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

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 II 

airplanes, 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 MCAI 

describes 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 


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