30378 Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations

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:

98–12–06 Stemme GmbH & Co. KG:

Amendment 39–10562; Docket No. 97–

CE–129–AD.

Applicability: Model S10 (serial numbers

10–12 through 10–60), and Model S10–V

(serial numbers 14–002 through 14–022) and

transformed Model S10–V (serial numbers

14–012M to 14–060M) sailplanes, certificated

in any category.

Note 1: This AD applies to each sailplane

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

sailplanes 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 (e) 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 in the

body of this AD, unless already

accomplished.

To prevent engine valve malfunction,

which could cause engine failure during

flight and loss of control of the sailplane,

accomplish the following:

(a) Within the next 30 days after the

effective date of this AD, insert a revision in

the Limitations Section 2.4.2.1, Fuel, of the

flight manual (FM) that states: ‘‘Only

authorized fuel is AVGAS 100LL’’ in

accordance with the Instructions section of

Stemme Service Bulletin (SB) Document No.

A31–10–021, dated June 28, 1995.

(b) Incorporating the revision to the

Limitations Section of the FM, as required by

paragraph (a) of this AD, may be performed

by the owner/operator holding at least a

private pilot certificate as authorized by

section 43.7 of the Federal Aviation

Regulations (14 CFR 43.7), and must be

entered into the aircraft records showing

compliance with this AD in accordance with

section 43.9 of the Federal Aviation

Regulations (14 CFR 43.9).

(c) Within the next 60 days after the

effective date of this AD, accomplish

paragraphs (c)(1), (c)(2), and (c)(3) of this AD;

(1) Inspect the fine fuel filter for the

accumulation of chopped cotton fibers, and

replace the filter if it is contaminated, prior

to further flight, in accordance with the

Instructions section of Stemme SB Document

No. A31–10–021, dated June 28, 1995; and,

(2) Inspect the engine in accordance with

LIMBACH Flugmotoren Technical Bulletin

No. 47, dated June 28, 1995.

(3) If a brownish-black sticky residue is

found on the engine, prior to further flight,

disassemble and clean the engine in

accordance with LIMBACH Flugmotoren

Technical Bulletin No. 47, dated June 28,

1995.

(d) Special flight permits may be issued in

accordance with §§ 1.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the sailplane to a

location where the requirements of this AD

can be accomplished.

(e) An alternative method of compliance or

adjustment of the compliance times that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, FAA, 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 Manager, Small Airplane

Directorate.

(f) Questions or technical information

related to Stemme Service Bulletin No. A31–

10–021, dated June 28, 1995, and LIMBACH

Flugmotoren Technical Bulletin No. 47,

dated June 28, 1995, should be directed to

Stemme GmbH & Co. KG, Gustav-MeyerAllee 25, D–13355 Berlin, Federal Republic

of Germany. 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.

(g) The insertion, inspections, and

replacement required by this AD shall be

done in accordance with Stemme Service

Bulletin No. A31–10–021, dated June 28,

1995, and Limbach Flugmotoren Technical

Bulletin No. 47, dated June 28, 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

Stemme GmbH & Co. KG, Gustav-MeyerAllee 25, D–13355 Berlin, Federal Republic

of Germany. 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 German AD 95–273, dated July 11, 1995.

(h) This amendment becomes effective on

July 17, 998.

Issued in Kansas City, Missouri, on May

27, 1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–14614 Filed 6–3–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–22–AD; Amendment

39–10564; AD 98–12–08]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France (Formerly Aerospatiale, Society

Nationale Industrielle, Sud Aviation)

Model SA–365N, SA–365N1, SA–365N2,

and SA–366G1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France

(Formerly Aerospatiale, Society

Nationale Industrielle, Sud Aviation)

Model SA–365N, SA–365N1, SA–

365N2, and SA–366G1 helicopters, that

requires an inspection of the

transmission deck for cracks; repair of

any cracked transmission deck; and

replacement of the transmission deck

support beams (support beams) with

redesigned support beams. This

amendment is prompted by several

reports of cracks in the transmission

deck and support beams. The actions

specified by this AD are intended to

detect cracks that reduce the strength of

the main gearbox strut attachment and

could result in failure of the main
Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations 30379

gearbox mounting, and subsequent loss

of control of the helicopter.

DATES: Effective July 9, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 9, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Mike Mathias, Aerospace Engineer,

FAA, Rotorcraft Directorate, ASW–111,

2601 Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5123, fax

(817) 222–5961.

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 Eurocopter France

SA–365N, SA–365N1, SA–365N2, and

SA–366G1 helicopters was published in

the Federal Register on December 3,

1997 (62 FR 63912). That action

proposed to require an inspection of the

transmission deck for cracks; repair of

any cracked transmission deck; and

replacement of the support beams with

redesigned support beams.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 137

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 50 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $5,000 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $1,096,000.

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 a new airworthiness directive to

read as follows:

AD 98–12–08 Eurocopter France (Formerly

Aerospatiale, Society Nationale

Industrielle, Sud Aviation): Amendment

39–10564. Docket No. 96–SW–22–AD.

Applicability: Model SA–365N, SA–365N1,

SA–365N2, and SA–366G1 helicopters,

certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To detect cracks that reduce the strength of

the main gearbox strut attachment and could

result in failure of the main gearbox

mounting, and subsequent loss of control of

the helicopter, accomplish the following:

(a) For Model SA–365N, SA–365N1, and

SA–366G1 helicopters, on or before attaining

4,000 hours time-in-service (TIS), or within

50 hours TIS after the effective date of this

AD, whichever occurs later; and for Model

SA–365N2 helicopters, on or before attaining

2,000 hour TIS, or within 50 hours TIS after

the effective date of this AD, whichever

occurs later; perform the following:

(1) Inspect the transmission deck for cracks

using a dye-penetrant inspection method, in

accordance with paragraph BB of Eurocopter

France Telex Service No. 10011, dated

February 24, 1995. If a crack is found in the

transmission deck, repair prior to further

flight.

Note 2: A FAA-approved repair solution

can be initiated by contacting the American

Eurocopter Technical Support Department,

ATTN: Manager, telephone (972) 641–3460,

fax (972) 641–3527.

(2) Replace the currently installed

transmission deck support beams, part

numbers (P/N) 365A21–3365–49 and

365A21–3365–CY, with reinforced

transmission deck support beams, P/N

365A21–3365–JE–01 and 365A21–3365–JF–

01, in accordance with the Accomplishment

Instructions in Eurocopter France Service

Bulletin No. 05.00.36, Rev. 1, dated

December 16, 1996.

(b) After completion of paragraphs (a)(1)

and (a)(2) of this AD, clean, prime and paint

the affected areas of the transmission deck

and the reinforced support beams in

accordance with paragraph BB 2A of

Eurocopter France Telex Service No. 10011,

dated February 24, 1995.

(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, Rotorcraft

Standards Staff, FAA, Rotorcraft Directorate.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Rotorcraft Standards Staff.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(e) The inspection and repair or

modification, if necessary, shall be done in

accordance with the Accomplishment

Instructions in Eurocopter France Service

Bulletin No. 05.00.36, Rev. 1, dated

December 16, 1996, and paragraphs BB and

BB 2A of Eurocopter France Telex Service

No. 10011, dated February 24, 1995. This
30380 Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations

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

American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. Copies may be inspected at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

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

(f) This amendment becomes effective on

July 9, 1998.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 95–068–017(B) and AD 95–067–

038(B), both dated April 12, 1995.

Issued in Fort Worth, Texas, on May 28,

1998.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 98–14929 Filed 6–3–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–AGL–61]

Modification of Class D Airspace;

Minot AFB, ND; and Class E Airspace;

Minot, ND; Correction

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule; correction.

SUMMARY: This action corrects one error

in the legal description of a final rule

that was published in the Federal

Register on March 23, 1998 (63 FR

13778), Airspace Docket No. 97–AGL–

61. The final rule modified Class D

Airspace at Minot AFB, ND, and

modified Class E Airspace at Minot, ND.

EFFECTIVE DATE: 9091 UTC, June 18,

1998.

FOR FURTHER INFORMATION CONTACT:

Michelle M. Behm, Air Traffic Division,

Airspace Branch, AGL–520, Federal

Aviation Administration, 2300 East

Devon Avenue, Des Plaines, IL 60018,

telephone: (847) 294–7477.

SUPPLEMENTARY INFORMATION:

History

Federal Register Document 98–7405,

Airspace Docket No. 97–AGL–61,

published on March 23, 1998 (63 FR

13778) rule modified Class D Airspace

at Minot AFB, ND, and modified Class

E Airspace at Minot, ND. One error was

discovered in the legal description for

the Class E airspace for Minot, ND. This

action corrects that error.

Correction to Final Rule

Accordingly, pursuant to the

authority delegated to me, the legal

description for the Class E airspace

Minot, ND, as published in the Federal

Register March 23, 1998 (63 FR 13778),

(FR Doc. 98–7405), is corrected as

follows:

PART 71—[CORRECTED]

§ 71.7 [Corrected]

AGL ND E5 Minot, ND [Corrected]

On page 13779, in the Class E airspace

designation for Minot, ND, incorporated by

reference in § 71.1, in column 2, line 11 from

top of column, the phrase ‘‘Deering TACAN

292 deg. radial’’ to read ‘‘Deering TACAN

312 degree radial’’.

Issued in Des Plaines, IL on May 20, 1998.

Maureen Woods,

Manager, Air Traffic Division, Great Lakes

Region.

[FR Doc. 98–14753 Filed 6–3–98; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ASO–28]

RIN 2120–AA66

Realignment of Jet Route J–66;

Tennessee

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This action realigns Jet Route

66 (J–66) in the State of Tennessee.

Realigning J–66 is necessary because the

route is aligned on a radial of the

Memphis Very High Frequency

Omnidirectional Range/Tactical Air

Navigation (VORTAC) and that

VORTAC will be moved south of its

present position. This action will ensure

that air traffic operations along the jet

route are not interrupted by the

relocation of the navigational aid. This

action coincides with the relocation of

the Memphis VORTAC.

DATES: Effective 0901 UTC, August 13,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 20, 1998.

ADDRESSES: Send comments on the rule

in triplicate to: Manager, Air Traffic

Division, ASO–500, Docket No. 97–

ASO–28, Federal Aviation

Administration, P.O. Box 20636,

Atlanta, GA 30320. Comments may be

also sent electronically to the following

Internet address: 9-Direct RuleComments@faa.dot.gov. Comments

delivered must be marked Airspace

Docket No. 97–ASO–28.

The official docket may be examined

in the Rules Docket, Office of the Chief

Counsel, Room 916G, 800 Independence

Avenue, SW., Washington, DC,

weekdays, except Federal holidays,

between 8:30 a.m. and 5:00 p.m.

FOR FURTHER INFORMATION CONTACT:

Patricia P. Crawford, Airspace and Rules

Division, ATA–400, Office of Air Traffic

Airspace Management, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone: (202) 267–8783.

SUPPLEMENTARY INFORMATION:

The Rule

The FAA is amending 14 CFR part 71

to modify J–66 in the State of

Tennessee. Realigning J–66 will ensure

that air traffic operations are not

interrupted by virtue of relocating the

Memphis VORTAC. The effective date

of this direct final rule coincides with

the effective date of relocation of the

Memphis VORTAC.

Incorporation by Reference

Jet route designations are published in

paragraph 2004 of FAA Order 7400.9E,

dated September 10, 1997, and effective

September 16, 1997, which is

incorporated by reference in 14 CFR

71.1. The jet route designation listed in

this document will be published

subsequently in the Order.

The Direct Final Rule Procedure

The FAA anticipates that this

regulation will not result in adverse or

negative comment and therefore is

issuing it as a direct final rule. Effective

August 13, 1998, the FAA will relocate

the Memphis, TN, VORTAC. Currently,

J–66 is aligned on a radial of the

Memphis VORTAC. The Memphis

VORTAC is scheduled to be relocated

2.85 miles south of its present position;

therefore, realigning J–66 is necessary to

ensure that air traffic operations are not

interrupted. The jet route will be

realigned with the Memphis VORTAC at

the new location. Unless a written

adverse or negative comment, or a

written notice of intent to submit an

adverse or negative comment is received

within the comment period, the

regulation will become effective on the

date specified above. After the close of

the comment period, the FAA will

publish a document in the Federal

Register indicating that no adverse or

negative comments were received and

confirming the date on which the direct

final rule will become effective. If the

FAA does receive, within the comment