14348 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Proposed Rules

TABLE 1.—P/N’S OF AFFECTED RIGID

TUBE FUEL MANIFOLDS

4–301–042–02 4–301–236–03

4–301–042–04 4–301–236–04

4–301–042–05 4–301–286–01

4–301–042–06 4–301–286–02

4–301–236–01 4–301–376–01

4–301–236–02

These engines are installed on, but not

limited to Aerospatiale AS350, Eurocopter

MBB–BK117 and HH–65A, Bell 222, Page

Thrush, Air Tractor AT–302, Piaggio P. 166–

DL3, Riley International R421, and Pacific

Aero 08–600 aircraft.

Note 1: This 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: Compliance with this AD is

required as specified below, unless already

done. To prevent engine fuel leakage due to

low-cycle fatigue (LCF) cracking of the rigid

tube fuel manifold, which could result in an

in-flight fire, do the following:

(a) Replace fuel manifolds that have

accumulated the following gas generator

rotor (Ng) cycles-since-new (CSN) on the

effective date of this AD or Ng cycles-inservice (CIS) on the effective date of this AD

since all tubes were replaced:

TABLE 2.—FUEL TUBE REPLACEMENT SCHEDULE

Ng CSN, or Ng CIS Since Total

Tube Replacement Replacement schedule

(1) 2,750 or less .......................... Before accumulating 3,000 total Ng cycles.

(2) More than 2,750 .................... Within 250 CIS after the effective date of this AD.

(3) Unknown ................................ (i) Within 2,000 CIS after the effective date of this AD, or

(ii) At the next engine removal, or

(iii) At the removal of the fuel manifold for cause, whichever is first.

New Life Limitation

(b) Do not install fuel manifolds with P/N’s

that are listed in Table 1 of this AD after the

effective date of this AD if they meet ANY

of the following conditions:

(1) The manifold has accumulated 3,000 or

more total Ng cycles; OR

(2) The manifold has had partial tube

replacements; OR

(3) The manifold has an unknown number

of Ng cycles.

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 Manager, Los

Angeles Aircraft Certification Office

(LAACO). Operators shall submit their

request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, LAACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the LAACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with §§ 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.

Issued in Burlington, Massachusetts, on

March 2, 2001.

David A. Downey,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–5737 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–05–AD]

RIN 2120–AA64

Airworthiness Directives; General

Electric Co. CF6–80C2 Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

General Electric Company (GE) CF6–

80C2 turbofan engines with certain stage

1 high pressure turbine (HPT) rotor

disks installed. This proposal would

require initial and repetitive inspections

of certain HPT rotor disks for cracks in

the bottom of the dovetail slot. This

proposed AD is prompted by a report of

an uncontained failure of an engine

during a high-power ground run for

maintenance. The actions specified by

this proposed AD are intended to detect

cracks in the bottoms of the dovetail

slots that could propagate to failure of

the disk and cause an uncontained

engine failure.

DATES: Comments must be received by

April 11, 2001.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2001–NE–05–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.

The service information referenced in

this AD may be obtained from General

Electric Company via Lockheed Martin

Technology Services, 10525 Chester

Road, Suite C, Cincinnati, Ohio 45215,

telephone (513) 672–8400, fax (513)

672–8422. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Proposed Rules 14349

12 New England Executive Park,

Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Ann

Mollica, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone: 781–238–7740, 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 action 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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NE–05–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRM’s

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. 2001–NE–05–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On September 22, 2000, a Boeing

767–2B7(ER), equipped with GE CF6–

80C2B2 model engines, experienced an

uncontained failure of the stage 1 HPT

rotor disk during a high-power ground

run for maintenance. The investigation

of the failure has indicated that the stage

1 HPT rotor disk separation was the

result of a crack that initiated in the aft

corner radius of the bottom of a dovetail

slot. The FFA had received two

additional reports of stage 1 HPT rotor

disks that were found to have cracks in

the aft corner radius of the bottom of the

dovetail slots. The cracks were found

during shop visits in 1996 and 1999. In

both cases, the cracks initiated from

handling type damage to the aft corner

radius of the bottoms of the dovetail

slots. The actions specified by this

proposed AD are intended to detect

cracks in the bottoms of the dovetail

slots that could propagate to failure of

the disk and cause an uncontained

engine failure.

Manufacturer’s Service Information

The FAA has reviewed and approved

the technical contents of GE alert

service bulletin (ASB) CF6–80C2 72–

A1026, dated January 17, 2001, that

describes procedures for fluorescent

penetrant, visual and eddy current

inspections of the bottoms of the

dovetail slots.

Differences Between the Manufacturer’s

Service Information and This AD

Although the GE ASB CF6–80C2 72–

A1026, dated January 17, 2001, only

requires a one-time inspection, the FAA

has determined that repetitive

inspections are required to achieve an

acceptable level of safety.

Determination of an Unsafe Condition

Since an unsafe condition has been

identified that is likely to exist or

develop on other GE CF6–80C2 engines

of the same type design, this AD is being

proposed to detect cracks in the bottoms

of the dovetail slots that could

propagate to failure of the disk and

cause an uncontained engine failure.

For stage 1 HPT rotor disks with greater

than 1,500 cycles-since-new (CSN), this

proposed AD would require an initial

inspection at the next shop visit before

accumulating 3,500 cycles-in-service

(CIS) after the effective date of this AD.

For disks with 1,500 CSN or fewer on

the effective date of this AD, this

proposed AD would require an initial

inspection at the next shop visit before

accumulating 5,000 CSN. This proposed

AD would also require repetitive

inspections at piece-part opportunity,

and if cracked, replacement with a

serviceable disk. The actions would be

done in accordance the service bulletin

described previously.

Economic Impact

There are approximately 2,954

engines of the affected design in the

worldwide fleet. The FAA estimates that

637 engines installed on aircraft of U.S.

registry would be affected by this

proposed AD. The FAA estimates that it

would take approximately 3 work hours

per engine to accomplish the proposed

actions, and the average labor rate is $60

per work hour. Required parts would

cost approximately $283,480 per engine.

The FAA also estimates that

approximately 191 engines per year will

have shop visits, and that of those 191

engines, approximately two disks per

year will have to be replaced. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $601,340 per year.

Regulatory Impact

This proposal does not have

federalism implications, as defined in

Executive Order 13132, because it

would 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 proposal. 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

adding the following new airworthiness

directive:

14350 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Proposed Rules

General Electric Co.: Docket 2001–NE–05–

AD.

Applicability: This airworthiness directive

(AD) is applicable to General Electric

Company (GE) CF6–80C2 series turbofan

engines with stage 1 high pressure turbine

(HPT) rotor disks, part numbers (P/N’s)

1531M84G02, 1531M84G06, 1531M84G08,

1531M84G10, 9392M23G10, 9392M23G12,

9392M23G21, and 1862M23G01 installed.

These engines are installed on, but not

limited to Airbus Industrie A300 and A310

series, Boeing 747 and 767 series, and

McDonnell Douglas MD–11 series airplanes.

Note 1: This 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 (f) of this AD. The

request should include an assessment of the

effect of the modification, alternation, 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: Compliance with this AD is

required as indicated below, unless already

done.

To detect cracks in the bottoms of the

dovetail slots that could propagate to failure

of the disk and cause an uncontained engine

failure, perform the following inspections:

(a) Inspect the stage 1 HPT rotor disk in

accordance with 3.A(1) through 3.C.(10)(i) of

the Accomplishment Instructions of GE alert

service bulletin (ASB) CF6–80C2 72–A1026,

dated January 17, 2001, and Table 1 of this

AD, and replace if necessary, as follows:

TABLE 1.—COMPLIANCE TIMES FOR STAGE 1 HPT DISK INSPECTIONS

Stage 1 HPT rotor disk cycles-since-new (CSN)

on the effective date of this AD Initial inspection Repetitive inspection

(1) 1,500 CSN or fewer ..................................... At the next engine shop visit (ESV) after the

effective date of this AD, but not to exceed

5,000 CSN.

At each piece-part exposure.

(2) More than 1,500 CSN .................................. At the next ESV after the effective date of this

AD, but not to exceed 3,500 cycles-in-service (CIS) after the effective date of this AD.

At each piece-part exposure.

(3) Any number of CSN if the disk has been inspected using CF6–80C2 72–A1024, dated

October 13, 2000, before the effective date

of this AD.

At the next ESV after the effective date of this

AD.

At each piece-part exposure.

(b) After the effective date of this AD, do

not install any stage 1 HPT rotor disk with

greater than zero CSN until it has been

inspected in accordance with 3.A.(1) through

3.C.(10)(i) of the Accomplishment

Instructions of GE ASB CF6–80C2 72–A1026,

dated January 17, 2001.

(c) Thereafter, inspect the disk at each

piece-part exposure, and replace if necessary.

Definitions

(d) The following definitions apply for this

AD:

(1) Piece-part exposure means the stage 1

HPT rotor disk is considered completely

disassembled as follows:

(i) When done in accordance with the

disassembly instructions in the engine

manufacturer’s Engine Manual, AND

(ii) the disk has accumulated more than

100 CIS since the last piece-part opportunity

inspection, if the disk was not damaged or

related to the cause for its removal from the

engine.

(2) An ESV is defined as the induction of

an engine into a shop where the separation

of a major engine flange will occur after the

effective date of this AD. The following

actions, either separately or in combination,

are not considered ESV’s for the purpose of

this AD.

(i) Induction of an engine into a shop

solely for removal of the upper compressor

stator case for airfoil maintenance.

(ii) Induction of an engine into a shop

solely for the module level inspection of the

high pressure compressor rotor 3–9 spool.

Reporting Requirements

(e) Report the following information on all

disks that equal or exceed the reject criteria

of GE ASB CF6–80C2 72–A1026, within 5

calendar days of the inspection, to the

Manager, Engine Certification Office.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(1) Engine model in which the stage 1 HPT

rotor disk was installed, AND

(2) Disk P/N, AND

(3) Disk serial number, AND

(4) CSN on the disk, AND

(5) Cycles-since-last-inspection, AND

(6) Date and location of the inspection

Alternative Methods of Compliance

(f) 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 (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, 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.

Special Flight Permits

(g) Special flight permits may be issued in

accordance with §§ 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.

Issued in Burlington, Massachusetts, on

February 27, 2001.

David A. Downey,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–5496 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF THE TREASURY

Internal Revenue Service

26 CFR Part 1

[REG–116050–99]

RIN 1545–AX65

Stock Transfer Rules: Carryover of

Earnings and Taxes; Correction

AGENCY: Internal Revenue Service (IRS),

Treasury.

ACTION: Correction to notice of proposed

rulemaking and notice of public

hearing.

SUMMARY: This document contains

corrections to a notice of proposed

rulemaking and notice of public hearing

that was published in the Federal

Register on Wednesday, November 15,

2000 (65 FR 69138), relating to the

carryover of certain tax attributes, such

as earnings and profits and foreign

income tax accounts, when two