Federal Register / Vol. 62, No. 235 / Monday, December 8, 1997 / Rules and Regulations 64513

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Robinson Helicopter

Company, 2901 Airport Drive, Torrance,

California 90505, telephone (310) 539–0508;

fax (310) 539–5198. Copies may be inspected

at the FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on

January 12, 1998.

Issued in Fort Worth, Texas, on November

25, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–31677 Filed 12–5–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–21–AD; Amendment

39–10232; AD 97–25–08]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CJ610 Series

Turbojet and CF700 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) CJ610 series turbojet and CF700

series turbofan engines. This action

requires removal from service of

possibly defective turbine torque rings

and compressor drive shafts which may

have been manufactured from

contaminated material; and replacement

with serviceable parts. This amendment

is prompted by a report of a cooling

plate removed from a GE CT58 series

engine that was found to have an ironrich inclusion that came from a

contaminated heat lot. Parts on GE

CJ610 series and CF700 series engines

which were manufactured from the

same and similar heat lots may also be

contaminated. The actions specified in

this AD are intended to prevent turbine

torque ring or compressor drive shaft

failure due to a manufacturing defect,

which could result in an uncontained

engine failure.

DATES: Effective January 2, 1998. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of January 2, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

February 6, 1998.

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–21–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 GE

Aircraft Engines, 1000 Western Ave.,

Lynn, MA 01910; telephone (781) 594–

3140, fax (781) 594–4805. 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:

Barbara Caufield, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7146,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration

received a report that certain turbine

torque rings and compressor drive shafts

installed on General Electric Company

(GE) CJ610 series turbojet and CF700

series turbofan engines were forged with

a contaminated alloy that could reduce

the life of the part. The FAA has

determined that certain heat lots of

A286 material were produced with ironrich inclusions during the vendor’s

normal Vacuum Induction Melt (VIM)

process. The manufacturer discovered a

cooling plate removed from a GE CT58

series turboprop engine had been

manufactured from this heat lot and was

found with an inclusion. This heat lot

was also used to manufacture turbine

torque rings and compressor drive shafts

on GE CJ610 series turbojet and CF700

series turbofan engines. This condition,

if not corrected, could result in turbine

torque ring or compressor drive shaft

failure due to a manufacturing defect,

which could result in an uncontained

engine failure.

The FAA has reviewed and approved

the technical contents of GE CF700

Service Bulletin (SB) No. A72–155,

dated May 22, 1997, and GE CJ610 SB

No. A72–147, dated May 22, 1997, that

describes procedures for removing

affected turbine torque rings and

compressor drive shafts from service,

and replacing 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 an uncontained engine failure

and damage to the aircraft. This AD

requires removing affected turbine

torque rings and compressor drive shafts

from service, and replacing with

serviceable parts. 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
64514 Federal Register / Vol. 62, No. 235 / Monday, December 8, 1997 / Rules and Regulations

Docket Number 97–ANE–21–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:

97–25–08 General Electric Company:

Amendment 39–10232. Docket 97–ANE–

21–AD.

Applicability: General Electric Company

(GE) CJ610 series turbojet and CF700 series

turbofan engines, with turbine torque rings

and compressor drive shafts identified in GE

CF700 Service Bulletin (SB) No. A72–155,

dated May 22, 1997, and GE CJ610 SB No.

A72–147, dated May 22, 1997. These engines

are installed on but not limited to the

following aircraft: Learjet 20 series, Israel

Aircraft Industries Westwind series, Hansa

Jet, Aero Commander Jet Commander,

Dassault Falcon 20 series, Sabreliner 265

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

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 (d)

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 turbine torque ring or

compressor drive shaft failure due to a

manufacturing defect, which could result in

an uncontained engine failure, accomplish

the following:

(a) For GE CF700 series turbofan engines,

accomplish the following in accordance with

GE CF700 SB No. A72–155, dated May 22,

1997:

(1) Remove from service affected turbine

torque rings, listed by serial number (S/N) in

paragraph 1. A.(3a) of GE CF700 SB No. A72–

155, dated May 22, 1997, and replace with

serviceable parts, within 50 hours time in

service (TIS), or 60 days after the effective

date of this AD, whichever occurs first.

(2) Remove from service affected turbine

torque rings and compressor drive shafts,

listed by S/N in GE paragraph 1.A.(3b) of GE

CF700 SB No. A72–155, dated May 22, 1997,

and replace with serviceable parts, within

300 hours TIS, or 12 months after the

effective date of this AD, whichever occurs

first.

(b) For GE CJ610 series turbojet engines,

accomplish the following in accordance with

GE CJ610 SB No. A72–147, dated May 22,

1997:

(1) Remove from service affected turbine

torque rings, listed by S/N in paragraph

1.A.(3a) of GE CJ610 SB No. A72–147, dated

May 22, 1997, and replace with serviceable

parts, within 50 hours TIS, or 60 days after

the effective date of this AD, whichever

occurs first.

(2) Remove from service affected turbine

torque rings and compressor drive shafts,

listed by S/N in paragraph 1.A.(3b) of GE

CJ610 SB No. A72–147, dated May 22, 1997,

and replace with serviceable parts, within

300 hours TIS, or 12 months after the

effective date of this AD, whichever occurs

first.

(c) After the effective date of this AD,

installation of uninstalled affected parts

identified by S/N in the SBs referenced in

paragraphs (a) and (b) of this AD is

prohibited.

(d) 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.

(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 GE

service documents:

Document No. Pages Date

CF700 SB No. A72–155 1–9 May 22,

1997.

Total Pages: 9.

CJ610 SB No. A72–147 1–9 May 22,

1997.

Total Pages: 9.

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 GE Aircraft Engines,

1000 Western Ave., Lynn, MA 01910;

telephone (781) 594–3140, fax (781)

594–4805. 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 January 2, 1998.

Issued in Burlington, Massachusetts, on

November 26, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–31862 Filed 12–5–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–04; Amendment 39–

10234; AD 97–25–10]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT9D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.