30112 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

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 copy of the final

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, 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 a new airworthiness directive

(AD) to read as follows:

98–11–31 British Aerospace: Amendment

39–10556; Docket No. 97–CE–100–AD.

Applicability: Jetstream Model 3101

airplanes, all serial numbers, certificated in

any category, that are equipped with

autopilot systems installed under Jetstream

Aircraft Limited (JAL) Modifications JM3027,

3243, 3352, or 3483.

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 within the next 12

calendar months after the effective date of

this AD, unless already accomplished.

To prevent failure of the autopilot elevator

electric system relays for the up and down

trim interlocks, which could result in

uncommanded trim servo operation and

possible loss of control of the airplane,

accomplish the following:

(a) Modify the autopilot system with

Jetstream Aircraft Ltd. (JAL) Kit No. JK 2628

in accordance with Jetstream 3100/3200

Series Service Bulletin No. 22–JK 2628,

Revision 2, Original Issue: October 21, 1996,

by installing two additional relays in the

relay box with associated wiring changes.

This relay box is located under the righthand crew seat in the cockpit.

(b) The modification required by paragraph

(a) of this AD eliminates the 800-hour life

limit requirement for the pitch-up and pitchdown relays. Operators are encouraged to

obtain the revision for their affected

maintenance manuals that is available from

the manufacturer.

(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) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, Aircraft Certification Service,

1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) Questions or technical information

related to Jetstream 3100/3200 Series Service

Bulletin No. 22–JK 2628, Revision 2, Original

Issue: October 21, 1996, should be directed

to British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland; telephone (01292)

479888; facsimile (01292) 479703. This

service information may be examined at the

FAA, Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

(f) The modification required by this AD

shall be done in accordance with Jetstream

3100/3200 Series Service Bulletin No. 22–JK

2628, Revision 2, Original Issue: October 21,

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 British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland. Copies may be

inspected at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri, 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 British AD No. 006–10–96, undated.

(g) This amendment becomes effective on

July 17, 1998.

Issued in Kansas City, Missouri, on May

21, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14191 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–43–AD; Amendment

39–10548; AD 98–11–23]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model CN–

235 series airplanes, that requires

modification of certain fastener holes of

the center wing. 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

this area, which could result in reduced

structural integrity of the wing.

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 Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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
Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations 30113

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 CASA

Model CN–235 series airplanes was

published in the Federal Register on

March 23, 1998 (63 FR 13801). That

action proposed to require modification

of certain fastener holes of the center

wing.

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.

Explanation of Changes Made to This

Final Rule

In the proposal, the FAA

inadvertently omitted reference to

Annex 1, dated June 10, 1993, of CASA

Service Bulletin SB–235–57–05,

Revision 2, dated June 21, 1996.

Therefore, the FAA has revised the final

rule accordingly.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 2 airplanes of

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

The FAA estimates that the actions

specified in CASA Service Bulletin SB–

235–57–14, will be required to be

accomplished on one airplane of U.S.

registry. These required actions will

take approximately 220 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$719 per airplane. Based on these

figures, the cost impact of the inspection

required by this AD on the single U.S.

operator is estimated to be $13,919.

For CASA Model CN–235 series

airplane, serial number C–011, on

which the actions specified in CASA

Service Bulletin SB–235–57–05 will be

required to be accomplished, those

required actions will take approximately

1,900 work hours per airplane to

accomplish, at an average labor rate of

$60 per work hour. Required parts will

cost approximately $11,330 per

airplane. Based on these figures, the cost

impact of the required actions for that

airplane is estimated to be $125,330.

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:

98–11–23 Construcciones Aeronauticas S.A.

(CASA): Amendment 39–10548. Docket

97–NM–43–AD.

Applicability: Model CN–235 series

airplanes; as listed in CASA Service Bulletins

SB–235–57–14, Revision 1, dated June 21,

1996; and SB–235–57–05, Revision 2, dated

June 21, 1996, including Annex 1, dated June

10, 1993; and Model CN–235 having serial

number C–011; 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 fastener

holes of the center wing, which could result

in reduced structural integrity of the wing,

accomplish the following:

(a) For airplanes listed in CASA Service

Bulletins SB–235–57–14, Revision 1, dated

June 21, 1996; and SB–235–57–05, Revision

2, dated June 21, 1996, including Annex 1,

dated June 10, 1993: Perform a rototest

inspection of the fastener holes of the center

wing to detect cracking, in accordance with

the applicable service bulletin, at the time

specified in paragraph (c) of this AD.

(1) If no crack is found, prior to further

flight, cold work the fastener holes in

accordance with the applicable service

bulletin.

(2) If any crack is found, prior to further

flight, remove it in accordance with the

service bulletin; repeat the rototest

inspection to detect cracking; and cold work

the fastener holes, in accordance with the

applicable service bulletin. If any crack is

found that cannot be removed using the

procedures specified in the applicable

service bulletin, prior to further flight, repair

it in accordance with a method approved by

the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate.

(b) For airplane serial number C–011:

Perform a rototest inspection of the fastener

holes of the center wing to detect cracking,

in accordance with CASA Service Bulletin

SB–235–57–05, Revision 2, dated June 21,

1996, including Annex 1, dated June 10,

1993, at the time specified in paragraph (c)

of this AD.

(1) If no crack is found, prior to further

flight, cold work the fastener holes in

accordance with the service bulletin.

(2) If any crack is found, prior to further

flight, remove it in accordance with the

service bulletin; repeat the rototest

inspection to detect cracking; and cold work

the fastener holes, in accordance with the

service bulletin. If any crack is found that

cannot be removed using the procedures

specified in the service bulletin, prior to

further flight, repair it in accordance with a

method approved by the Manager,

International Branch, ANM–116.

(c) Accomplish the inspection required by

paragraph (a) or (b) of this AD, as applicable,
30114 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 /Rules and Regulations

at the later of the times specified in

paragraphs (c)(1) and (c)(2) of this AD.

(1) Prior to the accumulation of 17,000

total flight cycles or 37,400 total flight hours,

whichever occurs first.

(2) Within 6 months after the effective date

of this AD.

(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 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 actions shall be done in accordance

with CASA Service Bulletin SB–235–57–14,

Revision 1, dated June 21, 1996, and CASA

Service Bulletin SB–235–57–05, Revision 2,

dated June 21, 1996, including Annex 1,

dated June 10, 1993, which contains the

following list of effective pages:

Page Nos.

Revision

level

shown

on page

Date shown on

page

1, 3–5, 12, 26–

29, 33, 34,

45–52.

2 June 21, 1996.

2, 6–11, 13–

25, 30–32,

35–44, 53–

65.

1 March 13, 1995.

Annex 1

1–46 ............... 5 June 10, 1993.

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 Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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 Spanish airworthiness directive 04/94,

dated August 1994.

(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. 98–14213 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–46–AD; Amendment

39–10552; AD 98–11–27]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

replacement of the existing pressure

dump and relief valves in the main and

auxiliary hydraulic systems with new

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

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.

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 FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. 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 Dornier

Model 328–100 series airplanes was

published in the Federal Register on

April 2, 1998 (63 FR 16167). That action

proposed to require replacement of the

existing pressure dump and relief valves

in the main and auxiliary hydraulic

systems with new 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 50 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 6

work hours per airplane to accomplish

the required replacement, 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 $18,000, or $360 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