Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations 32535

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 a new airworthiness directive to

read as follows:

2001–12–06 General Electric Company:

Amendment 39–12261. Docket No.

2000–NE–22–AD.

Applicability

This airworthiness directive (AD) is

applicable to CF34–1A, –3A, –3A1, –3A2,

–3B, and –3B1 turbofan engines with No. 5

bearing rotating air seal, part number (P/N)

4019T60G01 installed. These engines are

installed on but not limited to Bombardier

Inc. (Canadair) Model CL–600–2A12, Model

CL–600–2B16, and Model CL–600–2B19,

airplanes.

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 request approval for an

alternative method of compliance in

accordance with paragraph (f) 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

Compliance with this AD is required as

indicated, unless already done.

To prevent No.5 bearing rotating air seal

failures and possible uncontained engine

failures, do the following:

Magnetic Chip Detector Indicator Check

(a) Check magnetic chip detector indicators

in accordance with the following Table 1:

TABLE 1.—INITIAL AND REPETITIVE CHECKS

Engine model Initial check within: Then within every:

(1) CF34–3A1, –3B1, and –3B ......... 30 flight hours or 3 calendar days, whichever is

greater, from effective date of this AD.

30 flight hours time-since-last-inspected (TSLI) or 3

calendar days TSLI, whichever is greater.

(2) CF34–1A, –3A, and –3A2 ........... 100 flight hours, from the effective date of this AD .. 100 flight hours TSLI.

Chip Detector Indicator Check,

Authorization

(b) For CF34–3A1, –3B, and –3B1 turbofan

engine models, notwithstanding section 43.3

of the Federal Aviation Regulations (14 CFR

43.3), the checks required by paragraph (a) of

this AD, may be performed by an aircrew

member holding at least a private pilot

certificate. The operator of the airplane must

record completion of the checks in the

airplane records to show compliance with

this AD, in accordance with sections 43.9

and 91.417(a)(2)(v) of the Federal Aviation

Regulations 14 CFR part 43.9 and 14 CFR

part 91.417(a)(2)(v). The records must be

maintained as required by the applicable

Federal Aviation Regulation.

Detection of Chips

(c) If a chip detection is indicated, remove

the chip detector and disposition the chip,

and the engine, using the engine

maintenance manual procedures.

Replacement of Air Seal

(d) Remove No.5 bearing rotating air seal

P/N 4019T60G01, and replace with air seal

P/N 4019T60G03, in accordance with the

following Table 2:

TABLE 2.—COMPLIANCE TIMES FOR REPLACEMENT OF AIR SEAL

Engine model Replace at

(1) CF34–3A1, –3B1, and –3B ......................... Next shop visit when HPT is exposed, but do not exceed 15,000 cycles-in-service from the effective date of this AD.

(2) CF34–1A, –3A, and –3A2 ........................... Next 3000-hour hot section inspection or at next 6,000-hour overhaul, whichever occurs first,

but not to exceed 3,000 hours time-in-service from the effective date of this AD.

Mandatory Terminating Action

(e) Replacement of air seal P/N

4019T60G01 with air seal P/N 4019T60G03

constitutes terminating action for the

repetitive inspection requirements specified

in paragraph (a) of this AD.

Alternative Methods of Compliance

(f) 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 request through an appropriate

Federal Aviation Administration (FAA)

Principal Maintenance Inspector, 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 airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(g) Special flight permits may be issued in

accordance §§ 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.

Effective Date of This AD

(h) This amendment becomes effective on

July 20, 2001.

Issued in Burlington, Massachusetts, on

June 5, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–14824 Filed 6–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–07–AD; Amendment

39–12262; AD 2001–12–07]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CT58 Series and

Former Military T58 Series Turboshaft

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

32536 Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations

applicable to certain General Electric

Company (GE) CT58 series and former

military T58 series turboshaft engines.

This action requires the removal from

service of certain fuel flow divider

assemblies, and replacement with

serviceable parts. This amendment is

prompted by reports of large volumes of

fuel leakage from end caps on fuel flow

divider assemblies. The actions

specified in this AD are intended to

prevent fuel flow divider assembly fuel

leakage, which could cause an engine

fire, leading to an in-flight engine

shutdown and forced landing.

DATES: Effective July 2, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

August 14, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2001–NE–

07–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address:‘‘9-aneadcomment@faa.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; Attention: CT58/T58

International Program Manager, Mail

Zone: 564X9; fax: (781) 594–1527,

Internet address:

‘‘frank.federico@ae.ge.com’’. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299 telephone: (781) 238–7148;

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: On

December 7, 2000, the FAA was made

aware of three incidents of fuel leaking

from the temperature control valve

assembly, located on the fuel flow

divider assembly. An investigation by

GE revealed that the vendor of the

temperature control valve assembly end

caps did not accomplish the required

manufacturing process steps following

heat treatment. This has caused the end

caps to be susceptible to intergranular

corrosion which can result in cracking.

This condition, if not corrected, could

cause an engine fire, leading to an inflight engine shutdown and forced

landing.

Manufacturer’s Service Information

The FAA has reviewed and approved

the technical contents of GE Company

Alert Service Bulletin (ASB) CT58 73–

A0080, dated February 13, 2001, that

describes procedures for locating

suspect fuel flow divider assemblies,

part numbers (P/N’s) 4050T82G02 or

4067T04G02, then locating temperature

control assemblies P/N’s 5040T77G02 or

5040T87G02 by affected serial number

prefix, and then replacing fuel flow

divider assemblies with serviceable

parts.

FAA’s Determination of an Unsafe

Condition and Proposed Actions

Since an unsafe condition has been

identified that is likely to exist or

develop on other GE CT58 series

turboshaft engines of the same type

design, this AD is being issued to

prevent fuel flow divider assembly fuel

leakage, which could cause an engine

fire, leading to an in-flight engine

shutdown and forced landing. This AD

requires locating suspect fuel flow

divider assemblies by part number, then

locating affected temperature control

assemblies by part number and serial

number prefix, and then replacing fuel

flow divider assemblies with serviceable

parts.

Immediate Adoption of This AD

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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NE–07–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This final 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 final rule.

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, 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:

Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations 32537

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:

2001–12–07 General Electric Company:

Amendment 39–12262. Docket No.

2001–NE–07–AD.

Applicability

This airworthiness directive (AD) is

applicable to General Electric Company (GE)

CT58–140–1, –140–2, and former military

T58–GE–5, –8F, –10, –100, and –402

turboshaft engines, with fuel flow divider

assemblies part numbers (P/N’s)

4050T82G02, or 5040T77G02 having

temperature control assemblies with serial

numbers (SN’s) with the first two digits of 95,

96, 97, 98, or 99 installed. These engines are

installed on, but not limited to Agusta S.p.A.

AS–6N, Boeing Vertol 107–11, Sikorsky S–61

Series and S–62 Series, and the following

surplus military helicopters that have been

certified in accordance with sections 21.25 or

21.27 of the Federal Aviation Regulations (14

CFR 21.25 or 21.27): Carson S–61L, Firefly

UH–1F, Glacier CH–3E, Quentin HH52A,

Robinson Air Crane CH–3C, CH–3E, HH–3C,

and HH–3E, Sikorsky S–61A, S–61D, S–61E,

S–61V, and S–61V–1, and Siller Helicopters

CH–3A, and SH–3A.

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 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

Compliance with this AD is required as

indicated, unless already done.

To prevent fuel flow divider assembly fuel

leakage, which could cause an engine fire,

leading to an in-flight engine shutdown and

forced landing, do the following within 120

hours time-in-service after the effective date

of this AD:

(a) Locate the temperature control

assembly, which is mounted on the fuel flow

divider assembly and do the following:

(1) Read the temperature control assembly

SN, located on the temperature control

assembly end cap. The end cap can be

identified by a one-inch hex flange and by

being threaded into the fuel flow divider

body.

(2) If the first two digits of the SN are 95,

96, 97, 98, or 99, or if the SN cannot be

determined, replace the entire fuel flow

divider assembly. Further information

regarding SN location on the temperature

control assembly may be found in GE Alert

Service Bulletin CT58 73–A0080, dated

February 13, 2001.

(b) After the effective date of this AD, do

not install any fuel flow divider assembly P/

N 4050T82G02 or 5040T77G02, that has the

first two digits of the temperature control

assembly SN of 95, 96, 97, 98, or 99.

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, 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.

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 aircraft to

a location where the requirements of this AD

can be accomplished.

Effective Date of this AD

(e) This amendment becomes effective on

July 2, 2001.

Issued in Burlington, Massachusetts, on

June 5, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–14823 Filed 6–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ANM–25]

Revision of Class E Airspace, Cody,

WY

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action revises the Cody,

WY, Class E airspace to accommodate

airspace required for the establishment

of a new Area Navigation (RNAV)

Standard Instrument Approach

Procedures (SIAP) to the Yellowstone

Regional Airport, Cody, WY.

EFFECTIVE DATE: 0901 UTC, July 12,

2001.

FOR FURTHER INFORMATION CONTACT:

Brian Durham, ANM–520.7, Federal

Aviation Administration, Docket No.

00–ANM–25, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056;

telephone number: (425) 227–2527.

SUPPLEMENTARY INFORMATION:

History

On February 13, 2001, the FAA

proposed to amend title 14 Code of

Federal Regulations, part 71 (14 CFR

part 71) by revising Class E airspace at

Cody, WY, in order to accommodate a

new RNAV SIAP at Yellowstone

Regional Airport, Cody, WY (66 FR

9988). This amendment provides Class

E5 airspace at Cody, WY, to meet

current criteria standards associated

with the SIAP. Interested parties were

invited to participate in the rulemaking

proceeding by submitting written

comments on the proposal. No

comments were received.

The Rule

This amendment to Title 14 Code of

Federal Regulations, part 71 (14 CFR

part 71) revises Class E airspace at Cody,

WY, in order to accommodate a new

RNAV SIAP to the Yellowstone

Regional Airport, Cody, WY. This

amendment revises Class E5 airspace at

Cody, WY, to meet current criteria

standards associated with the RNAV

SIAP. The FAA establishes Class E

airspace where necessary to contain

aircraft transitioning between the

terminal and en route environments.

This rule is designed to provide for the

safe and efficient use of the navigable

airspace and to promote safe flight

operation sunder Instrument Flight

Rules (IFR) at the Yellowstone Regional

Airport and between the terminal and

en route transition stages.

The area will be depicted on

aeronautical charts for pilot reference.

The coordinates for this airspace docket

are based on North American Datum

83., Class E airspace areas extending

upward from 700 feet or more above the

surface of the earth, are published in

Paragraph 6005, of FAA Order 7400.9H

dated September 1, 2000, and effective

September 16, 2000, which is

incorporated by reference in 14 CFR

71.1. The Class E airspace designation

listed in this document will be

published subsequently in the Order.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore, (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT