41466 Federal Register / Vol. 79, No. 136 / Wednesday, July 16, 2014 / Proposed Rules 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@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 the 

European Aviation Safety Agency (EASA) AD 

No. 2013–0177, dated August 8, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0465. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2910, Hydraulic System, Main. 

Issued in Fort Worth, Texas, on July 8, 

2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16681 Filed 7–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0464; Directorate 

Identifier 2014–SW–002–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2013–18– 

01 for Eurocopter France Model EC 

155B, EC155B1, SA–365N, SA–365N1, 

AS–365N2, AS–365–N3, and SA–366G1 

helicopters. AD 2013–18–01 currently 

requires inspecting the collective pitch 

lever for correct locking and unlocking 

conditions. As published, AD 2013–18– 

01 contains certain errors. This 

proposed AD would retain the 

requirements of AD 2013–18–01, correct 

these errors, and update the type 

certificate holder’s name. The proposed 

actions are intended to detect an 

incorrectly adjusted collective pitch 

lever, which could result in loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 15, 

2014. 

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 

European Aviation Safety Agency 

(EASA) 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 Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the 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: Matt 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@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 

On August 21, 2013, we issued AD 

2013–18–01, amendment 39–17574 (78 

FR 56599, September 13, 2013) for 

Eurocopter France Model EC 155B, 

EC155B1, SA–365N, SA–365N1, AS– 

365N2, AS 365 N3, and SA–366G1 

helicopters, except helicopters with 

modification (MOD) 0767B5 installed. 

AD 2013–18–01 requires inspecting the 

collective pitch lever for correct 

unlocking with a spring scale, and if 

required, adjusting the collective pitch 

lever restraining tab and, for certain 

models, adjusting the collective link 

rods. AD 2013–18–01 also requires 

inspecting the collective pitch lever for 

the risk of inadvertent locking by 

measuring the clearance between the 

locking pin of the collective pitch lever 

and the L-section of the restraining tab, 

and if required, modifying the tab with 

a slight bend to the tab. 

AD 2013–18–01 was prompted by AD 

No. 2011–0154, dated August 22, 2011, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD 

2011–0154 to correct an unsafe 

condition for Eurocopter Model EC 

155B, EC155B1, SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters. EASA advises that two 

occurrences have been reported of 

inadvertent locking and unlocking of 

the collective pitch lever. One 

inadvertent collective pitch lever 

locking occurred when moving the 

collective pitch lever to the low-pitch 

position, and one inadvertent collective 

pitch lever unlocking occurred during 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 136 / Wednesday, July 16, 2014 / Proposed Rules 41467 

engine start. To address this unsafe 

condition, Eurocopter issued AS 365 

Alert Telex No. 67.00.10, SA 366 Alert 

Telex No. 67.05, and EC 155 Alert Telex 

No. 67A007, which describe procedures 

to inspect the collective pitch lever for 

correct locking and unlocking 

conditions. This inspection was 

mandated by Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) France AD No. 

F–2005–127, dated July 20, 2005. DGAC 

subsequently revised its AD, No. F– 

2005–127 R1, dated February 1, 2006 

(DGAC AD F–2005–127 R1), after 

Eurocopter issued Alert Service 

Bulletins containing the same 

inspection procedures and bearing the 

same numbers as the Alert Telexes. 

Since the issuance of DGAC AD F– 

2005–127 R1 Eurocopter developed an 

assembly comprised of a blade, a hinge, 

and a return spring to replace the 

flexible collective lever locking blade as 

terminating action for the inspection 

required by the AD. EASA then issued 

AD No. 2011–0154, which superseded 

DGAC AD F–2005–127 R1, retaining the 

inspection procedures for the collective 

pitch lever and removing from the 

applicability helicopters with the 

hinged, spring-loaded collective lever 

locking blade installed, designated as 

MOD 0767B65. 

As published, the AD number after 

the amendatory language section of AD 

2013–18–01 is incorrect. The AD 

number was published as ‘‘2013–18– 

11.’’ The MOD number in paragraph (a), 

Applicability, of the AD is incorrect. 

The correct MOD number is 0767B65. 

Also, since we issued AD 2013–18–01, 

the type certificate holder’s name for the 

affected models has changed from 

Eurocopter France to Airbus 

Helicopters. No other part of the 

regulatory information would be 

changed. 

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 our 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 the same 

type design. 

Related Service Information 

We reviewed Eurocopter (now Airbus 

Helicopters) Alert Service Bulletin 

(ASB) No. 67.00.10 for Model AS365 

helicopters, ASB No. 67.05 for Model 

SA366 helicopters, and ASB No. 

67A007 for Model EC155 helicopters. 

All three ASBs are Revision 1 and are 

dated February 25, 2009. These ASBs 

describe procedures for inspecting and 

adjusting the collective pitch lever for 

correct locking and unlocking 

conditions. 

Eurocopter has also issued ASB No. 

67.00.12, Revision 0, dated February 25, 

2009, for Model AS365 helicopters; ASB 

No. 67.07, Revision 0, dated February 

25, 2009, for Model AS366 helicopters; 

and ASB No. 67–009, Revision 1, dated 

July 19, 2010, for Model EC 155 

helicopters. These ASBs contain the 

procedures for MOD 0767B65. 

Proposed AD Requirements 

This proposed AD would retain all of 

the inspection and adjustment 

requirements of AD 2013–18–01. It 

would also would correct the AD 

number after the amendatory language, 

correct the MOD number in paragraph 

(a), and reflect the current type 

certificate holder’s name and contact 

information. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 32 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this proposed AD. 

Inspecting and adjusting the collective 

pitch lever would require about 1 work 

hour at an average labor rate of $85 per 

hour, for a total cost per helicopter of 

$85 and a cost to U.S. operators of 

$2,720. 

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. Amend § 39.13 by removing 

Airworthiness Directive (AD) 2013–18– 

01, Amendment 39–17574 (78 FR 

56599, September 13, 2013), and adding 

the following new AD: 

Airbus Helicopters (Previously Eurocopter 

France): Docket No. FAA–2014–0464; 

Directorate Identifier 2014–SW–002–AD. 

(a) Applicability 

This AD applies to Model EC 155B, 

EC155B1, SA–365N, SA–365N1, AS–365N2, 

AS 365 N3, and SA–366G1 helicopters, 

except helicopters with modification (MOD) 

0767B65 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

inadvertent locking and unlocking of the 

collective pitch lever, which could result in 

subsequent loss of control of the helicopter. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
41468 Federal Register / Vol. 79, No. 136 / Wednesday, July 16, 2014 / Proposed Rules 

(c) Affected AD 

This AD supersedes AD 2013–18–01, 

Amendment 39–17574 (78 FR 56599, 

September 13, 2013). 

(d) Comments Due Date 

We must receive comments by September 

15, 2014. 

(e) 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. 

(f) Required Actions 

Within 50 hours time-in-service: 

(1) For Model EC155B and EC155B1 

helicopters: 

(i) Lock the collective pitch lever, and 

using a spring scale, measure the load (G) 

required to unlock the pilot’s collective pitch 

lever as depicted in Figure 1, Detail B of 

Eurocopter Alert Service Bulletin (ASB) No. 

67A007, Revision 1, dated February 25, 2009 

(ASB 67A007). 

(ii) If the collective pitch lever unlocks at 

a load less than 11 deca Newtons (daN) (24.7 

lbs) or greater than 14 daN (31.5 lbs), before 

further flight, adjust the collective pitch lever 

restraining tab (F) using the oblong holes. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Measure the clearance (J1) between the 

locking pin of the collective pitch lever (C) 

and the 

L-section of the restraining tab (F) as 

depicted in Figure 1, Detail A of ASB 

67A007. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 

millimeters (mm), before further flight, 

remove the restraining tab, clamp the 

restraining tab (F) in a vice with soft jaws, 

and gradually apply a load (H) to ensure a 

clearance of 3 mm or more, as depicted in 

Figure 1, Detail K of ASB 67A007. 

(2) For Model SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.00.10, Revision 1, dated February 

25, 2009 (ASB 67.00.10). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.00.10. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the 

L-section of the restraining tab (F) as 

depicted in Figure 1, Detail A of ASB 

67.00.10. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 

67.00.10. 

(3) For Model SA–366G1 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.05, Revision 1, dated February 

25, 2009 (ASB 67.05). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.05. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the Lsection of the restraining tab (F) as depicted 

in Figure 1, Detail A, of ASB 67.05. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 67.05. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@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. 

(h) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 67.00.12, Revision 0, dated February 25, 

2009; ASB No. 67.07, Revision 0, dated 

February 25, 2009; and ASB No. 67–009, 

Revision 1, dated July 19, 2010, which are 

not incorporated by reference, contain 

additional information about this AD. For 

service information identified in this AD, 

contact Airbus Helicopters, Inc., 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http://

www.airbushelicopters.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 (EASA) AD 

No. 2011–0154, dated August 22, 2011. You 

may view the EASA AD in the AD Docket on 

the internet at http://www.regulations.gov. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710: Main Rotor Control. 

Issued in Fort Worth, Texas, on July 8, 

2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16682 Filed 7–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

United States Mint 

31 CFR Part 100 

Redemption Rates and Procedures 

AGENCY: United States Mint, Treasury. 

ACTION: Notice of proposed rulemaking 

with request for comment. 

SUMMARY: The United States Mint 

proposes to amend Treasury regulations 

relating to the exchange of uncurrent, 

bent, partial, fused, and mixed coins. 

The proposed amendments aim to 

update redemption rates and 

procedures, as well as to resolve an 

apparent contradiction in the current 

regulation. 

DATES: Comments on the proposed rule 

must be received by September 15, 

2014. 

ADDRESSES: The United States Mint 

invites comments on all aspects of this 

proposed rule. In accordance with the 

eRulemaking Initiative, the Department 

of the Treasury publishes rulemaking 

information on www.regulations.gov. 

Regulations.gov offers the public the 

ability to comment on, search, and view 

publicly available rulemaking materials, 

including comments received on rules. 

Comments on this rule must be 

submitted using only the following 

methods: 

• Federal eRulemaking Portal: 

www.regulations.gov. Follow the 

instructions on the Web site for 

submitting comments. 

• Mail: United States Mint; Office of 

Chief Counsel; 801 9th Street NW.; 

Washington, DC 20220. 

• Hand Delivery/Courier: Same as 

mail address. 

FOR FURTHER INFORMATION CONTACT: 

Daniel P. Shaver, Chief Counsel, Office 

of Chief Counsel, United States Mint, at 


tkelley on DSK3SPTVN1PROD with PROPOSALS