This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510.

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# Rules and Regulations Federal Register 

### 9777

Vol. 78, No. 29

Tuesday, February 12, 2013

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0075; Directorate Identifier 2012–SW–104–AD; Amendment**  **39–17336; AD 2013–03–02]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

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

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

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA–365N1, AS– 365N2 and AS 365 N3 helicopters. That AD currently requires inspecting certain tail rotor hubs (TRH) for a crack and removing any cracked TRH. This AD requires the same actions but adds more part numbers to the list of affected TRHs. This AD is prompted by further analysis that indicates that additional part-numbered TRHs must be inspected for cracks. The actions specified by this AD are intended to detect a crack in the TRH and prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.

**DATES :**  This AD becomes effective February 27, 2013.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of February 27, 2013.

We must receive comments on this AD by April 15, 2013.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001.

• Hand Delivery: Deliver to the ‘‘Mail’’ address 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 economic 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 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.

**FOR FURTHER INFORMATION CONTACT :**  Robert Grant, Aviation Safety Engineer, Standards Staff, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222–5328; email robert.grant@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments.

Discussion

On September 14, 2012, we issued AD 2012–19–09, Amendment 39–17204 (77 FR 58925, September 25, 2012), for Eurocopter Model EC 155B, EC155B1, SA–365N1, AS–365N2 and AS 365 N3 helicopters with a 10-bladed TRH, part number (P/N) 365A33351100, 365A33351101, or 365A33351102, installed. That AD requires visually inspecting the TRH for a crack and removing the TRH if a crack exists. The AD was prompted by reports of cracks on two TRHs. Those actions are intended to prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, issued EASA AD No. 2011–0144, dated July 26, 2011, to correct an unsafe condition for Eurocopter Model EC 155B, EC155B1, SA–365N1, AS–365N2 and AS 365 N3 helicopters, based on reports of 2 cases of cracked TRHs. Pending further investigation, EASA AD 2011–0144 required repetitive inspections of 10-bladed TRHs every 55 flight hours. EASA considered the actions in its AD to be interim measures and expected further AD actions. Actions Since Existing AD Was Issued

Since we issued AD 2012–19–09, Amendment 39–17204 (77 FR 58925, September 25, 2012), Eurocopter determined that helicopters with 11- bladed TRHs must also be inspected for cracks. Based on this further analysis by Eurocopter, EASA determined that the inspections must also be applied to AS 365 N2 helicopters with an 11-bladed TRH. Therefore, EASA issued superseding EASA AD 2012–0227, dated October 29, 2012, to extend the applicability to include the 11-bladed TRHs.


### 9778 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations

FAA’s Determination

These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, 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.

Related Service Information

Following the report of cracks found on the TRH of a Model AS–365 helicopter, Eurocopter issued Alert Service Bulletin (ASB) No. EC 155– 05A021, Revision 0, dated April 11, 2011, for Model EC 155B and EC155B1 helicopters and ASB No. AS365– 05.00.60, Revision 0, dated April 11, 2011, for Model SA–365N1, AS–365N2, AS 365 N3, and some military helicopters. After a second report of TRH cracks, the ASBs were revised, dated July 20, 2011, to mandate and reduce the repetitive inspection interval from 110 flight hours to 55 flight hours.

On October 9, 2012, Eurocopter again revised ASB No. AS365–05.00.60 by issuing Revision 2 to extend the applicability to 11-bladed TRHs in Model AS 365 N3 helicopters.

The ASBs call for visually inspecting the TRH for a crack and, if a crack is found, removing the TRH. EASA classified these ASBs as mandatory and issued superseding AD No. 2012–0227 to ensure the continued airworthiness of these helicopters.
AD Requirements

This AD requires visually inspecting the TRH for a crack within 55 hours time in service (TIS) and, if a crack exists, removing the TRH from service. This inspection must be repeated at intervals not to exceed 55 hours TIS.

Interim Action

We consider this AD to be an interim action because Eurocopter is still investigating the cause of TRH cracks. If a final action is later identified, we might consider additional rulemaking. Costs of Compliance

We estimate that this AD will affect 44 helicopters of U.S. Registry and thatlabor costs will average $85 a workhour. We expect that it will take 1 workhour to visually inspect the TRH for a crack, and that helicopters will average 5 inspections per year. Thus, we estimate a total annual cost of $425 per helicopter, and $18,700 for the U.S. operator fleet.
FAA’s Justification and Determination of the Effective Date

Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule, because the required corrective actions must be accomplished within 55 hours TIS, a very short time period based on the average utilization rate of the highest usage helicopter model.

Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impractical and contrary to the public interest and that good cause exists for making this amendment effective in less than 30 days. 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, 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:

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

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing Amendment 39–17204 (77 FR 58925, September 25, 2012) and adding the following new airworthiness directive (AD):
2013–03–02 Eurocopter France Helicopters: Amendment 39–17336; Docket No. FAA–2013–0075; Directorate Identifier 2012–SW–104–AD.
(a) Applicability

This AD applies to Eurocopter Model EC 155B, EC155B1, SA–365N1, AS–365N2 and AS 365 N3 helicopters with a 10-bladed tail rotor hub (TRH), part number (P/N) 365A33351100, 365A33351101, or 365A33351102 installed; and Model AS 365 N3 helicopters with an 11-bladed TRH, P/N 365A33216001or 365A33216003, installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in the TRH that could lead to a tail rotor jam, and subsequent reduced or loss of control of the helicopter.

(c) Affected ADs

This AD supersedes AD 2012–19–09, Amendment 39–17204, Docket No. FAA– 2012–1018, Directorate Identifier 2011–SW– 052–AD (77 FR 58925, September 25, 2012).

(d) Effective Date

This AD becomes effective February 27,
2013.


### 9779 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations

(e) 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.
(f) Required Actions

(1) Within 55 hours time-in-service (TIS), and thereafter at intervals not to exceed 55 hours TIS, using a light, visually inspect the TRH for a crack in the entire area shown as Area C of the TRH in Figure 1 of Eurocopter Alert Service Bulletin (ASB) No. EC155– 05A021, Revision 1, dated July 20, 2011, or ASB No. AS365–05.00.60, Revision 2, dated October 9, 2012, as applicable to your helicopter model. The inspection area is on the tail gearbox (TGB) side of the TRH. The TGB is shown as (c) in figures 2 and 3 of the ASBs. You must pay particular attention to the area around the screws, shown as (e) in Figure 3 of the ASBs, and the TRH between the lower part of the TGB and its fairing, shown as (d) in figures 2 and 3 of the ASBs, using details D and E of Figure 3 in the ASBs. You must turn the tail rotor by hand to inspect the entire Area C.

(2) If there is a crack on the TRH, remove the TRH from service.
(g) Special flight permits

No special flight permits will be permitted.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Standards Staff, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222–5328; email robert.grant@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.

(i) Additional Information

The subject of this AD is addressed in European Aviation Safety Agency AD No. 2012–0227, dated October 29, 2012.
(j) Subject

Joint Aircraft Service Component (JASC) Code: 6420, Tail Rotor Head.
(k) 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) Eurocopter Alert Service Bulletin No. EC155–05A021, Revision 1, dated July 20,
2011.

(ii) Eurocopter Alert Service Bulletin No. AS365–05.00.60, Revision 2, dated October 9,
2012. (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 view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(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 Fort Worth, Texas, on January 28,
2013. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–02581 Filed 2–11–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1111; Directorate Identifier 2012–NM–114–AD; Amendment**  **39–17342; AD 2013–03–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Hawker Beechcraft Corporation (Type**  **Certificate Previously Held by Raytheon Aircraft Company; Beech**  **Aircraft Corporation) Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (Type Certificate previously held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400A airplanes. This AD was prompted by a report that the wiring for the 5-volt direct current (DC) system is undersized and does not have adequate circuit protection for the smaller gauge wire. This AD requires installing an in-line fuse in the 5-volt DC system for each of the five instrument lighting control power supplies. We are issuing this AD to prevent failure of the wiring, which could result in smoke in the cockpit, loss of cockpit lighting, and potential damage to surrounding wiring for other cockpit equipment such as the stick shaker function or angle-of-attack indicators.

**DATES :**  This AD is effective March 19,
2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 19, 2013.

**ADDRESSES :**  For service information identified in this AD, contact Hawker Beechcraft Corporation, Department 62, P.O. Box 85, Wichita, KS 67201–0085; telephone 316–676–8238; fax 316–676– 6706; email tmdc@hawkerbeechcraft.com; Internet https://www.hawkerbeechcraft.com/ service

_ support/pubs. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Richard Rejniak, Aerospace Engineer, Electrical Systems and Avionics Branch, ACE–119W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; phone: (316) 946–4128; fax (316) 946–4107; email: richard.rejniak@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on November 5, 2012 (77 FR 66411). That NPRM proposed to require installing an in-line fuse in the 5-volt DC system for each of the five instrument lighting control power supplies.

Comments

We gave the public the opportunity to participate in developing this AD. We