Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Rules and Regulations 26787

Applicability: Model EMB–135 and –145

series airplanes, as listed in EMBRAER

Service Bulletin 145–26–0008, dated

December 19, 2000; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that certain tubing fittings of the

fire extinguishing systems are properly

torqued, accomplish the following:

Torque and Paint

(a) Within 100 flight hours after the

effective date of this AD, apply torque to the

tubing fittings of the fire extinguishing

system of the engines in the inner side of the

left- and right-hand pylons, and apply torque

paint to the fittings, per EMBRAER Service

Bulletin 145–26–0008, dated December 19,

2000.

(b) Within 400 flight hours after the

effective date of this AD, do the actions

specified in paragraphs (b)(1), (b)(2), (b)(3),

and (b)(4) of this AD, as applicable, per

EMBRAER Service Bulletin 145–26–0008,

dated December 19, 2000.

(1) For all airplanes: Apply torque to the

remaining tubing fittings (i.e., those fittings

not indicated in paragraph (a) of this AD) of

the engine fire extinguishing system in the

tail cone compartment, rear electronic

compartment, and baggage compartment, and

to the tubing fittings between the pylon walls

and the left- and right-hand engines.

(2) For all airplanes: Apply torque to the

tubing fittings of the fire extinguishing

system of the auxiliary power unit.

(3) For airplanes configured with a Class

‘‘C’’ baggage compartment: Apply torque to

all tubing fittings of the fire extinguishing

system of the baggage compartment.

(4) For all airplanes: Apply torque painting

to the tubing fittings.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Atlanta

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with EMBRAER Service Bulletin 145–26–

0008, dated December 19, 2000. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Boulevard, Suite 450, Atlanta,

Georgia; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 3: The subject of this AD is addressed

in Brazilian airworthiness directive 2001–02–

01, dated February 21, 2001.

Effective Date

(f) This amendment becomes effective on

May 30, 2001.

Issued in Renton, Washington, on May 7,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11900 Filed 5–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–49–AD; Amendment 39–

12228; AD 2000–03–03 R1]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF34 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to General Electric Company

CF34 series turbofan engines, that

currently requires revisions to the

Engine Maintenance Program specified

in the manufacturer’s Instructions for

Continued Airworthiness (ICA) for

General Electric Company (GE) CF34

series turbofan engines. Those revisions

require enhanced inspection of selected

critical life-limited parts at each piecepart exposure. The existing AD also

requires that an air carrier’s approved

continuous airworthiness maintenance

program incorporate these inspection

procedures. This amendment removes

inspection requirements for parts

removed from engines mounted onwing. This amendment is prompted by

the high removal rate and subsequent

piece-part exposure of fan disks due to

certain maintenance procedures. This

additional exposure has resulted in fan

disk focused inspection rates that

exceed the intent of the focused

inspection initiative. The actions

specified by this AD are intended to

prevent critical life-limited rotating

engine part failure, which could result

in an uncontained engine failure and

damage to the airplane.

DATES: Effective June 19, 2001.

ADDRESSES: The information referenced

in this AD may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at

the Office of the Federal Register, 800

North Capitol Street, NW., 7th Floor,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Kevin Donovan, Aerospace Engineer

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7743,

fax (238) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by revising AD 2000–03–03,

Amendment 39–11560 (65 FR 5759),

which is applicable to General Electric

Company CF34 series turbofan engines,

was published in the Federal Register

on August 18, 2000 (65 FR 50468). The

action removed inspection requirements

for parts removed from engines

mounted on-wing.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Change to Aircraft Model Designation

One comment asks that the

Applicability Section be changed to

reflect the Department of Transportation

(DOT) aircraft model designation rather

than the Bombardier aircraft model

designation.

The FAA agrees. The model

designation has been changed to reflect

the DOT designation.

26788 Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Rules and Regulations

Remove ASB Reference

A comment requests that the FAA

remove the reference to Alert Service

Bulletin (ASB) 72–A0103 contained in

subparagraph (A) of the change to the

instructions for continue airworthiness

(ICA’s).

The FAA agrees. The language of the

ASB has subsequently been

incorporated into the manual cited, SEI–

756, chapter 72–00–00. Therefore,

reference to the ASB in the required

change to the ICA’s is not needed.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order 13132, because it 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. Accordingly, the

FAA has not consulted with state

authorities prior to publication of this

rule.

For the reasons discussed above, I

certify that this action (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); and (3)

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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (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

removing Amendment 39–11560 (65 FR

5759, February 7, 2000), and by adding

a new airworthiness directive (AD),

Amendment 39–12228 to read as

follows:

2000–03–03 R1 General Electric Company:

Amendment 39–12228. Docket 99–NE–

49–AD. Revises AD 2000–03–03,

Amendment 39–11560.

Applicability: General Electric Company

(GE) CF34–3A1 and –3B1 series turbofan

engines, installed on but not limited to

Bombardier Canadair CL 600–2B19(RJ)

aircraft.

Note 1: This AD applies to each engine

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

engines that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any engine from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent critical life-limited rotating

engine part failure, which could result in an

uncontained engine failure and damage to

the airplane, accomplish the following:

Inspections

(a) Within the next 30 days after the

effective date of this AD, revise the CF34

Engine Maintenance Program, Chapter 5–21–

00, of the GE CF34 Series Turbofan Engine

Manual, SEI–756. For air carrier operations,

revise the approved continuous

airworthiness maintenance program, by

adding the following:

‘‘9. CF34–3A1 and CF34–3B1 Engine

Maintenance Program—Mandatory

Inspection Requirements.

(A) This procedure is used to identify

specific piece-parts that require mandatory

inspections that must be accomplished at

each piece-part exposure using the applicable

Chapters referenced in Table 804 for the

inspection requirements. The inspection

requirements listed in Table 804 are not

required for any piece-part exposure

resulting when the engine remains on-wing

while performing maintenance practice,

special procedure Number 41 listed in SEI–

756, chapter 72–00–00.

(B) Piece-part exposure is defined as

follows: Note: Fan disk piece-part includes

the fan disk with the 56 fan pin bushings

installed.

(1) For engines that utilize the ‘‘On

Condition’’ maintenance requirements: The

part is considered completely disassembled

to the piece-part level when done in

accordance with the disassembly instructions

in the GEAE authorized overhaul Engine

Manual, and the part has accumulated more

than 100 cycles-in-service since the last

piece-part opportunity inspection, provided

that the part was not damaged or related to

the cause for its removal from the engine.

(2) For engines that utilize the ‘‘Hard

Time’’ maintenance requirements: The part is

considered completely disassembled when

done in accordance with the disassembly

instructions used in the ‘‘Minor

Maintenance’’ or ‘‘Overhaul’’ instructions in

the GEAE engine authorized Engine Manual,

and the part has accumulated more than 100

cycles-in-service since the last piece-part

opportunity inspection, provided that the

part was not damaged or related to the cause

for its removal from the engine.

C. Refer to Table 804 below for the

mandatory inspection requirements.

TABLE 804.—MANDATORY INSPECTION REQUIREMENTS

Part nomenclature Manual/chapter section/subject Mandatory Inspection

Fan Disk (all) ................................... 72–21–00, INSPECTION ............... All areas (FPI); 1 Bores (ECI).2

Stage 1 high pressure turbine

(HPT) Rotor Disk (all).

72–46–00, INSPECTION ............... All areas (FPI); 1 Bores (ECI); 2 Boltholes (ECI); 2 Air Holes (ECI).2

Stage 2 HPT Rotor Disk (all) .......... 72–46–00, INSPECTION ............... All Areas (FPI); 1 Bores (ECI).2

(a) Boltless Rim Configuration ........................................................ Boltholes (FPI); 1 Air Holes (FPI).1

(b) Bolted Rim Configuration ... ........................................................ Boltholes (ECI); 2 Air Holes (ECI).2

HPT Rotor Outer Torque Coupling

(all).

72–46–00, INSPECTION ............... All areas (FPI); 1 Bore (ECI) 2

1FPI = Fluorescent Penetrant Inspection Method.

2ECI = Eddy Current Inspection.‘‘

Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Rules and Regulations 26789

(b) Except as provided in paragraph (c) of

this AD, and notwithstanding the provisions

of section 43.16 of the Federal Aviation

Regulations (14 CFR 43.16), these mandatory

inspections shall be performed only in

accordance with the CF34 Engine

Maintenance Program, Chapter 5–21–00, of

the General Electric Company, CF34 Series

Turbofan Engine Manual, SEI–756.

Alternative Method of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Engine

Certification Office (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector (PMI),

who may add comments and then send it to

the Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the ECO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Continuous Airworthiness Maintenance

Program

(e) FAA-certificated air carriers that have

an approved continuous airworthiness

maintenance program in accordance with the

record keeping requirement of § 121.369(c) of

the Federal Aviation Regulations [14 CFR

121.369(c)] must maintain records of the

mandatory inspections that result from

revising the CF34 Engine Maintenance

Program and the air carrier’s continuous

airworthiness program. Alternately,

certificated air carriers may establish an

approved system of record retention that

provides a method for preservation and

retrieval of the maintenance records that

include the inspections resulting from this

AD, and include the policy and procedures

for implementing this alternate method in the

air carrier’s maintenance manual required by

§ 121.369(c) of the Federal Aviation

Regulations [14 CFR 121.369(c)]; however,

the alternate system must be accepted by the

appropriate PMI and require the maintenance

records be maintained either indefinitely or

until the work is repeated. Records of the

piece-part inspections are not required under

§ 121.380(a)(2)(vi) of the Federal Aviation

Regulations [14 CFR 121.380(a)(2)(vi)]. All

other operators must maintain the records of

mandatory inspections required by the

applicable regulations governing their

operations.

Note 3: The requirements of this AD have

been met when the engine manual changes

are made and air carriers have modified their

continuous airworthiness maintenance plans

to reflect the Engine Maintenance Program

requirements specified in the GE CF34 Series

Turbofan Engine Manual.

This amendment becomes effective on May

30, 2001.

Issued in Burlington, Massachusetts, on

May 7, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–12005 Filed 5–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF THE TREASURY

Bureau of Alcohol, Tobacco and

Firearms

27 CFR Part 9

[T.D. ATF–453 ; RE: Notice No. 905]

RIN 1512–AA07

Long Island Viticultural Area (2000R–

219P)

AGENCY: Bureau of Alcohol, Tobacco

and Firearms (ATF), Treasury.

ACTION: Final Rule, Treasury decision.

SUMMARY: This final rule establishes a

viticultural area to be known as ‘‘Long

Island,’’ located in Nassau and Suffolk

counties, New York. This action is the

result of a petition filed by Richard

Olsen-Harbich on behalf of Raphael

Winery, the Petrocelli Family, and

Karen Meredith of Broadfields

Vineyards.

The establishment of viticultural areas

and the subsequent use of viticultural

area names as appellations of origin in

wine labeling and advertising allow

wineries to designate the specific areas

where the grapes used to make the wine

were grown. This enables consumers to

better identify the wines they may

purchase.

EFFECTIVE DATE: July 16, 2001.

FOR FURTHER INFORMATION CONTACT: Lisa

M. Gesser, Regulations Division, Bureau

of Alcohol, Tobacco and Firearms, 650

Massachusetts Avenue, NW.,

Washington, DC 20226 (202–927–9347).

SUPPLEMENTARY INFORMATION:

1. Background on Viticultural Areas

What Is ATF’s Authority To Establish a

Viticultural Area?

ATF published Treasury Decision

ATF–53 (43 FR 37672, 54624) on

August 23, 1978. This decision revised

the regulations in 27 CFR part 4,

Labeling and Advertising of Wine, to

allow the establishment of definitive

viticultural areas. The regulations allow

the name of an approved viticultural

area to be used as an appellation of

origin in the labeling and advertising of

wine.

On October 2, 1979, ATF published

Treasury Decision ATF–60 (44 FR

56692), which added a new part 9 to 27

CFR, American Viticultural Areas, for

providing the listing of approved

American viticultural areas, the names

of which may be used as appellations of

origin.

ATF does not wish to give the

impression by approving the Long

Island viticultural area that it is

approving or endorsing the quality of

wine from this area. ATF is approving

this area as being distinct from

surrounding areas, not better than other

areas. By approving this area, ATF will

allow wine producers to claim a

distinction on labels and advertisements

as to origin of the grapes. Any

commercial advantage gained can only

come from consumer acceptance of

wines from Long Island.

What Is the Definition of an American

Viticultural Area?

27 CFR 4.25a(e)(1), defines an

American viticultural area as a

delimited grape-growing region

distinguishable by geographical

features. Viticultural features such as

soil, climate, elevation, topography, etc.,

distinguish it from surrounding areas.

What Is Required To Establish a

Viticultural Area?

Any interested person may petition

ATF to establish a grape-growing region

as a viticultural area. The petition

should include:

• Evidence that the name of the

proposed viticultural area is locally

and/or nationally known as referring to

the area specified in the petition;

• Historical or current evidence that

the boundaries of the viticultural area

are as specified in the petition;

• Evidence relating to the

geographical features (climate, soil,

elevation, physical features, etc.) which

distinguish the viticultural features of

the proposed area from surrounding

areas;

• A description of the specific

boundaries of the viticultural area,

based on features which can be found

on United States Geological Survey

(U.S.G.S.) maps of the largest applicable

scale; and

• A copy of the appropriate U.S.G.S.

map(s) with the boundaries prominently

marked.

2. Long Island Petition

ATF received a petition from Richard

Olsen-Harbich on behalf of Raphael

Winery, the Petrocelli Family, and

Karen Meredith of Broadfields

Vineyards, proposing to establish a

viticultural area in Nassau and Suffolk

counties, New York, to be known as

‘‘Long Island.’’ This viticultural area