Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30115

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:

98–11–27 Dornier Luftfahrt GmbH:

Amendment 39–10552. Docket 98–NM–

46–AD.

Applicability: Model 328–100 series

airplanes, serial numbers 3005 through 3095

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.

To prevent failure of the pressure dump

and relief valves in the main and auxiliary

hydraulic systems, which could cause a loss

in hydraulic pressure for roll control spoilers

and brakes, and consequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 8 months after the effective date

of this AD, replace the existing pressure

dump and relief valves having part number

(P/N) ZHV29–1 with new valves having P/N

ZHV29–2, in the main and auxiliary

hydraulic systems, in accordance with

Dornier Service Bulletin SB–328–29–205,

dated February 12, 1997.

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

person shall install on any airplane any

pressure dump and relief valve having P/N

ZHV29–1.

(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 Dornier Service Bulletin

SB–328–29–205, dated February 12, 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 FAIRCHILD Dornier, Dornier Luftfahrt

GmbH, P.O. Box 1103, D–82230 Wessling,

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 97–072,

dated March 27, 1997.

(f) This amendment becomes effective on

July 8, 1998.

Issued in Renton, Washington, on May 22,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14218 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–52–AD; Amendment

39–10554; AD 98–11–29]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe 146 Series

Airplanes and Model Avro 146–RJ

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe 146 series airplanes and

Model Avro 146–RJ series airplanes,

that requires a one-time inspection to

detect corrosion of the threads of the

eyebolt and piston rod on the retraction

jack of the main landing gear (MLG);

and repair, 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 corrosion of the threads of the

eyebolt and piston rod on the retraction

jack of the MLG, which may cause the

eyebolt to detach from the jack, and

consequent unrestrained MLG

deployment or inability to retract the

MLG.

DATES: Effective July 8, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 8, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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 British

Aerospace Model BAe 146 series

airplanes and Model Avro 146–RJ series

airplanes was published in the Federal

Register on April 3, 1998 (63 FR 16447).

That action proposed to require a onetime inspection to detect corrosion of

the threads of the eyebolt and piston rod

on the retraction jack of the main

landing gear, and repair, if necessary.

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.
30116 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

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 25 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required inspection, and that the

average labor rate is $60 per work hour.

Based on this figure, the cost impact of

the AD on U.S. operators is estimated to

be $1,500, or $60 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:

98–11–29 British Aerospace Regional

Aircraft (Formerly British Aerospace

Regional Aircraft Limited, Avro

International Aerospace Division; British

Aerospace, PLC; British Aerospace

Commercial Aircraft Limited): Amendment

39–10554. Docket 98–NM–52–AD.

Applicability: Model BAe 146 series

airplanes and Model Avro 146–RJ series

airplanes, as listed in British Aerospace

Service Bulletin SB.32–145, Revision 1,

dated October 6, 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

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 corrosion of the threads of the

eyebolt and piston rod on the retraction jack

of the main landing gear (MLG), which may

cause the eyebolt to detach from the jack, and

consequent unrestrained MLG deployment or

inability to retract the MLG, accomplish the

following:

(a) Perform a one-time visual inspection to

detect corrosion of the threads of the eyebolt

and piston rod on the retraction jack of the

MLG, in accordance with British Aerospace

Service Bulletin SB.32–145, Revision 1,

dated October 6, 1997, at the time specified

in paragraph (a)(1), (a)(2), or (a)(3) of this AD,

as applicable. Except as provided by

paragraph (b) of this AD, if any corrosion is

detected: Prior to further flight, repair in

accordance with the service bulletin.

(1) For MLG retraction jacks that have

accumulated more than 7 and less than 9

years since date of manufacture: Inspect

within 2 years after the effective date of this

AD.

(2) For MLG retraction jacks that have

accumulated 9 or more years since date of

manufacture: Inspect within 1 year after the

effective date of this AD.

(3) For MLG retraction jacks other than

those identified in paragraph (a)(1) or (a)(2)

of this AD, and other than those MLG

retraction jacks having Part/Type No.

104628003 with serial numbers DH/0029/93

(where ‘‘93’’ identifies the year of

manufacture) and subsequent: Inspect within

6 years since date of manufacture, or within

2 years after the effective date of this AD,

whichever occurs later.

Note 2: British Aerospace Service Bulletin

SB.32–145, Revision 1, dated October 6,

1997, references Dowty Aerospace

Hydraulics—Cheltenham Service Bulletin

146–32–507, dated August 1, 1997, as an

additional source of service information to

accomplish the inspection and repair.

(b) If any corrosion is detected during the

inspection required by paragraph (a) of this

AD in areas other than those detailed in

British Aerospace Service Bulletin SB.32–

145, Revision 1, dated October 6, 1997: Prior

to further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

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

person shall install an eyebolt or piston rod

on the retraction jack of the MLG on any

airplane unless it has been modified in

accordance with British Aerospace Service

Bulletin SB.32–145, Revision 1, dated

October 6, 1997.

(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. 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–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 actions shall be done in accordance

with British Aerospace Service Bulletin

SB.32–145, Revision 1, dated October 6,

1997, which contains the following list of

effective pages:

Page number

shown on

page

Revision

level

shown on

page

Date shown on

page

1, 2 .............. 1 .............. Oct. 6, 1997.

3–7 ............... Original .... Sept. 18, 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 AI(R) American

Support, Inc., 13850 Mclearen Road,

Herndon, Virginia 20171. Copies may be

inspected at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at
Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30117

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Note 4: The subject of this AD is addressed

in British airworthiness directive 006–09–97.

(g) This amendment becomes effective on

July 8, 1998.

Issued in Renton, Washington, on May 22,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14217 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–134–AD; Amendment

39–10551; AD 98–11–26]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 340B and SAAB 2000 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

340B and SAAB 2000 series airplanes,

that requires modification of the check

valves of the airfoil de-icing system, or

replacement of the check valves with

improved valves. 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 failure of the check

valves, which could result in loss of

airfoil de-icing capability during single

engine operation, and consequent

reduced controllability of the airplane.

DATES: Effective July 8, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 8, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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 Saab Model

SAAB 340B and SAAB 2000 series

airplanes was published in the Federal

Register on April 1, 1998 (63 FR 15797).

That action proposed to require

modification of the check valves of the

airfoil de-icing system, or replacement

of the check valves with improved

valves.

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 125 Model

SAAB 340B and SAAB 2000 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 4 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will be provided 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

$30,000, or $240 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:

98–11–26 SAAB AIRCRAFT AB:

Amendment 39–10551. Docket 97–NM–

134–AD.

Applicability: Model SAAB 340B series

airplanes, serial numbers 240 through 430

inclusive; Model SAAB 2000 series airplanes,

serial numbers 002 through 050 inclusive,

and 052; 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 check valves,

which could result in loss of airfoil de-icing