Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations 20303

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:

98–09–06 SAAB Aircraft AB: Amendment

39–10485. Docket 97–NM–135–AD.

Applicability: Model SAAB SF340A series

airplanes having serial numbers –121, and

–125 through –159 inclusive; and Model

SAAB 340B series airplanes having serial

numbers –160 through –360 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 leakage of the fire extinguishing

agent, which could prevent proper

distribution of the agent within the lavatory

waste bin in the event of a fire, accomplish

the following:

(a) Within 3 months after the effective date

of this AD, accomplish paragraphs (a)(1) and

(a)(2) of this AD in accordance with Saab

Service Bulletin SAAB 340–25–235, dated

December 11, 1996.

(1) Perform an inspection to determine the

serviceability of the fire extinguisher in the

forward lavatory waste bin, in accordance

with the service bulletin. If any discrepancy

is found, prior to further flight, accomplish

the repair or replacement of the fire

extinguisher, as specified in the service

bulletin.

(2) Install a placard adjacent to the fire

extinguisher in the forward lavatory waste

bin in accordance with the service bulletin.

(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 actions shall be done in accordance

with Saab Service Bulletin SAAB 340–25–

235, dated December 11, 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 Saab

Aircraft AB, SAAB Aircraft Product Support,

S–581.88, Linko ̈ping, Sweden. 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

issued Swedish airworthiness directive SAD

No. 1–106, dated December 12, 1996.

(e) This amendment becomes effective on

May 29, 1998.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10482 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–186–AD; Amendment

39–10486; AD 98–09–07]

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 certain Fokker Model F27

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

700 series airplanes, that requires a

modification of the lapjoint below the

chine line at certain fuselage stations.

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 fatigue cracking in

the lapjoint below the chine line at

certain fuselage stations, which could

result in reduced structural integrity of

the fuselage.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

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 certain Fokker

Model F27 Mark 100, 200, 300, 400,

500, 600, and 700 series airplanes was

published in the Federal Register on

February 12, 1998 (63 FR 7078). That

action proposed to require a

modification of the lapjoint below the

chine line at certain fuselage stations.

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 140 work

hours per airplane to accomplish the

required modification (specified as Part

1 in the referenced service bulletin), at

an average labor rate of $60 per work
20304 Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations

hour. The cost of required parts will be

nominal. Based on these figures, the

cost impact of this modification

required by this AD on U.S. operators is

estimated to be $8,400 per airplane.

It will take approximately 300 work

hours per airplane to accomplish the

modification (specified as Part 2 in the

referenced service bulletin), at an

average labor rate of $60 per work hour.

The cost of required parts will be

nominal. Based on these figures, the

cost impact of this modification

required by this AD on U.S. operators is

estimated to be $18,000 per airplane.

It will take approximately 210 work

hours per airplane to accomplish the

modification (specified as Part 3 in the

referenced service bulletin), at an

average labor rate of $60 per work hour.

The cost of required parts will be

nominal. Based on these figures, the

cost impact of this modification

required by this AD on U.S. operators is

estimated to be $12,600 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:

98–09–07 Fokker: Amendment 39–10486.

Docket 96–NM–186–AD.

Applicability: Model F27 Mark 100, 200,

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

serial numbers 10102 through 10375

inclusive, that are operated or have been

operated at a maximum cabin pressure

differential of 5.5 pounds per square inch

(psi); 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 (d) 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 fatigue cracking in the lapjoint

below the chine line at certain fuselage

stations, which could result in reduced

structural integrity of the fuselage,

accomplish the following:

(a) For airplanes on which Fokker Service

Bulletin F27/53–68, dated July 4, 1966, or

Revision 1, dated July 19, 1967, has not been

accomplished: Prior to the accumulation of

32,000 total flight cycles, or within 2 years

after the effective date of this AD, whichever

occurs later, modify the lapjoint below the

chine line between fuselage station 1400 and

station 5050, in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/53–116, dated April 15,

1994. Accomplishment of this modification

and accomplishment of the requirements of

paragraph (b) of this AD constitute

terminating action for the repetitive

inspection requirements of items 53–30–02

and 53–30–03 of the Fokker Model F27

Structural Inspection Program (SIP), as

required by AD 96–13–07, amendment 39–

9675.

(b) For airplanes on which Fokker Service

Bulletin F27/53–85, dated February 16, 1970,

has not been accomplished: Prior to the

accumulation of 32,000 total flight cycles, or

within 2 years after the effective date of this

AD, whichever occurs later, modify the

lapjoint below the chine line between

fuselage station 5050 and station 12975, in

accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/53–116, dated April 15,

1994. Accomplishment of this modification

and accomplishment of the requirements of

paragraph (a) of this AD constitute

terminating action for the repetitive

inspection requirements of items 53–30–02

and 53–30–03 of the Fokker Model F27 SIP,

as required by AD 96–13–07.

(c) For airplanes on which Fokker Service

Bulletin F27/53–85, dated February 16, 1970,

has not been accomplished: Prior to the

accumulation of 56,000 total flight cycles, or

within 2 years after the effective date of this

AD, whichever occurs later, modify the

lapjoint below the chine line between

fuselage station 12975 and station 16660, in

accordance with Part 3 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/53–116, dated April 15,

1994. Accomplishment of this modification

constitutes terminating action for the

repetitive inspection requirements of item

53–30–04 of the Fokker Model F27 SIP, as

required by AD 96–13–07.

(d) 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.

(e) 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.

(f) The modifications shall be done in

accordance with Fokker Service Bulletin

F27/53–116, dated April 15, 1994. 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 94–092

(A), dated May 25, 1994.

(g) This amendment becomes effective on

May 29, 1998.
Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations 20305

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10481 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–337–AD; Amendment

39–10482; AD 98–09–03]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires a one-time, detailed visual

inspection for discrepancies of the

electrical bundles in the power

generation compartment, and 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 chafing and

consequent damage to the electrical

generation wires in the 101VU panel,

which could result in a loss of electrical

generation channels.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

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 A310 and A300–600 series

airplanes was published in the Federal

Register on February 9, 1998 (63 FR

6501). That action proposed to require

a one-time, detailed visual inspection

for discrepancies of the electrical

bundles in the power generation

compartment, and 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

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 94 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

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 $11,280, or $120 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:

98–09–03 Airbus: Amendment 39–10482.

Docket 97–NM–337–AD.

Applicability: Model A310 and A300–600

series airplanes on which any of the

following Airbus service bulletins (or earlier

versions) has been accomplished: A310–24–

2067, Revision 01, dated March 18, 1997;

A310–24–2072, Revision 01, dated February

4, 1997; A300–24–6058, Revision 01, dated

January 23, 1997; or A300–24–6064, Revision

01, dated February 4, 1997; 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 chafing and consequent damage

to the electrical generation wires in the

101VU panel, which could result in a loss of

electrical generation channels, accomplish

the following:

(a) Within 400 flight hours or 60 days after

the effective date of this AD, whichever