Federal Register / Vol. 67, No. 96 / Friday, May 17, 2002 / Proposed Rules 35057

§ 107.885 [Amended]

4. Amend 107.885 by removing

paragraph (b) and removing the

paragraph designation ‘‘(a)’’.

Dated: May 13, 2002.

Hector V. Barreto,

Administrator.

[FR Doc. 02–12466 Filed 5–16–02; 8:45 am]

BILLING CODE 8025–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002–NM–12–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–300, –400, –500, –600, –700,

–700C, –800, –900; 747–400; 757; 767;

and 777 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 Boeing Model 737–300, –400,

–500, –600, –700, –700C, –800, –900;

747–400; 757; 767; and 777 series

airplanes. This proposal would require

modifying the static inverter by

relocating resistor R170 of the static

inverter bridge assembly. This action is

necessary to prevent a standby static

inverter from overheating, which could

result in smoke in the flight deck and

cabin and loss of the electrical standby

power system. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

July 1, 2002.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2002–NM–

12–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. 2002–NM–12–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 Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Binh V. Tran, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2890; 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 2002–NM–12–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

2002–NM–12–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports that

static inverters had overheated on

several Boeing airplanes. In one

incident, smoke entered the flight deck

and the cabin, and the captain declared

an emergency. The smoke was traced to

the static inverter unit, a critical piece

of equipment that converts battery

power during a standby condition. The

type of static inverter involved in this

incident is used on the affected Boeing

airplane models. Analysis conducted by

the manufacturer indicates that the

proximity of resistor R170 to capacitors

C50 and C51 in the static inverter could

lead to overheating and consequent

damage or failure of those capacitors.

The results of the analysis suggest that

the combination of obstructed

convection cooling and localized heat

dissipation from resistor R170 resulted

in sufficient energy to damage the

adjacent capacitors. These conditions, if

not corrected, could result in smoke in

the flight deck and cabin and loss of the

electrical standby power system.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Letters 737–SL–24–165,

747–SL–24–058, 757–SL–24–069, 767–

SL–24–047, and 777–SL–24–028; dated

October 3, 2000. The service letters

describe procedures for modifying the

static inverter by relocating resistor

R170 of the static inverter bridge

assembly and reidentifying the static

inverter to indicate the new

modification level. Accomplishment of

the actions specified in the service

letters is intended to adequately address

the identified unsafe condition.

The service letters refer to Avionic

Instruments Inc. Service Bulletin 1–

002–0102–1000–24–24, dated July 19,

1999, as an additional source of service

information for relocating R170 and

reidentifying the static inverter.

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 letters.

35058 Federal Register / Vol. 67, No. 96 / Friday, May 17, 2002 / Proposed Rules

Cost Impact

There are approximately 3,832

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

1,882 airplanes of U.S. registry would be

affected by this proposed AD.

The cost impact discussed in ADs is

based on assumptions that no operator

has yet accomplished any of the

proposed requirements, and that no

operator would accomplish those

actions in the future if the proposed AD

were not adopted. However, the FAA

has been advised that manufacturer

warranty remedies are available for the

cost of modified replacement parts and

labor associated with accomplishing the

actions specified by this proposed AD.

Therefore, the economic cost impact of

this proposed AD on U.S. operators may

be minimal. 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 2002NM–12AD.

Applicability: The following airplanes,

certificated in any category:

TABLE 1.—APPLICABILITY

Model/series

Equipped with Avionic Instruments Inc. static inverters having

any of the following part numbers

(P/Ns)—

Which correspond to

Boeing P/Ns—

737–300, –400, –500, –600, –700, –800, –900 ......................... 1–002–0102–0265 ..................................................................... S282T004–5

747–400 ...................................................................................... 1–002–0102–0714 ..................................................................... S282T004–7

757 .............................................................................................. 1–111–0102–0714 ..................................................................... S282T004–8

767 .............................................................................................. 1–002–0102–1000 ..................................................................... S282T004–10

777.

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 a standby static inverter from

overheating, which could result in smoke in

the flight deck and cabin and loss of the

electrical standby power system, accomplish

the following:

Modification

(a) Within 18 months after the effective

date of this AD: Modify the static inverter by

relocating resistor R170 of the static inverter

bridge assembly and reidentifying the static

inverter to indicate the new modification

level, in accordance with Boeing Service

Letters 737–SL–24–165, 747–SL–24–058,

757–SL–24–069, 767–SL–24–047, and 777–

SL–24–028; dated October 3, 2000.

Note 2: The Boeing service letters refer to

Avionic Instruments Inc. Service Bulletin 1–

002–0102–1000–24–24, dated July 19, 1999,

as an additional source of service information

for the modification required by paragraph

(a) of this AD.

Spare Parts

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

person may install, on any airplane, a static

inverter having a part number listed in the

applicability section of this AD, unless the

static inverter has been modified in

accordance with the requirements of 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, Seattle

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, Seattle ACO.

Note 3: 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 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 May 10,

2002.

Ali Bahrami,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 02–12323 Filed 5–16–02; 8:45 am]

BILLING CODE 4910–13–P