### 30795 Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules

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 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 Airworthiness Directive (AD): Eurocopter Deutschland GmbH: Docket No. FAA–2013–0446; Directorate Identifier 2010–SW–007–AD. (a) Applicability

This AD applies to Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, with bearing, part number (P/N) LN9367GE6N2; rod, P/N L671M5040205; lever, P/N L671M5040101; and floor, P/N L533M1014101, L533M1014102, L533M1014103, L533M1014104, L533M1014105 or L533M1014106, installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as limited control of a tail rotor because of the binding of a bearing. This condition could result in subsequent loss of control of the helicopter.
(c) 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.
(d) Required Actions

(1) Within 100 hours time-in-service (TIS) and thereafter at intervals not to exceed 800 hours TIS, inspect each bearing for freedom of movement by turning and tilting the bearing as depicted in Figure 2 of Eurocopter Alert Service Bulletin No. EC135–67A–012, Revision 1, dated October 18, 2006 (ASB). During any inspection:

(i) If there is binding or rough turning, before further flight, replace the bearing with an airworthy bearing.

(ii) If there is chafing on the lower side of the floor that does not extend through the panel outer layer, before further flight, replace the bearing with an airworthy bearing.

(iii) If there is damage on the lower side of the floor in the area of the assembly opening that extends through the panel outer layer (revealing an open honeycomb cell or layer), before further flight, replace the bearing with an airworthy bearing and repair the floor.

(2) After performing the actions in (d)(1)(i) through (iii) of this AD, before further flight, install a Teflon strip and identify the floor by following the Accomplishment Instructions, paragraphs 3.E.(1) through 3.E.(4), of the
ASB.

(3) Within 100 hours TIS, modify and reidentify the rod as depicted in Figure 1 of the ASB and by following the Accomplishment Instructions, paragraphs 3.H.(1) through 3.H.(3)(f), of the ASB.
(e) Alternative Methods of Compliance (AMOC)

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

(2) For operations conducted under 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.

(f) Additional Information

(1) 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 copies 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 AD No. 2006–0318 R1, dated October 27, 2006.
(g) Subject

The Joint Aircraft System/Component (JASC) Code is 6720: Tail Rotor Control System.

Issued In Fort Worth, Texas, on May 14,

2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–12309 Filed 5–22–13; 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]** 

**RIN 2120–AA64**

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

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for Hamilton Standard Division model 6/ 5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF, 14SF, 247F, and 568F series propellers. This proposed AD was prompted by the amount of corrosion detected during major inspections (MIs). This proposed AD would require incorporating inspections, based on a calendar time, into the propeller maintenance schedule. We are proposing this AD to prevent corrosion that could result in propeller failure and loss of airplane control.

**DATES :**  We must receive comments on this proposed AD by July 22, 2013.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Hamilton Sundstrand Corporation, One Hamilton Road, Mail Stop 1A–3–C63, Windsor Locks, CT 06096–1010; or Hamilton Standard Division, One Hamilton Road, United Technologies Corporation, Mail Stop 1A–3–C63, Windsor Locks, CT 06096–1010; phone: 877–808–7575; fax: 860–660–0372; email: tech.solutions@hs.utc.com; Internet: http://myhs.hamiltonsundstrand.com.

You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England


### 30796 Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules

Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–
7125. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**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 :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2013–0262; Directorate Identifier 2013– NE–13–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 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 will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

We received reports about increased corrosion detected during MIs of Hamilton Standard Division model 6/ 5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF, 14SF, 247F, and 568F series propellers. The propellers were found to accumulate fewer flight hours per year as they aged. The longer time between MIs contributes to an increased potential for corrosion to accumulate to critical limits. Hamilton Sundstrand developed, and we approved, six Airworthiness Limitations Sections (ALSs) of the applicable maintenance manuals to date. Each ALS establishes the new compliance times for MIs of the blades and hubs by adding a calendar time limit for the inspection. This condition, if not corrected, could result in propeller failure and loss of airplane control.

Relevant Service Information

We reviewed the Hamilton Sundstrand ALS in Maintenance Manual P5185, Revision 13, dated December 13, 2011; P5206, Revision 9, dated February 22, 2013; P5186, Revision 12, dated January 20, 2012; P5207, Revision 2, dated June 28, 2012; P5188, Revision 10, dated January 14, 2013; and P5189, Revision 8, dated March 26, 2013. The ALS in these maintenance manuals lists the MIs for the associated propellers and prescribe a seven-year calendar time limit interval for MI of propeller blades and hubs.

FAA’s Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements

This proposed AD would require incorporating a seven-year calendar time limit, between MIs of propeller blades and hubs, into the propeller maintenance schedule, within 45 days after the effective date of the AD. Differences Between the Proposed AD and the Service Information

The updated maintenance manuals require that an MI of the blades and hubs be performed at the published flight hours or no later than seven years since the date since installation (DSI). The DSI will begin at initial installation after the most recent MI or initial installation after production. This proposed AD would require that the Hamilton Sunstrand propeller models, with an approved update to the maintenance manual ALS, have 45 days after the effective date of the AD to incorporate the seven-year calendar time limit. These models/manuals are: 14RF–9/P5186, 14RF–21/P5189, 14SF– 5/P5188, 14SF–7/P5185, 14SF–11E/ P5207, and 568F–1/P5206. This proposed AD would also require that the Hamilton Sundstrand and Hamilton Standard propeller models, without approved updates to the maintenance manual ALS, incorporate the seven-year calendar time limit into the propeller maintenance schedule within one year after the effective date of the AD. These models/manuals are: Hamilton Standard 24PF/61–12–01 and 6/5500/F/P5190, and Hamilton Sundstrand 14RF–19/ P5199, 14RF–37/P5209, 14SF–11/ P5196, 14SF–15/P5197, 14SF–23/P5197, 14SF–17/P5198, 14SF–19/P5198, 247F– 1/P4202, 247F–1E/P5204, 247F–3/ P5205, 568F–1/P5214, 568F–5/P5203, and 568F–7/P5211. Costs of Compliance

We estimate that this proposed AD would affect about 1,044 propeller/hub combinations installed on airplanes of U.S. registry. We also estimate that it would take about 160 hours per propeller to perform one MI. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $14,198,400. 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 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),

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and


### 30797 Federal Register / Vol. 78, No. 100 / Thursday, May 23, 2013 / Proposed Rules

(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. 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 airworthiness directive (AD): Hamilton Standard Division and Hamilton Sundstrand Corporation: Docket No. FAA–2013–0262; Directorate Identifier 2013–NE–13–AD.

(a) Comments Due Date

We must receive comments by July 22,
2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to Hamilton Standard Division 6/5500/F and 24PF and Hamilton Sundstrand Corporation 14RF, 14SF, 247F, and 568F series propellers.

(d) Unsafe Condition

This AD was prompted by the amount of corrosion detected during major inspections (MI). We are issuing this AD to prevent corrosion that could result in propeller failure and loss of airplane control.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.

(f) MI for Blades and Hubs That Have an Updated Airworthiness Limitations Section (ALS)

For Hamilton Sundstrand Corporation propeller models 14RF–9, 14RF–21, 14SF–5, 14SF–7, 14SF–11E, and 568F–1, that have an approved update to the ALS, within 45 days after the effective date of this AD, perform an MI on the blades and hubs no later than seven years since the date since installation (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 Sundstrand Corporation models/manuals 14RF–9/P5186, revision 12, January 20, 2012; 14RF–21/P5189, revision 8, March 26, 2013; 14SF–5/P5188, revision 10, dated January 14, 2013; 14SF–7/P5185, revision 13, dated December 13, 2011; 14SF– 11E/P5207, revision 2, dated June 28, 2012; and 568F–1/P5206 revision 9, dated February 22, 2013. (g) MI for Blades and Hubs That Do Not Have an Updated ALS

For Hamilton Standard Division model 6/ 5500/F and 24PF and Hamilton Sundstrand Corporation model 14RF–19, 14RF–37, 14SF–11, 14SF–15, 14SF–23, 14SF–17, 14SF–19, 247F–1, 247F–1E, 247F–3, 568F–1, 568F–5, 568F–7 propellers, 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 since 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 models/manuals for Hamilton Standard Division 6/5500/F/ P5190 and 24PF/61–12–01, and Hamilton Sundstrand Corporation 14RF–19/P5199, 14RF–37/P5209, 14SF–11/P5196, 14SF–15/ P5197, 14SF–23/P5197, 14SF–17/P5198, 14SF–19/P5198, 247F–1/P4202, 247F–1E/ P5204, 247F–3/P5205, 568F–1/P5214, 568F– 5/P5203, and 568F–7/P5211 propellers.
(h) Alternative Methods of Compliance (AMOCs)

The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request.

(i) Related Information

(1) For more information about this AD, 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.

(2) For service information identified in this AD, contact Hamilton Sundstrand Corporation, One Hamilton Road, Mail Stop 1A–3–C63, Windsor Locks, CT 06096–1010; or Hamilton Standard Division, United Technologies Corporation, One Hamilton Road, Mail Stop 1A–3–C63, Windsor Locks, CT 06096–1010; phone: 877–808–7575; fax: 860–660–0372; email: tech.solutions@hs.utc.com; Internet: http:// myhs.hamiltonsundstrand.com.

(3) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call

781–238–7125.

Issued in Burlington, Massachusetts, on May 17, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–12260 Filed 5–22–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 71**

**[Docket No. FAA–2012–1175; Airspace Docket No. 12–AAL–11]** 

**Proposed Amendment of Class E Airspace; Point Thomson, AK** 

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

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

**SUMMARY :**  This action proposes to modify the airspace at Point Thomson, AK by establishing Class E Airspace at Point Thomson Airstrip Airport, Point Thomson, AK. This will accommodate aircraft using a new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at the airport. The FAA is proposing this action to enhance the safety and management of aircraft operations at the airport.

**DATES :**  Comments must be received on or before July 8, 2013.

**ADDRESSES :**  Send comments on this proposal 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; telephone (202) 366–9826. You must identify FAA Docket No. FAA–2012–1175; Airspace Docket No. 12–AAL–11, at the beginning of your comments. You may also submit comments through the Internet at http://www.regulations.gov.

**FOR FURTHER INFORMATION CONTACT :**  Richard Roberts, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue SW., Renton, WA 98057; telephone (425) 203–4517.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal.

Communications should identify both docket numbers (FAA Docket No. FAA– 2012–1175 and Airspace Docket No. 12– AAL–11) and be submitted in triplicate