This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

6888

Vol. 62, No. 31

Friday, February 14, 1997

DEPARTMENT OF ENERGY

Office of Energy Efficiency and

Renewable Energy

10 CFR Part 431

[Docket No. EE–RM–96–400]

Energy Efficiency Program for Certain

Commercial and Industrial Equipment:

Test Procedures, Labeling, and

Certification Requirements for Electric

Motors

AGENCY: Office of Energy Efficiency and

Renewable Energy, Department of

Energy.

ACTION: Extension of public comment

period on proposed motor efficiency

regulations.

SUMMARY: On November 27, 1996 (61 FR

60440), the Department of Energy (DOE

or Department) proposed regulations to

implement the standards and test

procedures for commercial and

industrial electric motors established in

the Energy Policy and Conservation Act,

as amended (the Act or EPCA). In the

same notice of proposed rulemaking, the

Department also proposed to establish

efficiency labeling requirements and

compliance certification requirements

for motors, as directed by the Act.

On January 15, 1997, DOE held a

public hearing to receive oral comments

on the proposed rule. The transcript

from this hearing has been added to the

docket for this rulemaking, and is now

available for review in the Department

of Energy, Freedom of Information

Reading Room.

To ensure that the public has ample

opportunity to fully review and

comment on the proposed rulemaking

and the information that was presented

during the public hearing, today’s notice

extends the public comment period

from February 17 through March 10,

1997.

DATES: The Department will accept

written statements, comments, data, and

information regarding the proposed rule

for electric motors no later than March

10, 1997.

ADDRESSES: Written comments and

written statements (10 copies) should be

labeled ‘‘Electric Motor Rulemaking’’

(Docket No. EE–RM–96–400), and

submitted to: U.S. Department of

Energy, Office of Codes and Standards,

EE–43, 1000 Independence Avenue,

SW, Room 1J–018, Washington, DC

20585–0121. Telephone: (202) 586–

7574.

DOCKET: Supporting information used in

developing the proposed rule, a copy of

the transcript of the public hearing, and

other information received that is

pertinent to the rule, are contained in

Docket No. EE–RM–96–400. This Docket

is available for inspection and copying

at the Freedom of Information Reading

Room, U.S. Department of Energy,

Forrestal Building, Room 1E–190, 1000

Independence Avenue, SW,

Washington, DC 20585–0101, telephone

(202) 586–6020, between the hours of 9

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

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT:

James Raba, U.S. Department of Energy,

Office of Energy Efficiency and

Renewable Energy, Mail Station EE–43,

1000 Independence Avenue, SW,

Washington, DC 20585–0121, (202) 586–

8654.

Issued in Washington, DC, on February 10,

1997.

Christine A. Ervin,

Assistant Secretary, Energy Efficiency and

Renewable Energy.

[FR Doc. 97–3741 Filed 2–13–97; 8:45 am]

BILLING CODE 6450–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–168–AD]

RIN 2120–AA64

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 repetitive

detailed visual inspections to detect

cracks on frame 179 at the attachment

bracket for the door restraint cable, and

various follow-on actions. This proposal

also would require installation of new

doublers and stress pads on frame 179,

which would terminate the repetitive

inspections. This proposal is prompted

by reports of cracks in frame 179 of the

fuselage at the attachment bracket for

the door restraint cable on in-service

airplanes due to improper rigging of the

door restraint system. The actions

specified by the proposed AD are

intended to prevent such cracking,

which could result in structural failure

of the fuselage and consequent rapid

decompression of the pressurized

section of the fuselage.

DATES: Comments must be received by

March 27, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

168–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

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

written data, views, or arguments as

they may desire. Communications shall

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
Federal Register / Vol. 62, No. 31 / Friday, February 14, 1997 / Proposed Rules 6889

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 96–NM–168–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, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

96–NM–168–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, recently notified

the FAA that an unsafe condition may

exist on certain Jetstream Model 4101

airplanes. The CAA advises that it has

received reports of cracks in frame 179

of the fuselage at the attachment bracket

for the door restraint cable on these inservice airplanes. The existing design of

the door restraint cable will not

withstand continuous high loads that

are induced by improper rigging of the

door restraint system. Cracking in frame

179 of the fuselage, if not detected and

corrected, could result in structural

failure of the fuselage and consequent

rapid decompression of the pressurized

section of fuselage.

Explanation of Relevant Service

Information

Jetstream has issued Alert Service

Bulletin J41–A53–024, dated April 26,

1996, which describes procedures for

performing repetitive detailed visual

inspections to detect cracks on frame

179 at the attachment bracket for the

door restraint cable, and various followon actions. (These follow-on actions

include performing a test to verify

proper adjustment of the restraint cable,

and correcting any discrepancy.) For

cases where no cracks are detected

during inspection, the alert service

bulletin also describes procedures for

installation of new doublers and stress

pads on frame 179, which would

eliminate the need for repetitive

inspections. The CAA classified this

alert service bulletin as mandatory and

issued British airworthiness directive

004–04–96 in order to assure the

continued airworthiness of these

airplanes in the United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

repetitive detailed visual inspections to

detect cracks on frame 179 at the

attachment bracket for the door restraint

cable, and various follow-on actions.

The proposed AD also would require

installation of new doublers and stress

pads on frame 179, which would

constitute terminating action for the

repetitive inspection requirements. The

inspection, various follow-on actions,

and installation would be required to be

accomplished in accordance with the

alert service bulletin described

previously. If any crack is detected

during any visual inspection, the repair

would be required to be accomplished

in accordance with a method approved

by the FAA.

Cost Impact

The FAA estimates that 49 Jetstream

Model 4101 airplanes of U.S. registry

would be affected by this proposed AD.

The proposed inspection would take

approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

inspection proposed by this AD on U.S.

operators is estimated to be $5,880, or

$120 per airplane, per inspection cycle.

The proposed installation would take

approximately 8 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would be supplied by

the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of the installation proposed

by this AD on U.S. operators is

estimated to be $23,520, or $480 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

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.
6890 Federal Register / Vol. 62, No. 31 / Friday, February 14, 1997 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Jetstream Aircraft Limited: Docket 96–NM–

168–AD.

Applicability: Model 4101 airplanes,

constructors numbers 41004 through 41086

inclusive; 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) 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 cracking in frame 179 of the

fuselage, which could result in structural

failure of the fuselage and consequent rapid

decompression of the pressurized section of

the fuselage, accomplish the following:

(a) Prior to the accumulation of 3,000 total

flight cycles, or within 300 flight cycles after

the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection to detect cracks on frame 179 at

the attachment bracket for the door restraint

cable, in accordance with Part 1 of the

Accomplishment Instructions of Jetstream

Alert Service Bulletin J41–A53–024, dated

April 26, 1996.

(1) If no crack is detected, repeat the visual

inspection thereafter at intervals not to

exceed 1,000 flight cycles. After each

inspection, perform the actions specified in

paragraph (c) of this AD.

(2) If any crack is detected, prior to further

flight, repair it in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate. After repair, perform the actions

specified in paragraph (c) of this AD.

(b) Within 24 months after the effective

date of this AD, perform the visual inspection

specified in paragraph (a) of this AD in

accordance with Part 2 of the

Accomplishment Instructions of Jetstream

Alert Service Bulletin J41–A53–024, dated

April 26, 1996; and accomplish the

applicable follow-on actions specified in

paragraph (b)(1) or (b)(2) of this AD.

(1) If no crack is detected, prior to further

flight, install new doublers and stress pads

on frame 179 in accordance with the alert

service bulletin. Immediately after

installation, perform the actions specified in

paragraph (c) of this AD. Accomplishment of

these actions constitutes terminating action

for the repetitive inspection requirements of

paragraphs (a)(1) of this AD.

(2) If any crack is detected, prior to further

flight, repair it in accordance with a method

approved by the Manager, Standardization

Branch. Prior to further flight following

accomplishment of the repair, install new

doublers and stress pads on frame 179 in

accordance with the alert service bulletin;

and then perform the actions specified in

paragraph (c) of this AD. Accomplishment of

these actions constitutes terminating action

for the repetitive inspection requirements of

paragraphs (a)(1) of this AD.

(c) Prior to further flight following

accomplishment of the actions as specified in

paragraph (a)(1), (a)(2), (b)(1), or (b)(2) of this

AD, perform a test to verify proper

adjustment of the restraint cable, in

accordance with the alert service bulletin. If

the restraint cable has been improperly

adjusted, prior to further flight, correct the

discrepancy in accordance with the alert

service bulletin.

(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,

Standardization Branch. 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.

(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 February

5, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3691 Filed 2–13–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–62–AD]

RIN 2120–AA64

Airworthiness Directives; Industrie

Aeronautiche E Meccaniche Model

Piaggio P–180 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Industrie Aeronautiche E Meccaniche

(I.A.M.) Model Piaggio P–180 airplanes

that are equipped with a certain freon

air conditioning system. The proposed

action would require inspecting the

baggage compartment for stringer or air

cycle machine (ACM) by-pass duct

damage, repairing any damage found,

and modifying the freon air inlet duct

and electrical wiring. The proposed AD

results from trim system malfunction on

one of the affected airplanes, resulting

from contact between the freon air inlet

duct and the electrical wiring. The

actions specified by the proposed AD

are intended to prevent trim system

malfunction caused by contact between

the freon air inlet duct and electrical

wiring, which could result in loss of

control of the airplane.

DATES: Comments must be received on

or before April 25, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–62–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

I.A.M. Rinaldo Piaggio, S.p.A., Via

Cibrario, 4 16154, Genoa, Italy. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Maurice Kuttler, Program Manager,

Brussels Aircraft Certification Division,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone 32 2 508

2715; facsimile 32 2 230 6899; or Mr.

Roman T. Gabrys, Project Officer, Small

Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6932;

facsimile (816) 426–2169.

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