9634 Federal Register / Vol. 78, No. 28 / Monday, February 11, 2013 / Proposed Rules 

edited to remove any identifying or 

contact information. Public comments 

may also be viewed electronically or in 

paper in Room MP–500 of the Board’s 

Martin Building (20th and C Streets, 

NW.) between 9 a.m. and 5 p.m. on 

weekdays. 

SUPPLEMENTARY INFORMATION: The Board 

published a document in the Federal 

Register of November 23, 2012, (77 FR 

70124) requesting public comment on a 

policy statement on the approach to 

scenario design for stress testing that 

would be used in connection with the 

supervisory and company-run stress 

tests conducted under the Board’s 

regulations issued pursuant to the 

Dodd-Frank Wall Street Reform and 

Consumer Protection Act and the 

Board’s capital plan rule. The address to 

submit public comments was 

inadvertently omitted from that notice. 

This document corrects that omission. 

By order of the Board of Governors of the 

Federal Reserve System. 

Dated: February 7, 2013. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2013–03162 Filed 2–7–13; 4:15 pm] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0119; Directorate 

Identifier 2011–SW–034–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

AS350 and AS355 helicopters, to 

require inspecting for a crack in the 

control lever attachment yokes, and if 

needed, replacing the tail rotor gearbox 

(TGB). This proposed AD is prompted 

by improper casting of TGB casing 

assemblies, which may lead to cracking. 

A crack in the control lever attachment 

yokes could cause a loss of tail rotor 

pitch control, and consequently, loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by April 12, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone 817–222–5328; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2011– 

0104, dated May 27, 2011, to correct an 

unsafe condition for the Eurocopter 

Model AS 350 and AS 355 helicopters. 

EASA advises that cracks were found on 

some TGB casing assemblies when a 

dye-penetrant inspection was performed 

after the machining of the control lever 

attachment yokes. The inspection 

followed the repair of the manufacturing 

mold. EASA reports that cracks in the 

TGB casing assemblies, if not detected 

and corrected, could lead to a crack on 

the control lever attachment yokes, 

which could cause the loss of tail rotor 

pitch control and subsequent loss of 

control of the helicopter. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to the applicable 

bilateral agreement with France, EASA, 

its technical representative has notified 

us of the unsafe condition described in 

its AD. We are proposing this AD 

because we evaluated all known 

relevant information and determined 

that an unsafe condition is likely to 

exist or develop on other products of 

these same type designs. 

Related Service Information 

Eurocopter issued Alert Service 

Bulletin (ASB) No. AS350–65.00.46 for 

Model AS350 helicopters and ASB 

AS355–65.00.22 for AS355 helicopters. 

Both ASBs are Revision 0 and dated 

May 18, 2011. The ASBs call for nondestructive inspections, such as a dyepenetrant inspection, to check for cracks 

in the attachment yokes of the TGB 

casing assemblies. If there is a crack, the 

ASBs call for replacing the TGB with an 

airworthy TGB and returning the 

replaced TGB to Eurocopter. 


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Federal Register / Vol. 78, No. 28 / Monday, February 11, 2013 / Proposed Rules 9635 

Proposed AD Requirements 

This proposed AD would require, 

within 100 hours time in service (TIS), 

dye-penetrant inspecting for a crack in 

the control lever attachment yokes of 

the TGB casing assembly. If a crack 

exists, before further flight, this 

proposed AD would require replacing 

the TGB with an airworthy TGB. 

Differences Between This Proposed AD 

and the EASA AD 

We propose that the inspection for a 

crack in the attachment yokes of the 

TGB casing assemblies be performed 

within 100 hours TIS. EASA requires 

that the inspection be conducted within 

26 months or 660 flight hours if the TGB 

casing assemblies have less than 550 

flight hours and within 110 flight hours 

or 13 months if the TGB casing 

assemblies have 550 or more flight 

hours. We do not include the Model 

AS350BB helicopter because it is not 

type certificated in the United States, 

but we do include models AS350C and 

AS350D1. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 693 helicopters of U.S. 

Registry and that labor costs would 

average $85 per work-hour. We estimate 

that it would take two hours to inspect 

TGB casing assemblies for a cost of $170 

per helicopter, and $117,810 for the U.S. 

fleet. No parts would be needed. 

Replacing the TGB would require five 

work hours for a labor cost of $425. 

Parts would cost $37,825 for a total cost 

of $38,250 per helicopter. 

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, 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): 

Eurocopter France Helicopters (Eurocopter): 

Docket No. FAA–2013–0119; Directorate 

Identifier 2011–SW–034–AD. 

(a) Applicability 

This AD applies to Eurocopter AS350C, D, 

D1, B, BA, B1, B2, and B3; and AS355E, F, 

F1, F2, N, and NP helicopters, with a tailrotor 

gearbox (TGB) casing assembly, part number 

(P/N) 350A33–1090–02 and serial number (S/ 

N) MA47577, MA47585, MA47587 through 

MA47593, MA47597 through MA47600, 

MA47602, MA47604, MA47606, MA47610, 

MA47613, MA47615, MA47617, MA47619 

through MA47624, MA47626, MA47628, or 

MA47631 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the control lever attachment yoke of 

the TGB casing assembly, which could result 

in loss of tail rotor pitch control and loss of 

helicopter control. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

Within 100 hours time in service: 

(1) Remove the control lever, as depicted 

in Figure 1, item (b), of Eurocopter Alert 

Service Bulletin No. AS350–65.00.46 or No. 

AS355–65.00.22, both Revision 0 and both 

dated May 18, 2011, as applicable for your 

model helicopter (ASBs). 

(2) Strip the paint from the TGB control 

lever attachment yokes, as depicted in Figure 

2, item (z), of the ASBs. 

(3) Perform a Fluorescent Penetrant 

Inspection (Aerospace Material Specification 

2647 or equivalent) on the TGB control lever 

attachment yokes for a crack. 

(4) If a crack exists, before further flight, 

replace the TGB with an airworthy TGB. 

(5) If there is no crack, clean the inspected 

area and apply chemical conversion coating 

(Alodine 1200 or equivalent), Epoxy primer, 

and top coat paint. 

(e) Alternative Methods of Compliance 

(AMOC) 

(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– 

5328; 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. 

(f) Additional Information 

(1) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

http://www.eurocopter.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0104, dated May 27, 2011. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 


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9636 Federal Register / Vol. 78, No. 28 / Monday, February 11, 2013 / Proposed Rules 

Issued in Fort Worth, Texas, on February 

1, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02989 Filed 2–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1001; Directorate 

Identifier 2012–NM–020–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

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 Cessna Aircraft Company 

Model 500, 501, 550, 551, S550, 560, 

560XL, and 650 airplanes. That NPRM 

proposed to require an inspection to 

determine if certain air conditioning (A/ 

C) compressor motors are installed and 

to determine the accumulated hours on 

certain A/C drive motor assemblies; 

repetitive replacement of the brushes in 

the drive motor assembly, or as an 

option to the brush replacement, 

deactivation of the A/C system and 

placard installation; and return of 

replaced brushes to Cessna. That NPRM 

was prompted by multiple reports of 

smoke and/or fire in the tailcone caused 

by sparking due to excessive wear of the 

brushes in the A/C motor. This action 

revises that NPRM by revising the 

optional A/C system deactivation 

procedure. We are proposing this 

supplemental NPRM to prevent the 

brushes in the A/C motor from wearing 

down beyond their limits, which could 

result in the rivet in the brush 

contacting the commutator causing 

sparks and consequent fire and/or 

smoke in the tailcone with no means to 

detect or extinguish the fire and/or 

smoke. Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this supplemental NPRM by March 28, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: 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 Cessna 

Aircraft Co., P.O. Box 7706, Wichita, KS 

67277; telephone 316–517–6215; fax 

316–517–5802; email 

citationpubs@cessna.textron.com; 

Internet https:// 

www.cessnasupport.com/newlogin.html. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christine Abraham, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; phone: 

316–946–4165; fax: 316–946–4107; 

email: wichita-cos@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–2012–1001; Directorate Identifier 

2012–NM–020–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 to include an AD that would 

apply to the products listed above. That 

NPRM published in the Federal 

Register on September 26, 2012 (77 FR 

59146). That NPRM proposed to require 

an inspection to determine the 

accumulated hours on certain A/C drive 

motor assemblies; repetitive 

replacement of the brushes in the drive 

motor assembly, or as an option to the 

brush replacement, deactivation of the 

air conditioner; and return of replaced 

brushes to Cessna. 

Actions Since Previous NPRM (77 FR 

59146, September 26, 2012) Was Issued 

Since we issued the previous NPRM 

(77 FR 59146, September 26, 2012), 

Cessna has revised the A/C system 

deactivation procedure. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (77 FR 

59146, September 26, 2012). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Change A/C System 

Deactivation Procedure 

Cessna requested that we change the 

A/C system deactivation procedure 

specified in paragraph (j)(1) of the 

previous NPRM (77 FR 59146, 

September 26, 2012), because simply 

pulling the circuit breaker does not 

disable the A/C compressor motor for 

Model 560XL airplanes, and the circuit 

breaker labeling differs depending on 

the airplane model. Cessna stated that 

the vapor cycle A/C circuit breaker 

labeled ‘‘AIR COND’’ for Model 500, 

501, 550, 551, S550, and 560 airplanes 

should be pulled, and the vapor cycle 

A/C circuit breaker labeled ‘‘FWD EVAP 

FAN’’ for Model 650 airplanes should 

be pulled. Cessna also stated that, for 

Model 560XL airplanes, deactivation of 

the A/C system requires removing a 


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