Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules 40555

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Dornier Luftfahrt GMBH: Docket 99–NM–

364–AD.

Applicability: All Model 328–300 series

airplanes, certificated in any category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent an undetected dragging parking

brake, and consequent decreased acceleration

during the takeoff roll, increased takeoff

distance, and possible runway overrun,

accomplish the following:

AFM Revision

(a) Within 10 days after the effective date

of this AD: Revise the Limitations Section of

the FAA-approved Airplane Flight Manual

by inserting a copy of Dornier 328J All

Operators Telefax AOT–328J–32–001, dated

September 9, 1999.

Alternative Methods of Compliance

(b) 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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Operations

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 1: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(c) 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.

Note 2: The subject of this AD is addressed

in German airworthiness directive 1999–352,

dated November 18, 1999.

Issued in Renton, Washington, on June 26,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–16644 Filed 6–29–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–21–AD]

RIN 2120–AA64

Airworthiness Directives; International

Aero Engines AG V2500–A5/D5 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain International Aero Engines (IAE)

V2500–A5/D5 series turbofan engines,

identified by serial number. This

proposal would require the removal of

engines assembled with an improper

High Pressure Turbine (HPT) module

configuration from service prior to

accumulating 5,100 or 7,600 cycles in

the improper configuration, or at the

next shop visit, depending on the type

of improper HPT configuration, and

restoration to type design. This

proposed amendment is prompted by

reports of engines that do not conform

to the engine type design, which could

cause a Low Cycle Fatigue (LCF) life

reduction of the HPT stage 1 disk. The

actions specified by the proposed AD

are intended to restore engines to type

design configuration and to prevent

possible LCF failure of the HPT stage 1

disk, which could result in an

uncontained engine failure and damage

to the airplane.

DATES: Comments must be received by

July 31, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–21–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

submitted to the Rules Docket by using

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

be inspected at this location between 8

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

Friday, except Federal holidays. The

service information referenced in this

AD may be obtained from International

Aero Engines, 400 Main Street, East

Hartford, CT 06108; telephone (860)

565–5515; fax (860) 565–5510. This

information may be examined at the

FAA, New England Region, Office of the

Regional 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–

5299; telephone 781–238–7133, fax

781–238–7199.

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 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 2000–NE–21–AD.’’ 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

Regional Counsel, Attention: Rules

Docket No. 2000–NE–21–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports that during

recent shop visits at various overhaul

and repair facilities, 32 V2500–A5/D5

series engines have been assembled

with improper HPT module

configurations. The improper HPT

assemblies resulted from incorrect or

incomplete incorporation of several IAE

service bulletins (SB) required for

proper assembly of the high secondary

cooling airflow HPT stage 1 turbine

blades and cooling duct, which were

40556 Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules

introduced as part of the V2533–A5

HPT configuration. The new high

secondary cooling airflow HPT stage 1

blade and modified stage 1 HPT cooling

duct assembly were introduced to

improve the blade cooling and blade

durability. This configuration became

the new standard for all V2500-A5 and

D5 series engines. Service Bulletins

V2500–ENG–72–0242 and SB V2500–

ENG–72–0241 introduced the ‘‘high

airflow’’ HPT blades and stage 1 HPT

cooling duct assembly, respectively, to

the other V2500–A5/D5 models. For

engines with thrust ratings below 33K,

the HPT module can be assembled with

either the low airflow stage 1 HPT

blades and low airflow or high airflow

stage 1 HPT cooling duct assembly (pre

SB V2500–ENG–72–0242 and pre or

post SB V2500–ENG–72–0241,

respectively) or with the high airflow

stage 1 HPT blades and high airflow

cooling duct assembly (post SB V2500–

ENG–72–0242 and post SB V2500–

ENG–72–0241, respectively). The FAA

has reports of 32 engines that have been

assembled with an intermix of high

airflow and low airflow HPT hardware.

There are five improper configurations

of the HPT module in the field as

defined below.

Configuration Stage 1 HPT blade Stage 1 HPT cooling

duct assembly

Towel bar seals part no.

2A0530

Number

Affected

engines

X ............................................................................. Full set of High Flow ...... Low Flow ........................ Installed .......................... 19

X* ............................................................................ 3 or fewer High Flow ..... Low Flow ........................ Installed .......................... 2

X′ ............................................................................ 2 High Flow .................... Low Flow ........................ Not Installed ................... 1

Y ............................................................................. Full set of High Flow ...... High Flow ....................... Installed .......................... 9

Z ............................................................................. Full set of Low Flow ...... High Flow ....................... Installed .......................... 1

Baseline: After installation of Service Bulletins

(SB) 72–0242 and SB 72–0241.

Full set of High Flow ...... High Flow ....................... Not Installed.

Configuration X and X′ result in

higher temperature in the OD rim cavity

of the HPT stage 1 disk than the design

intended. The consequence of this disk

rim temperature increase is a debit to

the life of the disk. An engineering

review has determined that if engines in

configuration X are removed from

service and restored to an approved

configuration prior to accumulating

5,100 cycles in configuration X, the HPT

disk assembled in an approved

configuration will meet its chapter 5 life

limit. The disk rim temperature increase

for configuration X′ engine is less severe

than for the configuration X. An

engineering review has determined that

if the engine in configuration X′ is

removed from service and restored to an

approved configuration prior to

accumulating 7,600 cycles in

configuration X′, the HPT disk

assembled in an approved configuration

will meet its chapter 5 life limit.

Configurations X*, Y, and Z do not

effect the HPT disk rim temperatures

significantly. However, these are not

approved configurations. This proposed

AD will require the removal of engines

with HPT modules built to

configuration X*, Y, or Z from service

and the restoration to type design at the

next shop visit.

The actions specified by the proposed

AD are intended to restore the engine to

type design and prevent possible LCF

failure of the stage 1 HPT disk, which,

if not corrected, could lead to an

uncontained engine failure and damage

to the airplane.

Service Information

IAE has issued All Operators Wire

(AOW) No. 1053, Issue 2, dated June 20,

2000, which identifies engines with

HPT modules utilizing non type design

configurations by serial numbers and by

specific configurations. (configuration

X, X*, X′, Y, or Z).

Proposed Actions

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design registered in the United

States, the proposed AD would require

the removal from service of certain

V2500–A5/D5 series engines, identified

by serial numbers, prior to accumulating

5,100 or 7,600 cycles in the improper

configuration, or at the next shop visit,

depending on the type of improper HPT

module configuration and the

restoration type design.

Economic Analysis

There are approximately 32 engines in

the worldwide fleet with the HPT

module assembled in an improper

configuration. The FAA estimates that

12 engines installed on aircraft of US

registry would be removed from service

before scheduled shop visits as a result

of this proposed AD. The cost of early

removal and restoration to type design

will be approximately $6,000 per

engine. Based on these figures, the total

cost impact of the proposed AD on US

operators is estimated to be $72,000.

Regulatory Impact

This proposal 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 proposal.

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules 40557

International Aero Engines: Docket No.

2000–NE–21–AD.

Applicability: International Aero Engines

(IAE) V2500–A5 and V2500–D5 series

turbofan engines listed by Serial Number (S/

N) as follows: V10011, V10035, V10036,

V10039, V10040, V10041, V10054, V10067,

V10079, V10080, V10084, V10111, V10121,

V10123, V10124, V10130, V10131, V10139,

V10166, V10172, V10174, V10180, V10199,

V10221, V10341, V20001, V20013, V20017,

V20019, V20023, V20033, V20037.

These engines are installed on, but not

limited to, Airbus Industries A319, A320,

A321 series, and McDonnell Douglas MD–90

series airplanes.

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 (b)

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 restore the engines to type design and

to prevent possible low cycle fatigue (LCF)

failure of the HPT stage 1 disk, which could

lead to an uncontained engine failure and

damage to the airplane, accomplish the

following:

Removal and Restoration of the HPT Module

(a) For those engines identified by serial

numbers in Table 1 of this AD, with HPT

modules built to configuration X, X′, X*, Y,

or Z, remove from service in accordance with

Table 1 and restore the HPT module to type

design in accordance with IAE All Operators

Wire (AOW) 1053, Issue 2, dated 6/20/00.

TABLE 1

Engine serial No. HPT module

configuration HPT hardware Reconfigure at or prior to:

V10084, V10035, V10036, V10039,

V10130, V10011, V10040, V10079,

V10080, V10124, V10123, V10111,

V20013, V20017, V10172, V10174,

V20019, V10180, V20023.

X High Flow Blades: Post SB72–0242;

Low Flow Duct Assembly: Pre SB72–

0241; Towel Bar Seals, P/N 2A0530:

Installed.

The earlier of the next shop visit; or accumulating either 5100 cycles in service (CIS) in configuration X, or 100

CIS after the effective date of this AD,

whichever occurs later.

V20037 ..................................................... X′ 2 High Flow Blades: Post SB72–0242;

Low Flow Duct or Assembly: Pre

SB72–0241; Towel Bar Seals, P/N

2A0530: Not Installed.

The earlier of the next shop visit; or accumulating either 7600 CIS in configuration X′, or 100 CIS after the effective date of this AD, whichever occurs

later.

V20001, V20033 ....................................... X* 3 or fewer High Flow Blades: Post

SB72–0242; Low Flow Duct Assembly: Pre SB72–0241; Towel Bar Seals,

P/N 2A0530: Installed.

Next Shop Visit.

V10199, V10166, V10054, V10131,

V10139, V10041, V10121, V10067,

V10341.

Y High Flow Blades: Post SB 72–0242;

High Flow Duct Assembly: Post

SB72–0241; Towel Bar Seals, P/N

2A0530: Installed.

Next Shop Visit.

V10221 ..................................................... Z Low Flow Blades: Pre SB72–0242; High

Flow Duct Assembly: Post SB72–

0241; Towel Bar Seals, P/N 2A0530:

Installed.

Next Shop Visit.

Alternate Methods of Compliance

(b) 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 Principal 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.

Ferry Flights

(c) 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.

Issued in Burlington, Massachusetts, on

June 23, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–16643 Filed 6–29–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF LABOR

Mine Safety and Health Administration

30 CFR Parts 57, 72, and 75

RIN 1219–AA74 and 1219–AB11

Diesel Particulate Matter Exposure of

Underground Miners

AGENCY: Mine Safety and Health

Administration (MSHA), Labor.

ACTION: Proposed rule; availability of

documents; request for comments.

SUMMARY: We (MSHA) are reopening the

rulemaking records of our proposed

rules on diesel particulate matter

exposure of underground coal miners

and underground metal and nonmetal

miners. The reopenings are limited in

scope. Their purpose is to permit public

comment on a few recent documents

that we have added to these records,

including some agency investigations to

verify assertions made by commenters.

DATES: We must receive your comments

by July 31, 2000.

ADDRESSES: Send your comments by

regular mail or hand deliver them to

MSHA, Office of Standards,

Regulations, and Variances, 4015

Wilson Boulevard, Room 631,

Arlington, VA 22203–1984. You also

may send them by telefax (fax) to

MSHA, Office of Standards,

Regulations, and Variances, 703–235–

5551; or by electronic mail (e-mail) to

comments@msha.gov. If you send your