12414 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

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 the failure of the main fitting,

which could lead to collapse of the nose land

gear (NLG) during landing, accomplish the

following:

(a) For airplanes on which NLG part

number 200876001 or 200876003 has been

installed:

(1) Prior to the accumulation of 4,000 total

landings or within 30 days after the effective

date of this AD, whichever occurs later,

conduct an eddy current or ultra high

sensitivity penetrant inspection of the NLG,

in accordance with British Aerospace Service

Bulletin S.B. 32–131, Revision 2, dated July

10, 1993. Repeat the inspection thereafter at

intervals not to exceed 4,000 landings.

(2) If cracking is detected during any

inspection required by this paragraph, prior

to further flight, replace the currently

installed NLG with a new or serviceable unit,

or repair the crack, in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. After

replacement or repair, repeat the inspection

at intervals not to exceed 4,000 landings.

(b) For airplanes on which NLG part

number 200876002, 200876004, or

201138002 has been installed:

(1) Prior to the accumulation of 16,000

total landings or within 30 days after the

effective date of this AD, whichever occurs

later, conduct an eddy current or ultra

sensitivity penetrant inspection of the NLG,

in accordance with British Aerospace Service

Bulletin S.B. 32–131, Revision 2, dated July

10, 1993. Repeat the inspection thereafter at

intervals not to exceed 8,000 landings.

(2) If cracking is detected during any

inspection required by this paragraph, prior

to further flight, replace the currently

installed NLG with a new or serviceable unit,

or repair the crack, in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. After

replacement or repair, repeat the inspection

at intervals not to exceed 8,000 landings.

(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 shall be done in

accordance with British Aerospace Service

Bulletin S.B. 32–131, Revision 2, dated July

10, 1993, which contains the following

effective pages:

Page No.

Revision

level

shown on

page–

Date shown on

page

1 ................... 2 ............... July 10, 1993.

2–4– ............. 1 .............. Nov. 12, 1992.

Appendix A–

1 1–4.

Original– .. Dec. 6, 1991.

The replacement and repair shall be done in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate. 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 Holdings, Inc., Avro International

Aerospace Division, P.O. Box 16039, Dulles

International Airport, Washington DC 20041–

6039. 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

April 6, 1995.

Issued in Renton, Washington, on February

15, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4254 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 92–ANE–11; Amendment 39–

9151; AD 95–03–15]

Airworthiness Directives; Textron

Lycoming ALF502R Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Textron Lycoming

ALF502R series turbofan engines, that

reduces the service life for the No. 2

stage turbine disk, reduces the service

lives for No. 1 and No. 3 through No. 7

stage compressor rotor disks, and

requires a scheduled removal of these

disks from service. This amendment is

prompted by reports of cracks in disks

returned from the field and in disks

tested by the manufacturer. The actions

specified by this AD are intended to

prevent disk failure resulting in a

possible uncontained engine failure.

DATES: Effective on May 8, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 8,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Engines, 550 Main

Street, Stratford, CT 06497. 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; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Textron Lycoming

ALF502R series turbofan engines was

published in the Federal Register on

March 16, 1993 (58 FR 14185). That

action proposed to reduce the service

life for the No. 2 stage turbine disk,

reduce the service lives for No. 1 and

No. 3 through No. 7 stage compressor

rotor disks, and require a scheduled

removal of these disks from service in

accordance with Textron Lycoming

Service Bulletin (SB) ALF502R 72–281,

dated February 7, 1992.

The compliance section of this final

rule has been revised to specify the

reduced service lives for each affected

disk, to clarify that the reduced service

lives are the new life limits.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule with the changes described

previously.

On October 28, 1994, AlliedSignal

Inc. purchased the turbine engine

product line of Textron Lycoming, but

as of this date the anticipated name

change on the type certificate for the

ALF502R series engines has not

occurred.

There are approximately 700 Textron

Lycoming ALF502R series turbofan
Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12415

engines of the affected design in the

worldwide fleet. The FAA estimates that

200 engines installed on aircraft of U.S.

registry will be affected by this AD. The

required reduction in service life will

cost $41,400 per engine based on the

cost of a new disk prorated over the

reduced service life as compared to the

current service life. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$8,280,000.

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

adding the following new airworthiness

directive:

95–03–15 Textron Lycoming: Amendment

39–9151. Docket 92–ANE–11.

Applicability: Textron Lycoming ALF502R

series turbofan engines installed on but not

limited to British Aerospace BAe-146 aircraft.

Compliance: Required as indicated, unless

accomplished previously.

To prevent No. 2 stage turbine disk, and

No. 1 and No. 3 through No. 7 stage

compressor rotor disk, failure resulting in

possible uncontained engine failure,

accomplish the following:

(a) Remove from service No. 2 stage turbine

disks, P/Ns 2–121–058–18, 2–121–058–20,

and 2–121–058–R24, in accordance with the

schedule defined in paragraph B(1) of Table

1 of Textron Lycoming Service Bulletin (SB)

ALF502R 72–281, dated February 7, 1992,

and replace with a disk with cycle

accumulation no greater than the reduced

service life limit of 10,000 cycles.

(b) Remove from service No. 1 stage

compressor rotor disks, P/N 2–101–331–04,

in accordance with paragraph A(1) of Table

1 of Textron Lycoming SB No. ALF502R 72–

281, dated February 7, 1992, and replace

with a disk with cycle accumulation no

greater than the reduced service life limit of

12,500 cycles.

(c) Remove from service No. 3 stage

compressor rotor disks, P/Ns 2–101–263–02,

2–101–263–05, 2–101–263–06, 2–101–263–

09, and 2–101–263–R10, in accordance with

paragraph A(2) of Table 1 of Textron

Lycoming SB No. ALF502R 72–281, dated

February 7, 1992, and replace with a disk

with cycle accumulation no greater than the

reduced service life limit of 11,800 cycles.

(d) Remove from service No. 4 stage

compressor rotor disks, P/Ns 2–100–042–03,

2–100–042–07, 2–100–042–09, and 2–100–

042–R08, in accordance with paragraph A(3)

of Table 1 of Textron Lycoming SB No.

ALF502R 72–281, dated February 7, 1992,

and replace with a disk with cycle

accumulation no greater than the reduced

service life limit of 9,000 cycles.

(e) Remove from service No. 5 stage

compressor rotor disks, P/Ns 2–100–043–01,

2–100–043–07, 2–100–043–09, and 2–100–

043–R08, in accordance with paragraph A(4)

of Table 1 of Textron Lycoming SB No.

ALF502R 72–281, dated February 7, 1992,

and replace with a disk with cycle

accumulation no greater than the reduced

service life limit of 12,300 cycles.

(f) Remove from service No. 6 stage

compressor rotor disks, P/Ns 2–100–044–01,

2–100–044–05, 2–100–044–07, and 2–100–

044–R06, in accordance with paragraph A(5)

of Table 1 of Textron Lycoming SB No.

ALF502R 72–281, dated February 7, 1992,

and replace with a disk with cycle

accumulation no greater than the reduced

service life limit of 12,500 cycles.

(g) Remove from service No. 7 stage

compressor rotor disks, P/Ns 2–100–045–01,

2–100–045–05, 2–100–045–07, and 2–100–

045–R06, in accordance with paragraph A(6)

of Table 1 of Textron Lycoming SB No.

ALF502R 72–281, dated February 7, 1992,

and replace with a disk with cycle

accumulation no greater than the reduced

service life limit of 9,200 cycles.

(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 methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(i) The actions required by this AD shall be

done in accordance with the following

Textron Lycoming service bulletin:

Document No. Pages Date

ALF502R 72–281 1–5 Feb. 7, 1992.

Total pages .. 5

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 Textron Lycoming, 550 Main Street,

Stratford, CT 06497. 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.

(j) This amendment becomes effective on

May 8, 1995.

Issued in Burlington, Massachusetts, on

February 8, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–4125 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF THE TREASURY

Internal Revenue Service

26 CFR Part 1

[TD 8581]

RIN 1545–AQ87

Certain Cash or Deferred

Arrangements and Employee and

Matching Contributions Under

Employee Plans; Correction

AGENCY: Internal Revenue Service (IRS),

Treasury.

ACTION: Correction to final regulations.

SUMMARY: The final regulations (TD

8581), which are the subject of these

corrections were published in the

Federal Register for Friday, December

23, 1994 (59 FR 66165). The final

regulations govern certain cash or

deferred arrangements and employee

and matching contributions under

employee plans.

EFFECTIVE DATE: December 23, 1994.