### 52215 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules

(3) If you do not have any of the affected ECi cylinder assemblies installed on your engine, no further action is required.
(4) Cylinder Identification and Serial Number Location

(i) Check the cylinder assembly P/N and Class number. The ECi cylinder assembly, P/ N AEC631397, Class 71 or Class 76, is stamped on the bottom flange of the cylinder barrel. Guidance on the P/N and Class number description and location can be found in ECi Service Instruction No. 99–8– 1, Revision 9, dated February 23, 2009.

(ii) If you cannot see the cylinder assembly P/N when the cylinder assembly is installed on the engine, you may use the following alternative method of identification:

(A) Remove the cylinder assembly rocker box cover.

(B) Find the letters ECi, cast into the cylinder head between the valve stems.

(C) Check the cylinder head casting P/N. Affected cylinder assemblies have the cylinder head casting P/N, AEC65385, cast into the cylinder head between the valve
stems.

(D) Find the cylinder assembly S/N as specified in paragraph (e)(4)(iii) or (e)(4)(iv) of this AD, as applicable.

(iii) For ECi cylinder assemblies, P/N AEC631397, manufactured through 2008, find the cylinder assembly S/N stamped on the intake port boss two inches down from the top edge of the head.

(iv) For ECi cylinder assemblies, P/N AEC631397, manufactured on or after January 1, 2009, find the cylinder assembly S/N stamped just below the top edge of the head on the exhaust port side.
(5) Removal From Service

(i) For any affected cylinder assembly with 680 or fewer operating hours time-in-service (TIS) since new on the effective date of this AD, remove the cylinder assembly from service before reaching 1,000 operating hours TIS since new.

(ii) For any affected cylinder assembly with more than 680 operating hours TIS since new and 1,000 or fewer operating hours TIS since new on the effective date of this AD, remove the cylinder assembly from service within the next 320 operating hours TIS or within 1,160 operating hours TIS since new, whichever occurs first.

(iii) For any affected cylinder assembly with more than 1,000 operating hours TIS since new on the effective date of this AD, remove the cylinder assembly from service within the next 160 operating hours or at next engine overhaul, whichever occurs first.

(iv) For any affected cylinder assembly that has been overhauled, remove the cylinder assembly from service within the next 80 operating hours TIS after the effective date of this AD.

(f) Installation Prohibitions

After the effective date of this AD: (1) Do not repair, or reinstall onto any engine, any cylinder assembly removed per this AD.

(2) Do not install any affected ECi cylinder assembly that has been overhauled, into any engine. (3) Do not install any engine that has one or more affected overhauled ECi cylinder assemblies, onto any aircraft.

(4) Do not return to service any aircraft that has an engine installed with an ECi cylinder assembly subject to this AD, if the cylinder assembly has 1,000 or more operating hours TIS.
(g) Alternative Methods of Compliance (AMOCs)

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

(h) Related Information

(1) For more information about this AD, contact Jurgen E. Priester, Aerospace Engineer, Delegation Systems Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76193; phone: 817–222–5190; fax: 817–222–5785; email: jurgen.e.priester@faa.gov.

(2) For ECi Service Instruction No. 99–8– 1, Revision 9, dated February 23, 2009, contact Engine Components International Division, 9503 Middlex Drive, San Antonio, TX 78217; phone: 210–820–8101; Internet: http://www.eci.aero/pages/tech

_ svcpubs.aspx.

(3) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125.

Issued in Burlington, Massachusetts, on August 10, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2015–21205 Filed 8–27–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3642; Directorate Identifier 2015–CE–028–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; SOCATA Airplanes** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for SOCATA Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion of the horizontal stabilizer. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by October 13, 2015.

**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 proposed AD, contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, telephone: (954) 893–1400; fax: (954) 964–4141; Internet: http://www.socata.com. You may review this 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 by searching for and locating Docket No. FAA–2015– 3642; 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 (telephone (800) 647–5527) is in the

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

**FOR FURTHER INFORMATION CONTACT :**  Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@faa.gov.

**SUPPLEMENTARY INFORMATION :** 


### 52216 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2015–3642; Directorate Identifier 2015–CE–028–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:// 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

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2015– 0130, dated July 7, 2015 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

During accomplishment of SOCATA Service Bulletin (SB) SB10–152–55 at original issue, some operators reported finding heavy corrosion of the horizontal stabilizer (HS) spar.

The results of the technical investigation have identified that the corrosion was caused by humidity ingress in the HS on aeroplanes subject to severe environmental conditions.

This condition, if not detected and corrected, could result in buckling and permanent HS distortion, possibly resulting in reduced control of the aeroplane.

To address this unsafe condition, SOCATA issued SB 10–152–55 Revision 1 to provide instructions for inspection and corrective action.

For the reasons described above, this AD requires repetitive inspections of the affected area of the HS and, depending on findings, accomplishment of applicable corrective action(s).

You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–3642.

Related Service Information Under 1 CFR Part 51

SOCATA has issued DAHER– SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April 2015. The service information describes procedures for inspection for corrosion on horizontal stabilizer spar and repair, if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section of this NPRM. FAA’s Determination and Requirements of the Proposed 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 proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance

We estimate that this proposed AD will affect 195 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 proposed AD. The average labor rate is $85 per work-hour.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $33,150, or $170 per product.

In addition, we estimate that any necessary follow-on actions would take about 15 to 38 work-hours and require parts costing $250 to $400 depending on the type of repair, for a cost of $2,325 to $4,280 per product. The cost may vary depending on the extent of damage found. We have no way of determining the number of products that may need these actions. 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, 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. 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 AD:

SOCATA: Docket No. FAA–2015–3642; Directorate Identifier 2015–CE–028–AD.

(a) Comments Due Date

We must receive comments by October 13,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to SOCATA Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes, all manufacturer serial numbers, certificated in any category.
(d) Subject

Air Transport Association of America (ATA) Code 55: Stabilizers.


### 52217 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules

(e) Reason

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as humidity in the horizontal stabilizer on airplanes subject to severe environmental conditions. We are issuing this AD to detect and correct corrosion of the horizontal stabilizer (HS) spar, which could lead to result in buckling and permanent HS distortion, possibly resulting in reduced control.
(f) Actions and Compliance

Unless already done, do the actions in paragraphs (f)(1) through (f)(5) of this AD:

(1) Within 13 months after the effective date of this AD and repetitively thereafter at intervals not to exceed 72 months, do a special detailed inspection of the HS spar following the instructions of DAHER– SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April 2015.

(2) If no discrepancy is detected during any inspections required by paragraph (f)(1) of this AD, protect the HS spar following the instructions of DAHER–SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April 2015.

(3) If any discrepancy is detected during any inspection required by paragraph (f)(1) of this AD, before further flight, do the applicable corrective action(s) following the instructions of DAHER–SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April 2015.

(4) Accomplishment of protection or corrective actions on an airplane as required by paragraph (f)(2) or (f)(3) of this AD, as applicable, does not constitute terminating action for the repetitive inspections as required by paragraph (f)(1) of this AD for that airplane.

(5) Inspections and corrective actions on an airplane, done before the effective date of this AD following the instructions of DAHER– SOCATA TB Aircraft Recommended Service Bulletin SB 10–152, dated May 2013, are acceptable to comply with the requirements of this AD for that airplane. After the effective date of this AD, repetitive inspections and applicable corrective actions, as required by this AD, must be done as required by paragraph (f)(1) of this AD following the instructions of DAHER– SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April 2015.
(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: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; fax: (816) 329– 4090; email: albert.mercado@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.
(h) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2015–0130, dated July 7, 2015; and DAHER–SOCATA TB Aircraft Recommended Service Bulletin SB 10–152, dated May 2013, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–3642. For service information related to this AD, contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, telephone: (954) 893–1400; fax: (954) 964–4141; Internet: http://www.socata.com. You may review this 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.

Issued in Kansas City, Missouri, on August 20, 2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–21283 Filed 8–27–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 187**

**[Docket No.: FAA–2015–3597; Notice No. 15–06]** 

**RIN 2120–AK53**

**Update of Overflight Fee Rates**

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

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

**SUMMARY :**  This proposed rule would update existing overflight fee rates using more current FAA cost accounting and air traffic activity data. Overflight fees are charges for aircraft flights that transit U.S.-controlled airspace, but neither land in nor depart from the United States. Overflight fee rates were last updated in 2011. As a result, the FAA is not recovering the full cost of the services it provides. The FAA proposes to increase the rates for Enroute and Oceanic overflights based on fiscal year 2013 cost and air traffic activity data. The FAA proposes to phase in this rate increase over three years in equal percentage terms. This is a less burdensome approach than the alternative of phasing in the new rates in equal absolute terms, and is the same methodology used in the previous rulemaking. Finally, the FAA proposes several organizational and clarifying revisions to the overflight fee requirements.

**DATES :**  Send comments on or before October 27, 2015.

**ADDRESSES :**  Send comments identified by docket number FAA–2015–3597 using any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically.

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

• Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

• Fax: Fax comments to Docket Operations at 202–493–2251.

Privacy: In accordance with 5 U.S.C. 553(c), DOT solicits comments from the public to better inform its rulemaking process. DOT posts these comments, without edit, including any personal information the commenter provides, to www.regulations.gov, as described in the system of records notice (DOT/ALL– 14 FDMS), which can be reviewed at www.dot.gov/privacy.

Docket: Background documents or comments received may be read at http://www.regulations.gov at any time. Follow the online instructions for accessing the docket or go to the Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

**FOR FURTHER INFORMATION CONTACT :**  For technical questions concerning this action, contact Aleksandra Damsz, Financial Analyst, Office of Financial Analysis, AFA–400, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone (202) 267–8055; email aleksandra.damsz@faa.gov.