8198 Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

I.A.M. Rinaldo Piaggio: Docket No. 96–CE–

56–AD.

Applicability: Model P180 airplanes (all

serial numbers), 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 (f) 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 within the next 100

hours time-in-service (TIS) after the effective

date of this AD, and thereafter as indicated

in the body of this AD, unless already

accomplished.

To prevent fatigue cracks in the rudder

torque tube bottom flange which could result

in loss of rudder control and possible loss of

the airplane, accomplish the following:

(a) Inspect the area around the torque tube,

bottom flange, and vertical support pin of the

rudder for cracks (using a dye penetrant

method) and visually inspect for cracks in

the fasteners that connect the torque tube to

the bottom flange.

Note 2: The inspection in Part A of the

Compliance section of Piaggio Service

Bulletin (SB) 80–0076, ORIGINAL ISSUE:

May 30, 1995, uses different criteria than the

inspection required in paragraph (a) of this

AD. This AD takes precedence over Piaggio

SB 80–0076.

(b) If cracks are found, prior to further

flight, modify the rudder torque tube bottom

flange by replacing any cracked part with a

part of improved design in accordance with

Part B and Attachment #1 of the

ACCOMPLISHMENT INSTRUCTIONS of

Piaggio SB 80–0076, ORIGINAL ISSUE: May

30, 1995.

(c) If no cracks are found, continue to

inspect at intervals not to exceed 100 hours

TIS thereafter until cracks appear. If cracks

appear during any inspection required by

this AD, prior to further flight, modify the

rudder torque tube bottom flange by the

replacing cracked part with a part of

improved design in accordance with Part B

and Attachment #1 of the

ACCOMPLISHMENT INSTRUCTIONS of

Piaggio SB 80–0076, ORIGINAL ISSUE: May

30, 1995.

(d) Modifying the rudder torque tube flange

by replacing a cracked torque tube bottom

flange, part number (P/N) 80–373108–103,

with an improved torque tube bottom flange

(P/N 80–373201–001) is considered a

terminating action for the repetitive

inspections required in paragraph (c) of this

AD.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Brussels Aircraft Certification

Division, FAA, Europe, Africa, and Middle

East Office, c/o American Embassy, B–1000

Brussels, Belgium; or the Manager, Small

Airplane Directorate, Aircraft Certification

Service, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels Aircraft Certification Division or

Manager, Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Division or the Small Airplane

Directorate.

(g) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to I. A. M. Rinaldo

Piaggio, S.p.A., Via Cibrario, 4 16154 Genoa,

Italy; or may examine these documents at the

FAA, Central Region, Office of the Assistant

Chief Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on

February 14, 1997.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–4371 Filed 2–21–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 97–ANE–08]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D–200 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to Pratt &

Whitney JT8D–200 series turbofan

engines, that currently requires for front

compressor front hubs (fan hubs),

cleaning; initial and repetitive eddy

current (ECI) and fluorescent penetrant

inspections (FPI) of tierod and

counterweight holes for cracks; removal

of bushings; the cleaning and ECI and

FPI of bushed holes for cracks; and, if

necessary, replacement with serviceable

parts. In addition, the current AD

requires reporting the findings of

cracked fan hubs. This action will not

change the current AD’s inspection

procedures, or the effectivity date that

starts the cycle count for the initial

inspection schedules. This AD will,

however, add an additional inspection

schedule that requires the initial

inspection of certain fan hubs with

standard drilled holes and coolant

channel drilled (CCD) holes to occur

earlier than the existing AD requires.

This proposal is prompted by additional

investigation since publication of the

current AD that reveals that certain fan

hubs with standard drilled holes and

CCD holes may be more susceptible to

cracking. This proposal also requires

reporting the results of the initial fan

hub inspections. The actions specified

by the proposed AD are intended to

prevent fan hub failure due to tierod,

counterweight, or bushed hole cracking,

which could result in an uncontained

engine failure and damage to the

aircraft.

DATES: Comments must be received by

April 25, 1997.

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–08, 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’’.

Comments sent via the Internet must

contain the docket number in the

subject line. Comments may be

inspected at this location between 8:00

a.m. and 4:30 p.m., Monday through

Friday, except Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860)

565–6600, fax (860) 565–4503. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Diane Cook, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–
Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules 8199

5299; telephone (617) 238–7134, fax

(617) 238–7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal 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–08.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, New England Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 97–ANE–08, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On January 13, 1997, the Federal

Aviation Administration (FAA) issued

airworthiness directive AD 97–02–11,

Amendment 39–9896 (62 FR 4902,

February 3, 1997), applicable to Pratt &

Whitney (PW) JT8D–200 series turbofan

engines, to require cleaning, initial and

repetitive eddy current inspections (ECI)

and fluorescent penetrant inspections

(FPI) for cracks of tierod and

counterweight holes; removal of

bushings; the cleaning and initial and

repetitive ECI and FPI of bushed holes

for cracks; and, if necessary, replacing

with serviceable parts. The compliance

requirements allow selection of

inspection schedules depending on

front compressor front hub (fan hub)

Serial Numbers (S/Ns) listed in PW

Alert Service Bulletin (ASB) No. A6272,

dated September 24, 1996, and includes

an inspection schedule for those fan

hubs whose S/Ns are not listed in the

ASB. In addition, the AD requires

reporting findings of cracked fan hubs.

That action was prompted by a report of

an uncontained failure of a fan hub.

That condition, if not corrected, could

result in fan hub failure due to tierod,

counterweight, or bushed hole cracking,

which could result in an uncontained

engine failure and damage to the

aircraft.

Since the issuance of that AD, the

FAA has conducted additional

investigation of fan hub cracking and

has determined it necessary to include

an additional inspection schedule for

certain fan hubs with standard drilled

holes and coolant channel drilled (CCD)

holes. The FAA reviewed the

manufacturing records of all fan hubs, a

total of 253 which had notations related

to the tierod or counterweight holes.

Notations are made in the

manufacturing records if an event

occurred during manufacture of the hole

such as a tool break, which can result

in work hardened material, which is

more susceptible to cracking. Of the 253

fan hubs with such notations, 113 were

manufactured with a CCD and the

remaining 140 were manufactured with

a standard drill. Although CCD fan hubs

are more prone to a work hardened

layer, a standard drill, under certain

circumstances, may also cause a work

hardened layer and subsequent

cracking.

The FAA has reviewed and approved

the technical contents of PW ASB No.

A6272, dated September 24, 1996, that

describes procedures for cleaning and

ECI and FPI of tierod and counterweight

holes for cracks; removal of bushings;

and the cleaning, FPI, and ECI of bushed

holes for cracks. Even though the ASB

contains three of the S/Ns of the fan

hubs that were removed from service in

accordance with AD 96–15–06, the

manufacturer has informed the FAA

that these fan hubs have been destroyed

during the investigation to confirm the

failure mode.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 97–02–11 to include an

additional inspection schedule for

certain fan hubs with standard drilled

holes and CCD holes without changing

inspection procedures, the existing

inspection schedules, or the current

effectivity date of March 5, 1997.

There are approximately 2,624

engines of the affected design in the

worldwide fleet. The FAA estimates that

1,279 engines installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take 20

work hours per engine for 360 engines

to disassemble, remove, inspect, and

reassemble engines, and 4 work hours

per engine for 919 engines to inspect at

piece-part exposure, and that the

average labor rate is $60 per work hour.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $862,560.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9896 (62 FR

4902, February 3, 1997) and by adding
8200 Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules

a new airworthiness directive to read as

follows:

Pratt & Whitney: Docket No. 97–ANE–08.

Supersedes AD 97–02–11, Amendment

39–9896.

Applicability: Pratt & Whitney JT8D–209,

–217, –217C, and –219 series turbofan

engines with front compressor front hub (fan

hub), Part Number (P/N) 5000501–01,

installed. These engines are installed on but

not limited to McDonnell Douglas MD–80

series aircraft.

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 (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 fan hub failure due to tierod,

counterweight, or bushed hole cracking,

which could result in an uncontained engine

failure and damage to the aircraft,

accomplish the following:

(a) Inspect fan hubs for cracks in

accordance with the Accomplishment

Instructions, Paragraph A, Part 1, and, if

applicable, Paragraph B, of PW ASB No.

A6272, dated September 24, 1996, as follows:

(1) For fan hubs identified by Serial

Numbers (S/Ns) in Table 2 of this AD, after

the fan hub has accumulated more than 4,000

cycles since new (CSN), as follows:

(i) Initially inspect within 790 cycles in

service after March 5, 1997 (the effective date

of AD 97–02–11), or 4,790 CSN, whichever

occurs later.

(ii) Thereafter, reinspect after accumulating

2,500 CIS since last inspection, but not to

exceed 10,000 CIS since last inspection.

(2) For fan hubs identified by S/Ns in

Appendix A of PW ASB No. A6272, dated

September 24, 1996, after the fan hub has

accumulated more than 4,000 CSN, as

follows:

(i) Select an initial inspection interval from

Table 1 of this AD, and inspect accordingly.

TABLE 1

Initial inspection Reinspection

1. Within 1,050 cycles in service (CIS) after the effective date of AD

97–02–11, March 5, 1997, or prior to accumulating 5,050 CSN,

whichever occurs later;

After accumulating 2,500 CIS since last inspection, but not to exceed 6,000 CIS since last inspection.

or

2. Within 990 CIS after the effective date of AD 97–02–11, March 5,

1997, or prior to accumulating 4,990 CSN, whichever occurs later;

After accumulating 2,500 CIS since last inspection, but not to exceed 8,000 CIS since last inspection.

or

3. Within 965 CIS after the effective date of AD 97–02–11, March 5,

1997, or prior to accumulating 4,965 CSN, whichever occurs later.

After accumulating 2,500 CIS since last inspection, but not to exceed 10,000 CIS since last inspection.

TABLE 2

[Hubs with traveler notations]

Non CCD Non CCD Non CCD Non CCD

M67663 M67802 P66880 S25545

M67671 M67812 P66885 S25558

M67675 M67826 R32732 S25564

M67681 M67829 R32733 S25598

M67685 M67830 R32735 S25618

M67686 M67831 R32740 S25621

M67687 M67832 R32741 S25637

M67697 M67834 R32810 S25640

M67700 M67843 R32849 T50693

M67706 M67849 R32850 T50752

M67710 M67858 S25222 T50785

M67712 M67866 S25464 T50791

M67713 M67868 S25481 T50792

M67714 M67869 S25483 T50819

M67715 M67872 S25484 T50823

M67716 M67888 S25486 T50827

M67717 N71771 S25488 T50874

M67722 N71804 S25489 T50875

M67723 N71806 S25490 T51058

M67725 N71810 S25491 T51104

M67726 N71811 S25492 R33186

M67730 N71875 S25494 S25528

M67731 N71876 S25495

M67746 N71921 S25497

M67751 N71965 S25498

M67753 N72062 S25499

M67764 N72126 S25500

M67765 N72152 S25501

M67784 N72162 S25502

M67791 N72207 S25505

M67792 N72216 S25506

M67793 N72219 S25507

M67794 N72242 S25508

M67795 P66693 S25509

TABLE 2—Continued

[Hubs with traveler notations]

Non CCD Non CCD Non CCD Non CCD

M67796 P66695 S25514

M67797 P66696 S25529

M67798 P66698 S25532

M67799 P66699 S25541

M67800 P66737 S25543

M67801 P66753 S25544

CCD Hub CCD Hub CCD Hub

P66747 R33099 S25292

P66756 R33107 S25299

P66800 R33113 S25301

P66814 R33124 S25302

P66819 R33131 S25308

P66831 R33132 S25312

R32767 R33133 S25316

R32787 R33136 S25323

R32792 R33152 S25334

R32795 R33157 S25335

R32796 R33163 S25337

R32800 R33165 S25344

R32807 R33168 S25369

R32856 R33171 S25377

R32860 R33173 S25378

R32870 R33180 S25381

R32883 R33181 S25394

R32905 R33189 S25399

R32926 R33194 S25402

R32930 R33198 S25406

R32952 R33201 S25411

R32964 R33202 S25413

R32966 R33207 S25414

R32971 S25193 S25415

R32976 S25195 S25418

TABLE 2—Continued

[Hubs with traveler notations]

Non CCD Non CCD Non CCD Non CCD

R32981 S25207 S25419

R32990 S25208 S25421

R32994 S25221 S25422

R33000 S25229 S25430

R33004 S25238 S25437

R33040 S25246 S25439

R33055 S25248 S25449

R33059 S25250

R33077 S25256

R33080 S25262

R33082 S25268

R33086 S25278

R33087 S25287

R33089 S25288

R33090

(ii) Thereafter, reinspect at intervals that

correspond to the selected inspection

interval.

(3) If a fan hub is identified in both Table

2 of this AD and Appendix A of PW ASB No.

A6272, dated September 24, 1996, inspect in

accordance with paragraph (a)(1) of this AD.

(4) For fan hubs with S/Ns not listed in

Table 2 of this AD or in Appendix A of PW

ASB No. A6272, dated September 24, 1996,

after the fan hub has accumulated more than

4,000 CSN, inspect the next time the fan hub

is in the shop at piece-part level, but not to

exceed 10,000 CIS after March 5, 1997.

(5) Prior to further flight, remove from

service fan hubs found cracked or that exceed

the bushed hole acceptance criteria described
Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules 8201

in PW ASB No. A6272, dated September 24,

1996.

(b) Report the number of completed

inspections on a monthly basis and report

findings of cracked fan hubs in accordance

with Accomplishment Instructions,

Paragraph F, of Attachment 1 to PW ASB No.

A6272, dated September 24, 1996, within 48

hours after inspection to Robert Guyotte,

Manager, Engine Certification Branch, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–5299;

telephone (617) 238–7142, fax (617) 238–

7199; Internet: Robert.Guyotte@faa.dot.gov.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine 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 Engine

Certification Office.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

Issued in Burlington, Massachusetts, on

February 14, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–4370 Filed 2–21–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF LABOR

Employment Standards Administration

20 CFR Parts 718, 722, 725, 726 and

727

RIN 1215–AA99

Regulations Implementing the Federal

Coal Mine Health and Safety Act of

1969, as Amended; Extension of

Comment Period

AGENCY: Employment Standards

Administration, Labor.

ACTION: Proposed rule; extension of

comment period.

SUMMARY: This document extends the

period for filing comments regarding the

proposed rule to amend and revise the

regulations implementing the Black

Lung Benefits Act. This action is taken

to permit additional comment from

interested persons.

DATE: Comments must be received on or

before May 23, 1997.

ADDRESSES: Send written comments on

the proposed rule to James L. DeMarce,

Director, Division of Coal Mine

Workers’ Compensation, Room C–3520,

Frances Perkins Building, 200

Constitution Ave., NW, Washington, DC

20210.

FOR FURTHER INFORMATION CONTACT:

James L. DeMarce, (202) 219–6692.

SUPPLEMENTARY INFORMATION: In the

Federal Register of the January 22, 1997

(62 FR 3338–3435), the Department of

Labor published a proposed rule

intended to amend and revise the

regulations implementing the Black

Lung Benefits Act, subchapter IV of the

Federal Coal Mine Health and Safety

Act of 1969, as amended. Interested

persons were requested to submit

comments on or before March 24, 1997.

The Department has received requests

for an extension of the comment period

from groups representing coal mine

operators, coal mine construction

companies, the insurance industry,

organized labor, and black lung

claimants. Because of the interest in this

proposal, the Department believes that it

is desirable to extend the comment

period for all interested persons.

Therefore, the comment period for the

proposed rule, amending and revising

20 CFR parts 718, 722, 725, 726 and

727, is extended through May 23, 1997.

Signed at Washington, DC, this 18 day of

February, 1997.

Bernard E. Anderson,

Assistant Secretary for Employment

Standards.

[FR Doc. 97–4467 Filed 2–21–97; 8:45 am]

BILLING CODE 4510–27–M

DEPARTMENT OF VETERANS

AFFAIRS

38 CFR Parts 3 and 4

RIN 2900–AH41

Service Connection of Dental

Conditions for Treatment Purposes

AGENCY: Department of Veterans Affairs.

ACTION: Proposed rule.

SUMMARY: The Department of Veterans

Affairs is proposing to amend its

adjudication regulations for determining

service connection of dental conditions

for purposes of eligibility for outpatient

dental treatment. Current regulations

contain overlapping provisions which

do not clearly state requirements for

service connection, and provide that

service connection will be granted for

certain dental conditions shown after a

‘‘reasonable period of service’’ without

defining what constitutes such a period.

We intend to consolidate the

information, and replace the term

‘‘reasonable period of service’’ with a

precise period of 180 days. We also

propose to eliminate redundant

material, and to clearly state

requirements for service connection for

purposes of eligibility for outpatient

dental treatment.

DATES: Comments must be received on

or before April 25, 1997.

ADDRESSES: Mail or hand deliver written

comments to: Director, Office of

Regulations Management (02D),

Department of Veterans Affairs, 810

Vermont Ave., NW, Room 1154,

Washington, DC 20420. Comments

should indicate that they are submitted

in response to ‘‘RIN 2900–AH41.’’ All

written comments will be made

available for public inspection at the

above address in the Office of

Regulations Management, Room 1158,

between the hours of 8 a.m. and 4:30

p.m., Monday through Friday (except

holidays).

FOR FURTHER INFORMATION CONTACT:

Lorna Fox, Consultant, Regulations

Staff, Compensation and Pension

Service (213), Veterans Benefits

Administration, Department of Veterans

Affairs, 810 Vermont Ave., NW,

Washington, DC 20420, (202) 273–7223.

SUPPLEMENTARY INFORMATION: The

provisions of 38 U.S.C. 1712 (restated in

38 CFR 17.123) set forth eligibility

requirements for VA outpatient

treatment of dental conditions and

disabilities. This section provides that

veterans with non-compensable serviceconnected dental conditions are entitled

to a one-time correction of the dental

condition provided that certain

requirements are met, including

application for dental treatment made

within 90 days of service discharge.

Following completion of this initial

care, subsequent additional treatment

may be provided in certain other cases,

i.e., if the veteran was a prisoner of war,

if the dental condition or disability is

due to combat or other in-service

trauma, or if the veteran has serviceconnected disabilities rated at 100

percent.

38 CFR part 4, the Schedule for Rating

Disabilities, provides evaluations for

dental conditions considered disabling

in nature. (See § 4.150, Schedule of

ratings—dental and oral conditions.)

There are other dental conditions,

however, which are not considered

disabling and thus do not generally fall

under the purview of § 4.150. The issue

of service connection arises for these

conditions only for the purpose of