Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules 7385

installed on the Aerospatiale Model

ATR42 series airplanes; therefore, both

of those models may be subject to this

same unsafe condition.

Explanation of Relevant Service

Information

Aerospatiale has released two

Aerospatiale Service Bulletins ATR42–

52–0072 and ATR72–52–1040, both

dated October 2, 1995, which describe

procedures for modifying the ‘‘down-toopen’’ configuration of the handle of the

passenger/crew door to an ‘‘up-to-open’’

configuration. If the airplane is flying

unpressurized, this modification will

prevent inadvertent opening of the door

in flight by a person leaning or falling

on the handle and, during an emergency

evacuation, will eliminate any

confusion concerning the direction in

which the handle moves to an open

position.

U.S. Type Certification of the Airplane

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement.

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

modification of the handle of the

passenger/crew door to change the

‘‘down-to-open’’ configuration to an

‘‘up-to-open’’ configuration. The actions

would be required to be accomplished

in accordance with the service bulletins

described previously.

Cost Impact

The FAA estimates that 16

Aerospatiale Model ATR42 and ATR72

series airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 15 work

hours per airplane to accomplish the

proposed actions, and that the average

labor rate is $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 proposed AD on U.S.

operators is estimated to be $14,400, or

$900 per airplane.

The cost impact figure discussed

above is 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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Aerospatiale: Docket 96–NM–141–AD.

Applicability: Model ATR42 and ATR72

series airplanes on which Aerospatiale

Modification 04019 has been accomplished,

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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 inadvertent opening of the

passenger/crew door during unpressurized

flight, or delays in opening the passenger/

crew door during an emergency evacuation;

accomplish the following:

(a) Within 6 months after the effective date

of this AD, modify the handle of the

passenger/crew door by changing its

configuration to an oup-to-openo

configuration in accordance with

Aerospatiale Service Bulletin ATR42–52–

0072 (for Model ATR42 series airplanes), or

ATR72–52–1040 (for Model ATR72 series

airplanes), both dated October 2, 1995.

(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,

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.

(c) 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

11, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3967 Filed 2–18–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–96–AD]

RIN 2120–AA64

Airworthiness Directives; Israel

Aircraft Industries (IAI), Ltd. Model

1125 Westwind Astra Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness
7386 Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules

directive (AD) that is applicable to

certain IAI Model 1125 Westwind Astra

series airplanes. This proposal would

require repetitive inspections to detect

loose or damaged rivets that fasten a

certain support beam to the frame of the

fuselage; and modification of the

attachment between the support beam

and fuselage by installation of

additional fasteners, if necessary. This

proposal also would require the

eventual accomplishment of this

modification on all airplanes, which

would terminate the repetitive

inspections. This proposal is prompted

by reports indicating that the

attachment between this beam and the

fuselage has become loose on several

airplanes. Movement of this beam could

restrict the movement of the elevator

and rudder controls cab that run

through the bellcranks attached to it.

The actions specified by the proposed

AD are intended to prevent movement

of this beam, which could restrict

movement of the elevator and rudder

controls, and consequently lead to

reduced controllability of the airplane.

DATES: Comments must be received by

March 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

96–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

Technical Publications, Astra Jet

Corporation, 77 McCullough Drive,

Suite 11, New Castle, Delaware 19720.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; 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

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–96–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–96–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Administration of

Israel (CAAI), which is the

airworthiness authority for Israel,

recently notified the FAA that an unsafe

condition may exist on certain IAI

Model 1125 Westwind Astra series

airplanes. The CAAI advises that it has

received reports indicating that rivets

fastening the support beam to the

fuselage frame at station 452.00 have

become loose on several Model 1125

Westwind Astra series airplanes. Should

these rivets loosen where the beam

attaches to the frame, the beam could

move. Because the elevator and rudder

controls run through bellcranks that are

connected to this beam, movement of

this beam could restrict the movement

of these controls. This condition, if not

corrected, could result in reduced

controllability of the airplane.

Explanation of Relevant Service

Information

Astra Jet has issued Service Bulletin

SB 1125–53–135, dated April 26, 1995,

which describes procedures for

repetitive visual inspections of the

rivets fastening the support beam to the

fuselage frame at station 452.00; these

inspections are to detect any rivet that

is loose or has been damaged by the

relative movement of the rivet against

the support beam (a ‘‘fretted rivet’’).

This service bulletin also describes

procedures for modifying the

attachment between the beam and the

fuselage by the installation of additional

fasteners that will strengthen this

attachment. Accomplishment of this

modification eliminates the need for

repetitive inspections. The CAAI

classified this service bulletin as

mandatory and issued Israeli

airworthiness directive 95–34, dated

May 18, 1995, in order to assure the

continued airworthiness of these

airplanes in Israel.

FAA’s Conclusions

This airplane model is manufactured

in Israel and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAAI has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAAI,

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 visual inspections to detect

loose or fretted rivets that fasten the

support beam to the fuselage frame at

station 452.00. Should any loose or

fretted rivet be detected, the proposed

AD would require modification of the

attachment between the beam and the

fuselage by the installation of additional

fasteners. Additionally, this proposed

AD would require that this modification

be installed eventually on all affected

airplanes. Accomplishment of this

modification also would terminate the

requirement for repetitive inspections.

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

Cost Impact

The FAA estimates that 58 IAI Model

1125 Westwind Astra series airplanes of

U.S. registry would be affected by this

proposed AD.

It would take approximately 1 work

hour per airplane to accomplish the

proposed visual inspection, and the

average labor rate is $60 per work hour.
Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules 7387

Based on these figures, the cost impact

of the proposed inspection on U.S.

operators is estimated to be $3,480, or

$60 per airplane, per inspection.

It would take approximately 8 work

hours per airplane to accomplish the

proposed terminating modification, and

the average labor rate is $60 per work

hour. The cost of parts is minimal.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be $27,840, 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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Israel Aircraft Industries (IAI), Ltd.: Docket

96–NM–96–AD.

Applicability: Model 1125 Westwind Astra

series airplanes as listed in IAI Service

Bulletin SB 1125–53–135, dated April 26,

1995; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (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: Required as indicated, unless

accomplished previously.

To prevent movement of the support beam

attached to the fuselage frame at station

452.00, which could restrict movement of the

elevator and rudder controls, and

consequently lead to reduced controllability

of the airplane, accomplish the following:

(a) Within 50 hours time-in-service after

the effective date of this AD, conduct a visual

inspection to detect loose or damaged

(‘‘fretted’’) rivets that fasten the support beam

to the fuselage frame at station 452.000, in

accordance with Part A of IAI Service

Bulletin SB 1125–53–135, dated April 26,

1995.

(1) If no loose or fretted rivet is detected,

repeat this inspection thereafter at intervals

not to exceed 250 hours time-in-service until

the modification required by paragraph (b) of

this AD is accomplished.

(2) If any loose or fretted rivet is detected,

prior to further flight, modify the support

beam in accordance with Part B of IAI

Service Bulletin SB 1125–53–135, dated

April 26, 1995. After this modification is

accomplished, no further action is required

by paragraphs (a) or (b) of this AD.

(b) Within 500 hours time-in-service after

the effective date of this AD, modify the

support beam in accordance with Part B of

IAI Service Bulletin SB 1125–53–135, dated

April 26, 1995. Accomplishment of this

modification constitutes terminating action

for the repetitive inspections required by

paragraph (a)(1) of this AD.

(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.

Issued in Renton, Washington, on February

11, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3969 Filed 2–18–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–ANE–38]

RIN 2120–AA64

Airworthiness Directives; General

Electric Aircraft Engines CF700 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 Aircraft Engines (GE)

CF700 series turbofan engines. This

proposal would require replacement of

existing fan guards with new, improved

fan guards. This proposal is prompted

by a report of uncontained fan blades

which separated from the engine during

an overspeed. The actions specified by

the proposed AD are intended to

prevent an overspeed of the aft fan disk

from resulting in an uncontained engine

failure and damage to the aircraft.

DATES: Comments must be received by

March 21, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96-ANE–38, 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.

The service information referenced in

the proposed rule may be obtained from

GE Aircraft Engines, 1000 Western Ave.,

Lynn, MA 01910; telephone (617) 594–

3140, fax (617) 594-4805. This

information may be examined at the