Federal Register / Vol. 60, No. 242 / Monday, December 18, 1995 / Proposed Rules 65035

(c) If any finding of cracking is confirmed,

prior to further flight, accomplish paragraph

(c)(1), (c)(2), or (c)(3) of this AD.

(1) Repair the cracked area in accordance

with a method approved by the Manager,

Atlanta Aircraft Certification Office (ACO),

FAA, Small Airplane Directorate. Thereafter,

perform the repetitive inspections and

follow-on actions required by paragraph (b)

of this AD. Or

(2) Repair the rear spar upper and lower

caps between IWS 228 and 346 in accordance

with the Lockheed Model L–1011 Structural

Repair Manual. Thereafter, perform the

repetitive inspections and follow-on actions

required by paragraph (b) of this AD. Or

(3) Modify the rear spar upper and lower

caps between IWS 228 and 346 in accordance

with the Lockheed service bulletins listed

below, as applicable. Accomplishment of the

modification constitutes terminating action

for the requirements of this AD.

• Lockheed L–1011 Service Bulletin 093–

57–184, Revision 7, dated December 6, 1994,

as amended by Change Notification 093–57–

184, R7–CN1, dated August 22, 1995; or

• Lockheed L–1011 Service Bulletin 093–

57–196, Revision 6, dated December 6, 1994,

as amended by Change Notification 093–57–

196, R6–CN1, dated August 22, 1995; or

• Lockheed L–1011 Service Bulletin 093–

57–203, Revision 4, dated March 27, 1995.

Note 4: Accomplishment of the

modification specified in paragraph (c)(3) of

this AD prior to the effective date of this AD

in accordance with the following Lockheed

service bulletins, as applicable, is considered

to be in compliance with this paragraph:

• Lockheed L–1011 Service Bulletin 093–

57–184, Revision 6, dated October 28, 1991;

• Lockheed L–1011 Service Bulletin 093–

57–184, Revision 7, dated December 6, 1994;

• Lockheed L–1011 Service Bulletin 093–

57–196, Revision 5, dated October 28, 1991;

• Lockheed L–1011 Service Bulletin 093–

57–196, Revision 6, dated December 6, 1994;

• Lockheed L–1011 Service Bulletin 093–

57–203, Revision 3, dated October 28, 1991;

or

• Lockheed L–1011 Service Bulletin 093–

57–203, Revision 3, dated October 28, 1991,

as amended by Change Notification 093–57–

203, R3–CN1, dated June 22, 1992.

(d) 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, Atlanta

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(e) 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.

Issued in Renton, Washington, on

December 11, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30646 Filed 12–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–41]

Airworthiness Directives; General

Electric Company CF34 Series

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) CF34

series turbofan engines. This proposal

would reduce the allowable operating

cyclic life limit for affected high

pressure compressor (HPC) stage 1 rotor

disks. This proposal is prompted by an

updated stress and life analysis. The

actions specified by the proposed AD

are intended to prevent HPC stage 1

rotor disk rupture, engine failure, and

damage to the aircraft.

DATES: Comments must be received by

February 16, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–41, 12 New England Executive

Park, Burlington, MA 01803–5299.

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:

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:

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 in triplicate 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 95–ANE–41.’’ 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

Assistant Chief Counsel, Attention:

Rules Docket No. 95–ANE–41, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has reviewed and approved an

updated stress and life analysis for high

pressure compressor (HPC) stage 1 rotor

disks installed in General Electric

Company (GE) CF34 series turbofan

engines. Although the FAA has not

received any reports of cracked or failed

HPC stage 1 rotor disks, the stress and

life analysis was performed using new,

improved methodology. This analysis

revealed that the published cyclic life

limits were higher than updated

calculated lives, which could result in

the operation of an HPC stage 1 rotor

disk beyond its cyclic life. This

condition, if not corrected, could result

in HPC stage 1 rotor disk rupture,

engine failure, and damage to the

aircraft.

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

reduce the allowable operating cyclic

life limit for affected HPC stage 1 rotor

disks.

There are approximately 440 engines

of the affected design in the worldwide

fleet. The FAA estimates that 150

engines installed on aircraft of U.S.

registry would be affected by this
65036 Federal Register / Vol. 60, No. 242 / Monday, December 18, 1995 / Proposed Rules

proposed AD, that it would take zero

additional work hours per engine to

accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Required parts would cost

approximately $7,667 per engine, based

on the estimated current part cost,

prorated downward by a factor equal to

the quotient of the difference between

the original cyclic life limit (9000

cycles) and the revised cyclic life limit

(6000 cycles) divided by the original

cyclic life limit. Based on these figures,

the total cost impact of the proposed AD

on U.S. operators is estimated to be

$1,150,000.

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), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

General Electric Company: Docket No. 95–

ANE–41.

Applicability: General Electric Company

(GE) Models CF34–1A, –3A, and –3A2

turbofan engines, with high pressure

compressor (HPC) stage 1 rotor disks, part

number 6040T79G01, installed. These

engines are installed on but not limited to

Canadair Limited Model CL–600–2A12 and

CL–600–2B16 aircraft.

Note: 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

use the authority provided in paragraph (b)

to request approval from the Federal Aviation

Administration (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 engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent HPC stage 1 rotor disk rupture,

engine failure, and damage to the aircraft,

accomplish the following:

(a) Remove from service HPC stage 1 rotor

disks prior to accumulating 6,000 cycles in

service since new, and replace with a

serviceable part.

(b) 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.

Issued in Burlington, Massachusetts, on

December 8, 1995.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 95–30645 Filed 12–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–128–AD]

Airworthiness Directives; Jetstream

Model 4101 Airplanes

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

certain Jetstream Model 4101 airplanes.

This proposal would require an

inspection to verify the proper position

of ‘‘door open’’ placards on the inside

of the main entrance door, and

replacement with new placards

appropriately positioned, if necessary.

This proposal is prompted by a report

that the ‘‘door open’’ placards on the

inside of the main entrance door, as

currently installed, may not be visible to

passengers or flightcrew when the door

handle is in the open position. The

actions specified by the proposed AD

are intended to ensure that certain

placards on the inside of the main

entrance door are clearly visible and

perform their intended function in the

event of an emergency evacuation.

DATES: Comments must be received by

January 23, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

128–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays.

The service information referenced in

the proposed rule may be obtained from

Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport,

Washington, DC 20041–6029. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such