phase of flight

such as takeoff or climb. This AD

requires:

• Limiting the number of PW4000

engines listed by serial number (SN) in

this AD, to no more than one engine

with potentially reduced stability on

each airplane within 10 cycles after

effective date of this AD. AND

• Removal of certain PW4000

engines, listed by SN in this AD, before

exceeding cyclic limits that are

determined by airplane model, or

within 100 cycles-in-service (CIS) after

the effective date of this AD whichever

occurs later. AND

• Removal of certain PW4000

engines, listed by SN in this AD, within

100 cycles after the effective date of this

AD, that have an HPC with 1,500 or

more CSO greater than the HPT CSO.

AND

• A minimum rebuild standard for

engines that are returned to service.

Immediate Adoption of This AD

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 2001–NE–09–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it

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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this final rule.

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, 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:

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21085

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:

2001–09–07 Pratt and Whitney:

Amendment 39–12212. Docket 2001–

NE–09–AD.

Applicability: This airworthiness directive

(AD) is applicable to Pratt and Whitney (PW)

model PW4050, PW4052, PW4056, PW4060,

PW4060A, PW4060C, PW4062, PW4152,

PW4156, PW4156A, PW4158, PW4160,

PW4460, PW4462, and PW4650 turbofan

engines. These engines are installed on, but

not limited to, certain models of Boeing 747,

Boeing 767, Airbus Industrie A300, Airbus

Industrie A310, and McDonnell Douglas MD–

11 series airplanes.

Note 1: This 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 (k) 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: Compliance with this AD is

required as indicated, unless already done.

To prevent multiple-engine power losses

due to high pressure compressor (HPC) surge

at a critical phase of flight such as takeoff or

climb, do the following:

(a) Within 10 cycles-in-service (CIS) after

the effective date of this AD, limit the

number of engines listed by SN in the

following Table 1 of this AD, to no more than

one per airplane:

TABLE 1. SUSPECTED HIGH SURGE RATE ENGINES

723845, 723934, 723936, 723962, 723966, 723967, 723969, 724012, 724013, 724016, 724030, 724040, 724041, 724045, 724057, 724073,

724115, 724137, 724153, 724175, 724195, 724196, 724198, 724200, 724351, 724383, 724501, 724612, 724615, 724616, 724625, 724629,

724689, 724808, 724827, 724829, 724830, 724833, 724837, 724838, 724848, 724855, 724857, 724858, 727316, 727317

(b) Engines that are removed in accordance with paragraph (a) of this AD may be installed on an airplane if ALL of the following

conditions are met:

(1) That airplane does not have any engines with a SN that is listed in Table 1 or Table 2 of this AD. AND

(2) The installed engines meet the requirements of paragraphs (d) and (e) of this AD. AND

(3) The airplane does not have any engines that incorporate the HPC Cutback Stator (CBS) configuration, which has been incorporated

as specified by the following PW service bulletins (SB’s) or earlier revisions: PW4ENG 72–706, Revision 3, dated July 17, 2000;

PW4ENG 72–711, dated June 13, 2000; or PW4ENG 72–704, dated July 17, 2000.

(c) After the effective date of this AD, do not install an engine with a SN that is listed in the following Table 2 of this AD,

or an engine incorporating the HPC CBS configuration as defined in (b)(3) of this AD, on an airplane that has an engine with

a SN that is listed in Table 1 of this AD:

TABLE 2. ENGINES RESTRICTED FROM INSTALLATION WITH SUSPECTED HIGH SURGE RATE ENGINES

717508, 717710CN, 723859, 723863, 723938, 723963, 724022, 724024, 724050, 724054, 724080, 724099, 724173, 724179, 724184, 724191,

724205, 724385, 724386, 724479, 724509, 724566, 724690, 724847, 724861, 724864, 724870, 724882, 724883, 724893, 727365, 727395,

727421, 727426, 727462, 727478, 727496, 727500, 727502, 727506, 727521, 727535, 727536, 727537, 727540, 727543, 727617, 727619,

727747, 733701, (d) Remove engines listed by SN in

Table 1 of this AD within 100 CIS after the effective date of this AD, or before exceeding the cyclic limits listed in the following

Table 3 of this AD, whichever occurs later:

TABLE 3. HIGH PRESSURE COMPRESSOR CYCLE LIMITS BY AIRPLANE

Airplane High pressure compressor (HPC) cycles

(1) Boeing 767 and 747 ................................................................................................................................ 2,500 cycles-since-overhaul (CSO).

(2) McDonnell Douglas MD–11 .................................................................................................................... 2,500 CSO.

(3) Airbus A300 and A310 ............................................................................................................................ 2,000 CSO.

(e) Within 100 CIS after the effective date

of this AD, remove engines listed by SN in

Table 1 of this AD that have an HPC with

1,500 or more CSO greater than the CSO of

the HPT.

(f) For any engine listed in the applicability

of this AD, that is inducted into the shop that

results in separation of the HPC and HPT

modules after the effective date of this AD,

do not install any HPC or HPT modules

where the CSO of the HPC will be 1,500 or

more cycles greater than the CSO of the HPT.

(g) When engines listed by SN in Table 1

of this AD are removed from service in

accordance with paragraphs (a), (d), or (e) of

this AD, they may be returned to service after

the accomplishment of an HPC overhaul and

meeting the requirements of paragraph (h)(1)

or (h)(2) of this AD without the installation

limitations of paragraphs (a), (b), (c) and (d)

of this AD.

(h) After the effective date of this AD, an

engine listed by SN in Table 2 of this AD,

that has HPC cycles since overhaul greater

than those shown in Table 3 of this AD, or

that has an HPC with 1,500 or more CSO

greater than the CSO of the HPT may be

returned to service without the limitations of

paragraph (c) of this AD after an HPC

overhaul is performed and EITHER of the

following have been done:

(1) The HPC and HPT have been modified

by the following PW SB’s, or earlier

revisions: PW4ENG 72–484, Revision 3,

dated July 1, 1997; PW4ENG 72–486,

Revision 2, dated April 28, 1998; PW4ENG

72–575, Revision 2, dated July 29, 1998; and

PW4ENG 72–514, Revision 3, dated August

10, 1999; OR

(2) The engine has been converted to the

Phase III configuration by the following PW

SB’s or earlier revisions: PW4ENG 72–490,

Revision 1, dated August 2, 1994; or

PW4ENG 72–504, Revision 1, dated May 9,

1995; or PW4ENG 72–572, dated June 16,

1995.

(i) Any engine listed in the applicability of

this AD inducted into the shop for HPC

overhaul after the effective date of this AD

must meet the requirements of paragraphs

(h)(1) or (h)(2) of this AD before return to

service.

Definitions

(j) For the purposes of this AD, the

following definitions apply:

(1) An HPC overhaul is defined as

restoration of the HPC stages 5 through 15

blade tip clearances to the limits specified in

21086 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

the applicable fits and clearances section of

the engine manual.

(2) An HPT overhaul is defined as

restoration of the HPT module stage 1 and 2

blade tip clearances to the limits specified in

the applicable fits and clearances section of

the engine manual.

Alternative Methods of Compliance

(k) 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, Engine

Certification Office (ECO). Operators shall

submit their requests through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(l) Special flight permits may be issued in

accordance with §§ 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.

Effective Date

(m) This amendment becomes effective

May 14, 2001.

Issued in Burlington, Massachusetts on

April 20, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–10463 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF THE TREASURY

Customs Service

19 CFR Part 24

[T.D. 01–34]

RIN 1515–AC82

Amended Procedure for Refunds of

Harbor Maintenance Fees Paid on

Exports of Merchandise

AGENCY: Customs Service, Department

of the Treasury.

ACTION: Interim regulations; correcting

amendment.

SUMMARY: This document contains

corrections to the interim regulations

(T.D. 01–25), which were published in

the Federal Register on March 28, 2001.

The interim regulations provide a new

procedure for requesting refunds of

harbor maintenance fees that were paid

on exports. The correction involves the

address to which refund requests for all

quarterly paid harbor maintenance fees

must be sent.

DATES: Effective on March 28, 2001.

FOR FURTHER INFORMATION CONTACT:

Deborah Thompson, Accounts

Receivable Branch, Accounting Services

Division, (317) 298–1200 (ext. 4003).

SUPPLEMENTARY INFORMATION:

Background

Interim regulations providing a new

procedure for requesting refunds of

harbor maintenance fees that were paid

on exports were published as T.D. 01–

25 in the Federal Register (66 FR 16854)

on Wednesday, March 28, 2001. The

interim regulation amended

§ 24.24(e)(4), Customs Regulations (19

CFR 24.24(e)(4)). An error was

contained in paragraphs (e)(4)(i) and

(e)(4)(ii)(A) of § 24.24 regarding the zip

code in the address to send requests for

refunds for harbor maintenance fees

paid on both export and non-export

movements. This document corrects

that error. The correct address to send

requests for quarterly paid harbor

maintenance fee refunds is: U.S.

Customs Service, HMT Refunds, 6026

Lakeside Blvd., Indianapolis, IN 46278.

List of Subjects in 19 CFR Part 24

Accounting, Claims, Customs duties

and inspection, Fees, Financial and

accounting procedures, Imports, Taxes,

User Fees.

Amendment to the Regulations

For the reasons stated in the

preamble, part 24 of the Customs

Regulations (19 CFR part 24) is

corrected as follows:

PART 24—CUSTOMS FINANCIAL AND

ACCOUNTING PROCEDURE

1. The authority citation for part 24

continues to read in part as follows:

Authority: 5 U.S.C. 301; 19 U.S.C. 58a—

58c, 66,1202 (General Note 22, Harmonized

Tariff Schedule of the United States), 1505,

1624; 26 U.S.C. 4461, 4462; 31 U.S.C. 9701.

* * * * *

2. Section 24.24 is amended by

revising the third sentence of paragraph

(e)(4)(i) and the first sentence of

paragraph (e)(4)(ii)(A) to read as follows:

§ 24.24 Harbor maintenance fee.

(e) * * *

(4) * * *

(i) A refund request should be mailed

to: U.S. Customs Service, HMT Refunds,

6026 Lakeside Blvd., Indianapolis,

Indiana 46278. * * *

(ii) * * *

(A) For export fee payments made

prior to July 1, 1990, the exporter (the

name that appears on the SED or

equivalent documentation authorized

under 15 CFR 30.39(b)) or its agent must

submit a letter of request for a refund to

the U.S. Customs Service, HMT

Refunds, 6026 Lakeside Blvd.,

Indianapolis, IN 46278, specifying the

grounds for the refund and identifying

the specific payments made. * * *

* * * * *

Dated: April 23, 2001.

Stuart P. Seidel,

Assistant Commissioner, Office of

Regulations and Rulings.

[FR Doc. 01–10484 Filed 4–26–01; 8:45 am]

BILLING CODE 4820–02–P

DEPARTMENT OF THE INTERIOR

Bureau of Indian Affairs

25 CFR Part 183

RIN: 1076–AE10

Use and Distribution of the San Carlos

Apache Tribe Development Trust Fund

and San Carlos Apache Tribe Lease

Fund

AGENCY: Bureau of Indian Affairs,

Interior.

ACTION: Final rule.

SUMMARY: The Bureau of Indian Affairs

(BIA) is amending its regulations by

adding a new part in response to the

San Carlos Apache Tribe Water Rights

Settlement Act. The Act sets up two

funds for the benefit of the San Carlos

Apache Tribe, namely, the San Carlos

Apache Tribe Development Trust Fund

and the San Carlos Apache Tribe Lease

Fund. This regulation sets out the

criteria and processes involved in the

distribution of principal and income for

the Trust Fund and the distribution of

income accrued for the Lease Fund, as

administered by the BIA. The Act

required the Secretary to promulgate

rules no later than 30 days after

December 31, 1999. The Secretary

consulted extensively with the Tribe on

the content of the rule from January

through July 2000. Since the rule is

more than one year late in being

promulgated, the Secretary is issuing

this rule as a Final Rule that will

become effective upon publication.

DATES: This rule is effective on April 27,

2001. Comments must be received on or

before June 26, 2001.

ADDRESSES: Send comments to: Terry

Virden, Director, Office of Trust

Responsibilities, Bureau of Indian

Affairs, Attn: Branch of Irrigation and

Power, MS 3061–MIB, Code 210, 1849

C Street, NW., Washington, DC 20240;

Telephone (202) 208–5480.

FOR FURTHER INFORMATION CONTACT:

Wayne Nordwall, Regional Director,