## 22305 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

Parts Installation

(l) As of the effective date of this AD, no person may install, on any airplane, a THSA, unless it is in compliance with the requirements of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI does not include a reporting requirement; however, the service bulletin recommends reporting. Paragraph (k) of this AD specifies a reporting requirement.

Other FAA AD Provisions

(m) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved.Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (n) Refer to MCAI EASA Airworthiness Directive 2010–0092, dated May 21, 2010; Airbus Mandatory Service Bulletin A300– 27A6067, Revision 02, including Appendix 01, dated October 18, 2010; Airbus Mandatory Service Bulletin A310–27A2104, Revision 02, including Appendix 01, dated October 18, 2010; and Goodrich Actuation Systems Component Maintenance Manual with Illustrated Parts List, Horizontal Stabilizer Actuator, P/N 47142 Series, Document 27–44–13, Revision 8, dated December 12, 2008, for related information.
Material Incorporated by Reference

(o) You must use Airbus Mandatory Service Bulletin A310–27A2104, Revision 02, including Appendix 01, dated October 18, 2010; and Airbus Mandatory Service Bulletin A300–27A6067, Revision 02, including Appendix 01, dated October 18, 2010; to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating actions specified by this AD, you must use Goodrich Actuation Systems Component Maintenance Manual with Illustrated Parts List, Horizontal Stabilizer Actuator, P/N 47142 Series, Document 27–44–13, Revision 8, dated December 12, 2008, to perform those actions unless the AD specifies otherwise. (The LOEP in Goodrich Actuation Systems Component Maintenance Manual with Illustrated Parts List, Horizontal Stabilizer Actuator, P/N 47142 Series, Document 27– 44–13, Revision 8, dated December 12, 2008, specifies that page 749 is placed after page 748a; the correct placement of page 749 is between pages 748 and 747a. The LOEP of this document identifies two pages for the Illustrated Parts List section; there is only one page for that section (page 1001–1). The date on page 1014–1 of this document is incorrect; the correct date is March 6, 1998.)

(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 Airbus service information identified in this AD, contact Airbus SAS— EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// www.airbus.com.

(3) For Goodrich service information identified in this AD, contact Goodrich Corporation Actuation Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England; telephone +44 (0) 1902 624938; fax: +44 (0) 1902 788100; e-mail techpubs.wolverhampton@goodrich.com; Internet http://www.goodrich.com/TechPubs.

(4) 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.

(5) 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

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on March 23, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–8279 Filed 4–20–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1271; Directorate Identifier 2010–NM–187–AD; Amendment**  **39–16667; AD 2011–09–05]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Model 777–200, –300, and –300ER Series Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing an auto shutoff feature for the center override/jettison fuel pumps, and installing power control circuitry for the center override/jettison and main jettison fuel pumps. This AD also requires installing new software in the electrical load management system (ELMS) electronics units in certain power management panels; installing airplane information management system 2 (AIMS–2) software in the AIMS–2 hardware; and making certain wiring changes. This AD was prompted by results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

**DATES** 

### : This AD is effective May 26,
2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 26, 2011.

**ADDRESSES** 

### : 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


## 22306 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

me.boecom@boeing.com; Internet https://www.myboeingfleet.com . For GE Aviation service information identified in this AD, contact GE Aviation, Customer Services—Clearwater, P.O. Box 9013, Clearwater, Florida 33758; telephone 727–539–1631; fax 727–539– 0680; e-mail cs.support@ge.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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT** 

### : Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 917–6482; fax: 425–917–6590; e-mail: Georgios.Roussos@faa.gov

. **SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on December 30, 2010 (75 FR 82337). That NPRM proposed to require installing an auto shutoff feature for the center override/jettison fuel pumps, and installing power control circuitry for the center override/jettison and main jettison fuel pumps. That NPRM also proposed to require installing new software in the electrical load management system (ELMS) electronics units in certain power management panels; installing airplane information management system 2 (AIMS–2) software in the AIMS–2 hardware; and making certain wiring changes.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Boeing supports the NPRM. Request To Delay Issuance of AD To Specify Spring Washers Instead of Conical Springs

Japan Airlines (JAL) requested that we delay issuance of the AD until GE Aviation Service Bulletins 5000ELM– 28–456 and 6000ELM–28–457, both Revision 1, both dated January 7, 2010, are revised to correct Figure 8. JAL stated that Figure 8 shows conical springs rather than spring washers in the diagram. JAL stated that without this change, operators will be required to request an alternate method of compliance (AMOC).

We disagree with delaying issuance of this AD. However, we agree that clarification is needed in regard to the use of spring washers. Certain airplanes may use spring washers in lieu of conical springs in their relay assembly. Both the conical springs and spring washers are retained from the existing relay assembly to be used with the new relay. Either one of them is considered acceptable for use. New paragraph (m) has been added to the AD to identify the use of spring washers as an acceptable method of compliance if they are part of the existing relay assembly. Request To Delay Issuance of AD To Specify Label Installation

JAL requested that we delay the issuance of this AD until GE Aviation publishes new revisions to their service information (referenced in the NPRM) to add another procedure to install labels or separate the labels from the conversion kit. JAL explained that when it receives the labels as part of the conversion kit, the remaining shelf life of the labels is not adequate to allow the labels to be installed on the airplanes. JAL is concerned that, unless the service information is revised, these issues could delay incorporation of this AD or result in multiple AMOC requests.

We disagree with the request to delay this AD until GE Aviation issues revised service information. However, we agree with JAL’s concerns about the shelf life of the labels possibly affecting operators’ ability to comply with this AD within the required compliance times. This AD requires all actions, including labeling, in the Accomplishment Instructions of GE Aviation Service Bulletins 5000ELM– 28–456 and 6000ELM–28–457, both Revision 1, both dated January 7, 2010, to be accomplished. We have added paragraph (n) to this AD to provide an optional method of labeling.

Conclusion

We reviewed the relevant data, considered 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:

• Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM.

We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance

We estimate that this AD affects 2 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Installation: Groups 1 and 2,

Configuration 2. 149 work-hours × $85 per hour = $12,665 ................... $15,719 $28,384 ............... $56,768.

Installation: Groups 1 and 2,

Configuration 1. 2 work-hours × $85 per hour = $170 ............................ 15,719 $15,889 ............... $31,778.

Concurrent requirement: Install

ELMS software. 3 work-hours × $85 per hour = $255 ............................ 0 $255 .................... $510.

Concurrent requirement: Upgrade

AIMS–2 software. Up to 2 work-hours × $85 per hour = Up to $170 ........ 0 Up to $170 .......... Up to $340.

Concurrent requirement: P110

wiring changes. 3 work-hours × $85 per hour = $255 ............................ $1,164 $1,419 ................. $2,838.


## 22307 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

E STIMATED 

### C OSTS 

### —Continued

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Concurrent requirement: P210

wiring changes. 3 work-hours × $85 per hour = $255 ............................ 1,164 $1,419 ................. $2,838.



### 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

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),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. 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 FAA 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 (AD):
2011–09–05 The Boeing Company: Amendment 39–16667; Docket No. FAA–2010–1271; Directorate Identifier 2010–NM–187–AD.

Effective Date

(a) This AD is effective May 26, 2011.

Affected ADs

(b) None.
Applicability

(c) The Boeing Company Model 777–200, –300, and –300ER series airplanes; certificated in any category; as identified in Boeing Service Bulletin 777–28A0047, Revision 5, dated September 20, 2010.
Subject

(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 28, Fuel.

Unsafe Condition

(e) This AD was prompted by results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
Compliance

(f) Comply with this AD within the compliance times specified, unless already done.

Installation

(g) For airplanes in Groups 1 and 2, Configuration 2, as identified in Boeing Service Bulletin 777–28A0047, Revision 5, dated September 20, 2010: Within 36 months after the effective date of this AD, install a new P301 panel on the left side of the airplane, install a new P302 panel on the right side of the airplane, and change the wiring, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–28A0047, Revision 5, dated September 20, 2010, except as required by paragraphs (m) and (n) of this AD.

(h) For airplanes in Groups 1 and 2, Configuration 1, as identified in Boeing Service Bulletin 777–28A0047, Revision 5, dated September 20, 2010: Within 36 months after the effective date of this AD, perform bonding resistance measurements and rework the airplane installation as applicable, depending on airplane configuration, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 28A0047, Revision 5, dated September 20,
2010. Concurrent Requirements

(i) Prior to or concurrently with accomplishing the requirements of paragraph (g) of this AD, do the actions specified in paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD.

(1) Install new software in the electrical load management system (ELMS) electronics units in the P110, P210, and P310 power management panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–28A0040, Revision 1, dated March 18, 2010.

(2) Install airplane information management system 2 (AIMS–2) software in the AIMS–2 hardware, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–31– 0097, Revision 3, dated February 22, 2007.

(3) Modify the P110 left power management panel by incorporating wiring changes, in accordance with the Accomplishment Instructions of GE Aviation Service Bulletin 5000ELM–28–456, Revision 1, dated January 7, 2010, except as provided by paragraphs (m) and (n) of this AD.

(4) Modify the P210 right power management panel by incorporating wiring changes, in accordance with the Accomplishment Instructions of GE Aviation Service Bulletin 6000ELM–28–457, Revision 1, dated January 7, 2010, except as provided by paragraphs (m) and (n) of this AD.
Credit for Actions Accomplished in Accordance With Previous Service Information

(j) Installations done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 777–28A0040, dated April 13, 2007, are acceptable for compliance with the requirements of paragraph (i)(1) of this AD.

(k) Installations done before the effective date of this AD in accordance with Boeing Service Bulletin 777–28A0047, Revision 3, dated June 11, 2009; or Revision 4, dated May 20, 2010; are acceptable for compliance with the requirements of paragraphs (g) and (h) of this AD.

(l) Installations done before the effective date of this AD in accordance with Boeing Special Attention Service Bulletin 777–31– 0097, dated March 30, 2006; Revision 1, dated August 10, 2006; or Revision 2, dated October 26, 2006; are acceptable for


## 22308 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

compliance with the requirements of paragraph (i)(2) of this AD.
Optional Methods of Compliance With Certain Actions

(m) Where paragraph 2.A.(16) and Figure 8 of GE Aviation Service Bulletins 5000ELM– 28–456 and 6000ELM–28–457, both Revision 1, both dated January 7, 2010, identify the installation of conical springs for the relay to relay base fixing, installation of spring washers is an acceptable method of compliance when they are part of the existing relay assembly.

(n) Where paragraphs 2.A.(24) and 2.A.(25) of GE Aviation Service Bulletins 5000ELM– 28–456 and 6000ELM–28–457, both Revision 1, both dated January 7, 2010, specify the installation of a label to identify work carried out and to identify the appropriate service bulletin, an acceptable method of compliance is to use a suitable method to indelibly mark the appropriate service bulletin number on the reworked panel. Boeing Standard BAC5307 may be used as an additional source of guidance for part marking.
Alternative Methods of Compliance (AMOCs)

(o)(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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

Related Information

(p) For more information about this AD, contact Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425–917–6482; fax: 425–917–6590; e-mail: Georgios.Roussos@faa.gov.
Material Incorporated by Reference

(q) You must use the applicable service information contained in table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise.



### TABLE 

### 1—A LL 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Document Revision Date

Boeing Service Bulletin 777–28A0047 ........................................................................................................ 5 September 20, 2010. Boeing Service Bulletin 777–28A0040 ........................................................................................................ 1 March 18, 2010. Boeing Special Attention Service Bulletin 777–31–0097 ............................................................................ 3 February 22, 2007. GE Aviation Service Bulletin 5000ELM–28–456 ......................................................................................... 1 January 7, 2010. GE Aviation Service Bulletin 6000ELM–28–457 ......................................................................................... 1 January 7, 2010.

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

(2) For Boeing 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. For GE Aviation service information identified in this AD, contact GE Aviation, Customer Services— Clearwater, P.O. Box 9013, Clearwater, Florida 33758; telephone 727–539–1631; fax 727–539–0680; e-mail cs.support@ge.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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on April 12,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–9283 Filed 4–20–11; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0310; Directorate Identifier 2010–NM–133–AD; Amendment**  **39–16663; AD 2011–09–01]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A340–541 and –642 Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule; request for
comments.

**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:

* * * * *

* * * [S]ome Allowable Damage Limits and Repairs published in SRM Chapters 57–61–12 PB101 and 57–61–12 PB201 were devalidated starting from the SRM revision issued on January 2009. The terminology

‘‘ De-validated SRM ’’ used in this AD text refers to the SRM chapters mentioned above.

In order to prevent complete inner aileron split due to possible failure or disbonding of the repairs on the inner aileron panels performed as per ‘‘ devalidated SRM ’’ , which may result in flutter coupling of the free aileron part, this AD requires a one time inspection of the inner aileron panels to identify the presence of ‘‘ de-validated SRM ’’ repairs and, if necessary, to apply the associated corrective actions [repair]. 

### The flutter coupling of the free aileron part might result in separation of the aileron from the airplane, degradation of airplane control, and increased workload for the flight crew. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES** 

### : This AD becomes effective May 6, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 6, 2011.

We must receive comments on this AD by June 6, 2011.

**ADDRESSES** 

### : You may send comments by any of the following methods:

• 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 W12–40, 1200 New Jersey