54594 Federal Register / Vol. 64, No. 194 /Thursday, October 7, 1999 / Proposed Rules

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.

Issued in Burlington, Massachusetts, on

September 30, 1999.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 99–26211 Filed 10–6–99; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–49–AD]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF6–80A, CF6–80C2,

and CF6–80E1 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to General

Electric Company (GE) CF6–80A, CF6–

80C2, and CF6–80E1 series turbofan

engines, that currently requires

revisions to the Life Limits Section 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

would add additional disk bore eddy

current inspections (ECI) for the high

pressure turbine rotor (HPTR) Stage 1

and 2 disks for all affected engine

models, and would add fan forward

shaft inspections for the CF6–80C2

engine model only. This proposal is

prompted by additional focused

inspection procedures that have been

developed by the manufacturer. The

actions specified by this proposed AD

are intended to prevent critical lifelimited rotating engine part failure,

which could result in an uncontained

engine failure and damage to the

airplane.

DATES: Comments must be received by

December 6, 1999.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–ANE–49–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

sent via the Internet using the following

address: ‘‘9-ane-adcomment@faa.gov’’.

Comments sent via the Internet must

contain the docket number in the

subject line. Comments may be

inspected at this location between 8:00

a.m. and 4:30 p.m., Monday through

Friday, except Federal holidays.

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) 238–7192,

fax (781) 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 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 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 98–ANE–49–AD.’’ 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

Regional Counsel, Attention: Rules

Docket No. 98–ANE–49–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On April 2, 1999, the Federal

Aviation Administration (FAA) issued

airworthiness directive (AD) 99–08–13,

Amendment 39–11119 (64 FR 17951,

April 13, 1999), to require revisions to

the Life Limits Section of the

manufacturer’s Instructions for

Continued Airworthiness (ICA) for

General Electric Company (GE) CF6–

80A, CF6–80C2, and CF6–80E1 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, GE has

developed additional focused

inspection procedures. This proposal

would add disk bore eddy current

inspections (ECI) for the high pressure

turbine rotor (HPTR) Stage 1 and 2 disks

on all affected engine models, and

would add fan forward shaft inspections

for the CF6–80C2 engine model only.

Proposed Actions

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

supersede AD 99–08–13 to add disk

bore ECI for the HPTR Stage 1 and 2

disks on all affected engine models, and

to add fan forward shaft inspections for

the CF6–80C2 engine model only. The

inspections would be required at each

piece-part opportunity.

Economic Analysis

The FAA estimates that 700 engines

installed on airplanes of US registry

would be affected by this proposed AD,

that it would take approximately 4 work

hours per engine to accomplish the

proposed new disk bore ECI for the

HPTR Stage 1 and 2 disks on all affected

engine models, and that the average

labor rate is $60 per work hour. The

total cost of the new disk bore ECI for

the HPTR Stage 1 and 2 disks

inspections per engine would be

approximately $240. The FAA estimates

that approximately 83 HPTR Stage 1 and

2 disks would be exposed to the piecepart level per year; therefore, the total

annual cost for the added bore ECI is

estimated to be $19,920.

The FAA estimates that it would take

approximately 4 work hours per engine

to accomplish the proposed new fan

forward shaft inspections on the CF6–

80C2 engine model. The total cost of the

new fan forward shaft inspections per
Federal Register / Vol. 64, No. 194 /Thursday, October 7, 1999 / Proposed Rules 54595

engine would be approximately $240.

The FAA estimates that approximately

31 fan forward shafts would be exposed

to the piece-part level per year;

therefore, the total annual cost for the

added fan forward shaft inspections is

estimated to be $7,440.

Regulatory Impact

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

removing Amendment 39-11119 (64 FR

17951, April 13, 1999), and by adding

a new airworthiness directive, to read as

follows:

General Electric Company: Docket No. 98–

ANE–49–AD. Supersedes AD 99–08–13,

Amendment 39–11119.

Applicability: General Electric Company

(GE) CF6–80A, CF6–80C2, and CF6–80E1

series turbofan engines, installed on but not

limited to Airbus Industrie A300, A310, and

A330 series, Boeing 747 and 767 series, and

McDonnell Douglas MD–11 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 Life Limits 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

For CF6–80A Engines:

Disk, Fan Rotor, Stage 1 ................. All .......... 72–21–03 Paragraph 3. Fluorescent-Penetrant Inspect, and 72–21–03 Paragraph 4. Eddy

Current Inspect.

Disk, HPT Rotor, Stage One ........... All .......... 72–53–02 Paragraph 3. Fluorescent-Penetrant-Inspect Disk/Shaft per 70–32–02, and 72–

53–02 Paragraph 6. Eddy Current Inspection, and 72–53–02 Paragraph 7. Disk Bore

Area Eddy Current Inspection.

Disk, HPT Rotor, Stage Two ........... All .......... 72–53–06 Paragraph 3. Fluorescent-Penetrant Inspection, and 72–53–06 Paragraph 6.

Eddy Current Inspection of Rim Boltholes for Cracks, and 72–53–06 Paragraph 7. Disk

Bore Area Eddy Current Inspection.

For CF6–80C2 Engines:

Disk, Fan Rotor, Stage 1 ................. All .......... Task 72–21–03–200–000–004 Fluorescent-Penetrant Inspection, and Task 72–21–03–

200–000–008 Eddy Current Inspect Fan Rotor Disk Stage 1 Bore, Forward and Aft

Hub Faces, and Bore Radii.

Shaft, Fan Forward, ......................... All .......... Task 72–21–05–200–000–001 Fluorescent Penetrant Inspection, and Task 72–21–05–

200–000–005 Vent Hole Eddy Current Inspection.

Disk, HPT Rotor Stage One ............ All .......... Task 72–53–02–200–000–001 Fluorescent-Penetrant Inspect the HPT Rotor Stage 1

Disk/Shaft, and Task 72–53–02–200–000–005 Eddy Current Inspection, and Task 72–

53–02–200–000–006 Disk Bore Area Eddy Current Inspection.

Disk, HPT Rotor Stage Two ............ All .......... Task 72–53–06–200–000–002 Fluorescent-Penetrant Inspect the Stage 2 Disk, and Task

72–53–06–200–000–006 Eddy Current Inspection of the HPTR Stage 2 Rim Boltholes,

and Task 72–53–06–200–000–007 Disk Bore Area Eddy Current Inspection.

For CF6–80E1 Engines:

Disk, Fan Rotor, Stage One ............ All .......... Task 72–21–03–230–051 Fluorescent-Penetrant Inspection, and Task 72–21–03–250–

051 or 72-21–03–250–052 Eddy Current Inspection.

HPT Disk, Stage One ...................... All .......... Task 72–53–02–230–51 Fluorescent-Penetrant Inspection, and Task 72–53–02–200–

001–005 Eddy Current Inspection, and Task 72–53–02–200–001–006 Disk Bore Area

Eddy Current Inspection.

HPT Disk, Stage Two ...................... All .......... Task 72–53–06–230–051 Fluorescent-Penetrant Inspection, and Task 72–53–06–200–

001–006 Eddy Current Inspection of the HPTR Stage 2 Rim Boltholes, and Task 72–

53–06–200–001–007 Disk Bore Area Eddy Current Inspection.
54596 Federal Register / Vol. 64, No. 194 /Thursday, October 7, 1999 / Proposed Rules

(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 Life Limits

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)) of this chapter must maintain

records of the mandatory inspections that

result from revising the Life Limits 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.

Issued in Burlington, Massachusetts, on

September 30, 1999.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 99–26212 Filed 10–6–99; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–48–AD]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Pratt & Whitney JT8D series turbofan

engines, that currently requires

revisions to the Time Limits Section

(TLS) of the JT8D Turbofan Engine

Manuals to include required enhanced

inspection of selected critical lifelimited parts at each piece-part

exposure. This action would add

additional critical life-limited parts for

enhanced inspection. This proposal is

prompted by additional focused

inspection procedures that have been

developed by the manufacturer. The

actions specified by this proposed AD

are intended to prevent critical lifelimited rotating engine part failure,

which could result in an uncontained

engine failure and damage to the

airplane.

DATES: Comments must be received by

December 6, 1999.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–ANE–48–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

sent via the Internet using the following

address: ‘‘9–ane–adcomment@faa.gov’’.

Comments sent via the Internet must

contain the docket number in the

subject line. Comments may be

inspected at this location between 8:00

a.m. and 4:30 p.m., Monday through

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(781) 238–7175, fax (781) 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 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 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 98–ANE–48–AD.’’ 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

Regional Counsel, Attention: Rules

Docket No. 98–ANE–48–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On June 1, 1999, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 99–12–03,

Amendment 39–11187 (64 FR 30379,

June 8, 1999), to require revisions to the

Time Limits Section (TLS) of the Pratt

& Whitney (PW) JT8D–1, –1A, –1B, –7,

–7A, –7B, –9, –9A, –11, –15, –15A, –17,

–17A, –17R, and –17AR series Turbofan

Engine Manuals to include required

enhanced inspection of selected critical