Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules 13189

Model/Series STC number Docket number

Boeing 767–200 ................................................................................................................................... ST09022AC–D 2000–NM–243–AD

Boeing 747SP ...................................................................................................................................... ST09097AC–D 2000–NM–244–AD

Boeing 747–400 ................................................................................................................................... SA8843SW 2000–NM–245–AD

Airbus A340–211 .................................................................................................................................. ST0902AC–D 2000–NM–246–AD

Cost Impact

There are approximately 6 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 3

airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 4 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$720, or $240 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this proposed 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: 19 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

McDonnell Douglas: Docket 2000–NM–229–

AD.

Applicability: Model DC–9–51 and DC–9–

83 series airplanes modified by

Supplemental Type Certificate (STC)

SA8026NM, certificated in any category.

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 (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 the inability of the flight crew

to remove power from the in-flight

entertainment (IFE) system when necessary;

which, during a non-normal or emergency

situation, could result in inability to control

smoke or fumes in the airplane flight deck or

cabin; accomplish the following:

Deactivation and Removal

(a) Within 18 months after the effective

date of this AD, deactivate the IFE system

and remove the system from the airplane, in

accordance with Hollingsead International

Service Bulletin 2526–2332–001, dated July

19, 2000.

Spares

(b) As of the effective date of this AD, no

person shall install an IFE system in

accordance with STC SA8026NM on any

airplane.

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 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 Permits

(d) Special flight permits may be issued in

accordance with §§ 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

23, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–4941 Filed 3–1–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–231–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–10–30 Series

Airplanes Modified by Supplemental

Type Certificate ST00054SE

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

13190 Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

McDonnell Douglas Model DC–10–30

series airplanes modified by

supplemental type certificate (STC)

ST00054SE. This proposal would

require removal of the in-flight

entertainment (IFE) system installed by

that STC. This action is necessary to

prevent inability of the flight crew to

remove power from the IFE system

when necessary. Inability to remove

power from the IFE system during a

non-normal or emergency situation

could result in inability to control

smoke or fumes in the airplane flight

deck or cabin. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

April 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

231–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-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–231–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.

FOR FURTHER INFORMATION CONTACT:

Stephen S. Oshiro, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2793; fax (425) 227–1181.

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–231–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–231–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Federal Aviation Administration

(FAA) recently completed a review of

in-flight entertainment (IFE) systems

certified by supplemental type

certificate (STC) and installed on

transport category airplanes. The review

focused on the interface between the IFE

system and airplane electrical system,

with the objective of determining if any

unsafe conditions exist with regard to

the interface. STC’s issued between

1992 and 2000 were considered for the

review.

The type of IFE systems considered

for review were those that contain video

monitors (cathode ray tubes or liquid

crystal displays; either hanging above

the aisle or mounted on individual seat

backs or seat trays), or complex circuitry

(i.e., power supplies, electronic

distribution boxes, extensive wire

routing, relatively high power

consumption, multiple layers of circuit

protection, etc.). In addition, in-seat

power supply systems that provide

power to more than 20 percent of the

total passenger seats were also

considered for the review. The types of

IFE systems not considered for review

include systems that provide only audio

signals to each passenger seat, ordinary

in-flight telephone systems (e.g., one

telephone handset per group of seats or

bulkhead-mounted telephones), systems

that only have a video monitor on the

forward bulkhead(s) (or a projection

system) to provide passengers with

basic airplane and flight information,

and in-seat power supply systems that

provide power to less than 20 percent of

the total passenger seats.

Items considered during the review

include the following:

• Can the electrical bus(es) supplying

power to the IFE system be deenergized

when necessary without removing

power from systems that may be

required for continued safe flight and

landing?

• Can IFE system power be removed

when required without pulling IFE

system circuit breakers? [i.e., is there a

switch (dedicated to the IFE system or

a combination of loads) located in the

flight deck or cabin that can be used to

remove IFE power?]

• If the IFE system requires changes

to flight crew procedures, has the

airplane flight manual (AFM) been

properly amended?

• If the IFE system requires changes

to cabin crew procedures, have they

been properly amended?

• Does the IFE system require

periodic or special maintenance?

In all, approximately 180 IFE systems

approved by STC were reviewed by the

FAA. The review results indicate that

potential unsafe conditions exist on

some IFE systems installed on various

transport category airplanes. These

conditions can be summarized as:

• Electrical bus(es) supplying power

to the IFE system cannot be deenergized

when necessary without removing

power from systems that may be

required for continued safe flight and

landing.

• Power cannot be removed from the

IFE system when required without

pulling IFE system circuit breakers (i.e.,

there is no switch dedicated to the IFE

system or combination of systems for

the purpose of removing power).

• Installation of the IFE system has

affected crew (flight crew and/or cabin

crew) procedures, but the procedures

have not been properly revised.

FAA’s Determination

As part of its review of IFE systems,

the FAA has determined that an unsafe

condition exists on McDonnell Douglas

Model DC–10–30 series airplanes

modified by STC ST00054SE. The IFE

Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules 13191

system on these airplanes is connected

to an electrical bus that cannot be

deenergized without also removing

power from airplane systems necessary

for safe flight and landing. Additionally,

the flight crew and cabin crew

emergency procedures have not been

revised to advise the crew that they

cannot remove power from the IFE

system. This condition, if not corrected,

could result in inability to remove

power from the IFE system during a

non-normal or emergency situation, and

consequent inability to control smoke or

fumes in the airplane flight deck or

cabin.

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

require removal of the IFE system

installed by STC ST00054SE. The action

would be required to be accomplished

by a method approved by the FAA.

Subsequent to the FAA’s review of STC

ST00054SE, the STC holder informed

the FAA that the IFE system installed by

that STC has been removed from all

affected airplanes. However, the FAA

finds it necessary to propose this AD to

ensure that all operators have indeed

removed the IFE system and to prohibit

future installation of the system in other

eligible airplanes.

Calculation of Compliance Time

In developing an appropriate

compliance time for this action, the

FAA considered not only the degree of

urgency associated with addressing the

subject unsafe condition, but the

amount of time necessary to accomplish

the proposed actions, and the practical

aspect of accomplishing the proposed

actions within an interval of time that

parallels normal scheduled maintenance

for the affected operators. In

consideration of these factors, the FAA

has determined that 18 months after the

effective date of this AD represents an

appropriate interval of time allowable

wherein an acceptable level of safety

can be maintained.

Other Relevant Proposed Rulemaking

This proposed action is one of a

number of proposed AD’s on airplanes

modified by STC’s that have been

determined to be subject to similar

unsafe conditions. Other currently

proposed AD’s include the following

airplanes and STC’s:

Model/Series STC number Docket number

Boeing 757–200 ................................................................................................................................... SA1727GL 2000–NM–228–AD

McDonnell Douglas DC–9–51 and DC–9–83 ...................................................................................... SA8026NM 2000–NM–229–AD

Boeing 767–300 and 767–300ER ........................................................................................................ SA5765NM

SA5978NM

2000–NM–232–AD

Boeing 767–300 ................................................................................................................................... ST00157SE 2000–NM–233–AD

Boeing 747–100 and –200 ................................................................................................................... ST00196SE 2000–NM–234–AD

Boeing 767–200 ................................................................................................................................... SA5134NM 2000–NM–235–AD

Boeing 767–300 ................................................................................................................................... ST00118SE 2000–NM–236–AD

Boeing 737–300 ................................................................................................................................... ST00171SE 2000–NM–237–AD

Boeing 767–222ER .............................................................................................................................. SA4998NM 2000–NM–238–AD

Boeing 767–300 ................................................................................................................................... SA7019NM–D 2000–NM–239–AD

Boeing 747–100 and –200 ................................................................................................................... SA8622SW 2000–NM–240–AD

McDonnell Douglas DC–10–30 ............................................................................................................ SA8452SW 2000–NM–241–AD

Boeing 737–700 ................................................................................................................................... ST09100AC–D

ST09104AC–D

ST09105AC–D

ST09106AC–D

2000–NM–242–AD

Boeing 767–200 ................................................................................................................................... ST09022AC–D 2000–NM–243–AD

Boeing 747SP ...................................................................................................................................... ST09097AC–D 2000–NM–244–AD

Boeing 747–400 ................................................................................................................................... SA8843SW 2000–NM–245–AD

Airbus A340–211 .................................................................................................................................. ST0902AC–D 2000–NM–246–AD

Cost Impact

As stated previously, the STC holder

has informed the FAA that the subject

IFE system has been removed from all

affected airplanes. Therefore, the FAA

expects that there will be no future cost

impact on U.S. operators as a result of

the proposed rule.

However, if an airplane subject to this

AD is identified, the FAA estimates that

removal of the IFE system would take

approximately 12 work hours per

airplane, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of the proposed AD on

an affected airplane is estimated to be

$720 per airplane.

The cost impact figure discussed

above is based on information that the

subject IFE system has been removed

from all affected airplanes. The cost

impact figures discussed in most

proposed AD actions are based on

assumptions that no operator has yet

accomplished any of the proposed

requirements, and that no operator

13192 Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules

would accomplish those actions in the

future if the proposed 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

adding the following new airworthiness

directive:

McDonnell Douglas: Docket 2000–NM–231–

AD.

Applicability: Model DC–10–30 series

airplanes modified by supplemental type

certificate (STC) ST00054SE, certificated in

any category.

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 (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 the inability of flight crew to

remove power from the in-flight

entertainment (IFE) system when necessary;

which, during a non-normal or emergency

situation, could result in inability to control

smoke or fumes in the airplane flight deck or

cabin; accomplish the following:

Removal of IFE System

(a) Within 18 months after the effective

date of this AD, remove the IFE system

installed by STC ST00054SE by a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA. For a

removal method to be approved by the

Manager, Seattle ACO, as required by this

paragraph, the Manager’s approval letter

must specifically reference this AD.

Spares

(b) As of the effective date of this AD, no

person may install an IFE system by STC

ST00054SE on any airplane.

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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with §§ 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

23, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–4942 Filed 3–1–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–232–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing 767–

300 Series Airplanes Modified by

Supplemental Type Certificate

SA5765NM or SA5978NM

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 all

Boeing 767–300 series airplanes

modified by supplemental type

certificate (STC) SA5765NM or

SA5978NM. This proposal would

require removal of the in-flight

entertainment (IFE) system installed by

those STC’s. This action is necessary to

prevent the inability of the flight crew

to remove power from the IFE system

when necessary. Inability to remove

power from the IFE system during a

non-normal or emergency situation

could result in inability to control

smoke or fumes in the airplane flight

deck or cabin. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

April 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

232–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-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–232–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.

FOR FURTHER INFORMATION CONTACT:

Stephen S. Oshiro, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2793; fax (425) 227–1181.