## 16655 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations

(1) Where Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, specifies a compliance time relative to the date of issuance of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) Where Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, specifies contacting Boeing for repair data: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Optional New Modification for Areas 1, 2, 3, and 4

(m) For areas 1, 2, 3, and 4 as defined in Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008: Doing the modification and post-modification actions specified in Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, terminates the repetitive inspection requirements of paragraphs (g) and (h) of thisAD. Doing the modification and postmodification actions specified in Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, terminates the repetitive inspection requirements of paragraph (l) of this AD, except at the upper deck floor beam at body station (BS) 460 and 480 and the upper deck floor beams aft of BS 520.
No Reporting Requirement

(n) Although Boeing Alert Service Bulletin 747–53A2439, Revision 1, dated March 10, 2005; and Boeing Alert Service Bulletin 747– 53A2439, Revision 2, dated July 17, 2008; specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs)

(o)(1) The Manager, Seattle 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: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. Or, e-mail information to 9-ANM-Seattle-ACOAMOC-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) AMOCs approved previously in accordance with AD 2006–08–02, are approved as AMOCs for the corresponding provisions of this AD.

(4) 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.
Material Incorporated by Reference

(p) You must use Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the new optional actions specified by this AD, you must use Boeing Alert Service Bulletin 747–53A2696, dated October 16, 2008, to perform those actions, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this 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

.

(3) You may review copies of the 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.

(4) You may also review copies of the service information that is incorporated by reference 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

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_ federal

_regulations/ ibr

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. Issued in Renton, Washington, on March 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–6546 Filed 4–1–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2005–19559; Directorate Identifier 2004–NE–03–AD; Amendment 39–**  **16254; AD 2010–07–09]**

**RIN 2120–AA64**



### Airworthiness Directives; Rolls-Royce **plc RB211–Trent 700 Series Turbofan Engines** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211–Trent 700 series turbofan engines. That AD currently requires initial and repetitive borescopeinspections of the high-pressure-andintermediate pressure (HP–IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD requires the same actions, but adds additional inspections of the vent flow restrictor. This AD results from further analysis that the cleaning of the vent tubes required by AD 2007–02–05 could lead to loosened carbon fragments, causing a blockage downstream in the vent flow restrictor. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup that could cause uncontained engine failure and damage to the airplane.

**DATES** 

### : This AD becomes effective May 7, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of May 7, 2010.

**ADDRESSES** 

### : You can get the service information identified in this AD from Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 011–44–1332– 249428; fax: 011–44–1332–249223.

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** 

### : 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** 

### : The FAA proposed to amend 14 CFR part 39 by superseding AD 2007–02–05, Amendment 39–14892 (72 FR 2603, January 22, 2007), with a proposed AD. The proposed AD applies to Rolls-Royce plc RB211–Trent 700 series turbofan engines. We published the proposed AD in the Federal Register on October 26, 2009 (74 FR 54940). That action proposed to require initial and repetitive borescope inspections of the HP–IP turbine internal and external oil vent tubes for coking and carbon buildup, cleaning or replacing the vent tubes if necessary, and inspections of the vent flow restrictor. 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,


## 16656 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations

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 comments received. Request to Reference the Latest Service Bulletin

One commenter, Rolls-Royce plc, requests that we incorporate by reference the latest alert service bulletin (ASB) in the AD, which is ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009.

We agree. We changed the AD to incorporate by reference Revision 8 of that ASB. Request To Allow Previous Credit

Rolls-Royce plc requests that we allow previous credit to operators that performed the initial inspections specified in paragraph (f) of the proposed AD before the AD effective date, using Revision 4, Revision 5, Revision 6, or Revision 7 of ASB No. RB.211–72–AE302.

We agree and added a previous credit paragraph to the AD. Request to Change Initial Inspection Threshold

Rolls-Royce plc requests that we change the initial inspection threshold from 3 months to 2 months, to agree with the ASB.

We agree and changed the AD. Clarification of AD Compliance Section

We clarified paragraphs (g) and (h) of the AD compliance section to better align with the Rolls-Royce plc ASB.

Conclusion

We have carefully reviewed the available data, including the comments 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. Costs of Compliance

Based on the service information, we estimate that this AD will affect about 33 engines of U.S. registry. We also estimate that it will take about one work-hour per engine to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $2,000 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $68,640. 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, Incorporation by reference, 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 removing Amendment 39–14892 (72 FR 2603, January 22, 2007), and by adding a new airworthiness directive, Amendment 39–16254, to read as follows:
2010–07–09 Rolls-Royce plc: Amendment 39–16254. Docket No. FAA–2005–19559; Directorate Identifier 2004–NE–03–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective May 7, 2010.

Affected ADs

(b) This AD supersedes AD 2007–02–05, Amendment 39–14892.
Applicability

(c) This AD applies to Rolls-Royce plc RB211–Trent 768–60, RB211–Trent 772–60, and RB211–Trent 772B–60 series turbofan engines. These engines are installed on, but not limited to, Airbus A330–243, –341, –342 and –343 series airplanes.

Unsafe Condition

(d) This AD results from further analysis that the cleaning of the vent tubes required by AD 2007–02–05 could lead to loosened carbon fragments, causing a blockage downstream in the vent flow restrictor. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup that could cause uncontained engine failure and damage to the airplane.
Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Initial Inspections, Cleaning, and Replacements

(f) Using the schedule in Table 1 of this AD, borescope-inspect and clean asnecessary, the high-pressure-andintermediate pressure (HP–IP) turbine internal oil vent tubes, external oil vent tubes, and bearing chamber.


## 16657 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations

T ABLE 

### 1—I NITIAL 

### I NSPECTION 

### S CHEDULE

If the engine or the 05 Module Then initially inspect

Has reached 10,000 hours time-since-new (TSN) or reached 2,500 cycles-since-new (CSN) on the effective date of this AD. Within 2 months after the effective date of this AD.

Has fewer than 10,000 hours TSN and fewer than 2,500 CSN on the

effective date of this AD. Within 2 months after reaching 10,000 hours TSN or 2,500 CSN, whichever occurs first. Is returned for an engine shop visit ......................................................... Before returning to service.

(1) If after cleaning, there is still carbon in the vent tube that prevents cleaning tool number HU80298 from passing through the tube, then replace the internal oil vent tube within 10 cycles-in-service (CIS).

(2) If after cleaning, there is still carbon of visible thickness in either of the two external oil vent tubes, then replace the external oil vent tube before further flight.

(3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment Instructions and Appendix A of Rolls-Royce plc Alert Service Bulletin (ASB) No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the borescope inspections and cleaning of the oil vent tubes and bearing chamber.
Initial Visual Inspection of the Vent Flow Restrictor

(g) For engines that, on the effective date of this AD, have not accumulated 25 service cycles since the last cleaning and inspection specified in paragraphs (f) through (f)(3) of this AD, visually inspect the vent flow restrictor:

(1) Either after a high-power ground run immediately following the cleaning and inspection; or

(2) Within 25 service cycles of the last cleaning and inspection.

(h) For engines that, on the effective date of this AD, have accumulated 25 or more service cycles since the last cleaning and inspection specified in paragraphs (f) through (f)(3) of this AD, visually inspect the vent flow restrictor within 25 service cycles after the effective date of this AD.

(i) Use paragraph 3.A.(8) of the Accomplishment Instructions of Rolls-Royce plc ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the visual inspections. Repetitive Inspections, Cleaning, and Replacements

(j) Within 6,400 hours time-in-service since last inspection and cleaning, or within 1,600 cycles-since-last inspection and cleaning, or at the next engine shop visit, whichever occurs first, borescope-inspect the HP–IP turbine internal and external oil vent tubes and bearing chamber, and clean the oil vent tubes as necessary.

(1) If after cleaning there is still carbon in the internal oil vent tube that prevents cleaning tool, number HU80298, from passing through the tube, then replace the internal oil vent tube within 10 CIS.

(2) If after cleaning there is still carbon of visible thickness, in either of the two external oil vent tubes, then replace the external oil vent tube before further flight.

(3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment Instructions and Appendix A of Rolls-Royce plc ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the borescope inspections and cleaning of the oil vent tubes and bearing chamber.

(k) Visually inspect the vent flow restrictor either after a high-power ground run or within 25 service cycles after performing the cleaning and inspection specified in paragraph (f) through (f)(3) of this AD. Use paragraph 3.A.(8) of the Accomplishment Instructions of Rolls-Royce plc ASB No. RB.211–72–AE302, Revision 8, dated October 21, 2009, to do the visual inspection.

Definition

(l) For the purpose of this AD, an engine shop visit is induction of the engine into the engine shop for any cause.

Previous Credit

(m) Initial inspections specified in paragraph (f) of this AD and performed beforethe effective date of this AD using RollsRoyce plc ASB No. RB.211–72–AE302, Revision 4, dated April 30, 2007, or Revision 5, dated May 22, 2007, or Revision 6, dated January 29, 2009, or Revision 7, dated April 30, 2009, satisfy the initial inspection requirements in paragraph (f) of this AD.
Alternative Methods of Compliance

(n) 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

(o) European Aviation Safety Agency AD 2007–0201, dated August 1, 2007, and AD 2007–0202 (corrected August 8, 2007), also address the subject of this AD.

(p) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & 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.
Material Incorporated by Reference

(q) You must use Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AE302, Revision 8, dated October 21, 2009, including Appendix A, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; 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/cfr/ibrlocations.html.

Issued in Burlington, Massachusetts, on March 25, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–7283 Filed 4–1–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–1166; Directorate Identifier 2009–NM–107–AD; Amendment**  **39–16255; AD 2010–07–10]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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:

One operator reported loss of both pitch trims following autopilot disengagement after take off. Subsequent shop findings revealedsevere damage to the power gears. Malphasing between the hydraulic motors was suspected to have induced excessive loads into the gear train, leading to collapse of one bearing on a shaft of the main gear, causing severe tooth damage. The combination of tooth damage and gear tilting caused the disconnection of two of the three hydraulic motors, resulting in jamming of the THSA [trimmable horizontal stabilizer actuator] gearbox and consequent loss of THSA control.