60760 Federal Register / Vol. 72, No. 207 / Friday, October 26, 2007 / Rules and Regulations 

PART 301—DOMESTIC QUARANTINE 

NOTICES 

■ Accordingly, we are adopting as a 

final rule, without change, the interim 

rule that amended 7 CFR part 301 and 

that was published at 72 FR 40061–

40062 on July 23, 2007. 

Done in Washington, DC, this 22nd day of 

October 2007. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. E7–21119 Filed 10–25–07; 8:45 am] 

BILLING CODE 3410–34–P 

NUCLEAR REGULATORY 

COMMISSION 

10 CFR Part 72 

RIN 3150–AI21 

List of Approved Spent Fuel Storage 

Casks: TN–68 Revision 1, Confirmation 

of Effective Date 

AGENCY: Nuclear Regulatory 

Commission. 

ACTION: Direct final rule: confirmation of 

effective date. 

SUMMARY: The Nuclear Regulatory 

Commission (NRC) is confirming the 

effective date of October 30, 2007, for 

the direct final rule that was published 

in the Federal Register on August 16, 

2007 (72 FR 45880). This direct final 

rule amended the NRC’s regulations to 

revise the TN–68 cask system listing to 

include Amendment No. 1 to Certificate 

of Compliance (CoC) No. 1027. 

DATES: Effective Date: The effective date 

of October 30, 2007, is confirmed for 

this direct final rule. 

ADDRESSES: Documents related to this 

rulemaking, including any comments 

received, may be examined at the NRC 

Public Document Room, located at One 

White Flint North, 11555 Rockville 

Pike, Rockville, MD 20852. 

FOR FURTHER INFORMATION CONTACT: 

Jayne M. McCausland, Office of Federal 

and State Materials and Environmental 

Management Programs, U.S. Nuclear 

Regulatory Commission, Washington, 

DC 20555, telephone (301) 415–6219, 

e-mail jmm2@nrc.gov. 

SUPPLEMENTARY INFORMATION: On August 

16, 2007 (72 FR 45880), the NRC 

published a direct final rule amending 

its regulations at 10 CFR 72.214 to 

revise the TN–68 cask system listing 

within the ‘‘List of Approved Spent Fuel 

Storage Casks’’ to include Amendment 

No. 1 to CoC No. 1027. This amendment 

modifies the CoC by revising several 

fuel parameters that include increasing 

fuel burnup to 60 gigawatts-day/metric 

ton of uranium, increasing total cask 

decay heat to 30 kilowatts, increasing 

maximum average fuel enrichment to 

4.7 weight percent uranium-235, and 

decreasing minimum fuel assembly 

cooling time to 7 years. Amendment No. 

1 will also add up to eight damaged fuel 

assemblies as authorized contents of the 

cask and reduce the cask spacing on the 

storage pad. In the direct final rule, NRC 

stated that if no significant adverse 

comments were received, the direct 

final rule would become final on 

October 30, 2007. The NRC did not 

receive any comments on the direct 

final rule. Therefore, this rule will 

become effective as scheduled. 

Dated at Rockville, Maryland, this 22nd 

day of October, 2007. 

For the Nuclear Regulatory Commission. 

Michael T. Lesar, 

Chief, Rulemaking, Directives and Editing 

Branch, Division of Administrative Services, 

Office of Administration. 

[FR Doc. E7–21143 Filed 10–25–07; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27496; Directorate 

Identifier 2005–SW–37–AD; Amendment 39–

15238; AD 2007–22–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. Model 205A, 

205A–1, 205B, 212, 412, 412CF, and 

412EP Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final Rule. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the specified Bell Helicopter 

Textron, Inc. (Bell) Helicopters. That AD 

currently requires inspecting each 

affected tail rotor blade (blade) forward 

tip weight retention block (tip block) 

and the aft tip closure (tip closure) for 

adhesive bond voids, and removing any 

blade with an excessive void from 

service. That AD also requires 

modifying certain blades by installing 

shear pins and tip closure rivets. This 

amendment contains the same 

requirements but expands the 

applicability to include other part and 

serial-numbered blades. This AD also 

clarifies the requirement to re-identify 

the modified blade by adding ‘‘FM’’

after the part number and also requires 

dynamically balancing the tail rotor. 

The existing AD was prompted by five 

occurrences of missing tip blocks or tip 

closures resulting in minor to 

substantial damage. This amendment 

was prompted by the determination that 

the AD should apply to other affected 

part and serial-numbered blades. The 

actions specified by this AD are 

intended to prevent loss of a tip block 

or tip closure, loss of a blade and 

subsequent loss of control of the 

helicopter. 

DATES: Effective November 30, 2007. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

30, 2007. 

ADDRESSES: You may get the service 

information identified in this AD from 

Bell Helicopter Textron, Inc., P.O. Box 

482, Fort Worth, Texas 76101, telephone 

(817) 280–3391, fax (817) 280–6466. 

Examining the 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 

AD, the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (telephone 800–647–5527) is the 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Certification Office, Fort 

Worth, Texas 76193–0170, telephone 

(817) 222–5447, fax (817) 222–5783. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 by 

superseding AD 2002–09–04, 

Amendment 30–12737 (67 FR 22349, 

May 3, 2002), for the specified Bell 

model helicopters was published in the 

Federal Register on March 13, 2007 (72 

FR 11295). The action proposed: 

retaining requirements to inspect the tip 

block and the tip closure for adhesive 

bonding voids and to remove any blade 

with an excessive void from service; 

retaining requirements to modify certain 

blades by installing shear pins and tip 

closure rivets in the tip area of the 

affected blades; expanding the 

applicability to include more blades and 

clarifying other requirements. 

Since issuing AD 2002–09–04, Bell 

issued further revisions to Alert Service 

Bullet (ASB) Nos. 205–00–80, 205B–00–


rmajette on PROD1PC63 with RULES
Federal Register / Vol. 72, No. 207 / Friday, October 26, 2007 / Rules and Regulations 60761 

34, 212–00–111, 412–00–106, and 

412CR–00–13, Revision A, dated 

December 20, 2000. The revisions add 

blades with a serial number (S/N) prefix 

of ‘‘A’’ or ‘‘AFS’’ and number of 11530 

to 13594, 13603 to 13618, and also 

change the ‘‘effectivity’’ of the blades. 

The latest revisions, Revisions D, all 

dated March 18, 2005, provide an 

alternative fastener for the blade tip 

closure rivets installation. The revised 

ASBs also state that blades with S/N A 

or AFS–11926, 13351, 13367, 13393, 

13400, 13402, 13515, 13540, 13568, 

13595 to 13602, 13619, and subsequent 

will be modified before delivery. 

The previously described unsafe 

condition is likely to exist or develop on 

other helicopters of these same type 

designs. Therefore, this AD supersedes 

AD 2002–09–04 to expand the 

applicability for the blade part and 

serial number. This AD also clarifies the 

requirement to re-identify the modified 

blade by adding ‘‘FM’’ after the part 

number and also requires dynamically 

balancing the tail rotor. Because blades, 

S/N with a prefix of ‘‘A’’ or ‘‘AFS’’ and 

a number 11926, 13351, 13367, 13393, 

13400, 13402, 13515, 13540, 13568, 

13595 to 13602, 13619, and subsequent, 

will be modified before delivery, we are 

excluding them from the applicability of 

this AD. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. 

The FAA estimates that this AD will 

affect 281 helicopters of U.S. registry. 

The required actions will take about 3 

work hours per helicopters to inspect 

certain blades, install the shear pins and 

tip closure rivets, reidentify the 

modified blades, and dynamically 

balance the blade assembly at an 

average labor rate of $80 per work hour. 

Required supplies will cost about $35 

per helicopter. Based on these figures, 

we estimate the total cost impact of the 

AD on U.S. operators to be $77,275. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 reason discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12833; 

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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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. 

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. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. Section 39.13 is amended by 

removing Amendment 39–12737 (67 FR 

22349, May 3, 2002), and by adding a 

new airworthiness directive (AD), 

Amendment 39–15238, to read as 

follows: 

2007–22–02 Bell Helicopter Textron, Inc.: 

Amendment 39–15238. Docket No. 

FAA–2007–27496; Directorate Identifier 

2005–SW–37–AD. Supersedes AD 2002–

09–04, Amendment 39–12737, Docket 

No. 2001–SW–37–AD. 

Applicability 

Model 205A, 205A–1, 205B, 212, 412, 

412CF, and 412EP helicopters with a tail 

rotor blade (blade), part number 212–010–

750–009 through –129, all serial numbers 

except serial numbers with a prefix of ‘‘A’’

or ‘‘AFS’’ and the number 11926, 13351, 

13367, 13393, 13400, 13402, 13515, 13540, 

13568, 13595 through 13602, 13619, and 

subsequent assigned numbers, installed, 

certificated in any category. 

Compliance 

Within 100 hours time-in-service, unless 

accomplished previously. 

To prevent loss of the forward tip weight 

retention block (tip block) or aft tip closure 

(tip closure), loss of the blade, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Inspect the tip block and tip closure for 

voids. Remove from service any blade with 

a void in excess of that allowed by the 

Component Repair and Overhaul Manual 

limitations. 

(b) Inspect the tip block attachment 

countersink screws in four locations to 

determine if the head of each countersunk 

screw is flush with the surface of the 

abrasion strip. The locations of these four 

screws are depicted on Figure 1 of Bell 

Helicopter Textron, Inc. Alert Service 

Bulletins 205–00–80, 205B–00–34, 212–00–

111, 412–00–106, and 412CF–00–13, all 

Revision D, all dated March 18, 2005 (ASB). 

If any of these screws are set below the 

surface of the abrasion strip or are covered 

with filler material, install shear pins by 

following the Accomplishment Instructions, 

Part A, Shear Pin Installation paragraphs, of 

the ASB appropriate for your model 

helicopter. 

(c) Install the aft tip closure rivets, reidentify the modified blade by adding an 

‘‘FM,’’ and dynamically balance the tail rotor 

hum assembly by following the 

Accomplishment Instructions, Part B, Aft Tip 

Closure Rivet Installation paragraphs, of the 

ASB appropriate for your model helicopter. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, ATTN: Michael Kohner, Aviation 

Safety Engineer, Fort Worth, Texas 76193–

0170, telephone (817) 222–5447, fax (817) 

222–5783, for information about previously 

approved alternative methods of compliance. 

(e) Inspecting certain screws to determine 

if they are flush with the surface of the 

abrasion strip, modifying blades by installing 

shear pins or aft tip closure rivets as 

necessary, and re-identifying the modified 

blade shall be done by following Bell 

Helicopter Textron, Inc. Alert Service 

Bulletins 205–00–80, 205B–00–34, 212–00–

111, 412–00–106, and 412CF–00–13, all 

Revision D, all dated March 18, 2005. The 

Director of the Federal Register approved this 

incorporation by reference under 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 


rmajette on PROD1PC63 with RULES
60762 Federal Register / Vol. 72, No. 207 / Friday, October 26, 2007 / Rules and Regulations 

obtained from Bell Helicopter Textron, Inc., 

P.O. Box 482, Fort Worth, Texas 76101, 

telephone (817) 280–3391, fax (817) 280–

6466. Copies may be inspected at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

(f) This amendment becomes effective 

November 30, 2007. 

Issued in Fort Worth, Texas, on October 10, 

2007. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–5186 Filed 10–25–07; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28976; Directorate 

Identifier 2007–NE–28–AD; Amendment 39–

15244; AD 2007–22–08] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211 Trent 768–60, 772–60, 

772B–60, and 772C–60 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

provided by the aviation authority for 

the United Kingdom to identify and 

correct an unsafe condition on an 

aviation product. The MCAI states the 

following: 

This action is necessary following the 

discovery of IP Compressor Rotor stage 2–3 

interstage spacer cracking on an in-service 

Trent 700 engine. Stress analysis of the 

damaged rotor has shown a possible threat to 

the rotor integrity, the cracking therefore 

presents a potential unsafe condition. The 

cause of the cracking is currently under 

investigation. 

We are issuing this AD to detect cracks 

in the stage 2–3 interstage spacer of the 

intermediate pressure (IP) Compressor 

Rotor. Cracking of the stage 2–3 

interstage spacer could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective 

November 13, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of RR service bulletins (SBs) RB.211–

72–AE753, Revision 1, dated May 24, 

2005, and RB.211–72–AF197, dated 

December 20, 2006, listed in the AD as 

of November 13, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey, Avenue, 

SE., Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 16 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

christopher.spinney@faa.gov; telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0136, 

dated May 14, 2007, to correct an unsafe 

condition for the specified products. 

The EASA AD states: 

This Airworthiness Directive requires 

inspections for cracks in the stage 2–3 

interstage spacer of the IP Compressor Rotor 

during shop visit. 

This action is necessary following the 

discovery of IP Compressor Rotor stage 2–3 

interstage spacer cracking on an in-service 

Trent 700 engine. Stress analysis of the 

damaged rotor has shown a possible threat to 

the rotor integrity, the cracking therefore 

presents a potential unsafe condition. The 

cause of the cracking is currently under 

investigation. 

You may obtain further information by 

examining the EASA AD in the AD 

docket. 

Relevant Service Information 

Rolls-Royce plc has issued Service 

Bulletins RB.211–72–AE753, Revision 1, 

dated May 24, 2005, and RB.211–72–

AF197, dated December 20, 2006. The 

actions described in that service 

information are intended to correct the 

unsafe condition identified in the EASA 

AD. 

FAA’s Determination and Requirements 

of this AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the United 

Kingdom, they have notified us of the 

unsafe condition described in the EASA 

AD and service information referenced 

above. We are issuing this AD because 

we evaluated all the information 

provided by the EASA and determined 

the unsafe condition exists and is likely 

to exist or develop on other products of 

the same type design. We are issuing 

this AD to detect cracks in the stage 2–

3 interstage spacer of the IP Compressor 

Rotor. Cracking of the stage 2–3 

interstage spacer could result in an 

uncontained engine failure and damage 

to the airplane. This AD requires 

inspecting the stage 2–3 interstage 

spacer using an eddy current inspection 

process at every shop visit. You must 

use the service information described 

previously to perform the actions 

required by this AD. 

FAA’s Determination of the Effective 

Date 

Although no airplanes that are 

registered in the United States use these 

engines, the possibility exists that the 

engines could be used on airplanes that 

are registered in the United States in the 

future. The unsafe condition described 

previously is likely to exist or develop 

on other RR RB211 Trent 768–60, 772–

60, 772B–60, and 772C–60 turbofan 

engines of the same type design. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are unnecessary 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 


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