28294 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules

§ 1160.208 Powers of the Board.

* * * * *

(g) To select committees and

subcommittees, to adopt bylaws, and to

adopt such rules for the conduct of its

business as it may deem advisable; and

the Board may establish working

committees of persons other than Board

members;

* * * * *

5. In § 1160.505, the text is designated

paragraph (a) and a new paragraph (b)

is added to read as follows:

§ 1160.505 Patents, copyrights, inventions

and publications.

* * * * *

(b) Should patents, copyrights,

inventions, and publications be

developed through the use of funds

collected by the Board under this

subpart, and funds contributed by

another organization or person,

ownership and related rights to such

patents, copyrights, inventions, and

publications shall be determined by the

agreement between the Board and the

party contributing funds towards the

development of such patent, copyright,

invention, and publication in a manner

consistent with paragraph (a) of this

section.

Dated: May 18, 1998.

Enrique E. Figueroa,

Administrator, Agricultural Marketing

Service.

[FR Doc. 98–13772 Filed 5–21–98; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF AGRICULTURE

7 CFR Parts 3015, 3016 and 3019

RIN 0503–AA16

Uniform Administrative Requirements

for Grants and Cooperative

Agreements to State and Local

Governments and Uniform

Administrative Requirements for

Grants and Agreements with

Institutions of Higher Education,

Hospitals, and Other Non-Profit

Organizations

AGENCY: Department of Agriculture,

USDA.

ACTION: Notice of proposed rulemaking;

extension of comment period.

SUMMARY: On February 17, 1998, USDA

published in the Federal Register (63

FR 7734) a Notice of Proposed

Rulemaking (NPRM) in which USDA

proposed to revise its grants

management regulations in order to

bring the entitlement programs it

administers under the same regulations

that already apply to nonentitlement

programs and identify exceptions to

these general rules that apply only to

entitlement programs. This document

extends the comment period for that

NPRM in order to give interested parties

ample time to comment.

DATES: The period for written comments

is extended from May 19, 1998 to June

18, 1998.

ADDRESSES: Comments must be mailed

or faxed to Gerald Miske, Supervisory

Management Analyst, Fiscal Policy

Division, Office of the Chief Financial

Officer, USDA, Room 3022 South

Building, 1400 Independence Avenue,

SW, Washington, D.C. 20250; FAX (202)

690–1529. Written comments may be

inspected at the above address from 8:00

a.m. to 5:00 p.m. A copy of the

Regulatory Cost/Benefit Assessment

referenced in the Regulatory Impact

Analysis section of this preamble can be

obtained from Gerald Miske,

Supervisory Management Analyst,

Fiscal Policy Division, Office of the

Chief Financial Officer, USDA, Room

3022 South Building, 1400

Independence Avenue, SW,

Washington, D.C. 20250. This

assessment may be examined at the

same address.

FOR FURTHER INFORMATION CONTACT:

Gerald Miske, Supervisory Management

Analyst, Fiscal Policy Division, Office of

the Chief Financial Officer, USDA, at

the above address; telephone (202) 720–

1553.

Dated: May 19, 1998.

Sally Thompson,

Chief Financial Officer.

[FR Doc. 98–13773 Filed 5–21–98; 8:45 am]

BILLING CODE 3410–90–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–09–AD]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. PA–24, PA–28R,

PA–30, PA–32R, PA–34, and PA–39

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

revise Airworthiness Directive (AD) 97–

01–01, which currently requires

repetitively inspecting the main gear

sidebrace studs for cracks on The New

Piper Aircraft, Inc. (Piper) Models PA–

24, PA–28R, PA–30, PA–32R, PA-34,

and PA–39 series airplanes, and

replacing any main gear sidebrace stud

found cracked. The Federal Aviation

Administration (FAA) has approved

certain alternative methods of

compliance (AMOC) for AD 97–01-01,

and has determined that these AMOC’s

should be incorporated into the AD. The

proposed AD would retain all the

actions of AD 97–01–01, and would

incorporate certain AMOC’s as a way of

accomplishing the actions specified in

AD 97–01–01. The actions specified by

the proposed AD are intended to

prevent a main landing gear collapse

caused by main gear sidebrace stud

cracks, which could result in loss of

control of the airplane during landing

operations.

DATES: Comments must be received on

or before July 23, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 96-CE–09-

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.

Information that applies to the

proposed AD may be examined at the

Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

William O. Herderich, Aerospace

Engineer, FAA, Atlanta Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; telephone: (770) 703–6084;

facsimile: (770) 703–6097.

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
Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules 28295

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. 96-CE–09-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. 96-CE–09-AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

AD 97–01–01, Amendment 39–9872

(62 FR 10, January 2, 1997), currently

requires repetitively inspecting the main

gear sidebrace studs for cracks on Piper

Models PA–24, PA–28R, PA–30, PA–

32R, PA–34, and PA–39 series airplanes,

and replacing any main gear sidebrace

stud found cracked. The actions

specified by AD 97–01-01 are intended

to prevent a main landing gear collapse

caused by main gear sidebrace stud

cracks, which could result in loss of

control of the airplane during landing

operations.

Actions Since Issuance of Previous Rule

Since issuance of AD 97–01–01, the

FAA has approved alternative methods

of compliance for modifying the existing

bracket assembly as terminating action

for the repetitive inspection requirement

of that AD.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the subject described above,

the FAA has determined that (1) the

alternative methods of compliance

approved for modifying the existing

bracket assembly should be made

available as an option of complying

with the current AD; and (2) AD action

should be taken to prevent a main

landing gear collapse caused by main

gear sidebrace stud cracks, which could

result in loss of control of the airplane

during landing operations.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Piper Models PA-24,

PA–28R, PA–30, PA–32R, PA–34, and

PA–39 series airplanes of the same type

design, the FAA is proposing to revise

AD 97–01–01. The proposed AD would

retain all the actions of AD 97–01–01,

and would incorporate alternative

methods of compliance for modifying

the existing bracket assembly, as

terminating action for the repetitive

inspection requirement of that AD.

Cost Impact

The cost impact of the proposed AD

would be the same as is currently

required by AD 97–01–01. As a

courtesy, the FAA is reprinting that cost

information in the following paragraphs.

The FAA estimates that 13,200

airplanes in the U.S. registry would be

affected by the proposed AD, that it

would take approximately 5 workhours

per airplane to accomplish the proposed

action, and that the average labor rate is

approximately $60 an hour. Based on

these figures, the total cost impact of the

proposed inspection on U.S. operators is

estimated to be $3,960,000. This figure

represents the total cost of the proposed

initial inspection, and does not reflect

costs for any of the proposed repetitive

inspections or possible replacements.

The FAA has no way of determining

how many main gear side brace studs

may need replacement or how many

repetitive inspections each owner/

operator may incur over the life of the

airplane.

In addition, the proposed AD would

require the same inspections required

by AD 95–20–07 (which was superseded

by AD 97–01–01). The only difference

between the proposed AD and AD 95–

20–07 is the addition of an inspectionterminating modification option and the

elimination of (from the ‘‘Applicability’’

section of the AD) certain airplanes that

incorporate a certain main side brace

stud assembly. The proposed AD would

also not provide any additional cost

impacts over that already required by

AD 95–20–07.

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

removing Airworthiness Directive 97–

01–01, Amendment 39–9872 (62 FR 10,

January 2, 1997), and by adding a new

AD to read as follows:

The New Piper Aircraft, Inc.: Docket No. 96-

CE–09-AD; Revises AD 97–01–01,

Amendment 39–9872.

Applicability: The following airplane

models and serial numbers, certificated in

any category:

1. All serial numbers of Models PA–24,

PA–24–250, PA–24–260, PA–24–400, PA–30,

and PA–39 airplanes;

2. The following model and serial number

airplanes that are not equipped with a Piper

part number (P/N) 78717–02 (or FAAapproved equivalent part number) main gear

sidebrace stud in both right and left main

gear sidebrace bracket assemblies:

Model Serial Nos.

PA–28R–180 .... 28R–30002 through 28R–

31135, and 28R–

7130001 through 28R–

7130013.

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

35820, and 28R–

7135001 through 28R–

7635539.

PA–28R–201 .... 28R–7737002 through

28R–7737096.

PA–28R–201T .. 28R–7703001 through

28R–7703239.

PA–32R–300 .... 32R–7680001 through

32R–7780444.
28296 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules

Model Serial Nos.

PA–34–200 ....... All serial numbers.

PA–34–200T .... 34–7570001 through 34–

7770372.

Note 1: P/N 78717–02 sidebrace stud was

installed at manufacture on Piper Model PA–

34–200T airplanes, serial numbers 34–

7670325 through 34–7770372.

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 (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 initially as follows,

and thereafter as specified in the body of this

AD:

1. For the affected Models PA–28R–180,

PA–28R–200, PA–28R–201, PA–28R–201T,

PA–32R–300, PA–34–200, and PA–34–200T

airplanes: Within the next 100 hours time-inservice (TIS) after the effective date of this

AD; or, if the main gear sidebrace stud has

already been inspected or replaced as

specified in this AD, within 500 hours TIS

after the last inspection or replacement;

whichever occurs later.

2. For the affected Models PA–24, PA–24–

250, PA–24–260, PA–24–400, PA–30, and

PA–39 airplanes: Within the next 100 hours

TIS after the effective date of this AD; or, if

the main gear sidebrace stud has already

been inspected or replaced as specified in

this AD, within 1,000 hours TIS after the last

inspection or replacement; whichever occurs

later.

To prevent main landing gear (MLG)

collapse caused by main gear sidebrace stud

cracks, which could result in loss of control

of the airplane during landing operations,

accomplish the following:

Note 3: The paragraph structure of this AD

is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 4: (A), (B), (C), etc.

Level 2, Level 3, and Level 4 structures are

designations of the Level 1 paragraph they

immediately follow.

(a) Remove both the left and right main

gear sidebrace studs from the airplane in

accordance with the instructions contained

in the Landing Gear section of the

maintenance manual, and inspect each main

gear sidebrace stud for cracks, using Type I

(fluorescent) liquid penetrant or magnetic

particle inspection methods. Figure 1 of this

AD depicts the area of the sidebrace stud

shank where the sidebrace stud is to be

inspected.

Note 4: All affected Models PA–24 and

PA–24–250 airplanes were equipped at

manufacture with P/N 20829–00 main gear

sidebrace studs. All affected Models PA–24–

260, PA–24–400, PA–30, and PA–39

airplanes were equipped at manufacture with

P/N 22512–00 main gear sidebrace studs. The

Appendix included with this AD contains

information on determining the P/N of the

bracket assembly (which contains the main

gear side brace stud) on the affected PA–28R,

PA–32R, and PA–34 series airplanes.

BILLING CODE 4910–13–U
Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules 28297

BILLING CODE 4910–13–C
28298 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Proposed Rules

(1) For any main gear sidebrace stud found

cracked, prior to further flight, replace the

cracked stud with an FAA-approved

serviceable part (part numbers referenced in

the table in paragraph (b) of this AD or FAAapproved equivalent part number) in

accordance with the instructions contained

in the Landing Gear section of the applicable

maintenance manual, and accomplish one of

the following, as applicable:

(i) Reinspect (and replace as necessary) as

specified in paragraph (b) of this AD; or

(ii) For the affected Models PA–28R–180,

PA–28R–200, PA–28R–201, PA–28R–201T,

PA–32R–300, PA–34–200, and PA–34–200T

airplanes, the 9/16-inch main gear sidebrace

studs (P/N 95299–00, 95299–02, or P/N

67543, as applicable) are no longer

manufactured. Install a new main gear

sidebrace stud bracket assembly, P/N 95643–

06, P/N 95643–07, P/N 95643–08, or P/N

95643–09, as applicable. No repetitive

inspections will be required by this AD for

these affected airplane models when this

bracket assembly is installed; or

(iii) For the affected Models PA–28R–180,

PA–28R–200, PA–28R–201, PA–28R–201T,

PA–32R–300, PA–34–200, and PA–34–200T

airplanes, ream the existing two-piece

bushings to an inside diameter of .624-inch

to .625-inch, chamfer the head side of the

bushing to accommodate the radius in the

shank of the main gear sidebrace stud, and

install the 5⁄8-inch stud, P/N 78717–02. No

repetitive inspections will be required by this

AD when this action is accomplished. If the

bushings cannot be reamed while installed in

the bracket (i.e., the bushings are loose), then

install a main gear sidebrace bracket

assembly, P/N 95643–06, P/N 95643–07, P/N

95643–08, or P/N 95643–09, as applicable.

Models PA–28R–180 and PA–28R–200 with

serial numbers as specified in the Appendix

to this AD may be equipped with a bracket

casting identified with casting number

67073–2 or 67073–3 and may require the

following modification to P/N 78717–02 for

proper installation:

(A) Reduce the length of the stud to 1.688

± 0.15 inches;

(B) Add additional rolled threads to 1.125

± .015 inches from the flange. Note that the

stud is heat treated to 180 to 200 ksi; and

(C) Drill an additional roll pin hole 90

degrees to the existing hole, and

approximately 1.480 inches from the flange.

(iv) No repetitive inspections will be

required by this AD when a P/N 78717–02 (or

FAA-approved equivalent part number) main

gear sidebrace stud is installed in the existing

bracket assembly or when a bracket

assembly, P/N 95643–07 (or FAA-approved

equivalent part number), P/N 95643–08 (or

FAA-approved equivalent part number), or P/

N95643–09 (or FAA-approved equivalent

part number), as applicable, is installed.

(2) For any main gear sidebrace stud not

found cracked, prior to further flight,

reinstall the uncracked stud in accordance

with the instructions contained in the

Landing Gear section of the applicable

maintenance manual, and reinspect and

replace (as necessary) as specified in

paragraph (b) of this AD.

(b) Reinspect both the left and right main

gear sidebrace studs, using Type I

(fluorescent) liquid penetrant or magnetic

particle inspection methods. Replace any

cracked stud or reinstall any uncracked stud

as specified in paragraphs (a)(1) and (a)(2) of

this AD, respectively:

Part number installed

TIS inspection interval

(hours)

Model airplanes installed on

20829–00 (Piper parts) or FAA-approved equivalent part number.1,000 PA–24 and PA–24–250.

22512–00 (Piper parts) or FAA-approved equivalent part number.1,000 PA–24–260, PA–24–400, PA–30, and PA–39.

95299–00 or 95299–02 (Piper parts) or FAA-approved equivalent part number.500 PA–28R–180 and PA–28R–200 not equipped with casting number 67073–2 or 67073–3, PA–28R–201, PA–28R–201T, PA–

32R–300, PA–34–200, and PA–34–200T.

67543 (Piper parts) or FAA-approved equivalent part number .... 500 PA–28R–180 and PA–28R–200 equipped with casting number

67073–02 or 67073–03.

Note 5: Accomplishing the actions of this

AD does not affect the requirements of AD

77–13–21, Amendment 39–3093. The

tolerance inspection requirements of that AD

still apply for Piper PA–24, PA–30, and PA–

39 series airplanes.

(c) Owners/operators of the affected

Models PA–28R–180, PA–28R–200, PA–28R–

201, PA–28R–201T, PA–32R–300, PA–34–

200, and PA–34–200T airplanes may

accomplish one of the following at any time

to terminate the repetitive inspection

requirement of this AD:

(1) Install a main gear sidebrace bracket

assembly, P/N 95643–06 (or FAA-approved

equivalent part number), P/N 95643–07 (or

FAA-approved equivalent part number), P/N

95643–08 (or FAA-approved equivalent part

number), or P/N 95643–09 (or FAA-approved

equivalent part number), as applicable,

which contains the 5/8-inch diameter main

gear sidebrace stud, P/N 78717–02 (or FAAapproved equivalent part number), and the

one-piece bushing, P/N 67026–12 (or FAAapproved equivalent part number).

Accomplish these installations in accordance

with the instructions contained in the

Landing Gear section of the applicable

maintenance manual; or

(2) Ream the existing two-piece bushings to

an inside diameter of .624-inch to .625-inch,

chamfer the head side of the bushing to

accommodate the radius in the shank of the

main gear sidebrace stud, and install the 5/

8-inch stud, P/N 78717–02 (or FAA-approved

equivalent part number). No repetitive

inspections will be required by this AD when

this action is accomplished. If the bushings

cannot be reamed while installed in the

bracket (i.e., the bushings are loose), then

install a main gear sidebrace bracket

assembly, P/N 95643–06 (or FAA-approved

equivalent part number), P/N 95643–07 (or

FAA-approved equivalent part number), P/N

95643–08 (or FAA-approved equivalent part

number), or P/N 95643–09 (or FAA-approved

equivalent part number), as applicable.

Models PA–28R–180 and PA–28R–200 with

serial numbers as specified in the Appendix

to this AD may be equipped with a bracket

casting identified with casting number

67073–2 or 67073–3 and may require the

following modification to P/N 78717–02 (or

FAA-approved equivalent part number) for

proper installation:

(i) Reduce the length of the stud to 1.688

± 0.15 inches;

(ii) Add additional rolled threads to 1.125

± .015 inches from the flange. Note that the

stud is heat treated to 180 to 200 ksi; and

(iii) Drill an additional roll pin hole 90

degrees to the existing hole, and

approximately 1.480 inches from the flange.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(e) 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, Atlanta Aircraft Certification Office

(ACO), One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia 30349.

(1) The request shall be forwarded through

an appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Atlanta ACO.

(2) Alternative methods of compliance

approved in accordance with AD 97–01–01,

Amendment 39–9872 (revised by this action),

or AD 95–20–07, Amendment 39–9386

(superseded by AD 97–01–01), are

considered approved as alternative methods

of compliance with this AD.

Note 6: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(f) Information related to this AD may be

inspected at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri.
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.