21074 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

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:

2001–08–21 Lockheed: Amendment 39–

12198. Docket 2000–NM–41–AD.

Applicability: All Model L–1011–385

series airplanes; certificated in any category.

Note 1: This AD applies to each airplane

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

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 chafing of the fuel level control

switch wiring harness, which could cause

arcing and result in a fire in the fuel tank,

accomplish the following:

Inspection, Replacement, and Installation

(a) Within 18 months after the effective

date of this AD: Verify the part number (P/

N) of the wiring harness conduit and perform

a general visual inspection of the fuel level

control switch, the fuel level control switch

wiring harness, and the wiring harness

conduit to detect any visible damage, any

wear or chafing, broken or missing O-rings,

or indications of electrical arcing, in

accordance with the Accomplishment

Instructions in Lockheed Service Bulletin

093–28–094, dated March 3, 2000.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

(b) Prior to further flight after

accomplishment of the requirements in

paragraph (a) of this AD, accomplish the

actions specified in paragraphs (b)(1) and

(b)(2), as applicable; in accordance with the

Accomplishment Instructions in Lockheed

Service Bulletin 093–28–094, dated March 3,

2000.

(1) Install sleeving over each fuel level

control switch wiring harness and install the

modified fuel level control switch.

(2) If a conduit with P/N 97590–103 is

installed, replace the conduit with one

having P/N 97590–121, install sleeving over

each fuel level control switch wiring harness,

and install the modified fuel level control

switch.

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, Atlanta

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with Lockheed Service Bulletin 093–28–094,

dated March 3, 2000. 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 Lockheed Martin Aircraft &

Logistics Center, 120 Orion Street,

Greenville, South Carolina 29605. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

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

Atlanta Aircraft Certification Office, One

Crown Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

Effective Date

(f) This amendment becomes effective on

June 1, 2001.

Issued in Renton, Washington, on April 18,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10174 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–182–AD; Amendment

39–12202; AD 2001–08–25]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330–301, –321, –322, and –342 Series

Airplanes and Airbus Model A340

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A330–301, –321, –322, and –342 series

airplanes and certain Airbus Model

A340 series airplanes. This action

requires reinforcement of the wing

structure at the inboard pylon rear

pickup area. This action is necessary to

prevent fatigue cracking of the bottom

skin and reinforcing plate of the wing

due to bending, which could lead to

reduced structural integrity of the

airplane wing. This action is intended to

address the identified unsafe condition.

DATES: Effective May 14, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 14,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

May 29, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

182–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–182–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21075

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

certain Airbus Model A330–301, –321,

–322, and –342 series airplanes and

certain Airbus Model A340 series

airplanes. The DGAC advises that,

during wing fatigue tests, cracks were

detected on the bottom skin and

reinforcing plates of stringers 10 and 11

between ribs 10 and 10A at the inboard

pylon rear pickup. This condition, if not

corrected, could result in reduced

structural integrity of the airplane wing.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletins

A330–57–3021, Revision 03, including

Appendices 01 and 02, (for Model A330

series airplanes), and A340–57–4025,

Revision 02, including Appendices 01

and 02 (for Model A340 series

airplanes), both dated November 5,

1999, which describe procedures for

reinforcement of the wing structure at

the inboard pylon rear pickup area. This

involves removing the existing

reinforcing plate; performing highfrequency eddy current tests for cracks,

and corrective action, if necessary; and

installing a larger reinforcing plate and

packer plate. Accomplishment of the

actions specified in the service bulletins

is intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directives 2000–178–

121(B) and 2000–179–147(B), both

dated May 3, 2000, in order to assure

the continued airworthiness of these

airplanes in France.

Airbus Service Bulletin A330–57–

3021, Revision 03, including

Appendices 01 and 02, dated November

5, 1999, specifies the prior or concurrent

accomplishment of Airbus Service

Bulletin A330–54–3005. Revision 01,

dated October 19, 1999, of this service

bulletin, describes procedures for

replacing five existing fillets with five

new fillets, one existing firewall with

one new firewall, one existing case

drainpipe with one new case drainpipe,

and modifying the contour milling of

the external tip of rib 19A on the left

hand (LH) and right hand (RH) pylons.

Airbus Service Bulletin A340–57–

4025, Revision 02, including

Appendices 01 and 02, dated November

5, 1999, specifies the prior or concurrent

accomplishment of Airbus Service

Bulletin A340–54–4003. Revision 01,

dated April 26, 2000, of this service

bulletin, describes procedures for

replacing five existing fillets with five

new fillets and one existing firewall

with one new firewall on the LH and RH

inboard pylons.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.19) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design that may be registered in the

United States at some future time, this

AD is being issued to prevent fatigue

cracking of the bottom skin and

reinforcing plate of the airplane wings

due to bending, which could lead to

reduced structural integrity of the

wings. This AD requires

accomplishment of the actions specified

in the service bulletins described

previously, except as discussed below.

Differences Between Rule and Service

Bulletins

Operators should note that, although

the service bulletins specify that the

manufacturer may be contacted for

disposition of certain repair conditions,

this AD requires the repair of those

conditions to be accomplished per a

method approved by either the FAA, or

the DGAC (or its delegated agent). In

light of the type of repair that would be

required to address the identified unsafe

condition, and in consonance with

existing bilateral airworthiness

agreements, the FAA has determined

that, for this AD, a repair approved by

either the FAA or the DGAC would be

acceptable for compliance with this AD.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicability

of this AD currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this AD is necessary

to ensure that the unsafe condition is

addressed in the event that any of these

subject airplanes are imported and

placed on the U.S. Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, for Model A330–

301, –321, –322, and –342 series

airplanes, to follow Airbus Service

Bulletin A330–57–3021, Revision 03,

including Appendices 01 and 02, dated

November 5, 1999, it would require

approximately 380 work hours to

accomplish the required replacements,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $44,800 per airplane.

Based on these figures, the expected

cost of these replacements per airplane

would be $67,600.

Also for Model A330–301, –321, –322,

and –342 series airplanes, to follow

Airbus Service Bulletin A330–54–3005,

Revision 01, dated October 19, 1999, it

would require approximately 36 work

hours to accomplish the required

replacements, at an average labor rate of

$60 per work hour. Required parts

would cost approximately $15,774 per

airplane. Based on these figures, the

expected cost of these replacements per

airplane would be $17,934.

For Airbus Model A340 series

airplanes, to follow Airbus Service

Bulletin A340–57–4025, Revision 02,

including Appendices 01 and 02, dated

November 5, 1999, it would require

approximately 380 work hours to

accomplish the required replacements,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $44,800 per airplane.

Based on these figures, the expected

cost of these replacements per airplane

would be $67,600.

Also for Model A340 series airplanes,

to follow Airbus Service Bulletin A340–

54–4003, Revision 01, dated April 26,

2000, it would require approximately 26

work hours to accomplish the required

replacements, at an average labor rate of

$60 per work hour. Required parts

would cost approximately $ 15,358 per

airplane. Based on these figures, the

21076 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

expected cost of these replacements per

airplane would be $16,918.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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

shall 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g.,≤ reasons

or data) for each request.

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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–182–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.

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 DOT

Regulatory Policies and Procedures (44

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

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

adding the following new airworthiness

directive:

2001–08–25 Airbus Industrie: Amendment

39–12202. Docket 2000–NM–182–AD.

Applicability: Model A330–301, –321,

–322, and –342 series airplanes, as listed in

Airbus Service Bulletin A330–57–3021,

Revision 03, including Appendices 01 and

02, dated November 5, 1999; and Model

A340 series airplanes, as listed in Airbus

Service Bulletin A340–57–4025, Revision 02,

including Appendices 01 and 02, dated

November 5, 1999; certificated in any

category.

Note 1: This AD applies to each airplane

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

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 (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 fatigue cracking of the airplane

wing bottom skin and reinforcing plate due

to wing bending, which could lead to

reduced structural integrity of the wing,

accomplish the following:

Modification

(a) For Model A330 series airplanes, prior

to the accumulation of 12,000 total flight

cycles or 37,300 total flight hours, whichever

occurs first, accomplish the actions required

by paragraphs (a)(1) and (a)(2) of this AD.

(1) Prior to, or concurrently with, the

accomplishment of the tasks required by

paragraph (a)(2) of this AD, replace five

existing fillets with five new fillets, one

existing firewall with one new firewall, and

one existing case drainpipe with one new

case drainpipe, and modify the contour

milling of the external tip of rib 19A on each

of the left and right wing pylons, in

accordance with Airbus Service Bulletin

A330–54–3005, Revision 01, dated October

19, 1999.

(2) Concurrently with, or subsequent to,

the accomplishment of the tasks required by

paragraph (a)(1) of this AD, reinforce the

wing structure at the inboard pylon rear

pickup area on both wings (including

performing high-frequency eddy current

rototests, corrective actions if necessary, and

installing a larger reinforcing plate and

packer plate) in accordance with Airbus

Service Bulletin A330–57–3021, Revision 03,

including Appendices 01 and 02, dated

November 5, 1999.

(b) For Model A340 series airplanes, prior

to the accumulation of 15,000 total flight

cycles or 59,600 total flight hours, whichever

occurs first, accomplish the actions required

by paragraphs (b)(1) and (b)(2) of this AD.

(1) Prior to, or concurrently with, the

accomplishment of the tasks required by

paragraph (b)(2) of this AD, reinforce the

wing structure at the inboard pylon rear

pickup area of both wings (including

performing high-frequency eddy current

rototests, corrective actions if necessary, and

installing a larger reinforcing plate and

packer plate) in accordance with Airbus

Service Bulletin A340–57–4025, Revision 02,

including Appendices 01 and 02, dated

November 5, 1999.

(2) Concurrently with, or subsequent to,

the accomplishment of the tasks required by

paragraph (b)(1) of this AD, replace five

existing fillets with five new fillets and one

existing firewall with one new firewall on

each of the left and right wing inboard

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21077

pylons, in accordance with Airbus Service

Bulletin A340–54–4003, Revision 01, dated

April 26, 2000.

(c) If any discrepancy is found during any

inspection or rototest required by paragraphs

(a)(2) or (b)(1) of this AD, prior to further

flight, accomplish applicable repairs in

accordance with Airbus Service Bulletin

A330–57–3021, Revision 03, including

Appendices 01 and 02, dated November 5,

1999 (for Model A330 series airplanes), or

Airbus Service Bulletin A340–57–4025,

Revision 02, including Appendices 01 and

02, dated November 5, 1999 (for Model A340

series airplanes). If the service bulletin

specifies to contact the manufacturer for

appropriate action: Prior to further flight,

repair in accordance with a method approved

by either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate; or the Direction Ge ́ne ́rale de

l’Aviation Civile (or its delegated agent).

Note 2: Accomplishment of the

modifications required by paragraphs (a)(1)

and (a)(2) or paragraphs (b)(1) and (b)(2) prior

to the effective date of this AD in accordance

with the service bulletins listed in Table 1,

as follows, is considered acceptable for

compliance with the applicable actions in

this AD:

TABLE 1.—PRIOR SERVICE BULLETINS CONSIDERED ACCEPTABLE FOR COMPLIANCE

Model Service bulletin Revision level Date

A330 .............................. A330–57–3021 Original ............................................................. March 25, 1996.

A330–57–3021 01 ..................................................................... September 1, 1998.

A330–57–3021 02 ..................................................................... April 9, 1999.

A330 .............................. A330–54–3005 Original ............................................................. March 25, 1996.

A340 .............................. A340–57–4025 Original ............................................................. March 25, 1996.

A340–57–4025 01 ..................................................................... September 1, 1998.

A340 .............................. A340–54–4003 Original ............................................................. March 25, 1996.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) Except as provided by paragraph (c) of

this AD, the actions must be done in

accordance with Airbus Service Bulletin

A330–57–3021, Revision 03, including

Appendices 01 and 02, dated November 5,

1999; Airbus Service Bulletin A340–57–4025,

Revision 02, including Appendices 01 and

02, dated November 5, 1999; Airbus Service

Bulletin A330–54–3005, Revision 01, dated

October 19, 1999; and Airbus Service

Bulletin A340–54–4003, Revision 01, dated

April 26, 2000; as applicable. 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 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 directives 2000–

178–121(B) and 2000–179–147(B), both dated

May 3, 2000.

Effective Date

(g) This amendment becomes effective on

May 14, 2001.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10338 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–276–AD; Amendment

39–12205; AD 2001–08–28]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires revising

the Airworthiness Limitations Section

of the maintenance manual (767

Airworthiness Limitations Instructions

(ALI)). The revision will incorporate

into the ALI certain inspections and

compliance times to detect fatigue

cracking of principal structural elements

(PSE). This amendment is prompted by

analysis of data that identified specific

initial inspection thresholds and

repetitive inspection intervals for

certain PSE’s to be added to the ALI.

The actions specified by this AD are

intended to ensure that fatigue cracking

of various PSE’s is detected and

corrected; such fatigue cracking could

adversely affect the structural integrity

of these airplanes.

DATES: Effective June 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Linda Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: John

Craycraft, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue SW., Renton, Washington;

telephone (425) 227–2782; fax (425)

227–1181.

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 certain Boeing

Model 767 series airplanes was

published in the Federal Register on

January 28, 1999 (64 FR 4372). That

action proposed to require revising the

Airworthiness Limitations Section of

the maintenance manual (767

Airworthiness Limitations Instructions

(ALI)). The revision would incorporate