Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations 37763

stage 4–5 interstage seal teeth during each

shop visit as defined in paragraph (c) of this

AD, and if necessary, replace with

serviceable parts prior to returning the engine

to revenue service, in accordance with GE

Service Bulletin (SB) No. 72–352, Revision 2,

dated March 31, 1998.

(c) For the purpose of this AD, an engine

shop visit is defined as any time an engine

has maintenance performed that involves

separation of a major engine flange (such as

removal of an LPT module or HPC ‘‘top

case’’).

(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 methods of

compliance with this airworthiness directive,

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 inspection requirements

of this AD can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following GE

service documents:

Document Number Pages Revision Date

SB No. 72–352 ........................................................................................................................... 1–32 2 March 31, 1998.

Total pages: 32

ASB No. 72–A357 ...................................................................................................................... 1–30 2 April 21, 1998.

Total pages: 30

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 General Electric Technical Services,

Attention: Leader for distribution/microfilm,

10525 Chester Road, Cincinnati, OH 45215;

telephone (513) 672–8400 Ext. 130, fax (513)

672-8422. 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. 98–18647 Filed 7–10–98; 9:29 a.m.]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–13–AD; Amendment

39–10653; AD 98–15–02]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

Limited, Aero Division-Bristol,

S.N.E.C.M.A, Olympus 593 Series

Turbojet Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Rolls-Royce Limited, Aero

Division-Bristol, S.N.E.C.M.A. Olympus

593 series turbojet engines. This action

requires identifying reduced postrebroaching cyclic life limits for certain

rebroached stage 6 high pressure

compressor (HPC) disks, inspecting the

rebroached disks for cracks, and, if

necessary, removing from service

cracked disks. This amendment is

prompted by reports of the low cyclic

lives at which some rebroached stage 6

HPC disks have been found cracked.

The actions specified in this AD are

intended to prevent rebroached stage 6

HPC disk failure, 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. 98–ANE–

13–AD, 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 RollsRoyce, PO Box 3, Filton, Bristol BS12

7QE, England; telephone 01–17–979–

1234, fax 01–17–979–7575. 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:

Jason Yang, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7747, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom (UK), recently notified the

Federal Aviation Administration (FAA)

that an unsafe condition may exist on

Rolls-Royce Limited (R–R), Aero

Division-Bristol, S.N.E.C.M.A Olympus

593 Mk. 610–14–28 turbojet engines.

The CAA advises that they have

received reports of cracked, rebroached

stage 6 high pressure compressor (HPC)

disks. There are currently no affected

engines operated on aircraft of U.S.

registry. This AD, then, is necessary to

require accomplishment of the required

actions for engines installed on aircraft

currently of foreign registry that may

someday be imported into the U.S. or

for engines installed on aircraft which

currently operate in U.S. airspace.

Accordingly, the FAA has determined

that notice and prior opportunity for

comment are unnecessary and good

cause exists for making this amendment

effective in less than 30 days. This

condition, if not corrected, could result

in rebroached stage 6 HPC disk failure,

which could result in an uncontained

engine failure and damage to the

aircraft.

R–R has issued Service Bulletin (SB)

No. OL.593–72–9016–416, Revision 1,

dated December 5, 1997, that specifies

procedures for identifying the new,

reduced, cyclic life limits for individual

stage 6 HPC disks, and SB No. OL.593–

72–8951–364, Revision 5, dated August

31, 1995, that specifies procedures for

inspection of rebroached stage 6 HPC

disks for cracks. The CAA classified
37764 Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations

these SBs as mandatory and issued AD

007–06–96 in order to assure the

airworthiness of these engines in the

UK.

This engine model is manufactured in

the UK and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

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, this AD requires identifying

reduced post-rebroaching cyclic life

limits for rebroached stage 6 high

pressure compressor (HPC) disks

(B509174 to B509181), inspecting the

rebroached disks for cracks, and if

necessary, removing from service

cracked disks. The actions would be

required to be accomplished in

accordance with the SBs described

previously.

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 98–ANE–13–AD.’’ 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

adding the following new airworthiness

directive:

98–15–02 Rolls-Royce Limited, Aero

Division-Bristol, S.N.E.C.M.A.:

Amendment 39–10653. Docket 98–ANE–

13–AD.

Applicability: Rolls-Royce Limited (R-R),

Aero Division-Bristol, S.N.E.C.M.A. Olympus

593 Mk. 610–14–28 turbojet engines,

installed on but not limited to British

Aerospace/Aerospatiale Concorde 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 rebroached stage 6 high

pressure compressor (HPC) disk failure,

which could result in an uncontained engine

failure and damage to the aircraft,

accomplish the following:

(a) Accomplish the following in

accordance with R–R Service Bulletin (SB)

No. OL.593–72–9016–416, Revision 1, dated

December 5, 1997:

(1) Remove from service rebroached HPC

stage 6 disks (B509174 to B509181) listed in

Table 1 and 5 of the SB prior to exceeding

the earliest of the following:

(i) 1,100 cycles in service (CIS) since

rebroaching, or

(ii) 2,700 cycles since new (CSN) prior to

January 1, 2000, or

(iii) 2,500 CSN after December 31, 1999.

(2) Inspect the HPC stage 6 disks listed in

Table 2 and 6 of the SB within the CIS

intervals since rebroach as defined in these

Tables. Disks with cracks in any blade root

slot must be removed from service. Perform

the inspection in accordance with R-R SB No.

OL.593–72–8951–364, Revision 5, dated

August 31, 1995.

(3) Remove from service HPC stage 6 disks

listed in Table 2 and 6 of the SB prior to

exceeding the maximum post-rebroach cyclic

life limits as defined in these Tables, or 2,500

CSN after December 31, 1999, whichever

occurs first.

(b) An alternative method of compliance or

adjustment of the compliance time that
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.