264 Federal Register / Vol. 75, No. 2 / Tuesday, January 5, 2010 / Proposed Rules 

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: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2009–1228; Directorate 

Identifier 2009–NM–015–AD. 

Comments Due Date 

(a) We must receive comments by February 

19, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 382, 382B, 382E, 382F, and 

382G series airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of fatigue 

cracks of the lower surface of the center wing 

box. The Federal Aviation Administration is 

issuing this AD to detect and correct such 

cracks, which could result in the structural 

failure of the wings. 

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 

(g) At the times specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, whichever 

occurs latest: Do a nondestructive inspection 

of the lower surface of the center wing box 

for any damage, in accordance with 

Lockheed Service Bulletin 382–57–85 (82– 

790), Revision 2, dated August 23, 2007, 

including Appendixes A, B, C, D, E, F, and 

G, Revision 1, dated March 8, 2007. Repeat 

the inspections thereafter at intervals not to 

exceed 10,000 flight hours. 

(1) Prior to the accumulation of 40,000 

total flight hours on the center wing. 

(2) Within 365 days after the effective date 

of this AD. 

(3) Within 10,000 flight hours on the center 

wing box after the accomplishment of the 

service bulletin if done before the effective 

date of this AD. 

Note 1: These inspection procedures 

supplement the existing Hercules Air 

Freighter progressive inspection procedures 

and previously issued Lockheed Martin 

service bulletins. After the effective date of 

this AD, there are no inspection procedures 

in those documents that fully meet the 

requirements of this AD. 

Corrective Action 

(h) If any damage is found during any 

inspection required by this AD: Before 

further flight, repair any damage using a 

method approved by the Manager, Atlanta 

Aircraft Certification Office (ACO), FAA. For 

a repair method to be approved by the 

Manager, Atlanta ACO, as required by this 

paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Exceptions to the Service Bulletin 

(i) Lockheed Service Bulletin 382–57–85 

(82–790), Revision 2, dated August 23, 2007, 

including Appendixes A, B, C, D, E, F, and 

G, Revision 1, dated March 8, 2007, specifies 

that operators may adjust thresholds and 

intervals, use alternative repetitive 

inspection intervals, and use alternative 

inspection methods, if applicable. However, 

this AD requires that any alternative methods 

or intervals be approved by the Manager, 

Atlanta ACO. For any alternative methods or 

intervals to be approved by the Manager, 

Atlanta ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically refer to this AD. 

(j) Where Lockheed Service Bulletin 382– 

57–85 (82–790), Revision 2, dated August 23, 

2007, including Appendixes A, B, C, D, E, F, 

and G, Revision 1, dated March 8, 2007, 

specifies that alternative repetitive 

inspections intervals may be used for coldworked holes, this AD does not allow the 

longer interval. This AD requires that all 

cold-worked and non-cold worked holes be 

re-inspected at 10,000-flight-hour intervals. 

(k) Where Lockheed Service Bulletin 382– 

57–85 (82–790), Revision 2, dated August 23, 

2007, including Appendixes A, B, C, D, E, F, 

and G, Revision 1, dated March 8, 2007, 

describes procedures for submitting a report 

of any damages, this AD does not require 

such action. 

Inspections Accomplished in Accordance 

With Lockheed Service Bulletin 382–57–83 

(82–783) 

(l) Inspections accomplished before the 

effective date of this AD, in accordance with 

Lockheed Service Bulletin 382–57–83 (82– 

783), Revision 1, dated August 22, 2006, 

including Appendix B, dated March 18, 

2005, are considered acceptable for 

compliance with the corresponding action 

specified in paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Atlanta Aircraft 

Certification Office, 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: Carl Gray, 

Aerospace Engineer, Airframe Branch, ACE– 

117A, FAA, Atlanta Aircraft Certification 

Office, 1701 Columbia Avenue, College Park, 

GA 30337; telephone (404) 474–5554; fax 

(404) 474–5606. 

(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. 

Issued in Renton, Washington, on 

December 23, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31289 Filed 1–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1004; Directorate 

Identifier 2009–NE–36–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–Trent 800 Series Turbofan 

Engines 

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) 

issued 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: 

During 2004, an incident was reported 

involving uncontained multiple 

intermediate-pressure (IP) turbine blade 

release on a Trent 700 engine. The blade 

release was the result of an overspeed of the 

IP turbine rotor that was initiated by an 

internal fire in the high-pressure/ 

intermediate-pressure (HP/IP) bearing 

chamber. Post-incident analysis and 

investigation has established that blockage of 

the HP/IP turbine bearing oil vent tube due 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 2 / Tuesday, January 5, 2010 / Proposed Rules 265 

to carbon deposits was a significant factor in 

the failure sequence. The Trent 800 has a 

similar type design standard to that of the 

Trent 700 and has also been found in service 

to be susceptible to carbon deposits in the oil 

vent tube. 

We are proposing this AD to prevent 

internal oil fires due to coking and 

carbon buildup in the HP/IP turbine 

bearing oil vent tube that could cause 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by February 4, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

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. 

Contact Rolls-Royce plc, P.O. Box 31, 

Derby, England; telephone: 011–44– 

1332–249428; fax: 011–44–1332– 

249223, for the service information 

identified in this proposed 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 proposed 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: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

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–2009–1004; Directorate Identifier 

2009–NE–36–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 based on 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 with FAA 

personnel concerning this proposed AD. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, notified us that an unsafe 

condition may exist on Rolls-Royce plc 

RB211 Trent 800 series turbofan 

engines. The MCAI states: 

During 2004, an incident was reported 

involving uncontained multiple IP turbine 

blade release on a Trent 700 engine. The 

blade release was the result of an overspeed 

of the IP turbine rotor that was initiated by 

an internal fire in the HP/IP bearing chamber. 

Post-incident analysis and investigation has 

established that blockage of the HP/IP turbine 

bearing oil vent tube due to carbon deposits 

was a significant factor in the failure 

sequence. The Trent 800 has a similar type 

design standard to that of the Trent 700 and 

has also been found in service to be 

susceptible to carbon deposits in the oil vent 

tube. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Rolls-Royce plc has issued Alert 

Service Bulletin (ASB) No. RB.211–72– 

AE362, Revision 1, dated April 3, 2009. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom (U.K.) and is approved for 

operation in the United States. Pursuant 

to our bilateral agreement with the U.K., 

EASA has notified us of the unsafe 

condition described in the MCAI. We 

are proposing this AD because we 

evaluated all information provided by 

EASA and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

require inspection of the HP/IP turbine 

vent tube and bearing chamber during 

each shop visit of the engine for coking 

and carbon buildup in the HP/IP turbine 

bearing oil vent tube. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 138 RB211 Trent 800 series 

turbofan engines installed on airplanes 

of U.S. registry. We also estimate that it 

would take about one work-hour per 

engine to comply with this proposed 

AD. The average labor rate is $80 per 

work-hour. Required parts would cost 

about $2,000 per engine. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$287,040. 

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; 


srobinson on DSKHWCL6B1PROD with PROPOSALS
266 Federal Register / Vol. 75, No. 2 / Tuesday, January 5, 2010 / Proposed Rules 

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. 

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: 

Rolls-Royce plc: Docket No. FAA–2009– 

1004; Directorate Identifier 2009–NE– 

36–AD. 

Comments Due Date 

(a) We must receive comments by February 

4, 2010. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc 

RB211–Trent 875–17, Trent 877–17, Trent 

884–17, Trent 884B–17, Trent 892–17, Trent 

892B–17, and Trent 895–17 turbofan engines. 

These engines are installed on, but not 

limited to, Boeing 777 series airplanes. 

Reason 

(d) During 2004, an incident was reported 

involving uncontained multiple 

intermediate-pressure (IP) turbine blade 

release on a Trent 700 engine. The blade 

release was the result of an overspeed of the 

IP turbine rotor that was initiated by an 

internal fire in the high-pressure/ 

intermediate-pressure (HP/IP) bearing 

chamber. Post-incident analysis and 

investigation has established that blockage of 

the HP/IP turbine bearing oil vent tube due 

to carbon deposits was a significant factor in 

the failure sequence. The Trent 800 has a 

similar type design standard to that of the 

Trent 700 and has also been found in service 

to be susceptible to carbon deposits in the oil 

vent tube. 

This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent internal oil fires 

due to coking and carbon buildup in the 

HP/IP turbine bearing oil vent tube that could 

cause uncontained engine failure and damage 

to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) At the next engine shop visit after the 

effective date of this AD and thereafter at 

each engine shop visit, using the 

Accomplishment Instructions of Rolls-Royce 

plc Alert Service Bulletin No. RB.211–72– 

AE362, Revision 1, dated April 3, 2009: 

(i) Inspect the HP/IP turbine bearing 

internal and external oil vent tubes and 

bearing chamber for carbon buildup. 

(ii) Clean and flush the tubes and bearing 

chamber as required. 

(iii) Reject any oil vent tubes that do not 

meet inspection requirements after cleaning. 

(2) This AD does not require reporting of 

inspection results, as does paragraphs 

3.B.(4)(g) and 3.C.(9) of Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE362, 

Revision 1, dated April 3, 2009. 

FAA AD Differences 

(f) None. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency AD 2009–0071 (corrected 

April 14, 2009), and Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE362, 

Revision 1, dated April 3, 2009, for related 

information. Contact Rolls-Royce plc, P.O. 

Box 31, Derby, England; telephone: 011–44– 

1332–249428; fax: 011–44–1332–249223, for 

a copy of this service information. 

(i) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

December 29, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31275 Filed 1–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Bureau of Customs and Border 

Protection 

DEPARTMENT OF THE TREASURY 

19 CFR Parts 101, 113, and 133 

[Docket No. USCBP–2006–0013] 

RIN 1505–AB54 

Customs and Border Protection’s 

Bond Program 

AGENCIES: Customs and Border 

Protection, Department of Homeland 

Security; Department of the Treasury. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This document proposes 

amendments to title 19 of the Code of 

Federal Regulations to reflect the 

centralization of the continuous bond 

program at Customs and Border 

Protection’s (CBP’s) Revenue Division, 

Office of Finance. Pursuant to this 

centralization, continuous bonds must 

be filed at the Revenue Division via 

mail, fax, or in an electronic format, and 

the Revenue Division will assume the 

bond functions previously performed at 

the port level. The authority to approve 

single transaction bonds will remain 

with port directors. The changes 

proposed in this document support 

CBP’s bond program by ensuring an 

efficient and uniform approach to the 

approval, maintenance, and periodic 

review of continuous bonds. 

Additionally, the proposed changes 

update provisions to accommodate the 

use of information technology and 

modern business practices. 

DATES: Comments must be received on 

or before March 8, 2010. 

ADDRESSES: You may submit comments, 

identified by Docket No. USCBP–2006– 

0013, by one of the following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments 

via Docket No. USCBP–2006–0013. 

• Mail: Trade and Commercial 

Regulations Branch, Regulations and 

Rulings, Customs and Border Protection, 

799 9th St., NW. (Mint Annex), 

Washington, DC 20229–1179. 

Instructions: All submissions received 

must include the agency name and 

docket number for this rulemaking. All 

comments received will be posted 

without change to http:// 

www.regulations.gov, including any 

personal information provided. For 

detailed instructions on submitting 

comments and additional information 

on the rulemaking process, see the 


srobinson on DSKHWCL6B1PROD with PROPOSALS