Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations 37761

certified by the Board of Directors,

because the FDIC is retaining a

regulation which it had proposed to

remove, the final action merely

maintains the existing status quo and

makes only non-substantive technical

revisions to the existing sections.

List of Subjects in 12 CFR Part 360

Savings associations.

For the reasons set out in the

preamble, part 360 of chapter III of title

12 of the Code of Federal Regulations is

amended as follows:

PART 360—RESOLUTION AND

RECEIVERSHIP RULES

1. The authority citation for part 360

continues to read as follows:

Authority: 12 U.S.C. 1821(d)(11), 1821

(e)(8)(D)(i), 1823(c)(4); Sec. 401(h), Pub. L.

101–73, 103 Stat. 357.

2 Paragraph (b) of § 360.1 is revised to

read as follows:

§ 360.1 Least-cost resolution.

* * * * *

(b) Purchase and assumption

transactions. Subject to the requirement

of section 13(c)(4)(A) of the FDI Act (12

U.S.C. 1823(c)(4)(A)), paragraph (a) of

this section shall not be construed as

prohibiting the FDIC from allowing any

person who acquires any assets or

assumes any liabilities of any insured

depository institution, for which the

FDIC has been appointed conservator or

receiver, to acquire uninsured deposit

liabilities of such institution as long as

the applicable insurance fund does not

incur any loss with respect to such

uninsured deposit liabilities in an

amount greater than the loss which

would have been incurred with respect

to such liabilities if the institution had

been liquidated.

3. Paragraph (e) of § 360.2 is revised

to read as follows:

§ 360.2 Federal Home Loan banks as

secured creditors.

* * * * *

(e) The receiver for a borrower from

a Federal Home Loan Bank shall allow

a claim for a prepayment fee by the

Bank if, and only if:

(1) The claim is made pursuant to a

written contract that provides for a

prepayment fee, provided, however, that

such prepayment fee allowed by the

receiver shall not exceed the present

value of the loss attributable to the

difference between the contract rate of

the secured borrowing and the

reinvestment rate then available to the

Bank; and

(2) The indebtedness owed to the

Bank by such borrower is secured by

sufficient collateral in which a perfected

security interest in favor of the Bank

exists or as to which the Bank’s security

interest is entitled to priority under

section 306(d) of the Competitive

Equality Banking Act of 1987 (CEBA)

(12 U.S.C. 1430(e), footnote (1), or

otherwise so that the aggregate of the

outstanding principal on the advances

secured by such collateral, the accrued

but unpaid interest thereon and the

prepayment fee applicable to such

advances can be paid in full from the

amounts realized from such collateral.

For purposes of this paragraph (e)(2),

the adequacy of such collateral shall be

determined as of the date such

prepayment fees shall be due and

payable under the terms of the written

contract providing therefor.

By order of the Board of Directors.

Dated at Washington, DC, this 7th day of

July 1998.

Federal Deposit Insurance Corporation.

James LaPierre,

Deputy Executive Secretary.

[FR Doc. 98–18620 Filed 7–13–98; 8:45 am]

BILLING CODE 6714–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–17–AD; Amendment

39–10654; AD 98–15–03]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company GE90 Series

Turbofan 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 General Electric Company

(GE) GE90 series turbofan engines. This

action requires initial and repetitive

eddy current inspections (ECI) for

cracks in the high pressure compressor

(HPC) stage 2–6 spool, and, if necessary,

replacement with serviceable parts. This

amendment is prompted by reports of

cracks in the stage 3–4 and stage 4–5

interstage seal teeth and spacer arms.

The actions specified in this AD are

intended to identify cracks in the HPC

stage 2–6 spool, 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–

17–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 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. 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: Ian

Dargin, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received reports of cracked high

pressure compressor (HPC) stage 2–6

spools installed on General Electric

Company (GE) GE90–76B/ –77B/ –85B/

–90B/ –92B series turbofan engines.

There have been 10 HPC spools found

with cracks. The investigation into the

cause of the cracking is ongoing;

however, the FAA has determined that

the HPC stage 2–6 spool may develop

cracks in the stage 3–4 and stage 4–5

interstage seal teeth that could

propagate into the stage 3–4 and stage

4–5 spacer arms, aft of the seal teeth.

This AD requires inspection of the

spacer arm aft of the seal teeth and also

includes an inspection requirement for

the spacer arm forward of the seal teeth

that provides additional data to support

the investigation and mitigates the risk

of an HPC stage 2–6 spool failure from

a crack propagating into the spacer arm

forward of the seal teeth. The FAA has

determined the most likely cause of

crack initiation is due to areas of heat

affected zone in the seal teeth that is the

result of excessive heat generated when
37762 Federal Register / Vol. 63, No. 134 /Tuesday, July 14, 1998 /Rules and Regulations

the rotating seal teeth rub into the static

honeycomb material. This condition, if

not corrected, could result in HPC stage

2–6 spool cracking, which could result

in an uncontained engine failure and

damage to the aircraft.

The FAA has reviewed and approved

the technical contents of GE Alert

Service Bulletin (ASB) No. 72–A357,

Revision 2, dated April 21, 1998, that

describes procedures for on-wing eddy

current inspection (ECI) for cracks in the

HPC stage 2–6 spool spacer arm forward

and aft of the stage 3–4 and stage 4–5

interstage seal teeth, and GE Service

Bulletin (SB) No. 72–352, Revision 2,

dated March 31, 1998, that describes

procedures for ECI of stage 3–4 and

stage 4–5 interstage seal teeth.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

identify cracks in the HPC stage 2–6

spool, which could result in an

uncontained engine failure and damage

to the aircraft. This AD requires:

(1) Initial and repetitive on-wing ECI

for cracks in the HPC stage 2–6 spool

spacer arms forward and aft of the stage

3–4 and stage 4–5 interstage seal teeth,

and, if necessary, replacement with a

serviceable engine.

(2) A shop level ECI for cracks in the

HPC stage 2–6 spool stage 3–4 and stage

4–5 interstage seal teeth, and, if

necessary, replacement with serviceable

parts.

Since this investigation is ongoing,

further rulemaking may be necessary.

The actions are required to be

accomplished in accordance with the

service documents 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–17–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:

98–15–03 General Electric Company:

Amendment 39–10654. Docket 98-ANE–

17–AD.

Applicability: General Electric Company

(GE) GE90–76B/ –77B/ –85B/ –90B/ –92B

series turbofan engines, with high pressure

compressor (HPC) stage 2–6 spools, Part

Numbers 350–005–761–0, 350–005–765–0,

350–005–769–0, 350–005–770–0, or 350–

005–771–0, installed. These engines are

installed on but not limited to Boeing 777

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 identify cracks in the high pressure

compressor (HPC) stage 2–6 spool, which

could result in an uncontained engine failure

and damage to the aircraft, accomplish the

following:

(a) Perform initial and repetitive on-wing

eddy current inspections (ECI) for cracks in

HPC stage 2–6 spool spacer arms in

accordance with GE Alert Service Bulletin

(ASB) No. 72–A357, Revision 2, dated April

21, 1998.

(1) Perform inspections of the spacer arm

forward and aft of the stage 3–4 and 4–5 seal

teeth as follows:

(i) Perform the initial inspection prior to

exceeding 500 cycles since new (CSN).

(ii) Thereafter, inspect at intervals not to

exceed 250 cycles in service (CIS) since last

inspection.

(2) Remove the engine from service if the

ECI reveals a spool with a crack indication

and replace with a serviceable engine prior

to further flight.

(b) Perform initial and repetitive ECI for

cracks in the HPC 2–6 spool stage 3–4 and
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