58892 Federal Register / Vol. 62, No. 211 / Friday, October 31, 1997 / Rules and Regulations

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, 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

removing amendment 39–9030 (59 FR

48563, eptember 22, 1994), and by

adding a new airworthiness directive

(AD), amendment 39–10185 to read as

follows:

97–22–13 Airbus Industrie: Amendment

39–10185. Docket 96-NM–252-AD.

Supersedes AD 94–20–02, Amendment 39–

9030.

Applicability: Model A320 and A321 series

airplanes, on which Airbus Modification

24612 or Airbus Service Bulletin A320–31–

1080 has not been accomplished; certificated

in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 prevent severely reduced controllability

of the airplane during approach, accomplish

the following:

(a) At the applicable time specified in

either paragraph (a)(1) or (a)(2) of this AD,

revise the Limitations Section of the FAAapproved Airplane Flight Manual (AFM) to

include the information specified in Airbus

A320/A321 Flight Manual Temporary

Revision 9.99.99/20, dated June 14, 1994.

Note 2: This may be accomplished by

inserting a copy of Airbus A320/A321 Flight

Manual Temporary Revision 9.99.99/20,

dated June 14, 1994, in the AFM. When this

temporary revision has been incorporated in

the general revisions of the AFM, the general

revisions may be inserted in the AFM,

provided the information contained in the

general revisions is identical to that specified

in Temporary Revision 9.99.99/20.

(1) For Model A320 series airplanes: Revise

the AFM within 10 days after October 7, 1994

(the effective date of AD 94–20–02,

amendment 39–9030).

(2) For Model A321 series airplanes: Revise

the AFM within 10 days after the effective

date of this AD.

(b) Within 6 months after the effective date

of this AD, install a new, improved flight

warning computer (FWC) in accordance with

Airbus Service Bulletin A320–31–1080,

Revision 01, dated July 12, 1996 or Revision

2, dated October 24, 1996. Prior to further

flight after accomplishing this installation,

remove the AFM revision required by

paragraphs (a) of this AD.

(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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Operations

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

(e) The installation shall be done in

accordance with Airbus Service Bulletin

A320–31–1080, Revision 01, dated July 12,

1996, or Airbus Service Bulletin A320–31–

1080, Revision 02, dated October 24, 1996.

Airbus Service Bulletin A320–31–1080,

Revision 01, dated July 12, 1996, contains the

following list of effective pages:

Page number

Revision

level

shown on

page

Date shown on

page

1, 3, 4, 6–8 ... 1 .............. July 12, 1996.

2, 5, 9–13 ..... Original .... Jan. 4, 1995.

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.

The revision to the AFM shall be done in

accordance with Airbus A320/A321 Flight

Manual Temporary Revision 9.99.99/20,

dated June 14, 1994. The incorporation by

reference of this document was approved

previously by the Director of the Federal

Register as of October 7, 1994 (59 FR 48563,

September 22, 1994).

Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in French airworthiness directive 96–079–

079(B), dated April 10, 1996.

(f) This amendment becomes effective on

December 5, 1997.

Issued in Renton, Washington, on October

23, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–28615 Filed 10–30–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–52–AD; Amendment

39–10186; AD 97–22–14]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF6–50 and –80C2

Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to General Electric Company

(GE) CF6–50 and –80C2 series turbofan

engines. This action requires removal

from service of defective high pressure

compressor rotor (HPCR) stage 3–9

spools, and replacement with

serviceable parts. This amendment is

prompted by a report of an uncontained

failure of an HPCR stage 3–9 spool

installed on a GE model CF6–80C2

turbofan engine. The actions specified

in this AD are intended to prevent

failure of the HPCR stage 3–9 spool,

which can result in an uncontained

engine failure and damage to the

aircraft.

DATES: Effective November 17, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

17, 1997.
Federal Register / Vol. 62, No. 211 / Friday, October 31, 1997 / Rules and Regulations 58893

Comments for inclusion in the Rules

Docket must be received on or before

December 30, 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.

97–ANE–52–AD, 12 New England

Executive Park, Burlington, MA 01803–

5299. Comments may also be sent via

the Internet using the following address:

‘‘9-ad-engineprop@faa.dot.gov’’.

Comments sent via the Internet must

contain the docket number in the

subject line.

The service information referenced in

this AD may be obtained from General

Electric Company Technical Services,

Attention: Leader for distribution/

microfilm, 10525 Chester Road,

Cincinnati, OH 45215; telephone (513)

672–8400 Ext. 114, fax (513) 672–8422.

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:

William Ricci, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7142,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received a report of an uncontained

failure of a high pressure compressor

rotor (HPCR) stage 3–9 spool installed

on a GE model CF6–80C2 turbofan

engine. The investigation revealed that

a crack initiated in the HPCR stage 3–

9 spool and propagated in low cycle

fatigue to rapid fracture and disk

rupture. The crack initiated from an

oxygen stabilized alpha region located

in the area of the stage 3 dovetail blade

slot and propagated radially inward to

the disk bore. The FAA has determined

that HPCR stage 3–9 spools produced

from the same melt of material may also

be affected. The investigation is

continuing and pending the results of

the investigation the requirements of

this AD may be changed. This

condition, if not corrected, could result

in failure of the HPCR stage 3–9 spool,

which can result in an uncontained

engine failure and damage to the

aircraft.

The FAA has reviewed and approved

the technical contents of GE CF6–50

Service Bulletin (SB) 72–A1139, dated

October 17, 1997, and GE CF6–80C2 SB

72–A906, dated October 17, 1997, that

describe procedures for removal from

service of defective HPCR 3–9 spools,

and replacement with serviceable parts.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

prevent failure of the HPCR 3–9 spool.

This AD requires, within 30 days after

the effective date of this AD, removal

from service of defective HPCR 3–9

spools, and replacement with

serviceable parts. This calendar enddate was determined based upon risk

analysis. The actions are required to be

accomplished in accordance with the

SBs described previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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 97–ANE–52–AD.’’ 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:

97–22–14 General Electric Company:

Amendment 39–10186. Docket 97–ANE–

52–AD.

Applicability: General Electric Company

(GE) CF6–50 and –80C2 series turbofan

engine, installed on but not limited to Boeing

767 and 747 series, McDonnell Douglas DC–

10 and MD–11, and Airbus Industries A300

and A310 series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine identified in the

preceding applicability provision, regardless
58894 Federal Register / Vol. 62, No. 211 / Friday, October 31, 1997 / Rules and Regulations

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

request approval for an alternative method of

compliance in accordance with paragraph (b)

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 failure of the high pressure

compressor rotor (HPCR) 3–9 spool, which

can result in an uncontained engine failure

and damage to the aircraft, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, remove from service HPCR 3–9

spools identified by serial number in the

applicable service bulletin (SB), and replace

with serviceable parts, as follows:

(1) For GE CF6–50 series turbofan engines,

remove and replace in accordance with GE

CF6–50 SB 72–A1139, dated October 17,

1997.

(2) For GE CF6–80C series turbofan

engines, remove and replace in accordance

with GE CF6–80C2 SB 72–A906, dated

October 17, 1997.

(b) 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. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

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.

(c) 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.

(d) The actions required by this AD shall

be done in accordance with the following GE

SBs:

Document No. Pages Date

CF6–50 SB 72–

A1139.

1–7 Oct. 17, 1997.

Total pages: 7.

CF6–80C2 SB

72–A906.

1–7 Oct. 17, 1997.

Total pages: 7.

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 General Electric Company Technical

Services, Attention: Leader for distribution/

microfilm, 10525 Chester Road, Cincinnati,

OH 45215; telephone (513) 672–8400 Ext.

114, fax (513) 672–8422. 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.

(e) This amendment becomes effective on

November 17, 1997.

Issued in Burlington, Massachusetts, on

October 22, 1997.

James C. Jones,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–28742 Filed 10–30–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–11–AD; Amendment 39–

10187; AD 97–22–16]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Models 1900, 1900C,

and 1900D Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Models 1900,

1900C, and 1900D airplanes (formerly

referred to as Beech Models 1900,

1900C, and 1900D airplanes). This AD

requires fabricating and installing a

placard that restricts the use of the

forward and aft vent blower assemblies

to only the ‘‘OFF’’ or ‘‘HIGH’’ position.

This AD also requires incorporating a

modification that would replace the

bearings on the vent blower assemblies

with improved design bearings, and

provide thermal protection for the vent

blowers, as applicable. Incorporating the

modification will eliminate the need for

the placard. The AD results from reports

of vent blower assembly bearings

seizing and locking the blower motor on

several of the affected airplanes. The

actions specified by this AD are

intended to prevent the vent blower

assembly bearings from seizing, which

could result in smoke emanating from

the insulating material covering the

electrical wiring and entering the

airplane cabin.

DATES: Effective December 5, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

5, 1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

the Raytheon Aircraft Company, P.O.

Box 85, Wichita, Kansas 67201–0085.

This information may also be examined

at the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–11–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Harvey Nero, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4137; facsimile

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Raytheon Models 1900,

1900C, and 1900D airplanes was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on May 29, 1997 (62 FR 29086). The

NPRM proposed to require (1)

fabricating and installing a placard that

restricts the use of the vent blower

assemblies; and (2) incorporating a

modification that would replace the

bearings in the vent blower assemblies

with improved design bearings, and

provide thermal protection for the vent

blowers, as applicable. Incorporating the

modification would eliminate the need

for the placard. Accomplishment of the

proposed modification as specified in

the NPRM would be in accordance with

the Update Procedures for the

Electromech Technologies EM630

Blower (Raytheon P/N 114–380028–1

for Installation of Kit P/N’s 630–201–1

and 630–201–2), dated December 9,

1996; and Advanced Industries, Inc.

Installation Procedure for the Resistor

Wiring Harness Kit on the BC80A–1

Blower, dated October 9, 1996. Both of

these documents are referenced in

Raytheon Service Bulletin No. 2721,

Issued: January 1997.

The NPRM resulted from vent blower

assembly bearings seizing and locking

the blower motor on several of the

affected airplanes.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the