33928 Federal Register / Vol. 74, No. 133 / Tuesday, July 14, 2009 / Proposed Rules 

(b)(1) * * * 

(ii) 500 hours of work experience, 

under the supervision of an authorized 

user who meets the requirements in 

§§ 35.57, 35.690, or equivalent 

Agreement State requirements at a 

medical institution, involving— 

* * * * * 

(2) Has completed 3 years of 

supervised clinical experience in 

radiation therapy, under an authorized 

user who meets the requirements in 

§§ 35.57, 35.690, or equivalent 

Agreement State requirements, as part of 

a formal training program approved by 

the Residency Review Committee for 

Radiation Oncology of the Accreditation 

Council for Graduate Medical Education 

or the Royal College of Physicians and 

Surgeons of Canada or the Committee 

on Postdoctoral Training of the 

American Osteopathic Association. This 

experience may be obtained 

concurrently with the supervised work 

experience required by paragraph 

(b)(1)(ii) of this section; and 

(3) Has obtained written attestation 

that the individual has satisfactorily 

completed the requirements in 

paragraph (a)(1) or paragraphs (b)(1) and 

(b)(2), and paragraph (c), of this section, 

and has achieved a level of competency 

sufficient to function independently as 

an authorized user of each type of 

therapeutic medical unit for which the 

individual is requesting authorized user 

status. The written attestation must be 

signed by a preceptor authorized user 

who meets the requirements in §§ 35.57, 

35.690, or equivalent Agreement State 

requirements for an authorized user for 

each type of therapeutic medical unit 

for which the individual is requesting 

authorized user status; and 

* * * * * 

Dated at Rockville, Maryland, this 26th day 

of June 2009. 

For the Nuclear Regulatory Commission. 

R.W. Borchardt, 

Executive Director for Operations. 

[FR Doc. E9–16656 Filed 7–13–09; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0636; Directorate 

Identifier 2009–NM–031–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100B SUD, –200B, –300, 

–400, and –400D Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 747–100B SUD, –200B, 

–300, –400, and –400D series airplanes. 

The existing AD currently requires 

repetitive inspections for cracking in 

fuselage stringers 8L, 8R, 10L, and 10R 

at body stations 460, 480, and 500 frame 

locations; and repair if necessary. This 

proposed AD would revise the 

applicability to include an additional 

airplane, and reduce compliance times 

for the initial inspection and repetitive 

intervals for Model 747–400 series 

airplanes that have been converted to 

the large cargo freighter configuration. 

This proposed AD results from findings 

of cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body stations 460, 480, 

and 500 frame locations. We are 

proposing this AD to detect and correct 

fatigue cracking in certain fuselage 

stringers, which, if left undetected, 

could result in fuselage skin cracking 

that reduces the structural integrity of 

the skin panel, and consequent rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 28, 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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@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–2009–0636; Directorate Identifier 

2009–NM–031–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

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 

On July 13, 2005, we issued AD 2005– 

15–08, amendment 39–14197 (70 FR 

43020, July 26, 2005), for certain Boeing 

Model 747–100B SUD, –200B, –300, 

–400, and –400D series airplanes. That 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 74, No. 133 / Tuesday, July 14, 2009 / Proposed Rules 33929 

AD requires repetitive inspections for 

cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body stations 460, 480, 

and 500 frame locations; and repair if 

necessary. That AD resulted from 

findings of cracking in fuselage stringers 

8L, 8R, 10L, and 10R at body stations 

460, 480, and 500 frame locations. We 

issued that AD to detect and correct 

fatigue cracking in certain fuselage 

stringers, which, if left undetected, 

could result in fuselage skin cracking 

that reduces the structural integrity of 

the skin panel, and consequent rapid 

depressurization of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2005–15–08, 

Boeing has revised the service 

information cited in that AD. AD 2005– 

15–08 cited Boeing Alert Service 

Bulletin 747–53A2484, dated June 26, 

2003, as the source of service 

information for the required and 

optional actions. Revision 1, dated 

February 12, 2009, adds airplane 

variable number RS699 to the airplane 

effectivity; that variable number was 

inadvertently omitted from Boeing Alert 

Service Bulletin 747–53A2484, dated 

June 26, 2003. Also, Model 747–400 

series airplanes that have been 

converted to the large cargo freighter 

(LCF) configuration (i.e., variable 

numbers RT631 and RT632) have been 

moved from Group 3 to a new Group 4 

with reduced compliance times for the 

initial and repetitive inspections, and 

have revised access instructions due to 

a different interior configuration. 

Procedures are otherwise unchanged. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2005– 

15–08 and would continue to require 

repetitive inspections for fatigue 

cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body station 460, 480, 

and 500 frame locations; and repair if 

necessary. This proposed AD would 

also revise the applicability to include 

an additional airplane, and reduce 

compliance times for initial inspection 

and repetitive interval for Model 747– 

400 series airplanes that have been 

converted to the large cargo freighter 

configuration. 

Change to Existing AD 

This proposed AD would retain 

certain requirements of AD 2005–15–08. 

Since AD 2005–15–08 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2005–15–08 

Corresponding 

requirement in this 

proposed AD 

paragraph (d) ............ paragraph (e). 

paragraph (e) ............ paragraph (f). 

paragraph (f) ............. paragraph (g). 

paragraph (g) ............ paragraph (k). 

paragraph (h) ............ paragraph (l). 

paragraph (i) ............. paragraph (m). 

Costs of Compliance 

There are about 246 airplanes of the 

affected design in the worldwide fleet. 

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 Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection (required by AD 

2005–15–08).

3 $80 $240 per inspection cycle .. 69 $16,560 per inspection cycle. 

Inspection (proposed) ........ 3 80 $240 per inspection cycle .. 70 $16,800 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 have 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 that the 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing amendment 39–14197 (70 FR 


sroberts on DSKD5P82C1PROD with PROPOSALS
33930 Federal Register / Vol. 74, No. 133 / Tuesday, July 14, 2009 / Proposed Rules 

43020, July 26, 2005) and adding the 

following new AD: 

Boeing: Docket No. FAA–2009–0636; 

Directorate Identifier 2009–NM–031–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by August 28, 2009. 

Affected ADs 

(b) This AD supersedes AD 2005–15–08. 

Applicability 

(c) This AD applies to Boeing Model 747– 

100B SUD, –200B, –300, –400, and –400D 

series airplanes, certificated in any category; 

as identified in Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from findings of 

cracking in fuselage stringers 8L, 8R, 10L, 

and 10R at body station 460, 480, and 500 

frame locations. We are issuing this AD to 

detect and correct fatigue cracking in the 

specified fuselage stringers, which, if left 

undetected, could result in fuselage skin 

cracking that reduces the structural integrity 

of the skin panel, and consequent rapid 

depressurization of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2005–15–08 

Inspection for Certain Airplanes Subject to 

AD 2005–15–08 With New Service Bulletin 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003, except airplanes identified in 

paragraph (j) of this AD, do a detailed 

inspection for cracking in fuselage stringers 

8L, 8R, 10L, and 10R at body station 460, 

480, and 500 frame locations, in accordance 

with Part 1 of the Accomplishment 

Instructions in Boeing Alert Service Bulletin 

747–53A2484, dated June 26, 2003; or Boeing 

Service Bulletin 747–53A2484, Revision 1, 

dated February 12, 2009. Do the inspections 

at the applicable time specified in paragraph 

(g)(1) or (g)(2) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 3,000 flight cycles until the 

requirements of paragraph (l) of this AD are 

accomplished. After the effective date of this 

AD, use only Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009. 

(1) For airplanes with 19,000 total flight 

cycles or less as of August 30, 2005 (the 

effective date of AD 2005–15–08): Prior to the 

accumulation of 8,000 total flight cycles, or 

within 2,000 flight cycles after August 30, 

2005, whichever is later, not to exceed 20,000 

total flight cycles. 

(2) For airplanes with more than 19,000 

total flight cycles as of August 30, 2005: 

Within 1,000 flight cycles after August 30, 

2005. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

New Requirements of This Ad 

Inspection: Variable Number RS699 

(h) For Model 747 airplane variable 

number RS699, do a detailed inspection for 

cracking in fuselage stringers 8L, 8R, 10L, 

and 10R at body station 460, 480, and 500 

frame locations, in accordance with Boeing 

Service Bulletin 747–53A2484, Revision 1, 

dated February 12, 2009, at the later of the 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD. 

(1) Before the accumulation of 8,000 total 

flight cycles. 

(2) Within 2,000 flight cycles after the 

effective date of this AD. 

(i) For Model 747 airplane variable number 

RS699, repeat the inspection specified in 

paragraph (h) of this AD thereafter at 

intervals not to exceed 3,000 flight cycles 

until the actions specified in paragraph (k) or 

(l) of this AD are accomplished. 

Inspection: Group 4 Airplanes 

(j) For Group 4 airplanes as identified in 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009, do a 

detailed inspection for cracking in fuselage 

stringers 8L, 8R, 10L, and 10R at body station 

460, 480, and 500 frame locations, within 

1,000 flight cycles after the effective date of 

this AD. Do the actions in accordance with 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. Repeat 

the inspection thereafter at intervals not to 

exceed 1,500 flight cycles until the actions 

specified in paragraph (k) or (l) of this AD are 

accomplished. 

Repair 

(k) If cracking is found during any 

inspection required by this AD: Before 

further flight, repair the affected stringer in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003; or Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009. After the effective date of this AD, use 

only Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. 

Accomplishment of the repair terminates the 

repetitive inspections required by this AD for 

that repaired stringer/frame location only. 

Optional Terminating Action 

(l) Installing new frame clips and new 

doublers, and repairing as applicable, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003; or Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009; terminates the repetitive inspections 

required by this AD. After the effective date 

of this AD, use only Boeing Service Bulletin 

747–53A2484, Revision 1, dated February 12, 

2009. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle 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, or lacking a principal 

inspector, your local Flight Standards District 

Office. 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. 

(4) AMOCs approved previously in 

accordance with AD 2005–15–08, 

amendment 39–14197, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

Issued in Renton, Washington, on July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16575 Filed 7–13–09; 8:45 am] 

BILLING CODE 4910–13–P 

LIBRARY OF CONGRESS 

Copyright Office 

37 CFR Parts 201 and 202 

[Docket No. 2009–4] 

Electronic Registration for Deposit 

Account Holders 

AGENCY: Copyright Office, Library of 

Congress. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Copyright Office is 

proposing to amend its regulations to 

require that applications for registration 

paid for by deposit account debits be 

submitted electronically using the 


sroberts on DSKD5P82C1PROD with PROPOSALS