Federal Register / Vol. 66, No. 106 / Friday, June 1, 2001 / Rules and Regulations 29689

Authority: 7 U.S.C. 450, 7711, 7712, 7713,

7714, 7751 and 7754; 19 U.S.C. 1306; 21

U.S.C. 111, 114a, 134a, 134b, 134c, 134f, 136,

and 136a; 31 U.S.C. 9701; 42 U.S.C. 4331 and

4332; 7 CFR 2.22, 2.80, and 371.4.

§ 94.1 [Amended]

2. In § 94.1, paragraph (a)(2) is

amended by removing the words

‘‘France,’’, ‘‘Ireland,’’, and ‘‘The

Netherlands,’’.

§ 94.11 [Amended]

3. In § 94.11, paragraph (a) is

amended by removing the words

‘‘France,’’, ‘‘The Netherlands,’’, and

‘‘Republic of Ireland,’’.

Done in Washington, DC, this 25th day of

May 2001.

Craig A. Reed,

Administrator, Animal and Plant Health

Inspection Service.

[FR Doc. 01–13757 Filed 5–31–01; 8:45 am]

BILLING CODE 3410–34–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–18–AD; Amendment

39–12246; AD 2001–11–05]

RIN 2120–AA64

Airworthiness Directives; CFM

International (CFMI) CFM56–2, –2B, –3,

–5B, –5C and –7B 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 CFMI CFM56–2, –2B, –3,

–5B, –5C and –7B series turbofan

engines. This action requires limiting

engines with certain No. 4 bearings to

one on each airplane, replacement of

certain No. 4 bearings, and increased

frequency of inspections for magnetic

particles until the suspect bearing is

replaced. This action is prompted by

reports of two bearing failures in the

fleet since December 2000. The actions

specified in this AD are intended to

prevent bearing failures, which could

cause an engine failure.

DATES: Effective June 11, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

July 31, 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–

18–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.

FOR FURTHER INFORMATION CONTACT:

James Rosa, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7152, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: This

proposal is prompted by reports of two

No. 4 bearing failures on CFMI CFM56–

7B series turbofan engines since

December 2000. Inspections of the failed

bearings indicate marginal metallurgical

structure, most likely due to an uneven

heat treatment process. Both failed

bearings are from a manufacturing lot of

47 parts simultaneously heat-treated.

This condition, if not corrected, could

result in bearing failures, which could

cause an engine failure.

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 CFMI CFM56–2, –2B,

–3, –5B, –5C and –7B series turbofan

engines of the same type design, this AD

is being issued to prevent bearing

failures which could cause an engine

failure.

This AD requires:

• Limiting the number of engines

with a suspect No. 4 bearing installed to

one on each airplane within 300 hours

time-in-service (TIS) after the effective

date of this AD, but no later than July

1, 2001, whichever occurs earlier. AND

• Increasing the frequency of

inspections for magnetic particles until

the suspect bearing is replaced. AND

• Replacing all suspect No. 4 bearings

within 2,000 hours TIS after the

effective date of this AD, but no later

than December 31, 2001, whichever

occurs earlier.

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–18–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

29690 Federal Register / Vol. 66, No. 106 / Friday, June 1, 2001 / Rules and Regulations

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:

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:

2001–11–05 CFM International:

Amendment 39–12246. Docket 2001–

NE–18–AD.

Applicability: This airworthiness directive

(AD) is applicable to CFM International

CFM56–2, –2B, –3, –5B, –5C and –7B series

turbofan engines with a No. 4 bearing, part

number (P/N) 305–355–717–0, that has a

serial number (SN) listed in Table 1 of this

AD installed. These engines are installed on,

but not limited to Airbus Industrie A319,

A320, A321 and A340 series airplanes,

Boeing 737 and KC135 series airplanes, and

McDonnell Douglas DC8 series 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 (h) 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 bearing failures, which could

cause an engine failure, do the following:

Number of Hours Until Number of Engines

Must Be Limited

(a) Limit the number of engines with a

suspect No. 4 bearing that has a SN listed in

the following Table 1 of this AD to one on

each airplane within 300 hours time-inservice (TIS) after the effective date of this

AD, but no later than July 1, 2001, whichever

occurs earlier:

TABLE 1.—CFM56 ENGINES WITH SUSPECT NO. 4 BEARINGS

Part No. Part serial

No.

Engine

model

Engine serial

No.

305–355–717–0 ................................................................................................................................... DB387598–C 2B 714172

305–355–717–0 ................................................................................................................................... DB387670–5 2 692251

305–355–717–0 ................................................................................................................................... DB387608–F 3 725109

305–355–717–0 ................................................................................................................................... DB387612–8 3 720493

305–355–717–0 ................................................................................................................................... DB387614–4 3 721253

305–355–717–0 ................................................................................................................................... DB387625–H 3 720383

305–355–717–0 ................................................................................................................................... DB387647–Y 3 857594

305–355–717–0 ................................................................................................................................... DB387650–6 3 721237

305–355–717–0 ................................................................................................................................... DB387651–5 3 726245

305–355–717–0 ................................................................................................................................... DB387661–K 3 856671

305–355–717–0 ................................................................................................................................... DB387604–K 5B 779783

305–355–717–0 ................................................................................................................................... DB387605–J 5B 779784

305–355–717–0 ................................................................................................................................... DB387603–L 5B 779785

305–355–717–0 ................................................................................................................................... DB387590–5 5B 779786

305–355–717–0 ................................................................................................................................... DB387591–4 5B 779787

305–355–717–0 ................................................................................................................................... DB387634–3 5B 779796

305–355–717–0 ................................................................................................................................... DB387658–D 5B 779798

305–355–717–0 ................................................................................................................................... DB387654–2 5B 779799

305–355–717–0 ................................................................................................................................... DB387683–G 5B 779802

305–355–717–0 ................................................................................................................................... DB387648–W 5B 779803

305–355–717–0 ................................................................................................................................... DB387660–L 5B 779804

305–355–717–0 ................................................................................................................................... DB387606–H 5B 779960

305–355–717–0 ................................................................................................................................... DB387618–O 5B 779961

305–355–717–0 ................................................................................................................................... DB387599–B 5C 741948

305–355–717–0 ................................................................................................................................... DB387609–Y 7B 876395

305–355–717–0 ................................................................................................................................... DB387611–7 7B 876399

305–355–717–0 ................................................................................................................................... DB387615–3 7B 876400

305–355–717–0 ................................................................................................................................... DB387601–N 7B 876401

305–355–717–0 ................................................................................................................................... DB387594–1 7B 876403

305–355–717–0 ................................................................................................................................... DB387592–3 7B 876405

305–355–717–0 ................................................................................................................................... DB387610–8 7B 876406

305–355–717–0 ................................................................................................................................... DB387600–P 7B 876410

305–355–717–0 ................................................................................................................................... DB387649–V 7B 876421

305–355–717–0 ................................................................................................................................... DB387678–C 7B 876423

305–355–717–0 ................................................................................................................................... DB387652–4 7B 876424

305–355–717–0 ................................................................................................................................... DB387659–C 7B 876429

305–355–717–0 ................................................................................................................................... DB387693–1 7B 876431

305–355–717–0 ................................................................................................................................... DB387655–1 7B 876432

305–355–717–0 ................................................................................................................................... DB387684–F 7B 876434

305–355–717–0 ................................................................................................................................... DB387588–V 7B 876727

305–355–717–0 ................................................................................................................................... DB387657–E 7B 876729

305–355–717–0 ................................................................................................................................... DB387653–3 7B 876730

305–355–717–0 ................................................................................................................................... DB387597–D 7B 877404

305–355–717–0 ................................................................................................................................... DB387602–M 7B 877408

Federal Register / Vol. 66, No. 106 / Friday, June 1, 2001 / Rules and Regulations 29691

TABLE 1.—CFM56 ENGINES WITH SUSPECT NO. 4 BEARINGS—Continued

Part No. Part serial

No.

Engine

model

Engine serial

No.

305–355–717–0 ................................................................................................................................... DB387589–U 7B 877427

305–355–717–0 ................................................................................................................................... DB387656–O 7B 875232

305–355–717–0 ................................................................................................................................... DB387671–4 7B 874219

Replacement of Suspect No. 4 Bearings

(b) For engines that have a suspect No. 4

bearing that has a SN listed in Table 1 of this

AD, replace the No. 4 bearing with a

serviceable part within 2,000 hours TIS, after

the effective date of this AD, but no later than

December 31, 2001, whichever occurs earlier.

Installation of Suspect No. 4 Bearings

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

not install any No. 4 bearing that has a SN

listed in Table 1 of this AD.

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

not install any engine that has a No. 4 bearing

with a serial number listed in Table 1 of this

AD.

Initial Inspections for Chip Detector

Indications

(e) For engines that have a suspect No. 4

bearing that has a SN listed in Table 1 of this

AD, inspect for magnetic chip indications

within in the specified times, and if

necessary, disposition as follows:

(1) For CFM56–5B engines, check

electronic magnetic chip detector (EMCD)

visual indicator within 50 to 75 hours TIS

after the effective date of this AD.

(2) For CFM56–5C engine (741948), check

for class 2 Electronic Centralized Aircraft

Monitor (ECAM) message ‘‘MAGNETIC CHIP

DETECTED’’ before further flight.

(3) For CFM56–7B engines equipped with

Debris Monitoring System (DMS) option,

check Flight Management Computer—Master

Control Display Unit (FMC–MCDU) for

message 79–2114 before further flight.

(4) For CFM56–7B engines equipped with

classic magnetic chip detectors (MCD),

inspect aft sump MCD within 50 to 75 hours

TIS after the effective date of this AD.

(5) For CFM56–2, –2B, and –3 engines,

inspect aft sump MCD within 50 to 75 hours

TIS after the effective date of this AD.

(6) If bearing particles are found, remove

engine from service before further flight.

Repetitive Inspections for Chip Detector

Indications

(f) Thereafter, inspect for chip indications

in accordance with the specified time-sincelast-inspection (TSLI), and if necessary,

disposition as follows:

(1) For CFM56–5B engines, check EMCD

visual indicator every 50–75 hours TSLI.

(2) For CFM56–5C engine (741948), check

for class 2 ECAM message ‘‘MAGNETIC CHIP

DETECTED’’ after every flight.

(3) For CFM56–7B engines equipped with

DMS option, check FMC–MCDU for message

79–2114 once per day.

(4) For CFM56–7B engines equipped with

classic MCD, inspect aft sump MCD every

50–75 hours TSLI.

(5) For CFM56–2, –2B, and –3 engines,

inspect aft sump MCD every 50–75 hours

TSLI.

(6) If bearing particles are found, remove

engine from service before further flight.

Terminating Action

(g) Replacement of a No. 4 bearing that has

a SN listed in Table 1 of this AD with a No.

4 bearing that does not have a SN listed in

Table 1 of this AD is terminating action for

the repetitive inspection requirements

specified in paragraph (f) of this AD.

Alternative Methods of Compliance

(h) 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 request 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

(i) 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

(j) This amendment becomes effective on

June 11, 2001.

Issued in Burlington, Massachusetts, on

May 24, 2001.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–13720 Filed 5–31–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 01–ACE–2]

Amendment to Class E Airspace;

Phillipsburg, KS

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This document confirms the

effective date of a direct final rule which

revises Class E airspace at Phillipsburg,

KS.

EFFECTIVE DATE: 0901 UTC, July 12,

2001.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Division,

Airspace Branch, ACE–520C, DOT

Regional Headquarters Building, Federal

Aviation Administration, 901 Locust,

Kansas City, MO 64106; telephone:

(816) 329–2525.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on March 2, 2001 (66 FR

13011). The FAA uses the direct final

rulemaking procedure for a noncontroversial rule where the FAA

believes that there will be no adverse

public comment. This direct final rule

advised the public that no adverse

comments were anticipated, and that

unless a written adverse comment, or a

written notice of intent to submit such

an adverse comment, were received

within the comment period, the

regulation would become effective on

July 12, 2001. No adverse comments

were received, and thus this notice

confirms that this direct final rule will

become effective on that date.

Issued in Kansas City, MO, on May 9, 2001.

Richard L. Day,

Acting Manager, Air Traffic Division, Central

Region.

[FR Doc. 01–13673 Filed 5–31–01; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 97

[Docket No. 30249; Amdt. No. 2052]

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.