44422 Federal Register / Vol. 78, No. 142 / Wednesday, July 24, 2013 / Rules and Regulations 

If the level of activity in the 

report was: And the report was filed late, the civil money penalty is: Or the report was not filed, the civil money penalty is: 

$250,000–349,999.99 .......... [$2475 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$10,900 × [1 + (.25 × Number of previous violations)]. 

$350,000–449,999.99 .......... [$3300 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$11,000 × [1 + (.25 × Number of previous violations)]. 

$450,000–549,999.99 .......... [$4125 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$12,100 × [1 + (.25 × Number of previous violations)]. 

$550,000–649,999.99 .......... [$4950 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$13,200 × [1 + (.25 × Number of previous violations)]. 

$650,000–749,999.99 .......... [$5775 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$14,300 × [1 + (.25 × Number of previous violations)]. 

$750,000–849,999.99 .......... [$6600 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$15,400 × [1 + (.25 × Number of previous violations)]. 

$850,000–949,999.99 .......... [$7425 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$16,500 × [1 + (.25 × Number of previous violations)]. 

$950,000 or over .................. [$9250 + ($200 × Number of days late)] × [1 + (.25 × 

Number of previous violations)].

$17,600 × [1 + (.25 × Number of previous violations)]. 

aThe civil money penalty for a respondent who does not have any previous violations will not exceed the level of activity in the report. 

* * * * * 

On behalf of the Commission. 

Dated: July 18, 2013. 

Ellen L. Weintraub, 

Chair, Federal Election Commission. 

[FR Doc. 2013–17703 Filed 7–23–13; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0638; Directorate 

Identifier 2013–SW–026–AD; Amendment 

39–17519; AD 2013–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350C, 

AS350D, and AS350D1 helicopters with 

a single hydraulic system and a certain 

hydraulic pump drive installed. This 

AD requires inspecting the hydraulic 

pump drive pulley bearing (pulley 

bearing) for leaks, rust, overheating, and 

condition. This AD is prompted by six 

reports of hydraulic pump drive belt 

failure caused by seizure of the pulley 

bearing. These actions are intended to 

prevent hydraulic pump drive belt 

failure, loss of hydraulic servo 

assistance, and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective 

August 8, 2013. 

We must receive comments on this 

AD by September 23, 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 AD, the foreign 

authority’s 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 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: 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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2013–0044–E, dated February 27, 


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Federal Register / Vol. 78, No. 142 / Wednesday, July 24, 2013 / Rules and Regulations 44423 

2013, to correct an unsafe condition for 

Eurocopter Model AS350B, AS350BA, 

AS350BB, AS350B1, AS350B2, 

AS350B3, and AS350D helicopters. 

EASA advises that six events were 

reported of hydraulic pump drive belt 

failure caused by seizure of the pulley 

bearing, and that a preliminary 

investigation concluded the installation 

of a new hydraulic pump drive 

(installed in accordance with 

Eurocopter modification 079566) may 

have caused excessive degradation. 

EASA further states that this condition, 

for helicopters with a single hydraulic 

system, can lead to loss of hydraulic 

servo assistance and an increase in pilot 

work load that requires landing as soon 

as possible. For these reasons, the EASA 

AD requires repetitive inspections of the 

hydraulic pump drive belt and pulley 

bearing and if required, replacing the 

hydraulic pump drive assembly. 

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 the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter issued AS350 Emergency 

Alert Service Bulletin No. 05.00.72, 

Revision 1, dated June 11, 2013 (EASB 

05.00.72), for Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, 

ASAS350D, and for non-FAA typecertificated Models AS350L1 and 

AS350BB helicopters. EASB 05.00.72 

describes procedures for inspecting the 

pulley bearing for leaking grease, 

condition of the lip seals, rust on the lip 

seals, evidence of overheating revealed 

by brown discoloring of the bearing, and 

for the condition of the sealing flanges. 

EASB 05.00.72 also describes 

procedures for rotating the bearing 

manually to determine if there are any 

friction points, brinelling, or noises 

from the bearing. EASB 05.00.72 

requires these inspections within 10 

hours time-in-service (TIS) for installed 

bearings with 165 or more hours TIS 

since installation. For bearings with less 

than 165 hours TIS since installation, 

EASB 05.00.72 requires inspecting the 

bearing upon reaching 165 hours TIS. 

AD Requirements 

This AD requires, for hydraulic pump 

drives with 165 or more hours TIS since 

installation, within 10 hours TIS and 

thereafter at intervals not exceeding 25 

hours TIS, decoupling the pulley and 

inspecting the pulley bearing for leaking 

grease, a crack or tear in the lip seals, 

a run of rust on the lip seals, indication 

of overheating shown by brown coloring 

on the inner ring of the bearing, any 

distortion, impact, wear, a tear, a crack, 

or loss of grease on the sealing flanges, 

or for a friction point, brinelling, or 

noise from the bearing. If any of these 

conditions exist, this AD requires 

replacing the hydraulic pump drive 

assembly before further flight. If the 

hydraulic pump drive assembly is 

replaced, the repetitive inspection 

requirements of this AD still apply. 

Interim Action 

We consider this AD to be an interim 

action. Eurocopter is still investigating 

the cause of this condition. If a final 

action is later identified, we might 

consider additional rulemaking. 

Costs of Compliance 

We estimate that this AD will affect 

36 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. 

At an average labor rate of $85 per 

hour, inspecting the bearing pulley 

would require about 1.5 work-hours, for 

a cost per helicopter of $128, and a total 

cost to U.S. operators of $4,608, per 

inspection cycle. 

If required, replacing the hydraulic 

pump drive assembly would require 

about 1.5 work-hours, and required 

parts would cost about $8,543, for a 

total cost per helicopter of $8,671. 

According to Eurocopter’s service 

information, some of the costs of this 

AD may be covered under warranty, 

thereby reducing the cost impact on 

affected individuals. We do not control 

warranty coverage by Eurocopter. 

Accordingly, we have included all costs 

in our cost estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the required corrective 

actions must be accomplished within 10 

hours TIS, a very short time period 

based on the average flight-hour 

utilization rate of these helicopters in 

the helicopter emergency medical 

service and air tour industries. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

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 AD and placed it in the AD docket. 


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44424 Federal Register / Vol. 78, No. 142 / Wednesday, July 24, 2013 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2013–15–03 Eurocopter France 

(Eurocopter): Amendment 39–17519; 

Docket No. FAA–2013–0638; Directorate 

Identifier 2013–SW–026–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

AS350B, AS350BA, AS350B1, AS350B2, 

AS350B3, AS350C, AS350D and AS350D1 

helicopters with a single hydraulic system 

and with a hydraulic pump drive installed in 

accordance with modification 079566 that 

has 165 or more hours time-in-service (TIS) 

since installation, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

seizure of the hydraulic pump drive pulley 

bearing. This condition could result in 

hydraulic pump drive belt failure, loss of 

hydraulic servo assistance, and subsequent 

loss of control of the helicopter. 

(c) Comments Due Date 

We must receive comments on this AD by 

September 23, 2013. 

(d) Effective Date 

This AD becomes effective August 8, 2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time. 

(f) Required Actions 

Within 10 hours TIS, and thereafter at 

intervals not exceeding 25 hours TIS: 

(1) Uncouple the pulley from the hydraulic 

pump. 

(2) Using a mirror and a light, inspect the 

hydraulic pump drive pulley bearing (pulley 

bearing) for leaking grease from each lip seal 

of the four greasing orifices (lip seal) due to 

wear, a crack or tear in a lip seal, a run of 

rust on a lip seal, indication of overheating 

shown by brown coloring on the inner ring 

of the bearing, and for any distortion, impact, 

wear, a tear, a crack, or loss of grease on each 

sealing flange. 

(3) Manually rotate the pulley bearing 

through several full turns and inspect for a 

friction point, brinelling, or a noise from the 

bearing. 

(4) If there is any leaking grease from a lip 

seal, a crack or tear in a lip seal, a run of rust 

on a lip seal, indication of overheating shown 

by brown coloring on the inner ring of the 

bearing, or distortion, impact, wear, a tear, a 

crack, or loss of grease on a sealing flange, 

or a friction point, brinelling, or noise from 

the bearing, before further flight, replace the 

hydraulic pump drive assembly. 

(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, 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. 

(h) Additional Information 

(1) Eurocopter AS350 Emergency Alert 

Service Bulletin No. 05.00.72, Revision 1, 

dated June 11, 2013, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. 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 (EASA) 

Emergency AD No. 2013–0044–E, dated 

February 27, 2013. 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: 2913: Hydraulic Pump, Main. 

Issued in Fort Worth, Texas, on July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–17622 Filed 7–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 357 

[Docket No. RM12–18–000; Order No. 783] 

Revisions to Page 700 of FERC Form 

No. 6 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Final rule. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) is 

modifying Page 700 of FERC Form No. 

6 (Form 6) to facilitate the calculation of 

an oil pipeline’s actual return on equity 

for preliminary screening purposes. The 

Commission will expand the 

information provided regarding Rate 

Base (line 5), Rate of Return (line 6), 

Return on Rate Base (line 7), and 

Income Tax Allowance (line 8). 

DATES: Effective Date: This rule will 

become effective September 23, 2013. 

FOR FURTHER INFORMATION CONTACT: 

James Sarikas (Technical Information), 

Office of Energy Market Regulation, 

888 First Street NE., Washington, DC 

20426, (202) 502–6831, 

James.Sarikas@ferc.gov. 

Brian Holmes (Technical Information), 

Office of Enforcement, 888 First Street 

NE., Washington, DC 20426, (202) 

502–6008, Brian.Holmes@ferc.gov. 

Andrew Knudsen (Legal Information), 

Office of the General Counsel, 888 

First Street NE., Washington, DC 

20426, (202) 502–6527, 

Andrew.Knudsen@ferc.gov. 

SUPPLEMENTARY INFORMATION: 

144 FERC ¶ 61,049 

Final Rule 

Table of Contents 

Paragraph 

Nos. 

I. Introduction ........................................................................................................................................................................................... 1 

II. Background ........................................................................................................................................................................................... 2 

III. NOPR Comments ................................................................................................................................................................................ 6 

IV. Discussion ........................................................................................................................................................................................... 7 

A. Rate Base ....................................................................................................................................................................................... 9 


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