Federal Register / Vol. 63, No. 145 /Wednesday, July 29, 1998 /Rules and Regulations 40361

inspection required by paragraph (a) of this

AD.

(e) For Models TB9 and TB10 airplanes,

with a serial number in the range of 400

through 412, or with a serial number in the

range of 414 through 9999; accomplish the

following on the wing front attachments on

the fuselage sides:

(1) If no cracks are found on the wing front

attachments on the fuselage sides during any

inspection required by paragraph (a) of this

AD, upon accumulating 12,000 landings on

these wing front attachments or within the

next 100 landings after the effective date of

this AD, whichever occurs later, and

thereafter at intervals not to exceed 12,000

landings provided no cracks are found during

any inspection required by paragraph (a) of

this AD, incorporate Modification Kit OPT10

908100 in accordance with Socata Technical

Instruction of Modification OPT10 9081–53,

Amendment 2, dated October 1994.

(2) If a crack(s) is found on the wing front

attachments on the fuselage sides during any

inspection required by paragraph (a) of this

AD, prior to further flight, incorporate

Modification Kit OPT10 908100 in

accordance with Socata Technical Instruction

of Modification OPT10 9081–53, Amendment

2, dated October 1994. Incorporate this kit at

intervals not to exceed 12,000 landings

thereafter provided no cracks are found

during any inspection required by paragraph

(a) of this AD.

Note 3: ‘‘Unless already accomplished’’

credit may be used if the kits that are

required by paragraphs (c)(1), (d)(1), and

(e)(1) of this AD are already incorporated on

the applicable airplanes. As specified in the

AD, repetitive incorporation of these kits

would still be required at intervals not to

exceed 12,000 landings provided no cracks

are found.

(f) 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.

(g) An alternative method of compliance or

adjustment of the initial or repetitive

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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(h) Questions or technical information

related to the service information referenced

in this AD should be directed to the

SOCATA—Groupe AEROSPATIALE, Socata

Product Support, Aeroport Tarbes-OssunLourdes, B P 930, 65009 Tarbes Cedex,

France; telephone: 33–5–62–41–76–52;

facsimile: 33–5–62–41–76–54; or the Product

Support Manager, SOCATA Aircraft, North

Perry Airport, 7501 Pembroke Road,

Pembroke Pines, Florida 33023; telephone:

(954) 893–1400; facsimile: (954) 964–1402.

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.

(i) The inspections required by this AD

shall be done in accordance with Socata

Service Bulletin No. SB 10–081–57,

Amendment 1, dated August 1996. The

modifications required by this AD shall be

done in accordance with Socata Technical

Instruction of Modification OPT10 9198–53,

dated October 1994; Socata Technical

Instruction of Modification OPT10 9081–53,

Amendment 2, dated October 1994; and

Socata Technical Instruction No. 9110, which

incorporates the following pages:

Pages Revision level Date

0 and 1 ................................................................................................................................ Amendment 1 ....................... January 31, 1992.

2 through 11 ........................................................................................................................ Original Issue ....................... October 1985.

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 SOCATA—Groupe AEROSPATIALE,

Socata Product Support, Aeroport TarbesOssun-Lourdes, B P 930, 65009 Tarbes

Cedex, France or the Product Support

Manager, SOCATA Aircraft, North Perry

Airport, 7501 Pembroke Road, Pembroke

Pines, Florida 33023. 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 5: The subject of this AD is addressed

in French AD 94–264(A), dated December 7,

1994.

(j) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 21,

1998.

Brian A. Hancock,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–20080 Filed 7–28–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–14–AD; Amendment 39–

10679; AD 98–16–04]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company 180, 182, and 185

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Cessna Aircraft Company

(Cessna) 180, 182, and 185 series

airplanes that have wing extension

supplemental type certificate (STC)

SA00276NY or supplemental type

approval (STA) SA93–136 incorporated.

This AD requires inspecting between

wing station (W.S.) 90 and W.S. 110 for

an angle stiffener at the lower wing spar

splice. If the angle stiffener is not

installed, this AD requires installing a

reinforcing strap. This AD is the result

of failed test results revealing that the

wings of these Cessna airplanes, without

the stiffener, do not meet the applicable

design requirements after being

modified by the above STC. The actions

specified by this AD are intended to

prevent wing failure during flight

caused by the absence of an angle

stiffener, which could cause loss of

control of the airplane.

DATES: Effective September 21, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

21, 1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Air Research Technology, Inc., 3440

McCarthy, Montreal, Quebec, Canada

H4K 2P5; telephone: (514) 337–7588;

facsimile: (514) 337–3293. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–14–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Sol Maroof, Aerospace Engineer, FAA,

New York Aircraft Certification Office,

10 Fifth Street, 3rd Floor, Valley Stream,
40362 Federal Register / Vol. 63, No. 145 /Wednesday, July 29, 1998 /Rules and Regulations

New York, 11581–1200; telephone:

(516) 256–7522; facsimile: (516) 568–

2716.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to all Cessna 180, 182, and 185

series airplanes equipped with wing

extension STC SA00276NY or STA

SA93–136 was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on March 19, 1998

(63 FR 13374). The NPRM proposed to

require inspecting the inside of the

underside of the wing, near Wing

Station (W.S.) 100, for an angle stiffener.

If an angle stiffener is not installed, the

proposed AD would require installing a

reinforcement strap along the lower

wing spar. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with Air

Research Technology Service Bulletin

No. SB–1–96, Issue 1, dated April 11,

1996.

The NPRM was the result of failed test

results revealing that the wings of these

Cessna airplanes, without the stiffener,

do not meet the applicable design

requirements after being modified by

the above STC or STA.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that there are 55

airplanes in the U.S. registry that will be

affected by this AD, that it will take

approximately 1 workhour for the initial

inspection and 7 workhours for the

installation of the reinforcement strap

per airplane, and that the average labor

rate is approximately $60 an hour. Parts

are supplied by the wing extension kit

manufacturer at no cost to the owner/

operator. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $26,400, or

$480 per airplane. The FAA has no way

to determine the number of owners/

operators who may have already

accomplished this action, and will

presume that none of the owners/

operators of the affected airplanes have

accomplished this action.

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 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:

98–16–04 Cessna Aircraft Company:

Amendment 39–10679; Docket No. 97–CE–

14–AD.

Applicability: The following airplane

models, all serial numbers, certificated in any

category, that have wing extension

supplemental type certificate (STC)

SA00276NY or supplemental type approval

(STA) SA93–136 incorporated.

Note 1: The STA is the Canadian version

of the U.S. STC.

Models: 180, 180A, 180B, 180C, 180D,

180E, 180F, 180G, 180H, 180J, 180K, 182,

182A, 182B, 182C, 182D, 182E, 182F, 182G,

182H, 182J, 182K, 182L, 182M, 182N, 182P,

182Q, 182R, 182S, R182, T182, TR182, 185,

185A, 185B, 185C, 185D, 185E, A185E,

A185F.

Note 2: 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 50

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent wing failure during flight

caused by the absence of an angle stiffener,

which could cause loss of control of the

airplane, accomplish the following:

(a) Inspect inside the left and right wings,

aft of the spar, closest to where the strut

connects to the wing, for an angle stiffener

along the lower spar cap between Wing

Station (W.S.) 90 and W.S. 110 in accordance

with Part A of the Accomplishment

Instructions of Air Research Technology, Inc.

(ART) Service Bulletin (SB) No. SB–1–96,

Issue 1, dated April 11, 1996.

(b) If an angle stiffener is not installed,

prior to further flight, install a stainless steel

reinforcement strap on the underside of each

wing, along the spar at W.S. 100.50 in

accordance with Part B of the

Accomplishment Instructions of ART SB No.

SB–1–96, Issue 1, dated April 11, 1996.

(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, New York Aircraft

Certification Office, 10 Fifth Street, 3rd Floor,

Valley Stream, New York, 11581–1200. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, New York Aircraft Certification

Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York Aircraft

Certification Office.
Federal Register / Vol. 63, No. 145 /Wednesday, July 29, 1998 /Rules and Regulations 40363

(e) The inspection and installation required

by this AD shall be done in accordance with

Air Research Technology Service Bulletin

No. SB–1–96, Issue 1, dated April 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 Air Research Technology, Inc., 3440

McCarthy, Montreal, Quebec, Canada H4K.

Copies may be inspected at the FAA, Central

Region, ffice 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.

(f) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 23,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–20225 Filed 7–28–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–ACE–6]

Amendment to Class D and Class E

Airspace; St. Joseph, MO

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; withdrawal.

SUMMARY: This action withdraws the

Direct final rule, request for comments

mending the Class D and Class E

airspace designations at St. Joseph, MO.

The Direct final rule, request for

comments is being withdrawn due to an

error in the original Docket 98–ACE–6

(63 FR 20528), published April 27, 1998

and a delay in publication of the

correction. Therefore, a determination

has been made to withdraw the Direct

final rule, request for comments and

resubmit it at a later date.

EFFECTIVE DATE: This withdrawal is

effective July 29, 1998.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Division,

Airspace Branch, ACE–520C, Federal

Aviation Administration, 601 East 12th

Street, Kansas City, MO 64106;

telephone: (816) 426–3408.

SUPPLEMENTARY INFORMATION:

The Direct Final Rule

On April 27, 1998, a Direct final rule,

request for comments was published in

the Federal Register to amend the Class

D and Class E airspace designations at

St. Joseph, MO. The Class E airspace,

700 feet and above was enlarged to

comply with the criteria specified in

FAA Order 7400.2D. The Class D and

Class E surface area designations were

revised to reflect a change to the Airport

Reference Point. The FAA has

encountered a delay in publication of an

extension of comment period and a

correction to Docket 98–ACE–6;

therefore, it is necessary to withdraw

the Direct final rule, request for

comments.

Conclusion

In consideration of the

aforementioned publication delay,

action is being taken to withdraw the

Direct final rule, request for comments

until an appropriate comment period is

provided.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Withdrawal of the Direct final rule,

request for comments

Accordingly, pursuant to the

authority delegated to me, Airspace

Docket No. 98–ACE–6, as published in

the Federal Register on April 27, 1998

(63 FR 20528), is hereby withdrawn.

Authority: 49 U.S.C. 40103, 40113, 40120;

E. O. 10854, 24 FR 9565, 3 CFR, 1959–1963

Comp., p. 389.

Issued in Kansas City, MO, on July 10,

1998.

Christopher R. Blum,

Acting Manager, Air Traffic Division, Central

Region.

[FR Doc. 98–20116 Filed 7–28–98; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Part 744

[Docket No. 970428099–8185–06]

RIN 0694–AB60

Additions to Entity List: Russian

Entities

AGENCY: Bureau of Export

Administration, Commerce.

ACTION: Final rule.

SUMMARY: The Export Administration

Regulations (EAR) provide that the

Bureau of Export Administration (BXA)

may inform exporters, individually or

through amendment to the EAR, that a

license is required for exports or

reexports to certain entities. The EAR

contains a list of such entities. This rule

adds to the entity list certain Russian

entities under investigation by the

Russian government for suspected

export control violations involving

weapons of mass destruction and

missile technology. Exports or reexports

of all items subject to the EAR to these

newly added entities now require a

license, and applications will be

reviewed with a presumption of denial.

EFFECTIVE DATE: This rule is effective

July 29, 1998.

FOR FURTHER INFORMATION CONTACT:

Eileen M. Albanese, Office of Exporter

Services, Bureau of Export

Administration, Telephone: (202) 482–

0436.

SUPPLEMENTARY INFORMATION:

Background

General Prohibition Five (§ 736.2(b)(5)

of the EAR) prohibits exports and

reexports to certain end-users or enduses (described in part 744 of the EAR)

without a license. In the form of

Supplement No. 4 to part 744, BXA

maintains an ‘‘Entity List’’ to provide

notice informing the public of certain

entities subject to such licensing

requirements. This rule adds certain

entities in Russia to this list. This rule

further adds a new § 744.10 describing

license requirements and review

standards for exports and reexports to

such entities.

Although the Export Administration

Act (EAA) expired on August 20, 1994,

the President invoked the International

Emergency Economic Powers Act and

continued in effect, to the extent

permitted by law, the provisions of the

EAA and the EAR in Executive Order

12924 of August 19, 1994, continued by

Presidential notices of August 15, 1995,

August 14, 1996, and August 15, 1997.

Rulemaking Requirements

1. This final rule has been determined

to be not significant for the purposes of

Executive Order 12866.

2. Notwithstanding any other

provision of law, no person is required

to respond to nor be subject to a penalty

for failure to comply with a collection

of information subject to the

requirements of the Paperwork

Reduction Act unless that collection of

information displays a current valid

OMB Control Number. This rule

involves a collection of information

requirements subject to the Paperwork

Reduction Act of 1980 (44 U.S.C. 3501

et seq.). This collection has been

approved by the Office of Management

and Budget under control number 0694–

0088.

3. This rule does not contain policies

with Federalism implications sufficient

to warrant preparation of a Federalism

assessment under Executive Order

12612.