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**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0936; Directorate Identifier 2013–CE–033–AD; Amendment**  **39–17652; AD 2013–22–20]**

**RIN 2120–AA64**

**Airworthiness Directives; Embraer S.A. Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Embraer S.A. Model EMB–505 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking in the stator pressure plate of the brake assembly, which may lead to loss of brake parts on the runway and reduced brake capability with possible runway excursion. We are issuing this AD to require actions to address the unsafe condition on these products.

**DATES :**  This AD is effective November 8,
2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 8, 2013.

We must receive comments on this AD by December 23, 2013.

**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 W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact EMBRAER S.A., Phenom Maintenance Support, Avenida Brigadeiro Faria Lima, 2170, Putim, CEP: 12227–901, Sao Jose dos Campos, Sao Paulo, Brasil; phone: (+55 12) 3927– 1000; Fax: (+55 12) 3927–6600, Ext. 1448; email: phenom.reliability@ embraer.com.br: Internet: http:// www.embraerexecutivejets.com/en-US/customer-support/Pages/Service-CenterNetwork.aspx. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.
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 street address for the Docket 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 :**  Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090; email: jim.rutherford@ faa.gov

.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The Agencia Nacional De Aviacoa Civil (ANAC), which is the aviation authority for Brazil, has issued emergency AD No.: 2013–09–01, dated September 26, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

It has been found the occurrence of cracks in the stator pressure plate of the brake assembly of the airplane, which may lead to loss of brake parts in the runway, and to a reduced airplane brake capability with possible runway excursion event. Since this condition may occur in other airplanes of the same type and affects flight safety, an immediate corrective action is required. Thus, sufficient reason exists to request compliance with this EAD in the indicated time limit without prior notice.
The MCAI requires an inspection to determine if the airplane has the affected part number (P/N) brake assembly installed and inspection for cracks of the affected brake assembly with repair or replacement as necessary. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0936. Relevant Service Information

Embraer S.A. has issued Phenom Alert Service Bulletin No. 505–32– A011, dated September 13, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the 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 this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracking of the stator pressure plate of the brake assembly could lead to loss of brake parts on the runway, which could result in reduced brake capability with a possible runway excursion. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

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–2013–0936; Directorate Identifier 2013–CE–033– 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


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will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance

We estimate that this AD will affect 88 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour.

Based on these figures, we estimate the cost of the AD on U.S. operators to be $14,960, or $170 per product.

In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $2,324, for a cost of $2,409 per product for repair; or 3 work-hours and require parts costing $25,187, for a cost of $25,442 per product for brake assembly replacement. We have no way of determining the number of products that may need these actions.

According to the manufacturer, all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 that 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),

(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 AD:
2013–22–20 Embraer—Empresa Brasileira de Aeronautica S.A.: Amendment 39– 17652; Docket No. FAA–2013–0936; Directorate Identifier 2013–CE–033–AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective November 8, 2013.

(b) Affected ADs

None.
(c) Applicability

This AD applies to Embraer S.A. Models EMB–505 airplanes, all serial numbers, that

are:

(1) Equipped with a part number (P/N) DAP00097–01 or P/N DAP00097–02 brake assembly; and

(2) certificated in any category.
(d) Subject

Air Transport Association of America (ATA) Code 32: Landing Gear.

(e) Reason

This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking in the stator pressure plate of the brake assembly, which may lead to loss of brake parts on the runway. We are issuing this AD to detect and correct cracking of the stator pressure plate and possible loss of brake parts on the runway, which could result in reduced brake capability and a possible runway excursion.
(f) Actions and Compliance

Unless already done, do the following actions in paragraphs (f)(1) through (f)(9) of this AD, including all subparagraphs.

(1) If the number of cycles is unknown, calculate the compliance times of cycles in this AD by using hours time-in-service (TIS). Multiply the number of hours TIS on the brake assembly by .71 to come up with the number of cycles. For the purposes of this AD some examples are below:

(i) 500 hours TIS equates to 355 cycles; and (ii) 12 hours equates to 9 cycles. (2) Do a general visual inspection (GVI) for cracks in the stator pressure plate on both the left hand (LH) and right hand (RH) brake assemblies following the Accomplishment Instructions in Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013. Use the compliance times in paragraphs (f)(2)(i) and (f)(2)(ii):

(i) For brake assemblies with 300 flight cycles or less since new or since the last overhaul: Before or upon accumulating 150 flight cycles or within the next 30 flight cycles, whichever occurs later, and repetitively thereafter at intervals not to exceed 60 flight cycles or the next tire change, whichever occurs first.

(ii) For brake assemblies with more than 300 flight cycles since new or since the last overhaul: Within the next 10 flight cycles and repetitively thereafter at intervals not to exceed 60 flight cycles or the next tire change, whichever occurs first.

(3) If no cracks are found during any of the inspections required in paragraph (f)(2) of this AD, continue the repetitive inspection intervals required in paragraph (f)(2) of this AD, including all subparagraphs.

(4) If during any of the inspections required in paragraph (f)(2) of this AD, including all subparagraphs, any crack is found in the stator pressure plate, before further flight, do a detailed inspection (DET) following the Accomplishment Instructions in Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013.

(5) If no cracks beyond the acceptable limits are found during the DET required in paragraph (f)(4) of this AD, continue the repetitive inspection intervals required in paragraph (f)(2) in this AD, including all subparagraphs.

(6) If cracks that exceed the acceptable limits are found during the DET required in paragraph (f)(4) of this AD, before further flight, repair the brake assembly following Appendix 2 of Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013; or replace the brake assembly with a brake assembly that has been inspected and found free of cracks that exceed the acceptable limits following the Accomplish Instructions of Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013. After repair or replacement of the brake assembly, the brake assembly is subject to the inspections required in paragraphs (f)(2), including all subparagraphs, of this AD.


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Note 1 to paragraph (f)(6) of this AD: Appendix 2 of Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013, includes Meggitt Aircraft Braking System Service Bulletin No. SB–32–1625, dated September 13, 2013.

(7) For the purposes of this AD, a GVI is a visual examination of an interior or exterior area, installation or assembly, to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light. It may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.

(8) For the purposes of this AD, a DET 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 mirrors, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate access procedures may be required.

(9) After the effective the date of this AD, do not install on any airplane a brake assembly P/N DAP00097–01 or P/N DAP00097–02 unless it is inspected per the requirements of this AD and continues to be crack free or the cracks do not exceed the allowable limits.
(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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.

(3) Reporting Requirements: For any reporting requirement in this AD, 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.

(h) Related Information

Refer to MCAI Agencia Nacional De Aviacoa Civil (ANAC) AD No.: 2013–09–01, dated September 26, 2013, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA–2013–0936.
(i) Material Incorporated by Reference

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

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Embraer Phenom Alert Service Bulletin No. 505–32–A011, dated September 13, 2013.

(ii) Reserved. (3) For service information identified in this AD, contact EMBRAER S.A., Phenom Maintenance Support, Avenida Brigadeiro Faria Lima, 2170, Putim, CEP: 12227–901, Sao Jose dos Campos, Sao Paulo, Brasil; phone: (+55 12) 3927–1000; Fax: (+55 12) 3927–6600, Ext. 1448; email: phenom.reliability@embraer.com.br; Internet:http://www.embraerexecutivejets.com/enUS/customer-support/Pages/Service-CenterNetwork.aspx.

(4) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

(5) You may view this 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/cfr/ibrlocations.html

.

Issued in Kansas City, Missouri, on October 30, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–26474 Filed 11–7–13; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0519; Directorate Identifier 2010–SW–068–AD; Amendment**  **39–17623; AD 2013–20–17]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for ECD Model BO105C (C–2 and CB–2 Variants) and BO105S (CS–2 and CBS–2 Variants) helicopters with a certain third stage turbine wheel installed. This AD requires installing a placard on the instrument panel and revising the limitations section of the rotorcraft flight manual (RFM). This AD is prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective December 13, 2013.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of December 13, 2013.

**ADDRESSES :**  For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. 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 foreignauthority’s AD, any incorporated-byreference service information, the economic evaluation, any comments