Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19675

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:

Empresa Brasileira De Aeronautica S.A.

(EMBRAER): Docket 98–NM–65–AD.

Applicability: Model EMB–145 series

airplanes, serial numbers 145004

through 145027 inclusive, equipped

with horizontal stabilizer anti-icing

valve having part number (P/N) 329445;

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 (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 failure of the horizontal

stabilizer anti-icing valve, which could cause

the horizontal stabilizer thermal anti-icing

system to be inoperative, and could result in

reduced controllability of the airplane,

accomplish the following:

(a) Within 400 flight hours after the

effective date of this AD, replace the

horizontal stabilizer anti-icing valve with a

new anti-icing valve, and reinforce the

insulation over the anti-icing ducts of the

horizontal stabilizer thermal anti-icing

system; in accordance with EMBRAER

Service Bulletin 145–30–0007, dated

November 13, 1997.

(b) As of the effective date of this AD, no

person shall install on any airplane a

horizontal stabilizer anti-icing valve having

part number 329445.

(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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small 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, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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.

Note 3: The subject of this AD is addressed

in Brazilian airworthiness directive 98–01–

04, dated January 15, 1998.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10468 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–63–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 Series 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 Saab Model SAAB 2000 series

airplanes. This proposal would require

repetitive inspections to detect chafing

of the hydraulic pipe on the emergency

uplock release system of the main

landing gear (MLG); testing of the

hydraulic pipe for leaks, if necessary;

and repair of the hydraulic pipe, if

necessary. This proposal also would

require modification of the attachment

bolt and attachment hole on the

structural panel, which would terminate

the repetitive inspection requirements

of this AD. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent chafing between

the hydraulic pipe on the emergency

uplock release system of the MLG and

an attachment bolt on a structural panel,

which could result in rupture of the

hydraulic pipe, loss of hydraulic

pressure, and consequent inability to

activate the emergency MLG extension.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

63–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

Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 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
19676 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–63–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–114, Attention: Rules Docket No.

98–NM–63–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

notified the FAA that an unsafe

condition may exist on certain Saab

Model SAAB 2000 series airplanes. The

LFV advises that it has received reports

indicating that interference may exist

between the hydraulic pipe on the

emergency uplock release system of the

main landing gear (MLG) and an

attachment bolt on a structural panel.

Investigation has revealed that the

design of the emergency uplock release

system on certain SAAB 2000 series

airplanes causes the hydraulic pipe and

the attachment bolt to be susceptible to

this type of interference. Such

interference may cause chafing of the

hydraulic pipe. This condition, if not

corrected, could result in rupture of the

hydraulic pipe, loss of hydraulic

pressure, and consequent inability to

activate the emergency MLG extension.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin

2000–29–007, Revision 01, dated

August 18, 1997, which describes

procedures for repetitive visual

inspections to detect chafing of the

hydraulic pipe on the emergency uplock

release system of the MLG; testing of the

hydraulic pipe for leaks, if necessary;

and repair of the hydraulic pipe, if

necessary. The service bulletin also

describes procedures for modification of

the attachment bolt and attachment hole

on the structural panel, which would

eliminate the need for the repetitive

inspections described in the service

bulletin. Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The LFV

classified this service bulletin as

mandatory and issued Swedish

airworthiness directive (SAD) 1–112R1,

dated August 21, 1997, in order to

assure the continued airworthiness of

these airplanes in Sweden.

FAA’s Conclusions

This airplane model is manufactured

in Sweden 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 LFV has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LFV,

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

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 3 airplanes of

U.S. registry would be affected by this

proposed AD. It would take

approximately 3 work hours per

airplane to accomplish the proposed

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the inspection

required by this AD on U.S. operators is

estimated to be $540, or $180 per

airplane.

It would take approximately 6 work

hours per airplane to accomplish the

proposed modification, 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 modification required

by this AD on U.S. operators is

estimated to be $1,080, or $360 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:

SAAB Aircraft AB: Docket 98–NM–63–AD.

Applicability: Model SAAB 2000 series

airplanes, serial numbers -002 through -059

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 (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.

Note 2: Accomplishment of the actions

required by this AD prior to the effective date
Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19677

of this AD in accordance with Saab Service

Bulletin 2000–29–007, dated April 29, 1997,

are considered acceptable for compliance

with the applicable actions specified in this

AD.

To prevent chafing between the hydraulic

pipe on the emergency uplock release system

of the main landing gear (MLG) and an

attachment bolt on a structural panel, which

could result in rupture of the hydraulic pipe,

loss of hydraulic pressure, and consequent

inability to activate the emergency MLG

extension, accomplish the following:

(a) Within 300 flight hours after the

effective date of this AD, perform a visual

inspection to detect chafing of the hydraulic

pipe on the emergency uplock release system

of the MLG, in accordance with Saab Service

Bulletin 2000–29–007, Revision 01, dated

August 18, 1997.

(1) If no chafing is detected, repeat the

visual inspection thereafter at intervals not to

exceed 300 flight hours.

(2) If any chafing is detected, prior to

further flight, perform a test of the hydraulic

pipe to detect leaks in accordance with the

service bulletin.

(i) If no leaking is detected, repeat the

actions required by paragraph (a) of this AD

thereafter at intervals not to exceed 300 flight

hours.

(ii) If any leaking is detected, prior to

further flight, repair the hydraulic pipe and

accomplish paragraph (b) of this AD, in

accordance with the service bulletin.

(b) Within 900 flight hours after the

effective date of this AD, modify the

attachment bolt and attachment hole on the

structural panel, in accordance with Saab

Service Bulletin 2000–29–007, Revision 01,

dated August 18, 1997. Accomplishment of

this modification constitutes terminating

action for the repetitive inspection

requirements 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–216.

(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.

Note 4: The subject of this AD is addressed

in Swedish airworthiness directive (SAD) 1–

112R1, dated August 21, 1997.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10473 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–66–AD]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) EMB–145 Series 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 EMBRAER EMB–145 series

airplanes. This proposal would require

modification of the windshield heating

system in the flight compartment. This

proposal is prompted by reports of

overheating and delamination of the

windshield because the windshield

heating system failed to shut off during

flight. The action specified by the

proposed AD is intended to prevent

failure of the windshield heating

system, which could result in reduced

pilot visibility, structural degradation of

the windshield, and depressurization of

the airplane during flight.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

66–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

Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225,

Sao Jose dos Campos—SP, Brazil. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT: John

W. McGraw, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6098;

fax (770) 703–6097.

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 98–NM–66–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–114, Attention: Rules Docket No.

98–NM–66–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

overheating and delamination of the

windshield in the flight compartment

because the windshield heating system

failed to shut off during flight. The

cause of the failure of the windshield

heating system has been attributed to

failure of the contactor in the closed

position and failure of the electrical

connections between the contactor and