52212 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Withdrawal 

Accordingly, we withdraw the NPRM, 

Docket No. FAA–2013–0627, Directorate 

Identifier 2012–NM–021–AD, which 

was published in the Federal Register 

on July 24, 2013 (78 FR 44469). 

Issued in Renton, Washington, on August 

20, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21247 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–2012–0002; Directorate 

Identifier 2011–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; Continental 

Motors, Inc. Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Airmotive Engineering Corp. 

(AEC) replacement parts manufacturer 

approval (PMA) cylinder assemblies 

marketed by Engine Components 

International Division (ECi). We 

subsequently issued an initial 

supplemental NPRM (SNPRM) that 

proposed to modify the schedule for 

removal of the affected cylinder 

assemblies, added that overhauled 

affected cylinder assemblies be removed 

within 80 hours, eliminated a reporting 

requirement, and removed a 

requirement for initial and repetitive 

inspections. This second SNPRM 

reopens the comment period to allow 

the public the chance to comment on 

additional information added to the 

docket of this proposed rule. We are 

proposing this SNPRM to prevent 

failure of the cylinder assemblies, which 

could lead to failure of the engine, inflight shutdown, and loss of control of 

the airplane. 

DATES: We must receive comments on 

this SNPRM by September 28, 2015. 

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: 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 Engine 

Components International Division, 

9503 Middlex Drive, San Antonio, TX 

78217; phone: 210–820–8101; Internet: 

http://www.eci.aero/pages/tech_

svcpubs.aspx. 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. 

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–2012– 

0002; 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: 

Jurgen E. Priester, Aerospace Engineer, 

Delegation Systems Certification Office, 

FAA, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

phone: 817–222–5190; fax: 817–222– 

5785; email: jurgen.e.priester@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–2012–0002; Directorate Identifier 

2011–NE–42–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 issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain AEC replacement PMA 

cylinder assemblies marketed by ECi. 

These assemblies are used on 

Continental Motors, Inc. (CMI) model 

520 and 550 reciprocating engines, and 

all other CMI engine models approved 

for the use of models 520 and 550 

cylinder assemblies such as the CMI 

model 470 when modified by STC. The 

NPRM published in the Federal 

Register on August 12, 2013 (78 FR 

48828). The NPRM proposed to require 

initial and repetitive inspections, 

immediate replacement of cracked 

cylinder assemblies, and replacement of 

cylinder assemblies at reduced times-inservice (TIS) since new. The NPRM also 

proposed to prohibit the installation of 

affected cylinder assemblies into any 

engine. 

We subsequently issued an SNPRM 

which published in the Federal Register 

on January 8, 2015 (80 FR 1008). The 

SNPRM proposed a modified schedule 

for removal of the affected cylinder 

assemblies, added that overhauled 

affected cylinder assemblies be removed 

within 80 hours, eliminated a reporting 

requirement, and removed the 

requirement for initial and repetitive 

inspections. 

Actions Since Previous SNPRM Was 

Issued 

Since we issued the SNPRM (80 FR 

1008, January 8, 2015), we received 

numerous additional comments on the 

proposed rule. After reviewing the 

comments, we decided to reopen the 

docket so that we could provide 

additional information to explain the 

rationale for this AD action. We also 

wanted to provide commenters with the 

opportunity to comment on this 

additional information. We added the 

following information to Docket No. 

FAA–2012–0002: (1) The risk analysis 

conducted by the FAA’s Chief Scientific 

and Technical Adviser, Aircraft Safety 

Analysis; (2) a risk analysis using the 

Small Airplane Risk Analysis methods; 

(3) a June 2011, presentation by 

Airmotive Engineering to the FAA 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules 52213 

concerning its ECi cylinder assemblies; 

(4) a list of ECi cylinder assembly failure 

reports consisting of only those reports 

where both cylinder serial number and 

Time in Service are included in the 

reports; (5) a list of additional failures 

of ECi cylinder assemblies reported by 

a maintenance organization; (6) copies 

of the slides discussed with the NTSB 

on June 9, 2015 during the meeting with 

the NTSB to understand its comments to 

2011–NE–42–AD, and (7) Airmotive 

Engineering Corporation Technical 

Report 1102–13, dated April 30, 2011. 

In addition, we met with National 

Transportation Safety Board (NTSB) 

representatives on June 9, 2015, to 

clarify the NTSB’s basis for its 

comments of FAA’s actions in this 

proposed rule. 

We are taking this opportunity to 

respond to a limited number of 

comments. Specifically, we found that 

numerous commenters cited differences 

between the FAA’s proposed action and 

the NTSB’s recommendations in NTSB 

Safety Recommendation A–12–7. We 

will respond to remaining comments to 

the initial SNPRM (80 FR 1008, January 

8, 2015) and to this second SNPRM 

when we issue the final rule. 

Comments to the Previous SNPRM 

Request To Provide Supporting 

Information 

Danbury Aerospace, Inc., and others 

in their comments to the SNPRM (80 FR 

1008, January 8, 2015), requested that 

we provide additional information that 

supports this AD action. 

We agree. We added our risk analyses 

and other technical information, such as 

the list of cylinder failures noted above 

and ECi Technical Report 1102–13 that 

supports this proposed rule, to Docket 

No. FAA–2012–0002 to help 

commenters and the general public 

understand the need for this proposed 

rule. 

Request To Withdraw the SNPRM 

Because ECi Cylinder Assemblies Are 

Not Unsafe 

Several operators, maintenance 

organizations, and private citizens asked 

that we withdraw the SNPRM (80 FR 

1008, January 8, 2015) because the 

affected ECi cylinder assemblies have an 

equivalent, or lower, failure rate than 

that of cylinder assemblies 

manufactured by the original equipment 

manufacturer (OEM). 

We disagree. We found that the failure 

rate for ECi cylinder assemblies is much 

higher than for OEM cylinder 

assemblies over the same period. 

Accident data confirms, that engines 

and airplanes may not always continue 

to operate safely with a separated 

cylinder and that separated cylinders 

have been the precipitating event in at 

least two fatal accidents. This accident 

data is included in the risk analyses that 

we uploaded to the docket (see NTSB 

Accident Identifiers NYC02FA178 and 

ERA11WA008, which are cited in these 

analyses). We did not withdraw this 

proposed rule. 

Request To Review Comparison of 

Failure Rate Between OEM and ECi 

Cylinder Assemblies 

The NTSB commented that the 

comparison between failure rates of 

OEM and ECi cylinder assemblies was 

not valid because the cylinder heads 

represented substantially different 

designs. 

We disagree that the comparison 

between OEM and ECi cylinder 

assemblies is not valid. The ECi PMA 

design was reverse engineered by ECi 

from earlier vintage OEM cylinders, and 

uses the same time between overhaul 

(TBO) as the OEM cylinders. Since these 

ECi cylinder assemblies are approved to 

the same TBO as the OEM cylinders, the 

ECi cylinders should have durability 

that is equivalent to the OEM cylinders. 

Our comparison of ECi cylinder 

assembly service history with the OEM 

cylinder assembly history showed that 

the rate of separation for the affected 

ECi cylinder assemblies is at least 32 

times greater than that of OEM cylinder 

assemblies over the same period. We 

uploaded this data for commenter 

review. It may be viewed in Docket No. 

FAA–2012–0002. We did not change 

this proposed AD. 

Request To Revise Applicability 

The NTSB commented that it has not 

investigated any cases involving engines 

with cylinder assemblies ranging from 

serial number (S/N) 1 through S/N 1043. 

The NTSB indicated that cylinder 

assemblies in this S/N range should not 

be affected by the AD. 

We disagree. Cylinder assemblies 

with S/N 1 through S/N 1043 have the 

same design as noted in this SNPRM, 

exhibit the same unsafe condition, and 

therefore must be included in the 

applicability. We did not change this 

proposed AD. 

The NTSB also commented that AD 

2004–08–10, which was issued on May 

5, 2004, requires replacement before 

further flight of ECi cylinder assemblies 

ranging from S/N 1044 through S/N 

7708 installed on CMI 520 and 550 

series engines. According to AD 2004– 

08–10, ECi identified a manufacturing 

discrepancy that occurred between 

September 2002 and May 2003 affecting 

cylinder assemblies S/N 1044 through 

S/N 7708, which resulted in an overhardened condition that would reduce 

the fatigue strength of the aluminum 

cylinder head. The NTSB commented, 

therefore, that cylinder assemblies S/N 

1044 through S/N 7708 should not be 

included in the proposed AD. 

We disagree. AD 2004–08–10 does not 

apply to all cylinder assemblies S/N 

1044 through S/N 7708; it applies only 

to cylinder assemblies having specific 

cast markings. Cylinder assemblies S/N 

1004 through S/N 7708 have the same 

design as noted in this SNPRM, exhibit 

the same unsafe condition, and 

therefore must be included in the 

applicability. We did not change this 

proposed AD. 

The NTSB also commented that, 

based on its review of the additional 

seal band interference fit data provided 

by ECi, action is only required for 165 

cylinder assemblies S/N 36210 through 

S/N 61176. 

We disagree. We have received 

reports of separations of cylinder 

assemblies S/N 36210 through S/N 

61176 that were not among the 165 

cylinders that ECi claimed may be at 

risk for separation due to insufficient 

head to barrel interference fit. We have 

uploaded information in Docket No. 

FAA–2012–0002 that identifies S/Ns of 

failed cylinder assemblies that were not 

among the 165 cylinder assemblies 

identified by ECi. We did not change 

this proposed AD. 

The NTSB commented that the 

applicability represented by the 

SNPRM—S/N 1 through S/N 61176— 

represents a much larger number of 

affected cylinder assemblies than is 

supported by its investigations. 

We disagree. ECi’s next increase in 

the design interference fit was 

incorporated beginning with S/N 61177. 

Consequently, all cylinder assemblies S/ 

N 1 through S/N 61176 are at risk for 

separation in the first thread due to 

insufficient interference fit. We, 

therefore, find that based on service 

failure data, identified in the docket as 

‘‘U.S. DOT/FAA—04 ECi 520–550 

Cylinder Separations,’’ and ECI’s 

implementation of design 

improvements, this proposed AD must 

apply to cylinder assemblies S/N 1 

through S/N 61176. We did not change 

this proposed AD. 

Request To Include Repetitive 

Inspection Requirement 

The NTSB commented that we should 

impose a repetitive inspection 

requirement for certain ECi cylinder 

assemblies and their removal once they 

reach the manufacturer’s recommended 

TBO. This repetitive inspection 

requirement was part of the NPRM (78 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
52214 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules 

FR 48828, August 12, 2013), but we 

removed it from the SNPRM (80 FR 

1008, January 8, 2015). 

The NTSB observed that the FAA had 

published Special Airworthiness 

Information Bulletin (SAIB) NE–07– 

09R1, dated March 21, 2007, and 

approved ECi Mandatory Service 

Bulletin 06–2, Revision 2, dated October 

26, 2006. Both of these documents 

emphasize the importance of 

conducting periodic inspections of ECi 

cylinder assemblies. 

We disagree. We have found, based on 

service experience since the publication 

of SAIB NE–07–09R1, that the 

inspection and tests are not reliable in 

detecting cracked cylinders and the cost 

associated with such ongoing tests 

outweighs the safety benefit. In 

addition, the crack propagation growth 

rate is unknown. As a result, we have 

received field reports of separated 

cylinders that occurred within the 

repetitive 50-hour compression test and 

leak check inspection intervals 

proposed by the NPRM. We did not 

change this proposed AD. 

The NTSB also noted that repetitive 

inspections are not perfect but are still 

effective in detecting cracks that have 

propagated through the cylinder wall. 

These inspections provide an added 

level of safety from the time of the 

issuance of the final rule AD until the 

required removal of the cylinder 

assembly. 

We disagree. We find that repetitive 

inspections until TBO are inconsistent 

with the serious hazard represented by 

cylinder assembly failures. See the 

‘‘U.S. DOT/FAA–01 Risk Analysis 

White Paper’’ for 2011–NE–42–AD that 

we uploaded to the AD docket on June 

23, 2015. Therefore, we are requiring 

removal of affected cylinder assemblies 

from service prior to TBO. We did not 

change this proposed AD. 

FAA’s Determination 

We are proposing this SNPRM to 

allow the public the opportunity to 

comment on additional information we 

added to the docket of this proposed 

rule. 

Proposed Requirements of this SNPRM 

As proposed in the first SNPRM 

published on January 8, 2015 (80 FR 

1008), this second SNPRM would 

require removal of the affected cylinder 

assemblies, including overhauled 

cylinder assemblies, according to a 

phased removal schedule. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 5,000 CMI models 

IO–520, TSIO–520, IO–550, and IOF– 

550 reciprocating engines and all other 

CMI engine models approved for the use 

of CMI models 520 and 550 cylinder 

assemblies (such as the CMI model 470 

when modified by STC), installed on 

airplanes of U.S. registry. The average 

labor rate is $85 per hour. We estimate 

that about 18 hours would be required 

to replace all six cylinder assemblies 

during overhaul maintenance. We 

estimate the pro-rated value of the cost 

of replacement of six cylinder 

assemblies to be about $4,202 per 

engine. Based on these figures, we 

estimate the total cost of this proposed 

AD to U.S. operators to change all ECi 

cylinder assemblies to be $28,660,000. 

Our cost estimate is exclusive of 

possible warranty coverage. 

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 

(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): 

Continental Motors, Inc. (formerly Teledyne 

Continental Motors, Inc., formerly 

Continental): Docket No. FAA–2012– 

0002; Directorate Identifier 2011–NE– 

42–AD. 

(a) Comments Due Date 

We must receive comments by September 

28, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Continental Motors, 

Inc. (CMI) model 520 and 550 reciprocating 

engines, and to all other CMI engine models 

approved for the use of model 520 and 550 

cylinder assemblies such as the CMI model 

470 when modified by supplemental type 

certificate (STC), with Airmotive Engineering 

Corp. replacement parts manufacturer 

approval (PMA) cylinder assemblies, 

marketed by Engine Components 

International Division (hereinafter referred to 

as ECi), part number (P/N) AEC631397, with 

ECi Class 71 or Class 76, serial number (S/ 

N) 1 through S/N 61176, installed. 

(d) Unsafe Condition 

This AD was prompted by multiple failure 

reports of cylinder head-to-barrel separations 

and cracked and leaking aluminum cylinder 

heads. We are issuing this AD to prevent 

failure of the cylinder assemblies, which 

could lead to failure of the engine, in-flight 

shutdown, and loss of control of the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Review the engine maintenance records 

to determine if any affected cylinder 

assemblies are installed. 

(2) If you cannot determine based on 

review of engine maintenance records if any 

affected cylinder assemblies are installed, 

comply with paragraph (e)(4) of this AD. 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules 52215 

(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: 


Lhorne on DSK5TPTVN1PROD with PROPOSALS