Federal Register / Vol. 66, No. 34 / Tuesday, February 20, 2001 / Proposed Rules 10849

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.

Issued in Renton, Washington, on February

12, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4056 Filed 2–16–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–190–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

McDonnell Douglas Model MD–11

series airplanes, that currently requires

a one-time inspection to detect riding,

chafing, or damage of the wire bundles

adjacent to the disconnect panel bracket

of the observer’s station. That AD also

requires repair or replacement of

damaged wires with new or serviceable

wires; installation of anti-chafing

sleeving on the wire bundles, if

necessary; and installation of a grommet

along the entire upper aft edge of the

disconnect panel bracket. This action

would require an identical one-time

inspection, follow-on actions, and

similar corrective actions, if necessary;

but the proposed installation of antichafing sleeving would be required for

all airplanes. This action is necessary to

detect riding or chafing of the wire

bundles adjacent to the disconnect

panel bracket assembly, which could

result in a fire in the wire bundles and

smoke in the cockpit. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

April 6, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

190–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 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-nprmcomment@faa.gov.

Comments sent via fax or the Internet

must contain ‘‘Docket No. 2000–NM–

190–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

the proposed rule 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 FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

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;

telephone (562) 627–5350; fax (562)

627–5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this action may be changed in light

of the comments received.

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 proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–190–AD.’’

The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–190–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On May 5, 1997, the FAA issued AD

97–10–12, amendment 39–10024 (62 FR

25839, May 12, 1997), applicable to

certain McDonnell Douglas Model MD–

11 series airplanes, to require a one-time

inspection to detect riding, chafing, or

damage of the wire bundles adjacent to

the disconnect panel bracket of the

observer’s station. That AD also requires

repair or replacement of damaged wires

with new or serviceable wires;

installation of anti-chafing sleeving on

the wire bundles, if necessary; and

installation of a grommet along the

entire upper aft edge of the disconnect

panel bracket. That action was

prompted by a report indicating that the

circuit breakers tripped on a Model

MD–11 series airplane due to inflight

arcing behind the avionics circuit

breaker panel as a result of chafing of

the wire bundles adjacent to the

disconnect panel bracket assembly. The

requirements of that AD are intended to

detect and correct such chafing, which

could result in a fire in the wire bundles

and smoke in the cockpit.

The incident that prompted AD 97–

10–12 is not considered to be related to

an accident that occurred off the coast

of Nova Scotia involving a McDonnell

10850 Federal Register / Vol. 66, No. 34 / Tuesday, February 20, 2001 / Proposed Rules

Douglas Model MD–11 series airplane.

The cause of that accident is still under

investigation.

Other Related Rulemaking

The FAA, in conjunction with Boeing

and operators of Model MD–11 series

airplanes, is continuing to review all

aspects of the service history of those

airplanes to identify potential unsafe

conditions and to take appropriate

corrective actions. This proposed AD is

one of a series of actions identified

during that process. The process is

continuing and the FAA may consider

additional rulemaking actions as further

results of the review become available.

Actions Since Issuance of Previous Rule

Since the issuance of AD 97–10–12,

the FAA has determined that

installation of anti-chafing sleeving on

all wire bundles in the subject area,

regardless if the wire bundle appears to

riding or chafing, is necessary. Riding or

chafing of the wire bundles adjacent to

the disconnect panel bracket assembly,

if not detected and corrected, could

result in a fire in the wire bundles and

smoke in the cockpit.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

McDonnell Douglas Alert Service

Bulletin MD11–24A111, Revision 01,

dated July 27, 2000. The service bulletin

describes, for certain airplanes,

procedures for a one-time general visual

inspection to detect riding, chafing, or

damage of the wire bundles adjacent to

the disconnect panel bracket. The

service bulletin also describes, for

certain airplanes, procedures for repair

of damaged wires; installation of antichafing sleeving on the wire bundles;

and installation of a protective grommet

along the edge of the disconnect panel

bracket. Accomplishment of these

actions specified in the service bulletin

is intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 97–10–12 to require, for

certain airplanes, accomplishment of

the additional actions specified in the

service bulletin described previously.

Differences Between the Proposed AD

and Service Bulletin

Operators should note that the

Revision Transmittal Sheet of the

service bulletin incorrectly reads

‘‘Additional work is required for

airplanes previously modified by

Service Bulletin MD11–24–111.

Additional work requirement is to be

accomplished as outlined under Group

2. An additional 0.8 man-hour is

required.’’ The FAA has consulted with

the airplane manufacturer and

determined that additional work is NOT

required for Group 2 airplanes. The term

‘‘modified,’’ as described above and in

Group 1 and Group 2 listing in the

effectivity of the service bulletin, refers

to installation of anti-chafing sleeving

on the wire bundles. Therefore, the

proposed AD affects McDonnell Douglas

Model MD–11 series airplanes, as listed

in McDonnell Douglas Alert Service

Bulletin MD11–24A111, Revision 01,

dated July 27, 2000; certificated in any

category; except those airplanes on

which anti-chafing sleeving was

installed on the wire bundles per

paragraph (a)(1) or (a)(2) of AD 97–10–

12.

Cost Impact

There are approximately 195 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 60 airplanes of U.S.

registry would be affected by this

proposed AD.

The inspection and installation that

are proposed in this AD action would

take approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. The

cost of required parts would be nominal.

Based on these figures, the cost impact

of the proposed inspection and

installation of this AD on U.S. operators

is estimated to $7,200, or $120 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the current or proposed 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 proposed herein

would not have a substantial direct

effect on the States, on the relationship

between the national Government and

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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

removing amendment 39–10024 (62 FR

25839, May 12, 1997), and by adding a

new airworthiness directive (AD), to

read as follows:

McDonnell Douglas: Docket 2000–NM–190–

AD. Supersedes AD 97–10–12,

Amendment 39–10024.

Applicability: Model MD–11 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD11–24A111,

Revision 01, dated July 27, 2000; certificated

in any category; except those airplanes on

which anti-chafing sleeving was installed on

the wire bundles per paragraph (a)(1) or (a)(2)

of AD 97–10–12.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

Federal Register / Vol. 66, No. 34 / Tuesday, February 20, 2001 / Proposed Rules 10851

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: Where there are differences

between the referenced service bulletin and

the AD, the AD prevails.

To detect riding or chafing of the wire

bundles adjacent to the disconnect panel

bracket assembly, which could result in a fire

in the wire bundles and smoke in the

cockpit, accomplish the following:

General Visual Inspection and Corrective

Actions, If Necessary

(a) Within 6 months after the effective date

of this AD, perform a general visual

inspection to detect riding, chafing, or

damage of the wire bundles adjacent to the

disconnect panel bracket, per paragraph

3.B.2. of the Accomplishment Instructions of

McDonnell Douglas Alert Service Bulletin

MD11–24A111, Revision 01, dated July 27,

2000.

Note 3: 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.’’

(1) If any riding or chafing is found, and

if any damage is found: Before further flight,

repair damaged wires; install anti-chafing

sleeving on the wire bundles; and install a

protective grommet along the entire upper aft

edge of the disconnect panel bracket; per

Condition 1 of paragraph 3.B.2 of the

Accomplishment Instructions of the service

bulletin.

(2) If any riding or chafing is found, but no

damage is found: Before further flight, install

anti-chafing sleeving on the wire bundles,

and install a protective grommet along the

entire upper aft edge of the disconnect panel

bracket, per Condition 2 of paragraph 3.B.2.

of the Accomplishment Instructions of the

service bulletin.

(3) If no riding, chafing, or damage is

found: Before further flight, install antichafing sleeving on the wire bundles, and

install a protective grommet along the entire

upper aft edge of the disconnect panel

bracket, per Condition 3 of paragraph 3.B.2.

of the Accomplishment Instruction of the

service bulletin.

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 4: 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

(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.

Issued in Renton, Washington, on February

12, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4055 Filed 2–16–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–189–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain McDonnell Douglas Model MD–

11 series airplanes. This proposal would

require an inspection of the upper

avionics circuit breaker panel at the

main observer’s station to detect damage

of the wires and to verify the correct

routing of the wire bundles; corrective

actions, if necessary; and installation of

a new clamp, spacer, and sta-straps.

This action is necessary to prevent

chafing in the upper avionics circuit

breaker panel of the main observer’s

station, which could result in arcing and

consequent smoke and/or fire in the

cockpit. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

April 6, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

189–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 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-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–189–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

the proposed rule 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 FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Technical Specialist,

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this action may be changed in light

of the comments received.

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 proposed rule. All comments

submitted will be available, both before