### 67020 Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations

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


### 67021 Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations

received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington,
DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Chinh Vuong, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email chinh.vuong@ faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On June 20, 2013, at 78 FR 37150, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to ECD Model BO105C (C–2 and CB–2 Variants) and BO105S (CS–2 and CBS–2 Variants) helicopters with a third stage turbine wheel, part number (P/N) 23065833, installed. The NPRM proposed to require installing a placard on the instrument panel next to the triple RPM indicator and revising the Limitations sections of the Model BO 105C/CS andBO105 CB/CBS RFMs to limit steadystate operations between speeds of 86.5% and 95.5%. The proposed requirements were 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.

The NPRM was prompted by AD No. 2010–0128, dated June 25, 2010, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued AD No. 2010–0128 to correct an unsafe condition for Model BO 105 C, BO 105 D, and BO 105 S helicopters, and certain variants of those models. EASA advises that several failures of third stage turbine wheels used in Rolls Royce Corporation (RRC) 250 series engines have occurred. According to EASA, RRC has determined that detrimental vibrations can occur within a particular range of turbine speeds, and may be a contributing factor to these failures. This condition, if not corrected, could result in loss of engine power, possibly resulting in an emergency landing and injuries to the helicopter occupants. To address this, RRC issued Commercial Engine Bulletin (CEB) A–1400, now at revision 3, for engines with a third stage turbine wheel, P/N 23065833, installed. CEB A–1400 introduces an operational limitation to avoid engine power turbine (N2) steady-state operation in a speed range between 86.5% and 95.5% for more than 60 seconds in single or cumulative events. In response, ECD has revised the RFM and has provided aplacard to inform pilots to avoid steadystate operations between 86.5% and 95.5% turbine speeds.

The EASA AD requires amending the RFMs and installing a placard as described in ECD Alert Service Bulletin No. BO105–60–110, Revision 1, dated March 3, 2010 (ASB BO105).

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 37150, June 20, 2013).

FAA’s Determination

These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

ECD has issued ASB BO105, which contains procedures for installing a placard on the instrument panel stating the prohibited steady-state turbine operating range. Revision 1 of ASB BO105 removed the temporary RFM pages as these changes were included in the most recent revisions of the BO105C/CS and BO105CB/CBS RFMs.
Costs of Compliance

We estimate that this AD affects 80 helicopters of U.S. Registry.

Based on an average labor rate of $85 per hour, we estimate that operators will incur the following costs in order to comply with this AD. Amending the RFM will require about 0.5 work-hour, for a cost per helicopter of about $43 and a cost to U.S. operators of $3,440. Installing the decal will require about 0.2 work-hour, and required parts will cost about $5, for a cost per helicopter of $22 and a cost to U.S. operators of $1,760. Based on these estimates, the total cost of this AD is $65 per helicopter and $5,200 for the U.S. operator fleet. 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 helicopters 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 to the extent that it justifies making a regulatory distinction; 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.

We prepared an economic evaluation of the estimated costs to comply with this 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.
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:


### 67022 Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations

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):
2013–20–17 Eurocopter Deutschland GMBH (ECD): Amendment 39–17623; Docket No. FAA–2013–0519; Directorate Identifier 2010–SW–068–AD.
(a) Applicability

This AD applies to ECD Model BO105C (C– 2 and CB–2 Variants) and BO105S (CS–2 and CBS–2 Variants) helicopters with a third stage turbine wheel, part number 23065833, installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a third stage turbine vibration, which could result in turbine failure, engine power loss and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective December 13,

2013.
(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Within 30 days: (1) For BO105C–2 and BO105CS–2 Variant helicopters, revise the Rotorcraft Flight Manual (RFM), Section 2, Limitations Section, by inserting page 2–25 of ECD Flight Manual BO 105 C/CS, revision 5, dated March 12, 2010.

(2) For BO105CB–2 and BO105CBS–2 Variant helicopters, revise the RFM, Section 2, Limitations Section, by inserting pages 2– 8 and 2–27 of ECD Flight Manual BO 105 CB/ CBS, revision 8, dated March 12, 2010.

(3) Install a placard on the instrument panel next to the triple RPM indicator that states: MIN. CONTINUOUS 98% N2—MIN. TRANSIENT 95% N 2 . (f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Chinh Vuong, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email chinh.vuong@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
(g) Additional Information

(1) ECD Alert Service Bulletin No. BO105– 60–110, Revision 1, dated March 3, 2010, which is not incorporated by reference,
contains additional information about the subject of this AD. 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 a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2010–0128, dated June 25, 2010. You may view the EASA AD on the internet in
the AD Docket at http://www.regulations.gov.

(h) Subject

Joint Aircraft Service Component (JASC)
Code: 7250: Turbine Section.

(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) Page 2–25 of Section 2, Limitations, of Eurocopter Deutschland GmbH Flight Manual BO 105 C/CS, Revision 5, dated March 12, 2010.

(ii) Pages 2–8 and 2–27 of Section 2, Limitations, of Eurocopter Deutschland GmbH Flight Manual BO 105 CB/CBS, Revision 8, dated March 12, 2010.

(3) For Eurocopter 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.

(4) You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

(5) You may also 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 Fort Worth, Texas, on September
20, 2013.
Scott A. Horn, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–26562 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–2013–0481; Directorate Identifier 2011–SW–003–AD; Amendment**  **39–17653; AD 2013–22–21]**

**RIN 2120–AA64**

**Airworthiness Directives; Bell Helicopter Textron, Inc., Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 206A, 206B, 206L, 206L–1, 206L–3, 206L–4, and 407 helicopters with an Apical Industries, Inc. (Apical) emergency float kit installed under Supplemental Type Certificate (STC) Number SR01535LA. This AD was prompted by an incident in which the floats installed on a helicopter failed to deploy. This AD requires inspecting, labeling, and replacing the float inflation hoses. We are issuing this AD to prevent failure of the emergency floatation gear to deploy during an emergency event.

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

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

**ADDRESSES :**  For service information identified in this AD, contact Apical Industries, Inc., 2608 Temple Heights Drive, Oceanside, CA 92056–3512; telephone (760) 724–5300; fax: (760) 758–9612; or at www.apicalindustries.com . You may review copies of 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 Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the STC, 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,