69612 Federal Register / Vol. 75, No. 219 / Monday, November 15, 2010 / Proposed Rules 

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 with FAA 

personnel concerning this proposed AD 

rescission. Using the search function of 

the Web site, anyone can find and read 

the comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

On April 23, 1998, the FAA Engine & 

Propeller Directorate issued engine AD 

98–09–27 (63 FR 24911, May 6, 1998). 

On April 30, 2001, the FAA Transport 

Airplane Directorate issued airplane AD 

2001–09–14 (66 FR 23838, May 10, 

2001). Those ADs both require the same 

initial and repetitive visual inspections 

of Rolls-Royce plc RB211–Trent 768 and 

772 series turbofan engine thrust 

reverser hinge lugs and attachment ribs 

for cracks, and, if necessary, removal 

from service and replacement with 

serviceable parts. 

Since we issued engine AD 98–09–27 

and airplane AD 2001–09–14, we 

determined that duplicate ADs to 

address the same unsafe condition were 

unnecessary. 

FAA’s Determination and Requirements 

of This Proposed AD Rescission 

We are proposing this AD rescission 

of AD 98–09–27 because we evaluated 

all information and determined that two 

FAA ADs with the same requirements 

are not necessary. 

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 

rescission would not have federalism 

implications under Executive Order 

13132. This proposed AD rescission 

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 rescission of a 

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 rescission and placed 

it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 

rescinding airworthiness directive (AD) 

98–09–27, Amendment 39–10508 (63 

FR 24911, May 6, 1998): 

Rolls-Royce plc: Docket No. FAA–2010– 

0960; Directorate Identifier 98–ANE–09– 

AD. 

Comments Due Date 

(a) We must receive comments by 

December 30, 2010. 

Affected ADs 

(b) This AD rescinds AD 98–09–27. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

RB211–Trent 768, 772, and 772B turbofan 

engines. These engines are installed on, but 

not limited to, Airbus A330–341 and A330– 

342 series airplanes. 

Issued in Burlington, Massachusetts, on 

November 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28583 Filed 11–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1111; Directorate 

Identifier 2010–NM–129–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200B, –300, –400, 

–400D, and –400F Series Airplanes 

Powered by Pratt and Whitney 4000 or 

General Electric CF6–80C2 Series 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 747–200B, –300, –400, –400D, 

and –400F series airplanes. This 

proposed AD would require an 

inspection to determine the part number 

of the door and to determine if the 

correct mid-pivot access door is 

installed, and the installation of a 

marker on the mid-pivot access door, 

and if necessary, repetitive ultrasonic 

inspections for cracking of the midpivot bolt assembly and eventual 

replacement of the mid-pivot bolt 

assembly. This proposed AD results 

from a report that the left and right 

spring beam mid-pivot bolt assembly 

access doors for the No. 1 strut were 

inadvertently installed in the incorrect 

position during strut modification. We 

are proposing this AD to detect and 

correct incorrectly installed mid-pivot 

bolt assemblies on the spring beam on 

the outboard struts. Incorrectly installed 

bolt assemblies could lead to fatigue 

cracking and consequent fracturing of 

the mid-pivot bolt assembly, which 

could lead to loss of the spring beam 

load path and the possible separation of 

a strut and engine from the airplane 

during flight. 

DATES: We must receive comments on 

this proposed AD by December 30, 

2010. 

ADDRESSES: You may send comments by 

any of the following methods: 


hsrobinson on DSK69SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 219 / Monday, November 15, 2010 / Proposed Rules 69613 

• 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. 

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: 

Kenneth Paoletti, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6434; 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–2010–1111; Directorate Identifier 

2010–NM–129–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 

We have received a report that the 

mid-pivot access doors on the No. 1 

strut were inadvertently installed in the 

incorrect position during strut 

modification. The design of the access 

doors can allow the doors to be installed 

on either side of the strut. The midpivot access door has machined tabs 

that fit the slots in the head of the midpivot bolt assembly. The machined tabs 

correctly orient the mid-pivot bolt 

assembly and prevent the mid-pivot bolt 

from rotating in the spring beam. The 

correct orientation of the mid-pivot bolt 

reduces the fatigue on the cross-drilled 

lubrication channel. If the lubrication 

channel is not in the correct orientation, 

fatigue cracking could develop in the 

mid-pivot bolt assembly. The fatigue 

cracking could lead to the fracture of the 

mid-pivot bolt assembly. Fracture of the 

mid-pivot bolt assembly could result in 

the loss of the spring beam load path. 

Loss of the spring beam load path could 

result in the separation of a strut and 

engine from the airplane during flight. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–54A2232, dated 

April 15, 2010. The service bulletin 

describes procedures for doing an 

inspection to determine the part number 

of the door and to determine if the 

correct mid-pivot access door is 

installed. For airplanes on which the 

correct door is installed, the service 

bulletin describes procedures for 

installing a marker on the mid-pivot 

access door. For airplanes on which the 

correct access door is not installed, 

Boeing Alert Service Bulletin 747– 

54A2232, dated April 15, 2010, 

describes procedures for rotating the 

mid-pivot bolt assembly to the correct 

orientation and replacing the access 

door, and installing the marker on the 

mid-pivot access door. In addition, for 

those airplanes without the correct door, 

the service bulletin describes 

procedures for doing one of two options: 

• Doing repetitive ultrasonic 

inspections for cracks of the mid-pivot 

bolt assembly, and if no cracking is 

found, eventually replacing the 

assembly. 

• Replacing the mid-pivot bolt 

assembly before further flight. Replacing 

the mid-pivot bolt assembly terminates 

the need for repetitive inspections. 

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 these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 95 airplanes of U.S. 

registry. We also estimate that it would 

take about 3 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $24,225, or $255 per 

product. 

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: 


hsrobinson on DSK69SOYB1PROD with PROPOSALS
69614 Federal Register / Vol. 75, No. 219 / Monday, November 15, 2010 / Proposed Rules 

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. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–1111; Directorate Identifier 2010– 

NM–129–AD. 

Comments Due Date 

(a) We must receive comments by 

December 30, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200B, –300, –400, 

–400D, and –400F series airplanes, 

certificated in any category; equipped with 

Pratt and Whitney 4000 or General Electric 

CF6–80C2 series engines, as identified in 

Boeing Alert Service Bulletin 747–54A2232, 

dated April 15, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/pylons. 

Unsafe Condition 

(e) This AD results from a report that the 

left and right spring beam mid-pivot bolt 

assembly access doors for the no. 1 strut were 

inadvertently installed in the incorrect 

position during strut modification. The 

Federal Aviation Administration is issuing 

this AD to detect and correct incorrectly 

installed mid-pivot bolt assemblies on the 

spring beam on the outboard struts. 

Incorrectly installed bolt assemblies could 

lead to fatigue cracking and consequent 

fracturing of the mid-pivot bolt assembly, 

which could lead to loss of the spring beam 

load path and the possible separation of a 

strut and engine from the airplane during 

flight. 

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. 

Inspection To Determine if Correct Door Is 

Installed 

(g) Within 24 months after the effective 

date of this AD, do an inspection to 

determine if the correct mid-pivot access 

door is installed, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2232, dated April 

15, 2010. 

(h) If, during the inspection required by 

paragraph (g) of this AD, the correct midpivot door is found to be installed, before 

further flight, install a marker on the midpivot access door, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2232, dated April 

15, 2010. 

(i) If, during the inspection required by 

paragraph (g) of this AD, the correct midpivot door is not found to be installed, before 

further flight, do the actions required by 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2232, dated April 15, 2010. 

(1) Rotate the mid-pivot bolt assembly to 

the correct orientation and replace the midpivot access door with a new or serviceable 

mid-pivot access door. 

(2) Install a marker on the mid-pivot access 

door. 

(3) Do the actions required by paragraph 

(i)(3)(i) or (i)(3)(ii) of this AD. 

(i) (Option 1) Do an ultrasonic inspection 

for cracking of the mid-pivot bolt assembly. 

(A) If no cracking is found, do the actions 

required by paragraphs (i)(3)(i)(A)(1) and 

(i)(3)(i)(A)(2) of this AD. 

(1) Repeat the ultrasonic inspection for 

cracking of the mid-pivot bolt assembly 

thereafter at intervals not to exceed 24 

months until the action required by 

paragraph (i)(3)(i)(A)(2) of this AD is done. 

(2) Within 60 months after the effective 

date of this AD, replace the mid-pivot bolt 

assembly with a new mid-pivot bolt 

assembly. Replacement terminates the 

repetitive inspections required by paragraph 

(i)(3)(i)(A)(1) of this AD. 

(B) If any cracking is found, replace the 

mid-pivot bolt assembly with a new midpivot bolt assembly, before further flight. 

(ii) (Option 2) Replace the mid-pivot bolt 

assembly with a new mid-pivot bolt 

assembly. 

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: 

Kenneth Paoletti, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6434; fax (425) 

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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 

November 2, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28605 Filed 11–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 516 

[Docket No. FDA–2010–N–0534] 

New Animal Drugs for Minor Use and 

Minor Species 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Proposed rule. 

SUMMARY: The Food and Drug 

Administration (FDA) is proposing to 

amend its regulations regarding new 

animal drugs for minor use and minor 

species to update language and to clarify 

the regulations consistent with the 

explanations in the preambles to the 

proposed and final rules establishing 

them. This action is being taken to 

ensure accuracy and clarity in the 

Agency’s regulations. This proposed 

rule is a companion document to the 

direct final rule published elsewhere in 

this issue of the Federal Register. 

DATES: Submit electronic or written 

comments by January 31, 2011. 

ADDRESSES: You may submit comments, 

identified by Docket No. FDA–2010–N– 

0534, by any of the following methods: 


hsrobinson on DSK69SOYB1PROD with PROPOSALS