36680 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

and aft large lower lobe cargo doors, as 

applicable, to determine the part number and 

serial number, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–52A0100, Revision 2, 

dated September 26, 2013; and Eaton Service 

Bulletin 692D100–52–4, Revision 2, dated 

August 1, 2013. Do the applicable corrective 

actions at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 767–52A0100, Revision 2, 

dated September 26, 2013, except as required 

by paragraph (i) of this AD. A review of 

maintenance records for the part number and 

serial number is acceptable in lieu of the 

inspection if the part and serial numbers of 

the rotary actuator can be conclusively 

determined from that review. 

(h) Inspection for Part Numbers, and ReIdentification or Replacement, for Model 777 

Airplanes 

For Model 777–200, –200LR, –300, 

–300ER, and 777F series airplanes: Within 72 

months after the effective date of this AD, 

inspect each rotary actuator installed in the 

forward and aft large lower lobe cargo doors, 

as applicable, to determine the part number 

and serial number, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–52–0053, Revision 1, 

dated September 26, 2013; and Eaton Service 

Bulletin 692D100–52–4, Revision 2, dated 

August 1, 2013. Do the applicable corrective 

actions at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 777–52–0053, Revision 1, 

dated September 26, 2013, except as required 

by paragraph (i) of this AD. A review of 

maintenance records for the part number and 

serial number is acceptable in lieu of the 

inspection if the part and serial numbers of 

the rotary actuator can be conclusively 

determined from that review. 

(i) Exception to the Service Information 

Where Boeing Service Bulletin 767– 

52A0100, Revision 2, dated September 26, 

2013; and Boeing Service Bulletin 777–52– 

0053, Revision 1, dated September 26, 2013, 

specify a compliance time after the issue date 

‘‘of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

rotary actuator having Boeing part number 

S135W132–3 (supplier part number 

692D100–13) may be installed on any 

airplane. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6457; fax: 425–917–6590; email: 

susan.l.monroe@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. For Eaton service 

information identified in this AD, contact 

Eaton Corporation, Aerospace Operations, 3 

Park Plaza, Suite 1200, Irvine, CA 92614; 

telephone 949–253–2100; fax 949–253–2111; 

Internet http://www.eaton.com. You may 

view this referenced service information at 

the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15250 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0347; Directorate 

Identifier 2013–NM–173–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200 

and –300 series airplane equipped with 

Pratt & Whitney Model JT9D or PW4000 

engines. This proposed AD was 

prompted by a report of several cases of 

low hydraulic pressure or loss of 

electrical power to the alternating 

current motor pump (ACMP) on the left 

engine. This proposed AD would 

require inspecting for damage of the 

wiring bundles in the left engine’s strut 

and corrective actions if necessary, and 

installing new wire support brackets 

and bundle clamp. We are proposing 

this AD to detect and correct chafed 

wire bundles due to rubbing against 

structure or a hydraulic piping elbow, 

which could result in electrical arcing 

in a flammable fluid leakage zone, and 

would provide a possible ignition 

source for fuel vapors and hydraulic 

fluids. Ignited fuel vapors or hydraulic 

fluid in an area without a fire detection 

or suppression system could result in an 

uncontained engine strut fire and 

structural damage to the engine strut. 

DATES: We must receive comments on 

this proposed AD by August 14, 2014. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this 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 by searching for 

and locating Docket No. FAA–2014– 

0347; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 36681 

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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6482; 

fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0347; Directorate Identifier 2013– 

NM–173–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 have received a report of several 

cases of low hydraulic pressure or loss 

of electrical power to the ACMP on the 

left engine. These cases were found to 

be caused by a damaged power feeder 

wire bundle in the outboard aft fairing 

area of the left engine strut. In most of 

the cases, the wire bundle had chafed 

against the fuse pin washer at the 

midspar fitting and signs of arcing were 

found. In one case, the wire bundle was 

found to have chafed against a hydraulic 

piping elbow near the fuse pin washer, 

which resulted in a severed wire bundle 

and a hole in the hydraulic piping 

elbow. That hole in the hydraulic piping 

elbow, if not found, could result in a 

hydraulic fluid leak. Wire bundles that 

are chafed due to rubbing against 

structure or the hydraulic piping elbow, 

if not detected and corrected, could 

result in electrical arcing in a flammable 

fluid leakage zone, and would provide 

a possible ignition source for fuel vapors 

and hydraulic fluids. Ignited fuel vapors 

or hydraulic fluid in an area without a 

fire detection or suppression system 

could result in an uncontained engine 

strut fire and structural damage to the 

engine strut. 

Related Rulemaking 

AD 2004–16–12, Amendment 39– 

13768 (69 FR 51002, August 17, 2004), 

also applies to certain Model 767 

airplanes that are powered by Pratt & 

Whitney engines. AD 2004–16–12 

required actions to prevent fatigue 

cracking in primary strut structure, 

which could result in separation of the 

strut and engine from the airplane. One 

of those actions is the prior or 

concurrent accomplishment of Boeing 

Service Bulletin 767–29–0057, dated 

December 16, 1993; or Revision 1, dated 

August 14, 2003. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 767–29A0115, dated May 22, 

2013. For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0347. 

Boeing Alert Service Bulletin 767– 

29A0115, dated May 22, 2013, specifies 

concurrent or prior accomplishment of 

Boeing Service Bulletin 767–29–0057, 

Revision 3, dated June 9, 2011, for 

modification of certain wire bundles. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

inspecting for damage of the wiring 

bundles in the left engine’s strut, and 

corrective actions if necessary; and 

installing new wiring support brackets 

and bundle clamp. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 

for compliance with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of crucial AD 

requirements and help provide 

consistent judgment in AD compliance. 

The actions specified in Boeing Alert 

Service Bulletin 767–29A0115, dated 

May 22, 2013, described previously 

include steps that are labeled as RC 

(required for compliance) because these 

steps have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As noted in Boeing Alert Service 

Bulletin 767–29A0115, dated May 22, 

2013, steps labeled as RC must be done 

to comply with the proposed AD. 

However, steps that are not labeled as 

RC are recommended. Those steps that 

are not labeled as RC may be deviated 

from, done as part of other actions, or 

done using accepted methods different 

from those identified in Boeing Alert 

Service Bulletin 767–29A0115, dated 

May 22, 2013, without obtaining 

approval of an alternative method of 

compliance (AMOC), provided the steps 

labeled as RC can be done and the 

airplane can be put back in a serviceable 

condition. Any substitutions or changes 

to steps labeled as RC will require 

approval of an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 126 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and installation ............................... 13 work-hours × $85 per hour = $1,105 ........ $349 $1,454 $183,204 


emcdonald on DSK67QTVN1PROD with PROPOSALS
36682 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 proposed 

regulation is within the scope of that 

authority because it addresses an unsafe 

condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2014–0347; Directorate Identifier 2013– 

NM–173–AD. 

(a) Comments Due Date 

We must receive comments by August 14, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Boeing Company 

Model 767–200 and –300 series airplanes, 

certificated in any category, equipped with 

Pratt & Whitney Model JT9D or PW4000 

engines, as identified in Boeing Alert Service 

Bulletin 767–29A0115, dated May 22, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Unsafe Condition 

This AD was prompted by a report of 

several cases of low hydraulic pressure or 

loss of electrical power to the alternating 

current motor pump (ACMP) on the left 

engine. We are issuing this AD to detect and 

correct chafed wire bundles due to rubbing 

against structure or a hydraulic piping elbow, 

which could result in electrical arcing in a 

flammable fluid leakage zone, and would 

provide a possible ignition source for fuel 

vapors and hydraulic fluids. Ignited fuel 

vapors or hydraulic fluid in an area without 

a fire detection or suppression system could 

result in an uncontained engine strut fire and 

structural damage to the engine strut. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Actions 

Within 48 months after the effective date 

of this AD, do a detailed inspection for 

damage of the wiring bundles in the left 

engine’s strut, and all applicable corrective 

actions; and install new wire support 

brackets and bundle clamps; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–29A0115, 

dated May 22, 2013. Do all applicable 

corrective actions before further flight. 

(h) Prior or Concurrent Action 

For airplanes identified as Group 1 

airplanes in Boeing Alert Service Bulletin 

767–29A0115, dated May 22, 2013: Prior to 

or concurrently with doing the actions 

required by paragraph (g) of this AD, do a 

modification of the wire bundles, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

29–0057, Revision 3, dated June 9, 2011. 

Note 1 to paragraph (h) of this AD: For 

certain airplanes, paragraph (b) of AD 2004– 

16–12, Amendment 39–13768 (69 FR 51002, 

August 17, 2004), references Boeing Service 

Bulletin 767–29–0057, dated December 16, 

2003; and Boeing Service Bulletin 767–29– 

0057, Revision 1, dated August 14, 2003; as 

concurrent requirements. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using any of the 

service information identified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD, which are 

not incorporated by reference in this AD. 

(1) Boeing Service Bulletin 767–29–0057, 

dated December 16, 1993. 

(2) Boeing Service Bulletin 767–29–0057, 

Revision 1, dated August 14, 2003. 

(3) Boeing Service Bulletin 767–29–0057, 

Revision 2, dated September 24, 2009. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(k) Related Information 

(1) For more information about this AD, 

contact Georgios Roussos, Aerospace 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 36683 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: (425) 917– 

6482; fax: (425) 917–6590; email: 

georgios.roussos@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this 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. 

Issued in Renton, Washington, on June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15247 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Alcohol and Tobacco Tax and Trade 

Bureau 

27 CFR Part 9 

[Docket No. TTB–2014–0006; Notice No. 

144] 

RIN 1513–AC09 

Proposed Establishment of the 

Fountaingrove District Viticultural Area 

AGENCY: Alcohol and Tobacco Tax and 

Trade Bureau, Treasury. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Alcohol and Tobacco Tax 

and Trade Bureau (TTB) proposes to 

establish the approximately 38,000-acre 

‘‘Fountaingrove District’’ viticultural 

area in Sonoma County, California. The 

proposed viticultural area lies entirely 

within the larger, multicounty North 

Coast viticultural area. TTB designates 

viticultural areas to allow vintners to 

better describe the origin of their wines 

and to allow consumers to better 

identify wines they may purchase. TTB 

invites comments on this proposed 

addition to its regulations. 

DATES: Comments must be received by 

August 29, 2014. 

ADDRESSES: Please send your comments 

on this notice to one of the following 

addresses (please note that TTB has a 

new address for comments submitted by 

U.S. mail): 

• Internet: http://www.regulations.gov 

(via the online comment form for this 

notice as posted within Docket No. 

TTB–2014–0006 at ‘‘Regulations.gov,’’ 

the Federal e-rulemaking portal); 

• U.S. Mail: Director, Regulations and 

Rulings Division, Alcohol and Tobacco 

Tax and Trade Bureau, 1310 G Street 

NW., Box 12, Washington, DC 20005; or 

• Hand delivery/courier in lieu of 

mail: Alcohol and Tobacco Tax and 

Trade Bureau, 1310 G Street NW., Suite 

200–E, Washington, DC 20005. 

See the Public Participation section of 

this notice for specific instructions and 

requirements for submitting comments, 

and for information on how to request 

a public hearing or obtain or review 

copies of the petition and supporting 

materials. 

FOR FURTHER INFORMATION CONTACT: 

Karen A. Thornton, Regulations and 

Rulings Division, Alcohol and Tobacco 

Tax and Trade Bureau, 1310 G Street 

NW., Box 12, Washington, DC 20005; 

phone 202–453–1039, ext. 175. 

SUPPLEMENTARY INFORMATION: 

Background on Viticultural Areas 

TTB Authority 

Section 105(e) of the Federal Alcohol 

Administration Act (FAA Act), 27 

U.S.C. 205(e), authorizes the Secretary 

of the Treasury to prescribe regulations 

for the labeling of wine, distilled spirits, 

and malt beverages. The FAA Act 

provides that these regulations should, 

among other things, prohibit consumer 

deception and the use of misleading 

statements on labels and ensure that 

labels provide the consumer with 

adequate information as to the identity 

and quality of the product. The Alcohol 

and Tobacco Tax and Trade Bureau 

(TTB) administers the FAA Act 

pursuant to section 1111(d) of the 

Homeland Security Act of 2002, 

codified at 6 U.S.C. 531(d). The 

Secretary has delegated various 

authorities through Treasury 

Department Order 120–01 (Revised), 

dated December 10, 2013, to the TTB 

Administrator to perform the functions 

and duties in the administration and 

enforcement of this law. 

Part 4 of the TTB regulations (27 CFR 

part 4) authorizes the establishment of 

definitive viticultural areas and the use 

of their names as appellations of origin 

on wine labels and in wine 

advertisements. Part 9 of the TTB 

regulations (27 CFR part 9) sets forth 

standards for the preparation and 

submission to TTB of petitions for the 

establishment or modification of 

American viticultural areas (AVAs) and 

lists the approved AVAs. 

Definition 

Section 4.25(e)(1)(i) of the TTB 

regulations (27 CFR 4.25(e)(1)(i)) defines 

a viticultural area for American wine as 

a delimited grape-growing region having 

distinguishing features as described in 

part 9 of the regulations and a name and 

a delineated boundary as established in 

part 9 of the regulations. These 

designations allow vintners and 

consumers to attribute a given quality, 

reputation, or other characteristic of a 

wine made from grapes grown in an area 

to the wine’s geographic origin. The 

establishment of AVAs allows vintners 

to describe more accurately the origin of 

their wines to consumers and helps 

consumers to identify wines they may 

purchase. Establishment of an AVA is 

neither an approval nor an endorsement 

by TTB of the wine produced in that 

area. 

Requirements 

Section 4.25(e)(2) of the TTB 

regulations outlines the procedure for 

proposing the establishment of an AVA 

and provides that any interested party 

may petition TTB to establish a grapegrowing region as an AVA. Section 9.12 

of the TTB regulations (27 CFR 9.12) 

prescribes the standards for petitions 

requesting the establishment or 

modification of AVAs. Petitions to 

establish an AVA must include the 

following: 

• Evidence that the region within the 

proposed AVA boundary is nationally 

or locally known by the AVA name 

specified in the petition; 

• An explanation of the basis for 

defining the boundary of the proposed 

AVA; 

• A narrative description of the 

features of the proposed AVA that affect 

viticulture, such as climate, geology, 

soils, physical features, and elevation, 

that make the proposed AVA distinctive 

and distinguish it from adjacent areas 

outside the proposed AVA; 

• The appropriate United States 

Geological Survey (USGS) map(s) 

showing the location of the proposed 

AVA, with the boundary of the 

proposed AVA clearly drawn thereon; 

and 

• A detailed narrative description of 

the proposed AVA boundary based on 

USGS map markings. 

Fountaingrove District Petition 

TTB received a petition from Douglas 

Grigg of Walnut Hill Vineyards, LLC, on 

behalf of the Fountaingrove Appellation 

Committee, proposing the establishment 

of the ‘‘Fountaingrove District’’ AVA in 

Sonoma County, California. The 

committee originally proposed the name 

‘‘Fountaingrove’’ but later requested to 

change the name to ‘‘Fountaingrove 

District’’ in order to avoid affecting 

current use of the word 

‘‘Fountaingrove,’’ standing alone, in 

brand names on wine labels. The 


emcdonald on DSK67QTVN1PROD with PROPOSALS