19678 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

the busbar. This condition, if not

corrected, could result in reduced pilot

visibility, structural degradation of the

windshield, and depressurization of the

airplane during flight.

Explanation of Relevant Service

Information

EMBRAER has issued Service Bulletin

145–30–0008, dated November 10, 1997,

which describes procedures for

modification of the windshield heating

system in the flight compartment. This

modification involves installation of a

support beam between frames 10 and 12

at the right- and left-hand cockpit floor;

installation of an additional contactor,

circuit breaker, and associated wiring;

and installation of an auxiliary relay

and associated wiring. Accomplishment

of the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

The Departmento de Aviacao Civil

(DAC), which is the airworthiness

authority for Brazil, has approved this

service bulletin.

FAA’s Conclusions

The FAA has reviewed the service

bulletin described previously and has

determined that accomplishment of the

actions specified in the service bulletin

will positively address the identified

unsafe condition.

U.S. Type Certification of the Airplane

This airplane model is manufactured

in Brazil 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.

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 17 airplanes

of U.S. registry would be affected by this

proposed AD. It would take

approximately 12 work hours per

airplane to accomplish the proposed

modifications, 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 this

figure, the cost impact of the proposed

AD on U.S. operators is estimated to be

$12,240, or $720 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:

Empresa Brasileira De Aeronautica S.A.

(EMBRAER): Docket 98–NM–66–AD.

Applicability: Model EMB–145 series

airplanes, serial numbers 145004 through

145029 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 (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 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,

accomplish the following:

(a) Within 60 days after the effective date

of this AD, modify the windshield heating

system in accordance with EMBRAER

Service Bulletin 145–30–0008, dated

November 10, 1997.

(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, 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.

(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 April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10477 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–75–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319 and A321–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.
Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19679

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A319 and A321–

100 series airplanes. This proposal

would require adjustment of the landing

gear unlocked-stop screw; replacement

of the shear pins in the reduction gear

box and the landing gear pulley

assembly with new or serviceable shear

pins; a one-time inspection to detect

discrepancies of the landing gear cut-out

valve; an operational test of the uplock

mechanical control system; and followon corrective actions, if necessary. 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 non-extension of

one or more landing gears, consequent

damage to the airplane structure, and

possible injury to passengers and

crewmembers.

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–

75–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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–75–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–75–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A319 and A321–100 series

airplanes. The DGAC advises that

certain Airbus Model A319 and A321–

100 series airplanes were manufactured

with the free-fall control mechanism for

the landing gear rigged incorrectly. The

landing gear unlocked-stop screw of the

reduction gear box was not adjusted

properly. Such improper adjustment of

the landing gear unlocked-stop screw

could lead to damage to the cut-out

valve and rupture of the four shear pins

in the free-fall mechanism during a freefall extension. This condition, if not

corrected, could result in non-extension

of one or more landing gears,

consequent damage to the airplane

structure, and possible injury to

passengers and crewmembers.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

Industrie A319/A321 All Operator Telex

(AOT) 32–15, dated July 1, 1997, which

describes procedures for adjustment of

the landing gear unlocked-stop screw;

replacement of the shear pins in the

reduction gear box and the landing gear

pulley assembly with new or serviceable

shear pins; a one-time visual inspection

of the main landing gear cut-out valve

to detect discrepancies (rupture,

distortion, and angular position); an

operational test of the uplock

mechanical control system; and followon corrective actions, if necessary. The

corrective actions include replacing the

cut-out valve with a new or serviceable

part and performing functional tests of

the normal extension and retraction of

the landing gear and of the free-fall

extension system. Accomplishment of

the actions specified in the AOT is

intended to adequately address the

identified unsafe condition. The DGAC

classified this AOT as mandatory and

issued French airworthiness directive

97–177–101(B), dated August 13, 1997,

in order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France and are 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 DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, 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 AOT described previously.

Cost Impact

The FAA estimates that 2 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 20 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$2,400, or $1,200 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
19680 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

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:

Airbus Industrie: Docket 98–NM–75–AD.

Applicability: Model A319 series airplanes,

manufacturer’s serial numbers 578 through

625 inclusive; and Model A321–100 series

airplanes, manufacturer’s serial numbers 385

through 620 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 (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 non-extension of one or more

landing gears, consequent damage to the

airplane structure, and possible injury to

passengers and crewmembers, accomplish

the following:

(a) Within 400 flight hours after the

effective date of this AD, accomplish the

actions required by paragraphs (a)(1), (a)(2),

(a)(3), and (a)(4) of this AD, in accordance

with Airbus Industrie A319/A321 All

Operator Telex (AOT) 32–15, dated July 1,

1997.

(1) Adjust the landing gear unlocked-stop

screw.

(2) Replace the shear pins in the reduction

gear box and the landing gear pulley

assembly with new or serviceable shear pins.

(3) Inspect the cut-out valve for

discrepancies. If any discrepancy to the cutout valve is detected, accomplish the

requirements of paragraphs (a)(3)(i) and

(a)(3)(ii) of this AD at the time specified in

the AOT.

(i) Replace the cut-out valve with a new or

serviceable part within the time specified in

the AOT.

(ii) After replacing the cut-out valve,

perform a functional test of the normal

extension and retraction of the landing gear

and of the free-fall extension system. If any

discrepancy is detected during the

accomplishment of either of the functional

tests, prior to further flight, repair in

accordance with the AOT.

(4) Perform an operational test of the gear

uplock and door uplock mechanical control

system. If any discrepancy is detected during

the accomplishment of the operational test,

prior to further flight, repair in accordance

with the AOT.

(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,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(c) Special flight permits may be issued in

accordance with §§ 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 French airworthiness directive 97–177–

101(B), dated August 13, 1997.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10476 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–86–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4100

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 British Aerospace (Jetstream)

Model 4100 airplanes. This proposal

would require an eddy current

conductivity test to measure the

conductivity of the upper splice plate of

the wing, and follow-on actions, if

necessary. 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 correct corrosion of the

upper splice plate of the wing, which

could result in reduced structural

integrity of the airplane.

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–

86–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

AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia

20171. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.