### 13536 Federal Register / Vol. 76, No. 49 / Monday, March 14, 2011 / Proposed Rules

Restatement of Requirements of AD 2009– 22–13, With Revised Service Information
Inspection and Related Investigative/ Corrective Actions

(g) For Model 767–200, –300, –300F, and –400ER series airplanes, as identified in Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008: Within 60 months after December 3, 2009 (the effective date of AD 2009–22–13), do the actions in paragraphs (g)(1) and (g)(2) of this AD.

(1) Inspect the motor operated valves (MOVs) in the main and center fuel tanks to determine if any MOV having part number (P/N) MA20A1001–1 is installed, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008; or Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review. After the effective date of this AD, only Revision 2 may be used.

(2) Do all applicable related investigative and corrective actions specified in and in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008; or Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010; except as provided by paragraph (h) of this AD. After the effective date of this AD, only Revision 2 may be used.

Alternative Part Numbers

(h) Where Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008; or Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010; specifies replacing any actuator having P/N MA20A1001–1 with a new actuator having P/N MA30A1001, a serviceable actuator having any of the following part numbers is also acceptable as a replacement part: MA30A1001; MA20A2027 (S343T003–56); MA11A1265–1 (S343T003–41); or AV–31–1 (S343T003– 111).
New Requirements of This AD
Inspection and Related Investigative/ Corrective Actions for Additional Airplanes

(i) For airplanes that are identified in Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010, but are not identified in paragraph (g) of this AD: Within 60 months after December 3, 2009, do the actions required by paragraph (g) of this AD in accordance with Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010.
Revised Inspection and Related Investigative/Corrective Actions Instructions for Certain Airplanes

(j) For airplanes having variable numbers (VNs) VN921, VN922, and VN966 through VN972 inclusive, that accomplished the actions required in paragraph (g) of this AD before the effective date of this AD in accordance with Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008: Within 60 months after December 3, 2009, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) Inspect the motor operated valves (MOVs) in the main and center fuel tanks to determine if any MOV having part number (P/N) MA20A1001–1 is installed, in accordance with Work Packages 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review.

(2) Do all applicable related investigative and corrective actions specified in and in accordance with Work Packages 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010; except as provided by paragraph (h) of this AD.

(k) For airplanes having VNs VF181 through VF184 inclusive that accomplished the actions required in paragraph (g) of this AD before the effective date of this AD in accordance with Boeing Alert Service Bulletin 767–28A0090, dated July 3, 2008; or Boeing Service Bulletin 767–28A0090, Revision 1, dated April 1, 2010: Within 60 months after December 3, 2009, do the actions in paragraphs (k)(1) and (k)(2) of this AD.

(1) Inspect the motor operated valves (MOVs) in the main and center fuel tanks to determine if any MOV having part number (P/N) MA20A1001–1 is installed, in accordance with Work Packages 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review.

(2) Do all applicable related investigative and corrective actions specified in and in accordance with Work Packages 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing Service Bulletin 767–28A0090, Revision 2, dated September 2, 2010; except as provided by paragraph (h) of this AD.
Credit for Actions Accomplished in Accordance With Previous Service Information

(l) Actions done before the effective date of this AD in accordance with Boeing Service Bulletin 767–28A0090, Revision 1, dated April 1, 2010, are acceptable for compliance with the requirements of paragraphs (i) and (j) of this AD.
Alternative Methods of Compliance (AMOCs)

(m)(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.

(3) AMOCs approved previously for AD 2009–22–13 are approved as AMOCs for the corresponding provisions of this AD.

Related Information

(n) For more information about this AD, contact Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone 425– 917–6505; fax 425–917–6590; e-mail: douglas.n.bryant@faa.gov.

(o) 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. 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.

Issued in Renton, Washington, on March 4,
2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–5721 Filed 3–11–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0159; Directorate Identifier 2010–NM–246–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Model CL–600–2C10 (Regional Jet**  **Series 700, 701, & 702), Model CL–600– 2D15 (Regional Jet Series 705), and**  **Model CL–600–2D24 (Regional Jet Series 900) Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) 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:

An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the


### 13537 Federal Register / Vol. 76, No. 49 / Monday, March 14, 2011 / Proposed Rules

Horizontal Stabilizer Trim Actuator (HSTA) of the CL–600–2C10, CL–600–2D15 and CL– 600–2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact onthe HSTA life limit. The teeth of these nonconformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane.
* * * * *

The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  We must receive comments on this proposed AD by April 28, 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 Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Bombardier, Inc., 400 Co ˆ te-Vertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; e-mail thd.crj@aero.bombardier.com; Internet http://www.bombardier.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 Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7303; fax (516) 794–5531.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2011–0159; Directorate Identifier 2010–NM–246–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

Transport Canada Civil Aviation which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2010–34, dated October 5, 2010 (referred to after this as ‘‘the MCAI’’ ), to correct an unsafe condition for the specified products. The MCAI states:

An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the Horizontal Stabilizer Trim Actuator (HSTA) of the CL–600–2C10, CL–600–2D15 and CL– 600–2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact onthe HSTA life limit. The teeth of these nonconformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane.

This [Canadian airworthiness] directive mandates replacement of the RBGs which have material hardness out of specification [with a modified HSTA].

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Bombardier has issued Service Bulletin 670BA–27–058, dated August 31, 2010; and SAGEM has issued SAGEM Service Bulletin 8489–27–007, Revision 1, dated August 10, 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 Proposed 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 proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This 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 proposed 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 proposed AD. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 387 products of U.S. registry. We also estimate that it would take about 9 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $296,055, or $765 per product. 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


### 13538 Federal Register / Vol. 76, No. 49 / Monday, March 14, 2011 / Proposed Rules

detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘ Subtitle VII, Part A, Subpart III, Section 44701: General requirements. ’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

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

2. Is not a ‘‘ significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

2. The FAA amends § 39.13 by adding the following new AD:
Bombardier, Inc.: Docket No. FAA–2011– 0159; Directorate Identifier 2010–NM– 246–AD. Comments Due Date (a) We must receive comments by April 28,
2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702), Model CL–600–2D15 (Regional Jet Series 705), and Model CL–600–2D24 (Regional Jet Series 900) airplanes, certificated in any category, equipped with a horizontal stabilizer trim actuator having part numbers (P/Ns) 8489–5, 8489–6, 8489–7, and 8489–7R. Subject

(d) Air Transport Association (ATA) of America Code 27: Flight controls.

Reason

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

An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the Horizontal Stabilizer Trim Actuator (HSTA) of the CL–600–2C10, CL–600–2D15 and CL– 600–2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact onthe HSTA life limit. The teeth of these nonconformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane.
* * * * *
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.
Modifying the HSTA

(g) For airplanes having any HSTA with S/N 107, 111, 124, 126, 135, 139, 142, 145, 146, 266, 268, 271, 274, 276, 277, 280, 282 through 285 inclusive, 290, 292, 294, 297, 299, 307, 309, 320, 337, 400, 402, 403, 410, 412, 418, 421 through 428 inclusive, 430, 435 through 439 inclusive, 441, 443 through 446 inclusive, 448 through 450 inclusive, 452 through 454 inclusive, 456, 459, 461, 463 through 470 inclusive, 472, 474 through 476 inclusive, 478, 545 through 549 inclusive, 570, 571, 573, 574, 600, 603, 608, 612 through 616 inclusive, 623, 627, and 629 through 659 inclusive: At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD, replace the HSTA with a modified HSTA, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–27–058, dated August 31, 2010.

(1) For HSTAs that have accumulated 8,700 total flight cycles or less as of the effective date of this AD: Within 3,000 flight cycles from the effective date of this AD, or before the HSTA has accumulated 10,500 flight cycles, whichever occurs first.

(2) For HSTAs that have accumulated more than 8,700 total flight cycles as of the effective date of this AD: Within 1,800 flight cycles after the effective date of this AD.

(h) For airplanes having any HSTA with S/N 185, 479, 481, 482, 485, 487, 489, 491 through 496 inclusive, 498, 499, 501, 503, 504, 506, 507, 509, 512 through 514 inclusive, 517, 519 through 522 inclusive, 524, 526 through 528 inclusive, 530, 534 through 536 inclusive, 539, 542, and 543: Within 1,800 flight cycles after the effective date of this AD, replace the affected HSTA with a modified HSTA in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–27–058, dated August 31, 2010.

Parts Installation

(i) As of the effective date of this AD, no person may install a HSTA, having P/N 8489–5, 8489–6, 8489–7, or 8489–7R, with any serial numbers identified in paragraph (g) or (h) of this AD, on any airplane, unless that HSTA has been modified in accordance with SAGEM Service Bulletin 8489–27–007, Revision 1, dated August 10, 2010, and that HSTA has a suffix ‘‘B ’’ beside the serial number.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, 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. Send information to Attn: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. 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 FAA-approved 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

(k) Refer to MCAI Canadian Airworthiness Directive CF–2010–34, dated October 5, 2010; Bombardier Service Bulletin 670BA– 27–058, dated August 31, 2010; and SAGEM Service Bulletin 8489–27–007, Revision 1, dated August 10, 2010, for related information.


### 13539 Federal Register / Vol. 76, No. 49 / Monday, March 14, 2011 / Proposed Rules

Issued in Renton, Washington, on March 4,
2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5722 Filed 3–11–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0216; Directorate Identifier 2010–NM–197–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.**  **(EMBRAER) Model ERJ 190 Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) 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:

* * * The pylon internal shear pin was found cracked during a regular check. Further investigation revealed that the failure occurred due to hydrogen embrittlement. The ANAC [Age ˆ ncia Nacional de Aviac

 ̧ a  ̃ o Civil] is issuing this AD to prevent insufficient strength of the pylon to wing attachment, which in combination with an engine imbalance caused by a fan blade out could cause pylon to wing attachment failure and consequent engine separation.
* * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  We must receive comments on this proposed AD by April 28, 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 Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170—Putim—12227–901 Sa  ̃ o Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 123309–0732; fax +55 12 3927–7546; email distrib@embraer.com.br; Internet http://www.flyembraer.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 Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Cindy Ashforth, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 227–2768; fax: 425–227–1149; e-mail: cindy.ashforth@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2011–0216; Directorate Identifier 2010–NM–197–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The Age ˆ ncia Nacional de Aviac

 ̧ a  ̃ o Civil (ANAC), which is the aviation authority for Brazil, has issued Brazilian Airworthiness Directive 2010–08–02, dated September 20, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

* * * The pylon internal shear pin was found cracked during a regular check. Further investigation revealed that the failure occurred due to hydrogen embrittlement. The ANAC [Age ˆ ncia Nacional de Aviac

 ̧ a  ̃ o Civil] is issuing this AD to prevent insufficient strength of the pylon to wing attachment, which in combination with an engine imbalance caused by a fan blade out could cause pylon to wing attachment failure and consequent engine separation.
* * * * *

Required actions include replacing pylon shear pins in the rear outboard and inboard shear pin assembly in the right- and left-hand pylons with new parts. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

EMBRAER has issued Service Bulletins 190–54–0010, dated May 19, 2010; and 190LIN–54–0001, dated June 21, 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 Proposed 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 proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This 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.