12726 Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NM–27–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it 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:

2001–03–52 Bombardier Inc. (Formerly

Canadair): Amendment 39–12125.

Docket 2001–NM–27–AD.

Applicability: Model CL–600–2B16 (CL–

604) series airplanes, serial numbers 5301

through 5489 inclusive; certificated in any

category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fuel migration under conditions

of acceleration and/or climb, which could

result in the airplane exceeding the aft center

of gravity limit, and consequent loss of

control of the airplane, accomplish the

following:

Airplane Flight Manual Revision

(a) Within 5 days after the effective date of

this AD, revise the Limitations and Abnormal

Procedures Sections of the Canadair

Challenger CL–604 Airplane Flight Manual

(AFM) PSP–604–1, by inserting a copy of

Canadair Challenger Temporary Revision

(TR) No. 604/13, dated February 1, 2001, into

the AFM.

(b) When the information in TR No. 604/

13, dated February 1, 2001, has been

incorporated into the FAA-approved general

revisions of the AFM, the general revisions

may be inserted in the AFM, and the TR may

be removed from the AFM.

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, New York

Aircraft Certification Office (ACO). Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 1: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Note 2: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2001–07, dated February 2, 2001.

Incorporation by Reference

(d) The AFM revision shall be done in

accordance with Canadair Challenger

Temporary Revision No. 604/13, dated

February 1, 2001. 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 Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087, Station

Centre-ville, Montreal, Quebec H3C 3G9,

Canada. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

FAA, New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley Stream,

New York; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

March 5, 2001, to all persons except those

persons to whom it was made immediately

effective by emergency AD 2001–03–52,

issued February 2, 2001, which contained the

requirements of this amendment.

Issued in Renton, Washington, on February

13, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4217 Filed 2–27–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–57–AD; Amendment

39–12124; AD 2001–04–06]

RIN 2120–AA64

Airworthiness Directives; CFM

International, S.A. CFM56–3, –3B, and

–3C Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to CFM International, S.A.

CFM56–3, –3B, and –3C series turbofan

engines. This amendment requires that

use of certain lubricants no longer on

the manufacturer’s approved list be

discontinued. In addition, this

amendment requires a one-time fan disk

dovetail wear measurement, and if wear

exceeds certain limits, requires an

ultrasonic inspection for cracks in the

fan disk, and, if necessary, removal from

service of fan disks and replacement

with serviceable parts. This amendment

is prompted by reports of fan disk heavy

wear and cracks. The actions specified

by this amendment are intended to

prevent fan disk failure, which could

result in an uncontained engine failure

and damage to the aircraft.

DATES: Effective date April 4, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of April 4, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFM International, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2800, fax (513) 552–2816.

This information may be examined at

the FAA, New England Region, Office of

the Regional 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:

Glorianne Niebuhr, Aerospace Engineer,

Engine Certification Office, FAA, Engine

Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations 12727

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7132,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to CFM International

S.A. CFM56–3, –3B, and –3C Series

Turbofan Engines was published in the

Federal Register on March 3, 2000 (65

FR 11505). That action proposed to

require a one-time fan disk dovetail

wear measurement, and if wear exceeds

certain limits, require an ultrasonic

inspection for cracks in the fan disk,

and, if necessary, require removal from

service of fan disks and replacement

with serviceable parts. That action was

prompted by reports of fan disk heavy

wear and cracks. That condition, if not

corrected, could result in an

uncontained engine failure and damage

to the aircraft.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Compliance Intent

One commenter suggests that the

compliance intent of the AD would be

met if an operator accomplished Boeing

task card C72–31–02–2A–1 or –2, and

Boeing Aircraft Maintenance Manual

(AMM) 72–31–02, tasks on page 601.

The FAA disagrees. The Boeing task

card only describes the procedure for

lubricating fan blade dovetails. In

addition, the AMM does not lead the

operator to perform ultrasonic

inspection and does not explain how to

gain serviceability.

When Inspection Is Not Required

One commenter suggests that the

information contained in paragraphs

1.A. (1) and (2) of CFMI SB 72–854,

Revision 2, should be added to the AD

to clarify when the inspection is NOT

required. The FAA partially agrees. The

information is already included in the

flowcharts in the referenced SB.

However, to further clarify when an

inspection is NOT required, information

has been added to new paragraphs (h),

(i) and (j) of this AD.

Requirements of Revision 1 and

Revision 2

One commenter is concerned that the

requirements of CFMI CFM56–3 SB 72–

854 Revision 1 and CFMI CFM56–3 SB

72–854 Revision 2 are different and that

the AD will result in another round of

inspections after they have already been

done according to Revision 1. Other

commenters want to be sure that credit

will be given for performing Revision 1

of the SB. The FAA partially agrees and

clarification has been added to the AD

to allow Revision 1 as a method of

compliance. There is no technical

difference between Revision 1 and 2.

Revision 2 simply adds flowcharts for

clarification.

Clarification of Wear Limits

One commenter states that the wear

limits in the SB are inconsistent with

the wear limits in the AD (.004 inch vs.

.005 inch). The FAA does not agree.

There is no difference between the AD

and the SB. The two measurements

noted (.004 and .005) are applied in

different contexts. The .004 inch limit in

SB paragraph 1.A.(2) refers to the last

inspection performed in accordance

with the engine shop manual and is one

of the conditions required to avoid the

inspection per the AD. However, the

.005 inch limit is a result of the on-wing

inspection required by the AD to

determine if the disk is serviceable or if

further inspections are necessary.

Inspection Parameters

One commenter asks that the second

bullet in paragraph 1.A of the SB, which

states that for ‘‘fan disks relubricated

with a currently recommended

lubricant, inspection of these disks is

due at 20,000 cycles-since-new (CY)/

35,000 hours-since-new (H) thresholdsince-new or rebroached,’’ be added to

the compliance section of the AD to

clarify when it is possible to wait until

20,000 cycles to perform the inspection.

The FAA agrees with the intent of the

second bullet in paragraph 1.A of the SB

and clarification has been added to new

paragraph (k) of the compliance section

to further explain when it is possible to

wait until 20,000 cycles to inspect.

Rebroached Fan Disks

The manufacturer asks that a

statement be added to the effectivity

section of the AD that rebroached fan

disks do not require an inspection per

this AD. The FAA agrees and has added

new paragraph (i) to the AD, stating that

inspections will not be required for

rebroached fan disks.

Where To Perform the Inspection

One commenter requests that the fan

disk inspections be performed at the

shop visit level instead of on-wing. The

commenter further states that there is a

low failure rate and incidents that

occurred resulted from the use of an

uncommon lubricant. The FAA does not

agree. The lubricant being discontinued

was an approved lubricant. The

lubricant has since been taken off of the

approved lubricant list. But before that

time, any and all operators had the

possibility of being exposed. As stated

in SB paragraph 1.A.(1), if the fan disk

has used a currently approved lubricant

and has the recommended configuration

installed before 3,000 cycles/5250

hours, inspection is not required.

Otherwise inspection per the AD is

necessary to maintain a minimum

acceptable level of safety. In addition, a

cracked fan disk could lead to an

uncontained failure. The risk analysis

shows that the control program

described in this AD meets the

minimum level of safety.

Labor Requirement

One commenter asks the FAA to add

two hours for ultrasonic inspection to

the labor requirement. The FAA does

not agree. The two hours for ultrasonic

inspection is already included in the

estimated nine man-hours detailed in

the AD. It is also spelled out in detail

in paragraph 1.F.(4) of the SB.

Availability of Blade Replacements

One commenter asks that the FAA

revise the on-wing inspection

requirement to a shop visit when it is

necessary to install the 37° fan blades.

The commenter is concerned that blades

are not always available and down time

may result. The FAA does not agree.

The manufacturer has informed the

FAA that all parts should be readily

available for purchase and installation.

In addition, this method meets the

minimum acceptable level of safety

necessary for this program.

Wear Measurement Tool

One commenter, who questions the

accuracy and repeatability of the

measuring tool with respect to the

allowable max wear limit of .005 inch,

asks that the FAA consider eliminating

the wear measurement tool in the

inspection process. The FAA does not

agree. The current wear measurement

tool is acceptable for this inspection

program. This issue was addressed in

the beginning of the program. The .005

inch wear limit takes into consideration

the accuracy and repeatability factor. In

addition, new improvements have since

been introduced to this tool and courses

have been provided to explain how to

use it properly. Repeatability and

reproducibility tests were performed in

overhaul shops in 1997. This is the

current best practice that is compatible

with existing maintenance constraints

and practices.

12728 Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations

Concurrence as Written

One commenter concurs with the AD

as written.

After careful review of the available

data, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Regulatory Impact

This proposal 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 proposal.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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:

2001–04–06 CFM International: Amendment

39–12124. Docket 98–ANE–57–AD.

Applicability: CFM International, S.A

(CFMI) CFM56–3, –3B, and –3C series

turbofan engines, installed on but not limited

to Boeing 737 series aircraft.

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 (l)

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 fan disk failure, which could

result in an uncontained engine failure and

damage to the aircraft, accomplish the

following:

Wear Measurement (Thrust Rating Category

A Only)

(a) For CFM56–3, –3B, and –3C series

engines operating at the category A thrust

rating on the effective date of this AD that

have never previously operated at the

category B or C thrust ratings, perform a one

time fan disk dovetail wear measurement in

accordance with section 2.B.(1) of Service

Bulletin (SB) CFMI CFM56–3/–3B/–3C, No.

72–854, Revision 1, dated August 7, 1998, or

section 2.B.(1) of SB CFMI CFM56–3/–3B/–

3C, No. 72–854, Revision 2, dated November

29, 1999, using the intervals defined in

section 1.D.(1)(a)(1) and 1.D.(1)(a)(2) of the

SB’s, and the current fan disk time and cycles

on the effective date of the AD.

Inspection

(1) Perform a local ultrasonic inspection for

cracks in the fan disk in accordance with

section 2.B.(2) of the SB, if required by the

wear criteria described in section 1.D.(1)(b)1

of the SB.

Removal

(i) Remove from service prior to further

flight fan disks that do not meet the

ultrasonic inspection criteria defined in

paragraph 2.B.(2)(d)8b of the SB, and replace

with a serviceable part.

(ii) Remove from service within 50 cyclesin-service (CIS), fan disks that meet the

ultrasonic inspection criteria defined in

paragraph 2.B.(2)(d)8b of the SB, if the wear

measurement is greater than or equal to 9

mils.

(2) Install dampers, as required, in

accordance with the compliance times and

criteria described in section 1.D.(1)(b)1 of the

SB.

Wear Measurement (Thrust Rating Category

A, if the Engine Was Previously Operated at

Thrust Rating Categories B or C)

(b) For CFM56–3, –3B, and –3C series

engines operating at the category A thrust

rating on the effective date of this AD that

have previously operated at the category B or

category C thrust ratings, perform a one-time

fan disk dovetail wear measurement in

accordance with section 2.B.(1) of SB CFMI

CFM56–3/–3B/–3C, No. 72–854, Revision 1,

dated August 7, 1998, or section 2.B.(1) of SB

CFMI CFM56–3/–3B/–3C, No. 72–854,

Revision 2, dated November 29, 1999, using

the intervals defined in section 1.D.(1)(a)(1)

and 1.D.(1)(a)(2) of the SB’s, and the current

fan disk time and cycles on the effective date

of the AD.

Inspection

(1) Perform a local ultrasonic inspection for

cracks in the fan disk in accordance with

section 2.B.(2) of the SB, if required by the

wear criteria described in section 1.D.(1)(b)2

of the SB.

Removal

(i) Remove from service prior to further

flight fan disks that do not meet the

ultrasonic inspection criteria defined in

paragraph 2.B.(2)(d)8b of the SB, and replace

with a serviceable part.

(ii) Remove from service within 50 CIS, fan

disks that meet the ultrasonic inspection

criteria defined in paragraph 2.B.(2)(d)8b of

the SB, if the wear measurement is greater

than or equal to 9 mils.

(2) Install dampers, as required, in

accordance with the compliance times and

criteria described in section 1.D.(1)(b)2 of the

SB.

Wear Measurement (Thrust Rating Category

B, Regardless of Whether the Engine Was

Previously Operated at Thrust Rating

Categories A or C)

(c) For CFM56–3B and –3C series engines

operating at the category B thrust rating on

the effective date of this AD, regardless of

whether the engine was previously operated

at thrust rating categories A or C, perform a

one-time fan disk dovetail wear measurement

in accordance with section 2.B.(1) of CFMI

CFM56–3/–3B/–3C Service Bulletin (SB) No.

72–854, Revision 1, dated August 7, 1998, or

section 2.B.(1) of CFMI CFM56–3/–3B/–3C

SB No. 72–854, Revision 2, dated November

29, 1999, using the intervals defined in

section 1.D.(1)(a)(1) and 1.D.(1)(a)(2) of the

SB’s, and the current fan disk time and cycles

on the effective date of the AD.

Inspection

(1) Perform a local ultrasonic inspection for

cracks in the fan disk in accordance with

section 2.B.(2) of the SB, if required by the

wear criteria described in section 1.D.(1)(c) of

the SB.

Removal

(i) Remove from service prior to further

flight fan disks that do not meet the

ultrasonic inspection criteria defined in

paragraph 2.B.(2)(d)8b of the SB, and replace

with a serviceable part.

(ii) Remove from service within 50 CIS, fan

disks that meet the ultrasonic inspection

Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations 12729

criteria defined in paragraph 2.B.(2)(d)8b of

the SB, if the wear measurement is greater

than or equal to 9 mils.

(2) Remove and replace fan blades and

install dampers, as required, in accordance

with the compliance times and criteria

described in section 1.D.(1)(c) of the SB.

Wear Measurement (Thrust Rating Category

C, Regardless of Whether the Engine Was

Previously Operated at Thrust Rating

Categories A or B)

(d) For CFM56–3C series engines operating

at the category C thrust rating on the effective

date of this AD, regardless of whether the

engine was previously operated at category A

or B thrust ratings, perform a one-time fan

disk dovetail wear measurement in

accordance with section 2.B.(1) of SB CFMI

CFM56–3/–3B/–3C, No. 72–854, Revision 1,

dated August 7, 1998, or section 2.B.(1) of SB

CFMI CFM56–3/–3B/–3C SB, No. 72–854,

Revision 2, dated November 29, 1999, using

the intervals defined in section 1.D.(1)(a)(1)

and 1.D.(1)(a)(2) of the SB’s and the current

fan disk time and cycles on the effective date

of the AD.

Inspection

(1) Perform a local ultrasonic inspection for

cracks in the fan disk in accordance with

section 2.B.(2) of the SB, if required by the

wear criteria described in section 1.D.(1)(d)

of the SB.

Removal

(i) Remove from service prior to further

flight fan disks that do not meet the

ultrasonic inspection criteria defined in

paragraph 2.B.(2)(d)8b of the SB, and replace

with a serviceable part.

(ii) Remove from service within 50 CIS, fan

disks that meet the ultrasonic inspection

criteria defined in paragraph 2.B.(2)(d)8b of

the SB, if the wear measurement is greater

than or equal to 5 mils.

(2) [Reserved]

Cleaning and Lubrication of Fan Disk/Blade

(e) If the fan disk is determined to be

serviceable, clean and lubricate the fan disk

and fan blades using the instructions in

paragraph 2.B.(2)(d)8d of the SB.

Definitions

(f) The category A, B, and C thrust ratings

listed in paragraphs (a) through (d) of this AD

are defined in chapter 05 of the CFM56–3

model series Engine Shop Manual, CFMI–

TP.SM.5.

Lubricants

(g) After the effective date of this AD, the

following lubricants are no longer approved

for use on the CFMI CFM56–3, –3B, and –3C

series engines: Sandstrom 27A, ZIP D5460,

Surf-kote A 1625, Tiolube 70 and Tiolube 75/

75.

When Inspection Is Not Required

(h) The actions required by paragraphs (a),

(b), (c), and (d), (e) of this AD are not

required if the fan disk has been equipped

with configurations (1) or (2) below prior to

reaching 3,000 cycles-since-new, or 5,250

hours-since-new, whichever occurs first, and

has never been relubricated using one of the

lubricants identified in paragraph (g) of this

AD:

(1) For fan disks operating at a thrust rating

of 20,000 pounds or less, the fan disk has

either 25° fan blades with dampers or 37° fan

blades with or without dampers.

(2) For fan disks operating at a thrust rating

of more than 20,000 pounds, the fan disk has

37° fan blades with dampers.

(i) Inspection is not required for fan disks

that used lubricants identified in paragraph

(g) but were then rebroached prior to

exceeding the .004 inch wear limit, then were

not lubricated with the lubricants identified

in paragraph (g) AND were equipped with

fan blade configurations specified either in

sub-paragraph (h)(1) or (h)(2) of this AD.

(j) Inspection is also not required for fan

disks that were inspected to and within

Engine Shop Manual limits of .004 inch wear

limit, then were not lubricated with the

lubricants identified in paragraph (g) AND

were equipped with fan blade configurations

specified either in sub-paragraph (h)(1) or

(h)(2) of this AD.

When Inspection Can Wait Until 20,000

Cycles-Since-New (CSN)/35,000 Time-SinceNew (TSN)

(k) For disks that have never been

relubricated since first manufacture using

one of the lubricants identified in paragraph

(g) of this AD, the inspections required by

paragraphs (a), (b), (c), and (d) of this AD are

required at 20,000 CSN or 35,000 hours TSN,

whichever occurs first.

Alternative Methods of Compliance

(l) 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

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.

Ferry Flights

(m) Special flight permits may be issued in

accordance with §§ 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.

Incorporation by Reference Material

(n) The FAA has reviewed and approved

the technical content of the listed CFMI SBs.

The actions required by this AD shall be

done in accordance with the following CFMI

SBs:

Document No. Pages Revision Date

CFM56 –3/–3B/–3C, SB No. 72–854 ............................................................................... 1–39 1 August 7, 1998.

Total pages ............................................................................................................ 39

CFM56 –3/–3B/–3C, SB No. 72–854 ............................................................................... 1–40 2 November 29, 1999.

Total pages ............................................................................................................ 40

The incorporations by reference were

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 CFM International, Technical

Publications Department, 1 Neumann Way,

Cincinnati, OH 45215; telephone: (513) 552–

2800, fax: (513) 552–2816. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA

01803–5299; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(o) This amendment becomes effective on

April 4, 2001.

Issued in Burlington, Massachusetts, on

February 12, 2001.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 01–4216 Filed 2–27–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–69–AD; Amendment

39–12126; AD 2001–04–07]

RIN 2120–AA64

Airworthiness Directives; SOCATAGroupe Aerospatiale Model TBM 700

Airplanes

AGENCY: Federal Aviation

Administration, DOT.