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

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 

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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: 

ESTIMATED COSTS

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. 

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

ESTIMATED COSTS—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 

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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—ALL MATERIAL INCORPORATED BY REFERENCE

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 

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