Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules 28299

(g) This amendment revises AD 97–01–01,

Amendment 39–9872, which superseded AD

95–20–07, Amendment 39–9386.

Appendix to Docket No. 96–CE–09–AD

Information to Determine Main Gear

Sidebrace Stud Assembly Part Number (P/N)

—The P/N 95643–00/-01/-02/-03 bracket

assembly contains the 9/16-inch diameter

main gear sidebrace stud, P/N 95299–00/-

02, and a two-piece bushing, P/N 67026–

6.

—The P/N 95643–06/-07/-08/-09 bracket

assembly contains the 5/8-inch diameter

main gear sidebrace stud, P/N 78717–02,

and a one-piece bushing, P/N 67026-12.

—Both the one-piece and the two-piece

bushing have a visible portion of the

bushing flange, i.e., bushing shoulder.

—Whether a one-piece or two-piece bushing

is installed may be determined by

measuring the outside diameter of the

bushing flange with a micrometer (jaws of

the caliper must be 3/32-inch or less). The

two-piece bushing will have an outside

diameter of 1.00 inch and the one-piece

bushing will have an outside diameter of

1.128 to 1.130 inches. This measurement is

not valid for the following airplanes:

Model Serial Nos.

PA–28R–180 .... 28R–30004 through 28–

31270.

PA–28R–200 .... 28R–35001 through 28R–

35820, and 28R–

7135001 through 28R–

7135062.

The main gear sidebrace studs on these

airplanes will require removal to determine

the P/N installed.

—The one-piece bushing contains a visible

chamfer in the center of the bushing, and

the chamfer in the two-piece bushing is not

visible when the stud is installed.

—If P/N 95643–00/-01/-02/-03 bracket

assembly is installed or the above

information cannot be utilized, the main

gear sidebrace stud will need to be

removed from the bracket to determine the

shank diameter and main gear sidebrace

stud P/N.

—P/N 95299–00 and P/N 95299–02 main

gear sidebrace studs are 9/16-inch in

diameter.

—P/N 78717–00 main gear sidebrace studs

are 5/8-inch in diameter.

—P/N 95643–00/-01/-02/-03 bracket

assembly may have been modified to

accommodate the 5/8-inch diameter main

gear sidebrace stud, P/N 78717–02.

—The embossed number of 95363 on the

bracket forging is not the bracket assembly

P/N.

—The bracket assemblies identified with

casting number 67073–2 or 67073–3

contain a 9/16-inch diameter main gear

sidebrace stud, P/N 67543, and two-piece

bushing, P/N 67026–2 and 67026–3.

—Model PA–28R–180 airplanes, serial

numbers 28R-30004 through 28R–31270;

and Model PA–28R–200 airplanes, serial

numbers 28R–35001 through 28R–35820

and 28R–7135001 through 28R–7135062,

are equipped from the factory with bracket

assemblies identified with casting number

67073–2 and 67073–3.

—P/N 67543 main gear sidebrace studs are 9/

16-inch in diameter.

Issued in Kansas City, Missouri, on May

14, 1998.

Michael Gallagher,

Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–13656 Filed 5–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–72–AD]

RIN 2120–AA64

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Models TB9

and TB10 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

SOCATA—Groupe AEROSPATIALE

(Socata) Models TB9 and TB10

airplanes. The proposed AD would

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).

The proposed AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for France. The

actions specified by the proposed 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: Comments must be received on

or before June 25, 1998.

ADDRESSES: Submit comments in

triplicate to 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. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from the

SOCATA—Groupe AEROSPATIALE,

Socata Product Support, Aeroport

Tarbes-Ossun-Lourdes, 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

information also may be examined at

the Rules Docket at the address above.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 95–CE–72–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

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.
28300 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on all Socata Model

TB9 airplanes and certain Socata Model

TB10 airplanes. The DGAC reports 15

cases of cracks found on the wing front

attachments of the referenced airplanes.

This condition, if not detected and

corrected in a timely manner, could

result in structural failure of the wing

attachment and the wing separating

from the airplane if the airplane is

operated with cracked wing front

attachments over an extended period of

time.

Relevant Service Information

Socata has issued Service Bulletin No.

SB 10–081–57, Amendment 1, dated

August 1996, which specifies

procedures for inspecting the wing front

attachments on the wing and fuselage

sides for cracks. Also included in this

service bulletin is reference to certain

wing front attachment kits that should

be incorporated on the Socata Models

TB9 and TB10, depending on the

inspection results. The procedures for

incorporating the modification kits are

in the Technical Instructions for

Modification included with each kit.

The DGAC classified this service

bulletin as mandatory and issued DGAC

AD 94–264(A), dated December 7, 1994,

in order to assure the continued

airworthiness of these airplanes in

France.

The FAA’s Determination

This airplane model is manufactured

in France and is type certificated for

operation in the United States under the

provisions of § 21.29 of the Federal

Aviation Regulations (14 CFR 21.29)

and the applicable bilateral

airworthiness agreement.

Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC;

reviewed all available information,

including the service information

referenced above; and determined that

AD action is necessary for products of

this type design that are certificated for

operation in the United States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Socata Models TB9 and

TB10 airplanes of the same type design

registered in the United States, the FAA

is proposing AD action. The proposed

AD would 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 inspections 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.

Cost Impact

The FAA estimates that 113 airplanes

in the U.S. registry would be affected by

the proposed AD.

The proposed inspection would 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 the

proposed inspection on U.S. operators is

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

airplane.

The proposed modification would

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

proposed modifications on U.S.

operators is estimated to be $344,085, or

$3,045 per airplane.

Regulatory Impact

The regulations proposed herein

would 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

proposal would 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) if

promulgated, 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 draft

regulatory evaluation prepared for this

action has been placed 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Socata—Groupe Aerospatiale: 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,
Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules 28301

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 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

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 9181–53,

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 9181–53, 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 aleady 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.

Note 5: The subject of this AD is addressed

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

1994.

Issued in Kansas City, Missouri, on May

14, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–13653 Filed 5–21–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF HEALTH AND

HUMAN SERVICES

Food and Drug Administration

21 CFR Parts 315 and 601

[Docket No. 98N–0040]

Regulations for In Vivo

Radiopharmaceuticals Used for

Diagnosis and Monitoring

AGENCY: Food and Drug Administration,

HHS.

ACTION: Proposed rule.

SUMMARY: The Food and Drug

Administration (FDA), in response to

the requirements of the Food and Drug

Administration Modernization Act of

1997 (FDAMA), is proposing to amend

the drug and biologics regulations by

adding provisions that would clarify the

evaluation and approval of in vivo