75620 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

Issued in Renton, Washington, on

November 22, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30439 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–36–AD; Amendment

39–12022; AD 2000–24–15]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes,

that requires a one-time detailed visual

inspection to detect discrepancies of all

electrical wiring installations in various

areas of the airplane; and corrective

actions, if necessary. This amendment is

necessary to prevent electrical arcing

and/or heat damaged wires due to

improper wire installations during

manufacture and/or maintenance of the

airplane, and consequent fire and smoke

in various areas of the airplane. This

amendment is intended to address the

identified unsafe condition.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 8,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Aircraft

Group, Long Beach Division, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). This information

may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5350;

fax (562) 627–5210.

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 McDonnell

Douglas Model MD–11 series airplanes

was published in the Federal Register

on July 27, 2000 (65 FR 46218). That

action proposed to require a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in various areas of the

airplane; and corrective actions, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request for Reporting Requirement

One commenter requests that the FAA

add a reporting requirement for the

inspection findings. The commenter

states that serious reporting is not

possible using the reporting sheet

attached to the referenced Boeing

service bulletin. The commenter

believes that it is important to collect

the details of the inspection results

using a database.

The FAA does not concur. The FAA

understands the need to collect useful

data in a consistent, detailed manner

when investigating possible wiring

service difficulties. However, the FAA

has already conducted an extensive

investigation of the wiring on

McDonnell Douglas Model MD–11

series airplanes. As part of the

investigation, the FAA has performed its

own inspections on numerous in-service

and in-production airplanes. The FAA

has analyzed the data from the

inspections and incorporated follow-on

actions as part of a comprehensive

corrective action plan; this AD is part of

that plan. Therefore, the FAA has

determined that the need for a reporting

requirement for the required inspections

to detect and correct minor wiring

discrepancies in various areas of the

airplane is not necessary.

Revise Corrective Action

One commenter notes that paragraph

(c) of the NPRM reads, ‘‘If no gap

between the wire bundle and blanket

can be seen when pressure is applied to

the blanket, before further flight,

reposition wires or clamps so that a gap

can been seen when pressure is applied

to the blanket.’’ The commenter asks,

‘‘Will this requirement be valid for all

the wire gauges in every area? Does this

requirement replace the existing DPS

1.834–7, Par. 4.1.12.1?’’

From these questions, the FAA infers

that the commenter is requesting that

the scope of the corrective action

specified in paragraph (c) of the NPRM

apply only to wiring that is routed over

structural frames. The FAA concurs. In

its attempt to provide instructions for

accomplishing certain corrective

actions, which were not provided in the

referenced service bulletin (discussed in

the preamble of the NPRM), the FAA

did not carry forward the scope of the

test requirement into the corrective

action specified in paragraph (c) of the

AD. For clarification purposes, the FAA

has revised paragraph (c) of the final

rule to read, ‘‘If no gap between the wire

bundle and blanket can be seen where

the wiring is routed over structural

frames * * * .’’

Actions Since Issuance of the NPRM

The FAA has reviewed and approved

the following service bulletins:

Service bulletin Revision level Date

McDonnell Douglas Service Bulletin MD11–24–171 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–170 .............................................. Revision 01 ............................................ November 6, 2000.

Boeing Service Bulletin MD11–24–167, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

Boeing Service Bulletin MD11–24–165, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

Boeing Service Bulletin MD11–24–163, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–188 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–161 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–162 .............................................. Revision 01 ............................................ November 6, 2000.

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75621

The procedures described in these

service bulletins are identical to those

described in the original issue of the

service bulletins (which were referenced

in the NPRM as the appropriate sources

of service information for doing the

proposed actions), but contain certain

editorial changes. No additional work is

necessary on airplanes changed per the

original issue of the service bulletins.

Therefore, the FAA has revised the final

rule to include Revision 01 of these

service bulletins as additional sources of

service information.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 182 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 60 airplanes of U.S.

registry will be affected by this AD.

It will take approximately 10 work

hours per airplane to accomplish each

of the six inspections specified in

paragraphs (a)(1), (a)(2), (a)(3), (a)(4),

(a)(5), and (a)(6) of this AD, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of these indicated inspections required

by this AD on U.S. operators is

estimated to be $216,000, or $3,600 per

airplane.

It will take approximately 5 work

hours per airplane to accomplish the

inspection specified in paragraph (a)(7)

of this AD, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of this indicated

inspection required by this AD on U.S.

operators is estimated to be $18,000, or

$300 per airplane.

It will take approximately 12 work

hours per airplane to accomplish the

inspection specified in paragraph (a)(8)

of this AD, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of this indicated

inspection required by this AD on U.S.

operators is estimated to be $43,200, or

$720 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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:

2000–24–15 McDonnell Douglas:

Amendment 39–12022. Docket 2000–

NM–36–AD.

Applicability: Model MD–11 series

airplanes, manufacturer’s fuselage numbers

0447 through 0449 inclusive, 0451 through

0464 inclusive, 0466 through 0489 inclusive,

0491 through 0517 inclusive, 0519 through

0552 inclusive, 0554 through 0556 inclusive,

0557, 0558 through 0633 inclusive, and 0635;

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 (e) 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.

Note 2: The FAA recommends that the

actions required by this AD be accomplished

immediately after accomplishing the

replacement of metallized

polyethyleneteraphthalate (MPET) insulation

blankets, as required by AD 2000–11–02,

amendment 39–11750 (65 FR 34341, May 26,

2000).

To prevent electrical arcing and/or heat

damaged wires due to improper wire

installations during manufacture and/or

maintenance of the airplane, and consequent

fire and smoke in various areas of the

airplane, accomplish the following:

One-Time Detailed Visual Inspection

(a) Within 5 years after the effective date

of this AD, accomplish the actions specified

in paragraphs (a)(1), (a)(2), (a)(3), (a)(4), (a)(5),

(a)(6), (a)(7), and (a)(8) of this AD, as

applicable.

(1) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the center and aft cargo

compartments from stations Y=1521.000 to

Y=2007.000, in accordance with paragraph

3.B., ‘‘Work Instructions,’’ of the

Accomplishment Instructions of McDonnell

Douglas service Bulletin MD11–24–171,

dated April 4, 2000, or Revision 01, dated

November 6, 2000.

Note 3: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc. may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(2) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the forward cargo

compartment from stations Y=595.000 to

Y=6–73.500, in accordance with the

paragraph 3.B., ‘‘Work Instructions,’’ of the

75622 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

Accomplishment Instructions of McDonnell

Douglas Service Bulletin MD11–24–170,

dated April 12, 2000, or Revision 01, dated

November 6, 2000.

(3) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the forward passenger

compartment from stations Y=5–11.000 to

Y=2007.000, in accordance with the

paragraph 3.B., ‘‘Work instructions,’’ of the

Accomplishment Instructions of McDonnell

Douglas Service bulletin MD11–24–167,

dated April 4, 2000, or Boeing Service

Bulletin MD11–24–167, revision 01,

including Appendix 1, dated November 6,

2000.

(4) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the forward passenger

compartment from stations Y=756.000 to

Y=1501.000, in accordance with the

paragraph 3.B., ‘‘Work instructions,’’ of the

Accomplishment Instructions of McDonnell

Douglas Service Bulletin MD11–24–165,

dated April 4, 2000, or Boeing Service

Bulletin MD11–24–165, Revision 01,

including Appendix, dated November 6,

2000.

(5) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the forward passenger

compartment from stations Y=465.000 to

Y=755.000, in accordance with the paragraph

3.B., ‘‘Work instructions,’’ of the

Accomplishment Instructions of McDonnell

Douglas Service Bulletin MD11–24–163,

dated April 4, 2000, or Boeing Service

Bulletin MD11–24–163, Revision 01,

including Appendix 1, dated November 6,

2000.

(6) For all airplanes: Perform a one-time

detailed visual inspection to detect

discrepancies of all electrical wiring

installations in the flight compartment and

forward drop ceilings areas from stations

Y=275.000 to Y=464.000, in accordance with

the paragraph 3.B., ‘‘Work Instructions,’’ of

the Accomplishment Instructions of

McDonnell Douglas Service Bulletin MD11–

24–188, dated April 28, 2000, or Revision 01,

dated november 6, 2000.

(7) For airplanes having manufacturer’s

fuselage numbers 0447 through 0449

inclusive, 0451 through 0464 inclusive, 0466

through 0489 inclusive, 0491 through 0517

inclusive, 0519 through 0552 inclusive, 0554

through 0556 inclusive, 0557, 0558 through

0633 inclusive: Perform a one-time detailed

visual inspection to detect discrepancies of

all electrical wiring installations in the center

accessory compartment from stations y=6–

50.000 to Y=1179.000, in accordance with

the paragraph 3.B., ‘‘Work Instructions,’’ of

the Accomplishment Instructions of

McDonnell Douglas Service Bulletin MD11–

24–161, dated April 10, 2000, or Revision 01,

dated November 6, 2000.

(8) For airplanes having manufacturer’s

fuselage numbers 0447 through 0449

inclusive, 0451 through 0464 inclusive, 0466

through 0489 inclusive, 0491 through 0517

inclusive, 0519 through 0552 inclusive, 0554

through 0556 inclusive, 0557, 0558 through

0633 inclusive: Perform a one-time detailed

visual inspection to detect discrepancies of

all electrical wiring installations in the main

avionics compartment from stations

y=275.000 to Y=464.000, in accordance with

the paragraph 3.B., ‘‘Work Instructions,’’ of

the Accomplishment Instructions of

McDonnell Douglas Service Bulletin MD11–

24–162, dated April 10, 2000, or Revision 01,

dated November 6, 2000.

Corrective Action

(b) If any discrepancy is detected during

the inspection required by paragraph (a)(1),

(a)(2), (a)(3), (a)(4), (a)(5), (a)(6), (a)(7), or

(a)(8) of this AD, before further flight,

accomplish the applicable corrective

action(s) in accordance with the

Accomplishment Instructions of the

following applicable service bulletins, except

as provided in paragraphs (c) and (d) of this

AD, as applicable:

(1) McDonnell Douglas Service Bulletin

MD11–24–171, dated April 4, 2000, or

Revision 01, dated November 6, 2000;

(2) McDonnell Douglas Service Bulletin

MD11–24–170, dated April 12, 2000, or

Revision 01, dated November 6, 2000;

(3) McDonnell Douglas Service Bulletin

MD11–24–167, dated April 4, 2000;

(4) Boeing Service Bulletin MD11–24–167,

dated April 4, 2000, Revision 01, including

Appendix, dated November 6, 2000;

(5) McDonnell Douglas Service Bulletin

MD11–24–165, dated April 4, 2000;

(6) Boeing Service Bulletin MD11–24–165,

Revision 01, including Appendix, dated

November 6, 2000;

(7) McDonnell Douglas Service Bulletin

MD11–24–163, dated April 4, 2000;

(8) Boeing Service Bulletin MD11–24–163,

Revision 01, including Appendix 1, dated

November 6, 2000;

(9) McDonnell Douglas Service Bulletin

MD11–24–188, dated April 28, 2000, or

Revision 01, dated November 6, 2000;

(10) McDonnell Douglas Service Bulletin

MD11–24–161, dated April 10, 2000, or

Revision 01, dated November 6, 2000; or

(11) McDonnell Douglas Service Bulletin

MD11–24–162, dated April 10, 2000, or

Revision 01, dated November 6, 2000.

Note 4: Where there are differences

between the AD and the referenced service

bulletins, the AD prevails.

(c) If no gap between the wire bundle and

blanket can be seen where the wiring is

routed over the structural frames when

pressure is applied to the blanket, before

further flight, reposition wires or clamps so

that a gap can be seen when pressure is

applied to the blanket.

(d) If any screw terminal of the flag lug bus

bar is loose, before further flight, retorque to

10 to 11 inch-pounds.

Alternative Methods of Compliance

(e) 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, Los

Angeles 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,

Los Angeles ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(f) 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

(g) Except as provided by paragraphs (c)

and (d) of this AD, the actions shall be done

in accordance with the following applicable

service bulletins:

Service bulletin Revision level Date

McDonnell Douglas Service Bulletin MD11–24–171 .............................................. Original .................................................. April 4, 2000.

McDonnell Douglas Service Bulletin MD11–24–171 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–170 .............................................. Original .................................................. April 12, 2000.

McDonnell Douglas Service Bulletin MD11–24–170 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–167 .............................................. Original .................................................. April 4, 2000.

Boeing Service Bulletin MD11–24–167, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–165 .............................................. Original .................................................. April 4, 2000.

Boeing Service Bulletin MD11–24–165, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–163 .............................................. Original .................................................. April 4, 2000.

Boeing Service Bulletin MD11–24–163, including Appendix .................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–188 .............................................. Original .................................................. April 28, 2000.

McDonnell Douglas Service Bulletin MD11–24–188 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–161 .............................................. Original .................................................. April 10, 2000.

McDonnell Douglas Service Bulletin MD11–24–161 .............................................. Revision 01 ............................................ November 6, 2000.

McDonnell Douglas Service Bulletin MD11–24–162 .............................................. Original .................................................. April 10, 2000.

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75623

Service bulletin Revision level Date

McDonnell Douglas Service Bulletin MD11–24–162 .............................................. Revision 01 ............................................ November 6, 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 Boeing Commercial Aircraft Group,

Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

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

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date

(h) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 22, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30440 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–37–AD; Amendment

39–12023; AD 2000–24–16]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes,

that requires an inspection of the one

phase remote control circuit breaker

(RCCB) in the main avionics

compartment and center accessory

compartment to determine its part

number and serial number, and

replacement of the RCCB with a certain

RCCB, if necessary. This action is

necessary to ensure that defective braze

joints of certain latch assemblies of the

RCCB are not installed on the airplane.

Defective braze joints could fail and

prevent the RCCB from tripping during

an overload condition, which could

result in a fire and smoke in certain wire

bundles that are routed to and from the

main avionics compartment or center

accessory compartment. This action is

intended to address the identified

unsafe condition.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 8,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Aircraft

Group, Long Beach Division, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). This information

may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5350;

fax (562) 627–5210.

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 McDonnell

Douglas Model MD–11 series airplanes

was published in the Federal Register

on July 27, 2000 (65 FR 46221). That

action proposed to require an inspection

of the one phase remote control circuit

breaker (RCCB) in the main avionics

compartment and center accessory

compartment to determine its part

number and serial number, and

replacement of the RCCB with a certain

RCCB, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 187 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 60 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 6 work hours

per airplane to accomplish the required

inspection, and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $21,600, or

$360 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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