## 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


## 22309 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT** 

### : Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone: 425–227–1138; fax: 425–227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0056, dated March 29, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

Following a Structural Repair Manual (SRM) repair strength re-valuation, some Allowable Damage Limits (ADL) and Repairs of holes and delaminations in composite panels have been found to be no more compliant with certification requirements for A340–500/–600 inner aileron.

Therefore, some 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 [tap test and detailed visual inspection or thermography 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 may result in separation of the aileron from the airplane, degradation of airplane control, and increased workload for the flight crew. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A340–57–5026, including Appendices 1 and 2, dated February 1, 2010. 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 AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD.

FAA’s Determination of the Effective Date

Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** 

### section. Include ‘‘ Docket No. FAA–2011–0310; Directorate Identifier 2010–NM–133– AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of 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 we receive about this AD. 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 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 this AD:

1. Is not a ‘‘ significant regulatory action ’’ under Executive Order 12866;

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 AD and placed it in the AD docket.


## 22310 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations

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 AD:

2011–09–01 Airbus: Amendment 39–16663. Docket No. FAA–2011–0310; Directorate Identifier 2010–NM–133–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective May 6, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A340– 541, and –642 airplanes; certificated in any category; all serial numbers.
Subject

(d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

(e) The mandatory continued airworthiness information (MCAI) states:


### * * * * *

* * * [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 may result in separation of the aileron from the airplane, degradation of airplane control, and increased workload for the flight crew.
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) Within 800 flight hours after the effective date of this AD, do a tap test and detailed inspection or a thermography inspection of the affected inner aileron panels at the left and right wings to detect any previously accomplished repairsperformed in accordance with any devalidated structural repair manual (SRM) defined in Airbus Mandatory Service Bulletin A340–57–5026, dated February 1, 2010; do the actions in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A340–57–5026, dated February 1, 2010.

Note 1: For the purposes of this AD, a detailed inspection is: ‘‘ An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. ’’

(h) A review of airplane maintenance records is acceptable in lieu of the inspection required by paragraph (g) of this AD if therepairs performed in accordance with devalidated SRM, defined in Airbus service bulletin A340–57–5026, dated February 1, 2010 (SRM revisions dated before January 2009), can be conclusively identified from that review.
Repair

(i) If any de-validated SRM repairs are found during any actions required by this AD, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (or its delegated agent).

Parts Installation

(j) As of the effective date of this AD, no person may install an inner aileron panel having a de-validated SRM repair as defined in Airbus Mandatory Service Bulletin A340– 57–5026, dated February 1, 2010, unless it is inspected as specified in paragraph (g) of this AD and all applicable corrective actions are done.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–
3356; telephone: 425–227–1138; 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.

(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.

Related Information

(l) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2010–0056, dated March 29, 2010; and Airbus Mandatory Service Bulletin A340–57–5026, dated February 1, 2010; for related information.
Material Incorporated by Reference

(m) You must use Airbus Mandatory Service Bulletin A340–57–5026, excluding Appendix 1 and including Appendix 2, dated February 1, 2010, to do the actions required by this AD, 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 Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; e-mail: airworthiness.A330-A340@airbus.com; Internet: http://www.airbus.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

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on April 8,

2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–9277 Filed 4–20–11; 8:45 am]

**BILLING CODE 4910–13–P**