16754 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 

2The compliance date in the final rule was 

originally published as April 14, 2008; it was 

corrected to April 14, 2009, in a correction 

published on October 27, 2008 (73 FR 63621). 

disease. Entities that possessed the 

select agents and toxins added in the 

final rule and that had not been 

registered were now required to register 

under the select agent regulations. 

To minimize the disruption of 

research or educational projects (e.g., 

teaching demonstrations) involving 

listed select agents or toxins, the final 

rule provided any individual or entity 

possessing newly added select agents or 

toxins as of the effective date of the final 

rule, November 17, 2008, with 

additional time to reach full compliance 

with the select agent regulations. The 

responsible official at all entities that 

possessed a new agent or toxin was 

required to provide notice to APHIS 

regarding their possession of the new 

agent(s) and toxin(s) by November 17, 

2008. The final rule also stated that, by 

April 14, 2009, all previously 

unregistered entities must be registered 

and thus in compliance with the 

regulations.2

Since the publication of the final rule, 

some entities have notified us that they 

use virulent Newcastle disease virus for 

bird vaccines, in research on cancer 

treatment in humans, and as a vector of 

antigenic proteins that enhance immune 

response to cancer and to diseases (e.g., 

influenza and avian influenza). This 

notice informs the public that we are 

extending the compliance date for 

registration of entities that are newly 

required to register to July 13, 2009, to 

give us additional time to determine 

how best to regulate those entities. 

Authority: 7 U.S.C. 8401; 7 CFR 2.22, 2.80, 

371.3, and 371.4. 

Done in Washington, DC, this 8th day of 

April 2009. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. E9–8383 Filed 4–10–09; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0827; Directorate 

Identifier 2008–NE–26–AD; Amendment 39– 

15879; AD 2009–08–06] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80A Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF6–80A series turbofan engines with 

certain stage 1 high-pressure turbine 

(HPT) rotor disks, installed. This AD 

requires removal from service of those 

stage 1 HPT rotor disks within 30 days 

after the effective date of the AD. This 

AD results from the FAA learning that 

those disks are susceptible to cracks 

developing at the aft chamfer of the 

blade dovetail slots. We are issuing this 

AD to prevent cracks developing at the 

aft chamfer of the blade dovetail slots 

that could propagate to a failure of the 

disk and cause an uncontained engine 

failure and damage to the airplane. 

DATES: This AD becomes effective May 

18, 2009. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: robert.green@faa.gov; 

telephone: (781) 238–7754, fax: (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF6–80A series turbofan 

engines with certain stage 1 HPT rotor 

disks, installed. We published the 

proposed AD in the Federal Register on 

September 4, 2008 (73 FR 51604). That 

action proposed to require removal from 

service of those stage 1 HPT rotor disks 

within 30 days after the effective date of 

the AD. 

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 provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Claim That Cost of Compliance Is 

Underestimated 

One commenter, FedEx Express, 

claims that we greatly underestimated 

the actual cost of compliance with the 

proposed AD. The proposed AD 

estimated 1 work-hour of labor. The 

commenter states that this estimate is 

accurate only when the engine is 

already removed and disassembled to 

piece-part exposure of the disk. The 

commenter states that the true cost to an 

airline, both in disruption to the 

operation and in the subsequent 

unplanned engine shop visit, would 

vastly exceed 1 work-hour. 

We agree that the cost of compliance 

should also cover the work-hours for an 

unplanned engine shop visit. We do not 

agree that it should factor in the cost of 

disruption to the operation. We are 

required to calculate only the direct cost 

to an operator, of labor and parts. We 

changed the cost of compliance 

paragraph to include an estimate for an 

unplanned engine shop visit. 

Clarification of Unsafe Condition 

Statement 

Since we issued the proposed AD, we 

clarified the unsafe condition statement 

as to where potential cracks could occur 

in the disk. We changed ‘‘cracks 

developing in the bottoms of the 

dovetail slots’’ to ‘‘cracks developing at 

the aft chamfer of the blade dovetail 

slots.’’ 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 16755 

Costs of Compliance 

We estimate that this AD will affect 3 

out of 316 CF6–80A series turbofan 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 1 work-hour per engine to 

perform the actions if the engine is 

already removed and disassembled to 

piece-part exposure of the disk, and will 

take about 115 work-hours per engine 

for an unplanned engine shop visit. The 

average labor rate is $80 per work-hour. 

Required parts would cost about 

$300,000 per engine. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $927,600. 

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 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 reasons discussed above, I 

certify that this AD: 

(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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 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 adding 

the following new airworthiness 

directive: 

2009–08–06 General Electric Company: 

Amendment 39–15879. Docket No. 

FAA–2008–0827; Directorate Identifier 

2008–NE–26–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 18, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–80A series turbofan 

engines with any of the following stage 

1 high-pressure turbine (HPT) rotor disk 

part numbers (P/Ns), installed: 

(1) 1380M69G01; 1380M69G02; 

1380M69G04; 1380M69G05; or 

1380M69G06; or 

(2) 9234M67G12; 9234M67G13; 

9234M67G14; 9234M67G15; or 

9234M67G16; or 

(3) 9362M58G04; or 

(4) 9367M45G01; 9367M45G03; 

9367M45G05; 9367M45G06; 

9367M45G07; or 9367M45G08. 

(d) These CF6–80A series turbofan 

engines are installed on, but not limited 

to, Airbus A310–200 series and Boeing 

767–200 and –300 series airplanes. 

Unsafe Condition 

(e) This AD results from the FAA 

learning that those disks are susceptible 

to cracks developing at the aft chamfer 

of the blade dovetail slots. We are 

issuing this AD to prevent cracks 

developing at the aft chamfer of the 

blade dovetail slots that could propagate 

to a failure of the disk and cause an 

uncontained engine failure and damage 

to the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed 

within 30 days after the effective date of 

this AD, unless the actions have already 

been done. 

(g) Remove from service HPT stage 1 

rotor disks identified by P/N in 

paragraph (c) of this AD. 

Prohibition of HPT Stage 1 Rotor Disks 

(h) After the effective date of this AD, 

do not install any of the HPT stage 1 

rotor disks, listed by P/N in paragraph 

(c) of this AD into any engine. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for 

this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Contact Robert Green, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

robert.green@faa.gov; telephone: (781) 

238–7754, fax: (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(k) None. 

Issued in Burlington, Massachusetts, on 

April 6, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8263 Filed 4–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1207; Directorate 

Identifier 2007–NE–47–AD; Amendment 39– 

15880; AD 2009–08–07] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. ALF502L–2 and 

ALF502L–2C Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Honeywell International Inc. ALF502L– 

2 and ALF502L–2C turbofan engines 

with certain high-pressure compressor 

(HPC) first stage discs installed. This AD 

requires performing a dimensional 

inspection to determine if excessive disc 

balance material was removed and a 

magnetic particle inspection if the disc