Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Proposed Rules 1299

Revision 1, dated December 9, 1996,

that identifies by serial number (S/N)

affected 4th stage LPT hubs, and

describes procedures for fluorescent

penetrant inspection (FPI) and eddy

current inspection (ECI) of 4th stage LPT

hubs for cracks.

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

require initial and repetitive FPI and

ECI of affected 4th stage LPT hubs for

cracks, and, if necessary, replacement

with serviceable parts. The actions

would be required to be accomplished

in accordance with the ASB described

previously.

The FAA estimates that 381 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take approximately 6 work

hours per engine to accomplish the

proposed actions, 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 $137,160.

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

adding the following new airworthiness

directive:

Pratt & Whitney: Docket No. 96–ANE–32.

Applicability: Pratt & Whitney (PW)

Models JT8D–1, –1A, –1B, –7, –7A, –7B, 9,

–9A, –11, –15, –17, and –17R turbofan

engines, with 4th stage low pressure turbine

(LPT) hubs identified by serial number (S/N)

in Table A of PW Alert Service Bulletin

(ASB) No. A6274, Revision 1, dated

December 97, 1996. These engines are

installed on but not limited to Boeing 727

and 737 series, and McDonnell Douglas DC–

9 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 (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 prevent 4th stage LPT blade failure due

to hub cracking, which can result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) Perform fluorescent penetrant

inspection (FPI) and eddy current inspection

(ECI) of affected 4th stage LPT hubs for

cracks, in accordance with Paragraph 2A of

PW ASB No. A6274, Revision 1, dated

December 9, 1996, as follows:

(1) Inspect at the next time after the

effective date of this AD that the hub is

removed from the module and has been

debladed.

(2) Thereafter, inspect each time the hub is

removed from the module and has been

debladed.

(3) Remove from service any cracked 4th

stage LPT hub and replace with a serviceable

part.

(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. 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.

Issued in Burlington, Massachusetts, on

January 2, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–469 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–ANE–35]

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 (PW) JT8D–200 series turbofan

engines, that currently requires

installation and periodic inspection of

temperature indicators installed on the

No. 4 and 5 bearing compartment

scavenge oil tube and performance of

any necessary corrective action. This

action would require the installation

and periodic inspection of temperature

indicators to all PW JT8D–200 series

engines, including those incorporating

the containment hardware specified in

with AD 93–23–10. This proposal is

prompted by report of an uncontained

turbine failure due to a high pressure

turbine (HPT) shaft fracture on an

engine that had the containment

hardware installed. The actions

specified by the proposed AD are

intended to prevent fracture of the HPT

shaft, which can result in uncontained

release of engine fragments, engine fire,

inflight engine shutdown, or possible

aircraft damage.

DATE: Comments must be received by

March 10, 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.

96–ANE–35, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.
1300 Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Proposed Rules

The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, Publication

Department, Supervisor Technical

Publications Distribution, M/S 132–30,

400 Main St., East Hartford, CT 06108;

telephone (860) 565–7700, 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–

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 96–ANE–35.’’ 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. 96–ANE–35, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On November 3, 1994, the Federal

Aviation Administration (FAA) issued

airworthiness directive AD 94–23–03,

Amendment 39–9065 (59 FR 61789,

December 2, 1994), applicable to Pratt &

Whitney (PW) JT8D–200 series turbofan

engines, to require installation and

periodic inspection of temperature

indicators installed on the No. 4 and 5

bearing compartment scavenge oil tube

and performance of any necessary

corrective action. That action was

prompted by reports of high pressure

turbine (HPT) shaft fractures caused by

oil fires that resulted from internal

leakage of thirteenth stage compressor

discharge air into the No. 4 and 5

bearing compartment. That condition, if

not corrected, could result in fracture of

the HPT shaft, which can result in

uncontained release of engine

fragments, engine fire, inflight engine

shutdown, or possible aircraft damage. Airworthiness directive 94–23–03

excluded from the applicability engines

that had installed HPT containment

hardware in accordance with AD 93–

23–10. Since the issuance of AD 94–23–

03, the FAA has received a report of an

uncontained turbine failure due to an

HPT shaft fracture on a PW Model

JT8D–219 engine that had the

containment hardware installed.

The FAA has reviewed and approved

the technical contents of PW Alert

Service Bulletin (ASB) No. 5944,

Revision 3, dated December 17, 1994,

and Revison 2, dated June 8, 1992, that

describe procedures for installation and

periodic inspection of temperature

indicators installed on the No. 4 and 5

bearing compartment scavenge oil tube

and performance of any necessary

corrective action.

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 94–23–03 to require

installation and periodic inspection of

temperature indicators to all PW JT8D–

200 series engines, including those

incorporating the containment hardware

specified in AD 93–23–10. The actions

would be required to be accomplished

in accordance with the SB described

previously. There are approximately 2,432

engines of the affected design in the

worldwide fleet. The FAA estimates that

1,044 engines installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 1.5 work hours per

engine to accomplish the proposed

actions, 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 $93,960.

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 39–9065 (59 FR

61789, December 2, 1994) and by adding

a new airworthiness directive to read as

follows:

Pratt & Whitney: Docket No. 96–ANE–35.

Supersedes AD 94–23–03, Amendment

39–9065.

Applicability: Pratt & Whitney (PW) JT8D–

209, –217, –217A, –217C, and –219 turbofan

engines, installed on but not limited to

McDonnell Douglas MD–80 series and Boeing

727 series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine identified in the

preceding applicability provision, regardless
Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Proposed Rules 1301

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 (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 as indicated, unless

accomplished previously.

To prevent fracture of the high pressure

turbine (HPT) shaft, which can result in

uncontained release of engine fragments,

engine fire, inflight engine shutdown, or

possible aircraft damage, accomplish the

following:

(a) Install and inspect one or two

temperature indicators, part number (P/N)

810486, or a single or double set of P/N

809129 and P/N 809130 temperature

indicators, on the No. 4 and 5 bearing

compartment scavenge oil tube, as follows:

(1) Install temperature indicators on the

No. 4 and 5 bearing compartment scavenge

oil tube in accordance with Section 2.A.(1) of

the Accomplishment Instructions of PW

Alert Service Bulletin (ASB) No. 5944,

Revision 3, dated December 16, 1994, or

Revision 2, dated June 8, 1992, within 90

days after the effective date of this

airworthiness directive (AD).

(2) Visually inspect temperature indicators

within 65 hours TIS of installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection.

(3) If upon inspection, the color of any

temperature indicator window(s) has turned

completely black, perform troubleshooting

and diagnostic testing and corrective action

as required, in accordance with Section

2.A.(2) (c) and (d) or (f) and (g), as applicable,

of the Accomplishment Instructions of PW

ASB No. 5944, Revision 3, dated December

16, 1994, or Revision 2, dated June 8, 1992.

Prior to returning the engine to service,

replace any temperature indicator that has

turned black and inspect in accordance with

paragraphs (a)(2) and (a)(3) of this AD.

(b) For aircraft installations utilizing one P/

N 810486 indicator or one set of P/N 809129

and 809130 indicators, and inspection

reveals a missing indicator, inspect the

remaining temperature indicator, if

applicable, to determine if the indicator

window has turned completely black. If the

indicator window has turned completely

black, perform troubleshooting and

diagnostic testing, and corrective action as

required, in accordance with paragraph (a)(3)

of this AD. If the indicator window has not

turned completely black or if there are no

additional indicators installed, then install a

new indicator in accordance with Section

2.A.(1) of the Accomplishment Instruction of

PW ASB No. 5944, Revision No. 3, dated

December 16, 1994, or Revision 2, dated June

8, 1992, prior to return to service, and

visually inspect the temperature indicator

within 65 hours TIS since installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection in

accordance with paragraphs (a)(2) and (a)(3)

of this AD.

(c) For aircraft installations utilizing two P/

N 810486 indicators or two sets of P/N

809129 and 809130 indicators, and

inspection reveals a missing indicator(s),

inspect the remaining temperature

indicator(s), if applicable, to determine if the

indicator window has turned completely

black. If the indicator window has turned

completely black, perform troubleshooting

and diagnostic testing, and corrective action

as required, in accordance with paragraph

(a)(3) of this AD. If the indicator window has

not turned completely black, install a new

indicator(s) in accordance with Section

2.A.(1) of the Accomplishment Instructions

of PW ASB No. 5944, Revision 3, dated

December 16, 1994, or Revision 2, dated June

8, 1992, prior to return to service, and

visually inspect the temperature indicator

within 65 hours TIS since installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection in

accordance with paragraphs (a)(2) and (a)(3)

of this AD.

(d) Report the data elements identified in

Appendix E of the Accomplishment

Instructions of PW ASB No. 5944, Revision

3, dated December 16, 1994, or Revision 2,

dated June 8, 1992, whenever an

overtemperature condition is observed on

any color temperature indicator which is the

result of an internal engine problem only and

not resulting from an external cause

corrected by the published troubleshooting

procedures. Data elements should be

reported within 30 days of determining that

the overtemperature condition is the result of

an internal engine problem, to Diane Cook,

Aerospace Engineer, Engine Certification

Office, Engine and Propeller Directorate,

Aircraft Certification Service, FAA, 12 New

England Executive Park, Burlington, MA

01803–05299; telephone (617) 238–7134, fax

(617) 238–7199; Internet:

Diane.Cook@faa.dot.gov. The reporting

requirements of this AD terminate six months

from the effective date of the AD.

(e) Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget under the provisions of the

Paperwork Reduction Act of 1980 (Pub. L.

96–511) and have been assigned OMB control

number 2120–0056.

(f) 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.

(g) 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

January 2, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–468 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

SECURITIES AND EXCHANGE

COMMISSION

17 CFR Chapter II

[Release Nos. 33–7377, 34–38118, 35–26641,

39–2345, IC–22439, IA–1603; File No. S7–

2–97]

List of Rules To Be Reviewed Pursuant

to the Regulatory Flexibility Act

AGENCY: Securities and Exchange

Commission.

ACTION: Publication of list of rules

scheduled for review.

SUMMARY: The Securities and Exchange

Commission is today publishing a list of

rules to be reviewed pursuant to Section

610 of the Regulatory Flexibility Act.

The list is published to provide the

public with notice that these rules are

scheduled for review by the agency and

to invite public comment on them.

DATES: Public comments are due by

January 31, 1997.

ADDRESSES: Persons wishing to submit

written comments should file three

copies with Jonathan G. Katz, Secretary,

Securities and Exchange Commission,

450 Fifth Street, N.W., Room 6184, Stop

6–9, Washington, D.C. 20549. All

submissions should refer to File No. S7–

2–97, and will be available for public

inspection and copying at the

Commission’s Public Reference Room,

Room 1026, at the same address.

FOR FURTHER INFORMATION CONTACT:

Anne H. Sullivan, Office of the General

Counsel, Securities and Exchange

Commission, 202–942–0954.

SUPPLEMENTARY INFORMATION: The

Regulatory Flexibility Act (‘‘RFA’’) (Pub.

L. No. 96–354, 94 Stat. 1165)

(September 19, 1980) requires that each

agency review every ten years each of its

rules that has a significant economic

impact upon a substantial number of

small entities. The purpose of the

review is ‘‘to determine whether such

rules should be continued without

change, or should be amended or

rescinded * * * to minimize any

significant economic impact of the rules

upon a substantial number of small

entities’’ (5 U.S.C. 610(a)).

The RFA stipulates the following

specific considerations that must be