75618 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

insulation blankets outboard and aft of the

receptacle area, and adjacent power cables,

which could result in smoke and fire in the

forward cargo compartment, accomplish the

following:

Replacement and Reroute

(a) Within 12 months after the effective

date of this AD, accomplish the actions

specified in paragraph (a)(1) or (a)(2) of this

AD, as applicable, in accordance with

McDonnell Douglas Alert Service Bulletin

MD11–24A138, dated April 3, 2000.

(1) For Group 1 airplanes listed in the

service bulletin: Replace the ground support

brackets with new brackets and reroute the

ground cables of the galley external power

and main external power.

(2) For Group 2 airplanes listed in the

service bulletin: Replace the ground support

bracket and reroute the ground cables of the

main external power.

Alternative Methods of Compliance

(b) 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 2: 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

(c) 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

(d) The actions shall be done in accordance

with McDonnell Douglas Alert Service

Bulletin MD11–24A138, 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 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

(e) 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. 00–30438 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–35–AD; Amendment

39–12021; AD 2000–24–14]

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

electrical wires routed above the door

actuation cables for minimum .50-inch

clearance with the door in the open and

closed position, damage due to chafing

or electrical arcing, or damaged door

actuation cables; and corrective actions,

if necessary. This action is necessary to

prevent damaged electrical wires or

damaged door actuation cables due to

chafing by the cables during operation

of the forward passenger door, which

could result in electrical arcing and

consequent smoke in the area above the

forward passenger door. 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 46216). That

action proposed to require an inspection

of the electrical wires routed above the

door actuation cables for minimum .50-

inch clearance with the door in the open

and closed position, damage due to

chafing or electrical arcing, or damaged

door actuation cables; and corrective

actions, 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 64 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 2 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 $7,680, or

$120 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

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75619

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:

2000–24–14 McDonnell Douglas:

Amendment 39–12021. Docket 2000–NM–

35–AD.

Applicability: Model MD–11 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD11–24A182, 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 (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 damaged electrical wires or

damaged door actuation cables due to chafing

by the cables during operation of the forward

passenger door, which could result in

electrical arcing and consequent smoke in the

area above the forward passenger door,

accomplish the following:

Inspection

(a) Except as provided by paragarph (b) of

this AD, within 6 months after the effective

date of this AD, perform a one-time general

visual inspection of the electrical wires

routed above the door actuation cables for

minimum .50-inch clearance with the door in

the open and closed position, damage due to

chafing or electrical arcing, or damaged door

actuation cables, in accordance with

McDonnell Douglas Alert Service Bulletin

MD11–24A182, 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 (Minimum Clearance and No

Chafed Electrical Wiring or Damaged Door

Actuation Cables)

(1) If minimum .50-inch clearance exists

between the electrical wires and door

actuation cables with the door in the open

and closed positions, and if no chafed

electrical wiring or damaged door actuation

cable is detected, no further action is

required by this AD.

Condition 2 (Less Than Minimum Clearance,

No Chafed Electrical Wiring or Damaged

Door Actuation Cables)

(2) If less than .50-inch clearance exists

between the electrical wires and door

actuation cables with the door in the open

and closed positions, and if no chafed

electrical wiring or damaged door actuation

cable is detected, before further flight, loosen

wire clamps as necessary, reposition

electrical wires to provide minimum

clearance, and tighten wire clamps, in

accordance with the service bulletin.

Condition 3 (Less Than Minimum Clearance,

Chafed Electrical Wiring or Damaged Door

Actuation Cables)

(3) If less than .50-inch clearance exists

between the electrical wires and door

actuation cables with the door in the open

and closed positions, and if any chafed

electrical wiring or damaged door actuation

cable is detected, before further flight,

replace damaged electrical wires with new

wires or repair damaged wires, loosen wire

clamps as necessary, reposition electrical

wires to provide minimum clearance, tighten

wire clamps, and replace damaged door

actuation cables with new cables, in

accordance with the service bulletin.

Exception to Inspection Required in

Paragraph (a) of This AD

(b) For Model MD–11 series airplanes, the

inspection required by paragraph (a) of this

AD is only applicable to functioning doors.

For Model MD–11F series airplanes or Model

MD–11 series airplanes converted to a

freighter configuration, equipped with one or

more disabled non-functioning doors that do

not have door acuating cables, the inspection

is NOT required for those disabled doors.

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, 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

(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 McDonnell Douglas Alert Service

Bulletin MD11–24A182, 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 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

(f) This amendment becomes effective on

January 8, 2001.

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.