5390 Federal Register / Vol. 70, No. 21 / Wednesday, February 2, 2005 / Proposed Rules 

Modification 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, modify 

wiring in the flight compartment by doing all 

actions in accordance with part 2 of the 

Accomplishment Instructions of the service 

bulletin. Following accomplishment of the 

actions in part 2 of the service bulletin, 

before further flight, do all actions associated 

with the functional test, including revising 

the Emergency Procedures section of the 

Raytheon Hawker 800XP Airplane Flight 

Manual to include the information in 

Temporary Change Part Number 140–

590032–0005TC7, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(1) If no damage was found during the 

inspection required by paragraph (g) of this 

AD: Do paragraph (h) within 300 flight hours 

or 180 days after the effective date of this AD, 

whichever is first. 

(2) If any damage is found during the 

inspection required by paragraph (g) of this 

AD: Do paragraph (h) before further flight 

after the damage is found. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Wichita ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19.

Issued in Renton, Washington, on January 

26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1925 Filed 2–1–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NE–40–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524 Series Turbofan 

Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Supplemental notice of 

proposed rulemaking; reopening of 

comment period. 

SUMMARY: This notice revises an earlier 

proposed airworthiness directive (AD), 

applicable to Rolls Royce plc (RR) 

RB211–524 series turbofan engines with 

certain part number (P/N) intermediate 

pressure (IP) compressor stage 5 disks 

installed. That proposal required new 

reduced IP compressor stage 5 disk 

cyclic limits. That proposal also 

required removing from service affected 

disks that already exceed the new 

reduced cyclic limit, and removing 

other affected disks before exceeding 

their cyclic limits, using a drawdown 

schedule. That proposal resulted from 

the discovery of cracks in the cooling air 

hole areas of the disk front spacer arm. 

This Supplemental Notice of Proposed 

Rulemaking (SNPRM) revises the 

proposed rule by correcting certain 

cycle life limits specified in Table 3 of 

that AD and by clarifying certain 

inspections. We are proposing this AD 

to prevent IP compressor stage 5 disk 

failure, which could result in 

uncontained engine failure and possible 

damage to the airplane.

DATES: Comments must be received by 

April 4, 2005.

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• By mail: Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

Attention: Rules Docket No. 2002–NE–

40–AD, 12 New England Executive Park, 

Burlington, MA 01803–5299. 

• By fax: (781) 238–7055. 

• By e-mail: 9-aneadcomment@faa.gov.

You can get the service information 

identified in this proposed AD from 

Rolls-Royce plc, PO Box 31 Derby, 

DE248BJ, United Kingdom; telephone 

011–44–1332–242424; fax 011–44–

1332–249936. 

You may examine the AD docket, by 

appointment, at the FAA, New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

2002–NE–40–AD’’ in the subject line of 

your comments. If you want us to 

acknowledge receipt of your mailed 

comments, send us a self-addressed, 

stamped postcard with the docket 

number written on it; we will datestamp your postcard and mail it back to 

you. We specifically invite comments 

on the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. If a person contacts us 

verbally, and that contact relates to a 

substantive part of this proposed AD, 

we will summarize the contact and 

place the summary in the docket. We 

will consider all comments received by 

the closing date and may amend the 

proposed AD in light of those 

comments. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Discussion 

On October 21, 2003 we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

add an AD to apply to RR RB211–524 

series turbofan engines, with certain P/

N IP compressor stage 5 disks installed. 

The Office of the Federal Register 

published that proposal as a notice of 

proposed rulemaking (NPRM) in the 

Federal Register on October 27, 2003 

(68 FR 61158). That NPRM would have 

required new reduced IP compressor 

stage 5 disk cyclic limits. The NPRM 

also required removing from service 

affected disks that already exceed the 

new reduced cyclic limit, and removing 

other affected disks before exceeding 

their cyclic limits, using a drawdown 

schedule. That NPRM resulted from the 

discovery of cracks in the cooling air 

hole areas of the disk front spacer arm. 

That condition, if not corrected, could 

result in IP compressor stage 5 disk 

failure, which could result in 

uncontained engine failure and possible 

damage to the airplane.

Since we issued that NPRM, we found 

an error in Table 3 at the date December 

1, 2008 row. The cycle life limits in 

columns 4 and 5 of this row were 

written incorrectly as 12,000. We have 

corrected those cycle life limits to 8,900 

and 9,000 CIS, respectively. We have 

removed the phrase ‘‘one-time’’ in 

reference to on-wing inspections. We 

also added a sentence to clarify that an 

on-wing inspection may be used to 

extend service life only once between 

shop visit inspections of the disk. 

Since these changes expand the scope 

of the originally proposed rule, we 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for public 

comment. 

Manufacturer’s Service Information 

We have reviewed and approved the 

technical contents of RR Mandatory 

Service Bulletin (MSB) No. RB.211–72–

D428, Revision 3, dated June 30, 2003, 

that specifies a drawdown schedule for 

Federal Register / Vol. 70, No. 21 / Wednesday, February 2, 2005 / Proposed Rules 5391

removing from service affected IP 

compressor stage 5 disks, using new RR 

Time Limits Manual (TLM), 05–10–01 

cyclic limits. The MSB also describes 

procedures for optional inspections at 

each shop visit to extend the disk life 

beyond the lives specified. The Civil 

Aviation Authority (CAA), the 

airworthiness authority of the United 

Kingdom (U.K.), has classified this 

service bulletin as mandatory and 

issued AD 006–04–2002 to ensure the 

airworthiness of these RR turbofan 

engines in the U.K. We have also 

reviewed and approved the technical 

contents of Service Bulletin (SB) No. 

RB.211–72–E148, dated March 13, 2003 

and SB No. RB.211–72–E150, Revision 

1, dated June 4, 2003, that provide an 

optional on-wing ECI of the affected 

disks, to extend the disk life beyond the 

lives specified. 

Differences Between This Proposed AD 

and the Manufacturer’s Service 

Information 

This proposed AD adds a requirement 

to change the service cyclic limits in the 

Time Limits Manual and to remove or 

inspect disks not later than 30 days after 

the effective date of this AD. 

FAA’s Determination of an Unsafe 

Condition and Proposed Actions 

These engine models, manufactured 

in the U.K., are type-certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Under this 

bilateral airworthiness agreement, the 

CAA has kept us informed of the 

situation described above. We have 

examined the CAA’s findings, reviewed 

all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. Therefore, we are proposing this 

AD, which would require: 

• Establishing new reduced IP 

compressor stage 5 disk cyclic limits. 

• Removing from service affected 

disks that already exceed the new 

reduced cyclic limit. 

• Removing other affected disks 

before exceeding their cyclic limits, 

using a drawdown schedule. 

• Allowing optional inspections at 

each shop visit or an on-wing ECI to 

extend the disk life beyond the specified 

life.

The proposed AD would require you to 

use the service information described 

previously to perform these actions.

Economic Analysis 

There are about 939 RR RB211–524 

series turbofan engines of the affected 

design in the worldwide fleet. We 

estimate that 35 engines installed on 

airplanes of U.S. registry will be affected 

by this proposed AD. We also estimate 

that it will take about 8 work hours per 

engine to perform an inspection, and 

300 work hours per engine to replace an 

IP compressor stage 5 disk. The average 

labor rate is $65 per work hour. 

Required parts will cost about $49,000 

per engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $2,415,700. 

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 Analysis 

We have 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 that the 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); and 

3. Would 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 a summary of the costs 

to comply with this proposal and placed 

it in the AD Docket. You may get a copy 

of this summary at the address listed 

under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Rolls Royce plc: Docket No. 2002–NE–40–

AD.

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by April 

4, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Rolls-Royce plc 

(RR) RB211–524 series turbofan engines 

listed in the following Table 1, with 

intermediate pressure (IP) compressor stage 5 

disk part numbers (P/Ns) listed in Table 2 of 

this AD, installed.

TABLE 1.—ENGINE MODELS AFFECTED

–524B–02 –524B–B–02 –524B3–02 –524B4–02 –524B4–D–02 

–524B2–19 –524B2–B–19 –524C2–19 –524C2–B–19 –524D4–19 

–524D4–B–19 –524D4X–19 –524D4X–B–19 –524D4–39 –524D4–B–39 

–524G2–19 –524G2–T–19 –524G3–19 –524G3–T–19 –524H2–19 

–524H2–T–19 –524H–36 –524H–T–36

These engines are installed on, but not limited to, Boeing 747, 767, and Lockheed L–1011 airplanes.

5392 Federal Register / Vol. 70, No. 21 / Wednesday, February 2, 2005 / Proposed Rules 

TABLE 2.—IP COMPRESSOR STAGE 5 DISK P/NS AFFECTED

LK60130 LK65932 LK69021 LK81269 LK83282 

LK83283 UL12290 UL15743 UL15744 UL15745 

UL19132 UL20785 UL20832 UL23291 UL25011 

UL36821 UL36977 UL36978 UL36979 UL36980 

UL36981 UL36982 UL36983 UL37078 UL37079 

UL37080 UL37081 UL37082 UL37083 UL37084 

Unsafe Condition 

(d) This AD results from discovery of 

cracks in the cooling air hole areas of the disk 

front spacer arm. The actions specified in 

this AD are intended to prevent IP 

compressor stage 5 disk failure, which could 

result in uncontained engine failure and 

possible damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Cycle Limits 

(f) Change the service cyclic limits 

contained in the Time Limits Manual, 05–

10–01, for the IP compressor stage 5 discs 

installed in the engine models listed in the 

following Table 3, within 30 days after the 

effective date of this AD.

TABLE 3.—CYCLIC LIFE LIMITS WITHOUT QUALIFYING MAGNETIC PARTICLE INSPECTION (MPI) OR EDDY CURRENT

INSPECTION (ECI) 

Date of reduced life limit 

Engine Models 

–524G2, G2–T, 

G3, G3–T, H2, H2–

T, H–36, H–T–36 

–524D4, D4–B, 

D4–B–39, D4X, 

D4X–B, D4–39 

–524B2, B2–B, C2, 

C2–B 

–524B–02, B–B–

02, B3–02, B4–02, 

B4–D–02 

November 30, 2002 ........................................................... 13,500 cycles-inservice (CIS) 16,150 CIS 16,000 CIS 16,200 CIS 

April 1, 2003 ....................................................................... 13,500 CIS 13,500 CIS 13,500 CIS 14,000 CIS

December 1, 2003 ............................................................. 12,000 CIS 13,500 CIS 13,500 CIS 14,000 CIS 

December 1, 2004 ............................................................. 11,000 CIS 13,500 CIS 12,000 CIS 12,000 CIS 

December 1, 2005 ............................................................. 11,000 CIS 12,000 CIS 12,000 CIS 12,000 CIS 

December 1, 2008 ............................................................. 7,830 CIS 8,700 CIS 8,900 CIS 9,000 CIS 

Optional Inspections 

(g) Before December 1, 2008, optional 

inspections are allowed at each shop visit or 

on-wing to extend the disk life. Guidance for 

these inspections is provided in paragraphs 

(h) or (i) of this AD. 

Optional Inspections at Shop Visit 

(h) Perform optional inspections at shop 

visit, as follows: 

(1) Remove corrosion protection from IP 

stage 5 disk. Information on corrosion 

protection removal can be found in the 

Engine Manual. 

(2) Visual-inspect and binocular-inspect 

the IP stage 5 disk for corrosion pitting at the 

cooling air holes and defender holes in the 

disk front spacer arm. Follow paragraph 3.C. 

of the Accomplishment Instructions of RR 

MSB No. RB.211–72–D428, Revision 3, dated 

June 30, 2003. Information on disk corrosion 

pitting limits can be found in the Engine 

Manual. 

(i) If the disk has corrosion pitting in 

excess of limits, remove the disk from 

service. 

(ii) If the disk is free from corrosion pitting, 

MPI the entire disk. Information on MPI can 

be found in the Engine Manual. If the disk 

passes MPI and no cracks are found, 

complete all other inspections, re-apply 

corrosion protection to disk, and return the 

disk to service in accordance with the cyclic 

limits allowed by paragraph (k) of this AD. 

Information on MPI limits can be found in 

the Engine Manual. Information on reapplying corrosion protection can be found 

in RR Repair FRS5900.

(iii) If the disk has corrosion pitting within 

limits, ECI all disk cooling air holes, defender 

holes, and inner and outer faces. Follow 

paragraph 3.D. of the Accomplishment 

Instructions of RR MSB No. RB.211–72–

D428, Revision 3, dated June 30, 2003. 

Information on corrosion pitting limits can be 

found in the Engine Manual. If the disk 

passes ECI and no cracks are found, MPI the 

entire disk. Information on MPI can be found 

in the Engine Manual. If the disk passes MPI 

and no cracks are found, re-apply corrosion 

protection to disk, and return the disk to 

service in accordance with the cyclic limits 

allowed by paragraph (k) of this AD. 

Optional On-Wing EC Inspections 

(i) For RB211–524B2/C2 and RB211–

524B4/D4 engine models, an on-wing ECI of 

the IP compressor stage 5 disk may be 

performed only once between shop visit 

inspections. Follow paragraphs 3.A. through 

3.F. of the Accomplishment Instructions of 

RR SB No. RB.211–72–E148, dated March 13, 

2003, and RR SB No. RB.211–72–E150, 

Revision 1, dated June 4, 2003, respectively, 

to do the ECI. If the disk passes the ECI and 

no cracks are found, an extension is allowed 

as specified in paragraph (k) of this AD. 

Definition of Shop Visit 

(j) For the purposes of this AD, a shop visit 

is defined as the separation of an engine 

major case flange. This definition excludes 

shop visits when only field maintenance type 

activities are performed in lieu of performing 

them on-wing. (i.e., for purposes such as to 

perform an on-wing inspection of a tail 

engine installation on a Lockheed L–1011 

airplane). 

Cyclic Life Extension 

(k) Disks that pass an optional inspection 

may remain in service after that inspection 

for the additional cycles listed in the 

following Table 4, until the next inspection, 

or December 1, 2008, or until the cyclic life 

limit published in the Time Limits Manual 

is reached, whichever occurs first.

TABLE 4.—CYCLIC LIFE EXTENSION

Engine models 

–524G2, G2–T, 

G3, G3–T, H2, H2–

T, H–36, H–T–36 

–524D4, D4–B, 

D4–B–39, D4X, 

D4X–B, D4–39 

–524B2, B2–B, C2, 

C2–B 

–524B–02, B–B–

02, B3–02, B4–02, 

B4–D–02 

Extension After Passing MPI ............................................. 1,600 cycles 2,000 cycles 2,000 cycles 2,000 cycles. 

Federal Register / Vol. 70, No. 21 / Wednesday, February 2, 2005 / Proposed Rules 5393

TABLE 4.—CYCLIC LIFE EXTENSION—Continued

Engine models 

–524G2, G2–T, 

G3, G3–T, H2, H2–

T, H–36, H–T–36 

–524D4, D4–B, 

D4–B–39, D4X, 

D4X–B, D4–39 

–524B2, B2–B, C2, 

C2–B 

–524B–02, B–B–

02, B3–02, B4–02, 

B4–D–02 

Extension After Passing In-Shop ECI ................................ 3,800 cycles 4,500 cycles 4,500 cycles 4,500 cycles. 

Extension After Passing On-Wing ECI .............................. 1,000 cycles 1,200 cycles 1,200 cycles 1,200 cycles. 

Disks That Have Been Intermixed Between 

Engine Models 

(l) Information on intermixing disks 

between engine models can be found in the 

RR Time Limits Manual, 05–00–01. 

Alternative Methods of Compliance 

(m) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Credit for Previous Inspections 

(n) Inspections done using RR SB No. 

RB.211–72–E150, dated April 17, 2003 are 

acceptable in meeting the requirements of 

this AD. 

Reporting Requirement 

(o) Report findings of all inspections of the 

IP stage 5 disk using paragraph 3.B.(2) of the 

Accomplishment Instructions of RR ASB 

RB.211–72–D428, Revision 3, dated June 30, 

2003. The Office of Management and Budget 

(OMB) has approved the reporting 

requirements specified in Paragraph 3.B. of 

the Accomplishment Instructions of RR ASB 

RB.211–72–D428, Revision 3, dated June 30, 

2003, and assigned OMB control number 

2120–0056. 

Related Information 

(p) CAA airworthiness directive 006–04–

2002, dated April 2002, also addresses the 

subject of this AD.

Issued in Burlington, Massachusetts, on 

January 25, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 05–1799 Filed 2–1–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF THE TREASURY

Alcohol and Tobacco Tax and Trade 

Bureau 

27 CFR Part 9 

[Notice No. 32] 

RIN: 1513–AA90 

Proposed Establishment of the Covelo 

Viticultural Area (2003R–412P)

AGENCY: Alcohol and Tobacco Tax and 

Trade Bureau, Treasury.

ACTION: Notice of proposed rulemaking.

SUMMARY: The Alcohol and Tobacco Tax 

and Trade Bureau proposes to establish 

the 38,000-acre ‘‘Covelo’’ viticultural 

area in Mendocino County, California, 

about 150 miles north of San Francisco. 

We designate viticultural areas to allow 

vintners to better describe the origin of 

their wines and to allow consumers to 

better identify wines they may 

purchase. We invite comments on this 

proposed addition to our regulations.

DATES: We must receive written 

comments on or before April 4, 2005.

ADDRESSES: You may send comments to 

any of the following addresses: 

• Chief, Regulations and Procedures 

Division, Alcohol and Tobacco Tax and 

Trade Bureau, Attn: Notice No. 32, P.O. 

Box 14412, Washington, DC 20044–

4412. 

• 202–927–8525 (facsimile). 

• nprm@ttb.gov (e-mail). 

• http://www.ttb.gov/alcohol/rules/

index.htm. An online comment form is 

posted with this notice on our Web site. 

• http://www.regulations.gov (Federal 

e-rulemaking portal; follow instructions 

for submitting comments). 

You may view copies of this notice, 

the petition, the appropriate maps, and 

any comments we receive about this 

proposal by appointment at the TTB 

Library, 1310 G Street, NW., 

Washington, DC 20220. To make an 

appointment, call 202–927–2400. You 

may also access copies of the notice and 

comments online at http://www.ttb.gov/

alcohol/rules/index.htm.

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.

FOR FURTHER INFORMATION CONTACT: N. 

A. Sutton, AVA Program Manager, 

Regulations and Procedures Division, 

Alcohol and Tobacco Tax and Trade 

Bureau, 925 Lakeville Street, No.158, 

Petaluma, CA 94952; telephone 415–

271–1254.

SUPPLEMENTARY INFORMATION:

Background on Viticultural Areas 

TTB Authority 

Section 105(e) of the Federal Alcohol 

Administration Act (the FAA Act, 27 

U.S.C. 201 et seq.) requires that alcohol 

beverage labels provide the consumer 

with adequate information regarding a 

product’s identity and prohibits the use 

of misleading information on those 

labels. The FAA Act also authorizes the 

Secretary of the Treasury to issue 

regulations to carry out its provisions. 

The Alcohol and Tobacco Tax and 

Trade Bureau (TTB) administers these 

regulations. 

Part 4 of the TTB regulations (27 CFR 

part 4) allows 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) contains the 

list of approved viticultural areas. 

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 

distinguishable by geographical 

features, the boundaries of which have 

been recognized and defined 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 its 

geographic origin. The establishment of 

viticultural areas allows vintners to 

describe more accurately the origin of 

their wines to consumers and helps 

consumers to identify wines they may 

purchase. Establishment of a viticultural 

area 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 an American viticultural area 

and provides that any interested party 

may petition TTB to establish a grapegrowing region as a viticultural area. 

Section 9.3(b) of the TTB regulations 

requires the petition to include—

• Evidence that the proposed 

viticultural area is locally and/or 

nationally known by the name specified 

in the petition; 

• Historical or current evidence that 

supports setting the boundary of the 

proposed viticultural area as the 

petition specifies;