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

25983

Vol. 60, No. 94

Tuesday, May 16, 1995

NUCLEAR REGULATORY

COMMISSION

10 CFR Part 20

RIN 3150–AD33

Low-Level Waste Shipment Manifest

Information and Reporting; Correction

AGENCY: Nuclear Regulatory

Commission.

ACTION: Final rule; correction.

SUMMARY: This document corrects a

notice appearing in the Federal Register

on Monday, March 27, 1995 (60 FR

15649). The action is necessary to

correct an error of omission. The text of

paragraph III E to Appendix G to Part 20

was inadvertently omitted from the

codified text of the final rule. The

wording for this paragraph is identical

to the existing corresponding paragraph

III E to Appendix F to Part 20. The text

paragraph was not changed in the

proposed rule and should have been

repeated verbatim as part of the new

Appendix G that was added in the final

rule.

EFFECTIVE DATE: This correction has the

same effective date as the final rule of

March 1, 1998.

FOR FURTHER INFORMATION CONTACT:

Mark Haisfield, Office of Nuclear

Regulatory Research, U.S. Nuclear

Regulatory Commission, Washington,

DC 20555–0001, telephone (301) 415–

6196.

List of Subjects in 10 CFR Part 20

Byproduct material, Criminal

penalties, Licensed material, Nuclear

materials, Nuclear power plants and

reactors, Occupational safety and

health, Packaging and containers,

Radiation protection, Reporting and

recordkeeping requirements, Source

material, Special nuclear material,

Waste treatment and disposal.

PART 20—STANDARDS FOR

PROTECTION AGAINST RADIATION

1. The authority citation for Part 20

continues to read as follows:

Authority: Secs. 53, 63, 65, 81, 103, 104,

161, 182, 186, 68 Stat. 930, 933, 935, 936,

937, 948, 953, 955 as amended (42 U.S.C.

2073, 2093, 2095, 2111, 2133, 2134, 2201,

2232, 2236), secs. 201, as amended, 202, 206,

88 Stat. 1242, as amended, 1244, 1246 (42

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

2. Paragraph III E is added to

Appendix G to Part 20 to read as

follows:

Appendix G to 10 CFR Part 20—

Requirements for Transfers of LowLevel Radioactive Waste Intended for

Disposal at Licensed Land Disposal

Facilities and Manifests

* * * * *

III. * * *

E. Any shipment or part of a shipment

for which acknowledgement is not

received within the times set forth in

this section must:

1. Be investigated by the shipper if the

shipper has not received notification or

receipt within 20 days after transfer; and

2. Be traced and reported. The

investigation shall include tracing the

shipment and filing a report with the

nearest Commission Regional Office

listed in Appendix D to this part. Each

licensee who conducts a trace

investigation shall file a written report

with the appropriate NRC Regional

Office within 2 weeks of completion of

the investigation.

Dated at Rockville, Maryland this 10th day

of May, 1995.

For the Nuclear Regulatory Commission.

John C. Hoyle,

Secretary of the Commission.

[FR Doc. 95–11987 Filed 5–15–95; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–188–AD; Amendment

39–9230; AD 95–10–13]

Airworthiness Directives; Boeing

Model 757 Series Airplanes Equipped

With Rolls Royce Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 757

series airplanes, that currently requires

inspections to detect fatigue-related

cracking or breakage of the hydraulic

tubing support brackets located on the

upper spar web in the engine struts;

further inspection to detect related

damage of the upper spar web, the fuel

lines, and the hydraulic lines, as

necessary; and repair or replacement of

cracked or damaged parts. That AD was

prompted by reports of fatigue-related

cracks in the hydraulic tubing support

brackets located on the upper spar web

in the engine struts. The actions

specified by that AD are intended to

prevent such fatigue-related cracking,

which could result in fuel or hydraulic

fluid leakage into the interior of the

engine strut and cause a fire. This

amendment requires installation of a

previously optional terminating action.

DATES: Effective June 15, 1995.

The incorporation by reference of

Boeing Alert Service Bulletin 757–

54A0030, Revision 1, dated December

20, 1993, as listed in the regulations was

approved previously by the Director of

the Federal Register as of February 28,

1994 (59 FR 6542).

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Sheila Kirkwood, Aerospace Engineer,
25984 Federal Register / Vol. 60, No. 94 / Tuesday, May 16, 1995 / Rules and Regulations

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2675; fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 94–04–04,

amendment 39–8822 (59 FR 11182,

March 10, 1994), which is applicable to

certain Boeing Model 757 series

airplanes, was published in the Federal

Register on December 29, 1994 (59 FR

67240). The action proposed to

supersede AD 94–04–04 to continue to

require inspections to detect fatiguerelated cracking or breakage of the

hydraulic tubing support brackets

located on the upper spar web in the

engine struts; further inspection to

detect related damage of the upper spar

web, the fuel lines, and the hydraulic

lines, as necessary; and removal, and

either repair or replacement of cracked

or damaged parts. That action also

proposed to require replacement of all

existing support brackets manufactured

from 2219 aluminum, 2024–T42

aluminum alloy, or 301 stainless steel

with new nickel alloy support brackets;

this replacement would constitute

terminating action for the repetitive

inspection requirements.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter supports the

proposed rule.

One commenter requests that the FAA

revise the proposal to allow support

brackets manufactured from 2219

aluminum, 2024–T42 aluminum alloy,

or 301 stainless steel to be replaced with

either new brackets made of 17–7PH

steel or new brackets made of nickel

alloy. The commenter states that it

previously received FAA approval of an

alternative method of compliance with

AD 94–04–04 for installation of new

brackets made of 17–7PH steel. This

commenter notes that it would be

burdensome to have to request FAA

approval for another alternative method

of compliance with this AD for an

action already accomplished. The FAA

concurs and has revised paragraph (f) of

the final rule accordingly.

One commenter requests that

references in the proposed rule to

‘‘nickel alloy brackets’’ be changed to

read ‘‘nickel alloy 625 brackets’’ in

order to avoid confusion with other

nickel alloy possibilities. The FAA

concurs and revised all references

accordingly throughout this final rule.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

There are approximately 132 Boeing

Model 757 series airplanes equipped

with Rolls Royce engines of the affected

design in the worldwide fleet. The FAA

estimates that 102 airplanes of U.S.

registry will be affected by this AD.

The actions currently required by AD

94–04–04 take approximately 4 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the total cost

impact of the currently required actions

on U.S. operators is estimated to be

$24,480, or $240 per airplane.

The replacement actions take

approximately 40 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$1,044 per airplane. Based on these

figures, the total cost impact of the

required replacement actions on U.S.

operators is estimated to be $351,288, or

$3,444 per airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from 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. 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

removing amendment 39–8822 (59 FR

11182, March 10, 1994), and by adding

a new airworthiness directive (AD),

amendment 39–9230, to read as follows:

95–10–13 Boeing: Amendment 39–9230.

Docket 94–NM–188–AD. Supersedes AD

94–04–04, Amendment 39–8822.

Applicability: Model 757 series airplanes

equipped with Rolls Royce engines; as listed

in Boeing Alert Service Bulletin 757–

54A0030, Revision 1, dated December 20,

1993; 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 (h) 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 airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fuel or hydraulic fluid leakage

into the interior of the engine strut, which

could cause a fire, accomplish the following:

(a) For Group 2 Airplanes: Within 60 days

after February 28, 1994 (the effective date of

AD 94–04–04, amendment 39–8822), perform

an inspection using a magnet to determine

whether the forward support bracket for the

hydraulic tubing on the upper spar web of

each engine strut is manufactured from 17–

7PH steel, in accordance with Boeing Alert
Federal Register / Vol. 60, No. 94 / Tuesday, May 16, 1995 / Rules and Regulations 25985

Service Bulletin 757–54A0030, Revision 1,

dated December 20, 1993. If any forward

support bracket is manufactured from 17–

7PH steel, no further action is required by

this AD for that forward bracket.

Note 2: The brackets positioned after the

forward bracket should be manufactured

from 17–7PH steel, as shown below:

Bracket Part No.

(Power

plant

station

No.)

First Bracket ....... 312N5817–13

(or equivalent).

PPS 102

Second Bracket .. 312N5817–19

(or equivalent).

PPS 120

Third Bracket ...... 312N5817–23

(or equivalent).

PPS 129

Fourth Bracket .... 312N5817–25

(or equivalent).

PPS 145

(b) For Groups 1 and 2 Airplanes: Within

60 days after February 28, 1994 (the effective

date of AD 94–04–04, amendment 39–8822)

(for Group 1 airplanes), and prior to further

flight following the inspection required by

paragraph (a) of this AD (for Group 2

airplanes), perform an initial visual

inspection to detect fatigue-related cracks or

breakage on the hydraulic tubing support

brackets not manufactured of 17–7PH steel

on the upper spar web of each engine strut,

in accordance with Boeing Alert Service

Bulletin 757–54A0030, Revision 1, dated

December 20, 1993. If any discrepancy is

detected, prior to further flight, accomplish

the following in accordance with the alert

service bulletin:

(1) For any support bracket that is

completely broken: Perform a further visual

inspection to detect worn areas or other

damage of the upper spar web, the fuel lines,

and the hydraulic lines; and prior to further

flight, accomplish paragraphs (b)(1)(i),

(b)(1)(ii), (b)(1)(iii), and (b)(1)(iv) of this AD

in accordance with the alert service bulletin:

(i) Repair any damaged upper spar web.

(ii) Repair or replace any damaged fuel line

with new or serviceable parts, as necessary.

(iii) Replace any damaged hydraulic line

with new or serviceable parts.

(iv) Remove any broken support bracket;

and, except as provided by paragraph (c) of

this AD, replace it with a new nickel alloy

625 bracket.

(2) For any support bracket that is cracked,

but not completely broken: Perform a further

visual inspection to detect damage of the

hydraulic pressure line only; and prior to

further flight, accomplish paragraphs (b)(2)(i)

and (b)(2)(ii) of this AD in accordance with

the alert service bulletin:

(i) Replace any damaged hydraulic

pressure line with new or serviceable parts,

as necessary.

(ii) Remove any cracked support bracket;

and, except as provided by paragraph (c) of

this AD, replace it with a new nickel alloy

625 bracket.

(c) For any airplane having a support

bracket that is removed during

accomplishment of paragraph (b)(1)(iv) or

(b)(2)(ii) of this AD: The following number of

flights are permitted prior to replacement of

any removed support bracket with a new

nickel alloy 625 bracket (in accordance with

Boeing Alert Service Bulletin 757–54A0030,

Revision 1, dated December 20, 1993),

provided that, prior to further flight, the

cracked or broken brackets are removed

completely, damaged spar webs are repaired,

and fuel lines and hydraulic lines are

repaired or replaced, in accordance with

paragraph (b) of this AD:

Bracket Part No. (power plant station No.) Flights permitted

First Bracket Removed .............................................................................................................. 312N5817–55 (PPS 102) ... No Flights.

Second Bracket Removed ......................................................................................................... 312N5817–69 (PPS 120) ... Ten Flights.

Third Bracket Removed ............................................................................................................. 312N5817–73 (PPS 129) ... Ten Flights.

Fourth Bracket Removed ........................................................................................................... 312N5817–75 (PPS 145) ... Three Flights.

Second and Third Brackets Removed ...................................................................................... ............................................. One Flight.

Multiple Brackets, other than Second and Third ....................................................................... ............................................. No Flights.

(d) For any airplane having a support

bracket that is manufactured from 2024–T42

aluminum alloy or 301 stainless steel: Repeat

the initial inspection required by paragraph

(b) of this AD thereafter at intervals not to

exceed 2,000 flight hours, in accordance with

the procedures described in Boeing Alert

Service Bulletin 757–54A0030, Revision 1,

dated December 20, 1993.

(e) For any airplane having a support

bracket that is manufactured from 2219

aluminum: Repeat the initial inspection

required by paragraph (b) of this AD

thereafter at intervals not to exceed 1,000

flight hours, in accordance with the

procedures described in Boeing Alert Service

Bulletin 757–54A0030, Revision 1, dated

December 20, 1993.

(f) Within 18 months after the effective

date of this AD: Replace all support brackets

manufactured from 2219 aluminum, 2024–

T42 aluminum alloy, or 301 stainless steel,

with either new 17–7PH steel brackets or

new nickel alloy 625 support brackets for the

hydraulic tubing on the upper spar web of

the engine struts at all locations, in

accordance with Boeing Alert Service

Bulletin 757–54A0030, Revision 1, dated

December 20, 1993. Accomplishment of this

modification constitutes terminating action

for the requirements of this AD.

(g) As of February 28, 1994 (the effective

date of AD 94–04–04, amendment 39–8822),

no person shall install any hydraulic tubing

support bracket on the upper spar web of the

engine struts that is manufactured from 2219

aluminum, 2024–T42 aluminum alloy, or 301

stainless steel on any airplane.

(h) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(i) 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.

(j) The inspections, repair, replacement,

and removal shall be done in accordance

with Boeing Alert Service Bulletin 757–

54A0030, Revision 1, dated December 20,

1993. The incorporation by reference of this

document was approved previously by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51 as of

February 28, 1994 (59 FR 65420). Copies may

be obtained from Boeing Commercial

Airplane Group, P.O. Box 3707, Seattle,

Washington 98124–2207. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(k) This amendment becomes effective on

June 15, 1995.

Issued in Renton, Washington, on May 9,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–11906 Filed 5–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–17; Amendment 39–

9228; AD 95–10–11]

Airworthiness Directives; General

Electric Company CF6 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is