### 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 repetitiveinspections 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


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

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;


### 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