8930 Federal Register / Vol. 60, No. 32 / Thursday, February 16, 1995 / Rules and Regulations

Authority: 49 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13—[Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–03–04 British Aerospace Regional

Aircraft Limited (Formerly British

Aerospace Commercial Aircraft Limited,

Vickers-Armstrongs Aircraft Limited):

Amendment 39–9141. Docket 94–NM–

109–AD.

Applicability: All Model Viscount 744,

745D, and 810 airplanes, certificated in any

category.

Note 1: This AD applies to each airplane

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

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of nose wheel steering

capability due to failure of the pivot pin,

accomplish the following:

(a) Prior to the accumulation of 1,100

landings after the effective date of this AD,

or within 14 months after the effective date

of this AD, whichever occurs first, perform a

magnetic particle inspection to detect cracks

of the nose wheel steering actuators

connecting (pivot) pins, in accordance with

either Viscount Preliminary Technical Leaflet

(PTL) 334, Issue 2, dated July 8, 1992 (for

Model 744 and 745D series airplanes); or

Viscount PTL 205, Issue 2, dated July 8, 1992

(for Model 810 series airplanes); as

applicable. Repeat this inspection thereafter

at intervals not to exceed 1,100 landings or

14 months, whichever occurs first.

(b) If any crack is found in a pivot pin

during any inspection required by this AD,

replace the pivot pin in accordance with

either Preliminary Technical Leaflet (PTL)

334, Issue 2, dated July 8, 1992 (for Model

744 and 745D series airplanes), or Viscount

PTL 205, Issue 2, dated July 8, 1992 (for

Model 810 series airplanes). After

replacement, repeat the inspection required

by paragraph (a) of this AD at intervals not

to exceed 1,100 landings or within 14

months, whichever occurs first.

(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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

(e) The inspections and replacement shall

be done in accordance with Viscount PTL

334, Issue 2, dated July 8, 1992; or Viscount

PTL 205, Issue 2, dated July 8, 1992; as

applicable. 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 British Aerospace Regional Aircraft

Ltd., Engineering Support Manager, Military

Business Unit, Chadderton Works, Greengate,

Middleton, Manchester M24 1SA, England.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

March 20, 1995.

Issued in Renton, Washington, on February

3, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–3245 Filed 2–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–11; Amendment 39–

9138; AD 95–03–01]

Airworthiness Directives; General

Electric Company CF6 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to General Electric Company

(GE) CF6–45/–50/–80A series turbofan

engines, that currently requires a onetime ultrasonic and eddy current

inspection of the high pressure

compressor rotor (HPCR) stage 3–9

spool for cracks. This amendment

retains the inspection requirements of

the current AD, but would accelerate the

inspection schedule, and introduce a

repetitive inspection requirement. This

amendment is prompted by a review of

the inspection results to date, which

indicate that the crack occurrence rate is

higher than initially projected. The

actions specified by this AD are

intended to prevent an uncontained

HPCR stage 3–9 spool failure, which

could result in damage to the aircraft.

DATES: Effective March 20, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 20,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from General Electric Aircraft Engines,

CF6 Distribution Clerk, Room 132, 111

Merchant Street, Cincinnati, OH 45246.

This information may be examined at

the Federal Aviation Administration

(FAA), New England Region, Office of

the Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA

01803–5299; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Robert J. Ganley, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7138;

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding airworthiness directive

(AD) 91–20–01, Amendment 39–8035

(56 FR 55230), which is applicable to

General Electric Company (GE) CF6–45/

–50/–80A series turbofan engines, was

published in the Federal Register on

May 3, 1994 (59 FR 22769). That action

proposed to retain the one-time

ultrasonic and eddy current inspection

of the high pressure compressor rotor

(HPCR) stage 3–9 spool for cracks as

required in the current AD, but would

accelerate the inspection schedule, and

introduce a repetitive ultrasonic and

eddy current inspection requirement in

accordance with GE CF6–50 Service

Bulletin (SB) No. 72–1000, Revision 2,

dated September 9, 1993, and GE CF6–

80A SB No. 72–583, Revision 4, dated

September 15, 1993.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters support the rule as

proposed.

One commenter states that the

repetitive inspection interval of 3,500

cycles in service (CIS) in compliance

paragraph (b) of the proposed rule

should be replaced with 4,000 CIS in
Federal Register / Vol. 60, No. 32 / Thursday, February 16, 1995 / Rules and Regulations 8931

order to avoid premature engine

removals. The FAA concurs that this

change will avoid some engine removals

while not decreasing the level of safety

provided by the proposed rule.

Accordingly, the FAA has made this

change in the final rule.

Although no comments were received

regarding compliance paragraphs (a)(3),

(a)(4), (c)(2), and (d), the FAA has

replaced 3,500 CIS with 4,000 CIS in

these paragraphs to maintain

consistency.

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.

There are approximately 462 GE CF6–

45/–50/–80A series engines of the

affected design in the worldwide fleet.

The FAA estimates that 67 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will take

approximately 584 work hours per

engine to accomplish the required

actions, and that the average labor rate

is $55 per work hour. Required parts

will cost approximately $127,412 per

engine. Based on these figures, and

assuming that 3 of the inspected spools

will require replacement, the total cost

impact of the AD on U.S. operators is

estimated to be $2,534,276.

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.

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, 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [AMENDED]

2. Section 39.13 is amended by

removing Amendment 39–8035 (56 FR

55230; October 25, 1991) and by adding

a new airworthiness directive to read as

follows:

95–03–01 General Electric Company:

Amendment 39–9138. Docket 94–ANE–

11. Supersedes AD 91–20–01,

Amendment 39–8035.

Applicability: General Electric Company

(GE) CF6–45/–50/–80A series turbofan

engines installed on, but not limited to,

Airbus A300 and A310 series, Boeing 747

and 767 series, and McDonnell Douglas DC–

10 series aircraft.

Compliance: Required as indicated, unless

accomplished previously.

To prevent an uncontained high pressure

compressor rotor (HPCR) stage 3–9 spool

failure, which could result in damage to the

aircraft, accomplish the following:

(a) Eddy current and ultrasonic inspect GE

CF6–45/-50 HPCR stage 3–9 spools, Part

Number (P/N) 9136M89G02, 9136M89G03,

9136M89G06, 9136M89G08, 9253M85G01,

9253M85G02, 9273M14G01, and

9331M29G01, with serial numbers (S/N)

listed in Table 2 of GE CF6–50 Service

Bulletin (SB) No. 72–1000, Revision 2, dated

September 9, 1993, as follows:

(1) For spools that have not been

previously inspected in accordance with GE

CF6–50 SB No. 72–888, Original, Revision 1,

Revision 2, Revision 3, or Revision 4, or GE

CF6–50 SB No. 72–1000, Original, Revision

1, or Revision 2, inspect in accordance with

paragraph 2.C of GE CF6–50 SB No. 72–1000,

Revision 2, dated September 9, 1993, at the

next engine shop visit, or by 30 days after the

effective date of this AD, whichever occurs

earlier.

(2) For spools that have been inspected in

accordance with GE CF6–50 SB No. 72–888,

Original, Revision 1, or Revision 2, inspect in

accordance with paragraph 2.D of GE CF6–

50 SB No. 72–1000, Revision 2, dated

September 9, 1993, at the next engine shop

visit, or by 30 days after the effective date of

this AD, whichever occurs earlier.

(3) For spools that have been inspected in

accordance with GE CF6–50 SB No. 72–888,

Original, Revision 1, or Revision 2, and GE

CF6–50 SB No. 72–1008, Original, inspect in

accordance with paragraph 2.D of GE CF6–

50 SB No. 72–1000, Revision 2, dated

September 9, 1993, at the next piece-part

exposure, or within 4,000 cycles in service

(CIS) since inspected in accordance with GE

CF6–50 SB No. 72–1008, Original, whichever

occurs earlier.

(4) For spools that have been inspected in

accordance with GE CF6–50 SB No. 72–888,

Revision 3, or Revision 4, or GE CF6–50 SB

No. 72–1000, Original, Revision 1, or

Revision 2, inspect in accordance with

paragraph 2.D of GE CF6–50 SB No. 72–1000,

Revision 2, dated September 9, 1993, at the

next piece-part exposure, or within 4,000 CIS

since inspected in accordance with, GE CF6–

50 SB No. 72–888, Revision 3, or Revision 4,

or GE CF6–50 SB No. 72–1000, Original,

Revision 1, or Revision 2, whichever occurs

earlier.

(b) Thereafter, for spools that have been

inspected in accordance with paragraph (a) of

this AD, reinspect in accordance with

paragraph 2.D of GE CF6–50 SB No. 72–1000,

Revision 2, dated September 9, 1993, at

intervals not to exceed 4,000 CIS since the

last inspection.

(c) Eddy current and ultrasonic inspect GE

CF6–80A HPCR 3–9 spool, P/N 9136M89G10,

with S/N’s listed in Table 2 of GE CF6–80A

SB No. 72–583, Revision 4, dated September

15, 1993, as follows:

(1) For spools that have not been

previously inspected in accordance with GE

CF6–80A SB No. 72–500, Original, Revision

1, Revision 2, Revision 3, or Revision 4, or

GE CF6–80A SB No. 72–583, Original,

Revision 1, Revision 2, Revision 3, or

Revision 4, inspect in accordance with

paragraph 2.C of GE CF6–80A SB No. 72–

583, Revision 4, dated September 15, 1993,

at the next engine shop visit, or by 30 days

after the effective date of this AD, whichever

occurs earlier.

(2) For spools that have been previously

inspected in accordance with GE CF6–80A

SB No. 72–500, Revision 3, or Revision 4, or

GE CF6–80A SB No. 72–583, Original,

Revision 1, Revision 2, Revision 3, or

Revision 4, inspect in accordance with

paragraph 2.D of GE CF6–80A SB No. 72–

583, Revision 4, dated September 15, 1993,

at the next piece-part exposure, or within

4,000 CIS since inspected in accordance with

GE CF6–80A SB No. 72–500, Revision 3, or

Revision 4, or GE CF6–80A SB No. 72–583,

Original, Revision 1, Revision 2, Revision 3,

or Revision 4, whichever occurs earlier.

(d) Thereafter, for spools that have been

inspected in accordance with paragraph (c) of

this AD, reinspect in accordance with

paragraph 2.D of GE CF6–80A SB No. 72–

583, Revision 4, dated September 15, 1993,

at intervals not to exceed 4,000 CIS since the

last inspection.

(e) Remove from service prior to further

flight HPCR stage 3–9 spools that meet or

exceed the reject criteria established in

Section 2.C and 2.D, as applicable, of GE

CF6–50 SB No. 72–1000, Revision 2, dated

September 9, 1993, and GE CF6–80A SB No.

72–583, Revision 4, dated September 15,

1993, as appropriate.

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

shop visit is defined as the induction of an
8932 Federal Register / Vol. 60, No. 32 / Thursday, February 16, 1995 / Rules and Regulations

engine into a shop for maintenance involving

the separation of any major flange.

(g) For the purpose of this AD, piece-part

exposure is defined as disassembly and

removal of the stage 3–9 spool from the

HPCR rotor.

(h) 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. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative method of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(i) 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.

(j) The actions required by this AD shall be

done in accordance with the following

service bulletins:

Document No. Pages Revision Date

GE CF6–50, SB No. 72–1000 .................................................................................................................... 1–37 2 Sept. 9, 1993.

Total pages: 37.

GE CF6–80A SB No. 72–583 .................................................................................................................... 1–34 4 Sept. 15, 1993.

Total pages: 34.

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 Aircraft Engines, CF6

Distribution Clerk, Room 132, 111 Merchant

Street, Cincinnati, OH 45246. Copies may be

inspected at the FAA, New England Region,

Office of the Assistant Chief 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.

(k) This amendment becomes effective on

March 20, 1995.

Issued in Burlington, Massachusetts, on

January 31, 1995.

Donald F. Perrault,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–3248 Filed 2–15–95; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF THE TREASURY

Internal Revenue Service

26 CFR Part 1

[TD 8580]

RIN 1545–AN06

Disposition of an Interest in a Nuclear

Power Plant; Correction

AGENCY: Internal Revenue Service (IRS),

Treasury.

ACTION: Correction to final regulations.

SUMMARY: This document contains

corrections to the final regulations (TD

8580), which was published in the

Federal Register for Tuesday, December

27, 1994 (59 FR 66471). The final

regulation relates to certain Federal

income tax consequences of a

disposition of an interest in a nuclear

power plant by a taxpayer that has

maintained a nuclear decommissioning

fund with respect to that plant.

EFFECTIVE DATE: December 27, 1994.

FOR FURTHER INFORMATION CONTACT:

Peter C. Friedman, (202) 622–3110 (not

a toll-free number).

SUPPLEMENTARY INFORMATION:

Background

The final regulations that are the

subject of these corrections are under

section 468A of the Internal Revenue

Code.

Need for Correction

As published, TD 8580 contains errors

which may prove to be misleading and

are in need of clarification.

Correction of Publication

Accordingly, the publication of final

regulations (TD 8580), which were the

subject of FR Doc. 94–31428, is

corrected as follows:

§ 1.468A–3 [Corrected]

1. On page 66474, column 1,

preceding § 1.468A–3, in instructional

‘‘Par. 4.’’, paragraph 2a is added

immediately following the text of

paragraph 2 to read as follows:

2a. In newly designated paragraph

(h)(1)(vi), the reference ‘‘paragraph

(h)(1)(viii)’’ is removed and ‘‘paragraph

(h)(1)(vii)’’ is added in its place.

§ 1.468A–5 [Corrected]

2. On page 66474, column 2,

preceding § 1.468A–5, in instructional

‘‘Par. 5.’’, paragraph 3a is added

immediately following the text of

paragraph 3 to read as follows:

3a. In newly designated paragraph

(b)(2)(vii) introductory text, the

reference ‘‘paragraph (b)(2)(vi)’’ is

removed from the last sentence and

‘‘paragraph (b)(2)(vii)’’ is added in its

place.

Dale D. Goode,

Federal Register Liaison Officer, Assistant

Chief Counsel (Corporate).

[FR Doc. 95–3770 Filed 2–15–95; 8:45 am]

BILLING CODE 4830–01–U

DEPARTMENT OF JUSTICE

Office of the Attorney General

28 CFR Part 0

[AG Order No. 1948–95]

Establishment of the Office of

Community Oriented Policing Services

AGENCY: Department of Justice.

ACTION: Interim rule with request for

comments.

SUMMARY: This order will amend the

Department of Justice organization

regulations to reflect the creation of the

Office of Community Oriented Policing

Services. This new office will

implement certain grant programs

authorized by the Violent Crime Control

and Law Enforcement Act of 1994. This

order will provide the public with a list

of the duties of the Director of the Office

of Community Oriented Policing

Services, and will amend the Code of

Federal Regulations in order to reflect

accurately the Department’s internal

management structure. Finally, this

order makes applicable to the Office of

Community Oriented Policing Services

certain parts of the Code of Federal

Regulations currently applicable only to

the Office of Justice Programs.

DATES: Interim rule effective February

16, 1995, comments must be received on

or before April 3, 1995.

ADDRESSES: Comments may be mailed to

the Office of the General Counsel, Office

of Community Oriented Policing

Services, U.S. Department of Justice,

P.O. Box 14440, Washington, DC 20044,

or delivered to Suite 300, 633 Indiana

Avenue, N.W., Washington, DC between

9 a.m. and 5:30 p.m. Comments received

may also be inspected at Suite 300

between 9:15 a.m. and 5:15 p.m.

FOR FURTHER INFORMATION CONTACT:

L. Anthony Sutin, General Counsel,

Office of Community Oriented Policing