60644 Federal Register / Vol. 62, No. 218 / Wednesday, November 12, 1997 / Rules and Regulations

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:

97–23–10 Dornier: Amendment 39–10198.

Docket 96–NM–115–AD.

Applicability: Model 328–100 series

airplanes having serial numbers 3005

through 3045 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

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 failure of the cable tension

regulator on both the left and right elevators,

and consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 6 months after the effective date

of this AD, modify the cable tension regulator

on both the left and right elevators by

installing two lateral plates on the lever arm,

in accordance with Dornier Service Bulletin

SB–328–27–116, dated September 26, 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,

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 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 Dornier Service Bulletin

SB–328–27–116, dated September 26, 1995.

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 Dornier Deutsche Aerospace, P.O. Box

1103, D–82230 Wessling, Federal Republic of

Germany. 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 German airworthiness directive 95–434,

dated November 14, 1995.

(e) This amendment becomes effective on

December 17, 1997.

Issued in Renton, Washington, on

November 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29444 Filed 11–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–165–AD; Amendment

39–10200; AD 97–23–12]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Mark 0100 and 0070 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F28

Mark 0100 and 0070 series airplanes,

that requires replacement of the fusible

pin in the upper torque link of the main

landing gear with an improved pin. 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 reduced structural integrity and

potential collapse of the main landing

gear.

DATES: Effective December 17, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

17, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. 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:

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 Fokker

Model F28 Mark 0100 and 0070 series

airplanes was published in the Federal

Register on August 11, 1997 (62 FR

42951). That action proposed to require

replacement of the fusible pin in the

upper torque link of the main landing

gear with an improved pin.
Federal Register / Vol. 62, No. 218 / Wednesday, November 12, 1997 / Rules and Regulations 60645

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 state that the

proposed AD does not affect their fleet

of airplanes.

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 10 Fokker

Model F28 Mark 0100 and 0070 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 14 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $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 AD on

U.S. operators is estimated to be $8,400,

or $840 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:

97–23–12 Fokker: Amendment 39–10200.

Docket 97–NM–165–AD.

Applicability: Model F28 Mark 0100 and

0070 series airplanes, equipped with

Menasco Aerospace Ltd. main landing gears

having part number (P/N) 41050, including

the fusible upper torque link pin having P/

N 41223–1; 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 reduced structural integrity and

potential collapse of the main landing gear,

accomplish the following:

(a) Within 12 months after the effective

date of this AD, replace any main landing

gear upper torque link fusible pin having P/

N 41223–1 with a pin having P/N 41223–3,

in accordance with Fokker Service Bulletin

SBF100–32–099, dated June 14, 1996.

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

person shall install a main landing gear

upper torque link fusible pin having P/N

41223–1 on any airplane.

(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 replacement shall be done in

accordance with Fokker Service Bulletin

SBF100–32–099, dated June 14, 1996. 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

Aircraft USA, Inc., 1199 North Fairfax Street,

Alexandria, Virginia 22314. 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 1996–

074 (A), dated June 28, 1996.

(f) This amendment becomes effective on

December 17, 1997.

Issued in Renton, Washington, on

November 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29443 Filed 11–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–167–AD; Amendment

39–10201; AD 97–23–13]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320 and A321 series airplanes, that

requires a one-time inspection for

discrepancies of the release cable of the

forward and rear passenger doors, and

replacement of any discrepant release

cable with a new release cable. This

amendment is prompted by the issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to