This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

40359

Vol. 63, No. 145

Wednesday, July 29, 1998

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–72–AD; Amendment 39–

10677; AD 98–16–03]

RIN 2120–AA64

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Models TB9

and TB10 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain SOCATA—Groupe

AEROSPATIALE (Socata) Models TB9

and TB10 airplanes. This AD requires

repetitively inspecting the wing front

attachments on the wing and fuselage

sides for cracks, and repetitively

incorporating a certain modification kit

(type of kit and time of incorporation

depends on whether cracks are found

during the inspection). This AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

France. The actions specified by this AD

are intended to prevent structural

failure of the wing front attachments

caused by fatigue cracking, which could

result in the wing separating from the

airplane if the airplane is operated with

cracked wing front attachments over an

extended period of time.

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

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–

1160; facsimile: (954) 964–4141. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 95–CE–72–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.

Karl Schletzbaum, Aerospace Engineer,

FAA, Small Airplane Directorate, 1201

Walnut Street, suite 900, Kansas City,

Missouri 64106; telephone: (816) 426–

6934; facsimile: (816) 426–2169.

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 certain Socata Models TB9 and

TB10 airplanes was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on May 22, 1998

(63 FR 28299). The NPRM proposed to

require repetitively inspecting the wing

front attachments on the wing and

fuselage sides for cracks, and

repetitively incorporating a certain

modification kit (type of kit and time of

incorporation depends on whether

cracks are found during the inspection).

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Socata Service Bulletin

No. SB 10–081–57, Amendment 1, dated

August 1996. Accomplishment of the

proposed modifications, as applicable,

would be required in accordance with

the Technical Instructions for

Modification included with each kit.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for France.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received.

Comment Disposition

Socata states that reference to one of

the service documents was incorrectly

referenced in the NPRM. In particular,

Socata Technical Instruction of

Modification OPT 109081–53 was

referenced as Socata Technical

Instruction of Modification OPT

109181–53 in both paragraphs (e)(1) and

(e)(2) of the AD.

The FAA concurs that this service

document was incorrectly referenced.

This was inadvertent on the FAA’s part.

The final rule will include the correct

reference to this document.

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 113 airplanes

in the U.S. registry will be affected by

this AD. The initial inspection will take

approximately 3 workhours per airplane

to accomplish, at an average labor rate

of approximately $60 an hour. Based on

these figures, the total cost impact of

this inspection on U.S. operators is

estimated to be $20,340, or $180 per

airplane.

The initial modifications will take

approximately 32 workhours to

accomplish, at an average labor rate of

$60 per hour. Parts cost approximately

$1,125 per airplane. Based on these

figures, the total cost impact of the

initial modifications on U.S. operators is

estimated to be $344,085, or $3,045 per

airplane.

These figures only take into account

the costs of the initial inspection and

initial modifications. The FAA has no

way of determining the number of

repetitive inspections and modifications

each owner/operator of the affected

airplanes will incur.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the
40360 Federal Register / Vol. 63, No. 145 /Wednesday, July 29, 1998 /Rules and Regulations

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:

98–16–03 Socata—Groupe Aerospatiale:

Amendment 39–10677; Docket No. 95–CE–

72–AD.

Applicability: The following airplane

models and serial numbers, certificated in

any category:

Model TB9, serial numbers 1 through 9999;

and

Model TB10, serial numbers 1 through 803,

805, 806, 809 through 815, 820, 821, and 822.

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 (g) 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 structural failure of the wing

front attachments caused by fatigue cracking,

which could result in the wing separating

from the airplane if the airplane is operated

with cracked wing front attachments over an

extended period of time, accomplish the

following:

Note 2: The compliance times of this AD

are presented in landings instead of hours

time-in-service (TIS). If the number of

landings is unknown, hours TIS may be used

by multiplying the number of hours TIS by

1.5.

(a) For all affected airplanes, upon

accumulating 3,000 landings on the 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 3,000 landings,

inspect the wing front attachments (both the

wing sides and fuselage sides) in accordance

with Socata Service Bulletin No. SB 10–081–

57, Amendment 1, dated August 1996.

(b) For all affected airplanes, accomplish

the following on the wing front attachments

on the wing sides:

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

attachments on the wing 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 6,000

landings provided no cracks are found during

any inspection required by paragraph (a) of

this AD, incorporate Modification Kit OPT10

911000 in accordance with 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.

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

attachments on the wing sides during any

inspection required by paragraph (a) of this

AD, prior to further flight, incorporate

Modification Kit OPT10 911000 in

accordance with Socata Technical Instruction

No. 9110. Incorporate this kit at intervals not

to exceed 6,000 landings thereafter provided

no cracks are found during any inspection

required by paragraph (a) of this AD.

(c) For Models TB9 and TB10 airplanes,

with a serial number in the range of 1

through 399, or with a serial number of 413;

that do not have either Socata Service Letter

(SL) 10–14 incorporated or Socata

Modification Kit OPT10 908100

incorporated, 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 6,000 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

919800 in accordance with Socata Technical

Instruction of Modification OPT10 9198–53,

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 919800 in

accordance with Socata Technical Instruction

of Modification OPT10 9198–53, 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.

(d) For Models TB9 and TB10 airplanes,

with a serial number in the range of 1

through 399, or with a serial number of 413;

that have either Socata Service Letter (SL)

10–14 incorporated or Socata Modification

Kit OPT10 908100 incorporated, 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

919800 in accordance with Socata Technical

Instruction of Modification OPT10 9198–53,

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 919800 in

accordance with Socata Technical Instruction

of Modification OPT10 9198–53, dated

October 1994. Incorporate this kit at intervals

not to exceed 12,000 landings thereafter

provided no cracks are found during any
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,