Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations 37765

provides an acceptable level of safety may be

used if approved by the Manager, Engine

Certification Office. Operators shall submit

their requests 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.

(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.

(d) The actions required by this AD shall

be performed in accordance with the

following R-R SB:

Document Number Pages Revision Date

OL.593–72–9016–416 ........................................................................................................... 1–8 1 December 5, 1997.

Total pages: 8

OL.593–72–8951–364 ........................................................................................................... 1–9 5 August 31, 1995.

Total pages: 9

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Rolls-Royce, PO Box 3, Filton, Bristol

BS12 7QE, England; telephone 01–17-979–

1234, fax 01–17–979–7575. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(e) This amendment becomes effective on

July 29, 1998.

Issued in Burlington, Massachusetts, on

July 6, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–18648 Filed 7–10–98; 9:32 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–04; Amendment 39–

10652; AD 97–25–10 R1]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT9D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to certain Pratt & Whitney

(PW) JT9D series turbofan engines, that

currently requires initial and repetitive

fluorescent penetrant inspections (FPI)

for cracks in cooling air holes of first

stage high pressure turbine (HPT) disks,

and replacement of cracked disks with

serviceable parts. In addition, the

current AD requires initial and

repetitive FPI for cracks in tie bolt holes

of certain other affected second stage

HPT disks installed in PW JT9D series

turbofan engines. This amendment calls

out the second stage HPT hub assembly

by part number (P/N) in addition to the

hub P/N for clarification of affected

parts, and references a service bulletin

that does not change any of the

requirements in the AD, but better

explains the inspection procedures that

are referenced in the current AD. This

amendment also increases the repetitive

inspection interval of first stage HPT

disks. This amendment is prompted by

the need to clarify the inspection

procedures and the parts affected by this

AD and by a re-evaluation of the risk

analysis, based on new data from

service, to establish a new repetitive

inspection interval for the first stage

HPT disk. The actions specified by this

AD are intended to prevent turbine disk

failure due to cooling air hole or tie bolt

hole cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

DATES: Effective July 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 29,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

September 14, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

04, 12 New England Executive Park,

Burlington, MA 01803-5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

The service information referenced in

this AD 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 Regional

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tara

Goodman, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7130, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: On

November 28, 1997, the Federal

Aviation Administration (FAA) issued

AD 97–25–10, Amendment 39–10234

(62 FR 64514, December 8, 1997),

applicable to certain Pratt & Whitney

(PW) JT9D series turbofan engines, to

require initial and repetitive fluorescent

penetrant inspections (FPI) for cracks in

cooling air holes of affected first stage

high pressure turbine (HPT) disks, and,

if necessary, replacement with

serviceable parts. In addition, that

airworthiness directive (AD) requires

initial and repetitive FPI for cracks in tie

bolt holes of all affected second stage

HPT disks. Finally, that action requires

reporting findings of cracked turbine

disks. That action was prompted by

reports of a cracked cooling air hole on

one first stage HPT disk, and a cracked

tie bolt hole on one second stage HPT

disk. That condition, if not corrected,

could result in turbine disk failure due

to cooling air hole or tie bolt hole

cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

Since the issuance of that AD, the

FAA received questions regarding

clarifying the inspection procedures for

second stage HPT disk tie bolt holes. In

addition, one commenter requested that

the 48 hour time requirement to notify

the FAA that a cracked disk is found be

changed to 10 working days. The

commenter explained that 48 hours is

not practical if a cracked disk is found

over a holiday weekend. The FAA

concurs, and has changed this revision

to the final rule AD to include a 10

working day reporting requirement.
37766 Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations

Also, based on new data and

subsequent re-evaluation of the risk

analysis since publication of the

existing AD, the FAA has determined

that the repetitive inspection interval for

first stage HPT disks may be extended.

This revision to the final rule AD

includes the extended inspection

interval.

The FAA has reviewed and approved

the technical contents of PW Service

Bulletin (SB) No. JT9D–7R4–72–536,

Revision 2, dated April 30, 1998, that

describes procedures for FPI for cracks

in tie bolt holes of all affected second

stage HPT disks.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD revises AD 97–25–

10 to call out the second stage HPT hub

assembly by part number (P/N) in

addition to the hub P/N for clarification

of affected parts, and reference a SB that

does not change any of the requirements

in the AD, but better explains the

inspection procedures that are

referenced in the current AD. The

actions are required to be accomplished

in accordance with PW SB No. JT9D–

7R4–72–536, Revision 2, dated April 30,

1998.

Since the issuance of that AD, the

FAA received a request to increase the

inspection interval for first stage HPT

disks. The FAA has determined, by

review of risk analysis, that extending

the inspection interval provides an

adequate margin of safety.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NE–04.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–10234 (62 FR

64514, December 8, 1997) and by adding

a new airworthiness directive,

Amendment 39–10652, to read as

follows:

97–25–10 R1 Pratt & Whitney: Amendment

39–10652. Docket 97–ANE–04. Revises

AD 97–25–10, Amendment 39–10234.

Applicability: Pratt & Whitney (PW) JT9D–

59A, –70A, –7Q, –7Q3, –7R4D, –7R4D1,

–7R4E, and –7R4E1 (AI–500) series turbofan

engines, installed on but not limited to

Airbus Industrie A300 and A310, Boeing 747

and 767, and McDonnell Douglas DC–10

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 (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.

Compliance: Required as indicated, unless

accomplished previously.

To prevent turbine disk failure due to

cooling hole or tie bolt hole cracking, which

could result in an uncontained engine failure

and damage to the aircraft, accomplish the

following:

(a) For first stage high pressure turbine

(HPT) disks, part numbers (P/Ns) 768001,

792701, 812901, 819801, 840501, 840401,

840701, 840601, and 840301, installed in PW

JT9D–59A, –70A, –7Q, and –7Q3 engines,

accomplish the following:

(1) Disks that have not been fluorescent

penetrant inspected or eddy current

inspected since introduction into service,

perform an initial fluorescent penetrant

inspection (FPI) for cracks in all 40 cooling

air holes in accordance with PW Turbojet

Engine Standard Practices Manual, P/N

585005, Chapter/Section 70–33, Special

Process Operation Procedure (SPOP) 84, as

follows:

(i) Disks with 3,500 cycles since new (CSN)

or more on the effective date of this AD,

inspect prior to accumulating 5,000 CSN, or

within 1,500 cycles in service (CIS) after the

effective date of this AD, whichever occurs

later.
Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations 37767

(ii) Disks with less than 3,500 CSN on the

effective date of this AD, inspect prior to

accumulating 5,000 CSN.

(2) Disks that have been reoperated in

accordance with PW Service Bulletin (SB)

No. 5815, Revision 2, dated July 31, 1992, or

prior revisions, that have not been

fluorescent penetrant inspected or eddy

current inspected since reoperation, perform

an initial FPI for cracks in all 40 cooling air

holes in Chapter/Section 70–33, SPOP 84, as

follows:

(i) Disks with 3,500 CIS or more since

reoperation on the effective date of this AD,

inspect prior to accumulating 5,000 CIS since

reoperation, or within 1,500 CIS after the

effective date of this AD, whichever occurs

later.

(ii) Disks with less than 3,500 CIS since

reoperation on the effective date of this AD,

inspect prior to accumulating 5,000 CIS since

reoperation.

(3) Disks that have been fluorescent

penetrant inspected, or eddy current

inspected, since introduction into service or

since reoperation, in accordance with PW SB

No. 5744, Revision 3, dated March 31, 1993,

or prior revisions, or PW JT9D–7Q, –7Q3

Engine Manual, P/N 777210, 72–51–00,

Inspection –03, or PW JT9D–59A, –70A

Engine Manual, P/N 754459, 72–51–00,

Heavy Maintenance Check –03, perform an

FPI for cracks in all 40 cooling air holes,

prior to accumulating 5,000 CIS since last FPI

or ECI, or within 250 CIS after the effective

date of this AD, whichever occurs later, in

accordance with PW Turbojet Engine

Standard Practices Manual, P/N 585005,

Chapter/Section 70–33, SPOP 84.

(4) Thereafter, perform FPI for cracks in all

40 cooling air holes at intervals not to exceed

5,000 CIS since last FPI, in accordance with

PW Turbojet Engine Standard Practices

Manual, P/N 585005, Chapter/Section 70–33,

SPOP 84.

(5) Prior to further flight, remove from

service cracked disks, and replace with

serviceable parts.

(b) For second stage HPT disks, P/N

5001802–01, or hub assembly, P/N 808242,

installed in PW JT9D–7R4D, –7R4D1, –7R4E,

and –7R4E1 (AI–500) engines, accomplish

the following:

(1) Disks that have not been fluorescent

penetrant inspected since introduction into

service, perform an initial FPI for cracks in

all 30 tie bolt holes in accordance with PW

SB No. JT9D–7R4–72–536, Revision 2, dated

April 30, 1998, as follows:

(i) Disks with 6,000 CSN or more on the

effective date of this AD, inspect within

2,000 CIS after the effective date of this AD.

(ii) Disks with less than 6,000 CSN on the

effective date of this AD, inspect prior to

accumulating 8,000 CSN.

(2) Disks that have been fluorescent

penetrant inspected since introduction into

service, perform an FPI for cracks in all 30

tie bolt holes, prior to accumulating 8,000

CIS since last FPI, or within 250 CIS after the

effective date of this AD, whichever occurs

later, in accordance with PW SB No. JT9D–

7R4–72–536, Revision 2, dated April 30,

1998.

(3) Thereafter, perform FPI for cracks in all

30 tie bolt holes at intervals not to exceed

8,000 CIS since last FPI, in accordance with

PW SB No. JT9D–7R4–72–536, Revision 2,

dated April 30, 1998.

(4) Prior to further flight, remove from

service cracked disks, and replace with

serviceable parts.

(c) Report findings of cracked turbine disks

within 10 working days after inspection to

Tara Goodman, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–5299;

telephone (781) 238–7130, fax (781) 238–

7199, Internet: ‘‘Tara.Goodman@faa.dot.gov’’.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(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, Engine

Certification Office. Operators shall submit

their requests 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 method of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The inspections shall be done in

accordance with the following PW SB:

Document Number Pages Revision Date

JT9D–7R4–72–536 .......................................................................................................... 1 2 .................... April 30, 1998.

2 Original ......... February 28, 1997.

3, 4 2 .................... April 30, 1998.

5, 6 Original ......... February 28, 1997.

7 2 .................... April 30, 1998.

8–10 1 .................... October 13, 1997.

Total pages: 10.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860) 565–

6600, fax (860) 565–4503. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

July 29, 1998.

Issued in Burlington, Massachusetts, on

July 6, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–18649 Filed 7–10–98; 9:33 am]

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Parts 740, 746, and 774

[Docket No. 980522136–8136–01]

RIN 0694–AB69

Exports to the Federal Republic of

Yugoslavia (Serbia and Montenegro);

Imposition of Foreign Policy Controls

AGENCY: Bureau of Export

Administration, Commerce.

ACTION: Final rule.

SUMMARY: Reacting to the use of

excessive force by Serbian police forces

against civilians in Kosovo, as well as

acts of violence by the Kosovar

Albanian extremists and fulfilling

United States obligations to implement

an international arms embargo

mandated by the United Nations

Security Council, the United States has

banned the sale and supply of arms and

related mate ́riel of all types to the

Federal Republic of Yugoslavia (Serbia

and Montenegro). To supplement the

State Department controls on items on

the U.S. Munitions List, the Bureau of

Export Administration (BXA) is

designating certain items on the

Commerce Control List (CCL) that are

subject to the arms embargo and

establishing a policy of denial to the

Federal Republic of Yugoslavia (Serbia

and Montenegro) on such items. No

embargoed items may be exported to the

Federal Republic of Yugoslavia (Serbia

and Montenegro) under any License

Exception, including shipments of

limited value (LVS).

In addition, this rule makes certain

editorial revisions to the Export