### 69597 Federal Register / Vol. 78, No. 224 / Wednesday, November 20, 2013 / Proposed Rules

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 proposed 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, 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

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):
AgustaWestland S.p.A. (Type Certificate formerly held by Agusta S.p.A) (Agusta) Helicopters: Docket No. FAA–2013– 0943; Directorate Identifier 2013–SW– 001–AD. (a) Applicability

This AD applies to Agusta Model A109C, A109E, A109K2, and A119 helicopters with a tail rotor blade retaining bolt (bolt), part number 109–8131–09–1, installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a bolt. This condition could result in failure of a bolt, release of a tail rotor blade, and subsequent loss of control of the helicopter.

(c) Comments Due Date

We must receive comments by January 21,
2014. (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

For each bolt with less than 400 hours time-in-service (TIS), before exceeding 500 hours TIS on the bolt, and for each bolt with 400 or more hours TIS, before accumulating an additional 100 hours TIS or 2 months on the bolt, whichever occurs first:

(1) Visually inspect each bolt for a crack, damage, corrosion, a nick, or missing cadmium plating in the central part of the bolt.

(i) If there is a crack, corrosion, a nick, any other damage, or missing cadmium plating in the central part of the bolt, before further flight, replace the bolt with an airworthy bolt.

(ii) If there is not a crack as a result of the initial visual inspection as required by paragraph (e)(1) of this AD, liquid-penetrant inspect the bolt in accordance with Annex A of Agusta Bollettino Tecnico No. 109–135 for Model A109C helicopters, No. 109EP–125 for Model A109E helicopters, No. 109K–55 for Model A109K2 helicopters, or No. 119–052 for Model A119 helicopters, all dated December 19, 2012, as applicable to your model helicopter. If there is a crack, before further flight, replace the bolt with an airworthy bolt.

(2) Thereafter, for Agusta Model A109C helicopters, repeat the required actions of paragraph (e)(1) of this AD at intervals not to exceed 300 additional hours TIS or 6 months, whichever occurs first. For Agusta Model A109E, A109K2, and A119 helicopters, repeat the required actions of paragraph (e)(1) of this AD at intervals not to exceed 200 additional hours TIS or 6 months, whichever occurs first.

(3) Do not install a bolt that has accumulated more than 400 hours TIS on any helicopter unless it has passed the required actions of paragraph (e)(1) of this AD.
(f) 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, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222– 5110; 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.
(g) Additional Information

The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013–0009, dated January 11, 2013. You may view the EASA AD in the AD Docket on the Internet at http://www.regulations.gov.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor.

Issued in Fort Worth, Texas, on October 30,
2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–27634 Filed 11–19–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0967; Directorate Identifier 2013–CE–042–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Piaggio Aero Industries S.p.A 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 Piaggio Aero Industries S.p.A Model P–180 airplanes that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI)


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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 cases of un-commanded operation of switched off nose-wheel steering system caused by internal leakage of a steering select/bypass valve, which could lead to loss of directional control on ground during take-off or landing, possibly resulting in a runway excursion. 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 January 6, 2014.

**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 Piaggio Aero Industries S.p.A-Airworthiness Office,Via Luigi Cibrario, 4–16154 GenovaItaly; phone: +39 010 6481353; fax: +39 010 6481881; email: airworthiness@ piaggioaero.it; Internet: http:// www.piaggioaero.com/#/en/aftersales/ service-support. 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. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2013–0967; 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 :**  Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
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–2013–0967; Directorate Identifier 2013–CE–042–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

On December 30, 2009, we issued AD 2009–21–08 R1, Amendment 39–16169 (75 FR 904, January 7, 2010). That AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2009–21–08 R1, Amendment 39–16169 (75 FR 904, January 7, 2010), the manufacturer has developed a modification that will terminate the required repetitive functional tests required in AD 2009– 21–08 R1.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2013– 0242R1, dated October 9, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Cases of un-commanded operation of switched off nose-wheel steering system were reported. Internal leakage of a Steering Select/Bypass Valve, installed in the nose landing gear (NLG) Steering Manifold, was identified as a failure cause.

This condition, if not detected and corrected, could lead to loss of directional control on ground during take-off or landing, possibly resulting in a runway excursion.

To address this unsafe condition, EASA issued AD 2009–0129 to require repetitive functional checks of the Steering Manifold to verify internal leakage proofness and accomplishment of the functional check upon installation of a replacement Steering Manifold on an aeroplane. Since that AD was issued, PAI issued Service Bulletin (SB) 80–0249 at revision 3, providing improved testing procedures.

For the reasons described above, this AD retains the requirements of EASA AD 2009– 0129, which is superseded, but requires accomplishment of the functional checks in accordance with the improved procedures and additionally, before release to service of an aeroplane after installation of a replacement NLG. This AD also introduces an optional modification, which constitutes terminating action for the repetitive functional checks required by this AD.

This AD is revised to introduce a relieving compliance time for aeroplanes earlier inspected in accordance with EASA AD
2009–0129. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0967.

Relevant Service Information

PIAGGIO AERO INDUSTRIES S.p.A has issued Mandatory Service Bulletin N. 80–0249, Rev. 3, dated July 22, 2013; Recommended Service Bulletin N. 80– 0285, and Recommended Service Bulletin N. 80–0286, Rev. 1, both dated September 30, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 112 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic functional test 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 $19,040, or $170 per product.

In addition, we estimate the following cost to do the proposed optional modification to terminate the proposed required repetitive functional tests. For Model P–180 Avanti airplanes, it would take about 40 work-hours and require


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parts costing $2,000, for a cost of $5,400 per product. For Model P–180 Avanti IIairplanes, it would take about 40 workhours and require parts costing $4,000, for a cost of $7,400 per product. We have no way of determining the number of operators that may choose this optional action. 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 proposed 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 removing Amendment 39–16169 (75 FR 904, January 7, 2010), and adding the following new AD:
PIAGGIO AERO INDUSTRIES S.p.A: Docket No. FAA–2013–0967; Directorate Identifier 2013–CE–042–AD.
(a) Comments Due Date

We must receive comments by January 6,
2014.
(b) Affected ADs

This AD supersedes AD 2009–21–08 R1, Amendment 39–16169 (75 FR 904, January 7, 2010).
(c) Applicability

This AD applies to PIAGGIO AERO INDUSTRIES S.p.A Model P–180 airplanes, serial numbers 1004 through 1218, certificated in any category.
(d) Subject

Air Transport Association of America (ATA) Code 32: Landing Gear.

(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 MCAIdescribes the unsafe condition as cases of uncommanded operation of switched off nosewheel steering system caused by internal leakage of a steering select/bypass valve. We are issuing this AD to prevent loss of directional control on ground during take-off or landing, which could result in a runway excursion.
(f) Actions and Compliance

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

(1) At whichever of the compliance times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD that occurs first and repetitively thereafter at intervals not to exceed 165 hours TIS, do a functional test of the nose landing gear (NLG) steering manifold following Part A2 of the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N. 80–0249, Rev. 3, dated July 22, 2013 (includes CONFIRMATION SLIP).

(i) Within the next 165 hours time-inservice (TIS) after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first; or

(ii) Within the next 165 hours TIS after the last inspection done in compliance with AD 2009–21–08 R1, Amendment 39–16169 (75 FR 904, January 7, 2010).

(2) Within the next 220 hours TIS or the next 6 months after the effective date of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 660 TIS or 12 months, whichever occurs first, do a functional test of the nose landing gear (NLG) steering manifold following Part A1 of the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N. 80–0249, Rev. 3, dated July 22, 2013 (includes CONFIRMATION SLIP).

(3) If, during any functional test required in paragraphs (f)(1) and (f)(2) of this AD, any NLG steering actuator movement discrepancy is detected, before further flight, replace the NLG steering manifold with a serviceable part as specified in Part A1 and Part A2 of the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N. 80–0249, Rev. 3, dated July 22, 2013 (includes CONFIRMATION SLIP).

(4) As of the effective date of this AD, installation of a replacement NLG steering manifold or a replacement NLG is allowed, provided that, before release to service, the NLG steering manifold passes a functional test following Part A1 of the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N. 80–0249, Rev. 3, dated July 22, 2013.

(5) To terminate the repetitive functional tests required in paragraphs (f)(1) and (f)(2) of this AD, at any time after the initial functional test required in paragraphs (f)(1) and (f)(2) of this AD, you may modify the electrical configuration of the steering system following the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Recommended) N. 80–0285, dated September 20, 2013 (includes CONFIRMATION SLIP), or the ACCOMPLISHMENT INSTRUCTIONS in PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Recommended) N. 80–0286, Rev. 1, dated September 20, 2013, as applicable.
(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: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329– 4090; email: mike.kiesov@faa.gov.

(i) 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.

(ii) AMOCs approved for AD 2009–21–08 R1 (75 FR 904, January 7, 2010) are not approved for AMOCs for this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from


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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 European Aviation Safety Agency (EASA) AD No. 2013–0242R1, dated October 9, 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–2013–0967. For service information related to this AD,contact Piaggio Aero Industries S.p.AAirworthiness Office, Via Luigi Cibrario, 4– 16154 Genova-Italy; phone: +39 010 6481353; fax: +39 010 6481881; email: airworthiness@ piaggioaero.it; Internet: http:// www.piaggioaero.com/#/en/aftersales/ service-support. 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.

Issued in Kansas City, Missouri, on November 5, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–27837 Filed 11–19–13; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0964; Directorate Identifier 2013–CE–035–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Piaggio Aero Industries S.p.A 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 certain Piaggio Aero Industries S.p.A. Model P– 180 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 insufficient clearance between one of the horizontal stabilizer end ribs and the corresponding elevator horn. 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 January 6, 2014.

**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 Piaggio Aero Industries S.p.A—Airworthiness Office,Via Luigi Cibrario, 4–16154 GenovaItaly; phone: +39 010 6481353; fax: +39 010 6481881; email: airworthiness@ piaggioaero.it; Internet: http:// www.piaggioaero.com/#/en/aftersales/ service-support. 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; 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 :**  Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
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–2013–0964; Directorate Identifier 2013–CE–035–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. 2013– 0239, dated September 30, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Insufficient clearance between one of the horizontal stabilizer end rib and the corresponding elevator horn was found on an in-service aeroplane.

This condition, if not detected and corrected, could lead to interference between the elevator and horizontal stabilizer surfaces, resulting in restricted elevator control and consequent reduced control of the aeroplane.

To address this potential unsafe condition, Piaggio Aero Industries (PAI) issued Service