Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations 15599 

which, although recognizable, appears 

cumbersome. Honeywell suggested that, 

‘‘Rated limited use 21⁄2-minute OEI’’ 

could be a better definition that would 

still distinguish it from the existing 

unlimited use of the 30-second, 2- 

minute, and 21⁄2-minute OEI ratings. 

We do not agree. The applicant 

requested the new rating be named in 

closer relation with the 30-second and 

2-minute OEI ratings for consistency 

across existing engine models and to 

align the new rating with the 30-second 

and 2-minute-OEI ratings at the 

rotorcraft level. We agree with the 

applicant’s proposed name. We also do 

not agree with the commenter that the 

30-second and 2-minute OEI ratings are 

‘‘unlimited use.’’ These ratings are 

limited to a maximum use of 3 times per 

flight and require post-flight inspection, 

per 14 CFR 1.1, Definitions. 

Applicability 

These special conditions are 

applicable to the GE CT7–2E1 turboshaft 

engine model. If GE applies later for a 

change to the type certificate, to include 

another closely related model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to that model, as well. This 

is true, provided the certification basis 

is the same or contains later 

amendments that satisfy the 

certification basis discussed in the 

section titled, ‘‘Type Certification 

Basis.’’ 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting these 

special conditions. This action affects 

certain novel or unusual design features 

on the CT7–2E1 turboshaft engine 

model. It is not a rule of general 

applicability and applies only to GE, 

whom requested FAA approval for this 

engine feature. 

List of Subjects in 14 CFR Part 33 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, the FAA issues the 

following special conditions as part of 

the type certification basis for the GE 

CT7–2E1 turboshaft engine model. 

1. Part 1 Definitions 

Unless otherwise approved by the 

Administrator and documented in the 

appropriate manuals and certification 

documents, the following definition 

applies: ‘‘Rated Flat 30-second and 2- 

minute One Engine Inoperative (OEI) 

Power,’’ with respect to rotorcraft 

turbine engines, means: (1) A rating for 

which the shaft horsepower and 

associated operating limitations of the 

30-second OEI and 2-minute OEI ratings 

are equal, and (2) the shaft horsepower 

is that developed under static 

conditions at the altitude and 

temperature for the hot day, and within 

the operating limitations established 

under part 33. The rating is for 

continuation of one flight operation 

after the failure or shutdown of one 

engine in multiengine rotorcraft. The 

rating is for up to three periods of use 

no longer than 2.5 minutes each in any 

one flight, and followed by mandatory 

inspection and prescribed maintenance 

action. 

2. Part 33 Requirements 

(a) In addition to the airworthiness 

standards in the type certification basis 

applicable to the engine and the 30- 

second and 2-minute OEI ratings, the 

special conditions in this section apply. 

(b) Section 33.7 Engine ratings and 

operating limitations. Flat 30-second 

and 2-minute OEI rating and operating 

limitations are established by power, 

torque, rotational speed, gas 

temperature, and time duration. 

(c) Section 33.27 Turbine, 

compressor, fan, and turbosupercharger 

rotor overspeed. In addition to the 

requirements of § 33.27(b): 

(1) The turbine and compressor rotors 

must have sufficient strength to 

withstand the test conditions specified 

in paragraph (2) below. 

(2) The applicant must determine, by 

analysis or other acceptable means, the 

most critically stressed rotor component 

of each turbine and compressor, 

including integral drum rotors and 

centrifugal compressors. These 

components must be tested for the 

conditions in paragraphs (i) or (ii) 

below. The test selection from the 

following paragraphs (i) or (ii) below is 

determined by the speed defined in 

paragraph (i)(B) or (ii)(B), whichever is 

higher. 

(i) Test for a period of 5 minutes: 

(A) At its maximum operating 

temperature, except as provided in 

§ 33.27(c)(2)(iv); and 

(B) At the highest speed determined, 

in accordance with § 33.27(c)(2)(i) 

through (iv). 

(C) This test may be performed using 

a separate test vehicle as desired. 

(ii) Test for a period of 5 minutes: 

(A) At its maximum operating 

temperature, except as provided in 

paragraph (ii)(C) below; and 

(B) At 100 percent of the highest 

speed that would result from failure of 

the most critical component of each 

turbine and compressor, or system, in a 

representative installation of the engine 

when operating at the flat 30-second 

and 2-minute OEI rating conditions; and 

(C) The test speed must take into 

account minimum material properties, 

maximum operating temperature, if not 

tested at that temperature, and the most 

adverse dimensional tolerances. 

(D) This test may be performed using 

a separate test vehicle as desired. 

Following the test, rotor growth and 

distress beyond dimensional limits for 

an overspeed condition are permitted 

provided the structural integrity of the 

rotor is maintained, as shown by a 

procedure acceptable to the FAA. 

(d) Section 33.67(d) Fuel system. 

Engines must incorporate a means, or a 

provision for a means, for automatic 

availability and automatic control of the 

flat 30-second and 2-minute OEI power 

for the duration of 2.5 minutes and 

within the declared operating 

limitations. 

(e) Section 33.87 Endurance test. The 

requirements applicable to 30-second 

and 2-minute OEI ratings, except for: 

(1) The test of § 33.87(a)(7) as 

applicable to the 21⁄2-minute OEI rating. 

(2) The tests in § 33.87(f)(2) and (3) 

must be run continuously for the 

duration of 2.5 minutes, and 

(3) The tests in § 33.87(f)(6) and (7) 

must be run continuously for the 

duration of 2.5 minutes. 

(f) Section 33.88 Engine 

overtemperature test. The requirements 

of § 33.88(c), except that the test time is 

5 minutes instead of 4 minutes. 

Issued in Burlington, Massachusetts on 

March 4, 2013. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–05676 Filed 3–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0689; Directorate 

Identifier 2009–SW–065–AD; Amendment 

39–17301; AD 2012–26–06] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft-Manufactured Model S–64F 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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15600 Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporationmanufactured Model S–64F helicopters, 

now under the Erickson Air-Crane 

Incorporated (Erickson) Model S–64F 

type certificate. This AD supersedes an 

existing AD which requires inspections, 

rework, and replacement, if necessary, 

of the main gearbox (MGB) second stage 

lower planetary plate (plate). Since we 

issued that AD, the manufacturer has 

conducted a configuration review and 

analysis, and a review of the service 

history of certain components. The 

actions of this AD are intended to 

establish life limits for certain 

components, remove various parts from 

service, and require consistency in the 

part numbers of certain four bladed tail 

rotor (T/R) assemblies to prevent fatigue 

cracking, failure from static overload, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective April 16, 

2013. 

ADDRESSES: For service information 

identified in this AD, contact Erickson 

Air-Crane Incorporated, ATTN: Chris 

Erickson/Compliance Officer, 3100 

Willow Springs Rd., P.O. Box 3247, 

Central Point, OR 97502, telephone 

(541) 664–5544, fax (541) 664–2312, 

email address 

cerickson@ericksonaircrane.com. You 

may review a copy of the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. 

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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Certification Office, Fort 

Worth, Texas 76137, telephone (817) 

222–5170, email 7-avs-asw-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 29, 2012, at 77 FR 38744, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Sikorsky Aircraft Corporationmanufactured Model S–64F helicopters, 

now under the Erickson Air-Crane 

Incorporated Model S–64F type 

certificate. That NPRM proposed to 

supersede existing AD 97–10–15 (62 FR 

28321, May 23, 1997), to require 

reducing or establishing the life limits 

for certain flight-critical components, 

removing other parts with service 

difficulties from service, and require 

that T/R blade assembly, P/N 65160– 

00001–048, be installed only as a set of 

four and not be installed with another 

part-numbered blade. The proposed 

requirements were intended to prevent 

a fatigue crack in a flight critical 

component, which could result in 

component failure from static overload 

and subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 38744, June 29, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design and that air safety 

and the public interest require adopting 

the AD requirements as proposed except 

for minor editorial changes to meet 

current publication requirements. These 

minor editorial changes are consistent 

with the intent of the proposals in the 

NPRM (77 FR 38744, June 29, 2012) and 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Related Service Information 

Erickson Service Bulletin No. 64F 

General-1, Rev. 17, contains the 

Airworthiness Limitations Schedule for 

the Model S–64F helicopter and lists the 

parts and assemblies with their 

specified retirement lives. 

Costs of Compliance 

We estimate that this AD will affect 7 

helicopters of U.S. Registry and 

estimate, at an average labor rate of $85 

per hour, the following costs for 

removing from service the parts listed in 

Table 2 of this AD: 

• Reviewing helicopter records to 

determine if an affected part is installed 

will require approximately 2 workhours, for a cost per helicopter of $170 

and a fleet cost of $1,190. 

• Replacing the rotary rudder spindle 

assembly will require 10 work-hours 

and a parts cost of $2,787, for a cost per 

helicopter of $3,637 and a fleet cost of 

$25,459. 

• Replacing the plate will require 40 

work-hours and a parts cost of $43,750, 

for a cost per helicopter of $47,150 and 

a fleet cost of $330,050. 

• Replacing the main servo bracket 

assembly will require 2 work-hours and 

a parts cost of $5,223, for a cost per 

helicopter of $5,393 and a fleet cost of 

$37,751. 

• Replacing the primary servo link 

assembly of the M/R tandem servo will 

require 10 work-hours and a parts cost 

of $14,533, for a cost per helicopter of 

$15,383 and a fleet cost of $107,681. 

• Replacing the T/R shoulder bolt 

will require 10 work-hours and a parts 

cost of $571, for a cost per helicopter of 

$1,421 and a fleet cost of $9,947. 

• Replacing the T/R Blade Assembly 

will require 8 work-hours and a parts 

cost of $125,765 for a cost per helicopter 

of $126,445 and a fleet cost of $885,115. 

• The total cost to replace the parts 

that are required to be removed from 

service is estimated to be $199,599 per 

helicopter and a fleet cost of $1,397,193. 

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 

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. 


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Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations 15601 

For the reasons discussed above, 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. 

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 

removing Amendment 39–10028 (62 FR 

28321, May 23, 1997) and adding the 

following new airworthiness directive 

(AD): 

2012–26–06 ERICKSON AIR-CRANE 

INCORPORATED: Amendment 39– 

17301; Docket No. FAA–2012–0689; 

Directorate Identifier 2009–SW–065–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation-manufactured Model S–64F 

helicopters, now under the Erickson AirCrane Incorporated Model S–64F type 

certificate, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack in a flight critical component. 

This condition could result in component 

failure from static overload and subsequent 

loss of control of the helicopter. 

(c) Other Affected ADs 

This AD supersedes AD 97–10–15, 

Amendment 39–10028 (62 FR 28321, May 23, 

1997). 

(d) Effective Date 

This AD becomes effective April 16, 2013. 

(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 

(1) Before further flight: 

(i) Remove from service any part with a 

number of hours time-in-service (TIS) equal 

to or greater than the part’s retirement life as 

stated in Table 1 to Paragraph (f) of this AD. 

TABLE 1 TO PARAGRAPH (f)—PARTS WITH NEW OR REVISED LIFE LIMITS

Part name Part No. (P/N) Retirement life 

Main Rotor (M/R) Blade Assembly ...................................................................................................... 6415–20601–045 13,280 hours TIS. 

Main Transmission Support Beam Assembly, LH ............................................................................... 6420–62363–045 9,300 hours TIS. 

Main Transmission Support Beam Assembly, RH ............................................................................... 6420–62363–046 9,300 hours TIS. 

Left Splice Fitting (Transition Fitting), Rotary, Rudder Boom .............................................................. 6420–66341–101 8,300 hours TIS. 

Right Splice Fitting (Transition Fitting), Rotary, Rudder Boom ........................................................... 6420–66341–102 8,300 hours TIS. 

M/R Drive Shaft .................................................................................................................................... 6435–20536–101 2,200 hours TIS. 

Pressure Plate Assembly, Rotary Wing Head ..................................................................................... 65101–11016–042 8,800 hours TIS. 

Horn and Liner Assembly ..................................................................................................................... 65102–11047–041 1,140 hours TIS. 

Lower Hub Plate Assembly .................................................................................................................. 65103–11009–041 15,500 hours TIS. 

Horizontal Hinge Pin, Rotary Wing Head ............................................................................................ 65103–11020–103 5,100 hours TIS. 

Damper Bracket Assembly, Rotary Wing Head ................................................................................... 65103–11032–043 20,000 hours TIS. 

Hub Subassembly, Rotary Wing .......................................................................................................... 65103–11310–043 21,600 hours TIS. 

Shaft Assembly, Pitch Control Tail Gearbox ....................................................................................... 65358–07035–043 9,400 hours TIS. 

Rod End Assembly, Primary Servo Assembly ..................................................................................... 65652–11212–041 20,800 hours TIS. 

Note 1 to Table 1 to Paragraph (f) of this 

AD: The list of parts in Table 1 to Paragraph 

(f) of this AD contains only a portion of the 

life-limited parts for this model helicopter 

and is not an all-inclusive list. 

(ii) Revise the retirement life of each part 

as shown in Table 1 to Paragraph (f) of this 

AD by making pen and ink changes or by 

inserting a copy of this AD into the 

Airworthiness Limitations section of the 

maintenance manual. 

(iii) Record on the component history card 

or equivalent record the retirement life for 

each part as shown in Table 1 to Paragraph 

(f) of this AD. 

(2) Before further flight, remove from 

service any part with a P/N listed in Table 

2 to Paragraph (f) of this AD, regardless of the 

part’s TIS. The P/Ns listed in Table 2 to 

Paragraph (f) of this AD are not eligible for 

installation on any helicopter. 

TABLE 2 TO PARAGRAPH (f)—PARTS TO BE REMOVED FROM SERVICE

Part name P/N 

Spindle Assembly, Rotary Rudder .................................................................................................................. 6410–30302–041. 

Main Gearbox Second Stage Lower Planetary Plate ..................................................................................... 6435–20516–101 or 6435–20516– 

102. 

Bracket Assembly, Main Servo ....................................................................................................................... 6435–20527–041 or 6435–20527– 

042. 

Primary Servo Link, Tandem Servo, M/R ....................................................................................................... 6465–62161–042. 

Shoulder Bolt, Tail Rotor (T/R) ....................................................................................................................... 65111–07001–102. 

T/R Blade Assembly ....................................................................................................................................... 65161–00001–041. 


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15602 Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations 

1Annual Charges for the Use of Government 

Lands, Order No. 774, 78 FR 5256 (January 25, 

2013), FERC Stats. & Regs. ¶ 31,341 (2013). 2 18 CFR Part 11 (2012). 

(3) Before further flight, if a T/R blade 

assembly, P/N 65160–00001–048, is 

installed, remove any of the other three T/R 

blade assemblies that have a different P/N 

and replace it with a T/R blade assembly, P/ 

N 65160–00001–048. The T/R blade 

assembly, 

P/N 65160–00001–048, must be installed in 

sets of four only. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

Fort Worth, Texas 76137, telephone (817) 

222–5170, email 7-avs-asw-170@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 

Erickson Service Bulletin No. 64F General1, Revision 17, dated August 17, 2010, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Erickson Air-Crane 

Incorporated, ATTN: Chris Erickson/ 

Compliance Officer, 3100 Willow Springs Rd, 

P.O. Box 3247, Central Point, OR 97502, 

telephone (541) 664–5544, fax (541) 664– 

2312, email address 

cerickson@ericksonaircrane.com. You may 

review a copy of this information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300: Main Rotor Drive System and 

6400: Tail Rotor System. 

Issued in Fort Worth, Texas, on March 1, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05503 Filed 3–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 11 

[Docket No. RM11–6–000] 

Annual Update to Fee Schedule for the 

Use of Government Lands by 

Hydropower Licensees 

AGENCY: Federal Energy Regulatory 

Commission, DOE. 

ACTION: Final rule; annual update to fee 

schedule. 

SUMMARY: In accordance with the 

Commission’s regulations, the 

Commission, by its designee, the 

Executive Director, issues this annual 

update to the fee schedule which lists 

per-acre rental fees by county (or other 

geographic area) for use of government 

lands by hydropower licensees. 

DATES: This rule is effective March 12, 

2013. 

FOR FURTHER INFORMATION CONTACT: 

Norman Richardson, Financial 

Management Division, Office of the 

Executive Director, Federal Energy 

Regulatory Commission, 888 First Street 

NE., Washington, DC 20426, (202) 502– 

6219, Norman.Richardson@ferc.gov. 

SUPPLEMENTARY INFORMATION: 

142 FERC ¶ 62,166 

Issued February 27, 2013. 

Section 11.2 of the Commission’s 

regulations provides a method for 

computing reasonable annual charges 

for recompensing the United States for 

the use, occupancy, and enjoyment of 

its lands by hydropower licensees.1

Annual charges for the use of 

government lands are payable in 

advance, and are based on an annual 

schedule of per-acre rental fees 

published in Appendix A to Part 11 of 

the Commission’s regulations.2 This 

document updates the fee schedule in 

Appendix A to Part 11 for fiscal year 

2013 (October 1, 2012, through 

September 30, 2013). 

Effective Date 

This Final Rule is effective March 12, 

2013. The provisions of 5 U.S.C. 804, 

regarding Congressional review of final 

rules, do not apply to this Final Rule 

because the rule concerns agency 

procedure and practice and will not 

substantially affect the rights or 

obligations of non-agency parties. This 

Final Rule merely updates the fee 

schedule published in the Code of 

Federal Regulations to reflect scheduled 

adjustments, as provided for in section 

11.2 of the Commission’s regulations. 

List of Subjects in 18 CFR Part 11 

Public lands. 

By the Director. 

Anton C. Porter, 

Director, Office of the Executive Director. 

In consideration of the foregoing, the 

Commission amends Chapter I, Title 18, 

Code of Federal Regulations, as follows. 

PART 11—[AMENDED] 

■ 1. The authority citation for Part 11 

continues to read as follows: 

Authority: 16 U.S.C. 792–828c; 42 U.S.C. 

7101–7352. 

■ 2. Appendix A to Part 11 is added to 

read as follows: 

APPENDIX A TO PART 11—FEE 

SCHEDULE FOR FY 2013 

State County Fee/acre/Yr 

Alabama ............. Autauga .............. $53.06 

Baldwin ............... 89.12 

Barbour ............... 48.00 

Bibb .................... 61.16 

Blount ................. 87.24 

Bullock ................ 55.08 

Butler .................. 58.11 

Calhoun .............. 86.56 

Chambers ........... 49.30 

Cherokee ............ 59.31 

Chilton ................ 75.66 

Choctaw ............. 46.85 

Clarke ................. 44.72 

Clay .................... 63.88 

Cleburne ............. 83.84 

Coffee ................. 59.17 

Colbert ................ 58.82 

Conecuh ............. 49.98 

Coosa ................. 56.88 

Covington ........... 61.08 

Crenshaw ........... 58.08 

Cullman .............. 101.36 

Dale .................... 57.51 

Dallas ................. 44.94 

DeKalb ................ 94.36 

Elmore ................ 71.03 

Escambia ............ 57.43 

Etowah ............... 82.01 

Fayette ............... 46.33 

Franklin ............... 57.56 

Geneva ............... 56.31 

Greene ............... 42.14 

Hale .................... 49.85 

Henry .................. 49.49 

Houston .............. 57.92 

Jackson .............. 57.45 

Jefferson ............. 93.62 

Lamar ................. 38.84 

Lauderdale ......... 63.48 

Lawrence ............ 70.94 

Lee ..................... 82.09 

Limestone ........... 72.47 

Lowndes ............. 44.45 

Macon ................. 51.29 

Madison .............. 72.96 

Marengo ............. 45.68 

Marion ................ 54.86 

Marshall .............. 101.03 

Mobile ................. 87.13 

Monroe ............... 48.84 

Montgomery ....... 53.09 

Morgan ............... 77.98 

Perry ................... 43.58 

Pickens ............... 51.13 

Pike .................... 59.09 

Randolph ............ 66.04 

Russell ................ 59.58 

St. Clair .............. 96.10 

Shelby ................ 101.11 

Sumter ................ 39.30 

Talladega ............ 63.37 

Tallapoosa .......... 67.48 

Tuscaloosa ......... 67.32 

Walker ................ 68.49 

Washington ........ 57.62 

Wilcox ................. 37.67 

Winston .............. 70.53 

Alaska ................. Aleutian Islands 

Chain.

1.52 


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