21642 Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Rules and Regulations

are made and air carriers have modified their

continuous airworthiness maintenance plans

to reflect the requirements in the engine

manuals.

(f) This amendment becomes effective on

October 23, 2000.

Issued in Burlington, Massachusetts, on

April 14, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–10159 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–39–AD; Amendment

39–11696; AD 2000–08–10]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company GE90 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain General Electric

Company GE90 series turbofan engines,

that currently requires revisions to the

Airworthiness Limitations Section

(ALS) of the manufacturer’s Instructions

for Continued Airworthiness (ICA) to

include required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure. This action

adds additional critical life-limited parts

for enhanced inspection. This

amendment is prompted by additional

focused inspection procedures for other

critical life-limited rotating engine parts

that have been developed by the

manufacturer. The actions specified by

this AD are intended to prevent critical

life-limited rotating engine part failure,

which could result in an uncontained

engine failure and damage to the

airplane.

DATES: Effective October 23, 2000.

ADDRESSES: The information referenced

in this AD may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Karen Curtis, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7134,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding (AD) 990817,

Amendment 3911123 (64 FR 17961),

that is applicable to General Electric

Company GE90 series turbofan engine

was published in the Federal Register

on October 7, 1999 (64 FR 54591). That

action proposed to require revisions to

the Airworthiness Limitations Section

of the manufacturer’s Instructions for

Continued Airworthiness (ICA) for

General Electric Company (GE) GE90

series turbofan engines to include

required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure.

New Inspection Procedures

Since the issuance of that AD,

additional focused inspection

procedures for other critical life-limited

rotating engine parts have been

developed by GE. This AD will require

modification of the airworthiness

limitations section in the manufacturers

manual and an air carrier’s approved

continuous airworthiness maintenance

program to incorporate these inspection

procedures.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the five

comments received.

‘‘Unsafe Condition’’

One commenter objects to the

language in the preamble of the NPRM

supersedure for the second phase of

enhanced inspections which includes a

finding of an ‘‘unsafe condition.’’ The

commenter asks that the term ‘‘unsafe

condition’’ be deleted and replaced with

the justification language from the

original NPRM. The FAA does not

agree. The commenter does not disagree

with the proposed rule itself but rather

with the term ‘‘unsafe condition’’ that is

contained in the preamble to the NPRM.

It is not the intent of the FAA to

completely change the enhanced disk

inspection program established by the

current AD, which evolved as a

cooperative effort between the FAA and

industry. This intervention strategy was

designed to reduce the number of

uncontained engine failures by

mandating enhanced nondestructive

inspections of critical rotating

components that could most likely

result in a hazard to the airplane in the

event of a failure. Since the engine

maintenance manuals did not mandate

these enhanced inspections, the current

AD was necessary to establish the

inspection program as an airworthiness

limitation. Regardless of the fact that it

was not stated explicitly in the original

NPRM, the FAA determined that an

‘‘unsafe condition’’ existed because the

engine maintenance manuals did not

contain enhanced inspections as an

airworthiness limitation. There was no

intent to imply any defect in the actual

engine hardware, but simply to state

that the maintenance manuals, that form

part of the approved engine design,

must be revised to mandate the

enhanced inspections. The supersedure

repeats that finding with respect to the

additional parts being added to the

enhanced inspection program. Because

a finding of an ‘‘unsafe condition’’ is

required for the FAA to issue an AD,

future NPRM’s adding parts to the

program will also include that finding.

‘‘Life Limits’’ vs. ‘‘Airworthiness

Limitations’’ Sections

One commenter recommends

replacing references to the ‘‘Life Limits’’

section with references to the

‘‘Airworthiness Limitations’’ section

because Chapter 5 now contains two

subsets, 05–11 for Life Limits, and 05–

21 for the mandatory inspection. The

FAA agrees. The Final Rule references

the ‘‘Airworthiness Limitations’’ section

instead of the ‘‘Life Limits’’ section.

Task Numbers and Inspection

Descriptions

One commenter recommends that 2nd

level task numbers and inspection

descriptions be used instead of the

subtask numbers to ensure that all

appropriate preparatory steps (e.g.

cleaning) are included in the mandatory

inspection. The FAA agrees. The Final

Rule has been revised accordingly to

ensure that all appropriate preparatory

steps (e.g. cleaning) are included in the

mandatory inspection.

Effectivity Date

Two commenters request that the

AD’s effectivity date be set to allow

sufficient time for publication of the

procedures, equipment procurement

and training necessary to perform the

mandatory inspection. The FAA agrees.

The effectivity date for the Final rule

has been extended to 180 days after

publication to allow sufficient time for

the publication of the inspection

procedures and for operators to prepare.

Removal of ‘‘of This Chapter’’ From

Paragraph (e) of the Compliance

Section

The statement ‘‘of this chapter’’ has

been removed from the first sentence of

paragraph (e) to improve the clarity of

the paragraph.

Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Rules and Regulations 21643

Economic Analysis

No comments were received on the

economic analysis contained in the

proposed rules. The FAA has

determined that the annual cost of

complying with this AD does not create

a significant economic impact on small

entities.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it does

not have a substantial direct effect 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. Accordingly, the

FAA has not consulted with state

authorities prior to publication of this

final rule.

For the reasons discussed above, I

certify that this action: (1) Is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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, 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 39–11123 (64 FR

17961, April 13, 1999), and by adding

a new airworthiness directive,

Amendment 39–11696 to read as

follows:

AD 2000–08–10 General Electric Company:

Amendment 39–11696. Docket No. 98–

ANE–39–AD. Supersedes AD 99–08–17,

Amendment 39–11123.

Applicability: General Electric Company

(GE) GE90–76B/ –77B/ –85B/ –90B/ –92B

series turbofan engines, installed on but not

limited to Boeing 777 series airplanes.

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 (c)

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 critical life-limited rotating

engine part failure, which could result in an

uncontained engine failure and damage to

the airplane, accomplish the following:

Inspections

(a) Within the next 30 days after the

effective date of this AD, revise the

manufacturer’s Airworthiness Limitations

Section of the Instructions for Continued

Airworthiness (ICA), and for air carrier

operations revise the approved continuous

airworthiness maintenance program, by

adding the following:

‘‘MANDATORY INSPECTIONS

(1) Perform inspections of the following

parts at each piece-part opportunity in

accordance with the instructions provided in

the applicable manual provisions:

Part nomenclature Part No.

(P/N) Inspect per engine manual chapter

For GE90 Engines:

HPCR, Disk, Stage 7 ........................................................... All ................. 72–31–07–200–001–001 Fluorescent Penetrant Inspection,

and 72–31–07–200–001–001 Eddy Current Inspection of the

Rim Boltholes.

HPTR, Interstage Seal ......................................................... All ................. 72–53–03–200–001–001 Fluorescent Penetrant Inspection,

and 72–53–03–200–001–001 Eddy Current Inspection of the

Bore.

Fan Disk, Stage 1 ................................................................ All ................. 72–21–03–200–001–001 Fluorescent Penetrant Inspection,

and 72–21–03–200–001–001 Eddy Current Inspection of the

Bore, and 72–21–03–200–001–001 Ultrasonic Inspection of

Dovetail Slots.

HPTR Disk, Stage 1 ............................................................. All ................. 72–53–02–200–001–002 Fluorescent Penetrant Inspection,

and 72–53–02–200–001–002 Eddy Current Inspection of the

Bore.

HPTR Disk, Stage 2 ............................................................. All ................. 72–53–04–200–001–004 Fluorescent Penetrant Inspection,

and 72–53–04–200–001–004 Eddy Current Inspection of the

Bore.

HPCR Disk, Stage 1 ............................................................ All ................. 72–31–05–200–001–001 Fluorescent Penetrant Inspection,

and 72–31–05–200–001–001 Eddy Current Inspection of the

Bore, and 72–31–05–200–001–001 Eddy Current Inspection

of the Dovetail Slots.

HPCR Spool, Stage 2–6 ...................................................... All ................. 72–31–06–200–001–001 Fluorescent Penetrant Inspection,

and 72–31–06–200–001–001 Eddy Current Inspection of the

S2 Dovetail Slots.

HPCR Seal, Compressor Discharge Pressure .................... All ................. 72–31–09–200–001–001 Fluorescent Penetrant Inspection,

and 72–31–09–200–001–001 Eddy Current Inspection of the

Boltholes.

21644 Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Rules and Regulations

(2) For the purposes of these mandatory

inspections, piece-part opportunity means:

(i) The part is considered completely

disassembled when accomplished in

accordance with the disassembly instructions

in the manufacturer’s engine manual; and

(ii) The part has accumulated more than

100 cycles in service since the last piece-part

opportunity inspection, provided that the

part was not damaged or related to the cause

for its removal from the engine.’’

(b) Except as provided in paragraph (c) of

this AD, and notwithstanding contrary

provisions in section 43.16 of the Federal

Aviation Regulations (14 CFR 43.16), these

mandatory inspections shall be performed

only in accordance with the Airworthiness

Limitations Section of the manufacturer’s

ICA.

Alternative Methods of Compliance

(c) 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 Engine Certification

Office (ECO). Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector (PMI), who

may add comments and then send it to the

ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Ferry Flights

(d) 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.

Continuous Airworthiness Maintenance

Program

(e) FAA-certificated air carriers that have

an approved continuous airworthiness

maintenance program in accordance with the

record keeping requirement of § 121.369(c) of

the Federal Aviation Regulations (14 CFR

121.369 (c)) must maintain records of the

mandatory inspections that result from

revising the Airworthiness Limitations

Section of the Instructions for Continuous

Airworthiness (ICA) and the air carrier’s

continuous airworthiness program.

Alternately, certificated air carriers may

establish an approved system of record

retention that provides a method for

preservation and retrieval of the maintenance

records that include the inspections resulting

from this AD, and include the policy and

procedures for implementing this alternate

method in the air carrier’s maintenance

manual required by § 121.369(c) of the

Federal Aviation Regulations (14 CFR

121.369(c)); however, the alternate system

must be accepted by the appropriate PMI and

require the maintenance records be

maintained either indefinitely or until the

work is repeated. Records of the piece-part

inspections are not required under

§ 121.380(a)(2)(vi) of the Federal Aviation

Regulations (14 CFR 121.380(a)(2)(vi)). All

other Operators must maintain the records of

mandatory inspections required by the

applicable regulations governing their

operations.

Note 3: The requirements of this AD have

been met when the engine manual changes

are made and air carriers have modified their

continuous airworthiness maintenance plans

to reflect the requirements in the engine

manuals.

(f) This amendment becomes effective on

October 23, 2000.

Issued in Burlington, Massachusetts, on

April 14, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–10157 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 99–AAL–18]

Revision of Class E Airspace;

Unalaska, AK

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action revises Class E

airspace at Unalaska, AK. The

establishment of a Global Positioning

System (GPS) instrument approach

procedure at Unalaska Airport made

this action necessary. This rule provides

adequate controlled airspace for aircraft

flying IFR procedures at Unalaska, AK.

EFFECTIVE DATE: 0901 UTC, June 15,

2000.

FOR FURTHER INFORMATION CONTACT: Bob

Durand, Operations Branch, Federal

Aviation Administration, 222 West 7th

Avenue, Box 14, Anchorage, AK 99513–

7587; telephone number (907) 271–

5898; fax: (907) 271–2850; email:

Bob.Durand@faa.gov. Internet address:

http://www.alaska.faa.gov/at or at

address http://162.58.28.41/at.

SUPPLEMENTARY INFORMATION:

History

On November 19, 1999, a proposal to

amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to revise

the Class E airspace at Unalaska, AK,

was published in the Federal Register

(64 FR 63261). The proposal was

necessary due to the establishment of a

GPS instrument approach procedure at

Unalaska, AK. Interested parties were

invited to participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No public comments to the proposal

were received; thus, the rule is adopted

as written.

The area would be depicted on

aeronautical charts for pilot reference.

The coordinates for this airspace docket

are based on North American Datum 83.

The Class E airspace areas designated as

700/1200 foot transition areas are

published in paragraph 6005 in FAA

Order 7400.9G, Airspace Designations

and Reporting Points, dated September

1, 1999, and effective September 16,

1999, which is incorporated by

reference in 14 CFR 71.1. The Class E

airspace designations listed in this

document will be published

subsequently in the Order.

The Rule

This amendment to 14 CFR part 71

revises the Class E airspace at Unalaska,

AK, through the establishment of a GPS

instrument approach. The area will be

depicted on aeronautical charts for pilot

reference. The intended effect of this

rule is to provide controlled airspace for

IFR operations at Unalaska, AK.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore—(1) Is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034; February 26, 1979); and (3)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR part 71 as follows:

PART 71—DESIGNATION OF CLASS A,

CLASS B, CLASS C, CLASS D, AND

CLASS E AIRSPACE AREAS;

AIRWAYS; ROUTES; AND REPORTING

POINTS

1. The authority citation for 14 CFR

part 71 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40103, 40113,

40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389.