28520 Federal Register / Vol. 61, No. 109 / Wednesday, June 5, 1996 / Proposed Rules

Airbus Industrie Models A300B2, A300B4,

A310–200, A310–300, A300–600, A320–100,

A320–200, A321–100, A330–300, A340–200,

and A340–300 series airplanes;

Beech Models 1900 and BE–65 through –90

(inclusive) series airplanes;

Boeing Models 727–100, 727–200, 737–

200, 737–300, 737–400, 737–500, 747–100,

747–200, 747–300, 747–400, 747SP, 757–200,

767–200, and 767–300 series airplanes;

Convair Model CV–580 airplanes;

de Havilland DHC–7 series airplanes and

Model DHC–8–100 airplanes;

Embraer Model EMB–120 series airplanes;

Fairchild Model F227 airplanes;

Fokker Models F28 Mark 100, Mark 1000,

and Mark 4000 series airplanes;

General Dynamics Models Convair 340 and

440 airplanes;

Gulfstream Models G–159 and G-IV

airplanes;

Lockheed Model L1011 series airplanes;

McDonnell Douglas Models DC–8–60, DC–

9–31, DC–9–51, DC–10–10; DC–10–30, DC–

10–30F, MD–11, and MD–80 series airplanes;

Rockwell International NA–265–65

airplanes;

Saab Model 340 series airplanes; and

Shorts Model 360 series airplanes.

Note 1: This AD applies to each airplane

on which the TCAS unit identified in the

preceding applicability provision has been

installed, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For affected TCAS units or 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 (d)

of this AD. The request should include an

assessment of the effect of the modification,

alteration, or repair on the unsafe condition

addressed by this AD; and, if the unsafe

condition has not been eliminated, the

request should include specific proposed

actions to address it.

Note 2: CAS–81 Traffic Alert and Collision

Avoidance Systems (TCAS) processors

having serial numbers 6066 and subsequent,

are not subject to the requirements of this

AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that the flightcrew is advised of

the potential hazard associated with failure

of the audio output of the CAS–81 TCAS, and

of the procedures necessary to address it,

accomplish the following:

(a) Within 3 calendar days after February

5, 1996 (the effective date of AD 95–26–15,

amendment 39–9495), revise the Limitations

Section of the FAA-approved Airplane Flight

Manual (AFM) to include the following. This

may be accomplished by inserting a copy of

this AD in the AFM.

‘‘In order to ensure that the audio output

of the CAS–81 TCAS operates properly,

accomplish the following:

• Prior to the first flight of the day; prior

to the accumulation of 10 hours of power;

and at the mid-point of any one flight

scheduled to exceed hours: Cycle the power

to the TCAS processor via the circuit breaker

or power bus.

• Prior to taxi before takeoff: Initiate the

TCAS functional test in accordance with

AFM procedures to verify operational

condition of the CAS–81 TCAS.’’

(b) For airplanes on which the

manufacturer has substantiated 30 degrees

Celsius as a maximum ambient temperature

for the TCAS processor location, the

following is considered to be an alternative

method of compliance for the AFM revision

requirements: Revise the Limitations Section

of the FAA-approved Airplane Flight Manual

(AFM) to include the following. This may be

accomplished by inserting a copy of this AD

in the AFM. After revising the AFM, the

AFM revision required by paragraph (a) of

this AD may be removed from the AFM.

‘‘In order to ensure that the audio output

of the CAS–81 TCAS operates properly,

accomplish the following:

Prior to each flight of up to 18 hours

duration, reset the TCAS circuit breaker and

conduct a TCAS self-test.’’

(c) Modification of the TPA–81A TCAS

processor receiver in accordance with Allied

Signal Service Bulletin TPA–81A–34–82,

dated January 1996, and Allied Signal

Service Bulletin TPA–81A–34–84, dated

January 1996, constitutes terminating action

for the requirements of this AD. After this

modification is accomplished, the AFM

revisions specified in paragraphs (a) and (b)

of this AD may be removed from the AFM.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Atlanta

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate. 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.

(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.

Issued in Renton, Washington, on May 30,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14038 Filed 6–4–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–ANE–57]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT9D 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 Pratt

& Whitney JT9D series turbofan engines.

This proposal would require installing

an improved design turbine exhaust

case (TEC) with a thicker containment

wall or modified TEC. This proposal is

prompted by reports of 64 uncontained

engine failures since 1972. The actions

specified by the proposed AD are

intended to prevent release of

uncontained debris from the turbine

exhaust case following an internal

engine failure, which can result in

damage to the aircraft.

DATES: Comments must be received by

August 5, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–57, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may also be submitted to the

Rules Docket by using the following

Internet address: ‘‘epdadcomments@mail.hq.faa.gov’’.

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, Publications

Department, Supervisor Technical

Publications Distribution, M/S 132–30,

400 Main St., East Hartford, CT 06108;

telephone (860) 565–7700. 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:

Daniel Kerman, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7130,

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
Federal Register / Vol. 61, No. 109 / Wednesday, June 5, 1996 / Proposed Rules 28521

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 95–ANE–57.’’ 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. 95–ANE–57, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has determined that the turbine

exhaust case (TEC) on Pratt & Whitney

(PW) JT9D–3, –7, –20, –59A, –70A, –7Q,

and –7R4 series turbofan engines may

not be capable of containing a release of

engine debris should an internal engine

failure occur. The FAA has determined,

based on service experience, that TEC

penetrations have resulted from

multiple internal gas path failure

modes. Primary penetrations of the TEC

have been isolated to the outer wall

between the leading edge of the casing

struts and the forward ‘‘P’’ flange. This

condition, if not corrected, could result

in release of uncontained debris from

the turbine exhaust case following an

internal engine failure, which can result

in damage to the aircraft.

Service experience has demonstrated

that there exists a need for out-of-plane,

aft containment. The FAA has received

reports of 64 uncontained failures of the

TEC since 1972.

These TEC penetrations have resulted

from a variety of failure modes. In some

incidents, the engine failures have

occurred as far upstream as the fan

module No. 1 bearing to as far

downstream as the sixth stage low

pressure turbine blades. In all instances

these failures have caused a balling

effect in which downstream debris has

penetrated through the TEC shell wall.

As a result of these uncontainments, PW

has refined their analytical containment

model based on the results of ballistics

testing. PW utilized this data to

establish new casing wall thickness

requirements for aft containment. Pratt

& Whitney has developed three

containment improvements: a

redesigned, thick-wall TEC developed

for all models of the JT9D engine;

containment shields for all models of

the JT9D engine; and a new TEC ‘‘P’’

flange and case wall replacement for all

models of the JT9D engine excluding the

Model JT9D–7R4D (BG–700 series)

turbofan engines.

The FAA has reviewed and approved

the technical contents of the following

PW Service Bulletins (SB’s): SB No.

6113, dated April 13, 1993; SB No.

5977, dated December 14, 1990; SB No.

JT9D–7R4–72–479, Revision 1, dated

November 12, 1993; SB No. 6243, dated

February 1, 1996; SB No. JT9D–7R4–72–

513, Revision 2, dated January 10, 1996;

SB No. 5907, dated March 27, 1990; SB

No. JT9D–7R4–72–407, Revision 1,

dated August 16, 1990; SB No. JT9D–

7R4–72–466, Revision 2, dated May 10,

1996; SB No. 6118, Revision 3, dated

January 10, 1996; and SB No. 6157,

dated February 9, 1994. These SB’s

describe replacing the previous TEC

with a new, thicker case wall TEC,

installing a new containment shield for

enhanced containment capability, and

replacing the TEC ‘‘P’’ flange and case

wall with a thicker cross section.

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 installing an improved design

TEC with a thicker containment wall,

modifying the existing TEC to

incorporate a containment shield, or

modifying the existing TEC to replace

the ‘‘P’’ flange and case wall. The FAA

has established a compliance end-date

of 48 months after the effective date of

this AD based upon shop visit rates for

hot section overhaul. The actions would

be required to be accomplished in

accordance with the service bulletins

described previously.

There are approximately 2,748

engines of the affected design in the

worldwide fleet. The FAA estimates that

740 engines installed on aircraft of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 14 work hours per engine

to accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Required parts would cost

approximately $1,404 per engine. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $1,660,560.

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

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Pratt & Whitney: Docket No. 95–ANE–57.

Applicability: Pratt & Whitney (PW) JT9D–

3, –7, –20, –59A, –70A, –7Q, and –7R4 series

turbofan engines, installed on but not limited

to Airbus A300 and A310 series; Boeing 747

and 767 series; and McDonnell Douglas DC–

10 series aircraft.

Note: 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
28522 Federal Register / Vol. 61, No. 109 / Wednesday, June 5, 1996 / Proposed Rules

use the authority provided in paragraph (b)

to request approval from the Federal Aviation

Administration (FAA). This approval may

address either no action, if the current

configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent release of uncontained debris

from the turbine exhaust case (TEC)

following an internal engine failure, which

can result in damage to the aircraft,

accomplish the following:

(a) At the next removal of the TEC from the

low pressure turbine case ‘‘P’’ flange for

overhaul, where the No. 4 bearing, carbon

seals, lubrication pressurization lines, or

scavenge lines are removed for maintenance

after the effective date of this AD, but not

later than 48 months after the effective date

of this AD, accomplish the following:

(1) For PW JT9D–3A, –7, –7A, –7AH, –7H,

–7F, –7J, –20, and –20J series turbofan

engines, accomplish any one of the following

actions:

(i) Install a thicker-walled TEC, with Part

Numbers (P/N’s) listed in PW SB No. 6113,

dated April 13, 1993, as applicable; or

(ii) Install a modified TEC that incorporates

a containment shield, with P/N’s listed in

PW SB No. 5907, dated March 27, 1990, as

applicable; or

(iii) Install a modified TEC that

incorporates a replacement ‘‘P’’ flange and

case wall, with P/N’s listed in PW SB No.

6118, Revision 3, dated January 10, 1996.

(2) For PW JT9D–7Q and –7Q3 series

turbofan engines, accomplish any one of the

following actions:

(i) Install a thicker-walled TEC, with P/N’s

listed in PW SB No. 5977, dated December

14, 1990; or

(ii) Install a modified TEC that incorporates

a containment shield, with P/N’s listed in

PW SB No. 5907, dated March 27, 1990, as

applicable; or

(iii) Install a modified TEC that

incorporates a replacement ‘‘P’’ flange and

case wall, with P/N’s listed in PW SB No.

6157, dated February 9, 1994.

(3) For PW JT9D–59A and –70A series

turbofan engines, accomplish one of the

following actions:

(i) Install a thicker-walled TEC, with P/N’s

listed in PW SB No. 6243, dated February 1,

1996; or

(ii) Install a modified TEC that incorporates

a containment shield, with P/N’s listed in

PW SB No. 5907, dated March 27, 1990, as

applicable;

(iii) Install a modified TEC that

incorporates a replacement ‘‘P’’ flange and

case wall, with P/N’s listed in PW SB No.

6157, dated February 9, 1994.

(4) For PW JT9D–7R4D (BG–700 series)

turbofan engines, accomplish either of the

following actions:

(i) Install a thicker-walled TEC, with P/N’s

listed in PW SB No. JT9D–7R4–72–479,

Revision 1, dated November 12, 1993; or

(ii) Install a modified TEC that incorporates

a containment shield, with P/N’s listed in

PW SB No. JT9D–7R4–72–407, Revision 1,

dated August 16, 1990, as applicable.

(5) For PW JT9D–7R4D (BG–800 series),

–7R4D (BG–900 series), –7R4D1 (AI–500

series), –7R4E (BG–800 series), –7R4E (BG–

900 series), –7R4E1 (AI–500 series), –7R4E1

(AI–600 series), –7R4E4 (BG–900 series),

–7R4G2 (BG–300 series), and –7R4H1 (AI–

600 series) turbofan engines, accomplish any

one of the following actions:

(i) Install a thicker-walled TEC, with P/N’s

listed in PW SB No. JT9D–7R4–72–513,

Revision 2, dated January 10, 1996; or

(ii) Install a modified TEC that incorporates

a containment shield, with P/N’s listed in

PW SB No. JT9D–7R4–72–466, Revision 2,

dated May 10, 1996; or

(iii) Install a modified TEC that

incorporates a replacement ‘‘P’’ flange and

case wall, with P/N’s listed in PW SB No.

JT9D–7R4–72–513, Revision 2, dated January

10, 1996.

(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: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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

May 22, 1996.

Robert E. Guyotte,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 96–14033 Filed 6–4–96; 8:45 am]

BILLING CODE 4910–13–P

OFFICE OF THE UNITED STATES

TRADE REPRESENTATIVE

19 CFR Part 132

Extension of Comment Period for

Administration of Tobacco Tariff-Rate

Quota

AGENCY: Office of the United States

Trade Representative.

ACTION: Notice of extension of comment

period.

SUMMARY: On February 20, 1996, the

Office of the United States Trade

Representative (USTR) published a

notice soliciting comments and views

on the administration of the tariff-rate

quota on leaf tobacco, established on

September 13, 1995, which was

operating on a first-come, first-served

basis (61 FR 6333). Because of request

by interested parties for an extension of

the comment period, USTR is extending

the comment period until June 19, 1996.

DATES: Comment period extended until

June 19, 1996.

ADDRESSES: Office of the U.S. Trade

Representative, Room 222, 600 17th

Street, NW., Washington, DC 20508,

attention: Tobacco Tariff-Rate Quota.

FOR FURTHER INFORMATION CONTACT:

Tom Perkins, Senior Economist, Office

of Agricultural Affairs, USTR, (202)

395–6127; or Rachel Shub, Assistant

General Counsel, USTR (202) 395–7305.

SUPPLEMENTARY INFORMATION: Persons

submitting written comments should

provide a statement, in ten copies, by

noon June 19, 1996 to Sybia Harrison,

Office of the United States Trade

Representative, Room 222, 600 17th

Street, NW., Washington, DC 20508,

attention: Tobacco Tariff-Rate Quota.

Non-confidential information received

will be available for public inspection

by appointment, in the USTR Reading

Room, Room 101, Monday through

Friday, 10:00 a.m. to 12:00 noon and

1:00 p.m. to 4:00 p.m. For an

appointment call Brenda Webb at (202)

395–6186. Business confidential

information will be subject to the

requirements of 15 CFR 2003.6 Any

business confidential material must be

clearly marked as such on the cover

letter or page and each succeeding page,

and must be accompanied by a nonconfidential summary thereof.

Jennifer Hillman,

General Counsel.

[FR Doc. 96–13992 Filed 6–4–96; 8:45 am]

BILLING CODE 3190–01–M

DEPARTMENT OF THE TREASURY

Customs Service

19 CFR Part 151

RIN 1515–AB75

Detention of Merchandise

AGENCY: Customs Service, Department

of the Treasury.

ACTION: Proposed rule.

SUMMARY: This document proposes

amendments to the Customs Regulations

to provide for procedures regarding the

detention of merchandise that is

undergoing extended Customs

examination. It is intended that the