Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75615

(1) The incorporation by reference of

McDonnell Douglas Alert Service Bulletin

MD11–25A194, Revision 06, dated January

27, 2000, is approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51.

(2) The incorporation by reference of

McDonnell Douglas Alert Service Bulletin

MD11–25A194, Revision 05, dated June 21,

1999; and McDonnell Douglas Alert Service

Bulletin MD11–24A068, Revision 01, dated

March 8, 1999, was approved previously by

the Director of the Federal Register as of

March 23, 2000 (65 FR 8034, February 17,

2000).

(3) 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

ACO, 3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(i) 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. 00–30436 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–33–AD; Amendment

39–12019; AD 2000–24–12]

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 to detect

chafing or damage of the electrical wires

leading to the terminal strips in the

center accessory compartment (CAC)

area; and corrective actions, if

necessary. This amendment also

requires revising the wire connection

stack up of certain cable terminals at the

electrical power center bays in the CAC,

and replacing certain terminal strips

with new strips and removing

applicable nameplates at electrical

power center bays. This action is

necessary to prevent arcing and

sparking damage to the power feeder

cables, terminal strips, and adjacent

structure, and consequent smoke and

fire in the CAC. 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 46211). That

action proposed to require an inspection

to detect chafing or damage of the

electrical wires leading to the terminal

strips in the center accessory

compartment (CAC) area; and corrective

actions, if necessary. That action also

proposed to require revising the wire

connection stack up of certain cable

terminals at the electrical power center

bays in the CAC, and replacing certain

terminal strips with new strips and

removing applicable nameplates at

electrical power center bays.

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 151 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 59 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately between 6

and 8 work hours per airplane

depending on the configuration of the

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately between $1,091

and $1,256 per airplane depending on

the configuration of the airplane. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

between $85,609 and $102,424, or

between $1,451 and $1,736 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

75616 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

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:

2000–24–12 McDonnell Douglas:

Amendment 39–12019. Docket 2000–

NM–33–AD.

Applicability: Model MD–11 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD11–24A097, dated

April 3, 2000; 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 arcing and sparking damage to

the power feeder cables, terminal strips, and

adjacent structure, and consequent smoke

and fire in the center accessory compartment,

accomplish the following:

Inspection

(a) Within 12 months after the effective

date of this AD, perform a one-time general

visual inspection to detect chafing or damage

of the electrical wires leading to the terminal

strips in the center accessory compartment

area, in accordance with McDonnell Douglas

Alert Service Bulletin MD11–24A097, dated

April 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.’’

Condition 1 (No Chafing or Damage)

(1) If no chafing or damage is detected, no

further action is required by this paragraph.

Condition 2 (Evidence of Chafing or Damage

on Terminal Strips)

(2) If any chafing or damage is detected on

the terminal strips, before further flight,

replace the terminal strip with a like part and

seal screw heads of replaced terminal strips,

in accordance with the service bulletin.

Condition 3 (Chafing or Damage Within

Limits)

(3) If any chafing is detected and if any

damage is detected within the limits

specified in the service bulletin, before

further flight, repair damage in accordance

with the service bulletin.

Condition 4 (Chafing or Damage Beyond

Limits)

(4) If any chafing is detected and if any

damage is detected beyond the limits

specified in the service bulletin, before

further flight, replace damaged wires with

new wires in accordance with the service

bulletin.

Revise Wire Connection of the Cable

Terminal Strips

(b) Within 12 months after the effective

date of this AD, revise the wire connection

stack up of certain cable terminals at the

electrical power center bays in the center

accessory compartment in accordance with

McDonnell Douglas Alert Service Bulletin

MD11–24A097, dated April 3, 2000.

Replacement of Terminal Strips and

Removal of Nameplate

(c) Within 12 months after the effective

date of this AD, replace the terminal strips

with new strips and remove the applicable

nameplate at electrical power center bays in

the center accessory compartment, in

accordance with McDonnell Douglas Alert

Service Bulletin MD11–24A097, dated April

3, 2000.

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, 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 3: 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 Permit

(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) The actions shall be done in accordance

with McDonnell Douglas Alert Service

Bulletin MD11–24A097, dated April 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 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 ACO, 3960 Paramount Boulevard,

Lakewood, California; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

Effective Date

(g) 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. 00–30437 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–34–AD; Amendment

39–12020; AD 2000–24–13]

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 replacing the ground

support bracket(s); and rerouting the

ground cables of the galley external

power and main external power, or

ground cables of the main external

power; as applicable. This action is

necessary to prevent arcing and heat

damage to the attachment points of the

main external and galley power