19172 Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules

and other means to be used to

demonstrate compliance with the

requirements of 10 CFR parts 11 and 73,

if applicable.

* * * * *

PART 70—DOMESTIC LICENSING OF

SPECIAL NUCLEAR MATERIAL

3. The authority citation for part 70

continues to read as follows:

Authority: Secs. 51, 53, 161, 182, 183, 68

Stat. 929, 930, 948, 953, 954, as amended,

sec. 234, 83 Stat. 444, as amended (42 U.S.C.

2071, 2073, 2201, 2232, 2233, 2282); secs.

201, as amended, 202, 204, 206, 88 Stat.

1242, as amended, 1244, 1245, 1246 (42

U.S.C. 5841, 5842, 5845, 5846).

Sections 70.1(c) and 70.20a(b) also issued

under secs. 135, 141, Pub. L. 97–425, 96 Stat.

2232, 2241 (42 U.S.C. 10155, 10161). Section

70.7 also issued under Pub. L. 95–601, sec.

10, 92 Stat. 2951 as amended by Pub. L. 102–

486, sec. 2902, 106 Stat. 3123 (42 U.S.C.

5851). Section 70.21(g) also issued under sec.

122, 68 Stat. 939 (42 U.S.C. 2152). Section

70.31 also issued under sec. 57d, Pub. L. 93–

377, 88 Stat. 475 (42 U.S.C. 2077). Sections

70.36 and 70.44 also issued under sec. 184,

68 Stat. 954, as amended (42 U.S.C. 2234).

Section 70.61 also issued under secs. 186,

187, 68 Stat. 955 (42 U.S.C. 2236, 2237).

Section 70.62 also issued under sec. 108, 68

Stat. 939, as amended (42 U.S.C. 2138).

4. In § 70.22, paragraph (h)(1) is

revised to read as follows:

§ 70.22 Contents of applications.

* * * * *

(h)(1) Each application for a license to

possess or use at any site or contiguous

sites subject to licensee control, a

formula quantity of strategic special

nuclear material as defined in § 70.4

other than a license for possession or

use of this material in the operation of

a nuclear reactor licensed pursuant to

part 50 of this chapter, must include a

physical security plan. The plan must

describe how the applicant will meet

the applicable requirements of part 73 of

this chapter in the conduct of the

activity to be licensed, including the

identification and description of jobs as

required by 10 CFR 11.11(a). The plan

must list tests, inspections, audits, and

other means to be used to demonstrate

compliance with the requirements of 10

CFR parts 11 and 73, if applicable.

* * * * *

Dated at Rockville, Maryland, this 5th day

of April, 1995.

For the Nuclear Regulatory Commission.

James M. Taylor,

Executive Director for Operations.

[FR Doc. 95–9369 Filed 4–14–95; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–CE–33–AD]

Airworthiness Directives; Beech

Aircraft Corporation Model 1900D

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 Beech Aircraft

Corporation (Beech) Model 1900D

airplanes. The proposed action would

require inspecting the cabin partition to

ensure that a right-hand forward

partition bracket exists on certain

airplanes, installing this bracket if it

does not exist, and improving the righthand forward partition installation on

all affected airplanes. Deficiencies

found during a structural analysis of the

cabin partition prompted the proposed

action. The actions specified by the

proposed AD are intended to prevent

cabin partition failure because of a

structural deficiency, which, if not

detected and corrected, could cause

passenger injury if the partition could

not withstand the load incurred with

the baggage compartment loaded to its

250-pound limit.

DATES: Comments must be received on

or before June 19, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 94–CE–33–

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

Beech Aircraft Corporation, P.O. Box 85,

Wichita, Kansas 67201–0085. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Steve Potter, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4124; facsimile

(316) 946–4407.

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. 94–CE–33–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

Assistant Chief Counsel, Attention:

Rules Docket No. 94–CE–33–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

The FAA has received a report from

the Beech Aircraft Corporation (Beech)

of a structural deficiency on Model

1900D airplanes. Beech reports that

certain Model 1900D airplanes may be

missing a bracket on the right-hand

forward cabin partition, and that, even

with this bracket installed, the airplane

model design may not be capable of

withstanding the load incurred with the

baggage compartment loaded to its 250-

pound limit. This condition, if not

detected and corrected, could result in

passenger injury if this load is incurred

with the airplane occupied.

Beech has issued Service Bulletin

(SB) No. 2556, Revision 1, dated

February 1995, which references Kit

Drawing No. 129–5007 and Kit No. 129–

5007–1 S. Kit Drawing No. 129–5007

specifies the design location of the

bracket that may be missing, and Kit No.

129–5007–1 S includes parts and

instructions necessary to improve the
Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules 19173

right-hand forward partition

installation.

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that (1) a

structural improvement should be

added to the right-hand forward

partition on Beech Model 1900D

airplanes; and (2) AD action should be

taken to prevent cabin partition failure

because of a structural deficiency,

which, if not detected and corrected,

could cause passenger injury if the

partition could not withstand the load

incurred with the baggage compartment

loaded to its 250-pound limit.

Since an unsafe condition has been

identified that is likely to exist or

develop in other Beech Model 1900D

airplanes of the same type design, the

proposed AD would require inspecting

the right-hand forward partition on

certain serial number airplanes to

ensure that the partition bracket exists,

installing this bracket if it does not

exist, and incorporating a structural

improvement to the right-hand forward

partition on all affected airplanes. The

proposed action would be accomplished

in accordance with Kit Drawing No.

129–5007 and the instructions to Kit No.

29–5007–1 S, as referenced in Beech SB

No. 2556, Revision 1, dated February

1995.

The FAA estimates that 73 airplanes

in the U.S. registry would be affected by

the proposed inspection and possible

installation and 91 airplanes in the U.S.

registry would be affected by the

proposed modification. The proposed

inspection and possible installation

would take approximately 5 workhours

per airplane to accomplish and the

proposed modification would take

approximately 5 workhours per airplane

to accomplish, with a labor rate of

approximately $60 an hour. Parts for the

proposed modification cost

approximately $650 per airplane. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $108,350. This figure is

based on the assumption that no owner/

operator of the affected airplanes has

accomplished the proposed

modification and no airplane has a

right-hand forward partition bracket

installed and would need one installed.

Beech has informed the FAA that it

has distributed parts (Kit No. 129–5007–

1 S) to accommodate approximately 58

of the affected airplanes. Assuming that

each of these distributed kits is

incorporated on one of the affected

airplanes, the cost of the proposed AD

would be further reduced by $55,100

from $108,350 to $53,250.

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

Beech Aircraft Corporation: Docket No. 94–

CE–33–AD.

Applicability: Model 1900D airplanes,

serial numbers UE–2 through UE–92,

certificated in any category.

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 use the authority

provided in paragraph (d) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any aircraft from the

applicability of this AD.

Compliance: Required within the next 400

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent cabin partition failure because

of a structural deficiency, which, if not

detected and corrected, could cause

passenger injury if the partition could not

withstand the load incurred with the baggage

compartment loaded to its 250-pound limit,

accomplish the following:

(a) For airplanes incorporating one of the

following serial numbers: UE–2 through UE–

68, UE–70 through UE–72, or UE–74 through

UE–77, inspect the cabin partition to ensure

that a right-hand partition bracket, part

number (P/N) 129–530043–79, exists. If this

bracket does not exist, prior to further flight,

install this bracket with P/N MS27039–1–09

screws and P/N AN960PD10 washers in

accordance with Kit Drawing No. 129–5007

as referenced in Beech SB No. 2556, Revision

1, dated February 1995.

(b) For all affected serial numbers (UE–2

through UE–92), improve the right-hand

forward partition installation in accordance

with the instructions to Kit No. 129–5007–1

S as referenced in Beech SB No. 2556,

Revision 1, dated February 1995.

(c) Special flight permits may be issued in

accordance with §§ 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, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the Beech Aircraft

Corporation, P.O. Box 85, Wichita, Kansas

67201–0085; or may examine this document

at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.
19174 Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules

Issued in Kansas City, Missouri, on April

11, 1995.

Dwight A. Young,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–9343 Filed 4–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–21–AD]

Airworthiness Directives; Piper Aircraft

Corporation Model PA–31T2 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 Piper

Aircraft Corporation (Piper) Model PA–

31T2 airplanes that have a Parker

Hannifin Wheel and Brake Conversion

Kit 199–111 installed in accordance

with Supplemental Type Certificate

(STC) SA599GL. The proposed action

would require rerouting the landing gear

emergency extension air line. Three

incidents of the brake cylinder

contacting the landing gear emergency

extension air line on both wheels

prompted the proposed action. The

actions specified by the proposed AD

are intended to prevent the brake

cylinder from chafing against the

landing gear emergency extension air

line when the gear is in the up and

locked position, which, if not detected

and corrected, could result in damage to

the air line and subsequent loss of

emergency gear extension capability.

DATES: Comments must be received on

or before June 19, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 95–CE–21–

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

Parker Hannifan Corporation, Aircraft

Wheel & Brake, 1160 Center Road, P.O.

Box 158, Avon, Ohio 44011; telephone

(216) 937–6211; facsimile (216) 937–

5409. This information also may be

examined at the Rules Docket at the

address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Nick Miller, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, 2300 East Devon Avenue, Room

232, Des Plaines, Illinois 60018;

telephone (708) 294–7379; facsimile

(708) 294–7834; or Mr. Charles Perry,

Aerospace Engineer, FAA, Atlanta

Aircraft Certification Office, Campus

Building, 1701 Columbia Avenue, suite

2–160, College Park, Georgia 30337–

2748; telephone (404) 305–7362;

facsimile (404) 305–7348.

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–21–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

Assistant Chief Counsel, Attention:

Rules Docket No. 95–CE–21–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

The FAA has received three reports of

the brake cylinder chafing against the

landing gear emergency extension air

line of both wheels on Piper Model PA–

31T2 airplanes that have a Parker

Hannifin Wheel and Brake Conversion

Kit 199–111 installed in accordance

with STC SA599GL. As the brake

linings become worn through regular

usage, the brake cylinder repositions.

Then, when the landing gear is in the up

and locked position, the brake cylinder

chafes against the air line. This

condition, if not detected and corrected,

could result in damage to the landing

gear emergency extension air line and

subsequent loss of emergency gear

extension capability.

Parker Hannifan has issued Service

Bulletin SB7034, dated April 23, 1994,

which specifies procedures for rerouting

the landing gear emergency extension

air line on these Piper Model PA–31T2

airplanes that have a Parker Hannifin

Wheel and Brake Conversion Kit 199–

111 installed in accordance with STC

SA599GL.

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that AD action

should be taken to prevent the brake

cylinder from chafing against the

landing gear emergency extension air

line when the gear is in the up and

locked position, which, if not detected

and corrected, could result in damage to

the air line and subsequent loss of

emergency gear extension capability.

Since an unsafe condition has been

identified that is likely to exist or

develop in other Piper Model PA–31T2

airplanes of the same type design that

have a Parker Hannifin Wheel and Brake

Conversion Kit 199–111 installed in

accordance with STC SA599GL, the

proposed AD would require rerouting

the landing gear emergency extension

air line. The proposed action would be

accomplished in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Parker Hannifan Service

Bulletin SB7034, dated April 23, 1994.

The FAA estimates that there are 62

Piper Model PA–31T2 airplanes in the

U.S. registry that could incorporate a

Parker Hannifin Wheel and Brake

Conversion Kit 199–111 (in accordance

with STC SA599GL), that it would take

approximately 4 workhours per airplane

to accomplish the proposed action, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $20 per airplane. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators

could be as much as $16,120 if all

affected airplanes had the referenced

conversion kit installed.

Parker Hannifan has informed the

FAA that it has distributed 31 kits to

Piper Model PA–31T2 airplane owners/

operators. Based on each of the 31 kits

being incorporated on an affected

airplane, the cost impact of the

proposed AD on U.S. owners and

operators would be reduced 50 percent

from $16,120 to $8,060. The reduction