### 63852 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations

(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 adding the following new airworthiness directive (AD):

2013–20–51 Agusta S.p.A: Amendment 39– 17628; Docket No. FAA–2013–0881; Directorate Identifier 2013–SW–056–AD. (a) Applicability

This AD applies to the following Agusta S.p.A. (Type certificate currently held by AgustaWestland S.p.A) (Agusta) helicopters, with a tail rotor drive shaft flexible disc coupling (Thomas coupling) nut, part number (P/N) MS21042L4, certificated in any category:

(i) Model A109A, A109A II, A109C, A109E, A109S, A109K2, AW109SP helicopters; and

(ii) Model A119 and AW119 MKII helicopters.
(b) Unsafe Condition

This AD defines the unsafe condition as a production deficiency in a certain Thomas coupling nut. This condition could result in failure of the Thomas coupling, failure of the tail drive shaft, and subsequent loss of control of the helicopter.
(c) Effective Date

This AD is effective October 25, 2013 to all persons except those persons to whom it was made immediately effective by Emergency AD 2013–20–51, issued on October 3, 2013, which contained the requirements of this amendment. (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

(1) Before further flight, using a borescope or light source and mirror, inspect each Thomas coupling nut for a crack. If any Thomas coupling nut is cracked, before further flight, replace all the Thomas coupling nuts with nuts, P/N NAS1805–4, torqueing each nut to 5.6–7.9 Nm.

(2) Within 10 hours time-in-service or 30 days, whichever occurs first, replace each Thomas coupling nut, P/N MS21042L4, with a nut, P/N NAS1805–4, torqueing each nut to 5.6–7.9 Nm.

(3) After the effective date of this EAD, do not install a nut, P/N MS21042L4, on any Thomas coupling.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email gary.b.roach@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) Agusta Alert Bollettino Tecnico (ABT) No. 109K–58, ABT No. 109–136, ABT No. 109EP–130, ABT No. 109L–066, ABT No. 109S–055, ABT No. 109SP–069, and ABT No. 119–061, all dated September 20, 2013, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact: Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39–0331–711133; fax 39 0331 711180; or at http://www.agustawestland.com/technicalbullettins. 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) Emergency Airworthiness Directive 2013– 0225–E, effective September 21, 2013. You may view the EASA AD at http:// www.regulations.gov in Docket No. FAA–
2013–0881. (h) Subject

Joint Aircraft Service Component (JASC): 6400 Tail rotor system.

Issued in Fort Worth, Texas, on October 16,
2013. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–24937 Filed 10–24–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0262; Directorate Identifier 2013–NE–13–AD; Amendment 39–**  **17548; AD 2013–16–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Hamilton Standard Division and Hamilton**  **Sundstrand Corporation Propellers**

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

**ACTION :**  Final rule; correction.

**SUMMARY :**  The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all Hamilton Standard Division model 6/5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF, 14SF, 247F, and 568F series propellers. A maintenance manual number in paragraph (g) of the Compliance section is incorrect. This document corrects that error. In all other respects, the original document remains the same.

**DATES :**  This final rule is effective October 25, 2013. The effective date for AD 2013–16–10 (78 FR 49660, August 15, 2013) remains September 19, 2013.

**ADDRESSES :**  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 :**  Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7761; fax: 781–238–7170; email: michael.schwetz@faa.gov

. **SUPPLEMENTARY INFORMATION :**  AD 2013– 16–10, Amendment 39–17548 (78 FR 49660, August 15, 2013), currently requires incorporating inspections, based on a calendar time, into the propeller maintenance schedule for Hamilton Standard Division model 6/ 5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF, 14SF, 247F, and 568F series propellers.


### 63853 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations

As published, the maintenance manual number, P4202, as part of the model/manual number, 247F–1/P4202, in paragraph (g) of the Compliance section is incorrect.

No other part of the preamble or regulatory information has been changed; therefore, only the changed portion of the final rule is being published in the Federal Register

.

The effective date for AD 2013–16–10 (78 FR 49660, August 15, 2013) remains September 19, 2013.
Correction of Regulatory Text

**§ 39.13 [Corrected]**

■ In the Federal Register of August 15, 2013, on page 49662, in the 1st column, paragraph (g) of AD 2013–16–10 is corrected to read as follows:

* * * * * (g) MI for Blades and Hubs That Do Not Have an Updated ALS

For Hamilton Standard Division propeller models 6/5500/F and 24PF and Hamilton Sundstrand Corporation propeller models 14RF–19, 14RF–37, 14SF–11, 14SF–15, 14SF–23, 14SF–17, 14SF–19, 247F–1, 247F–1E, 247F–3, 568F–1, 568F–5, and 568F–7, that do not have an approved update to the ALS, within one year after the effective date of this AD, perform an MI on the blades and hubs no later than seven years after the DSI. The DSI will begin at initial installation after the most recent MI or initial installation after production. Guidance on the inspections can be found in the applicable Hamilton Standard Division models/manuals 6/5500/F/P5190 and 24PF/61–12–01, and Hamilton Sundstrand Corporation models/ manuals 14RF–19/P5199, 14RF–37/ P5209, 14SF–11/P5196, 14SF–15/P5197, 14SF–23/P5197, 14SF–17/P5198, 14SF– 19/P5198, 247F–1/P5202, 247F–1E/ P5204, 247F–3/P5205, 568F–1/P5214, 568F–5/P5203, and 568F–7/P5211.

* * * * *

Issued in Burlington, Massachusetts, on October 15, 2013. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–25108 Filed 10–24–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0878; Directorate Identifier 2013–SW–033–AD; Amendment**  **39–17625; AD 2013–21–01]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France (Eurocopter) Helicopters** 

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

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

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires certain inspections of each tail rotor pitch horn assembly (pitch horn) for a crack, and if there is a crack, before further flight, replacing the pitch horn with an airworthy pitch horn. This AD is prompted by a report of a crack in the yoke of a pitch horn. These actions are intended to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter.

**DATES :**  This AD becomes effective October 25, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of October 25, 2013.

We must receive comments on this AD by December 24, 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 foreignauthority’s AD, any incorporated-byreference service information, 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, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; 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

We are adopting a new AD for the specified Eurocopter helicopters. This AD requires visually inspecting each