Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules 13219

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:

Boeing: Docket 2000–NM–244–AD.

Applicability: Model 747SP series

airplanes modified by supplemental type

certificate (STC) ST09097AC–D, 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 ensure that the flight crew is able to

remove electrical power from the passenger

entertainment system (PES) when necessary

and is advised of appropriate procedures for

such action, accomplish the following:

Modification and Airplane Flight Manual

Revision

(a) Within 18 months after the effective

date of this AD, do paragraphs (a)(1) and

(a)(2) of this AD.

(1) Modify the PES by installing a power

switch and a load-shed circuit breaker as

well as associated relays and wiring, in

accordance with Raytheon Service Bulletin

747(SP)VIP–24–1, dated September 22, 2000.

(2) Revise the Normal Procedures and

Emergency Procedures sections of the FAAapproved Airplane Flight Manual (AFM) to

advise the flight crew on using the power

switch installed by paragraph (a)(1) to

remove power from the PES in the event of

an emergency related to smoke or fire, in

accordance with Raytheon Flight Manual

Supplement 747SP–21, dated October 16,

2000, which is supplied with Raytheon

Service Bulletin 747(SP)VIP–24–1, dated

September 22, 2000.

Spares

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

person shall install a PES in accordance with

STC ST09097AC–D, on any airplane, unless

it is modified and the AFM is revised in

accordance with this AD.

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, Fort Worth

Airplane 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, Fort Worth ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth 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. 01–4951 Filed 3–1–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–245–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

Modified by Supplemental Type

Certificate SA8843SW

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 Model 747–400 series airplanes

modified by supplemental type

certificate SA8843SW. This proposal

would require modifying the passenger

entertainment system (PES) installed by

that STC and revising the Airplane

Flight Manual. This action is necessary

to ensure that the flight crew is able to

remove electrical power from the PES

when necessary and is advised of

appropriate procedures for such action.

Inability to remove power from the PES

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–

245–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–245–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

Raytheon Systems Company,

Intelligence Information and Aircraft

Integration Systems, 7500 Maehre Road,

13220 Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules

Waco, Texas 76705. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Fort Worth Airplane

Certification Office, 2601 Meacham

Blvd., Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT:

Ingrid Knox, Aerospace Engineer, FAA,

Fort Worth Airplane Certification

Office, ASW–150, 2601 Meacham Blvd.,

Fort Worth, Texas 76137–4298;

telephone (817) 222–5139; fax (817)

222–5960.

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–245–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–245–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 Boeing Model 747–

400 series airplanes modified by STC

SA8843SW. Currently, multiple circuit

breakers in the flight and avionics

compartments control power to various

components of the passenger

entertainment system (PES) installed by

that STC. To remove power from the

PES in the event of an emergency, the

flight crew must locate and open each

of the subject circuit breakers. This

condition, if not corrected, could result

in failure to remove power from the

entire PES during a non-normal or

emergency situation, and consequent

inability to control smoke or fumes in

the airplane flight deck or cabin.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Service Bulletin 747(400)VIP–

24–1, dated September 22, 2000, which

describes procedures for modifying the

PES by installing load shed relays and

cable assemblies. Installation of these

relays and cable assemblies will allow

power to all components of the PES

system to be controlled by existing

‘‘UTILITY BUS ON/OFF’’ power

switches in the cockpit.

The FAA also has reviewed and

approved Raytheon Flight Manual

Supplement 747–430, dated October 17,

2000. That Flight Manual Supplement

includes revisions to the Non-Normal

Procedures section of the FAA-approved

AFM to advise the flight crew that the

‘‘UTILITY BUS ON/OFF’’ power

switches control power to the PES and

Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules 13221

should be switched ‘‘off’’ in the event of

an emergency related to smoke or fire.

Accomplishment of the actions

specified in the service bulletin and

Flight Manual Supplement 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

require accomplishment of the actions

specified in the service bulletin and

Flight Manual Supplement described

previously, except as discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators also should note that the

service bulletin specifies that the

actions therein should be accomplished

at the next maintenance opportunity,

but not later than 12 months after

receipt of the service bulletin. 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, the availability of

necessary parts, 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

all 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

McDonnell Douglas DC–10–30 ............................................................................................................ ST00054SE 2000–NM–231–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 767–200 ................................................................................................................................... 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

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

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. The

single airplane included in the

applicability of this rule currently is

operated by a non-U.S. operator under

foreign registry; therefore, it is not

directly affected by this AD action.

However, the FAA considers that this

rule is necessary to ensure that the

unsafe condition is addressed in the

event that the subject airplane is

imported and placed on the U.S.

Register in the future.

Should the affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 80 work hours to

accomplish the proposed modification,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $94,574 per airplane.

Based on these figures, the cost impact

of the proposed modification would be

$99,374.

Should the affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 1 work hour to

accomplish the proposed manual

revision, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of the proposed manual

revision would be $60.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

13222 Federal Register / Vol. 66, No. 42 / Friday, March 2, 2001 / Proposed Rules

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: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 2000–NM–245–AD.

Applicability: Model 747–400 series

airplanes modified by supplemental type

certificate (STC) SA8843SW, 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 ensure that the flight crew is able to

remove electrical power from the entire

passenger entertainment system (PES) when

necessary and is advised of appropriate

procedures for such action, accomplish the

following:

Modification and Airplane Flight Manual

Revision

(a) Within 18 months after the effective

date of this AD, do paragraphs (a)(1) and

(a)(2) of this AD.

(1) Modify the PES to install load shed

relays and associated cable assemblies for the

PES, in accordance with Raytheon Service

Bulletin 747(400)VIP–24–1, dated September

22, 2000.

(2) Revise the Non-Normal Procedures

section of the FAA-approved Airplane Flight

Manual (AFM) to advise the flight crew on

using the ‘‘UTILITY BUS ON/OFF’’ power

switches to control power to the PES, in

accordance with Raytheon Flight Manual

Supplement 747–430, dated October 17,

2000.

Spares

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

person shall install a PES system in

accordance with STC SA8843SW on any

airplane, unless it is modified and the AFM

is revised in accordance with this AD.

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, Fort Worth

Airplane 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, Fort Worth ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth 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. 01–4952 Filed 3–1–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–246–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A340–211 Series Airplanes Modified by

Supplemental Type Certificate

ST09092AC–D

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

Airbus Model A340–211 series airplanes

modified by supplemental type

certificate ST09092AC–D. This proposal

would require modifying the passenger

entertainment system (PES) and revising

the Flight Crew Operating Manual. This

action is necessary to ensure that the

flight crew is able to remove electrical

power from the entire PES when

necessary and is advised of appropriate

procedures for such action. Inability to

remove power from the PES 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 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

246–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–246–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the