Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16477

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(e) 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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following R–R

SBs:

Document No. Pages Revision Date

RB.211–72–B482 ................................................................................................................ 1 3 ....................... September 27, 1996.

2 2 ....................... March 11, 1996.

3 3 ....................... September 27, 1996.

4 2 ....................... March 11, 1996.

5 3 ....................... September 27, 1996.

6 2 ....................... March 11, 1996.

7–8 3 ....................... September 27, 1996.

9 2 ....................... March 11, 1996.

Total Pages: 9.

RB.211–72–9764 ................................................................................................................. 1 2 ....................... November 10, 1995.

2 Original ............. August 20, 1993.

3 2 ....................... November 10, 1995.

4–6 1 ....................... August 25, 1995.

7–30 Original ............. August 20, 1993.

Supplement ......................................................................................................................... 1 Original ............. August 20, 1993.

Total Pages: 31.

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 Rolls-Royce North America, Inc., 2001

South Tibbs Ave., Indianapolis, IN 46241;

telephone (317) 230–3995, fax (317) 230–

4743. Copies may be inspected at the FAA,

New England Region, Office of the Assistant

Chief Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of the

Federal Register, 800 North Capitol Street

NW., suite 700, Washington, DC.

(g) This amendment becomes effective on

June 6, 1997.

Issued in Burlington, Massachusetts, on

March 26, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–8474 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–43; Amendment 39–

9977; AD 97–01–04]

RIN 2120–AA64

Airworthiness Directives; Textron

Lycoming and Superior Air Parts, Inc.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule, request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

97–01–04 that was sent previously to all

known U.S. owners and operators of

certain Textron Lycoming TIO–540,

LTIO–540, and IO–540 series

reciprocating engines with certain

Superior Air Parts, Inc. Parts

Manufacture Approval (PMA)

replacement cylinder assemblies

installed by individual letters. This AD

requires removal from service of

affected cylinder assemblies for higher

time cylinder assemblies and

replacement with serviceable parts, and

initial and repetitive dye penetrant

inspections for mid-time cylinder

assemblies, or replacement with

serviceable parts. This amendment is

prompted by a report of an inflight

engine failure of a Textron Lycoming

TIO–540 reciprocating engine with

affected Superior Air Parts, Inc. PMA

cylinder assemblies installed. The

actions specified by this AD are

intended to prevent cylinder head

separation, inflight loss of power,

possible engine failure, and fire.

DATES: Effective April 22, 1997 to all

persons except those persons to whom

it was made immediately effective by

priority letter AD 97–01–04, issued on

December 27, 1996, which contained

the requirements of this amendment.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 22,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

June 6, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–ANE–43, 12 New England Executive

Park, Burlington, MA 01803–5299.

The applicable service information

may be obtained from Superior Air

Parts, Inc., 14280 Gillis Road, Dallas, TX

75244–3792; telephone (800) 400–5949,

fax (972) 702–8723. This information

may be examined at the FAA, New

England Region, Office of the Assistant

Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at

the Office of the Federal Register, 800

North Capitol Street, NW., Suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: M.

Monica Merritt, Aerospace Engineer,

Special Certification Office, FAA,

Rotorcraft Directorate, 2601 Meacham

Blvd., Ft. Worth, TX 76137–4298;

telephone (817) 222–5196, fax (817)

222–5136.

SUPPLEMENTARY INFORMATION: On

December 27, 1996, the Federal

Aviation Administration (FAA) issued

priority letter airworthiness directive

(AD) 97–01–04, applicable to Textron

Lycoming Models TIO–540–A2C, –J2B,

–F2BD, –J2BD, –N2BD, –R2AD, –S1AD,

and LTIO–540–J2B, –F2BD, –J2BD,

N2BD, –R2AD, and IO–540–M1B5D

reciprocating engines, with Superior Air

Parts, Inc. Parts Manufacture Approval

(PMA) part number SL54000–A1, –A2,

–A2P, –A20P, and A21P series

replacement cylinder assemblies

installed, with serial numbers 001

through 650. That action was prompted

by a report from the Australian Civil

Aviation Authority (CAA) of a New

Piper Company Model PA31–350

aircraft, with a Textron Lycoming TIO–

540 engine installed, that suffered an

inflight engine failure. An examination
16478 Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations

of the engine revealed that a Superior

Air Parts, Inc. PMA part numbers

SL54000 series replacement cylinder

assembly experienced a cylinder head

separation. A soap leak check of the

other 5 cylinders detected bubbles in 2

cylinders indicating a crack. Superior

Air Parts has reported 12 fractured

cylinders from the field. The cause of

the cylinder head fractures and

separations appears to be that the design

of the PMA cylinder wall thickness is

too thin. This condition, if not

corrected, could result in cylinder head

separation, inflight loss of power,

possible engine failure, and fire.

The FAA has reviewed and approved

the technical contents of Superior Air

Parts, Inc. Mandatory Service Bulletin

(MSB) No. 96–002, Revision A, dated

December 17, 1996, that describes

procedures for dye penetrant

inspections of cylinder assemblies for

cracking.

Since the unsafe condition described

is likely to exist or develop on other

engines of the same type design, the

FAA issued priority letter AD 97–01–04

to prevent cylinder head separation,

inflight loss of power, possible engine

failure, and fire. The AD requires

removal of cylinders from engines with

300 or more hours Time in Service (TIS)

since installation of the affected

cylinder assemblies on the effective date

of this AD within 5 hours TIS after the

effective date of this AD, and

replacement with serviceable parts. For

engines with 245 hours or more TIS

since installation of the affected

cylinder assemblies on the effective date

of this AD, this AD requires an initial

dye penetrant inspection within 5 hours

TIS after the effective date of this AD,

followed by repetitive dye penetrant

inspections at intervals not to exceed 25

hours TIS until reaching the 300 hours

TIS limit, upon which the cylinder

assemblies must be removed from

service. Instead of the dye penetrant

inspections, operators may optionally

remove affected cylinder assemblies and

replace with serviceable parts. Cylinder

assemblies with less than 245 hours TIS

since installation of the affected

cylinder assemblies on the effective date

of this AD must begin the dye penetrant

inspections upon reaching 250 hours

TIS since installation of the affected

cylinder assemblies. The actions are

required to be accomplished in

accordance with the MSB described

previously.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

letters issued on December 27, 1996, to

all known U.S. owners and operators of

certain Textron Lycoming TIO–540,

LTIO–540, and IO–540 series

reciprocating engines with certain

Superior Air Parts, Inc. PMA

replacement cylinder assemblies

installed. These conditions still exist,

and the AD is hereby published in the

Federal Register as an amendment to

Section 39.13 of part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

make it effective to all persons.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–ANE–43.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects 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. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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, Incorporation by reference,

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

adding the following new airworthiness

directive:

97–01–04 Textron Lycoming and Superior

Air Parts, Inc.: Amendment 39–9977.

Docket 96–ANE–43.

Applicability: Textron Lycoming Models

TIO–540–A2C, –F2BD, –J2B, –J2BD, –N2BD,

–R2AD, –S1AD, and LTIO–540–J2B, –F2BD,

–J2BD, N2BD, –R2AD, and IO–540–M1B5D

reciprocating engines, with Superior Air

Parts, Inc. Parts Manufacture Approval

(PMA) part numbers SL54000–A1, –A2,

–A2P, –A20P, and A21P replacement

cylinder assemblies installed, with serial

numbers 001 through 650. These engines are

installed on but not limited to the following

aircraft: Bellanca DW–1 (Eagle), The New

Piper Aircraft Co. PA–31 and PA–32 series,

Riley Aircraft Cessna 310 conversion, and

Twin Commander Aircraft Corp. 700 series.

Note 1: This airworthiness directive (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
Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16479

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

request approval for an alternative method of

compliance in accordance with paragraph (e)

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 prevent cylinder head separation,

inflight loss of power, possible engine failure,

and fire, accomplish the following:

(a) Within 5 hours Time in Service (TIS)

after the effective date of this AD, for engines

with 300 or more hours TIS since installation

of the affected cylinder assemblies on the

effective date of this AD, remove from service

affected cylinder assemblies and replace with

serviceable parts.

(b) Within 5 hours TIS after the effective

date of this AD, for engines with 245 hours

but less than 300 hours TIS since installation

of the affected cylinder assemblies on the

effective date of this AD, accomplish the

following:

(1) Perform an initial dye penetrant

inspection for cracks in accordance with

Superior Air Parts, Inc. Mandatory Service

Bulletin (MSB) No. 96–002, Revision A,

dated December 17, 1996, or remove and

replace with a serviceable part.

(2) Thereafter, perform repetitive dye

penetrant inspections for cracks at intervals

not to exceed 25 hours TIS since last

inspection, in accordance with Superior Air

Parts, Inc. MSB No. 96–002, Revision A,

dated December 17, 1996, or remove and

replace with a serviceable part.

(3) Prior to further flight, remove from

service cylinder assemblies found cracked

during dye penetrant inspections and replace

with serviceable parts.

(4) Upon accumulating 300 hours TIS since

installation of the affected cylinder

assemblies, prior to further flight remove

from service affected cylinder assemblies and

replace with serviceable parts.

(c) For engines with less than 245 hours

TIS since installation of the affected cylinder

assemblies on the effective date of this AD,

accomplish the following:

(1) Upon accumulating 250 hours TIS since

installation of the affected cylinder

assemblies, perform an initial dye penetrant

inspection for cracks in accordance with

Superior Air Parts, Inc. MSB No. 96–002,

Revision A, dated December 17 , 1996, or

remove and replace with a serviceable part.

(2) Thereafter, perform repetitive dye

penetrant inspections for cracks at intervals

not to exceed 25 hours TIS since last

inspection, in accordance with Superior Air

Parts, Inc. MSB No. 96–002, Revision A,

dated December 17 , 1996, or remove and

replace with a serviceable part.

(3) Prior to further flight, remove from

service cracked cylinder assemblies and

replace with serviceable parts.

(4) Upon accumulating 300 hours TIS since

installation of the affected cylinder

assemblies, prior to further flight remove

from service affected cylinder assemblies and

replace with serviceable parts.

(d) For the purpose of this AD, a

serviceable part is defined as a cylinder

assembly other than a Superior Air Parts, Inc.

PMA part number SL54000 –A1, –A2, –A2P,

–A20P, and A21P replacement cylinder

assembly, with serial numbers 001 through

650.

(e) 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, Special

Certification Office. The request should be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Special Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Special

Certification Office.

(f) Special flight permits in accordance

with Sections 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) may not be issued.

(g) The actions required by this AD shall

be accomplished in accordance with the

following Superior Air Parts, Inc. MSB:

Document No. Pages Revision Date

96–002 ............................................................................................................................................... 1–4 A December 17, 1996.

Total pages 4.

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 Superior Air Parts, Inc., 14280 Gillis

Road, Dallas, TX 75244–3792; telephone

(800) 400–5949, fax (972) 702–8723. Copies

may be inspected at the FAA, New England

Region, Office of the Assistant Chief Counsel,

12 New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(h) This amendment becomes effective

April 22, 1997, to all persons except those

persons to whom it was made immediately

effective by priority letter AD 97–01–04,

issued December 27, 1996, which contained

the requirements of this amendment.

Issued in Burlington, Massachusetts, on

March 26, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–8476 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF THE TREASURY

Bureau of Alcohol, Tobacco and

Firearms

27 CFR Part 4

[T.D. ATF–388; Ref. Notice Nos. 581, 749

and 793]

RIN 1512–AB08

Gamay Beaujolais Wine Designation

(92F–042P)

AGENCY: Bureau of Alcohol, Tobacco

and Firearms (ATF), Department of the

Treasury.

ACTION: Treasury Decision, Final Rule.

SUMMARY: This final rule amends the

wine labeling regulations to allow use of

the term ‘‘Gamay Beaujolais’’ on

American wine labels for a period of 10

years. From the time this final rule takes

effect until the end of the phase-out

period, a wine which derives not less

than 75 percent of its volume from Pinot

noir grapes, Valdiguie ́ (‘‘Napa Gamay’’)

grapes, or a combination of both

varieties, may use ‘‘Gamay Beaujolais’’

as a type designation of varietal

significance. However, from January 1,

1999, until the end of the phase-out

period, brand labels using the

designation ‘‘Gamay Beaujolais’’ must

also bear in direct conjunction

therewith the varietal names Pinot noir

and/or Valdiguie ́, along with the

following statement on the brand or

back label: ‘‘Gamay Beaujolais is made

from at least 75 percent Pinot noir and/

or Valdiguie ́ grapes.’’ After the

expiration of the phase-out period, the

term ‘‘Gamay Beaujolais’’ will no longer

be recognized as a designation for

American wines.

EFFECTIVE DATE: This final rule is

effective May 7, 1997.

FOR FURTHER INFORMATION CONTACT:

Thomas B. Busey, Wine, Beer and

Spirits Regulation Branch, Bureau of

Alcohol, Tobacco and Firearms, 650

Massachusetts Avenue, NW,

Washington, DC 20226, Telephone:

(202) 927–8230.