34560 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain EMBRAER

EMB–145 series airplanes was

published in the Federal Register on

April 21, 1998 (63 FR 19677). That

action proposed to require modification

of the windshield heating system in the

flight compartment.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 17 airplanes

of U.S. registry will be affected by this

AD. It will take approximately 12 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour.

Required parts will 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

$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 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–13–17 EMPRESA BRASILEIRA dE

AERONAUTICA S.A. (EMBRAER):

Amendment 39–10605. 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.

(d) The modification shall be done in

accordance with EMBRAER Service Bulletin

145–30–0008, dated November 10, 1997. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected 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; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 11,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16050 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–102–AD; Amendment

39–10607; AD 98–13–19]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 100, 200, 300, 400, 500,

600, and 700 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, that requires a one-
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34561

time detailed visual inspection of the

forward fuel feed lines in the left- and

right-hand engine nacelles for chafing;

replacement of damaged parts with

serviceable parts; and modification of

the supports and improved routing for

the high- and low-tension leads of the

inboard ignition units. This amendment

is prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent chafing on the

forward fuel feed lines, which could

result in fuel leakage and consequent

increased risk of fire in the engine

nacelles.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., Technical

Support Department, P.O. Box 75047,

1117 ZN Schiphol Airport, the

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Fokker Model

F27 Mark 100, 200, 300, 400, 500, 600,

and 700 series airplanes was published

in the Federal Register on April 23,

1998 (63 FR 20141). That action

proposed to require a one-time detailed

visual inspection of the forward fuel

feed lines in the left- and right-hand

engine nacelles for chafing; replacement

of damaged parts with serviceable parts;

and modification of the supports and

improved routing for the high- and lowtension leads of the inboard ignition

units.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 34 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 1 work

hour per airplane to accomplish the

required 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 $2,040, or

$60 per airplane.

It will take approximately 4 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour. The

cost of required parts would be

minimal. Based on these figures, the

cost impact of the modification required

by this AD on U.S. operators is

estimated to be $8,160, or $240 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–13–19 Fokker Services B.V.:

Amendment 39–10607. Docket 98–NM–

102–AD.

Applicability: All Model F27 Mark 100,

200, 300, 400, 500, 600, and 700 series

airplanes; 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 chafing on the forward fuel feed

lines, which could result in fuel leakage and

consequent increased risk of fire in the

engine nacelles, accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform a one-time detailed

visual inspection of the left- and right-hand

engine nacelles for chafing of the forward

fuel feed lines by the high- and low-tension

leads of the inboard ignition units, in

accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/28–62, dated September

1, 1997. If any chafing is detected, prior to

further flight, replace the fuel line with a new

fuel line in accordance with Part 1 of the

Accomplishment Instructions of the service

bulletin.

(b) Within 6 months after the effective date

of this AD, modify the supports and reroute

the high- and low-tension leads of the

inboard ignition units, in accordance with

Part 2 of the Accomplishment Instructions of
34562 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

Fokker Service Bulletin F27/28–62, dated

September 1, 1997.

(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 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.

(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.

(e) The actions shall be done in accordance

with Fokker Service Bulletin F27/28–62,

dated September 1, 1997. This incorporation

by reference was approved by the Director of

the Federal Register in accordance with 5

U.S.C. 552(a) and 1 CFR part 51. Copies may

be obtained from Fokker Services B.V.,

Technical Support Department, P.O. Box

75047, 1117 ZN Schiphol Airport, the

Netherlands. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1997–

094 (A), dated September 30, 1997.

(f) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 11,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16049 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–75–AD; Amendment

39–10606; AD 98–13–18]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319 and A321–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A319 and A321–100 series airplanes,

that requires 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

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this 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: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A319 and A321–100 series

airplanes was published in the Federal

Register on April 21, 1998 (63 FR

19678). That action proposed to 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 onetime 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.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

The commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 2 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 20 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

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 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 adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.