29630 Federal Register / Vol. 74, No. 119 / Tuesday, June 23, 2009 / Proposed Rules 

(2) Five effective kilograms or more of 

plutonium, high-enriched uranium or 

uranium-233. 

(3) 10,000 kilograms or more of heavy 

water. (Note: Does not apply to exports 

of heavy water to Canada.) 

(4) Nuclear grade graphite for nuclear 

end use. 

(5) Radioactive waste. 

(c) The Commission will also publish 

in the Federal Register a notice of 

receipt of a license application, 

including applications for amendment 

or renewal but not applications for 

minor amendments, for an import of 

radioactive waste for which a specific 

license is required. 

34. Section 110.80 is revised to read 

as follows: 

§ 110.80 Basis for hearings. 

The procedures in this part will 

constitute the exclusive basis for 

hearings on export and import license 

applications. 

35. In § 110.81, paragraph (b) is 

revised to read as follows: 

§ 110.81 Written comments. 

* * * * * 

(b) These comments should be 

submitted within 30 days after public 

notice of receipt of the application on 

the NRC Web site or in the Federal 

Register and addressed to the Secretary, 

U.S. Nuclear Regulatory Commission, 

Washington, DC 20555–0001, Attention: 

Rulemakings and Adjudications Staff. 

* * * * * 

36. In § 110.82, paragraph (c) is 

revised to read as follows: 

§ 110.82 Hearing request or intervention 

petition. 

* * * * * 

(c) Hearing requests and intervention 

petitions will be considered timely only 

if filed not later than: 

(1) 30 days after notice of receipt in 

the Federal Register, for those 

applications published in the Federal 

Register; 

(2) 30 days after publication of notice 

on the NRC Web site at http:// 

www.nrc.gov; 

(3) 30 days after notice of receipt in 

the Public Document Room; or 

(4) Such other time as may be 

provided by the Commission. 

37. In § 110.112, paragraph (b) is 

revised to read as follows: 

§ 110.112 Reporter and transcript for an 

oral hearing. 

* * * * * 

(b) Except for any portions containing 

classified information, Restricted Data, 

Safeguards Information, proprietary 

information, or other sensitive 

unclassified information, transcripts 

will be made available at the NRC Web 

site, http://www.nrc.gov, and/or at the 

NRC Public Document Room. 

* * * * * 

Appendix L to Part 110 [Amended] 

38. Appendix L to part 110 is amended by 

adding ‘‘Carbon 11 (C 11)’’, ‘‘Cesium 129 (Cs 

129)’’, ‘‘Cobalt 57 (Co 57)’’, ‘‘Gallium 67 (Ga 

67)’’, ‘‘Gold 195 (Au 195)’’, ‘‘Indium 111 (In 

111)’’, ‘‘Iodine 123 (I 123)’’, ‘‘Iron 52 (Fe 52)’’, 

‘‘Nitrogen 13 (N 13)’’, ‘‘Oxygen 15 (O 15)’’, 

‘‘Potassium 43 (K 43)’’, ‘‘Rubidium 81 (Rb 

81)’’, ‘‘Yttrium 87 (Y 87)’’, and ‘‘Yttrium 88 

(Y 88)’’ in alphabetical order. 

Dated at Rockville, Maryland, this 17th day 

of June 2009. 

For the Nuclear Regulatory Commission. 

Annette Vietti-Cook, 

Secretary of the Commission. 

[FR Doc. E9–14679 Filed 6–22–09; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0553; Directorate 

Identifier 2008–NM–199–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, and 747SR Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Boeing Model 747–100, 747–100B, 747– 

200B, 747–200C, 747–200F, and 747SR 

series airplanes. This proposed AD 

would require a one-time general visual 

inspection for missing fasteners in 

certain stringer-to-stringer clip joints at 

the station (STA) 760 through STA 940 

frames, and related investigative and 

corrective actions if necessary. This 

proposed AD results from a report of 

broken and cracked frame shear ties, 

cracks on the frame doubler and frame 

web, and missing fasteners in the 

stringer (S)–10L stringer-to-stringer clip 

joint at the STA 820 frame. We are 

proposing this AD to detect and correct 

missing fasteners in the stringer-tostringer clip joints, which could result 

in shear tie and skin cracks and rapid 

in-flight decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 7, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207; telephone 

206–544–9990; fax 206–766–5682; 

e-mail DDCS@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0553; Directorate Identifier 

2008–NM–199–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

Federal Register / Vol. 74, No. 119 / Tuesday, June 23, 2009 / Proposed Rules 29631 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received a report indicating 

that, during routine maintenance, two 

operators found broken and cracked 

frame shear ties at the station (STA) 820 

frame between stringer (S)–10AL and 

S–11L. Also, cracks were found on the 

frame doubler and frame web near 

S–11L. Further inspection showed 

missing fasteners in the S–10L stringerto-stringer clip joint at the STA 820 

frame. The cracks and missing fasteners 

were found on airplanes that had 

accumulated 16,087 and 16,421 total 

flight cycles. 

Boeing analysis shows that the cracks 

were caused by increased load on the 

shear ties because of the missing 

fasteners in the stringer-to-stringer clip 

joint. Boeing investigation shows that 

similar cracking could occur in the 

frames adjacent to the tension ties if the 

stringer clip fasteners are not installed. 

Cracks in the shear ties, if not detected 

and corrected, could result in skin 

cracks and rapid in-flight 

decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2751, dated 

October 9, 2008. The service bulletin 

describes procedures for a one-time 

general visual inspection for missing 

fasteners in the S–10, S–10A, and S–11 

stringer-to-stringer clip joints at the STA 

760 through STA 940 frames, detailed 

and surface high frequency eddy current 

inspections to detect cracking of the 

adjacent frame and skin structure, 

installation of missing fasteners, and 

repairs of the shear ties, frame web, and/ 

or skin. For airplanes on which the 

repair was done, the service bulletin 

describes procedures for detailed 

inspections to detect cracks of the 

repairs and the adjacent structure 

within 10 inches of the repairs. The 

service bulletin also specifies a detailed 

inspection of the repair and adjacent 

structure every 3,000 flight cycles. 

FAA’s Determination and Requirements 

of this Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

Differences Between the Proposed AD 

and Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 84 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection .............. 4 $80 $0 $320 per inspection cycle ....... 84 $26,880 per inspection cycle. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect 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. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. 

29632 Federal Register / Vol. 74, No. 119 / Tuesday, June 23, 2009 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Boeing: Docket No. FAA–2009–0553; 

Directorate Identifier 2008–NM–199–AD. 

Comments Due Date 

(a) We must receive comments by August 

7, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747– 

100, 747–100B, 747–200B, 747–200C, 747– 

200F, and 747SR series airplanes, certificated 

in any category; as identified in Boeing Alert 

Service Bulletin 747–53A2751, dated October 

9, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report of broken 

and cracked frame shear ties, cracks on the 

frame doubler and frame web, and missing 

fasteners in the stringer (S)–10L stringer-tostringer clip joint at the station (STA) 820 

frame. We are proposing this AD to detect 

and correct missing fasteners at the stringerto-stringer clip joints, which could result in 

shear tie and skin cracks and rapid in-flight 

decompression of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspection for Missing Fasteners 

(g) Within 3,000 flight cycles after the 

effective date of this AD: Do a one-time 

general visual inspection for missing 

fasteners in the left and right side S–10, S– 

10A, and S–11 stringer-to-stringer clip joints 

at the STA 760 through 940 frames, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2751, dated October 9, 2008. If any 

fasteners are missing, before further flight, do 

detailed and surface high frequency eddy 

current inspections to detect cracking of the 

adjacent frame and skin structure in 

accordance with the Accomplishment 

Instructions of the service bulletin. Install all 

missing fasteners before further flight. 

(h) If any crack is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, repair any cracked 

shear ties, frame web, and/or skin in 

accordance with Boeing Service Bulletin 

747–53A2751, dated October 9, 2008. 

(i) If any repair is done in accordance with 

paragraph (h) of this AD, before 20,000 total 

flight cycles or within 3,000 flight cycles 

from the repair installation, whichever 

occurs later: Do a detailed inspection of the 

repair(s) and the adjacent structure within 10 

inches of the repair(s) for cracking. Repeat 

the inspection thereafter at intervals not to 

exceed 3,000 flight cycles. If any crack is 

found during this inspection, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to Attn: Ivan Li, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6437; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, in the FAA Flight Standards 

District Office (FSDO), or lacking a principal 

inspector, your local FSDO. The AMOC 

approval letter must specifically reference 

this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on June 15, 

2009. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14677 Filed 6–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0565; Directorate 

Identifier 2008–NM–217–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2A12 (CL–601) and CL– 

600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

[I]ncidents of throttle jam and engine 

shutdowns, caused by premature wear of the 

rack and pinion mechanism of part number 

(P/N) 2100140–005 and –007 Engine Throttle 

Control Gearbox (ETCG), installed on 

Bombardier CL–601 and 604 aircraft. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 23, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Rocco Viselli, Aerospace Engineer,